U.S. patent application number 16/299283 was filed with the patent office on 2020-09-17 for pressure relief door rotating exhaust deflector.
The applicant listed for this patent is Rohr, Inc.. Invention is credited to Jason K. Chen.
Application Number | 20200291813 16/299283 |
Document ID | / |
Family ID | 1000005059776 |
Filed Date | 2020-09-17 |
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United States Patent
Application |
20200291813 |
Kind Code |
A1 |
Chen; Jason K. |
September 17, 2020 |
PRESSURE RELIEF DOOR ROTATING EXHAUST DEFLECTOR
Abstract
A housing includes a pressure relief door and a deflector. The
pressure relief door includes a first door end disposed at a first
hinge axis of the housing and an opposing second door end. The
pressure relief door is rotatable between a first door position and
a second door position about the first hinge axis and defines a
portion of the housing in the first door position. The deflector
includes a first deflector end disposed at a second hinge axis of
the housing and an opposing second deflector end. The deflector is
rotatable between a first deflector position and a second deflector
position about the second hinge axis. Rotation of the pressure
relief door from the first door position to the second door
position effects rotation of the deflector from the first deflector
position to the second deflector position.
Inventors: |
Chen; Jason K.; (San Diego,
CA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Rohr, Inc. |
Chula Vista |
CA |
US |
|
|
Family ID: |
1000005059776 |
Appl. No.: |
16/299283 |
Filed: |
March 12, 2019 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F05D 2220/321 20130101;
F05D 2260/605 20130101; F01D 21/14 20130101; B64D 29/08 20130101;
F05D 2240/14 20130101 |
International
Class: |
F01D 21/14 20060101
F01D021/14; B64D 29/08 20060101 B64D029/08 |
Claims
1. A housing comprising: a pressure relief door comprising a first
door end disposed at a first hinge axis of the housing and an
opposing second door end, the pressure relief door rotatable
between a first door position and a second door position about the
first hinge axis and defining a portion of the housing in the first
door position; and a deflector comprising a first deflector end
disposed at a second hinge axis of the housing and an opposing
second deflector end, the deflector rotatable between a first
deflector position and a second deflector position about the second
hinge axis, wherein rotation of the pressure relief door from the
first door position to the second door position effects rotation of
the deflector from the first deflector position to the second
deflector position.
2. The housing of claim 1, wherein the deflector in the second
deflector position prevents rotation of the pressure relief door
from the second door position to the first door position.
3. The housing of claim 1, wherein the pressure relief door is
configured to rotate from the first door position to the second
door position in response to an internal pressure of the housing
greater than a predetermined pressure.
4. The housing of claim 1, wherein the deflector is configured to
remain in the second deflector position, after rotating from the
first deflector position to the second deflector position, until
repositioned by a user.
5. The housing of claim 3, further comprising a latch in
communication with the housing and the pressure relief door, the
latch configured to secure the pressure relief door in the first
position while the internal pressure of the housing is less than
the predetermined pressure.
6. The housing of claim 1, wherein the deflector comprises at least
one scallop disposed in the second deflector end.
7. The housing of claim 1, further comprising a lanyard connecting
the pressure relief door and the deflector.
8. The housing of claim 7, wherein the lanyard connects the second
door end to the second deflector end.
9. A gas turbine engine comprising: an engine core; and a core
cowling enclosing the engine core, the core cowling comprising: a
pressure relief door comprising a first door end disposed at a
first hinge axis of the core cowling and an opposing second door
end, the pressure relief door rotatable between a first door
position and a second door position about the first hinge axis and
defining a portion of the core cowling in the first door position;
and a deflector comprising a first deflector end disposed at a
second hinge axis of the core cowling and an opposing second
deflector end, the deflector rotatable between a first deflector
position and a second deflector position about the second hinge
axis, wherein rotation of the pressure relief door from the first
door position to the second door position effects rotation of the
deflector from the first deflector position to the second deflector
position.
10. The gas turbine engine of claim 9, wherein the deflector in the
second deflector position prevents rotation of the pressure relief
door from the second door position to the first door position.
11. The gas turbine engine of claim 9, wherein the deflector in the
first deflector position is configured to shield an interface
between the second door end and the core cowling from a heat source
within an interior of the core cowling.
