WO2001062592A2 - Inlet vortex bustor and ice protector for auxiliary power units - Google Patents
Inlet vortex bustor and ice protector for auxiliary power units Download PDFInfo
- Publication number
- WO2001062592A2 WO2001062592A2 PCT/US2001/005838 US0105838W WO0162592A2 WO 2001062592 A2 WO2001062592 A2 WO 2001062592A2 US 0105838 W US0105838 W US 0105838W WO 0162592 A2 WO0162592 A2 WO 0162592A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- door
- intake
- assembly
- auxiliary power
- bustor
- Prior art date
Links
- 230000001012 protector Effects 0.000 title description 2
- 239000002245 particle Substances 0.000 claims description 3
- 239000007787 solid Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Classifications
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/32—Inducing air flow by fluid jet, e.g. ejector action
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0213—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for auxiliary power units (APU's)
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
- B64D2041/002—Mounting arrangements for auxiliary power units (APU's)
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
- F05D2260/601—Fluid transfer using an ejector or a jet pump
Definitions
- This invention relates to inlets for auxiliary power units mounted in airplanes.
- Airplanes often have an on-board auxiliary power unit to provide electrical power and compressed air to various systems throughout the airplane.
- the auxiliary power unit is the main source of power to drive the environmental control systems, air driven hydraulic pumps, and the starters for the engines.
- Auxiliary power units may also provide pneumatic and electric power during flight.
- an intake duct 30 extends between an intake opening 32 in the exterior surface 16 of the tailcone and the air inlet of the auxiliary power unit 10.
- the intake duct 30 defines an airflow passage 34 through which the auxiliary power unit 10 draws in air.
- An inlet door 33 is pivotally attached to the airplane 14 at the aft end of the opening 32. When the inlet door 33 is open, air flows in the direction of the arrows under the influence of the auxiliary power unit itself (ground operation) or the airstream of the airplane and the auxiliary power unit (flight operation).
- inlet doors also referred to as scoops and typically comprise a closing wall contoured to the fuselage and have channel forming side plates contoured to the side walls of the inlet against which they fit upon closing.
- An example of such an inlet door is disclosed in Vanderleest et al,
- An object of the present invention is to provide an inlet door assembly that does not generate corner vortices during ground operations.
- the present invention meets this objective by providing an air inlet assembly for bringing air to an auxiliary power unit mounted in the compartment of an aircraft.
- the assembly includes a duct extending from an intake contoured to conform to the to the aircraft fuselage to an exit coupled to the inlet plenum of the auxiliary power unit.
- FIG. 1 is a cross-sectional schematic showing an auxiliary power unit mounted in the tailcone of an airplane.
- FIG. 2 is a perspective view of the auxiliary power unit intake duct having the vortex bustor contemplated by the present invention.
- FIGs. 3A and 3B are cross-sectional schematics showing the intake duct of FIG. 2 in both the open and closed position.
- FIGs. 4A and 4B show computer generated maps of the airflow entering the auxiliary power unit compressors with and without the vortex bustor contemplated by the present invention.
- FIG. 5 is a cross-sectional schematic of an alternative embodiment of vortex bustor of FIG. 2.
- FIG. 6 is a perspective view of the vortex bustor of FIG. 5.
- an auxiliary power unit 10 includes a load compressor 20, a power compressor 22 and a turbine 24.
- the auxiliary power unit 10 is positioned in a compartment 12, which is located in the aft fuselage of the airplane 14.
- the compartment 12 is separated from the rest of the fuselage by a firewall 18, and the exterior surfaces 16 of the airplane form the remaining walls of the compartment 12.
- An intake duct 30 extends between an intake opening 32 in the exterior surface 16 and the auxiliary power unit 10.
- the intake duct 30 defines an airflow passage 34 through which the auxiliary power unit 10 draws its combustion air.
