U.S. patent application number 15/647132 was filed with the patent office on 2018-01-18 for system, methods, and apparatus for air flow handling in an aircraft monument.
The applicant listed for this patent is B/E Aerospace, Inc.. Invention is credited to Donna Charlene Brownlie, Peter John Leslie Burd, Allan Coombs, Merv Davidson, Neil R. Elshaw, Sam Foster, Venkata Prasanth Suman Neti, Elizabeth M. Payne.
Application Number | 20180016012 15/647132 |
Document ID | / |
Family ID | 60941668 |
Filed Date | 2018-01-18 |
United States Patent
Application |
20180016012 |
Kind Code |
A1 |
Burd; Peter John Leslie ; et
al. |
January 18, 2018 |
System, Methods, and Apparatus for Air Flow Handling in an Aircraft
Monument
Abstract
In an illustrative embodiment, an aircraft galley ducting
assembly provides airflow to at least one compartment of an
aircraft galley monument. The ducting assembly may include a supply
air duct that provides a supply airflow path to a compartment that
includes an inlet port mounted to a compartment surface. A return
air duct may provide an exit airflow path for return air that has
circulated throughout the compartment and includes an outlet port
mounted to the compartment surface. An airflow adjustment apparatus
with an airflow adjustment surface is positioned within the supply
airflow path of the supply air duct or the exit airflow path of the
return air duct to cause a modification of airflow properties for
air passing across or through the airflow adjustment surface.
Inventors: |
Burd; Peter John Leslie;
(Carmarthenshire, GB) ; Elshaw; Neil R.; (Gosport,
GB) ; Foster; Sam; (Milton Keynes, GB) ; Neti;
Venkata Prasanth Suman; (Buckinghamshire, GB) ;
Coombs; Allan; (Dorset, GB) ; Brownlie; Donna
Charlene; (Northamptonshire, GB) ; Davidson;
Merv; (Wellington, FL) ; Payne; Elizabeth M.;
(Rowesham, GB) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
B/E Aerospace, Inc. |
Wellington |
FL |
US |
|
|
Family ID: |
60941668 |
Appl. No.: |
15/647132 |
Filed: |
July 11, 2017 |
Related U.S. Patent Documents
|
|
|
|
|
|
Application
Number |
Filing Date |
Patent Number |
|
|
62361460 |
Jul 12, 2016 |
|
|
|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F25D 23/10 20130101;
F25D 17/045 20130101; F25D 15/00 20130101; F25D 17/06 20130101;
B64D 9/003 20130101; Y10T 292/1083 20150401; Y10T 403/75 20150115;
Y10T 292/1043 20150401; B21D 53/92 20130101; F25B 2500/12 20130101;
F25D 2500/02 20130101; Y10T 292/106 20150401; B64D 2013/0629
20130101; F16B 5/0225 20130101; B64F 5/00 20130101; F25D 2317/063
20130101; Y10S 292/15 20130101; Y10T 292/1075 20150401; B64D 13/06
20130101; Y02T 50/40 20130101; F25D 11/003 20130101; F16B 5/0088
20130101; B64D 11/04 20130101 |
International
Class: |
B64D 11/04 20060101
B64D011/04; B64D 13/08 20060101 B64D013/08; B64D 13/06 20060101
B64D013/06 |
Claims
1. A ducting assembly for providing airflow to at least one
compartment of an aircraft galley monument, the ducting assembly
comprising: a supply air duct configured to provide a supply
airflow path from an external air system to a first compartment of
the at least one compartment, the supply air duct including an
inlet port mounted to a surface of the compartment to provide an
inlet path for air flowing from the supply air duct to the
compartment; a return air duct configured to provide an exit
airflow path to the external air system for return air that has
circulated throughout the compartment, the return air duct
including an outlet port mounted to a surface of the compartment to
provide an outlet path for the return air from the compartment to
the return air duct; and an airflow adjustment apparatus including
an airflow adjustment surface disposed within at least one of the
supply airflow path of the supply air duct and the exit airflow
path of the return air duct, the airflow adjustment surface
configured to cause a modification of airflow properties for air
flowing across or through the airflow adjustment surface.
2. The ducting assembly of claim 1, wherein the airflow properties
include at least one of pressure, velocity, direction, and sound
frequency.
3. The ducting assembly of claim 1, wherein the airflow adjustment
surface includes a plurality of apertures arranged in predetermined
patterns across a length and width of the airflow adjustment
surface such that the air flowing through supply air duct or the
return air duct flows through the plurality of apertures.
4. The ducting assembly of claim 3, wherein the plurality of
apertures includes a first set of apertures having a first diameter
and a second set of apertures having a second diameter that is
larger than the first diameter.
5. The ducting assembly of claim 4, wherein the air flowing through
the first set of apertures is configured to produce a first audible
tone a first frequency, and the air flowing through the second set
of apertures is configured to produce a second audible tone at a
second frequency such that a mutual frequency cancellation between
the first audible tone and the second audible tone is configured to
prevent a prominent audible tone at a single frequency.
6. The ducting assembly of claim 1, wherein the airflow adjustment
apparatus includes a mounting surface disposed around a periphery
of the air flow adjustment surface and substantially parallel to
the airflow adjustment surface, wherein the mounting surface is
configured to provide one or more locations for mounting the
airflow adjustment apparatus to at least one air duct wall.
7. The ducting assembly of claim 1, wherein the airflow adjustment
surface is positioned substantially perpendicular to a direction of
airflow through the supply air duct or the return air duct.
8. The ducting assembly of claim 1, wherein a shape of the airflow
adjustment apparatus corresponds to a shape of an interior of the
supply air duct or the return air duct such the airflow adjustment
apparatus fits snugly within an interior of the supply air duct or
the return air duct.
9. The ducting assembly of claim 1, wherein the airflow adjustment
apparatus includes a mounting surface positioned substantially
perpendicular to the airflow adjustment surface.
10. The ducting assembly of claim 9, wherein a wall of the supply
air duct or the return air duct includes a slot disposed within the
wall, wherein the airflow adjustment apparatus is configured to be
inserted through the wall into an interior of the supply air duct
or the return air duct.
11. The ducting assembly of claim 10, wherein a width of the slot
within the wall of the supply air duct or the return air duct
corresponds to a greatest width of the airflow adjustment
apparatus.
12. The ducting assembly of claim 10, wherein the mounting surface
is configured to be mounted to an outer surface of the wall at one
or more mounting locations when the airflow adjustment apparatus is
inserted into the slot.
13. A compartment disposed within an aircraft galley monument, the
aircraft galley compartment comprising: an enclosure configured to
house an equipment item, the enclosure comprising a rear surface,
an upper wall, and opposing side walls, wherein at least one of the
rear surface, upper wall, or opposing side walls includes one or
more air duct connections; and a ducting assembly comprising a
supply air duct configured to provide a supply airflow path from an
external air system to the enclosure, the supply air duct including
an inlet port mounted to a surface of the enclosure to provide an
inlet path for air flowing from the supply air duct to the
enclosure, a return air duct configured to provide an exit airflow
path to the external air system for return air that has circulated
throughout the enclosure, the return air duct including an outlet
port mounted to a surface of the enclosure to provide an outlet
path for the return air from the enclosure to the return air duct,
and an airflow adjustment apparatus including an airflow adjustment
surface disposed within at least one of the supply airflow path of
the supply air duct and the exit airflow path of the return air
duct, the airflow adjustment surface configured to cause a
modification of airflow properties for air passing across or
through the airflow adjustment surface.