12. The gas turbine engine of claim 9, wherein the pressure relief
door is configured to rotate from the first door position to the
second door position in response to an interior pressure of the
core cowling greater than a predetermined pressure.
13. The gas turbine engine of claim 12, further comprising a latch
in communication with the core cowling and the pressure relief
door, the latch configured to secure the pressure relief door in
the first position while the internal pressure of the core cowling
is less than the predetermined pressure.
14. The gas turbine engine of claim 9, wherein the deflector is
configured to remain in the second deflector position, after
rotating from the first deflector position to the second deflector
position, until repositioned by a user.
15. The gas turbine engine of claim 9, wherein the deflector, in
the second deflector position, is configured to direct heated gases
from an interior of the core cowling away from the core
cowling.
16. The gas turbine engine of claim 15, wherein bypass air flows
along a bypass flow path adjacent the core cowling and the
deflector directs the heated gases into a radially outer portion of
the bypass flow path.
17. The gas turbine engine of claim 9, wherein the deflector
comprises at least one scallop disposed in the second deflector
end.
18. The gas turbine engine of claim 16, wherein the deflector is
downstream of the pressure relief door with respect to the bypass
air flow.
19. The gas turbine engine of claim 9, wherein the core cowling
further comprises a lanyard connecting the pressure relief door and
the deflector.
20. A gas turbine engine comprising: a nacelle; an engine core
disposed within the nacelle; and a core cowling enclosing the
engine core, the nacelle and the core cowling defining a bypass
flow path therebetween, the core cowling comprising: a pressure
relief door comprising a first door end disposed at a first hinge
axis of the core cowling and an opposing second door end, the
pressure relief door rotatable between a first door position and a
second door position about the first hinge axis and defining a
portion of the core cowling in the first door position; a deflector
comprising a first deflector end disposed at a second hinge axis of
the core cowling and an opposing second deflector end, the
deflector rotatable between a first deflector position and a second
deflector position about the second hinge axis; and a lanyard
connecting the pressure relief door and the deflector, wherein
rotation of the pressure relief door from the first door position
to the second door position effects rotation of the deflector from
the first deflector position to the second deflector position, and
wherein the deflector, in the second deflector position, is
configured to direct heated gases from an interior of the core
cowling into a radially outer portion of the bypass flow path.
Description
BACKGROUND
1. Technical Field
[0001] This disclosure relates generally to core structures for gas
turbine engines, and more particularly to a pressure relief system
for the core cowling.
2. Background Information
[0002] The engine core of a gas turbine engine includes a core
cowling which forms an exterior housing of the engine core. The
core cowling is spaced from the engine core leaving a core
compartment therebetween. Additionally, the core cowling encloses
other engine core accessories, such pressurized air (e.g.,
compressor bleed air) lines or ducts, which may be disposed within
the core compartment. The gases contained within these lines may
have high temperatures and pressures which, if exposed to composite
structural materials as a result of a rupture in the lines (i.e., a
"burst duct event"), may cause damage to the composite structural
materials.
[0003] In order to address the above-describe concerns, pressure
relief doors have been used to vent high-temperature and
high-pressure gases from the core compartment during a burst duct
event. However, the high-temperature gases that have been vented
from the core compartment may still damage or degrade the structure
of the core cowling if they are allowed to "reattach" to the core
cowling after venting. To address this concern, heat shields, such
as titanium heat shields, have been used to protect portions of the
core cowling located downstream from the pressure relief doors.
However, these heat shields add weight to the gas turbine engine
and require costly materials. Additionally, integration of the heat
shield with the composite core cowling may reduce the structural
strength of the core cowling. Accordingly, a need exists for an
improved apparatus for relieving pressure within core
compartments.
SUMMARY
[0004] According to an embodiment of the present disclosure, a
housing includes a pressure relief door and a deflector. The
pressure relief door includes a first door end disposed at a first
hinge axis of the housing and an opposing second door end. The
pressure relief door is rotatable between a first door position and
a second door position about the first hinge axis and defines a
portion of the housing in the first door position. The deflector
includes a first deflector end disposed at a second hinge axis of
the housing and an opposing second deflector end. The deflector is
rotatable between a first deflector position and a second deflector
position about the second hinge axis. Rotation of the pressure
relief door from the first door position to the second door
position effects rotation of the deflector from the first deflector
position to the second deflector position.