- An inlet door 33 is pivotally attached to the airplane 14 at its trailing edge 31 to open and close the inlet opening 32. When the inlet door 33 is open as shown in FIG. 1 , air will flow in the direction of the arrows under the influence of the auxiliary power unit itself (ground operation) or the airstream of the airplane and the auxiliary power unit (flight operation).
- An inlet scoop 60 is mounted in the intake duct 30 to divert a portion of the air flowing through the air passage 34 into the compartment 12.
- the inlet scoop 60 starts to extend outwardly into the air passage 34 from a point 63 downstream from an outlet 50.
- the scoop 60 then extends upstream through the air passage to its mouth 64.
- the scoop 60 defines an airflow passage 66 through which a portion of the airflow in the airflow passage 34 is diverted through the outlet 50 and into the compartment 12.
- the air is directed from the outlet 50 to a first side 27 of the oil cooler 26.
- An eductor 70 is positioned along the exhaust passage 74 of the turbine 24.
- a vacuum duct 80 is positioned between the eductor 70 and a second side 28 of the oil cooler 26.
- the eductor 70 creates a low-pressure region in the vacuum duct 80.
- the vacuum duct 80 By positioning the vacuum duct 80 on the second side 28 of the oil cooler 26, the low-pressure region in the vacuum duct assists the scoop 60 in drawing air across the oil cooler 26.
- the first side 27 is an exterior side of the oil cooler facing the compartment 12 and the second side 28 is an interior side facing the auxiliary power unit 10. The cooling air is then mixed with the exhaust from the auxiliary power unit 10 and expelled into the ambient environment.
- the intake duct 30 extends has a flange 80 that mates to the inlet plenum of the auxiliary power unit and sidewalls 37 that extend from the flange 80 to the intake opening 32.
- the intake opening 32 is defined by an interior lip 82 that is bounded by outwardly extending wall 84. Upon mounting into the tailcone, the outer surface of the wall 84 abuts against the aircraft skin.
- Mounted to the aft side of the lip 82 is the inlet door or scoop 33.
- the inlet door 33 has a closing wall 90 and two side walls 92 and 94. A more detailed description of the inlet door 33 and how it is mounted can be found in Vanderleest, U.S. Patent No. 4,418,879 which is hereby incorporated by reference.
- the vortex bustor 100 comprises main plate 102 having inwardly extending side walls 104, 106.
- the plate 102 is solid.
- the plate 102 can have a screened portion.
- One end of the plate 102. is hinged to the lip 82 in a manner similar to the hinged connection of the inlet door 33.
- the opposite side of the plate 102 has a slot to accommodate an actuator 110 that opens and closes the door 33.
- the ends of the side walls 104 and 106 are hinged to the inner side of the side walls 92 and 94 respectively so that as the walls 92,94 move in and out the walls 104 and 106 move in and out.
- FIGs. 3A and 3B show the inlet door 33 and vortex bustor 100 in both the open and closed position.
- air flowing around the sidewalls is blocked by the side walls 104 and 106 thus eliminating corner vortices.
- the vortex bustor 100 is sized to fold down and tuck under the door 33 as door 33 closes flush with the aircraft skin as shown in FIG. 3B.
- FIGs. 4A and 4B show computer generated maps of the air flowing into the compressor 22.
- FIG. 4B represents the configuration of an inlet door 33 having sidewalls 92, 94 but no vortex bustor 100.
- Four vortices appear 120, 122, 124, 126. Two of these 126, 124 are associated with the auxiliary power unit inlet plenum where the air undergoes a 90 degree turn as in flows from the duct 30 to the compressor 22.
- the other two vortices 122, 120 are associated with air flowing around the side walls 92, 94 and are referred to as corner vortices.
- FIG. 4A represents the configuration of FIG. 4B with the addition of the vortex bustor 100. Viewing FIG.
