CN102910293A - Apu选择性冷却循环 - Google Patents

Apu选择性冷却循环 Download PDF

Info

Publication number
CN102910293A
CN102910293A CN2012102748484A CN201210274848A CN102910293A CN 102910293 A CN102910293 A CN 102910293A CN 2012102748484 A CN2012102748484 A CN 2012102748484A CN 201210274848 A CN201210274848 A CN 201210274848A CN 102910293 A CN102910293 A CN 102910293A
Authority
CN
China
Prior art keywords
apu
temperature
tail bone
challenge
aircraft
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN2012102748484A
Other languages
English (en)
Other versions
CN102910293B (zh
Inventor
B.C.德德
S.H.莱特
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hamilton Sundstrand Corp
Original Assignee
Hamilton Sundstrand Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hamilton Sundstrand Corp filed Critical Hamilton Sundstrand Corp
Publication of CN102910293A publication Critical patent/CN102910293A/zh
Application granted granted Critical
Publication of CN102910293B publication Critical patent/CN102910293B/zh
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
    • 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
    • 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
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • F05D2270/3032—Temperature excessive temperatures, e.g. caused by overheating
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Turbines (AREA)
  • Control Of Eletrric Generators (AREA)
  • Direct Current Feeding And Distribution (AREA)

Abstract

本发明涉及APU选择性冷却循环。具体地，一种APU包括控制器，所述控制器用于控制所述APU上来自相关联飞机的负载。所述控制器还接收关于所述APU周围的温度挑战的信息。如果所述温度挑战超过预定阈值，则所述控制器在减小的负载的情况下以冷却循环操作所述APU以减小相关联尾椎上来自所述APU的热负载。还公开了一种方法。