[0005] In the alternative or additionally thereto, in the foregoing
embodiment, the deflector in the second deflector position prevents
rotation of the pressure relief door from the second door position
to the first door position.
[0006] In the alternative or additionally thereto, in the foregoing
embodiment, the pressure relief door is configured to rotate from
the first door position to the second door position in response to
an internal pressure of the housing greater than a predetermined
pressure.
[0007] In the alternative or additionally thereto, in the foregoing
embodiment, the deflector is configured to remain in the second
deflector position, after rotating from the first deflector
position to the second deflector position, until repositioned by a
user.
[0008] In the alternative or additionally thereto, in the foregoing
embodiment, the housing further includes a latch in communication
with the housing and the pressure relief door. The latch is
configured to secure the pressure relief door in the first position
while the internal pressure of the housing is less than the
predetermined pressure.
[0009] In the alternative or additionally thereto, in the foregoing
embodiment, the deflector includes at least one scallop disposed in
the second deflector end.
[0010] In the alternative or additionally thereto, in the foregoing
embodiment, the housing further includes a lanyard connecting the
pressure relief door and the deflector.
[0011] In the alternative or additionally thereto, in the foregoing
embodiment, the lanyard connects the second door end to the second
deflector end.
[0012] According to another embodiment of the present disclosure, a
gas turbine engine includes an engine core and a core cowling
enclosing the engine core. The core cowling includes a pressure
relief door and a deflector. The pressure relief door includes a
first door end disposed at a first hinge axis of the core cowling
and an opposing second door end. The pressure relief door is
rotatable between a first door position and a second door position
about the first hinge axis and defines a portion of the core
cowling in the first door position. The deflector includes a first
deflector end disposed at a second hinge axis of the core cowling
and an opposing second deflector end. The deflector is rotatable
between a first deflector position and a second deflector position
about the second hinge axis. Rotation of the pressure relief door
from the first door position to the second door position effects
rotation of the deflector from the first deflector position to the
second deflector position.
[0013] In the alternative or additionally thereto, in the foregoing
embodiment, the deflector in the second deflector position prevents
rotation of the pressure relief door from the second door position
to the first door position.
[0014] In the alternative or additionally thereto, in the foregoing
embodiment, the deflector in the first deflector position is
configured to shield an interface between the second door end and
the core cowling from a heat source within an interior of the core
cowling.
[0015] In the alternative or additionally thereto, in the foregoing
embodiment, the pressure relief door is configured to rotate from
the first door position to the second door position in response to
an interior pressure of the core cowling greater than a
predetermined pressure.
[0016] In the alternative or additionally thereto, in the foregoing
embodiment, the gas turbine engine further includes a latch in
communication with the core cowling and the pressure relief door.
The latch is configured to secure the pressure relief door in the
first position while the internal pressure of the core cowling is
less than the predetermined pressure.
[0017] In the alternative or additionally thereto, in the foregoing
embodiment, the deflector is configured to remain in the second
deflector position, after rotating from the first deflector
position to the second deflector position, until repositioned by a
user.
[0018] In the alternative or additionally thereto, in the foregoing
embodiment, the deflector, in the second deflector position, is
configured to direct heated gases from an interior of the core
cowling away from the core cowling.
[0019] In the alternative or additionally thereto, in the foregoing
embodiment, bypass air flows along a bypass flow path adjacent the
core cowling and the deflector directs the heated gases into a
radially outer portion of the bypass flow path.
[0020] In the alternative or additionally thereto, in the foregoing
embodiment, the deflector includes at least one scallop disposed in
the second deflector end.
[0021] In the alternative or additionally thereto, in the foregoing
embodiment, the deflector is downstream of the pressure relief door
with respect to the bypass air flow.
[0022] In the alternative or additionally thereto, in the foregoing
embodiment, the core cowling further includes a lanyard connecting
the pressure relief door and the deflector.
[0023] According to another embodiment of the present disclosure, a
gas turbine engine includes a nacelle, an engine core disposed
within the nacelle, and a core cowling enclosing the engine core.