14. The compartment of claim 13, wherein the airflow adjustment
surface includes a plurality of apertures arranged in predetermined
patterns across a length and width of the airflow adjustment
surface such that the air flowing through the supply air duct or
the return air duct flows through the plurality of apertures.
15. The compartment of claim 14, wherein the plurality of apertures
includes a first set of apertures having a first diameter and a
second set of apertures having a second diameter that is larger
than the first diameter.
16. The compartment of claim 15, wherein the air flowing through
the first set of apertures is configured to produce a first audible
tone a first frequency, and the air flowing through the second set
of apertures is configured to produce a second audible tone at a
second frequency such that a mutual frequency cancellation between
the first audible tone and the second audible tone is configured to
prevent a prominent audible tone at a single frequency.
17. The compartment of claim 13, wherein the airflow adjustment
apparatus includes a mounting surface positioned substantially
perpendicular to the airflow adjustment surface.
18. The compartment of claim 17, wherein a wall of the supply air
duct or the return air duct includes a slot disposed across a width
of the wall, wherein the airflow adjustment apparatus is configured
to be inserted through the wall into an interior of the supply air
duct or the return air duct.
19. The compartment of claim 18, wherein a width of the slot within
the wall of the supply air duct or the return air duct corresponds
to a greatest width of the airflow adjustment apparatus.
20. The compartment of claim 18, wherein the mounting surface is
configured to be mounted to an outer surface of the wall at one or
more mounting locations when the airflow adjustment apparatus is
inserted into the slot.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application claims priority to U.S. Provisional Patent
Application Ser. No. 62/361,460, entitled "Aircraft Galley Monument
Systems, Apparatus and Methods for Use Thereof," filed Jul. 12,
2016. This application incorporates by reference, in its entirety,
the following prior patent application directed to ducting for
aircraft galleys: U.S. patent application Ser. No. 14/467,583,
entitled "Universal Modular Ducting for Chilled Aircraft Galleys,"
filed Aug. 25, 2014. This application also incorporates by
reference, in its entirety, the following prior patent application
direct to noise reduction in galley air systems: U.S. patent
application Ser. No. 13/940,012, entitled "Noise-Reducing Air Inlet
Grille for an Appliance," filed Jul. 11, 2013. All above identified
applications are hereby incorporated by reference in their
entireties.
BACKGROUND
[0002] The present disclosure relates to air flow management
systems for commercial aircraft. In-flight catering services
typically incorporate self-contained refrigeration units that are
cooled to prevent spoilage of food prior to distribution to
passengers, and to keep beverages at desired serving temperatures,
as well as separate ovens for heating food in the preparation of
hot meals to be served aboard aircraft. Currently space must be
allocated for each of the heating and cooling devices separately,
either in the same galley or in different galleys as well as for
the pathways for routing and directing air flow into and out of
galley monuments equipped with catering services that require
temperature control.
[0003] A modular aircraft galley monument may utilize a variety of
air flow elements for providing heating and cooling requirements
into and out of the galley monument. As the air flow elements often
involve circulation of air at a variety of temperatures, a number
of components may be used to affect such circulation. Components
can include ductwork, seals, plenums, filters, restrictors, and
various proportioning devices for adjusting or directing air
flow.
[0004] An aircraft galley monument may include a chilled air
distribution system for cooling and maintaining the perishable
contents of trolleys and other service units. When attempting to
evenly cool multiple cart bays, systems often use a continuous box
duct that feeds individual cart locations. However, this layout
creates difficulties in balancing airflow volumes and pressure
drops at individual air supply outlets, which may severely limit
the efficiency of the cooling system. The severity of the
difficulties increases relative to the number of compartments
needed to be chilled.
SUMMARY OF ILLUSTRATIVE EMBODIMENTS
[0005] The forgoing general description of the illustrative
implementations and the following detailed description thereof are
merely exemplary aspects of the teachings of this disclosure, and
are not restrictive.
[0006] In certain embodiments, an aircraft galley ducting assembly
may provide airflow to at least one aircraft galley compartment.
The ducting assembly may include a supply air duct that provides a
supply airflow path from an external air system to an aircraft
galley compartment that includes an inlet port mounted to a galley
compartment surface to provide an inlet path for air flowing into
the galley compartment. A return air duct may provide an exit
airflow path to the external air system for return air that has
circulated throughout the galley compartment and includes an outlet
port mounted to the galley compartment surface to provide an outlet
path for the return air to the return air duct. An airflow
adjustment apparatus with an airflow adjustment surface may be
positioned within the supply airflow path of the supply air duct or
the exit airflow path of the return air duct to cause a
modification of airflow properties for air passing across or
through the airflow adjustment surface.
BRIEF DESCRIPTION OF THE DRAWINGS
[0007] The accompanying drawings, which are incorporated in and
constitute a part of the specification, illustrate one or more
embodiments and, together with the description, explain these
embodiments. The accompanying drawings have not necessarily been
drawn to scale. Any values dimensions illustrated in the
accompanying graphs and figures are for illustration purposes only
and may or may not represent actual or preferred values or
dimensions. Where applicable, some or all features may not be
illustrated to assist in the description of underlying features. In
the drawings:
[0008] FIGS. 1A-1B illustrate perspective views of a galley
compartment with connections to an air conditioning unit (ACU);
[0009] FIGS. 2A-2E illustrate various views of example air
distribution duct housings for use with various galley monument
designs described herein including connections to an air handling
system;
[0010] FIGS. 3A-3C illustrate various views of a sealing collar for
sealing air flow between an ACU outlet and a duct inlet of a galley
monument;
[0011] FIGS. 4A-4C illustrate various views of a galley extraction
system;
[0012] FIG. 5 illustrates a perspective view of an air duct
extension;
[0013] FIG. 6 illustrates a perspective view of an air flow
device;
[0014] FIG. 7 illustrates an air extraction system;
[0015] FIGS. 8A-8C illustrate front and rear views of restrictors
for an air duct;
[0016] FIGS. 9A-9C illustrate various views of a restrictor for
restricting air flow within an air duct;
[0017] FIGS. 10A-10C illustrate various views of a gasper
assembly;
[0018] FIGS. 11A-11B illustrate various views of an air deflection
system for altering air flow within an air duct;
[0019] FIG. 12 illustrates an airflow adjuster for positioning
within an air duct of a galley monument;
[0020] FIG. 13 illustrates a pressure measurement system for
monitoring air flow within an air duct of a galley monument
system;
[0021] FIG. 14 illustrates a plenum for mounting above a
compartment of various galley monument designs described herein
including connections to an air handling system;
[0022] FIG. 15 illustrates a perspective view of a quick-change air
filter grille; and
[0023] FIGS. 16A-16D represent perspective views of an expansion
plenum.
DETAILED DESCRIPTION OF ILLUSTRATIVE EMBODIMENTS
[0024] The description set forth below in connection with the
appended drawings is intended to be a description of various,
illustrative embodiments of the disclosed subject matter. Specific
features and functionalities are described in connection with each
illustrative embodiment; however, it will be apparent to those
skilled in the art that the disclosed embodiments may be practiced
without each of those specific features and functionalities.