- the plenum effect vortices 126, 124 are still there, but the inlet corner vortices 122, 120 have been eliminated. Because the corner vortices 122, 120 are gone, the plenum vortices 126,124 readjust spatially. Thus, comparing FIG. 4A to 4B, the plenum vortices have repositioned themselves.
- an alternative vortex bustor 200 is fixedly mounted to the skin 16 of the aircraft forward of the lip 82 so has not to interfere with the opening and closing of the door 33.
- the vortex bustor 200 comprises main plate 202 having side walls 204, 206.
- the plate 202 is solid.
- the plate 202 can have a screened portion.
- the side wall 204 and 206 are spaced apart so as to surround the wall 84 as they extent toward the inlet door side plates 92,94. To reduce drag the walls 204, 206 are tapered.
- another advantage to the vortex bustors 100 and 200 is that if you cutback the scoop 60, then during inflight operation ice particles flowing along the surface of the airplane, will be deflected into the scoop 60 and from there into the eductor 79 where they will melt. This avoids the ice particles from being ingested by the compressor 20 and 22 where they can damage the compressor blades.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Air-Flow Control Members (AREA)
- Exhaust Gas After Treatment (AREA)
- Exhaust-Gas Circulating Devices (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
- Superstructure Of Vehicle (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA002401649A CA2401649C (en) | 2000-02-25 | 2001-02-21 | Inlet vortex bustor and ice protector for auxiliary power units |
EP01911137A EP1257468B1 (en) | 2000-02-25 | 2001-02-21 | Inlet vortex bustor and ice protector for auxiliary power units |
DE60107658T DE60107658T2 (en) | 2000-02-25 | 2001-02-21 | AIR INTAKE DIFFUSER AND IGNITION DEVICE FOR AUXILIARY ENGINES |
AT01911137T ATE284348T1 (en) | 2000-02-25 | 2001-02-21 | AIR INLET SWIRL DAMPER AND ICE PROTECTION DEVICE FOR AUXILIARY ENGINE |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/514,203 US6264137B1 (en) | 2000-02-25 | 2000-02-25 | Inlet vortex bustor and ice protector for auxiliary power units |
US09/514,203 | 2000-02-25 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2001062592A2 true WO2001062592A2 (en) | 2001-08-30 |
WO2001062592A3 WO2001062592A3 (en) | 2002-03-28 |
Family
ID=24046212
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2001/005838 WO2001062592A2 (en) | 2000-02-25 | 2001-02-21 | Inlet vortex bustor and ice protector for auxiliary power units |
Country Status (6)
Country | Link |
---|---|
US (1) | US6264137B1 (en) |
EP (1) | EP1257468B1 (en) |
AT (1) | ATE284348T1 (en) |
CA (1) | CA2401649C (en) |
DE (1) | DE60107658T2 (en) |
WO (1) | WO2001062592A2 (en) |
Cited By (3)
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---|---|---|---|---|
WO2002074621A1 (en) * | 2001-03-15 | 2002-09-26 | Honeywell International Inc. | Plenum entry bulk swirl generator |
DE102008002205A1 (en) * | 2008-06-04 | 2009-12-17 | Airbus Deutschland Gmbh | Air intake valve for an aircraft and method of manufacturing an air intake valve |
KR101211541B1 (en) | 2005-05-04 | 2012-12-12 | 한국항공우주산업 주식회사 | Structure for automatically opening and closing the scoop for an airplane |
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US6651929B2 (en) * | 2001-10-29 | 2003-11-25 | Pratt & Whitney Canada Corp. | Passive cooling system for auxiliary power unit installation |
DE10200459A1 (en) * | 2002-01-09 | 2003-07-24 | Airbus Gmbh | Air intake for an auxiliary engine in an aircraft |