The nacelle and the core cowling define a bypass flow path
therebetween. The core cowling includes a pressure relief door, a
deflector, and a lanyard connecting the pressure relief door and
the deflector. The pressure relief door includes a first door end
disposed at a first hinge axis of the core cowling and an opposing
second door end. The pressure relief door is rotatable between a
first door position and a second door position about the first
hinge axis and defines a portion of the core cowling in the first
door position. The deflector includes a first deflector end
disposed at a second hinge axis of the core cowling and an opposing
second deflector end. The deflector is rotatable between a first
deflector position and a second deflector position about the second
hinge axis. Rotation of the pressure relief door from the first
position to the second position effects rotation of the deflector
from the first deflector position to the second deflector
position.
[0024] The deflector, in the second deflector position, is
configured to direct heated gases from an interior of the core
cowling into a radially outer portion of the bypass flow path.
[0025] The present disclosure, and all its aspects, embodiments and
advantages associated therewith will become more readily apparent
in view of the detailed description provided below, including the
accompanying drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
[0026] FIG. 1 illustrates a side, cross-sectional view of a gas
turbine engine.
[0027] FIG. 2 illustrates an exterior side view of an engine core
cowling.
[0028] FIG. 3 illustrates an interior side view of an engine core
cowling.
[0029] FIG. 4A illustrates a pressure relief door in a shut
position.
[0030] FIG. 4B illustrates the pressure relief door of FIG. 4A in
an open position.
[0031] FIG. 4C illustrates the pressure relief door of FIG. 4A in
an open position.
[0032] FIG. 5 illustrates an aft view of a pressure relief door in
a shut position.
[0033] FIG. 6A illustrates a front view of an exemplary
deflector.
[0034] FIG. 6B illustrates a front view of another exemplary
deflector.
DETAILED DESCRIPTION
[0035] It is noted that various connections are set forth between
elements in the following description and in the drawings. It is
noted that these connections are general and, unless specified
otherwise, may be direct or indirect and that this specification is
not intended to be limiting in this respect. A coupling between two
or more entities may refer to a direct connection or an indirect
connection. An indirect connection may incorporate one or more
intervening entities.
[0036] Referring to FIG. 1 a gas turbine engine 10 generally
includes a fan section 12, a compressor section 14, a combustor
section 16, a turbine section 18, and an exhaust section 19
disposed about an axial centerline 20. The gas turbine engine 10
further includes a nacelle 22 defining an exterior housing of the
gas turbine engine 10 about the axial centerline 20. The nacelle 22
includes an outer barrel 24 defining a radially outermost surface
of the nacelle 22 and an inner barrel 26 defining a radially
innermost surface of the nacelle 22.
[0037] An engine core 28 generally includes all or part of the fan
section 12, compressor section 14, combustor section 16, turbine
section 18, and exhaust section 19. A core cowling 30 (i.e., a core
nacelle or core shroud) defines an exterior housing of the engine
core 28 about the axial centerline 20. In some embodiments, all or
part of the core cowling 30 may be made of, for example, composite
materials or any other suitable material. While the present
disclosure is discussed with respect to aircraft gas turbine
engines, it should be understood that the present disclosure is not
limited to use in gas turbine engines or aircraft and may be
applied to any other suitable vehicle, industrial application, or
environment where compartment pressure relief is desirable.
[0038] The inner barrel 26 and the core cowling 30 may generally
define an annular bypass duct 32 therebetween. The fan section 12
drives air along a bypass flow path B through the gas turbine
engine 10. At least a portion of the bypass flow path B may pass
through the bypass duct 32. As will be discussed in further detail,
the bypass flow path B through the bypass duct 32 may be referred
to in terms of a radially outer bypass flow path B1 and a radially
inner bypass flow path B2. The compressor section 14 drives air
along a core flow path C, separate from the bypass flow path B, for
compression and communication into the combustor section 16 and
then expansion through the turbine section 18.