[0025] Reference throughout the specification to "one embodiment"
or "an embodiment" means that a particular feature, structure, or
characteristic described in connection with an embodiment is
included in at least one embodiment of the subject matter
disclosed. Thus, the appearance of the phrases "in one embodiment"
or "in an embodiment" in various places throughout the
specification is not necessarily referring to the same embodiment.
Further, the particular features, structures or characteristics may
be combined in any suitable manner in one or more embodiments.
Further, it is intended that embodiments of the disclosed subject
matter cover modifications and variations thereof.
[0026] It must be noted that, as used in the specification and the
appended claims, the singular forms "a," "an," and "the" include
plural referents unless the context expressly dictates otherwise.
That is, unless expressly specified otherwise, as used herein the
words "a," "an," "the," and the like carry the meaning of "one or
more." Additionally, it is to be understood that terms such as
"left," "right," "top," "bottom," "front," "rear," "side,"
"height," "length," "width," "upper," "lower," "interior,"
"exterior," "inner," "outer," and the like that may be used herein
merely describe points of reference and do not necessarily limit
embodiments of the present disclosure to any particular orientation
or configuration. Furthermore, terms such as "first," "second,"
"third," etc., merely identify one of a number of portions,
components, steps, operations, functions, and/or points of
reference as disclosed herein, and likewise do not necessarily
limit embodiments of the present disclosure to any particular
configuration or orientation.
[0027] Furthermore, the terms "approximately," "about,"
"proximate," "minor variation," and similar terms generally refer
to ranges that include the identified value within a margin of 20%,
10% or preferably 5% in certain embodiments, and any values
therebetween.
[0028] All of the functionalities described in connection with one
embodiment are intended to be applicable to the additional
embodiments described below except where expressly stated or where
the feature or function is incompatible with the additional
embodiments. For example, where a given feature or function is
expressly described in connection with one embodiment but not
expressly mentioned in connection with an alternative embodiment,
it should be understood that the inventors intend that that feature
or function may be deployed, utilized or implemented in connection
with the alternative embodiment unless the feature or function is
incompatible with the alternative embodiment.
[0029] Aspects of the present disclosure may be directed to air
system connections to galley monuments that may interface with
various types of aircraft air handling systems based on a
functionality of the galley monument. For example, heated air
systems, air conditioning systems, and air extraction systems may
connect to various compartments for the storage of food, beverages,
equipment, and other items needed for servicing passengers and
flight operations. In one example, the galley monument may include
at least one of a trolley bay and a chilled trolley bay that may be
configured to house multiple sizes and types of trolleys and may be
positioned beneath a work surface of the galley monument.
[0030] In some implementations, the galley monument may include at
least one air duct associated with each of the external aircraft
air handling systems that may provide an intake an exhaust path for
air entering and/or leaving the compartments of the galley
monument, such as the trolley bays. For example, the air duct may
include an interior partition (not shown) that separates supply and
exhaust air flow paths and may further include air intake and an
air outlet manifolds.
[0031] In some implementations of galley monuments, air flow may be
an important consideration whether for supplying air into or
extracting air out of a galley monument. Air flow into the galley
monument may be provided for purposes of heating or cooling a
compartment or appliance of the monument, for example, a chilled
trolley bay, an oven, refrigerator, or beverage maker. Air from a
source, such as an Air Conditioning Unit (ACU) or heater may be
directed into the galley monument by various ducts, pipes, hoses,
and vents, such as those shown in FIGS. 1A-1B. In some examples,
air flow extraction or evacuation from the galley monument may be
provided for purposes such as reducing temperature, steam, or
odors, as illustrated by FIG. 14. In some examples, it may be
advantageous for each of the connections within an air flow
distribution system to be tightly sealed to a mounting surface or
component to allow for maximum cooling and/or heating efficiency.
To that end, seals such as those illustrated by FIGS. 3A-3C may be
beneficial to include where applicable, such as at joints
connecting an air supply source to a duct, pipe, or hose, or a
first duct, pipe, or hose connecting a second duct, pipe, hose, or
other air flow control device. Air flow control devices may be
adjustable or non-adjustable. Non-adjustable examples may include
devices with fixed shapes designed to change pressure or air flow
rates, or alter other air flow characteristics such as inducing or
reducing turbulence, between an inlet point and an outlet point,
such as a velocity reducing cone 2256 and an airbox 2406,
illustrated by FIGS. 6 and 7, respectively.
[0032] Further, air flow adjustment devices may be connected to
various ducts, pipes, hoses, and vents within the galley monument.
In some examples, air flow adjustment devices may be intended to be
adjustable while an aircraft is in-use (e.g., during a flight),
which may include gasper assembly 2000 (illustrated in FIGS.
10A-10C) and an air flow adjuster 2200 including a splitter 2208
(illustrated by FIG. 12). Other air flow adjustment devices may be
tuned, adjusted, or replaced with components that produce desired
air flow characteristics primarily during aircraft maintenance or
preparation for flight service (e.g., while the aircraft is
grounded and may be connected to shore power and other shore
services) such as an air distribution duct housing 1220 (FIGS.
2A-2E), restrictors 1280a, 1280b (FIGS. 8A-8C), a restrictor 2100
(FIGS. 9A-9C), and an air deflection system 1850 (FIGS.
11A-11B).
[0033] In some implementations, air flow characteristics can be
measured using a variety of devices, such as, for instance, a
pressure measurement system 1778 shown in FIG. 13 to determine air
pressure within a duct, plenum, housing, or other air flow system.
Measuring air flow characteristics may be helpful in determining
whether air flow adjustments, such as those made using air flow
adjustment devices, may produce intended or expected results in
each part of an air flow system.
[0034] Turning to FIGS. 1A-1B, perspective views of a chilled
galley compartment 1650 with connections to an ACU for supplying
chilled air to the chilled galley compartment 1650 are illustrated.
In some implementations, the chilled compartment 1650 may be a
chilled trolley bay configured to house one or more chilled
trolleys. In some implementations, the chilled compartment 1650 may
include an insulated door 1652, a cold air inlet 1654, and a return
air duct 1656.
[0035] The cold air inlet 1654 and the return air duct 1656 may
each be mounted at a first end to a rear side of the chilled galley
compartment 1650 to provide flow paths for chilled air and return
air into and out of the chilled galley compartment 1650. In some
examples, the cold air inlet 1654 and the return air duct 1656 may
each be connected at a second end to an ACU (not shown.) provides
cold air flow from the ACU to the chilled compartment 1650 through
the cold air inlet 1654, and evacuates warmer return air out of the
chilled galley compartment 1650 by drawing the return air out
through the return air duct 1656. In some implementations, the cold
air inlet 1654 may be positioned at an upper end of the rear
surface of the chilled galley compartment 1650 such that cold air
flows into an upper portion of the chilled galley compartment 1650
while the return air duct 1656 may be positioned such that return
air flows out from a lower portion of the chilled galley
compartment 1650.
[0036] The insulated door 1652 may be hingedly connected to an
opening at a front end of the chilled galley compartment 1650 to
allow access to the interior of the chilled galley compartment 1650
while the insulated door 1652 is in a first, open position. In a
second, closed position, the insulated door 1652 may seal the
interior of the chilled galley compartment 1650 to maintain control
over temperature within the compartment 1650. In some
implementations, the chilled galley compartment 1650 may provide
the functionality of a refrigerator.
[0037] In one example, the cold air inlet 1654 may be connected at
the second end to a Y-splitter 1660 in a case where the ACU
supplies cold air to more than one cold air inlet 1654, for
example, such as when there is more than one chilled compartment
1650, or when a chilled compartment 1650b includes more than one
cold air inlet 1654. The Y-splitter 1660 is then connected to the
ACU.