Description

APU选择性冷却循环
技术领域
本申请涉及辅助功率单元（“APU”），该辅助功率单元在关机时经历冷却循环，不过仅在极端温度条件下才这样。
背景技术
APU是已知的且通常设置在飞机中，并且在主飞机气体涡轮发动机的致动之前被启动。在启动主气体涡轮发动机之前，APU通过发电机提供电功率以供在飞机上使用。另外，APU可供应空气以供在飞机机舱内使用并且用于启动飞机发动机。
一旦主飞机发动机已经启动，则APU可关机。APU通常在刚刚关机之前处于重负载下，这是因为它们正在供应大量的电力加上空气以启动主气体涡轮发动机。因此，它们在关机时可能相当热。
飞机尾椎通常容纳了APU。通常用金属来制造飞机尾椎，然而近来已经用各种纤维复合材料来制造它们。例如，碳纤维材料正在得到使用。
这种碳纤维材料不能承受先前使用的金属尾椎所能承受的高温。例如，铝尾椎可承受450 ℉（232 ℃），而复合材料尾椎仅可承受200 ℉（93 ℃）。
发明内容
一种APU包括控制器，所述控制器用于控制所述APU上来自相关联飞机的负载。所述控制器还接收关于所述APU周围的温度挑战的信息。如果所述温度挑战超过预定阈值，则所述控制器在减小的负载的情况下以冷却循环操作所述APU以减小相关联尾椎上来自所述APU的热负载。还公开了一种方法。
从以下说明和附图可最佳地理解本发明的这些和其它特征，其后是简要描述。
附图说明
图1示意性地示出了飞机尾椎和APU。
图2是流程图。
具体实施方式
APU 22被示出安装在飞机的尾椎20中。如上所述，尾椎20可由复合材料制成，例如碳纤维材料。APU 22包括压缩机24，压缩机24从空气进口26抽吸空气。空气被压缩并且传送通过燃烧室28，然后该燃烧的产物经过涡轮30，然后通过排出喷嘴32离开。
涡轮30驱动压缩机24，并且进一步驱动齿轮箱34，齿轮箱34进而驱动发电机36。发电机36向控制器38提供电力以供飞机上使用。
另外，换向阀40可定位在压缩机24的下游。如图所示，空气42的被压缩机24压缩的一部分也可被输送到飞机。如图所示，在一个实施例中，控制器38还可控制阀40。
温度传感器44被示意性示出，并且也与控制器38连通。温度传感器44可感测环境温度。环境温度可以在尾椎20外侧或内侧。另一个传感器44’可感测排气32中的气体温度。与这两个温度不同，也可以感测指示尾椎20上可能出现的高热负载的其它变量。一般地，这些变量可称为温度挑战（temperature challenge）。
在一个实施例中采用环境温度，而在另一实施例中采用环境温度加上排气温度二者并且将它们与预定阈值进行比较。如果超过了阈值，则APU 22在关机时经历冷却循环。
在冷却循环中，APU 22继续压缩空气，燃烧燃料并且驱动涡轮30，从而驱动压缩机24，然后关机。然而，APU 22上的负载被减小。例如，换向阀40被致动，使得所有空气被引导到燃烧室28中。另外，可减小从发电机36取出的电力或停止从发电机36取出电力。另外，如果在输出轴和齿轮箱之间设置了离合器，则该离合器可在冷却模式期间打开。
这两个步骤均可执行，因为用于APU 22关机的时间通常与飞机上的主气体涡轮发动机正在运转并且从而能够通过自身来供应电力和空气有关。
APU 22在冷却模式中运行达到足以降低APU 22的热量（heat mass）的时间段，使得APU 22可完成冷却而不损坏尾椎20。
冷却循环可潜在地危及涡轮30。然而，不是在每次关闭APU 22时都使用冷却循环，从而对于涡轮30的损坏应当是最小的。
相反，如图2所示，一旦作出了关机决定100，则识别出温度挑战。将温度挑战与相同阈值进行比较102。如果温度挑战（例如，环境和/或排气温度或者一些其它变量）指示了对于尾椎的可能的热损坏，则运行冷却循环104。如果不是这样，则APU仅仅被关闭106。冷却循环可操作达若干分钟，例如小于十分钟并且在大约五分钟的量级上。图2所示的方法可由图1的控制器38执行。选择性地运行冷却循环可减小尾椎20上的热负载并且允许在尾椎20中使用复合材料而不增加热绝缘覆盖层的重量和费用，否则的话，需要热绝缘覆盖层来限制尾椎温度。
虽然已经公开了本发明的实施例，但本领域普通技术人员可认识到某些修改会落入本发明的范围内。为此，应研究所附权利要求以确定本发明的真实范围和内容。

Claims (16)