[0039] Referring to FIGS. 2, 3, and 5, the core cowling 30 may
include one or more pressure relief doors 34 configured to release
high-pressure and high-temperature gases from a compartment of the
engine core 28, for example, during a burst duct event. For
example, a plurality of pressure relief doors 34 may be
circumferentially spaced about the core cowling 30. The pressure
relief door 34 may be rotatably mounted to the core cowling 30 by,
for example, one or more hinges 36. For example, the hinges 36 may
be configured to permit rotation of the pressure relief door 34
about a hinge axis 36A. In some embodiments, the hinge axis 36A may
be substantially perpendicular to the bypass flow path B. The core
cowling 30 includes a pressure relief opening 35 corresponding to
the pressure relief door 34. The opening 35 has a first end 35E1
and an opposing second end 35E2. The opening 35 additionally has a
first side 35S1 and a second side 35S2, each side 35S1, 35S2
extending between the first end 35E1 and the second end 35E2. As
used herein, the term "substantially" with regard to an angular
relationship refers to the noted angular relationship +/-10
degrees.
[0040] In some embodiments, the pressure relief door 34 may be
disposed on an aft portion of the core cowling 30 proximate the
exhaust section 19 to ensure that high-temperature gases exiting
the pressure relief door 34 do not damage the nacelle 22 and core
cowling 30. For example, the pressure relief door 34 may be
disposed proximate the aft end of the nacelle 22. The core cowling
30 includes a downstream portion 31 disposed downstream of the
pressure relief door 34. In some embodiments, the downstream
portion 31 may include a heat shield 31S configured to protect the
structure of the downstream portion 31 from high-temperature gases
exiting through the pressure relief door opening 35. The heat
shield 31S may be, for example, titanium or any other suitable
high-temperature resistant material. In some embodiments, the heat
shield 31S may be an integral to the downstream portion 31 of the
core cowling 30. In some other embodiments, inclusion of a heat
shield 31S to protect the structure of the downstream portion 31
may not be necessary.
[0041] As will be discussed in further detail, the pressure relief
door 34 is rotatable between an open position (see FIG. 4B) and a
closed position (as shown in FIGS. 2, 3, and 4A). As used herein,
the "closed position" will be used to refer to the pressure relief
door 34 in a position so as to form a substantially continuous
exterior surface with the core cowling 30 (i.e., the pressure
relief door 30 is in a standard position for operation of the gas
turbine engine 10). As used herein, the "open position" will be
used to refer to the pressure relief door 34 in a position other
than the closed position (i.e., the pressure relief door 34 is
partially open, fully open, etc.).
[0042] The pressure relief door 34 may include one or more latches
38 configured to secure the pressure relief door 34 in the shut
position during normal operation of the gas turbine engine 10. The
latch 38 may be configured to release the pressure relief door 34
upon the occurrence of a predetermined condition, for example, a
high pressure in the interior of the core cowling 30. Actuation of
the latch 38 to release the pressure relief door 34 may be
accomplished by any suitable means including, for example, a
pressure sensing spring, or a hydraulically, pneumatically, or
electrically actuated release mechanism in communication with an
associated sensor (e.g., a pressure sensor). In some embodiments,
the interior pressure of the core cowling 30 may be sufficient to
rotate the pressure relief door 34 from the closed position to the
open position once the latch is released. In some other
embodiments, the pressure relief door 34 may include an apparatus
configured to effect rotation of the pressure relief door 34 from
the closed position to the open position.
[0043] Referring to FIGS. 4A, 4B, and 5, the pressure relief door
34 is shown in a closed position (FIG. 4A) and an open position
(FIG. 4B), respectively. The pressure relief door 34 includes a
first end 34E1 and an opposing second end 34E2. The first end 34E1
may be rotatably coupled to the core cowling 30 of the engine core
28 by the hinges 36 about the hinge axis 36A. The second end 34E2
is disposed proximate the core cowling 30 thereby defining an
interface 39 between the pressure relief door 34 and the core
cowling 30. In some embodiments, the second end 34E2 of the door
may be substantially flush with the core cowling 30 at the
interface 39. In the closed position, the pressure relief door 34
may form a portion of the core cowling 30 (i.e., the exterior
surface of the pressure relief door may form a substantially
continuous exterior surface of the core cowling 30.