[0038] Rather than feeding all of the chilled air produced by an
ACU into a homogeneous box duct as in conventional air flow
systems, the air flow system of the present disclosure may include
a bifurcated distribution duct to improve flow distribution
characteristics across each of the compartments within the galley
monument that receive air flow from the ACU.
[0039] Turning to FIGS. 2A-2E, an air distribution duct housing
1220 for use with various galley monument designs described herein
may include connections to an air handling system. In some
implementations, the air distribution duct housing 1220 may
bifurcate entering air flow vertically and/or horizontally such
that the air flow exiting each outlet of the air distribution duct
housing 1220 can be tuned to be substantially proportional (e.g.,
approximately equal) in pressure and volume from a nearest chilled
air supply outlet to a furthest air supply outlet from the chilled
air source. Attaining a substantially proportional distribution of
air pressure and volume across the air supply outlets may be
accomplished through a tuning of chambers within the duct housing
1220 using repositionable dividers or vanes to produce a Venturi
effect. In one example, the output air flow of the duct housing
1220 is used to chill at least three trolley bays in an aircraft
galley monument, such as a chilled trolley bay. In other designs,
similar duct housings can be used to chill from two galley
compartments to eight or more galley compartments based on
balancing specifications for the compartments. In one example, air
provided from the duct housings to the galley compartments may be
balanced within 5% of one another. However, the air flow provided
to galley compartments may also be unbalanced to meet prevailing
heat loads of a chilled compartment configuration. For example,
outermost compartments of a galley monument may have higher heat
loads than inner (middle) compartments such that more air flow may
be provided to the outer compartments to compensate for losses. The
distribution duct 1220 may be formed from fire approved Phenolic
glass, carbon reinforced Epoxy or Phenolic composite laminate, or
vacuum formed plastic. The selection of materials for the
distribution duct 1220 may be based on tradeoffs between weight of
the materials and cost. For example, vacuum form may have a lowest
cost but have a heaviest weight while carbon may have a highest
cost but a lightest weight. In some examples, the distribution duct
1220 may be made of glass fiber, which provides a balance between
cost and weight.
[0040] As illustrated in FIG. 2A, the air distribution duct housing
1220 may include an inlet port 1222, one or more inner exit ports
1224 (illustrated as two inner exit ports 1224a-1224b), and one or
more outer exit ports 1226 (illustrated as three outer exit ports
1226a-1226c). In some implementations, the inlet port 1222 may be
connected at a first end to an ACU (not shown) and at a second end
may be mounted to an interior surface of the aircraft galley
monument, as illustrated in relation to air distribution duct
housing 104 of FIG. 2E. As shown in an upward facing view of FIG.
2E from below looking toward the top of an aircraft galley 1229,
the air distribution duct housing 104 may be installed along four
separate galley compartments 1229a through 1229c, where compartment
1229a may be a double width compartment. In some examples, each
duct housing 104 for the separate compartments 1229a through 1229c
may be sealed off from one another in order to control individual
compartment air volumes to suit the heat load and compartment
layout. For this reason, additional air may be directed to the
galley compartment 1229a than to compartments 1229b and 1229c when
tuning the proportionate flow of air to the air distribution duct
housing 104 for each of the galley compartments 1220a-1229c.
Additionally, the galley compartment 1229a may be separated from
adjacent galley compartment 1229b by an electricity and fluid
conduit region 102. In some examples, the duct housing 104 passes
through the conduit region 102 as a sealed and insulated duct, and
the conduit region 102 may be open to ambient air. As illustrated
in FIG. 2A, for example, the outlets 1224a and 1226b are separated
by a wider gap than the separation of the other proximate outlets
of the air distribution duct housing 1220, a design option which
may be provided to block air from flowing against the conduit
region 102.
[0041] In some implementations, the connection of the air
distribution duct housing 1220 to the ACU at the inlet port 1222
may allow the air to flow through the inlet port 1222 into the air
distribution duct housing 1220. The ACU may be positioned proximate
the air distribution duct housing 1220 or connected remotely by a
main air duct feed. The ACU, for example, may be positioned
horizontally above or below the installation point of the air
distribution duct housing 1220.
[0042] Turning to FIG. 2C, a vertical divider 1228 may be provided
for distributing conditioned air flow, for example, between two
chilled trolley compartments. Specifically, air may flow into at
least one inner exit port 1224 and at least one outer exit port
1226 positioned along a substantially horizontal axis within the
air distribution duct housing 1220. The vertical divider 1228 may
separate the at least one inner exit port 1224 from the at least
one outer exit port 1226 to isolate air flows, allowing smoother,
more efficient air flows through the at least one inner exit port
1224 and the at least one outer exit port 1226. In some examples,
exit port 1226 may be directed upward to provide air to
compartments above a work deck, and the chiller itself may be
located within trolley bays below work deck (BWD) and may be
connected to inlet port 1222, and the exit port 1224 may provide
air flow to the BWD trolley bays. Depending on the application, the
vertical divider 1228 may be designed and positioned to divide the
air flows between the at least one inner exit port 1224 and the at
least one outer exit port 1226 evenly or by some other unequal
proportion such that the volume of air flow directed to the at
least one inner exit port 1224 may be greater than or less than the
volume of air flow directed to the at least one outer exit port
1226. In some examples, the duct housing 1220 may be modularly
constructed to more easily manufacture duct housings 1220 for
galley monuments having different compartment configurations.
[0043] To create multiple inner exit ports 1224 and multiple outer
exit ports 1226, in some embodiments, the air distribution duct
housing may include at least one horizontal divider 1229. The
horizontal dividers 1229, for example, may further bifurcate the
air flow and contribute to the Venturi effect. For example, an
aperture region 1227 may create a Venturi as air flow passing
through aperture region 1227 is restricted, which may increase a
velocity of the air flow and make the air flow more laminar and
directionally stable. To bifurcate a region close to the inlet 1222
without including the outer exit ports 1226, in other embodiments,
an air distribution duct housing may include only horizontal
inserts.
[0044] As illustrated in FIG. 2B, the horizontal divider(s) 1229
and vertical divider(s) 1228 may produce two primary airflow
chambers 1223 and 1225, as well as a subdivision chamber 1221 of
chamber 1225. Airflow within the subchamber 1221 is controlled by
the vertical divider(s) 1228, and a position of the vertical
divider 1228 may be tuned during design and manufacturing based on
computational fluid dynamics (CFD) models. Subdivision chamber 1221
may be used, for example, to chill regions of an equal size or
larger compartment, for example the compartment 1229a of FIG. 2E.
In some examples, the subdivision chamber 1221 may be used to
supply above work deck (AWD) compartments with both the supply air
flow and a separate extracted exhaust.
