CN102673793A - Exhaust ejector system of airplane auxiliary power unit - Google Patents

Exhaust ejector system of airplane auxiliary power unit Download PDF

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Publication number
CN102673793A
CN102673793A CN2012101889038A CN201210188903A CN102673793A CN 102673793 A CN102673793 A CN 102673793A CN 2012101889038 A CN2012101889038 A CN 2012101889038A CN 201210188903 A CN201210188903 A CN 201210188903A CN 102673793 A CN102673793 A CN 102673793A
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China
Prior art keywords
auxiliary power
ejector
power unit
exhaust
exhaust pipe
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CN2012101889038A
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Chinese (zh)
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CN102673793B (en
Inventor
吕其明
钟剑龙
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中国航空工业集团公司西安飞机设计研究所
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Priority to CN201210188903.8A priority Critical patent/CN102673793B/en
Publication of CN102673793A publication Critical patent/CN102673793A/en
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Abstract

The invention belongs to the field of aviation, and relates to an exhaust ejector system of an airplane auxiliary power unit. The exhaust ejector system of the airplane auxiliary power unit comprises an auxiliary power cabin, a cooling air inlet, an ejector, an exhaust pipe and a gas nozzle of the auxiliary power unit, wherein the auxiliary power unit is installed in the auxiliary power cabin, the cooling air inlet is installed in an airplane skin, and the cooling air is introduced into the auxiliary power cabin through a cooling air inlet pipeline. The ejector is a tapered exhaust pipe which is formed by contracting from the tail end of the auxiliary power cabin, and the outlet of the ejector is the exhaust pipe. The gas nozzle of the auxiliary power unit which is arranged in the cabin is positioned at the tapered convergent part of the ejector, is coaxial with the exhaust pipe, and keeps a certain distance from the inlet, so an ejector passage is formed. The exhaust ejector system utilizes the exhaust function of the auxiliary power unit, ejects the air in the cabin to realize aeration-cooling, so the efficiency and the economical efficiency of the system of the auxiliary power unit are effectively improved.

Description

一种飞机辅助动力装置排气引射系统 An aircraft auxiliary power unit exhaust ejector system

技术领域 FIELD

[0001] 本发明属于航空领域,涉及ー种用于飞机辅助动カ装置排气通风冷却的引射系统。 [0001] The present invention belongs to the field of aviation, airplanes relates ー species for the auxiliary cooling of the exhaust ventilation system ejector means movable ka.

背景技术 Background technique

[0002] 在现代大中型飞机上,辅助动力装置系统已经是普遍采用的常备辅助能源系统。 [0002] In modern medium-sized aircraft, auxiliary power unit system is already standing auxiliary energy system widely used. 辅助动力装置的主要功能是提供引气和发电。 The main function of the auxiliary power unit to provide a bleed air and power generation. 随着飞机的发展,引气和电能需要不断提高,导致辅助动カ装置及其上安装的发电机功率不断提高,带来需要大量強迫通风冷却的问题。 With the development of the aircraft, bleed air and electrical energy needs continue to increase, resulting in an auxiliary power generator device and move on ka installation continues to improve, bring issues to a large number of forced air cooling.

[0003]目前,很多飞机上的辅助动力装置系统都从压气机提取空气用于通风冷却,这对辅助动力装置功率有不小的影响,降低了辅助动力装置系统的效率。 [0003] Currently, a lot of auxiliary power unit on the aircraft systems are extracted from the ventilation air is used for cooling the compressor, which is not a small influence on the auxiliary power unit power, reducing the efficiency of the auxiliary power unit system. 同吋,辅助动力装置排出的燃气直接排至机外,其能量没有得到有效利用。 Inch with APU exhaust gas is directly discharged to outside the machine, its energy is not effectively utilized. 辅助动力装置排出的高温燃气,对周围环境及结构寿命也有很大的影响。 Hot gas discharged from the auxiliary power unit, but also have a great impact on the surrounding environment and the life of the structure.

发明内容 SUMMARY

[0004] 本发明的目的是:提供一种能够利用辅助动力装置排气动能,引射舱内空气,实现通风冷却的辅助动力装置排气引射系统。 [0004] The object of the present invention are: to provide a kinetic energy of the exhaust gas by the auxiliary power unit, cabin air ejector, auxiliary power to achieve an exhaust ventilation cooling means ejector system.

