CN109515728A - Aircraft heat management system and method with auxiliary hot oil case circuit - Google Patents
Aircraft heat management system and method with auxiliary hot oil case circuit Download PDFInfo
- Publication number
- CN109515728A CN109515728A CN201811327729.4A CN201811327729A CN109515728A CN 109515728 A CN109515728 A CN 109515728A CN 201811327729 A CN201811327729 A CN 201811327729A CN 109515728 A CN109515728 A CN 109515728A
- Authority
- CN
- China
- Prior art keywords
- fuel
- temperature
- control valve
- radiator
- flow
- 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
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/34—Conditioning fuel, e.g. heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
- B64D33/10—Radiator arrangement
Abstract
The present invention is aircraft heat management system and method with auxiliary hot oil case circuit, for the heat management problems for the heat sink wretched insufficiency that high-performance ultrasound speed aircraft of new generation faces, a kind of hot oil case subsidiary loop, including reflux steering control valve, hot oil case, engine flue radiator, covering radiator and distributing T-pipe control valve are devised on the basis of conventional heat pipe reason system.The steering control valve that flows back controls the whereabouts of return fuel, using the higher return fuel of the temporary storage temperature of hot oil case, reflux hot oil heating oil storage is avoided to cause irreversible heat sink loss；It is that hot oil tank fuel is cooling, and the flow of cooling fuel oil is controlled by flow valve that engine flue radiator, covering radiator, which are integrated in heat management system, the maximized cooling capacity for utilizing engine air duct air and covering；Using distributing T-pipe control valve, the low temperature fuel oil after control is cooled is mixed into the fuel oil cooling circuit of conventional heat pipe reason system, is stablized the temperature of cooling fuel oil, is avoided fuel oil temperature from being promoted and give heat management system bring pressure.
Description
Technical field
The present invention relates to aircraft heat management systems and method with auxiliary hot oil case circuit.
Background technique
In conventional heat pipe reason system, thermal force is cooling to be based on fuel oil cooling circuit, and fuel oil is used as heat sink and bosher simultaneously
Matter is that the various thermal force components in circuit are cooling, such as environmental control system radiator, electrical system radiator, hydraulic system radiator
Deng；Engine extracts the high temp oil-fired for completing cooling task from cooling line, and extra hot oil returns fuel tank through return line
In；Ram-air heat exchanger is provided in fuel flow returns pipeline, it is cooling for reflux hot oil.
High performance airplane of new generation integrates more and more high-power functional apparatus, in addition supersonic flight bring gas
Dynamic heating, it is horizontal to considerably increase complete machine thermal force；Convention heat sink such as ram-air are under supersonic flight state at the same time
Total temperature is promoted with speed and is quickly increased, and the ability that is allowed to cool declines rapidly until losing.
Complete machine thermal force will lead to Low oil Fuel consumed by engine to take away net quantity of heat, to produce when steeply rising
Raw a large amount of reflux hot oil；The decline of the convention heat sinks cooling capacity such as ram-air is not enough to cooling whole return fuels again, makes
A large amount of high temp oil-fireds pass back into fuel tank；As aerial mission promotes, reflux hot oil can constantly promote the temperature of oil tank fuel, give
Fuel oil is heat sink, and ability brings very big loss.
In conventional heat pipe reason system, ram-air heat exchanger is placed on return line, leads to its cooling capacity extremely
The flow of return fuel is relied on, reducing return fuel flow will lead to the waste of ram-air cooling capacity, increase return fuel
Flow can then reduce the waste that fuel oil temperature before engine causes fuel oil heat sink.
Conventional heat pipe reason system is only integrated with fuel oil and two kinds of ram-air heat sink, and the cooling capacity of ram-air is again
It is frequently subjected to limit, leads to the work of heat management system and its relies on the heat sink ability of fuel oil, gradually disappear in flight later period fuel oil
Under consumption and the constantly raised situation of temperature, heat management system can increasingly be difficult to control complete machine thermal force temperature.