[0045] FIGS. 3A-3C illustrate various views of a sealing collar
1900 for sealing air flow between an ACU outlet and a duct inlet of
a galley monument, according to an example embodiment, such as a
sealing collar for the inlet port 1222 of the distribution duct
housing 1220 (FIGS. 2A-2E). In some implementations, a first end of
the sealing collar 1900 may have a first inner diameter 1902 and a
second end of the sealing collar 1900 may have a second inner
diameter 1904. In some examples, the sealing collar 1900 may have a
tapered shape such that the first inner diameter 1902 is greater
than the second inner diameter 1904. In some examples, the sealing
collar 1900 may include threads 1908 disposed on an inner surface
of the second inner diameter 1904 to allow the sealing collar 1900
to screw onto a threaded ring, for example, a threaded ring 1912
bonded to a duct inlet 1910. In some implementations, the sealing
collar 1900 may be positioned between a duct inlet 1910 and an ACU
outlet 1914 (FIG. 3C). In one example, an angled edge 1906 may
surround an exterior surface of the sealing collar 1900 to allow
the sealing collar 1900 to fit into a similarly sized ACU outlet
1914, and for the sealing collar 1900 to be axially adjusted
through rotation about the threaded ring 1912, to form a
self-centering, airtight seal with the ACU outlet 1914 around a
portion of the angled edge 1906 that is the same diameter as the
ACU outlet 1914. Air flow may then be efficiently channeled from
the ACU outlet 1914 into the duct inlet 1910 through the sealing
collar 1900. In another example, the arrangement of the sealing
collar 1900 may be reversed such that the ACU outlet 1914 includes
threads 1908 and the duct inlet 1910 connects with the angled edge
1906 of the sealing collar 1900. In another example, the sealing
collar 1900 may connect the ACU outlet 1914 to the inlet port 1222
of the air distribution duct housing 1220 illustrated by FIGS.
2A-2E.
[0046] In some implementations, modular ducts and assemblies may be
connected to galley monuments to provide for the extraction of air
away from galley monuments. The assemblies may have compact or
space saving designs intended to connect to monument walls. The
assemblies may possess various shapes, lengths, and cross sections
to accommodate space limitations, to seal connections between
components, and to meet other functional requirements.
[0047] FIGS. 4A-4C illustrate various views of a galley extraction
system 1800, according to an example embodiment. In some
implementations, the galley extraction system 1800 may be included
as part of a galley monument to remove hot air, steam, and smells
away from ovens, coffee makers, and other galley appliances. The
galley extraction system 1800 may include a duct section 1802, a
first adapter 1804a and a second adapter 1804b, a first vertical
panel 1806a and a second vertical panel 1806b, and a first foam
seal 1808a and a second foam seal 1808b. In some examples, at least
one of the duct sections 1802 and the adapters 1804a, 1804b may
include fire retardant vacuum formed plastic.
[0048] In some implementations, the duct section 1802 may be
connected at a first end to a first side of the first adapter 1804a
and at a second end to the first side of the second adapter 1804b,
and the first adapter 1804a and the second adapter 1804b may be
fitted to the first vertical panel 1806a and the second vertical
panel 1806b, respectively. The vertical panel 1806a may be formed
to accommodate the adapter 1804a, which may allow the duct section
1802 to be positioned toward a rear interior surface of a galley
monument (labeled here as galley 1812) to channel air flow along a
length of the galley monument. In some implementations, the duct
section 1802 may have a cross section of at least one of any shape,
for example, square, rectangular, elliptical, or circular, over a
length of a series of duct sections 1802, with the adapters 1804a,
1804b and the vertical panels 1806a, 1806b shaped to correspond
accordingly to a compartment in which the duct section 1802 is
installed.
[0049] In some examples, the second sides of the first adapter
1804a and the second adapter 1804b may each connect to additional
duct section 1802 as needed. In this way, assemblies of the duct
section 1802, the adapters 1804a, 1804b, the vertical panels 1806a,
1806b, and the foam seals 1808 described above may be repeated in a
continuous series to provide various galley extraction systems 1800
with ducting of differing lengths. Further, at least one duct
section 1802 may have a duct opening 1810 to allow air to flow into
or out of the galley extraction system 1800.
[0050] FIG. 5 illustrates a perspective views of an air duct
extension 1300, according to an example embodiment. In some
implementations, the air duct extension 1300 may connect a galley
monument to an air handling system. In some examples, the air duct
extension 1300 may be designed to be removably connected to, and
direct air flow toward an end of, a duct, plenum (see, e.g., plenum
1230 of FIG. 14), or other opening in an air circulation system,
such as that in an aircraft galley. The air duct extension 1300 may
include an inlet 1302 mounted to a galley duct 1314 and an outlet
1304. In some examples, air flow exiting the galley duct 1314 may
enter the inlet 1302, be directed through the air duct extension
1300, and then exit the air duct extension 1300 through the outlet
1304 and into ductwork for an air handling system (not shown)
connected to the outlet 1304.
[0051] Turning to FIG. 6, a perspective view of an air flow device
2250 is illustrated. The illustration of FIG. 6 is from a
perspective of an interior of a galley monument such that air flows
"outward" from the perspective of FIG. 6 from the air flow device
2250 and into the galley monument. In some implementations, the air
flow device 2250 may be designed to smooth air flow and increase
throughput volume within an air duct 2260 that supplies air to the
galley monument. The air flow device 2250 may include a velocity
reducing cone 2256 positioned within the air duct 2260 between an
air inlet and an air outlet (not shown) in which a coned or tapered
end of the velocity reducing cone 2256 may be positioned to face
the air inlet 2252 and may be supported by at least one support
vane 2258 disposed around a periphery of the velocity reducing cone
2256. In one example, the velocity reducing cone 2256 may be
deployed at the position of the sealing collar 1900, illustrated in
FIGS. 3A-3C. In such an implementation, the velocity reducing cone
2256 may increase air flow by creating a low pressure zone, thus
encouraging air flow to exit the air duct with less turbulence.
[0052] In one example, the velocity reducing cone 2256 may be
supported by one support vane 2258. In another example, the
velocity reducing cone 2256 may be supported by two support vanes
2258. In another example, the velocity reducing cone 2256 may be
supported by three or more support vanes 2258.
[0053] FIG. 7 illustrates a cabin air extraction system 2400,
according to an example embodiment. In some examples, the air
extraction system 2400 may be configured to draw air from a
specific location to which the components of the air extraction
system 2400 are connected. For example, the air extraction system
2400 may withdraw air from an aircraft monument 2410, such as a
galley monument, or from the aircraft cabin itself. In some
implementations, the air extraction system 2400 may include at
least one air box 2406 mounted to a surface of the monument 2410
having an inlet 2402 that withdraws air that has circulated
throughout the monument 2410 and an outlet 2404 that may discharge
air from the air box 2406 to an external duct. In some examples,
the inlet 2402 may be connected to an air circulation duct within
the monument 2410, which may output air that has circulated
throughout one or more compartments of the monument 2410. In some
aspects, the air box 2406 may have a tapered shape in which a width
of the inlet 2402 may be greater than a width of the outlet 2404.
In some aspects, the unique, tapered shape of the air box 2406 may
enhance air flow received at the inlet and passing through the air
box 2406 and may provide increase efficiency and air extraction
capability of the air extraction system 2400 over
non-aerodynamically optimized systems. In some examples, the air
ducts may draw air through the plenums above the galley compartment
or from the rear of a compartment as required, and the shape of the
air box 2406 allows high air flows at low pressures to be
achieved.
[0054] In some implementations, the air box 2406 may include a
number of inlet ports connected to the galley (not shown) to
withdraw circulated air from multiple galley compartment containers
(not shown). In one example, the galley-facing surface of the air
box 2406 may include multiple air inlets, extracting air from three
separate modules of a galley monument. In some examples, the air
box 2406 may function to balance the extraction flow and pressure
across the number of inlets. An air box, for example, may be used
in place of or in addition to an air restrictor. To determine
design parameters of the air box 2406, in some implementations, an
air flow analysis may be performed to determine air flow
requirements for the multiple inlets.