[0005] 本发明的技术方案是:一种飞机辅助动力装置排气引射系统,其包括辅助动カ舱、冷却进气ロ、引射器、排气管、辅助动力装置燃气喷ロ,其中,所述辅助动カ舱内安装有辅助动カ装置,冷却进气ロ安装在飞机蒙皮上,并通过冷却进气管道将冷却空气引入辅助动力舱内,所述引射器为由辅助动カ舱末端收缩而成的喇叭形排气管,该引射器的出口即为排气管,设置在舱内辅助动カ装置燃气喷ロ位于引射器喇叭形收敛处,并与排气管同轴,且相距入口一定距离,形成引射通道。 [0005] aspect of the present invention is: an aircraft auxiliary power unit exhaust ejector system, which comprises a movable auxiliary compartment ka, cooling the intake air ro, ejector, an exhaust pipe, an auxiliary power unit gas jet ro, wherein said auxiliary compartment is attached to the movable auxiliary movable ka ka, cooling the intake air ro mounted on the aircraft skin, and the intake duct through the cooling air into the cooling compartment auxiliary power, assisted by the ejector movable ka shrinkage chamber from the end of the exhaust pipe of the horn, which is the ejector outlet exhaust pipe is provided in the cabin an auxiliary gas ejection means movable grades ro convergence of the lead at the transmitter horn, and the exhaust pipe coaxially to and spaced a distance from the inlet, the ejector channel is formed.

[0006] 舱内辅助动カ装置燃气喷ロ深入引射器喇叭形入口的距离在114mm〜165mm之间。 [0006] ka cabin auxiliary means movable between a gas jet ro flared inlet of the ejector depth distance 114mm~165mm.

[0007] 引射器排气管的管径大于辅助动力装置燃气喷ロ的口径。 [0007] The diameter of the ejector tube is greater than the exhaust gas discharge assisting power apparatus ro caliber.

[0008] 引射器排气管上设置有消音装置。 [0008] The ejector exhaust pipe is provided with a muffler device.

[0009] 本发明具有的优点和有益效果:本发明创造性通过喇叭形引射器设计,利用辅助动カ装置排气动能实现了对舱内气体的引射作用,对舱内进行通风冷却,具有较高的引射效率。 [0009] The present invention has advantages and beneficial effects: the present invention by the inventive ejector horn design, the auxiliary exhaust kinetic motion apparatus grades achieved ejector effect of the gas compartment of the cabin for ventilation and cooling, having high ejector efficiency. 其充分利用了排气能量,而不需要损耗辅助动カ装置的有效能量,提高了辅助动力装置系统的效率和经济性。 Which makes full use of the exhaust energy, without loss of effective energy-assisted device is movable grades, improved efficiency and economy of the auxiliary power unit system. 同吋,对排气能量的利用,能够降低排气温度,减小排气高温对周围环境的影响,提高周围结构的寿命。 Inch with, use of the exhaust energy, the temperature of the exhaust gas can be reduced, reducing the impact on the surrounding environment of the high temperature exhaust gas, to improve the life of the surrounding structures.

附图说明 BRIEF DESCRIPTION

[0010] 图I是本发明飞机辅助动カ装置排气引射系统的结构示意图, [0010] Figure I is a plane schematic structural view of the present invention, the auxiliary movable ejector ka means an exhaust system,

[0011] 其中,I-冷却进气ロ、2-辅助动力装置进气ロ、3-辅助动力装置舱、4-引射器、5-排气管、6-排气消音器、7-燃气喷ロ、8-辅助动力装置。 [0011] wherein, I- ro cool the intake air, 2 ro auxiliary power unit intake, 3- auxiliary power unit compartment, the ejector 4-, 5- exhaust pipe, exhaust muffler 6-, 7- gas spray ro, 8 auxiliary power unit.

具体实施方式 Detailed ways

[0012] 下面结合附图和实施例对本发明作进ー步说明: Drawings and embodiments of the present invention will be further described into ー [0012] conjunction with the following:

[0013] 请參阅图1,其是本发明飞机辅助动カ装置排气引射系统的结构示意图。 [0013] Referring to FIG. 1, the present invention is an aircraft which is movable auxiliary means ka emitted exhaust system structure diagram of primers. 所述飞机辅助动力装置排气引射系统包括辅助动カ舱3、冷却进气ロI、引射器4、排气管5、辅助动力装置燃气喷ロ7。 Said aircraft auxiliary power unit exhaust system comprising an auxiliary ejector movable grades compartment 3, cool the intake air ro I, ejector 4, the exhaust pipe 5, a gas jet ro auxiliary power unit 7. 其中,所述辅助动カ舱为中空结构,用于安装辅助动力装置。 Wherein the auxiliary compartment is movable grades hollow structure for mounting an auxiliary power unit. 冷却进气ロI安装在飞机蒙皮上,并通过冷却进气管道将冷却空气引入辅助动カ舱内。 I ro cooling the intake air is mounted on the aircraft skin, and cooled by cooling air intake duct introducing an auxiliary movable ka cabin. 引射器4为有辅助动カ舱末端收缩而成的喇叭形排气管,该引射器4的出口即为排气管5,上面设置有消音装置6。 4 is an ejector movable auxiliary flared end of the exhaust pipe grades shrink compartment formed, the ejector outlet 4 is the exhaust pipe 5, the top 6 is provided with a muffler device. 设置在舱I辅助动力装置燃气喷ロ7位于引射器喇叭形收敛处,并相距入口保持一定距离,以形成引射通道。 Housing I is provided an auxiliary power unit gas discharge horn incorporated ro 7 located at the convergence of the ejector, and maintain a certain distance away from the inlet, to form an ejector passage. 另外,引射器排气管的管径大于辅助动力装置燃气喷ロ7的口径,以保证引射性能。 Further, the diameter of the exhaust pipe of the ejector is greater than ro auxiliary power unit gas discharge aperture 7, to ensure that the ejector performance.

[0014] 工作时外部空气从冷却进气ロ进入舱内,对舱内辅助动力装置进行冷却。 [0014] In operation cooling the intake air from the outside air into the cabin ro, auxiliary power units on the cabin cooling. 而辅助动カ装置工作时,高温高速燃气从喷ロ喷出,进入引射器的排气管。 When the auxiliary device is operated actuator grades, high temperature and high gas discharged from the discharge ro, into the ejector exhaust pipe. 在喷ロ与引射器之间, 高速燃气形成射流,排气外层与周围空气掺混,并将周围空气带入引射器排气管,从而对舱内空气形成引射作用,实现对辅助动力装置的持续冷却。 Between the ejector and the discharge ro, high-speed gas jet is formed, the outer layer of the exhaust gas mixing with the ambient air and ambient air into the ejector exhaust pipe, thereby forming a cabin air ejector effect, to achieve continuously cooling the auxiliary power unit.

Claims (4)

1. 一种飞机辅助动力装置排气引射系统,其特征在于:包括辅助动力舱(3)、冷却进气口(I)、引射器(4)、排气管(5)、辅助动力装置燃气喷口(7),其中,所述辅助动力舱内安装有辅助动力装置,冷却进气口( I)安装在飞机蒙皮上,并通过冷却进气管道将冷却空气引入辅助动力舱内,所述引射器(4)为由辅助动力舱末端收缩而成的喇叭形排气管,该引射器(4)的出口即为排气管(5),设置在舱内辅助动力装置燃气喷口(7)位于引射器喇叭形收敛处,并与排气管同轴,且相距入口一定距离,形成引射通道。 1. An aircraft auxiliary power unit exhaust ejector system, characterized by: comprising an auxiliary power compartment (3), the cooling air inlet (the I), ejector (4), an exhaust pipe (5), an auxiliary power gas nozzle means (7), wherein the auxiliary power cabin mounted auxiliary power unit, the cooling air inlet (I) mounted on the aircraft skin, and the intake duct through the cooling air into the cooling compartment auxiliary power, the ejector (4) is a flared end of the exhaust pipe of the auxiliary power from shrinkage chamber, the outlet of the ejector (4) is the exhaust pipe (5), the auxiliary power unit compartment provided on the gas nozzle (7) located at the convergence of the ejector horn, and coaxial with the exhaust pipe, and spaced a distance from the inlet, the ejector channel is formed.
2.根据权利要求I所述的飞机辅助动力装置排气引射系统,其特征在于:舱内辅助动力装置燃气喷口(7)伸进引射器喇叭形入口的距离在114mm〜165mm之间。 According to claim I of the aircraft auxiliary power unit exhaust ejector system comprising: an auxiliary power unit compartment gas nozzle (7) projects into the ejector between the inlet from 114mm~165mm flared lead.
3.根据权利要求2所述的飞机辅助动力装置排气引射系统,其特征在于:引射器排气管的管径大于辅助动力装置燃气喷口(7)的口径。 The aircraft auxiliary power unit exhaust system of the ejector claim 2, wherein: the ejector exhaust pipe diameter is greater than the auxiliary power unit gas nozzle aperture (7).
4.根据权利要求3所述的飞机辅助动力装置排气引射系统,其特征在于:引射器排气管上设置有消音装置(6)。 4. The aircraft auxiliary power unit exhaust ejector system of claim 3, wherein: means is provided with a muffler (6) on the ejector exhaust pipe.
CN201210188903.8A 2012-06-08 2012-06-08 Exhaust ejector system of airplane auxiliary power unit CN102673793B (en)

