CN109573074A - A kind of oil cooling system for aircraft auxiliary power plant - Google Patents
A kind of oil cooling system for aircraft auxiliary power plant Download PDFInfo
- Publication number
- CN109573074A CN109573074A CN201811454072.8A CN201811454072A CN109573074A CN 109573074 A CN109573074 A CN 109573074A CN 201811454072 A CN201811454072 A CN 201811454072A CN 109573074 A CN109573074 A CN 109573074A
- Authority
- CN
- China
- Prior art keywords
- oil
- auxiliary power
- heat exchanger
- power unit
- pipe
- 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.)
- Pending
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 27
- 239000007924 injection Substances 0.000 claims abstract description 5
- 238000002347 injection Methods 0.000 claims abstract description 5
- 239000003921 oil Substances 0.000 claims description 55
- 239000010687 lubricating oil Substances 0.000 claims description 27
- 238000002485 combustion reaction Methods 0.000 claims description 9
- 239000002737 fuel gas Substances 0.000 claims description 6
- 230000008676 import Effects 0.000 claims description 5
- 239000000567 combustion gas Substances 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 239000000295 fuel oil Substances 0.000 claims description 2
- 239000003595 mist Substances 0.000 claims description 2
- 239000000203 mixture Substances 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000010773 plant oil Substances 0.000 description 1
Classifications
-
- 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
-
- 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
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
Abstract
A kind of oil cooling system for aircraft auxiliary power plant of the present invention, belongs to aviation accessory power system technical field.The present invention includes air intake duct, heat exchanger, injector, oil pump, oil pipe A, oil pipe B, is installed in aircraft auxiliary power plant cabin together with auxiliary power unit.The present invention uses injection radiating mode, and without rotary part, structure is simple, small in size, high reliablity, good cooling results, is the important leverage that auxiliary power unit works normally.
Description
Technical field
A kind of oil cooling system for aircraft auxiliary power plant of the present invention belongs to aviation accessory power system field.
Background technique
Auxiliary power unit is one of the necessary devices of modern Large Civil Aircraft, be mainly used for providing for aircraft auxiliary/
Emergency power supply and compressed air are typically mounted in the auxiliary power unit cabin of airplane tail group.
In the auxiliary power unit course of work, high-speed rotating bearing and motor generate a large amount of heat, these heats by
The lubricating oil circulated is absorbed and is taken away, and temperature increases after lubricating oil absorbs heat, in order to ensure the normal work of auxiliary power unit
Make, design has oil cooling system for being cooled down lubricating oil to reduce temperature.
Currently, it generallys use cooling fan or combustion-oil heat exchanger cools down lubricating oil, and cooling fan is with rotation
Component, bulky, structure is complicated, and reliability is poor；Combustion-oil heat exchanger requires lasting circulation fuel delivery, on ground
When aircraft engine does not work, cooling effect decline.
Summary of the invention
The object of the invention: providing a kind of aircraft auxiliary power plant oil cooling system, for taking away the heat of lubricating oil, drops
Low oil temperature.