[0055] In some implementations, restrictors may be used to modify
air flow within ducts or plenums, such as for changing a sound or
noise level, velocity, volume, or pressure of the air flow. In some
examples, individual inlet restrictors may be employed to assist in
balancing air extraction from the different galley compartments
within a galley monument. Any of the implementations of restrictors
described herein with respect to FIGS. 8A-8C and FIGS. 9A-9C may be
used in any of the air ducts described in U.S. patent application
Ser. No. 14/467,583, entitled "Universal Modular Ducting for
Chilled Aircraft Galleys," filed Aug. 25, 2014, the entire contents
of which is incorporated herein by reference.
[0056] For example, FIGS. 8A-8C illustrate front and rear views of
restrictors 1280 for an air flow system, according to example
embodiments. In some implementations, restrictors may 1280 may be
positioned within an air stream of the air flow system, for
example, within an air duct that supplies air to or withdraws air
from a galley monument. A first example restrictor 1280a,
illustrated in FIGS. 8A-8B, may include a number of balance holes
1282 of various sizes disposed across a surface of the restrictor
1280. In addition, a shape of the restrictor 1280a may be based on
a shape of an interior of the duct such that the restrictor 1280a
may fit snugly within the duct when positioned substantially
parallel to a direction of airflow through the duct. For example,
the restrictor 1280a shown in FIGS. 8A-8B may have a substantially
oval shape while the restrictor 1280b shown in FIG. 8C may have a
substantially rectangular shape. In some implementations,
restrictors may be formed with at least some of the balance holes
1282a,b removed or blanked off to fine tune a rate of air flow
through the restrictor 1280 in terms of volume and pressure. In
some examples, the restrictor 1280a may include one or more
mounting tabs 1284 to connect with another surface, for example, a
surface of an air distribution duct housing 1220 (as described in
relation to FIGS. 2A-2E) or plenum 1230 (as described in relation
to FIG. 14).
[0057] In some implementations, a sound frequency produced by air
flow through the air duct may be adjusted by use of multiple
balance holes 1282a, 1282b of different sizes (e.g., different
diameters), resulting in a less intrusive level of noise that may
provide additional comfort to a passenger within the aircraft. For
example, smaller balance holes may tend to produce higher frequency
sound, and larger balance holes may tend to produce lower frequency
sound. In some aspects, overlapping sound frequencies by using
multiple sizes of balance holes 1282 with the restrictor 1280 may
reduce an overall sound level, thereby preventing a prominent
audible tone at a single sound frequency. For example, a first set
of balance holes 1282a may have a first diameter corresponding to a
first predetermined frequency, and a second set of balance holes
1282b may have a second diameter that is larger than the first
diameter that corresponds to a second predetermined frequency that
is lower than the first predetermined frequency. In other examples,
more than two different sizes of balance holes may be used.
[0058] In another example, shown in FIG. 8C, a restrictor 1280b may
have a substantially rectangular shape with a number of balance
holes 1282 of various sizes disposed on the surface of the
restrictor 1280b that function similarly to that described above.
In addition, mounting tabs may be formed from an edge or lip 1286
that surrounds a surface of the restrictor 1280b that is covered
with balance holes 1282 to provide a surface to mount the
restrictor 1280b to one or more surfaces of the air duct that is
substantially parallel to the surface of the restrictor 1280b on
which the balance holes 1282a, 1282b are disposed. In some
examples, a height of the lip 1286 surrounding a periphery of the
restrictor 1280b may be different than a height of the surface of
the restrictor 1280b that is covered by the balance holes 1282. The
difference in height between the surfaces may be based on
dimensions and mounting locations within the duct so that the
restrictor 1280b cooperatively mounts to one or more duct
surfaces.
[0059] FIGS. 9A-9C illustrate various views of a restrictor 2100
for restricting air flow within an air duct, according to an
example embodiment. For example, FIG. 9A illustrates an
upward-looking perspective view within an interior of a galley
compartment 900 that shows an air duct 2110 positioned at an upper
end of the compartment with a restrictor 2100 inserted into the air
duct 2110 through a slot lower surface in the air duct 2110. For
example, FIG. 9A shows a lower surface of a mounting tab 2102 for
the restrictor 2100 that is mounted to a lower surface of the air
duct 2110.
[0060] As shown in FIG. 9B, in some implementations, the restrictor
2100 may include a restrictor blade 2104 mounted substantially
perpendicularly to a mounting tab 2102. In some examples, the
restrictor blade 2104 may be inserted into the air duct 2110
through a complementary slot or hole disposed in the lower surface
of the air duct 2110. In some implementations, the slot in the
lower surface of the air duct 2110 may have a width approximately
the same as or wider than a width of the restrictor blade 2104 to
provide for smooth insertion or withdrawal of the restrictor blade
2104 into the air duct 2110 while also ensuring that the restrictor
blade 2104 fits snugly within the slot. All or a portion of the
restrictor blade 2104 may be inserted into the slot, and the
restrictor 2100 may be secured to an outer wall of the duct 2110 or
other mounting location by at least one fastener connected to a
hole 2108 disposed on the mounting tab 2102. The position within
the air duct 2110 as well as cross sectional area, shape, and hole
pattern of the restrictor blade 2104 may alter air flow within the
duct 2110. In some implementations, a position of the restrictor
blade 2104 within the duct 2110 may be adjusted by varying a number
of washers connected to each fastener to change an effective height
of the restrictor blade 2104 inside the duct 2110. In one example,
the restrictor blade 2104 may be a solid rectangular plate. In
another example, the restrictor blade 2104 may include a number of
section holes 2114, as shown in FIG. 9C, that may be of various
sizes, allowing tuning of characteristics of air flow in the duct
2110, for example, velocity, pressure, direction, and sound
frequency.
[0061] Further, steps for a method of varying air flow and pressure
restriction within a duct may include changing a number of washers
between a fastener and a hole 2108 of a mounting tab 2102 to adjust
an effective height of a restrictor blade 2104 positioned within a
duct 2110, or exchanging a first restrictor 2100 connected to a
duct 2110 for a second restrictor 2100 having a restrictor blade
with a different effective cross sectional area.
[0062] In some implementations, air flow may be directed to
locations that have adjustable outlets, allowing a user to adjust a
volume of air flow reaching those locations. Adjustment may allow
fine tuning of the volume of air flowing to each of those
locations, as well as the proportion of air flow distributed to a
number of locations in cases where more than one location is
serviced by one source of air flow. In some implementations, an
amount of air flow may be directed to more than one location by
proportioning the amount of air flow between two locations or
directions, such that total air flow exiting an air flow adjustment
device remains constant while the amount of air flow directed
toward each location may be adjusted.
[0063] For example, FIGS. 10A-10C illustrate various views of
portions of a gasper assembly 2000 for a galley monument, that may
be used to distribute and direct air flow from a common source to a
number of locations throughout the galley monument or within the
greater aircraft cabin. In some implementations, the gasper
assembly 2000 may include a splitter 2006, a first and a second
gasper plenum 2008 (2008a, 2008b), and a respective first and a
second gasper 2010 for each of the gasper plenums 2008a,b (one
gasper 2010 is illustrated in FIG. 10C). In some examples, the
gasper 2010 may provide a portion of the air flow entering the
splitter 2006 to a location and in a direction that the gasper 2010
is oriented within the galley monument or aircraft cabin.