1.一种辅助功率单元（APU），包括：
压缩机，所述压缩机用于压缩空气并且将其输送到燃烧室中，所述空气在所述燃烧室中与燃料混合并燃烧并且经过涡轮，所述涡轮驱动发电机以产生电力；和
控制器，所述控制器用于控制所述APU上来自相关联飞机的负载，所述控制器还接收关于所述APU周围的温度挑战的信息，如果所述温度挑战超过预定阈值，则所述控制器在所述负载减小的情况下以冷却循环操作所述APU以减小相关联尾椎上来自所述APU的热负载。
2.如权利要求1所述的APU，其中，所述减小的负载包括减小从所述发电机取出到所述相关联飞机的电力的量。
3.如权利要求2所述的APU，其中，阀控制从所述压缩机到所述燃烧室的空气流，并且还用于将所述空气中的一些从所述压缩机传送到所述相关联飞机，在所述冷却循环中，所述阀被致动以减小流向所述飞机的空气流。
4.如权利要求1所述的APU，其中，所述温度挑战通过感测温度来确定。
5.如权利要求4所述的APU，其中，所感测的温度是环境温度。
6.如权利要求5所述的APU，其中，所述环境温度取自所述相关联尾椎的内侧，所述相关联尾椎接收所述APU。
7.如权利要求5所述的APU，其中，所述环境温度取自所述相关联尾椎的外侧，所述相关联尾椎接收所述APU。
8.如权利要求4所述的APU，其中，所感测的温度包括所述涡轮下游的排气温度。
9.一种选择性地冷却辅助功率单元（APU）的方法，包括如下步骤：
操作所述APU，并且识别关机决定；
感测与所述APU相关联的尾椎的温度挑战，将所述温度挑战与阈值进行比较；以及
如果所述温度挑战超过所述预定阈值，则在关机之前以冷却循环操作所述APU，并且如果所述温度挑战未超过所述预定阈值，则不以所述冷却循环操作所述APU。
10.如权利要求9所述的方法，其中，基于环境温度来评估所述温度挑战。
11.如权利要求10所述的方法，其中，所述环境温度取自所述相关联尾椎的内侧，所述相关联尾椎接收所述APU。
12.如权利要求10所述的方法，其中，所述环境温度取自所述相关联尾椎的外侧，所述相关联尾椎接收所述APU。
13.如权利要求10所述的方法，其中，还基于排气温度来评估所述温度挑战。
14.如权利要求9所述的方法，其中，所述冷却循环减小所述APU上来自相关联飞机的负载。
15.如权利要求14所述的方法，其中，在所述冷却循环中，从与所述APU相关联的发电机供应到所述飞机的电力被减小。
16.如权利要求14所述的方法，其中，在所述冷却循环中，从与所述APU相关联的压缩机被转移到所述飞机的空气的体积被减小。
CN201210274848.4A 2011-08-03 2012-08-03 辅助功率单元以及选择性地冷却辅助功率单元的方法 Active CN102910293B (zh)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US13/197178 2011-08-03
US13/197,178 US9188065B2 (en) 2011-08-03 2011-08-03 APU selective cool down cycle
US13/197,178 2011-08-03

Publications (2)

Publication Number Publication Date
CN102910293A true CN102910293A (zh) 2013-02-06
CN102910293B CN102910293B (zh) 2015-10-28

Family

ID=46939469

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201210274848.4A Active CN102910293B (zh) 2011-08-03 2012-08-03 辅助功率单元以及选择性地冷却辅助功率单元的方法

Country Status (4)

Country Link
US (1) US9188065B2 (zh)
EP (1) EP2554482B1 (zh)
CN (1) CN102910293B (zh)
BR (1) BR102012019188B1 (zh)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104724290A (zh) * 2013-12-20 2015-06-24 空中客车营运有限公司 负重承载组件及用于制造负重承载组件的方法
CN107444655A (zh) * 2016-05-26 2017-12-08 哈米尔顿森德斯特兰德公司 使用具有两个涡轮的空气循环机混合放出空气和冲压空气
US11506121B2 (en) 2016-05-26 2022-11-22 Hamilton Sundstrand Corporation Multiple nozzle configurations for a turbine of an environmental control system
US11511867B2 (en) 2016-05-26 2022-11-29 Hamilton Sundstrand Corporation Mixing ram and bleed air in a dual entry turbine system

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3012422B1 (fr) * 2013-10-31 2016-12-09 Microturbo Procede et systeme de generation de puissance auxiliaire dans un aeronef
EP3825531B1 (en) 2016-05-26 2023-05-03 Hamilton Sundstrand Corporation An energy flow of an advanced environmental control system
US10563577B2 (en) 2016-08-22 2020-02-18 United Technologies Corporation Low rotor boost compressor for engine cooling circuit
US11305885B2 (en) 2019-01-10 2022-04-19 Honeywell International Inc. Auxiliary power unit adaptive cooldown cycle system and method