The technical scheme is that a kind of auxiliary power unit oil cooling system, the auxiliary power applied to aircraft
System, the system comprises air intake duct B (2), heat exchanger (3), injector (6), oil pump (13), oil pipe A (15), oil pipe
B(16)；It is connected outside air intake duct B (2) and machine, injector (6) is mounted on auxiliary power unit jet pipe (7), heat exchanger (3) peace
Import mounted in injector (6), oil pump (13) are mounted on auxiliary power unit gear-box (12), oil pipe A (15) with change
The import of hot device (3) is connected, oil pipe B (16) is connected with the outlet of heat exchanger (3)；The oil cooling system and auxiliary power
Device is installed along in the auxiliary power unit cabin (4) of aircraft tail cone, when auxiliary power unit works, the outer air of machine by into
Air flue A (1) enters in compressor (10), and the outer air of machine enters combustion chamber (9) after compression, with the mist sprayed into combustion chamber (9)
Change fuel oil mixing after-combustion, generates high-temperature high-pressure fuel gas；High-temperature high-pressure fuel gas expansion work in turbine (8), turbine (8) drive
Oil pump (13) and generator (14) rotation on gear-box (12) and gear-box (12)；Oil pump (13) is gear-box (12) bottom
The lubricating oil in portion is pumped into heat exchanger (3) by oil pipe A (15), lubricating oil and the outer cold air of machine by injector (6) injection into
Row heat exchange, lubricating oil are cooled；Lubricating oil after cooling supplies bearing (11) and generator (14), and band by oil pipe B (16)
The heat that bearing running (11) and generator (14) generate, oil temperature increase；Lubricating oil after temperature raising, in oil pump (13)
Gear-box (12) bottom is flowed back under swabbing action；The combustion gas for leaving turbine (8) is discharged into exhaust pipe (5) by jet pipe (7),
Under the ejector action that the jet pipe (7) of high speed is vented, the outer air of machine enters auxiliary power unit cabin by air intake duct B (2)
(4), then by heat exchanger (3) enter injector (6), then mix heel row with auxiliary power unit exhaust in exhaust pipe (5)
Out outside machine, the outer air of machine takes away the heat of lubricating oil, plays the role of cooling lubricating oil by heat exchanger (3).
The circulation area of air intake duct B (2) is determined according to the ejector capacity of injector (6).
The heat exchanger (3) uses plate-fin heat exchanger.
The oil pump (13) uses gear pump.
Advantages of the present invention: relative to fan coolling mode, eliminating rotary part, reduces auxiliary power unit gear
The complexity of case, structure is simple, small in size, high reliablity；Relative to combustion-lubricating oil radiating mode, sustainer is overcome not
The problem of cooling effect difference when work.
Detailed description of the invention
Fig. 1 is oil cooling system operation principle schematic diagram of the invention；
Fig. 2 is partial sectional view of the invention.
Specific embodiment
The present invention is described in more detail with reference to the accompanying drawing.
A kind of auxiliary power unit oil cooling system, applied to the accessory power system of aircraft, the system comprises into
Air flue B (2), heat exchanger (3), injector (6), oil pump (13), oil pipe A (15), oil pipe B (16)；Air intake duct B (2) with
Be connected outside machine, injector (6) is mounted on auxiliary power unit jet pipe (7), heat exchanger (3) be mounted on injector (6) into
Mouthful, oil pump (13) is mounted on auxiliary power unit gear-box (12), oil pipe A (15) is connected with the import of heat exchanger (3),
Oil pipe B (16) is connected with the outlet of heat exchanger (3)；The oil cooling system and auxiliary power unit are installed along with aircraft
In the auxiliary power unit cabin (4) of tail cone, when auxiliary power unit works, the outer air of machine enters compressor by air intake duct A (1)
(10) in, the outer air of machine enters combustion chamber (9) after compression, with the atomized fuel mixing after-combustion sprayed into combustion chamber (9), produces
Raw high-temperature high-pressure fuel gas；High-temperature high-pressure fuel gas expansion work in turbine (8), turbine (8) drive gear-box (12) and gear-box
(12) oil pump (13) and generator (14) rotation on；The lubricating oil of gear-box (12) bottom is passed through oil pipe by oil pump (13)
A (15) is pumped into heat exchanger (3), and lubricating oil carries out heat exchange with the outer cold air of machine by injector (6) injection, and lubricating oil is cold
But；Lubricating oil after cooling supplies bearing (11) and generator (14) by oil pipe B (16), and with bearing running (11) and generator
(14) heat generated, oil temperature increase；Lubricating oil after temperature raising, flows back into tooth under the swabbing action of oil pump (13)
Roller box (12) bottom；The combustion gas for leaving turbine (8) is discharged into exhaust pipe (5) by jet pipe (7), in the jet pipe (7) of high speed
Under the ejector action of exhaust, the outer air of machine enters auxiliary power unit cabin (4) by air intake duct B (2), then passes through heat exchanger (3)
Into injector (6), after then mixing in exhaust pipe (5) with auxiliary power unit exhaust outside discharge machine, the outer air of machine passes through
Heat exchanger (3), takes away the heat of lubricating oil, plays the role of cooling lubricating oil.
