WO2014078003A2 - Gas turbine engine with inlet particle separator and thermal management - Google Patents
Gas turbine engine with inlet particle separator and thermal management Download PDFInfo
- Publication number
- WO2014078003A2 WO2014078003A2 PCT/US2013/065337 US2013065337W WO2014078003A2 WO 2014078003 A2 WO2014078003 A2 WO 2014078003A2 US 2013065337 W US2013065337 W US 2013065337W WO 2014078003 A2 WO2014078003 A2 WO 2014078003A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- gas turbine
- inlet
- turbine engine
- downstream
- air
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
- F02C7/052—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- This application relates to a gas turbine engine, wherein an inlet particle separator provides a thermal management function.
- Gas turbine engines include a compressor compressing air and delivering it into a combustor section.
- the air is mixed with fuel in the combustor and ignited. Products of the combustion pass downstream over turbine rotors driving them to rotate.
- gas turbine engine is a contra-rotating turbo prop gas turbine engine.
- air may be delivered into a compressor section, as mentioned above from an inlet.
- the air may include impurities and, thus, it is known to include an inlet particle separator which will tend to force dirt or other impurities radially outwardly, such that clean air is delivered into the compression section.
- a gas turbine engine has a nose cone at an inlet end spaced radially inwardly of a nacelle.
- a compressor is downstream of the nose cone.
- a core inlet delivers air downstream of the nose cone into the compressor.
- An inlet particle separator includes a manifold for delivering air radially outwardly of the core inlet. The air is delivered by the inlet particle separator passing over a heat exchanger before passing to an outlet.
- the heat exchanger cools oil associated with a gear reduction on the gas turbine engine.
- the compressor rotates about a central axis of the engine.
- the nose cone has a radially outermost portion which is radially outward of a radially inner end of the core inlet, such that air having heavier particles is generally directed radially outwardly of the core inlet and into the inlet particle separator.
- the manifold extends for 360 degrees about the axis of rotation.
- the manifold has an open inlet at an upstream end, and a downstream outlet over a limited portion of the 360 degrees of the circumferentially extending portion.
- an ejector is positioned downstream of the heat exchanger for selectively driving air across the heat exchanger.
- a turbine section is downstream of the compressor and drives propellers.
- Figure 1 schematically shows a gas turbine engine incorporating an inlet particle separator.
- Figure 2 is a detail of the inlet end of the gas turbine engine.
- Figure 3A shows an inlet particle separator
- Figure 3B is another view of the inlet particle separator.
- a gas turbine engine 20 is illustrated in Figure 1 having a nose cone 22 at an inlet end. Nose cone 22 is positioned radially inwardly of a nacelle 24. As shown, air passing the nose cone 22 may enter an inlet 50 of a manifold 28 and be directed across a heat exchanger 32.
- the heat exchanger 32 may be associated with cooling any fluid on the engine. As one example, the heat exchanger 32 may cool oil which is delivered to a gear reduction associated with the gas turbine engine 20.
- the ejector 31 Downstream of the heat exchanger 32 the air passes through the ejector 31.
- the ejector 31 is provided with a control 90 which selectively shoots air into the ejector 31 when the gas turbine engine 20 is on the ground, as there will not be ram air delivered into the inlet when an aircraft associated with the gas turbine engine 20 is not moving.
- An outlet 30 is downstream of the ejector 31.
- the nose cone 22 is designed to ensure the dirtier air will be delivered into the inlet 50, and the clean air passes into a path into a core inlet 26.
- Core inlet 26 feeds air into a compressor section 27, where it is compressed and delivered into a combustor section 25.
- the air is mixed with fuel and ignited, and products of this combustion pass downstream over turbine rotors 23, driving them to rotate.
- the engine 20 may be a contra-rotating prop aircraft with a pair of propellers 80 and 82 rotating in opposed directions.
- the propellers 80 and 82 are driven by the output shaft of a fan drive gear system 200, which in turn is powered by the turbine section 23.
- a fan drive gear system 200 which in turn is powered by the turbine section 23.
- other engine types may benefit from this disclosure.
- Figure 2 shows a detail of the nose cone 22.
- Nose cone 22 is shaped such that it has the highest or most radially outward point 100 which is radially further outward than an inner point 101 of a manifold 102 leading into the compressor 27.