Summary of the invention
According to an aspect of the invention, there is provided a kind of aircraft heat management system, characterized by comprising:
Conventional heat pipe manages system, and
Hot oil case circuit is assisted,
Conventional heat pipe reason system includes: fuel reserve tank, thermal force component,
Auxiliary hot oil case circuit includes: reflux steering control valve, hot oil case, hot oil transfer tube, check valve, engine
Flue radiator, the first flow control valve for engine flue radiator, covering radiator, for the of covering radiator
Two flow control valves, distributing T-pipe control valve, pressure difference turbine,
Wherein:
The reflux steering control valve is arranged on the return line of conventional heat pipe reason system, and flow back steering control valve
Two outlet ends pass through pipeline respectively and be connected to fuel reserve tank and hot oil case, reflux steering control valve is according to the temperature of return fuel
Adjustment turns to；
The outlet of the hot oil case is pressurized transfer tube, the engine flue radiator of check valve and parallel connection, covering
Radiator is sequentially connected with by the road；
First flow control valve is arranged on the upstream of the engine flue radiator, flows through air duct for control and dissipates
The flow of the cooled fuel oil of hot device；
Second flow control valve is arranged on the upstream of the covering radiator, flows through covering radiator for controlling
Cooled fuel flow；
The fuel oil total flow flowed out by hot oil case is determined by the aperture of first flow control valve and second flow control valve；
The entrance of the distributing T-pipe control valve and the fuel outlet of engine flue radiator and covering radiator
Fuel outlet connection, the first outlet of distributing T-pipe control valve is connected to through pressure difference turbine with hot oil tank inlet by pipeline, three
The second outlet of reduction of fractions to a common denominator flow control valve manages the combustion of system by pipeline in the mixing point and conventional heat pipe of thermal force component upstream end
Oil cooling loop connection.
Detailed description of the invention
Fig. 1 is aircraft heat management system hot oil case subsidiary loop topological structure diagram.
Fig. 2 is that hot oil case subsidiary loop control system architecture figure is shown.
Fig. 3 is engine flue radiator, covering radiator distribution diagram.
Fig. 4 is reflux 1 control strategy of switching valve.
Fig. 5 is 6/8 control strategy of flow valve.
Fig. 6 is 9 control strategy of three-way flow divider valve.
Specific embodiment
The present invention proposes one aiming at the problem that insufficient heat sink that above-mentioned high-performance ultrasound speed aircraft faces in the prior art
Kind assists hot oil tank system.The system of the invention while retaining conventional heat pipe reason system structure and its all functions,
Provide the hot oil case parallel with fuel reserve tank and mating cooling line system.As shown in Figure 1, according to one embodiment of present invention
Hot oil case auxiliary system be integrated with hot oil case, fuel flow returns controller and hot oil case cooling circuit.
The hot oil case and fuel reserve tank arranged in parallel is in the fuel oil cooling circuit of heat management system, for recycling reflux
Hotter fuel oil, the heating for avoiding reflux hot oil heat sink to oil storage fuel tank intermediate fuel oil, while hot oil is concentrated in hot oil case will
It is more convenient that it is cooled down, facilitate heat sink scheduling.Hot oil case, which can use, original in oil tank system is closer to aircraft weight
The seed oil case of the heart avoids increasing additional take-off weight, while avoiding influence of the heat sink scheduling to center of flying gravity.
The fuel flow returns control system is made of counter flow controller and reflux switching valve.Reflux switching valve is located at
Before heat management system return line end, oil storage tank inlet, counter flow controller is according to the return fuel temperature of temperature sensor measurement
The temperature of degree and fuel reserve tank intermediate fuel oil, control reflux switching valve adjust flow path.It is fired when return fuel temperature is higher than in fuel reserve tank
When one predetermined value of oil temperature, reflux switching valve control fuel oil is flowed into hot oil case, is otherwise flowed into fuel reserve tank.
