CN106672249A - High-temperature gas cooling device of aircraft fuel inerting system - Google Patents
High-temperature gas cooling device of aircraft fuel inerting system Download PDFInfo
- Publication number
- CN106672249A CN106672249A CN201611161305.6A CN201611161305A CN106672249A CN 106672249 A CN106672249 A CN 106672249A CN 201611161305 A CN201611161305 A CN 201611161305A CN 106672249 A CN106672249 A CN 106672249A
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- CN
- China
- Prior art keywords
- ram
- temperature gas
- air
- temperature
- valve
- 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 abstract description 13
- 239000000446 fuel Substances 0.000 title abstract description 11
- 239000002826 coolant Substances 0.000 claims abstract description 9
- 239000000295 fuel oil Substances 0.000 claims description 16
- 230000001105 regulatory effect Effects 0.000 claims description 12
- 206010031009 Oral pain Diseases 0.000 claims description 3
- 238000004891 communication Methods 0.000 claims description 3
- 239000002828 fuel tank Substances 0.000 abstract description 9
- 230000000630 rising effect Effects 0.000 abstract description 2
- 238000009434 installation Methods 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 3
- 238000010304 firing Methods 0.000 description 2
- 230000007257 malfunction Effects 0.000 description 2
- 238000004080 punching Methods 0.000 description 2
- 239000003507 refrigerant Substances 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000017525 heat dissipation Effects 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
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Temperature (AREA)
Abstract
The invention belongs to an aircraft fuel inerting system, and relates to a high-temperature gas cooling device of an aircraft fuel inerting system. The high-temperature gas cooling device of the aircraft fuel inerting system is characterized by comprising a ram-air adjusting valve (1), a ram-air outlet (2), a high-temperature gas inlet (3), a stop valve (4), a one-way valve (5), a ram-air inlet (6), a fan (7), a high-temperature gas outlet (8), a temperature sensor (9), a heat exchanger (10) and a controller (11). By the high-temperature gas cooling device of the aircraft fuel inerting system, the circumstance that fuel is used as a cooling medium to cause rising of local temperature in a fuel tank can be prevented, possibility of fuel pollution caused by leakage of a heat sink is completely eradicated, and complexity of installation and distribution of the fuel system due to the fact that equipment is arranged in the oil tank is prevented from being increased.
Description
Technical field
The invention belongs to aircraft fuel oil inerting system, is related at a kind of aircraft fuel oil inerting system high-temperature gas cooling down
Reason device.
Background technology
, typically from environmental control system bleed house steward's bleed, bleed temperature is higher, it is impossible to meet air for aircraft fuel oil inerting system
The gasinlet temperature of separator requires, needs to lower the temperature bleed.Fuel oil is typically chosen as refrigerant, by one-level or
The mode of multistage radiating is by the heat transfer of high temperature bleed to fuel oil.This radiating mode has certain limitation.First, can draw
The rising of local temperature in fuel tank is played, certain danger may be brought；Secondly as heat dissipation pipeline and radiator need to enter
Fuel tank is simultaneously immersed in fuel oil for a long time, thus there is the possibility of leakage pollution fuel oil；3rd, radiator needs to be arranged in oil mass
Sufficient occasion, is typically located at and directly supplies in the fuel tank of fuel oil to engine, and General Spatial is limited in fuel tank and needs
More part of appliance and pipeline etc. are arranged, thus increased the complexity of fuel system mounting arrangement.
The content of the invention
The purpose of the present invention is：A kind of aircraft fuel oil inerting system high-temperature gas heat sink is proposed, to prevent from firing
Oil causes local temperature in fuel tank to raise as cooling medium, prevents, because radiator leak causes to pollute the possibility of fuel oil, to keep away
Exempt from the complexity that fuel system mounting arrangement is increased because of the advancing equipment in fuel tank.