The circulation area of air intake duct B (2) is determined according to the ejector capacity of injector (6).
The heat exchanger (3) uses plate-fin heat exchanger.
The oil pump (13) uses gear pump.
Claims (4)
1. a kind of oil cooling system for aircraft auxiliary power plant, applied to the accessory power system of aircraft, feature
It is, the system comprises air intake duct B (2), heat exchanger (3), injector (6), oil pump (13), oil pipe A (15), oil pipe
B(16)；It is connected outside air intake duct B (2) and machine, injector (6) is mounted on auxiliary power unit jet pipe (7), heat exchanger (3) peace
Import mounted in injector (6), oil pump (13) are mounted on auxiliary power unit gear-box (12), oil pipe A (15) with change
The import of hot device (3) is connected, oil pipe B (16) is connected with the outlet of heat exchanger (3)；The oil cooling system and auxiliary power
Device is installed along in the auxiliary power unit cabin (4) of aircraft tail cone, when auxiliary power unit works, the outer air of machine by into
Air flue A (1) enters in compressor (10), and the outer air of machine enters combustion chamber (9) after compression, with the mist sprayed into combustion chamber (9)
Change fuel oil mixing after-combustion, generates high-temperature high-pressure fuel gas；High-temperature high-pressure fuel gas expansion work in turbine (8), turbine (8) drive
Oil pump (13) and generator (14) rotation on gear-box (12) and gear-box (12)；Oil pump (13) is gear-box (12) bottom
The lubricating oil in portion is pumped into heat exchanger (3) by oil pipe A (15), lubricating oil and the outer cold air of machine by injector (6) injection into
Row heat exchange, lubricating oil are cooled；Lubricating oil after cooling supplies bearing (11) and generator (14), and band by oil pipe B (16)
The heat that bearing running (11) and generator (14) generate, oil temperature increase；Lubricating oil after temperature raising, in oil pump (13)
Gear-box (12) bottom is flowed back under swabbing action；The combustion gas for leaving turbine (8) is discharged into exhaust pipe (5) by jet pipe (7),
Under the ejector action that the jet pipe (7) of high speed is vented, the outer air of machine enters auxiliary power unit cabin by air intake duct B (2)
(4), then by heat exchanger (3) enter injector (6), then mix heel row with auxiliary power unit exhaust in exhaust pipe (5)
Out outside machine, the outer air of machine takes away the heat of lubricating oil, plays the role of cooling lubricating oil by heat exchanger (3).
2. oil cooling system according to claim 1, it is characterised in that: the circulation area of air intake duct B (2) is according to injection
The ejector capacity of device (6) determines.
3. oil cooling system according to claim 1, it is characterised in that: the heat exchanger (3) uses plate fin heat-exchanging
Device.
4. oil cooling system according to claim 1, it is characterised in that: the oil pump (13) uses gear pump.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811454072.8A CN109573074A (en) | 2018-11-30 | 2018-11-30 | A kind of oil cooling system for aircraft auxiliary power plant |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811454072.8A CN109573074A (en) | 2018-11-30 | 2018-11-30 | A kind of oil cooling system for aircraft auxiliary power plant |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109573074A true CN109573074A (en) | 2019-04-05 |
Family
ID=65925876
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811454072.8A Pending CN109573074A (en) | 2018-11-30 | 2018-11-30 | A kind of oil cooling system for aircraft auxiliary power plant |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109573074A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110761901A (en) * | 2019-10-12 | 2020-02-07 | 中航通飞研究院有限公司 | Engine lubricating oil heat dissipation supercharging device that admits air |
| CN112407294A (en) * | 2020-10-30 | 2021-02-26 | 哈尔滨飞机工业集团有限责任公司 | Lubricating oil heat dissipation cabin heating system and method |
| CN112478181A (en) * | 2020-11-25 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne integrated cooling system |
