CN102673793B - Exhaust ejector system of airplane auxiliary power unit - Google Patents
Exhaust ejector system of airplane auxiliary power unit Download PDFInfo
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- CN102673793B CN102673793B CN201210188903.8A CN201210188903A CN102673793B CN 102673793 B CN102673793 B CN 102673793B CN 201210188903 A CN201210188903 A CN 201210188903A CN 102673793 B CN102673793 B CN 102673793B
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- auxiliary power
- power unit
- cabin
- exhaust
- injector
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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
Technical field
The invention belongs to aviation field, relate to a kind of ejection system for the cooling of aircraft auxiliary power plant aspiration ventilation.
Background technology
On modern times big-and-middle-sized aircraft, auxiliary power unit system has been the standing auxiliary energy system generally adopted.The radical function of auxiliary power unit is to provide bleed and generating.Along with the development of aircraft, bleed and electric energy need to improve constantly, and cause the generator power of auxiliary power unit and upper installation thereof to improve constantly, and bring the problem needing a large amount of forced ventilation cooling.
At present, the auxiliary power unit system on a lot of aircraft is all extracted air from air compressor and is used for ventilating and cooling, and this has no small impact to auxiliary power unit power, reduces the efficiency of auxiliary power unit system.Meanwhile, the combustion gas that auxiliary power unit is discharged directly drains into outside machine, and its energy is not utilized effectively.The high-temperature fuel gas that auxiliary power unit is discharged, also has a great impact surrounding environment and structural life-time.
Summary of the invention
The object of the invention is: provide one that auxiliary power unit can be utilized to be vented kinetic energy, air in injection cabin, realizes the auxiliary power unit exhaust ejector system of ventilating and cooling.
Technical scheme of the present invention is: a kind of Exhaust ejector system of airplane auxiliary power unit, it comprises auxiliary power cabin, cooling admission port, injector, freeing pipe, auxiliary power unit combustion gas spout, wherein, in described auxiliary power cabin, auxiliary power unit is installed, cooling admission port is arranged on aircraft skin, and by cooling induction tract, cooling-air is introduced in auxiliary power cabin, described injector is by the exhaust trumpet of auxiliary power cabin end-contraction, the outlet of this injector is freeing pipe, be arranged on auxiliary power unit combustion gas spout in cabin and be positioned at tubaeform convergence place of injector, and it is coaxial with freeing pipe, and at a distance of entrance certain distance, form injection passage.
In cabin, auxiliary power unit combustion gas spout gos deep into the distance of injector bellmouth entrance between 114mm ~ 165mm.
The caliber of injector freeing pipe is greater than the bore of auxiliary power unit combustion gas spout.
Injector freeing pipe is provided with sound arrester.
The advantage that the present invention has and beneficial effect: the invention by tubaeform eductor design, utilizes auxiliary power unit to be vented kinetic energy and achieves ejector action to gas in cabin, carry out ventilating and cooling, have higher induction efficiency in cabin.It takes full advantage of exhaust energy, and does not need the available energy of loss auxiliary power unit, improves efficiency and the economy of auxiliary power unit system.Meanwhile, to the utilization of exhaust energy, can exhaust temperature be reduced, reduce exhaust high temperature to the impact of surrounding environment, improve the life-span of surrounding structure.
Accompanying drawing explanation
Fig. 1 is the structural representation of Exhaust ejector system of airplane auxiliary power unit of the present invention,
Wherein, 1-cools admission port, 2-auxiliary power unit admission port, 3-auxiliary power unit cabin, 4-injector, 5-freeing pipe, 6-exhaust gas silencer, 7-combustion gas spout, 8-auxiliary power unit.
Detailed description of the invention
Below in conjunction with drawings and Examples, the invention will be further described:
Refer to Fig. 1, it is the structural representation of Exhaust ejector system of airplane auxiliary power unit of the present invention.Described Exhaust ejector system of airplane auxiliary power unit comprises auxiliary power cabin 3, cooling admission port 1, injector 4, freeing pipe 5, auxiliary power unit combustion gas spout 7.Wherein, described auxiliary power cabin is hollow structure, for installing auxiliary power unit.Cooling admission port 1 is arranged on aircraft skin, and is introduced in auxiliary power cabin by cooling-air by cooling induction tract.Injector 4 is for there being the exhaust trumpet of auxiliary power cabin end-contraction, and the outlet of this injector 4 is freeing pipe 5, is provided with sound arrester 6 above.Be arranged on cabin 1 auxiliary power unit combustion gas spout 7 and be positioned at tubaeform convergence place of injector, and keep certain distance, to form injection passage at a distance of entrance.In addition, the caliber of injector freeing pipe is greater than the bore of auxiliary power unit combustion gas spout 7, to ensure injection performance.
During work, extraneous air enters in cabin from cooling admission port, cools auxiliary power unit in cabin.And during auxiliary power unit work, high temperature and high speed combustion gas sprays from spout, enters the freeing pipe of injector.Between spout and injector, high-speed fuel gas forms jet, exhaust skin and surrounding air blending, and brings surrounding air into injector freeing pipe, thus forms ejector action to air in cabin, realizes the lasting cooling to auxiliary power unit.