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0968918A2 (en) * 1998-07-01 2000-01-05 The Boeing Company Auxiliary power unit passive cooling system
US6039287A (en) * 1996-08-02 2000-03-21 Alliedsignal Inc. Detachable integral aircraft tailcone and power assembly
CA2703108A1 (en) * 2001-10-29 2003-05-08 Pratt & Whitney Canada Corp. Passive cooling system for auxiliary power unit installation
US7168254B2 (en) * 2004-02-17 2007-01-30 Honeywell International Inc. Control logic for fuel controls on APUs
CN101005987A (zh) * 2004-08-16 2007-07-25 空中客车德国有限公司 飞行器中的空气冷却
US20080057848A1 (en) * 2006-08-31 2008-03-06 Honeywell International, Inc. Venturi gate valve assembly for an auxiliary power unit

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4936748A (en) 1988-11-28 1990-06-26 General Electric Company Auxiliary power source in an unducted fan gas turbine engine
GB9408678D0 (en) 1994-04-30 1994-06-22 Aisin Seiki Gas turbine engine driven auxilliary electric power unit
US5748500A (en) * 1995-11-14 1998-05-05 Electric Power Research Institute, Inc. System to assess the starting performance of a turbine
SG68002A1 (en) 1997-11-25 1999-10-19 Inst Of Microelectronics Natio Cmos compatible integrated pressure sensor
US6625504B2 (en) 2001-03-22 2003-09-23 Honeywell International Inc. Auxiliary power unit engine monitoring system
US6833206B2 (en) 2001-09-28 2004-12-21 Daimlerchrysler Ag Auxiliary power supply for a vehicle with a combustion engine and method for operating same
US6735951B2 (en) 2002-01-04 2004-05-18 Hamilton Sundstrand Corporation Turbocharged auxiliary power unit with controlled high speed spool
US6968701B2 (en) 2002-01-16 2005-11-29 United Technologies Corporation Engine integrated auxiliary power unit
EP1474596A4 (en) * 2002-02-15 2010-07-21 Ebara Corp APPARATUS FOR GAS TURBINE
US7367193B1 (en) 2003-07-23 2008-05-06 Hamilton Sundstrand Corporation Auxiliary power unit control method and system
US7417337B1 (en) * 2003-09-04 2008-08-26 Hamilton Sundstrand Corporation Method and system for facilitating no-break power transfer
US7093447B2 (en) 2004-08-25 2006-08-22 Hamilton Sundstrand Corporation Auxiliary power unit with an oil-free compressor
US7805947B2 (en) 2005-05-19 2010-10-05 Djamal Moulebhar Aircraft with disengageable engine and auxiliary power unit components
ES2316257B1 (es) * 2006-10-31 2010-01-12 Airbus España, S.L. Cono de cola para aeronave con carena movil y estructura de soporte de unidad auxiliar de energia y de sus elementos anexos.
GB2448116B (en) * 2007-04-05 2009-05-27 Rolls Royce Plc Means for cooling a bearing assembly
US8321120B2 (en) * 2009-01-16 2012-11-27 Honeywell International Inc. System and method for starting a gas turbine engine with inoperable exhaust gas turbine temperature sensor
US8510013B2 (en) * 2009-05-04 2013-08-13 General Electric Company Gas turbine shutdown
US8245517B2 (en) * 2009-05-19 2012-08-21 Hamilton Sundstrand Corporation Gas turbine starting with stepping speed control
CH702827A1 (de) * 2010-03-02 2011-09-15 Alstom Technology Ltd Verfahren zum Abkühlen einer Gasturbine.
US8307857B2 (en) * 2010-08-04 2012-11-13 Honeywell International Inc. Insulation assembly for use with an auxiliary power unit having an exhaust muffler