- the gas turbine engine rotates upon an axis x (Fig. 1) and the "radially outward" position is relative to the axis x.
- some impurities or dirt may still be delivered into the core inlet 26.
- the heavier particles containing impurities are generally directed radially outwardly of the core inlet 26, and into the inlet 50 of the manifold 28. That is, the majority of the impurities will be passed into the manifold 28, compared to what is passed into the core inlet 26.
- the manifold 28 includes a circumferentially extending portion 31 which surrounds a circumference of gas turbine engine 20 for 360 degrees about axis x.
- the inlet end 50 is not shown, but is generally open (see Figure 2), while the downstream end is closed as illustrated in this Figure.
- the circumferentially extending portion feeds into a circumferentially limited outlet 29 which passes air across the heat exchanger 32.
- Figure 3B shows another view of the same structure.
- the present invention now utilizes the inlet particle separator to perform a thermal management function and, thus, the efficiency of the overall operation of the gas turbine engine is improved.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Separating Particles In Gases By Inertia (AREA)
Abstract
A gas turbine engine includes a nose cone at an inlet end, and spaced radially inwardly of a nacelle. A compressor is downstream of the nose cone. A core inlet delivers air downstream of the nose cone into the compressor. An inlet particle separator includes a manifold for delivering air radially outwardly of the core inlet. Air delivered by the inlet particle separator passes over a heat exchanger before passing to an outlet.
Description
GAS TURBINE ENGINE WITH INLET PARTICLE SEPARATOR
AND THERMAL MANAGEMENT
BACKGROUND OF THE INVENTION
[0001] This application relates to a gas turbine engine, wherein an inlet particle separator provides a thermal management function.
[0002] Gas turbine engines are known, and include a compressor compressing air and delivering it into a combustor section. The air is mixed with fuel in the combustor and ignited. Products of the combustion pass downstream over turbine rotors driving them to rotate.
[0003] One type of gas turbine engine is a contra-rotating turbo prop gas turbine engine. In such a gas turbine engine, air may be delivered into a compressor section, as mentioned above from an inlet. The air may include impurities and, thus, it is known to include an inlet particle separator which will tend to force dirt or other impurities radially outwardly, such that clean air is delivered into the compression section.
[0004] Recently, the efficiency of gas turbine engines has become of increasing importance. Thus, the loss of air associated with the inlet particle separator, with no achieved benefit, hurts the efficiency of the overall engine.
SUMMARY OF THE INVENTION
[0005] In a featured embodiment, a gas turbine engine has a nose cone at an inlet end spaced radially inwardly of a nacelle. A compressor is downstream of the nose cone. A core inlet delivers air downstream of the nose cone into the compressor. An inlet particle separator includes a manifold for delivering air radially outwardly of the core inlet. The air is delivered by the inlet particle separator passing over a heat exchanger before passing to an outlet.
[0006] In another embodiment according to the previous embodiment, the heat exchanger cools oil associated with a gear reduction on the gas turbine engine.
[0007] In another embodiment according to any of the previous embodiments, the compressor rotates about a central axis of the engine. The nose cone has a radially outermost portion which is radially outward of a radially inner end of the core inlet, such that air having heavier particles is generally directed radially outwardly of the core inlet and into the inlet particle separator.
[0008] In another embodiment according to any of the previous embodiments, the manifold extends for 360 degrees about the axis of rotation.
[0009] In another embodiment according to any of the previous embodiments, the manifold has an open inlet at an upstream end, and a downstream outlet over a limited portion of the 360 degrees of the circumferentially extending portion.
[0010] In another embodiment according to any of the previous embodiments, an ejector is positioned downstream of the heat exchanger for selectively driving air across the heat exchanger.
[0011] In another embodiment according to any of the previous embodiments, a turbine section is downstream of the compressor and drives propellers.
[0012] These and other features of this application will be best understood from the following specification and drawings, the following of which is a brief description.
BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 schematically shows a gas turbine engine incorporating an inlet particle separator.
[0014] Figure 2 is a detail of the inlet end of the gas turbine engine.
[0015] Figure 3A shows an inlet particle separator.
[0016] Figure 3B is another view of the inlet particle separator.