[0044] The core cowling 30 may include one or more deflectors 40
configured to direct high-temperature gases from a core compartment
28C of the engine core 28 away from the downstream portion 31 of
the core cowling 30, for example, during a burst duct event. The
deflector 40 may be positioned relative to a respective pressure
relief door 34 so as to operate together to relieve an interior
pressure of the core compartment 28C. The deflector 40 includes a
first end 40E1 and an opposing second end 40E2. The deflector 40
may be rotatably mounted to the core cowling 30 at the first end
40E1 by, for example, one or more hinges 42. For example, the
hinges 42 may be configured to permit rotation of the deflector
about a hinge axis 42A. In some embodiments, the hinge axis 42A may
be substantially perpendicular to the bypass flow path B and/or
substantially parallel to the hinge axis 36A. As shown in FIGS. 4A
and 4B, in some embodiments, the pressure relief door 34 may be
rotatably mounted to the core cowling 30 proximate the first end
35E1 of the opening 35 while the deflector 40 is rotatably mounted
to the core cowling 30 proximate the second end 35E2 of the opening
35. For example, FIG. 4A shows the deflector 40 in a closed
position while FIG. 4B shows the deflector 40 in an open position.
In some embodiments, the deflector 40 may be disposed downstream
(i.e., with respect to the bypass flow path B) and/or aft of the
pressure relief door 34.
[0045] As shown in FIG. 4B, in some embodiments, the pressure
relief door 34 and corresponding deflector 40 may include a lanyard
44 connecting the pressure relief door 34 to the deflector 40.
Rotation of the pressure relief door from the closed position to
the open position may effect a corresponding rotation of the
deflector 40 from the closed position to the open position.
Rotation of the pressure relief door 34, as a result of gases
venting from the core compartment 38C, may cause the pressure
relief door 34 to pull the deflector 40 from the closed position to
the open position via the lanyard 44. In some embodiments, the
lanyard 44 may connect the second end 34E2 of the pressure relief
door 34 to the second end 40E2 of the deflector 40. In some other
embodiments, rotation of the deflector 40 from the closed position
to the open position, in response to rotation of the pressure
relief door 34 from the closed position to the open position, may
not require a lanyard 44 connecting the pressure relief door 34 to
the deflector 40. For example, rotation of the deflector 40 from
the closed position to the open position may be effected by a
spring or other biasing device or, alternatively, by the force of
gases venting from the compartment 28C (e.g., gases venting
substantially along a vent flow path V). Thus, rotation of the
pressure relief door 34 from the closed position to the open
position may release the deflector 40 to rotate from the closed
position to the open position.
[0046] FIG. 5 illustrates a side view of an exemplary pressure
relief door 34 from an aft perspective. The pressure relief door 34
of FIG. 5 has an orientation with respect to the core cowling 30
which is substantially similar to the orientation of the pressure
relief door 34 as shown in FIGS. 4A and 4B. As shown in FIG. 5, in
some embodiments, more than one deflector 40 may be rotatably
mounted to the core cowling 30, for example, proximate and aligned
with the first side 35S1 of the opening 35 and the second side 35S2
of the opening 35. Accordingly, in embodiments including a lanyard
44 connecting the pressure relief door 34 to the deflector 40, each
deflector of the more than one deflector 40 may include a lanyard
44 connecting the respective deflector 40 to the pressure relief
door 34. Rotation of the pressure relief door 34, about the hinge
axis 36A, from the closed position to the open position, may
thereby effect rotation of the more than one deflector 40 from the
closed position to the open position about the hinge axis 42A.
[0047] As previously discussed, the core cowling 30 encloses one or
more ducts or lines containing high-temperature and/or
high-pressure gas. An equipment failure leading to a rupture from
one of the ducts into the core compartment 28C (i.e., a burst duct
event) may rapidly fill the core compartment 28C with the
high-temperature and/or high-pressure gas. In response to the burst
duct event, the latch 38 may release the pressure relief door 34
from the closed position, thereby allowing the pressure relief door
34 to rotate to the open position. Rotation of the pressure relief
door 34 to the open position may further effect rotation of the
deflector 40 from the closed position to the open position via the
lanyard 44.