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105026267A (en) * 2012-12-24 2015-11-04 通用电气公司 Cryogenic fuel system with auxiliary power provided by boil-off gas
WO2017024394A1 (en) * 2015-08-07 2017-02-16 Pratt & Whitney Canada Corp. Engine assembly with combined engine and cooling exhaust
CN106672248A (en) * 2016-12-26 2017-05-17 中国航空工业集团公司西安飞机设计研究所 Ejection structure
CN106882400A (en) * 2017-03-14 2017-06-23 清华大学 Film cooling system with ejector and method
CN107416214A (en) * 2017-06-29 2017-12-01 南京航空航天大学 Air inlet ventilation structure used for aircraft auxiliary power system
CN108082503A (en) * 2017-11-30 2018-05-29 江西洪都航空工业集团有限责任公司 Ventilation cooling and exhaust system used for airplane auxiliary power device
CN108263622A (en) * 2017-12-27 2018-07-10 彩虹无人机科技有限公司 Active cooling device for low-speed airplane
US10240522B2 (en) 2015-08-07 2019-03-26 Pratt & Whitney Canada Corp. Auxiliary power unit with combined cooling of generator
US10267191B2 (en) 2015-08-07 2019-04-23 Pratt & Whitney Canada Corp. Turboprop engine assembly with combined engine and cooling exhaust

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EP0807576A2 (en) * 1996-05-15 1997-11-19 Daimler-Benz Aerospace Airbus Gesellschaft mit beschränkter Haftung Ejection and oil system for an auxiliary power unit of an aircraft
EP0968918A2 (en) * 1998-07-01 2000-01-05 The Boeing Company Auxiliary power unit passive cooling system
US6651929B2 (en) * 2001-10-29 2003-11-25 Pratt & Whitney Canada Corp. Passive cooling system for auxiliary power unit installation
CN101149025A (en) * 2006-09-20 2008-03-26 涡轮梅坎公司 Gas turbine helicopter engine with noise emission reduced through acoustical treatment of an eductor

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Publication number Priority date Publication date Assignee Title
EP0807576A2 (en) * 1996-05-15 1997-11-19 Daimler-Benz Aerospace Airbus Gesellschaft mit beschränkter Haftung Ejection and oil system for an auxiliary power unit of an aircraft
EP0968918A2 (en) * 1998-07-01 2000-01-05 The Boeing Company Auxiliary power unit passive cooling system
US6651929B2 (en) * 2001-10-29 2003-11-25 Pratt & Whitney Canada Corp. Passive cooling system for auxiliary power unit installation
CN101149025A (en) * 2006-09-20 2008-03-26 涡轮梅坎公司 Gas turbine helicopter engine with noise emission reduced through acoustical treatment of an eductor

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105026267A (en) * 2012-12-24 2015-11-04 通用电气公司 Cryogenic fuel system with auxiliary power provided by boil-off gas
CN105026267B (en) * 2012-12-24 2017-04-19 通用电气公司 Cryogenic fuel system having an auxiliary power provided by the vaporized gas
WO2017024394A1 (en) * 2015-08-07 2017-02-16 Pratt & Whitney Canada Corp. Engine assembly with combined engine and cooling exhaust
US10253726B2 (en) 2015-08-07 2019-04-09 Pratt & Whitney Canada Corp. Engine assembly with combined engine and cooling exhaust
US10267191B2 (en) 2015-08-07 2019-04-23 Pratt & Whitney Canada Corp. Turboprop engine assembly with combined engine and cooling exhaust
US10240522B2 (en) 2015-08-07 2019-03-26 Pratt & Whitney Canada Corp. Auxiliary power unit with combined cooling of generator
CN106672248A (en) * 2016-12-26 2017-05-17 中国航空工业集团公司西安飞机设计研究所 Ejection structure
CN106882400A (en) * 2017-03-14 2017-06-23 清华大学 Film cooling system with ejector and method
CN107416214A (en) * 2017-06-29 2017-12-01 南京航空航天大学 Air inlet ventilation structure used for aircraft auxiliary power system
CN108082503A (en) * 2017-11-30 2018-05-29 江西洪都航空工业集团有限责任公司 Ventilation cooling and exhaust system used for airplane auxiliary power device
CN108263622A (en) * 2017-12-27 2018-07-10 彩虹无人机科技有限公司 Active cooling device for low-speed airplane

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