DETAILED DESCRIPTION
[0017] A gas turbine engine 20 is illustrated in Figure 1 having a nose cone 22 at an inlet end. Nose cone 22 is positioned radially inwardly of a nacelle 24. As shown, air passing the nose cone 22 may enter an inlet 50 of a manifold 28 and be directed across a heat exchanger 32. The heat exchanger 32 may be associated with cooling any fluid on the engine. As one example, the heat exchanger 32 may cool oil which is delivered to a gear reduction associated with the gas turbine engine 20.
[0018] Downstream of the heat exchanger 32 the air passes through the ejector 31. The ejector 31 is provided with a control 90 which selectively shoots air into the ejector 31 when the gas turbine engine 20 is on the ground, as there will not be ram air delivered into the inlet when an aircraft associated with the gas turbine engine 20 is not moving. An outlet 30 is downstream of the ejector 31.
[0019] The nose cone 22 is designed to ensure the dirtier air will be delivered into the inlet 50, and the clean air passes into a path into a core inlet 26. Core inlet 26 feeds air
into a compressor section 27, where it is compressed and delivered into a combustor section 25. The air is mixed with fuel and ignited, and products of this combustion pass downstream over turbine rotors 23, driving them to rotate. The engine 20 may be a contra-rotating prop aircraft with a pair of propellers 80 and 82 rotating in opposed directions. The propellers 80 and 82 are driven by the output shaft of a fan drive gear system 200, which in turn is powered by the turbine section 23. Of course, other engine types may benefit from this disclosure.
[0020] Figure 2 shows a detail of the nose cone 22. Nose cone 22 is shaped such that it has the highest or most radially outward point 100 which is radially further outward than an inner point 101 of a manifold 102 leading into the compressor 27. As is known, the gas turbine engine rotates upon an axis x (Fig. 1) and the "radially outward" position is relative to the axis x. Of course, some impurities or dirt may still be delivered into the core inlet 26. However, due to the shape and positioning of the structure, the heavier particles containing impurities are generally directed radially outwardly of the core inlet 26, and into the inlet 50 of the manifold 28. That is, the majority of the impurities will be passed into the manifold 28, compared to what is passed into the core inlet 26.
[0021] As shown in Figure 3A, the manifold 28 includes a circumferentially extending portion 31 which surrounds a circumference of gas turbine engine 20 for 360 degrees about axis x. The inlet end 50 is not shown, but is generally open (see Figure 2), while the downstream end is closed as illustrated in this Figure. The circumferentially extending portion feeds into a circumferentially limited outlet 29 which passes air across the heat exchanger 32. Figure 3B shows another view of the same structure.
[0022] The present invention now utilizes the inlet particle separator to perform a thermal management function and, thus, the efficiency of the overall operation of the gas turbine engine is improved.
[0023] Although an embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.
Claims
1. A gas turbine engine comprising:
a nose cone at an inlet end, and spaced radially inwardly of a nacelle;
a compressor downstream of said nose cone, and a core inlet for delivering air downstream of said nose cone into said compressor; and
an inlet particle separator including a manifold for delivering air radially outwardly of said core inlet, said air delivered by the inlet particle separator passing over a heat exchanger before passing to an outlet.
2. The gas turbine engine as set forth in claim 1, wherein said heat exchanger cools oil associated with a gear reduction on the gas turbine engine.
3. The gas turbine engine as set forth in claim 1 wherein said compressor rotating about a central axis of the engine, and said nose cone has a radially outermost portion which is radially outward of a radially inner end of said core inlet, and such that air having heavier particles is generally directed radially outwardly of said core inlet and into said inlet particle separator.
4. The gas turbine engine as set forth in claim 1, wherein said manifold extends for 360 degrees about said axis of rotation.
5. The gas turbine engine set forth in claim 4, wherein said manifold having an open inlet at an upstream end, and a downstream outlet over a limited portion of the 360 degrees of the circumferentially extending portion.
6. The gas turbine engine as set forth in claim 1, wherein an ejector is positioned downstream of said heat exchanger, said ejector for selectively driving air across the heat exchanger.