US7210653B2 (en) * | 2002-10-22 | 2007-05-01 | The Boeing Company | Electric-based secondary power system architectures for aircraft |
US6896003B1 (en) * | 2002-11-12 | 2005-05-24 | The United States Of America As Represented By The Secretary Of The Navy | High efficiency low actuation force inlet door |
US7093666B2 (en) * | 2003-02-20 | 2006-08-22 | Pratt & Whitney Canada Corp. | Apparatus and method for providing fireproofing to an aircraft auxiliary power unit |
US6883751B2 (en) * | 2003-05-02 | 2005-04-26 | The Boeing Company | Apparatus and method for preventing foreign object damage to an aircraft |
US7014144B2 (en) * | 2003-07-22 | 2006-03-21 | Honeywell International, Inc. | Dual action inlet door and method for use thereof |
US7040576B2 (en) * | 2003-12-18 | 2006-05-09 | Pratt & Whitney Canada Corp. | Fire shield apparatus and method |
US20060061107A1 (en) * | 2004-03-24 | 2006-03-23 | Paul Cadaret | Energy scavenging methods and apparatus |
US7192462B2 (en) * | 2004-04-14 | 2007-03-20 | Aerospace Filtration Systems, Inc. | Engine air filter and sealing system |
US7137240B2 (en) * | 2004-08-18 | 2006-11-21 | Hamilton Sundstrand Corporation | Inlet muff anti-icing system for an auxiliary power unit |
US7364116B2 (en) * | 2004-09-27 | 2008-04-29 | The Boeing Company | Automatic control systems for aircraft auxiliary power units, and associated methods |
US7790878B2 (en) * | 2004-10-22 | 2010-09-07 | Alnylam Pharmaceuticals, Inc. | RNAi modulation of RSV, PIV and other respiratory viruses and uses thereof |
US7344107B2 (en) * | 2004-10-26 | 2008-03-18 | The Boeing Company | Dual flow APU inlet and associated systems and methods |
US7513119B2 (en) * | 2005-02-03 | 2009-04-07 | The Boeing Company | Systems and methods for starting aircraft engines |
US7600713B2 (en) * | 2005-03-04 | 2009-10-13 | Honeywell International Inc. | Pre-hung inlet door system |
US7540142B2 (en) * | 2006-02-21 | 2009-06-02 | Honeywell International Inc. | Multiple auxiliary power unit system inlet ducts controlled by a single actuator |
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US7600714B2 (en) * | 2006-04-20 | 2009-10-13 | Honeywell International Inc. | Diffusing air inlet door assembly |
US20080203218A1 (en) * | 2007-02-26 | 2008-08-28 | Honeywell International, Inc. | Systems And Methods For Reducing Pressure Loss Of Air Flowing From A First Area To A Second Area |
US8657567B2 (en) * | 2007-05-29 | 2014-02-25 | United Technologies Corporation | Nacelle compartment plenum for bleed air flow delivery system |
US7708230B2 (en) * | 2007-05-29 | 2010-05-04 | United Technologies Corporation | Flow distribution system for inlet flow control |
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US8141816B2 (en) * | 2008-04-30 | 2012-03-27 | Honeywell International Inc. | AFT inlet duct mounted door actuator |
US8079550B2 (en) * | 2008-07-18 | 2011-12-20 | Hamilton Sundstrand Corporation | Auxiliary power unit inlet door actuation mechanism |
US8113767B2 (en) * | 2008-09-15 | 2012-02-14 | Hamilton Sundstrand Corporation | Auxiliary power unit inlet duct with acoustic silencing |
US8141818B2 (en) * | 2009-07-02 | 2012-03-27 | Honeywell International Inc. | Ram door assemblies |
US8657227B1 (en) | 2009-09-11 | 2014-02-25 | The Boeing Company | Independent power generation in aircraft |
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US8738268B2 (en) | 2011-03-10 | 2014-05-27 | The Boeing Company | Vehicle electrical power management and distribution |
