U.S. patent application number 16/375064 was filed with the patent office on 2019-07-25 for air-driven particle pulverizer for gas turbine engine cooling fluid system.
The applicant listed for this patent is United Technologies Corporation. Invention is credited to Paul M. Lutjen, Anthony B. Swift.
Application Number | 20190226406 16/375064 |
Document ID | / |
Family ID | 55179549 |
Filed Date | 2019-07-25 |
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United States Patent
Application |
20190226406 |
Kind Code |
A1 |
Lutjen; Paul M. ; et
al. |
July 25, 2019 |
AIR-DRIVEN PARTICLE PULVERIZER FOR GAS TURBINE ENGINE COOLING FLUID
SYSTEM
Abstract
An air-driven particle pulverizer for a gas turbine engine
includes an array of fingers arranged about an axis. Each of the
fingers comprises a base and a terminal end. Each terminal end
extends away from the axis and canted toward one side. The terminal
ends are configured to pulverize particles in a fluid directed onto
the terminal ends.
Inventors: |
Lutjen; Paul M.;
(Kennebunkport, ME) ; Swift; Anthony B.; (North
Waterboro, ME) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
United Technologies Corporation |
Farmington |
CT |
US |
|
|
Family ID: |
55179549 |
Appl. No.: |
16/375064 |
Filed: |
April 4, 2019 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
14804926 |
Jul 21, 2015 |
|
|
|
16375064 |
|
|
|
|
62031303 |
Jul 31, 2014 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F02C 7/05 20130101; Y02T
50/60 20130101; F01D 25/12 20130101; F02C 7/18 20130101; F01D 11/12
20130101; Y02T 50/675 20130101; Y02T 50/671 20130101; F05D 2260/607
20130101; F05D 2240/11 20130101 |
International
Class: |
F02C 7/18 20060101
F02C007/18; F02C 7/05 20060101 F02C007/05; F01D 11/12 20060101
F01D011/12; F01D 25/12 20060101 F01D025/12 |
Goverment Interests
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT
[0002] This invention was made with government support under
Contract No. FA8650-09-D-2923-0021, awarded by the U.S. Air Force.
The Government has certain rights in this invention.
Claims
1. An air-driven particle pulverizer for a gas turbine engine
comprising: an array of fingers arranged about an axis, each of the
fingers comprises a base and a terminal end, each terminal end
extending away from the axis and canted toward one side, the
terminal ends configured to pulverize particles in a fluid directed
onto the terminal ends.
2. The air-driven particle pulverizer according to claim 1 wherein
a radial direction is normal to the axis, and the fingers arranged
at a non-normal angle relative to the axis and the radial
direction.
3. The air-driven particle pulverizer according to claim 1, wherein
the fingers are spaced axially relative to one another at an acute
angle.
4. The air-driven particle pulverizer according to claim 1, wherein
the fingers are tapered to an apex.
5. The air-driven particle pulverizer according to claim 1, wherein
the fingers include a coating providing a hardness greater than a
finger substrate.
6. The air-driven particle pulverizer according to claim 1, wherein
an enlarged recess is provided between the fingers.
7. The air-driven particle pulverizer according to claim 1, wherein
the fingers increase in length as a distance from the side
increases.
8. The air-driven particle pulverizer according to claim 1, wherein
the array of fingers is configured to be supported by an engine
static structure.
9. The air-driven particle pulverizer according to claim 1, the
array of fingers comprises axially spaced apart arrays of annular
fingers.
10. An air-driven particle pulverizer for a gas turbine engine
comprising: a plurality of fingers arranged in a fluid passageway
having an aperture, each of the fingers having a terminal end
extending from a base toward a terminal end, the terminal end
pointing towards the aperture and configured to pulverize particles
that flow through the aperture.
11. The air-driven particle pulverizer according to claim 10,
wherein the plurality of fingers increase in length as the distance
from the aperture increases.
12. The air-driven particle pulverizer according to claim 10
wherein a radial direction is normal to the axis, and the fingers
arranged at a non-normal angle relative to the axis and the radial
direction.
13. The air-driven particle pulverizer according to claim 10,
wherein the fingers are spaced axially relative to one another at
an acute angle.
14. The air-driven particle pulverizer according to claim 10,
wherein the fingers are tapered to an apex.
15. The air-driven particle pulverizer according to claim 10,
wherein the fingers include a coating providing a hardness greater
than a finger substrate.
16. The air-driven particle pulverizer according to claim 10,
wherein an enlarged recess is provided between the fingers.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application is a divisional of U.S. application Ser.
No. 14/804,926 filed Jul. 21, 2015, which claims priority to U.S.