The hot oil tank cooling system is by hot oil cooling line, cold oil return line and flow divider.Wherein hot oil is cooling
Pipeline is driven by independently fuel oil transfer tube, and is integrated with air duct heat exchanger and covering heat exchanger, contains wind outside using engine
Road air and aircraft skin both it is heat sink for hot oil it is cooling.In view of the cooling capacity of engine air duct air and aircraft skin
Huge with the variation of flight operating condition, each heat exchanger front end is provided with flow valve and its controller in pipeline, adjusts cooled heat
The flow of oil.Controller controls cooled fuel flow, control by heat exchanger import, outlet fuel temperature and heat sink temperature
Target is that heat exchanger efficiency is made to reach 80%, i.e., heat sink utilization rate reaches 80%.
Fuel oil after cooled is controlled through distributing T-pipe control valve, and a part returns to hot oil case, another part and heat management
The cooling fuel oil mixing of system.The control strategy of distributing T-pipe control valve is to reduce cooling circuit intermediate fuel oil temperature, makes heat management system
System is stablized in ideal operating condition, according to the temperature of fuel oil after cooling and cooling fuel oil confluence fuel oil temperature regulating three-way valve stream
Amount when fuel oil temperature is lower than below one predetermined value of oil storage after cooling, increases the flow proportional of mixed flow pipeline, and control target is
Mixed pour point temperature is controlled in a predetermined value.
The aircraft heat management system hot oil case auxiliary system remains the structure and function of conventional heat pipe reason system, leads to
Crossing introducing hot oil case recycling reflux hot oil avoids fuel oil heat sink temperature from rising, while by heat such as air duct heat exchanger, covering heat exchangers
It is heavy to be integrated in auxiliary system, enhance system entirety heat sink cooling capacity and heat sink dispatching.The hot oil case is auxiliary
Auxiliary system also passes through reasonable fuel oil allotment and flexible cooling control, maximumlly utilizes various heat sink cold sources, enhances heat pipe
The cooling capacity of reason system.
Further detailed description is made with reference to the accompanying drawing
The hot oil case subsidiary loop of aircraft heat management system according to an embodiment of the invention is as shown in Figure 1, described
Hot oil case subsidiary loop include reflux steering control valve 1, hot oil case 2, hot oil transfer tube 3, check valve 4, engine air duct dissipate
Hot device 5 and its flow control valve 6, covering radiator 7 and its flow control valve 8, distributing T-pipe control valve 9, pressure difference turbine 10；
The entrance of the reflux steering control valve 1 is connected to the return line end of conventional heat pipe reason system 100, and two
Outlet end is connected to fuel reserve tank 101, hot oil case 2 respectively；Hot oil case 2 is in parallel with fuel reserve tank 101, and the outlet of hot oil case 2, fuel oil increase
Pressure transfer tube 3, check valve 4, engine flue radiator 5 in parallel are sequentially connected to covering radiator 7.The outlet of hot oil case 2
Fuel oil is driven by booster pump 3, is sent to engine flue radiator 5 and the cooling of covering radiator 7 in parallel, cooled fuel oil
Flow is controlled by the aperture of the flow control valve 6 and 8 of the upstream of engine flue radiator 5 and covering radiator 7 in parallel；
Fuel oil confluence after cooled distributing T-pipe control valve 9 upstream position and be connected to the entrance of distributing T-pipe control valve 9.Three
Reduction of fractions to a common denominator flow control valve 9 controls the fuel oil after a part is cooled and leads to the fuel oil cooling circuit of conventional heat pipe reason system 100 to drop
Low circuit intermediate fuel oil temperature, another part return in hot oil case 2 through pressure difference turbine 10, reduce hot oil case intermediate fuel oil temperature.