[0064] In some implementations, the splitter 2006 may include a
gasper air inlet 2002, and a first and a second gasper outlet 2004
(2004a, 2004b). In other examples, the splitter 2006 may include
more than two outlets to direct air flow to more than two gaspers
2010. The gasper plenum 2008a may be coupled at a first end to the
first gasper outlet 2004a, and at a second end to a gasper 2010.
Similarly, the gasper plenum 2008b may be coupled at a first end to
the second gasper outlet 2004b, and at a second end to the gasper
2010b. Air flows from an external air source system into the
splitter 2006 by way of the gasper air inlet 2002. A portion of the
air flow exiting the splitter 2006 may exit through the first
gasper outlet 2004a, and a remainder of the air flow may exit the
splitter 2006 through the second gasper outlet 2004b.
[0065] In some implementations, each gasper 2010 may supply air to
a space such as a compartment of a galley monument or an aircraft
cabin, and air flow parameters of the air exiting the gasper 2010
into the space may be adjustable. In some examples, an external
surface of the gasper 2010 may include, for example, a bezel 2012
that may allow a user to easily rotate the gasper 2010 to adjust a
rate of exit air flow. For example, rotation of the gasper 2010 may
cause adjustment of a position of an internal valve disposed within
an interior of the gasper 2010. The internal valve may, for
example, be a disk valve or poppet valve that may be configured to
control the amount of air entering the space through the gasper
2010. In some examples, the gasper 2010 may also include a rotating
mount 2013 that may allow a direction of air flow exiting the
gasper 2010 to be adjusted by a user.
[0066] FIGS. 11A-11B illustrate various views of an air deflection
system 1850 for modifying air flow within an air duct. In some
implementations, the air deflection system 1850 may include an
inlet tube assembly 1852 that may include a first duct 1854a and a
second duct 1854b that share a common inlet 1856 for receiving air
flow into each of the ducts 1854a,b. In addition, each of the ducts
1854a,b includes a respective outlet 1870a,b that outputs
proportioned air flow to one or more spaces within the galley
monument, such as to compartments within the galley monument. In
some examples, the inlet tube assembly 1852 may also include more
than two ducts 1854 connected to the common inlet 1856 that receive
proportioned air flow from an air handling system.
[0067] In some implementations, at least one splitter 1858 may be
positioned inside the inlet 1856 upstream of the ducts 1854a,b such
that air flow that enters the inlet tube assembly 1852 from an
aircraft air handling system flows through the splitter 1858 before
flowing into the ducts 1854a,b. In some implementations, the
splitter 1858 may further include a vane 1860 (e.g. 1860a, 1860b)
to divide air flow entering the splitter 1858 between the duct
1854a and the duct 1854b. In some implementations, a total amount
of air flow entering a first (inlet) end of the splitter 1858 may
be equal to total air flow exiting a second (outlet) end of the
splitter 1858. However, a first portion of exiting air flow from
the splitter 1858 may be directed toward the first duct 1854a and a
second portion of exiting air flow from the splitter 1858 is
directed toward the second duct 1854b. In some examples, Rotation
of the splitter 1858 about a central axis perpendicular to its
diameter may cause an adjustment in a ratio of the first portion of
air flow to the second portion of air flow, thereby altering the
proportion of exiting air flow to the first duct 1854a and the
second duct 1854b. In some implementations, fixed amounts of
rotation of the splitter 1858 may produce proportionally known
changes in air flow rates between the duct 1854a and the duct
1854b. In addition, the splitter 1858 may include at least one
graduation 1862 about a circumference, for example, markings or
notches to more easily allow repeatable and/or discrete adjustment.
Due to varying proportions of exit air flow from the vane 1860 of
the splitter 1858, pressure or velocity of air flow entering the
first duct 1854a and the second duct 1854b may differ.
[0068] A variety of vane 1860 designs for the splitter 1858 are
possible, such as those shown in FIG. 11B. In one example, the vane
1860b may be a flat plane with a central longitudinal axis
positioned to pass through the center of an inner diameter of the
splitter 1858. In another example, the vane 1860 may be a flat
plane with a central longitudinal axis offset from the center of
the inner diameter of the splitter 1858. In another example, the
vane 1860a may be a curved plane and have at least one edge offset
from the center of the inner diameter of the splitter 1858. In
another example, the vane 1860 may be a curved plane and have at
least one edge pass through the center of the inner diameter of the
splitter 1858. In selecting a particular type of vane 1860 for the
splitter 1858, design characteristics of the galley monument (e.g.,
orientation, positioning, layout of compartments and modules),
and/or the balance and distribution of airflow through the galley
monument may be considered.
[0069] As shown in FIG. 11A, in some embodiments, multiple
splitters may be connected in series, such as first, second, third,
and fourth splitters 1858a-d and to allow additional precision and
flexibility in adjustment of air flow proportioning between the
duct 1854a and the duct 1854b. For example, each of the splitters
1858a-d have a predetermined amount of relative rotational offset
from the other connected splitters 1858a-d to achieve predetermined
air flow characteristics to each of the ducts 1854a,b.
[0070] Steps for a method of installing air deflectors with vanes
positioned in a repeatable position and having a predetermined
amount of rotational adjustment may include inserting the splitter
1858 into an inlet 1856, and rotating the splitter 1858 in discrete
amounts to change a proportion of air flow to a duct 1854a and a
duct 1854b by a repeatable amount. In some implementations, the
method may further include adding the second splitter 1858b in
series with the first splitter 1858a, adjusting airflow by rotation
of at least one of the splitter 1858a and the splitter 1858b.
Additional series-connected splitters may subsequently be attached
to an adjacent splitter 1858 in a similar fashion.
[0071] FIG. 12 illustrates an airflow adjuster 2200 that may be
positioned within an air duct of a galley monument, according to an
example embodiment. In some implementations, the airflow adjuster
2200 may include a base 2210 located on or within a duct 2202. The
base 2210 may include a splitter 2208 that may be configured to
divert air flow received through a supply inlet 2204 of the duct
2202 toward supply outlets 2206a,b. In some examples, the duct 2202
may include at least one connection point 2214 to which the base
2210 may be mounted and/or slideably connected. The at least one
connection point 2214 may be, for example, a groove or a slotted
hole. In some examples, the duct 2202 may further include a supply
inlet 2204 and two supply outlets 2206 (2206a, 2206b). In some
implementations, the splitter 2208 may be positioned adjacent to
the supply inlet 2204 of the duct 2202 such that substantially all
of the air flow is diverted toward the supply outlets 2206a,b
without inadvertently passing between sides of the splitter 2208
upon entering the duct 2202. Movement or translation of the base
2210 of the splitter 2208 along the connection points 2214 may
cause a change in the position of the splitter 2208 with respect to
the supply inlet 2204, thus changing a proportion of airflow
directed to each supply outlet 2206a and 2206b of the duct
2202.