Provisional Application No. 62/031,303, which was filed on Jul. 31,
2014 and is incorporated herein by reference.
BACKGROUND
[0003] This disclosure relates to an air-driven particle pulverizer
for a gas turbine engine cooling fluid system.
[0004] A gas turbine engine typically includes a fan section, a
compressor section, a combustor section and a turbine section. Air
entering the compressor section is compressed and delivered into
the combustor section where it is mixed with fuel and ignited to
generate a high-speed exhaust gas flow. The high-speed exhaust gas
flow expands through the turbine section to drive the compressor
and the fan section. The compressor section typically includes low
and high pressure compressors, and the turbine section includes low
and high pressure turbines.
[0005] In a typical gas turbine engine, cooling fluid is provided
from the compressor section to other regions of the engine.
Typically, dirt particles are driven toward the outer diameter of
the core flow path in the compressor section. These dirt particles
may undesirably be provided to engine components, such as a high
pressure turbine blade outer air seals. Cooling holes within the
blade outer air seal may become plugged with dirt particles. To
prevent plugging of the cooling holes, the holes may be enlarged
from their desired design hole size. As a result, the holes may be
larger than desired for cooling.
[0006] Honeycomb structures have been used to collect dirt in a
fluid passageway, but these structures are not designed to break
the dirt particles. Moreover, these structures have obstructed
cooling flow.
SUMMARY
[0007] In one exemplary embodiment, a cooling fluid system for a
gas turbine engine includes a structure that provides a fluid
passageway. The structure has a wall with an aperture that is in
fluid communication with the fluid passageway. The aperture is
configured to provide a fluid in a flow direction. Fingers are
arranged in the fluid passageway facing into flow direction. The
fluid passageway includes a cooling cavity immediately downstream
from the fingers and it is configured to receive fluid having
passed over or through the fingers.
[0008] In a further embodiment of the above, a cooling fluid source
is in fluid communication with the structure upstream from the
aperture.
[0009] In a further embodiment of any of the above, the cooling
fluid source is a compressor section. The structure is an engine
static structure that is arranged in a turbine section.
[0010] In a further embodiment of any of the above, the structure
is a vane support.
[0011] In a further embodiment of any of the above, the engine
static structure includes a blade outer air seal that is arranged
in the cooling cavity and is downstream from the fingers.
[0012] In a further embodiment of any of the above, the fingers are
canted toward the aperture.
[0013] In a further embodiment of any of the above, the aperture is
directed at the fingers.
[0014] In a further embodiment of any of the above, the gas turbine
engine includes an engine axis, and a radial direction normal to
the engine axis. The fingers are arranged at a non-normal angle
relative to the engine axis and the radial direction.
[0015] In a further embodiment of any of the above, the fingers are
spaced axially relative to one another at an acute angle.
[0016] In a further embodiment of any of the above, the fingers are
tapered to an apex.
[0017] In a further embodiment of any of the above, the fingers
include a coating that provides a hardness greater than a finger
substrate.
[0018] In a further embodiment of any of the above, an enlarged
recess is provided between the fingers.
[0019] In a further embodiment of any of the above, the fingers
increase in length as a distance from the aperture increases.
[0020] In another exemplary embodiment, an air-driven particle
pulverizer for a gas turbine engine includes an array of fingers
that are arranged about an axis and canted toward one side.
[0021] In a further embodiment of any of the above, a radial
direction is normal to the axis. The fingers are arranged at a
non-normal angle relative to the axis and the radial direction.
[0022] In a further embodiment of any of the above, the fingers are
spaced axially relative to one another at an acute angle.
[0023] In a further embodiment of any of the above, the fingers are
tapered to an apex.
[0024] In a further embodiment of any of the above, the fingers
include a coating that provides a hardness greater than a finger
substrate.
[0025] In a further embodiment of any of the above, an enlarged
recess is provided between the fingers.
[0026] In a further embodiment of any of the above, the fingers
increase in length as a distance from the side increases.
BRIEF DESCRIPTION OF THE DRAWINGS
[0027] The disclosure can be further understood by reference to the
following detailed description when considered in connection with
the accompanying drawings wherein:
[0028] FIG. 1 schematically illustrates a gas turbine engine
embodiment.
[0029] FIG. 2 is a schematic view of a section of the gas turbine
engine.
[0030] FIG. 3 is an enlarged cross-sectional view of an example
air-driven particle pulverizer in the section shown in FIG. 2.
[0031] FIG. 4 is an enlarged cross-sectional view of the air-driven
particle pulverizer.
[0032] FIG. 5 is an enlarged cross-sectional view of another
example air-driven particle pulverizer.