The effect of hot oil case 2 is, by being located at the reflux steering control valve 1 of reflux line end, recycling conventional heat pipe reason
The higher fuel oil of 100 reflux temperature of system.In the thermal force level of airplane complete machine, higher and ram-air cooling capacity is limited
Operating condition under, a large amount of hot oils that flow back, which directly return, will lead to the heat sink temperature rising of fuel oil in fuel reserve tank 101, cause irreversible
Heat sink loss.Temporarily recycling these hot oils using hot oil case 2 can be to avoid heat sink loss caused by reflux heat oil, and by hot oil collection
In get up, convenient further cooling, scheduling.
Engine flue radiator 5 and covering radiator 7 by arranged in parallel in hot oil case subsidiary loop, for cooling heat
High temp oil-fired in fuel tank 2.As shown in Fig. 2, the engine flue radiator 5, which is located at outside aircraft engine 200, contains air duct
In, belong to annular radiator, it is cooling for heat exchanger temperature end fuel oil stream using engine air duct air；Covering radiator 7 is located at
300 inside of aircraft skin, is become one using fine and closely woven fuel passage with covering, cooling for pipeline intermediate fuel oil stream；Engine 200
Air duct air has lot of advantages, and flow is big and stablizes, and independent of flying speed, and does not influence pneumatic and Stealth Fighter；
Same aircraft skin 300 be also it is ideal heat sink, there is very big heat dissipation area, and do not influence pneumatic and Stealth Fighter.
Engine flue radiator and covering radiator, which are introduced into heat management system, can significantly enhance the heat sink cold of its entirety
But ability.
As shown in figure 3, the hot oil case subsidiary loop of aircraft heat management system according to an embodiment of the invention is by institute
Reflux steering control valve 1, engine flue radiator flow control valve 6, the covering radiator flow control valve 8, Yi Jisan of category
9 Collaborative Control of reduction of fractions to a common denominator flow control valve completes storage, cooling and the recycling of hot oil, and the control foundation of each control valve, which is distributed across, is
The measurement data of the temperature sensor of system different location, these temperature sensors include: to flow back to turn in hot oil case subsidiary loop
First temperature sensor 11 of 1 entry position of control valve, the second temperature sensor 12 of 2 outlet port of hot oil case, engine wind
5 exit of road radiator setting third temperature sensor 13 and the 4th temperature sensor 14, the covering radiator 7 being arranged inside go out
5th temperature 15 of mouthful place's setting and the 6th temperature sensor 16 being arranged inside, 9 entry position of distributing T-pipe control valve
7th temperature sensor 17, conventional heat pipe manage the 8th temperature sensor 103 of 101 outlet port of fuel reserve tank in system 100, heat
9th temperature sensor 104 of 102 upstream of loaded components.
According to one embodiment of present invention, as shown in figure 4, reflux steering control valve 1 is measured according to temperature sensor 11
Return fuel temperature TreAnd the oil storage temperature T that temperature sensor 103 measuresmtControl reflux turns to, when return fuel temperature
Degree is higher than one preset value delta T of oil storage temperaturesetMore than, i.e. Tre>Tmt+ΔTsetWhen, reflux switching valve control return fuel flows into
In hot oil case 2, otherwise controls return fuel and flow into fuel reserve tank 101.
According to one embodiment of present invention, as shown in figure 5, engine flue radiator flow control valve 6 is according to second
The inlet and outlet fuel oil temperature T that temperature sensor 12, third temperature sensor 13 measureht、Tfh,out(inlet temperature is hot oil case
Outlet fuel temperature Tfh,in=Tht) and the 4th temperature sensor 14 measurement engine air duct air themperature Tfa, control quilt
The flow of cooling fuel oil.It is too low by the fuel flow of flue radiator, it is unable to fully the cooling capacity using air duct air,
Flow is excessively high to be will lead to fuel oil to be unable to fully the consumption of cooling and transfer tube more powerful.Therefore when heat sink temperature is lower than entrance fuel oil
Temperature, i.e. Tfa<ThtWhen, the heat exchange efficiency that control fuel flow meets flue radiator is stablized in a predetermined efficiency etaset1, i.e.,
(Tht-Tfh,out)/(Tht-Tfa)→ηset1；When heat sink temperature is higher than entrance fuel oil temperature Tfa>ThtWhen, close flow control valve.