The present invention technical solution be：A kind of aircraft fuel oil inerting system high-temperature gas heat sink, its feature exists
In：It includes that the outlet 2, high-temperature gas entrance 3 of ram-air regulating valve 1, ram-air, stop valve 4, check valve 5, punching press are empty
Gas entrance 6, the outlet 8, temperature sensor 9 of fan 7, high-temperature gas, heat exchanger 10 and controller 11；Ram-air regulating valve 1
Gas outlet 1b and ram-air outlet 2 connect, the air inlet 1a of ram-air regulating valve 1 and the cooling medium of heat exchanger 10
Outlet 10d connections, the cooling medium inlet 10c of heat exchanger 10 gas outlet 7b respectively with fan 7 and the outlet of check valve 5
Connection, ram-air entrance 6 respectively with the air inlet 7b and the inlet communication of check valve 5 of fan 7；High-temperature gas entrance 3 with
The high-temperature gas air inlet 10a connections of heat exchanger 10, the high-temperature gas gas outlet 10b of heat exchanger 10 respectively with TEMP
The temperature-sensitive mouth of device 9 is connected with high-temperature gas outlet 8；Control signal input 1c of ram-air regulating valve 1 and controller 11
Governor valve control signal output part 11a connects, the cut-out valve control signal of control signal input 4c of stop valve 4 and controller 11
Output end 11b connects, and control signal input 7c of fan 7 is connected with fan control signal output end 11c of controller 11.
It is an advantage of the invention that：A kind of aircraft fuel oil inerting system high-temperature gas heat sink is proposed, can prevent from firing
Oil causes local temperature in fuel tank to raise as cooling medium, has prevented because radiator leak causes to pollute the possibility of fuel oil,
Avoid the complexity that fuel system mounting arrangement is increased because of the advancing equipment in fuel tank.
Description of the drawings
Fig. 1 is the structural representation of the present invention.
Specific embodiment
The present invention is described in further details below.Referring to Fig. 1, a kind of aircraft fuel oil inerting system high-temperature gas cooling
Device, it is characterised in that：It includes the outlet 2, high-temperature gas entrance 3 of ram-air regulating valve 1, ram-air, stop valve 4, list
To valve 5, ram-air entrance 6, the outlet 8, temperature sensor 9 of fan 7, high-temperature gas, heat exchanger 10 and controller 11；Punching
Gas outlet 1b and the ram-air of pressure air control valve 1 exports 2 and connects, the air inlet 1a of ram-air regulating valve 1 and heat exchange
The cooling medium outlet 10d connections of device 10, the cooling medium inlet 10c of heat exchanger 10 respectively with the gas outlet 7b of fan 7 and
The outlet of check valve 5, ram-air entrance 6 respectively with the air inlet 7b and the inlet communication of check valve 5 of fan 7；
High-temperature gas entrance 3 is connected with the high-temperature gas air inlet 10a of heat exchanger 10, the high-temperature gas gas outlet of heat exchanger 10
10b exports 8 and connects with the temperature-sensitive mouth and high-temperature gas of temperature sensor 9 respectively；The control signal input of ram-air regulating valve 1
End 1c is connected with the governor valve control signal output part 11a of controller 11, control signal input 4c of stop valve 4 and controller 11
The connection of stop valve control signal output 11b, control signal input 7c of fan 7 and the fan control signal of controller 11
Output end 11c connects.
The present invention operation principle be：The present invention is carried out controllable cold as refrigerant using ram-air to high temperature bleed
But, the temperature of the high-temperature gas after the impression cooling of temperature sensor 9 on the downstream pipe of heat exchanger 10, and Real-time Feedback temperature
To controller 11, controller 11 automatically adjusts air and adjusts signal according to the real time temperature of feedback with the difference of target regulation temperature
The aperture of section valve 1, changes the flow of the cooling air for participating in heat exchange, to maintain the hot-gas temperature after cooling down predetermined
In the range of.When ram-air is not enough, fan 7 is opened in the control of controller 11, and using fan branch road high-temperature gas cooling institute is provided
The cooling tolerance for needing.Work as system malfunctions, such as ram-air blocked inlet, fan fails, ram-air flow failure of adjustment
And when situations such as controller failure causing cooling system to fail, controller 11 cuts off high temperature source of the gas by stop valve 4, prevents
It is dangerous.
One embodiment of the present of invention, the ram-air regulating valve 1 for being adopted, stop valve 4, check valve 5, fan 7, temperature
Degree sensor 9, heat exchanger 10 and controller 11 are finished parts.Controller 11 according to concrete demand for control software for editing, if
Determine control logic.The present embodiment can carry out logic control according to specific cooling demand for control to related finished parts, complete pre-
The fixed function that high-temperature gas is cooled to target temperature, and with the emergency switching-off ability under malfunction.