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US8444083B2 (en) * | 2011-06-30 | 2013-05-21 | Hamilton Sundstrand Corporation | Auxiliary power unit inlet |
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US9957060B2 (en) * | 2012-03-21 | 2018-05-01 | Hamilton Sundstrand Corporation | Deployable inlet scoop for an inboard ram air turbine |
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US9719352B2 (en) | 2014-12-17 | 2017-08-01 | Honeywell International Inc. | Compartment based inlet particle separator system |
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US10279920B1 (en) * | 2018-02-27 | 2019-05-07 | Brant Farrell | Foreign object debris barrier filter apparatus for an aircraft intake system |
CN110513162B (en) | 2018-05-22 | 2022-06-14 | 通用电气公司 | Bucket type entrance |
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CN109465791B (en) * | 2018-11-14 | 2020-11-03 | 中国直升机设计研究所 | Helicopter air inlet channel assembly assembling jig |
CN112960123B (en) * | 2021-03-26 | 2023-11-07 | 中国商用飞机有限责任公司 | Intake valve device of auxiliary power unit of airplane |
CN113772106B (en) * | 2021-09-15 | 2024-03-19 | 中国航空工业集团公司西安飞机设计研究所 | Combined auxiliary power air inlet device |
US11999500B2 (en) * | 2021-10-20 | 2024-06-04 | General Electric Company | Deployable inlet assembly for aerial vehicle |
GB2615834A (en) * | 2022-02-15 | 2023-08-23 | Bae Systems Plc | Cavity acoustic tones suppression |
EP4282765A1 (en) * | 2022-05-27 | 2023-11-29 | Airbus Operations, S.L.U. | Auxiliary power unit system of an aircraft |
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2000
- 2000-02-25 US US09/514,203 patent/US6264137B1/en not_active Expired - Fee Related
-
2001
- 2001-02-21 AT AT01911137T patent/ATE284348T1/en not_active IP Right Cessation
- 2001-02-21 CA CA002401649A patent/CA2401649C/en not_active Expired - Fee Related
- 2001-02-21 EP EP01911137A patent/EP1257468B1/en not_active Expired - Lifetime
- 2001-02-21 WO PCT/US2001/005838 patent/WO2001062592A2/en active IP Right Grant
- 2001-02-21 DE DE60107658T patent/DE60107658T2/en not_active Expired - Lifetime
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US4418879A (en) | 1980-12-29 | 1983-12-06 | The Boeing Company | Scoop and inlet for auxiliary power units and method |
US5655359A (en) | 1995-05-15 | 1997-08-12 | The Boeing Company | Passive cooling device and method for cooling an auxiliary power unit on an airplane |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2002074621A1 (en) * | 2001-03-15 | 2002-09-26 | Honeywell International Inc. | Plenum entry bulk swirl generator |
US6520738B2 (en) | 2001-03-15 | 2003-02-18 | Honeywell International, Inc. | Plenum entry bulk swirl generator |
KR101211541B1 (en) | 2005-05-04 | 2012-12-12 | 한국항공우주산업 주식회사 | Structure for automatically opening and closing the scoop for an airplane |
DE102008002205A1 (en) * | 2008-06-04 | 2009-12-17 | Airbus Deutschland Gmbh | Air intake valve for an aircraft and method of manufacturing an air intake valve |
US8403264B2 (en) | 2008-06-04 | 2013-03-26 | Airbus Operations Gmbh | Air inlet valve for an airplane and manufacturing method for an air inlet valve |
Also Published As
Publication number | Publication date |
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DE60107658D1 (en) | 2005-01-13 |
DE60107658T2 (en) | 2006-03-16 |
CA2401649A1 (en) | 2001-08-30 |
EP1257468A2 (en) | 2002-11-20 |
US6264137B1 (en) | 2001-07-24 |
ATE284348T1 (en) | 2004-12-15 |
CA2401649C (en) | 2007-05-15 |
WO2001062592A3 (en) | 2002-03-28 |
EP1257468B1 (en) | 2004-12-08 |
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