Similarly, as shown in figure 5, covering radiator flow control valve 8 is according to second temperature sensor 12, the 5th temperature sensing
The inlet and outlet fuel oil temperature T that device 15 measuresht、Tsh,outAnd the 6th temperature sensor 16 measure stressed-skin construction temperature Tskin,
The cooled fuel flow of control.Fuel flow by covering radiator is too low, is unable to fully the heat sink cooling using covering
Ability, flow is excessively high to be will lead to fuel oil to be unable to fully the consumption of cooling and transfer tube more powerful.Therefore when stressed-skin construction temperature is low
In entrance fuel oil temperature, i.e. Tskin<ThtWhen, the heat exchange efficiency that control fuel flow meets covering radiator is stablized predetermined at one
Efficiency etaset2, i.e. (Tht-Tsh,out)/(Tht-Tfa)→ηset2；When heat sink temperature is higher than entrance fuel oil temperature Tskin>ThtWhen, it closes
Flow control valve.
According to one embodiment of present invention, as shown in fig. 6, distributing T-pipe control valve 9 is according to the 7th temperature sensor 17
Hot oil temperature T after the cooling of measurementcf, the 8th temperature sensor 103 measurement oil storage temperature TmtAnd the 9th temperature sensor
The mixing ignition oil temperature T of 104 measurementsmix, controlling cooling after-burning oil is that two-way inflow conventional heat pipe reason 100 fuel oil of system is cold
But it in circuit, or flows through pressure difference turbine 10 and returns to hot oil case 2.The temperature of fuel oil is higher than oil storage temperature T after being cooledcf>Tmt
When, all cooled fuel flow returns are controlled into hot oil case by flow divider；The temperature of fuel oil is lower than oil storage temperature after being cooled,
That is Tcf<TmtWhen, mixed pour point temperature is stablized to a predetermined value T by flow divider control mixed flow fuel flowset；It is noticeable
It is that under such operating condition when cooled fuel oil temperature is higher or flow is smaller, all cooled fuel oil, which participates in mixed flow, to remain unchanged
Mixed pour point temperature can not be reduced to predetermined value Tset, aperture of the holding flow divider in mixed flow direction is 1 at this time.
Claims (10)
1. a kind of aircraft heat management system, characterized by comprising:
Conventional heat pipe manages system (100), and
Hot oil case circuit is assisted,
It includes: fuel reserve tank (101), thermal force component (102) that conventional heat pipe, which manages system (100),
Auxiliary hot oil case circuit includes: reflux steering control valve (1), hot oil case (2), hot oil transfer tube (3), check valve
(4), engine flue radiator (5), first flow control valve (6), covering radiator for engine flue radiator (5)
(7), second flow control valve (8), distributing T-pipe control valve (9), the pressure difference turbine (10) of covering radiator (7) are used for, in which:
The reflux steering control valve (1) is arranged on the return line of conventional heat pipe reason system (100), and reflux turns to control
Two outlet ends of valve (1) processed pass through pipeline respectively and are connected to fuel reserve tank (101) and hot oil case (2), flow back steering control valve (1)
It is adjusted and is turned to according to the temperature of return fuel；
Outlet, pressurization transfer tube (3), check valve (4) and the engine flue radiator in parallel of the hot oil case (2)
(5), covering radiator (7) is sequentially connected with by the road；
First flow control valve (6) is arranged on the upstream of the engine flue radiator (5), flows through air duct for controlling
The flow of the cooled fuel oil of radiator；
Second flow control valve (8) is arranged on the upstream of the covering radiator (7), flows through covering radiator for controlling
Cooled fuel flow；
It is determined by the fuel oil total flow that hot oil case (2) are flowed out by the aperture of first flow control valve (6) and second flow control valve (8)
It is fixed；
The entrance of the distributing T-pipe control valve (9) and the fuel outlet of engine flue radiator (5) and covering radiate
The fuel outlet of device (7) is connected to, and the first outlet of distributing T-pipe control valve (9) is by pipeline through pressure difference turbine (10) and hot oil case
(2) entrance is connected to, and the second outlet of distributing T-pipe control valve (9) passes through pipeline in the mixing of thermal force component (102) upstream end
Point is connected to the fuel oil cooling circuit of conventional heat pipe reason system (100).