[0033] The embodiments, examples and alternatives of the preceding
paragraphs, the claims, or the following description and drawings,
including any of their various aspects or respective individual
features, may be taken independently or in any combination.
Features described in connection with one embodiment are applicable
to all embodiments, unless such features are incompatible.
DETAILED DESCRIPTION
[0034] FIG. 1 schematically illustrates a gas turbine engine 20.
The gas turbine engine 20 is disclosed herein as a two-spool
turbofan that generally incorporates a fan section 22, a compressor
section 24, a combustor section 26 and a turbine section 28.
Alternative engines might include an augmenter section (not shown)
among other systems or features. The fan section 22 drives air
along a bypass flow path B in a bypass duct defined within a
nacelle 15, while the compressor section 24 drives air along a core
flow path C for compression and communication into the combustor
section 26 then expansion through the turbine section 28. Although
depicted as a two-spool turbofan gas turbine engine in the
disclosed non-limiting embodiment, it should be understood that the
concepts described herein are not limited to use with two-spool
turbofans as the teachings may be applied to other types of turbine
engines including three-spool architectures.
[0035] The exemplary engine 20 generally includes a low speed spool
30 and a high speed spool 32 mounted for rotation about an engine
central longitudinal axis A relative to an engine static structure
36 via several bearing systems 38. It should be understood that
various bearing systems 38 at various locations may alternatively
or additionally be provided, and the location of bearing systems 38
may be varied as appropriate to the application.
[0036] The low speed spool 30 generally includes an inner shaft 40
that interconnects a fan 42, a first (or low) pressure compressor
44 and a first (or low) pressure turbine 46. The inner shaft 40 is
connected to the fan 42 through a speed change mechanism, which in
exemplary gas turbine engine 20 is illustrated as a geared
architecture 48 to drive the fan 42 at a lower speed than the low
speed spool 30. The high speed spool 32 includes an outer shaft 50
that interconnects a second (or high) pressure compressor 52 and a
second (or high) pressure turbine 54. A combustor 56 is arranged in
exemplary gas turbine 20 between the high pressure compressor 52
and the high pressure turbine 54. A mid-turbine frame 57 of the
engine static structure 36 is arranged generally between the high
pressure turbine 54 and the low pressure turbine 46. The
mid-turbine frame 57 further supports bearing systems 38 in the
turbine section 28. The inner shaft 40 and the outer shaft 50 are
concentric and rotate via bearing systems 38 about the engine
central longitudinal axis A which is collinear with their
longitudinal axes.
[0037] The core airflow is compressed by the low pressure
compressor 44 then the high pressure compressor 52, mixed and
burned with fuel in the combustor 56, then expanded over the high
pressure turbine 54 and low pressure turbine 46. The mid-turbine
frame 57 includes airfoils 59 which are in the core airflow path C.
The turbines 46, 54 rotationally drive the respective low speed
spool 30 and high speed spool 32 in response to the expansion. It
will be appreciated that each of the positions of the fan section
22, compressor section 24, combustor section 26, turbine section
28, and fan drive gear system 48 may be varied. For example, gear
system 48 may be located aft of combustor section 26 or even aft of
turbine section 28, and fan section 22 may be positioned forward or
aft of the location of gear system 48.
[0038] The engine 20 in one example is a high-bypass geared
aircraft engine. In a further example, the engine 20 bypass ratio
is greater than about six (6), with an example embodiment being
greater than about ten (10), the geared architecture 48 is an
epicyclic gear train, such as a planetary gear system or other gear
system, with a gear reduction ratio of greater than about 2.3 and
the low pressure turbine 46 has a pressure ratio that is greater
than about five. In one disclosed embodiment, the engine 20 bypass
ratio is greater than about ten (10:1), the fan diameter is
significantly larger than that of the low pressure compressor 44,
and the low pressure turbine 46 has a pressure ratio that is
greater than about five 5:1. Low pressure turbine 46 pressure ratio
is pressure measured prior to inlet of low pressure turbine 46 as
related to the pressure at the outlet of the low pressure turbine
46 prior to an exhaust nozzle. The geared architecture 48 may be an
epicycle gear train, such as a planetary gear system or other gear
system, with a gear reduction ratio of greater than about 2.3:1. It
should be understood, however, that the above parameters are only
exemplary of one embodiment of a geared architecture engine and
that the present invention is applicable to other gas turbine
engines including direct drive turbofans.