[0048] Referring to FIG. 4B, in the open position, the deflector 40
directs high-temperature gas from the core compartment 28C into the
bypass flow path B thereby forcing the high-temperature gas to mix
with the relatively cooler bypass air. For example,
high-temperature gas may be vented from the core compartment 28C
substantially along the vent flow path V. As a result,
high-temperature gas may be prevented from reattaching to and
possibly damaging the downstream portion 31. In other words,
high-temperature fluids are directed sufficiently far into the
bypass flowpath B (e.g., radially away from the core cowling 30)
such that the gas do not deleteriously interact with (i.e.,
reattach to) the downstream portion 31. For example,
high-temperature gas may be directed towards the outer bypass flow
path B1 wherein reattachment of high-temperature gas with the
downstream portion 31 is reduced or eliminated. In other words,
heat gases directed towards the outer bypass flow path B1 may not
deleteriously affect the downstream portion 31. In some
embodiments, a maximum amount that the pressure relief door 34 may
rotate in direction R1 may depend on a length L1 of the lanyard 44
and/or a length L2 of the deflector 40.
[0049] Referring to FIG. 4B and 4C, during a burst duct event, the
pressure relief door 34 may reach an equilibrium position wherein
the force of the bypass flow path B on the exterior of the pressure
relief door 34 equals the force of the vent flow path V venting
from the core compartment 38C. Subsequent to the rotation of the
pressure relief door 34 to the open position, pressure within the
core compartment 38C may be reduced or returned substantially to a
typical operating pressure of the core compartment 38C, thereby
causing the pressure relief door 34 to rotate in direction R2
towards the core cowling 30.
[0050] As shown in FIG. 4C, in some embodiments, the deflector 40
is configured to remain in the open position after rotating from
the shut position to the open position, for example, in response to
a burst duct event. The deflector 40 in the open position may
prevent the pressure relief door 34 from returning to the closed
position. In said embodiments, the presence of the pressure relief
door 34 and the deflector 40 in the respective open positions may
provide a visual indication to ground crew personnel or other
equipment technicians that a burst duct event or other equipment
malfunction has occurred. Thus, the deflector 40 may remain in the
open position until repositioned by a user (e.g., ground crew
personnel).
[0051] Referring to FIGS. 6A and 6B, the deflector 40 may have a
substantially rectangular cross-sectional shape (see FIG. 6A). In
other embodiments, the deflector 40 may include one or more
scallops 46 disposed in the second end 40E2 of the deflector to
provide better mixing of high-temperature fluids from the core
compartment 38C with the air in the bypass flow path B. The
scallops 46 may have any suitable length L3 and/or width W to
effect mixing of the high-temperature fluids. In some embodiments,
one or more scallops 46 may have a different length L3 and/or width
W than one or more other scallops 46.
[0052] In some embodiments, operation of the pressure relief door
34 and the deflector 40 to prevent reattachment of high-temperature
fluids to the downstream portion 31 may reduce or eliminate the
need for the heat shield 31S in the downstream portion 31.
Elimination of the heat shield 31S may provide for an overall
reduction in the weight of the core cowling 30 and, thus, the
weight of the gas turbine engine 10. Further, elimination of the
heat shield 31S may result in greater structural strength of the
core cowling 30 by allowing a more continuous composite structure
which could otherwise be damaged by vented high-temperature fluids.
The increased continuous composite structure may provide additional
surface area for acoustic attenuating structures, such as honeycomb
structures, on the core cowling 30, thereby providing increased
sound attenuation proximate the downstream portion 31.
[0053] Referring again to FIG. 4A, in some embodiments, the
deflector 40 in the closed position may be configured to shield the
interface 39 between the pressure relief door 34 and the core
cowling 30 from a heat source (e.g., a heat source of the engine
core 28 as a result of general gas turbine engine 10 operation or a
mechanical failure such as a burst duct) within the core
compartment 28C. For example, the deflector 40 may be disposed
between the interface 39 and the heat source in order to prevent
excessive temperatures in composite portions of the interface 39.
In some embodiments, the deflector 40 may be made of a
high-temperature resistant material such as titanium or any other
suitable material for shielding the interface 39.
[0054] While various aspects of the present disclosure have been
disclosed, it will be apparent to those of ordinary skill in the
art that many more embodiments and implementations are possible
within the scope of the present disclosure. For example, the
present disclosure as described herein includes several aspects and
embodiments that include particular features. Although these
particular features may be described individually, it is within the
scope of the present disclosure that some or all of these features
may be combined with any one of the aspects and remain within the
scope of the present disclosure. Accordingly, the present
disclosure is not to be restricted except in light of the attached
claims and their equivalents.
* * * * *