Claims (4)
1. an Exhaust ejector system of airplane auxiliary power unit, it is characterized in that: comprise auxiliary power cabin (3), cooling admission port (1), injector (4), freeing pipe (5), auxiliary power unit combustion gas spout (7), wherein, in described auxiliary power cabin, auxiliary power unit is installed, cooling admission port (1) is arranged on aircraft skin, and by cooling induction tract, cooling-air is introduced in auxiliary power cabin, described injector (4) is by the exhaust trumpet of auxiliary power cabin end-contraction, the outlet of this injector (4) is freeing pipe (5), be arranged on auxiliary power unit combustion gas spout (7) in cabin and be positioned at tubaeform convergence place of injector, and it is coaxial with freeing pipe, and at a distance of entrance certain distance, form injection passage.
2. Exhaust ejector system of airplane auxiliary power unit according to claim 1, is characterized in that: in cabin, auxiliary power unit combustion gas spout (7) puts in the distance of injector bellmouth entrance between 114mm ~ 165mm.
3. Exhaust ejector system of airplane auxiliary power unit according to claim 2, is characterized in that: the caliber of injector freeing pipe is greater than the bore of auxiliary power unit combustion gas spout (7).
4. Exhaust ejector system of airplane auxiliary power unit according to claim 3, is characterized in that: injector freeing pipe is provided with sound arrester (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210188903.8A CN102673793B (en) | 2012-06-08 | 2012-06-08 | Exhaust ejector system of airplane auxiliary power unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210188903.8A CN102673793B (en) | 2012-06-08 | 2012-06-08 | Exhaust ejector system of airplane auxiliary power unit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102673793A CN102673793A (en) | 2012-09-19 |
| CN102673793B true CN102673793B (en) | 2015-04-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210188903.8A Active CN102673793B (en) | 2012-06-08 | 2012-06-08 | Exhaust ejector system of airplane auxiliary power unit |
Country Status (1)
| Country | Link |
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| CN (1) | CN102673793B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2801984C1 (en) * | 2022-12-28 | 2023-08-22 | Публичное акционерное общество "Объединенная авиастроительная корпорация" (ПАО "ОАК") | System of air exhaust jet deflectors of heat exchanger |
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| US9255664B2 (en) * | 2012-12-24 | 2016-02-09 | General Electric Company | Cryogenic fuel system with auxiliary power provided by boil-off gas |
| US10267191B2 (en) | 2015-08-07 | 2019-04-23 | Pratt & Whitney Canada Corp. | Turboprop 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 |
| 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 |
| CN106882400B (en) * | 2017-03-14 | 2018-06-22 | 清华大学 | A kind of film cooling system and method containing injector |
| CN107416214B (en) * | 2017-06-29 | 2020-02-21 | 南京航空航天大学 | Air inlet ventilation structure for auxiliary power system of airplane |
| CN108082503A (en) * | 2017-11-30 | 2018-05-29 | 江西洪都航空工业集团有限责任公司 | A kind of ventilating and cooling and exhaust system for aircraft auxiliary power plant |
| CN108263622A (en) * | 2017-12-27 | 2018-07-10 | 彩虹无人机科技有限公司 | A kind of dopey active cooling device |
| CN108408036A (en) * | 2018-03-07 | 2018-08-17 | 天津曙光天成科技有限公司 | A kind of multi-rotor unmanned aerial vehicle |
| CN108266273A (en) * | 2018-03-07 | 2018-07-10 | 天津曙光天成科技有限公司 | A kind of engine heat dissipating device and unmanned plane |
| CN109573074A (en) * | 2018-11-30 | 2019-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of oil cooling system for aircraft auxiliary power plant |
| CN109649667A (en) * | 2018-12-20 | 2019-04-19 | 中国航空工业集团公司西安飞机设计研究所 | A kind of method of ventilation of aircraft engine nacelle |
| CN110803288A (en) * | 2019-10-25 | 2020-02-18 | 中航通飞研究院有限公司 | Heating, injecting and mixing device for cabin |
| CN111806700B (en) * | 2020-07-08 | 2023-04-07 | 中国商用飞机有限责任公司 | Ventilation system suitable for air conditioning component cabin of aircraft and aircraft comprising same |
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| EP0807576A2 (en) * | 1996-05-15 | 1997-11-19 | DaimlerChrysler 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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2012
- 2012-06-08 CN CN201210188903.8A patent/CN102673793B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0807576A2 (en) * | 1996-05-15 | 1997-11-19 | DaimlerChrysler 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 (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2801984C1 (en) * | 2022-12-28 | 2023-08-22 | Публичное акционерное общество "Объединенная авиастроительная корпорация" (ПАО "ОАК") | System of air exhaust jet deflectors of heat exchanger |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102673793A (en) | 2012-09-19 |
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