Claims (1)
1. a kind of aircraft fuel oil inerting system high-temperature gas heat sink, it is characterised in that：It includes ram-air regulating valve
(1), ram-air outlet (2), high-temperature gas entrance (3), stop valve (4), check valve (5), ram-air entrance (6), wind
Fan (7), high-temperature gas outlet (8), temperature sensor (9), heat exchanger (10) and controller (11)；Ram-air regulating valve
(1) gas outlet (1b) and ram-air outlet (2) are connected, the air inlet (1a) of ram-air regulating valve (1) and heat exchanger
(10) cooling medium outlet (10d) connection, the cooling medium inlet (10c) of heat exchanger (10) goes out respectively with fan (7)
The outlet of gas port (7b) and check valve (5), ram-air entrance (6) respectively with the air inlet (7b) of fan (7) and single
To the inlet communication of valve (5)；High-temperature gas entrance (3) is connected with the high-temperature gas air inlet (10a) of heat exchanger (10), heat
The high-temperature gas gas outlet (10b) of exchanger (10) exports (8) even with the temperature-sensitive mouth and high-temperature gas of temperature sensor (9) respectively
It is logical；The control signal input (1c) of ram-air regulating valve (1) and the governor valve control signal output part of controller (11)
(11a) connect, the stop valve control signal output (11b) of stop valve (4) control signal input (4c) and controller (11)
Connection, the control signal input (7c) of fan (7) is connected with the fan control signal output end (11c) of controller (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611161305.6A CN106672249A (en) | 2016-12-15 | 2016-12-15 | High-temperature gas cooling device of aircraft fuel inerting system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611161305.6A CN106672249A (en) | 2016-12-15 | 2016-12-15 | High-temperature gas cooling device of aircraft fuel inerting system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106672249A true CN106672249A (en) | 2017-05-17 |
Family
ID=58869468
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611161305.6A Pending CN106672249A (en) | 2016-12-15 | 2016-12-15 | High-temperature gas cooling device of aircraft fuel inerting system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106672249A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108033027A (en) * | 2017-12-26 | 2018-05-15 | 南京航空航天大学 | A kind of green inerting fuel tank afterheat utilizing system |
| CN108128471A (en) * | 2017-12-15 | 2018-06-08 | 石家庄飞机工业有限责任公司 | A kind of aircraft fuel system fuel oil cooling device |
| CN108482688A (en) * | 2018-03-23 | 2018-09-04 | 南京航空航天大学 | Waste-heat recovery device in a kind of aircraft fuel-tank inert gas system |
| CN115108033A (en) * | 2022-05-30 | 2022-09-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft fuel oil heat sink dynamic control system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101005987A (en) * | 2004-08-16 | 2007-07-25 | 空中客车德国有限公司 | Cooling of air in an aircraft |
| CN101010238A (en) * | 2004-08-16 | 2007-08-01 | 空中客车德国有限公司 | Air supply for an aircraft |
| CN103561556A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Aeration-cooling method for avionic devices |
| WO2015082913A2 (en) * | 2013-12-02 | 2015-06-11 | Aero Systems Consultants LLC | Aircraft fuel systems |
| CN105644794A (en) * | 2014-12-02 | 2016-06-08 | 波音公司 | Cooling system for center wing fuel tank of aircraft |
-
2016
- 2016-12-15 CN CN201611161305.6A patent/CN106672249A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101005987A (en) * | 2004-08-16 | 2007-07-25 | 空中客车德国有限公司 | Cooling of air in an aircraft |
| CN101010238A (en) * | 2004-08-16 | 2007-08-01 | 空中客车德国有限公司 | Air supply for an aircraft |
| CN103561556A (en) * | 2013-11-05 | 2014-02-05 | 中国航空工业集团公司西安飞机设计研究所 | Aeration-cooling method for avionic devices |
| WO2015082913A2 (en) * | 2013-12-02 | 2015-06-11 | Aero Systems Consultants LLC | Aircraft fuel systems |
| CN105644794A (en) * | 2014-12-02 | 2016-06-08 | 波音公司 | Cooling system for center wing fuel tank of aircraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108128471A (en) * | 2017-12-15 | 2018-06-08 | 石家庄飞机工业有限责任公司 | A kind of aircraft fuel system fuel oil cooling device |
| CN108033027A (en) * | 2017-12-26 | 2018-05-15 | 南京航空航天大学 | A kind of green inerting fuel tank afterheat utilizing system |
| CN108482688A (en) * | 2018-03-23 | 2018-09-04 | 南京航空航天大学 | Waste-heat recovery device in a kind of aircraft fuel-tank inert gas system |
| CN115108033A (en) * | 2022-05-30 | 2022-09-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft fuel oil heat sink dynamic control system |
| CN115108033B (en) * | 2022-05-30 | 2024-05-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Dynamic control system for aircraft fuel heat sink |
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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: 20170517 |