[0039] A significant amount of thrust is provided by the bypass
flow B due to the high bypass ratio. The fan section 22 of the
engine 20 is designed for a particular flight condition--typically
cruise at about 0.8 Mach and about 35,000 feet (10,668 meters). The
flight condition of 0.8 Mach and 35,000 ft (10,668 meters), with
the engine at its best fuel consumption--also known as "bucket
cruise Thrust Specific Fuel Consumption (`TSFC`)"--is the industry
standard parameter of lbm of fuel being burned divided by lbf of
thrust the engine produces at that minimum point. "Low fan pressure
ratio" is the pressure ratio across the fan blade alone, without a
Fan Exit Guide Vane ("FEGV") system. The low fan pressure ratio as
disclosed herein according to one non-limiting embodiment is less
than about 1.45. "Low corrected fan tip speed" is the actual fan
tip speed in ft/sec divided by an industry standard temperature
correction of [(Tram .degree. R)/(518.7.degree. R)].sup.0.5. The
"Low corrected fan tip speed" as disclosed herein according to one
non-limiting embodiment is less than about 1150 ft/second (350.5
meters/second).
[0040] An example section of the engine 10 is show in FIG. 2. The
illustrated section includes a fixed stage 60 upstream from a
rotating stage 62. The fixed stage 60 includes a circumferential
array of vanes 64. The rotating stage 62 includes a circumferential
array of blades 68 mounted to a rotor 66 that is arranged
downstream from the vane 64. A blade outer air seal 70 is provided
at an outer diameter of the blades 68 to provide a seal relative to
a tip 72 of the blades 68.
[0041] Referring to FIG. 3, a cooling fluid source 74, such as a
compressor section, provides cooling fluid to the blade outer air
seal 70. In one example, the engine static structure 36 includes a
wall that supports the vanes 64. The wall has an aperture 78 in
fluid communication with a fluid passageway provided in the engine
static structure 36. The aperture is configured to provide a fluid
F in a flow direction.
[0042] An air-driven particle pulverizer 80 is supported by the
engine static structure 36, integrally or separately, and is
arranged in the fluid passageway. The air-driven particle
pulverizer includes fingers 84 facing into the flow F. The fluid
passageway includes a cooling cavity 76 immediately downstream from
the fingers 84 and which is configured to receive unobstructed
fluid from the fingers 84. That is, in the example, the cooling
cavity 76 is not in a discrete, separate cavity from the air-driven
particle pulverizer 80.
[0043] The blade outer air seal 70 is in fluid communication with
the cooling cavity 76 downstream from the fingers 84. The blade
outer air seal 70 includes cooling holes 82 that provide a fluid to
an area adjacent to the tip 72.
[0044] As shown in FIGS. 3 and 4, the fingers 84 are canted toward
the aperture 78. The fingers 84 spaced axially relative to one
another at an acute angle 92, shown in FIG. 4. In one example, the
aperture 78 directs the fluid F onto the fingers 84 to better
encourage the particles, (such as, for example, dirt, sand, CMAS or
airborne contaminants) to collide with the fingers, breaking the
larger dirt particles entrained in the fluid into smaller
particles.
[0045] A radial direction R is arranged normal to the engine axis
A. The fingers 84 are arranged at a non-normal angle relative to
the engine axis and the radial direction R. Axially spaced apart
arrays of annular fingers 84 may be provided. The fingers 84 may
instead be arranged only near the apertures 78 to reduce the weight
of the air-driven particle pulverizer. In the example, the fingers
84 increase in length as the distance from the aperture 78
increases.
[0046] In this manner, the dirt particles will more directly
collide into terminal ends 86 of the fingers 84. In the example
shown, the fingers 84 are tapered to an apex, which provides the
terminal ends 86. The fingers 84 may be coated with a suitable
material (such as, for example, a chromium-carbide-based material
like plasma sprayed chromium carbide--nickel chromium) to provide
hardness that is greater than a finger substrate, which may be
nickel alloy.
[0047] A tapered recess 88 between the fingers 84 captures large
particles that may be wedged into the recess by their momentum.
Referring to FIG. 5, an enlarged recess 90 may be arranged between
adjacent fingers 184 to collect dirt particles, if desired, which
prolongs the interval at which the air-driven particle pulverizer
180 should be cleaned.
[0048] It should also be understood that although a particular
component arrangement is disclosed in the illustrated embodiment,
other arrangements will benefit herefrom. Although particular step
sequences are shown, described, and claimed, it should be
understood that steps may be performed in any order, separated or
combined unless otherwise indicated and will still benefit from the
present invention.
[0049] Although the different examples have specific components
shown in the illustrations, embodiments of this invention are not
limited to those particular combinations. It is possible to use
some of the components or features from one of the examples in
combination with features or components from another one of the
examples.
[0050] Although an example embodiment has been disclosed, a worker
of ordinary skill in this art would recognize that certain
modifications would come within the scope of the claims. For that
reason, the following claims should be studied to determine their
true scope and content.
* * * * *