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6039287A (en) * 1996-08-02 2000-03-21 Alliedsignal Inc. Detachable integral aircraft tailcone and power assembly
EP0968918A2 (en) * 1998-07-01 2000-01-05 The Boeing Company Auxiliary power unit passive cooling system
CA2703108A1 (en) * 2001-10-29 2003-05-08 Pratt & Whitney Canada Corp. Passive cooling system for auxiliary power unit installation
US7168254B2 (en) * 2004-02-17 2007-01-30 Honeywell International Inc. Control logic for fuel controls on APUs
CN101005987A (zh) * 2004-08-16 2007-07-25 空中客车德国有限公司 飞行器中的空气冷却
US20080057848A1 (en) * 2006-08-31 2008-03-06 Honeywell International, Inc. Venturi gate valve assembly for an auxiliary power unit

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104724290A (zh) * 2013-12-20 2015-06-24 空中客车营运有限公司 负重承载组件及用于制造负重承载组件的方法
US10081431B2 (en) 2013-12-20 2018-09-25 Airbus Operations Gmbh Load bearing element and a method for manufacturing a load bearing element
CN107444655A (zh) * 2016-05-26 2017-12-08 哈米尔顿森德斯特兰德公司 使用具有两个涡轮的空气循环机混合放出空气和冲压空气
CN107444655B (zh) * 2016-05-26 2022-06-10 哈米尔顿森德斯特兰德公司 使用具有两个涡轮的空气循环机混合放出空气和冲压空气
US11506121B2 (en) 2016-05-26 2022-11-22 Hamilton Sundstrand Corporation Multiple nozzle configurations for a turbine of an environmental control system
US11511867B2 (en) 2016-05-26 2022-11-29 Hamilton Sundstrand Corporation Mixing ram and bleed air in a dual entry turbine system

Also Published As

Publication number Publication date
EP2554482B1 (en) 2014-07-02
US9188065B2 (en) 2015-11-17
CN102910293B (zh) 2015-10-28
BR102012019188A2 (pt) 2014-02-18
US20130031911A1 (en) 2013-02-07
EP2554482A1 (en) 2013-02-06
BR102012019188B1 (pt) 2021-01-12

Similar Documents

Publication Publication Date Title
CN102910293B (zh) 辅助功率单元以及选择性地冷却辅助功率单元的方法
US11939925B2 (en) Descent operation for an aircraft parallel hybrid gas turbine engine propulsion system
CN110615106B (zh) 用于飞机的加压空气系统及相关方法
US10550770B2 (en) Bleed air systems for use with aircraft and related methods
EP2620616B1 (en) Bleed air systems for use with aircrafts and related methods
US20130091850A1 (en) Method and system for reducing hot soakback
EP2727839B1 (en) Method of Controlling an Aircraft Electrical Power Generation System
EP2829706B1 (en) Bleed air systems for use with aircrafts and related methods
EP2669492B1 (en) Gas turbine compressor inlet pressurization and flow control system
EP2789537B1 (en) Aircraft environmental control system inlet flow control
US20170226934A1 (en) Hybridisation of the compressors of a turbojet
US20100170262A1 (en) Aircraft power and thermal management system with electric co-generation
US20170030268A1 (en) Method and arrangement for gas turbine engine surge control
US9470150B2 (en) Gas turbine power augmentation system
US20160237917A1 (en) Method for optimising the specific consumption of a twin helicopter
WO2009060889A1 (ja) ガスタービンの運転制御装置および運転制御方法
CN102953836A (zh) 操作燃气轮机组的方法及实施该方法的燃气轮机组
JP2012522173A (ja) 再熱ガスタービン装置、特に燃料電池を有する同装置
US10151211B2 (en) Apparatus and process for converting an aero gas turbine engine into an industrial gas turbine engine for electric power production
KR102242938B1 (ko) 항공기 터보머신의 비상 시동 시스템 및 방법
CN116163838A (zh) 气体供应系统
US20140298820A1 (en) Gas turbine engine and method for starting same
US11008116B2 (en) Gas turbine auxiliary power unit
RU2480601C2 (ru) Способ управления запуском газотурбинного двигателя
EP4407163A1 (en) Condensation control of steam injected turbine engine

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
C14 Grant of patent or utility model
GR01 Patent grant