[0072] In some implementations, measurement of air flow
characteristics, such as velocity, pressure, or temperature, within
a duct or plenum may be desired. A sensor placed within the air
flow may provide measurements or detect certain conditions about
the air flow. For example, FIG. 13 illustrates a pressure
measurement system 1778 for monitoring air flow within an air duct
of a galley monument system, according to an example embodiment. In
some implementations, the pressure measurement system 1778 may be
deployed for use within an air duct. In some implementations, the
pressure measurement system 1778 may include a pitot tube 1780
having an opening exposed to an air stream at a first end, a number
of pressure ports 1784 (e.g. 1784a, 1784b, 1784c) positioned along
a length of the pitot tube 1780, and a micromanometer (not shown)
connected at a second end. The pitot tube 1780 may be disposed
within an interior of air duct 1782 such that the micromanometer is
able to measure pressure within the air duct 1782. In one example,
the micromanometer electronically calculates air flow based on
static pressure within the pitot tube 1780, which may be output to
a control panel for an aircraft air handling system, which may be
located within a cockpit or at a flight crew station.
[0073] FIG. 14 illustrates a downward looking perspective view of
an interior of a galley compartment including a plenum 1230 mounted
at a rear end of an interior of the galley compartment, which may
include connections to an air handling system. In some
implementations, the plenum 1230 may be used for removal of
extracted air, which may include excess heat, odors, and/or visible
steam produced by galley insert equipment such as ovens, beverage
makers, and microwaves. In some examples, the plenum 1230 may pull,
withdraw, or collect the air to be extracted from within the galley
compartment and route the extracted air toward a second side of the
monument where the plenum 1230 connects to an extraction system,
such as the galley extraction system 1800 illustrated in FIGS.
4A-4C.
[0074] The plenum 1230 may include a cartridge housing 1232
connected to a plenum outlet, the cartridge housing 1232 holds an
air filter cartridge 1236 in place and may be secured by a
connector 1234 (1234a, 1234b) on a first edge and connected by a
mounting tab 1235 positioned on a second edge. The cartridge
housing 1232 may further incorporate an anti-cockroach mesh to trap
or filter any undesired objects from the extracted air. In some
examples, the air filter cartridge 1236 may filter air flow exiting
the plenum 1230 directed toward an aircraft cabin, and may change
color as filtration capacity is diminished to indicate a need for
replacement. In one example, the connectors 1234a, 1234b may be of
a quick release type to allow convenient access to the air filter
cartridge 1236, and may be removable without the use of additional
tools. In one example, the connectors 1234a, 1234b may be spring
loaded and may be engaged or released by a quarter of a turn. In
some implementations, an air restrictor 2100 (as illustrated in
FIG. 9A-9C) may be positioned within the plenum 1230 in order to
modify the air flow characteristics of the extracted air flowing
through the plenum 1230.
[0075] In some implementations, any of the components of the plenum
1230 or connected to the plenum outlet, the cartridge housing 1232,
the connectors 1234a, 1234b, the mounting tab 1235, and the air
filter cartridge may be formed partially or entirely from fire
approved Phenolic glass, carbon reinforced Epoxy or Phenolic
composite laminate, vacuum formed plastic or lightweight metallic
components. The internal airflow and pressure of the plenum 1230
may be changed or varied without removal from the galley monument
by the use of an easily accessible restrictor 2100, as illustrated
by FIGS. 9A-9C.
[0076] In some implementations, filters may be fitted to plenums,
air ducts, or vents to filter an air flow. Periodically, filters
may need to be serviced, changed, or replaced. An aircraft may
contain a number of filters located throughout aircraft ventilation
systems, which may include the air condition systems and air
handling systems that interface with air ducts supplying
conditioned or unconditioned air to a galley monument. Therefore,
access to filters, as well as the ability to easily service,
inspect, and/or replace them, may be important for efficient
servicing. For example, FIG. 15 illustrates a quick-change air
filter grille 2650, according to an example embodiment. In some
implementations, the air filter grille 2650 may be connected to a
plenum 2656 on a first edge by a hinge 2654 and on a second edge by
a quick release mechanism 1312. An air filter 2652 may be secured
by the air filter grille 2650 over the plenum 2656 such that air
passing through the air filter grille 2650 into the plenum 2656 is
filtered by the filter 2652 such that impurities in the air may be
trapped within the filter 2652. In some examples, the air filter
grille 2650 may be designed to allow ease of access to the air
filter 2652 by way of the quick release mechanism 1312 and by
rotating about the hinge 2654 only a small amount, for example in
the range of 10 to 15 degrees from the plenum 2656, before the air
filter 2652 may be installed or removed.
[0077] FIGS. 16A-16D illustrate perspective views of an expansion
plenum 1450 of an air duct for a galley monument. In some
implementations, the expansion plenum 1450 may include an inlet
1454 and an outlet 1456. The inlet 1454 may be connected at a first
end to an air source 1452, which may include a heated air source
with a heater, that supplies air to the expansion plenum 1450
through the inlet 1454, and the inlet 1454 may be connected at a
second end to a first end of the expansion plenum 1450. The outlet
1456, through which air exits the expansion plenum 1450 and enters
at least one compartment of the galley monument, may be positioned
at a second end of the expansion plenum 1450. Although the
expansion plenum 1450 may be designed to accommodate air from a
heated air source, the expansion plenum 1450 may also connect to
other non-heated and/or unconditioned air source systems.
[0078] In some implementations, the expansion plenum 1450 may be
shaped to distribute a relatively large, high pressure volume of
incoming air from the second end of the inlet 1454, diffuse the air
flow to reduce pressure at the outlet 1456 of the expansion plenum
1450, release low pressure air through a confined space, for
example inside a galley monument, and/or distribute the airflow
into, for example, an aircraft cabin. The expansion plenum 1450 may
additionally function to reduce noise of high pressure air
volume.
[0079] At least one internal divider 1458 may be positioned inside
the expansion plenum 1450 to aid in directing air flow between the
second end of the inlet 1454 and the outlet 1456 of the expansion
plenum 1450. The outlet 1456 may be relatively narrow and tall
(having a relatively high ratio of height to width) to fit into
certain spaces, for example, a corner where two monument galleys
meet. The ratio of a cross sectional area of the outlet 1456 to the
inlet 1454 may also be relatively high to reduce pressure and
velocity of air flow passing through the expansion plenum 1450. In
one example, the ratio of the cross-sectional outlet 1456 is
designed to enable a flow of about 40 litres per second (l/s) for
each outlet, at a maximum of 0.5 meters per second (m/s)
velocity.
[0080] In some implementations, monuments may contain compartments
for storage of equipment and supplies during flight. Some
compartments may contain removable storage devices such as trolleys
and standard unit containers. Equipment and supplies contained
within monument storage compartments may be secured while an
aircraft is in use to prevent unintended release. Further,
temperatures within a compartment may also be maintained at
different levels relative to an ambient temperature of a main cabin
of the aircraft such as through the use of air handling systems
described above and/or sealing systems such as doors and door
seals, designed to isolate an interior of a compartment from a
surrounding environment. Further, additional systems may be added
to indicate to users (such as flight crew) a state of use of a
compartment, such as preventing latching of a compartment door if a
turn button securing a removable storage device inside the
compartment is positioned a particular way to ensure securement of
the removable storage device.
[0081] While certain embodiments have been described, these
embodiments have been presented by way of example only, and are not
intended to limit the scope of the present disclosures. Indeed, the
novel methods, apparatuses and systems described herein can be
embodied in a variety of other forms; furthermore, various
omissions, substitutions and changes in the form of the methods,
apparatuses and systems described herein can be made without
departing from the spirit of the present disclosures. The
accompanying claims and their equivalents are intended to cover
such forms or modifications as would fall within the scope and
spirit of the present disclosures.
* * * * *