7. The gas turbine engine as set forth in claim 1, wherein a turbine section is downstream of said compressor and drives propellers.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/662,802 US20140119903A1 (en) | 2012-10-29 | 2012-10-29 | Gas Turbine Engine With Inlet Particle Separator and Thermal Management |
US13/662,802 | 2012-10-29 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2014078003A2 true WO2014078003A2 (en) | 2014-05-22 |
WO2014078003A3 WO2014078003A3 (en) | 2014-08-07 |
Family
ID=50547388
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2013/065337 WO2014078003A2 (en) | 2012-10-29 | 2013-10-17 | Gas turbine engine with inlet particle separator and thermal management |
Country Status (2)
Country | Link |
---|---|
US (1) | US20140119903A1 (en) |
WO (1) | WO2014078003A2 (en) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014092778A1 (en) * | 2012-12-10 | 2014-06-19 | United Technologies Corporation | Dual filtration particle separator |
WO2014137417A1 (en) * | 2013-03-05 | 2014-09-12 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine heat exchanger system |
FR3009583B1 (en) * | 2013-08-09 | 2015-07-31 | Snecma | TURBOMACHINE WITH BODY OF DEVIATION OF FOREIGN OBJECTS |
US10443429B2 (en) * | 2014-02-13 | 2019-10-15 | United Technologies Corporation | Gas turbine nacelle ventilation manifold having a circumferential varying cross-sectional area |
FR3043723B1 (en) * | 2015-11-13 | 2017-11-24 | Snecma | PROPELLER ASSEMBLY OF AN AIRCRAFT COMPRISING A GAS GENERATOR, TWO DEPTH BLOWERS AND AN AIR INLET HANDLE |
KR101887806B1 (en) | 2017-04-06 | 2018-08-10 | 두산중공업 주식회사 | a particle separator of gas turbine and a gas turbine comprising it |
US10906657B2 (en) * | 2018-06-19 | 2021-02-02 | Raytheon Technologies Corporation | Aircraft system with distributed propulsion |
US10759545B2 (en) | 2018-06-19 | 2020-09-01 | Raytheon Technologies Corporation | Hybrid electric aircraft system with distributed propulsion |
EP4067236A1 (en) * | 2021-03-29 | 2022-10-05 | Airbus Operations (S.A.S.) | Method for electric propulsion of an aircraft |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4527387A (en) * | 1982-11-26 | 1985-07-09 | General Electric Company | Particle separator scroll vanes |
US4928480A (en) * | 1988-03-04 | 1990-05-29 | General Electric Company | Separator having multiple particle extraction passageways |
US20070186534A1 (en) * | 2005-06-20 | 2007-08-16 | Snyder Philip H | Particle separators for gas turbine engines |
US20090145101A1 (en) * | 2004-12-01 | 2009-06-11 | Gabriel Suciu | Particle separator for tip turbine engine |
US20120159961A1 (en) * | 2010-12-24 | 2012-06-28 | Michael Stephen Krautheim | Gas turbine engine heat exchanger |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4685942A (en) * | 1982-12-27 | 1987-08-11 | General Electric Company | Axial flow inlet particle separator |
FR2788308A1 (en) * | 1999-01-07 | 2000-07-13 | Snecma | COOLING DEVICE FOR A TURBOMACHINE SPEED REDUCER |
GB0617769D0 (en) * | 2006-09-09 | 2006-10-18 | Rolls Royce Plc | An engine |
EP2488739B1 (en) * | 2009-10-16 | 2018-09-12 | Safran Aircraft Engines | Air intake for a as turbine engine within a nacelle |
-
2012
- 2012-10-29 US US13/662,802 patent/US20140119903A1/en not_active Abandoned
-
2013
- 2013-10-17 WO PCT/US2013/065337 patent/WO2014078003A2/en active Application Filing
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4527387A (en) * | 1982-11-26 | 1985-07-09 | General Electric Company | Particle separator scroll vanes |
US4928480A (en) * | 1988-03-04 | 1990-05-29 | General Electric Company | Separator having multiple particle extraction passageways |
US20090145101A1 (en) * | 2004-12-01 | 2009-06-11 | Gabriel Suciu | Particle separator for tip turbine engine |
US20070186534A1 (en) * | 2005-06-20 | 2007-08-16 | Snyder Philip H | Particle separators for gas turbine engines |
US20120159961A1 (en) * | 2010-12-24 | 2012-06-28 | Michael Stephen Krautheim | Gas turbine engine heat exchanger |
Also Published As
Publication number | Publication date |
---|---|
US20140119903A1 (en) | 2014-05-01 |
WO2014078003A3 (en) | 2014-08-07 |
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