| CN114180071A (en) * | 2021-11-19 | 2022-03-15 | 中国直升机设计研究所 | Heating system using lubricating oil as auxiliary heat source |
| WO2023002132A1 (en) * | 2021-07-21 | 2023-01-26 | Flying Whales | System for the thermal management of an external electric-power-generating nacelle equipping an electrically powered airship, nacelle and airship equipped with said system |
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|---|---|---|---|---|
| EP0968918A2 (en) * | 1998-07-01 | 2000-01-05 | The Boeing Company | Auxiliary power unit passive cooling system |
| US20020139120A1 (en) * | 2001-03-29 | 2002-10-03 | Honeywell International, Inc. | Tortuous path quiet exhaust eductor system |
| US20030080244A1 (en) * | 2001-10-29 | 2003-05-01 | Luc Dionne | Passive cooling system for auxiliary power unit installation |
| CN1556009A (en) * | 2003-12-30 | 2004-12-22 | 上海交通大学 | Liquid hydrogen fuel carrying and heat exchanging system of hydrogenfuel high speed airplane |
| US20050229602A1 (en) * | 2004-04-16 | 2005-10-20 | Whiting Michael O | Forced air cooling system |
| CN102673793A (en) * | 2012-06-08 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Exhaust ejector system of airplane auxiliary power unit |
| CN204327936U (en) * | 2014-12-03 | 2015-05-13 | 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 small flow lubrication system of full flight envelope work |
| CN107416214A (en) * | 2017-06-29 | 2017-12-01 | 南京航空航天大学 | A kind of perflation ventilation structure for aircraft secondary power systems |
| US20180050810A1 (en) * | 2016-08-19 | 2018-02-22 | General Electric Company | Propulsion engine for an aircraft |
| 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 |
-
2018
- 2018-11-30 CN CN201811454072.8A patent/CN109573074A/en active Pending
Patent Citations (10)
| 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 |
| US20020139120A1 (en) * | 2001-03-29 | 2002-10-03 | Honeywell International, Inc. | Tortuous path quiet exhaust eductor system |
| US20030080244A1 (en) * | 2001-10-29 | 2003-05-01 | Luc Dionne | Passive cooling system for auxiliary power unit installation |
| CN1556009A (en) * | 2003-12-30 | 2004-12-22 | 上海交通大学 | Liquid hydrogen fuel carrying and heat exchanging system of hydrogenfuel high speed airplane |
| US20050229602A1 (en) * | 2004-04-16 | 2005-10-20 | Whiting Michael O | Forced air cooling system |
| CN102673793A (en) * | 2012-06-08 | 2012-09-19 | 中国航空工业集团公司西安飞机设计研究所 | Exhaust ejector system of airplane auxiliary power unit |
| CN204327936U (en) * | 2014-12-03 | 2015-05-13 | 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 small flow lubrication system of full flight envelope work |
| US20180050810A1 (en) * | 2016-08-19 | 2018-02-22 | General Electric Company | Propulsion engine for an aircraft |
| CN107416214A (en) * | 2017-06-29 | 2017-12-01 | 南京航空航天大学 | A kind of perflation ventilation structure for aircraft secondary power systems |
| 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 |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110761901A (en) * | 2019-10-12 | 2020-02-07 | 中航通飞研究院有限公司 | Engine lubricating oil heat dissipation supercharging device that admits air |
| CN112407294A (en) * | 2020-10-30 | 2021-02-26 | 哈尔滨飞机工业集团有限责任公司 | Lubricating oil heat dissipation cabin heating system and method |
| CN112407294B (en) * | 2020-10-30 | 2022-11-22 | 哈尔滨飞机工业集团有限责任公司 | Lubricating oil heat dissipation cabin heating system and method |
| CN112478181A (en) * | 2020-11-25 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Airborne integrated cooling system |
| WO2023002132A1 (en) * | 2021-07-21 | 2023-01-26 | Flying Whales | System for the thermal management of an external electric-power-generating nacelle equipping an electrically powered airship, nacelle and airship equipped with said system |
| CN114180071A (en) * | 2021-11-19 | 2022-03-15 | 中国直升机设计研究所 | Heating system using lubricating oil as auxiliary heat source |
| CN114180071B (en) * | 2021-11-19 | 2023-10-27 | 中国直升机设计研究所 | Heating system using lubricating oil as auxiliary heat source |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190405 |