2. aircraft heat management system according to claim 1, it is characterised in that:
The auxiliary hot oil case circuit further comprises: passing in the first temperature of reflux steering control valve (1) inlet setting
Sensor (11) is exported in the second temperature sensor (12) of hot oil case (2) exit setting, in engine flue radiator (6)
Locate interior the 4th temperature sensor (14) being arranged of third temperature sensor (13), engine flue radiator (5) of setting, covering
Interior the 6th temperature sensor being arranged of the 5th temperature sensor (15), covering radiator 7 of skin radiator (7) exit setting
(16), in the 7th temperature sensor (17) of distributing T-pipe control valve (9) inlet setting；
Conventional heat pipe reason system (100) further comprises: in the 8th temperature sensor of fuel reserve tank (101) exit setting
(103) and in the 9th temperature sensor (104) that thermal force component (102) upstream end is arranged, it is used for hot oil case subsidiary loop
Control.
3. aircraft heat management system described in one of -2 according to claim 1, it is characterised in that:
A fuel tank close to the center of gravity of airplane in the hot oil case (2) airplane fuel tank system is realized, and avoids setting volume
Exterior part increases take-off weight.
4. aircraft heat management system described in one of -2 according to claim 1, it is characterised in that:
The reflux steering control valve (1) includes three-way diverter valve and controller, for according to the first temperature sensor (11)
The return fuel temperature of measurement and the fuel reserve tank fuel oil temperature of the 8th temperature sensor (103) measurement control return fuel stream
Road,
Wherein:
When return fuel temperature is higher than one predetermined value of oil storage temperature or more, reflux steering control valve (1) controls return fuel
It flows into hot oil case (2),
When return fuel temperature is not above one predetermined value of oil storage temperature or more, reflux steering control valve (1) control reflux
Fuel oil flows into fuel reserve tank (101).
5. aircraft heat management system described in one of -2 according to claim 1, it is characterised in that:
The engine flue radiator (5) is located in the outer culvert air duct of engine (200), belongs to annular radiator；
First flow control valve (6) includes flow valve and controller, for according to second and third temperature sensor (12 and 13)
The flue radiator inlet and outlet fuel oil temperature of measurement and the air duct air themperature of the 4th temperature sensor (14) measurement, control stream
Fuel flow through flue radiator,
Wherein:
When the temperature of air duct air is lower than hot oil temperature, flow valve (6) aperture regulation fuel flow is controlled, flue radiator is made
Heat exchange efficiency is stablized in a default efficiency.
The covering radiator (7) is located on the inside of aircraft skin (300), is integrated in one by fine and closely woven pipeline and stressed-skin construction
It rises；
Second flow control valve (8) includes flow valve and controller, for according to second and the 5th temperature sensor (12 and 15)
The covering radiator inlet and outlet fuel oil temperature of measurement and the stressed-skin construction temperature of the 6th temperature sensor (16) measurement, control stream
Fuel flow through radiator,
Wherein:
When stressed-skin construction temperature is lower than hot oil temperature, the aperture of first flow control valve (6) is controlled to adjusting fuel flow,
Control target is to stablize covering radiator heat exchange efficiency in a default efficiency,
The distributing T-pipe control valve (9) includes three-way flow divider valve and controller, for according to the 7th to the 9th temperature sensing
Fuel oil temperature after the temperature, oil storage temperature and mixed flow of hot oil after the cooling that device (17,103 and 104) measures respectively controls cold
But the shunt ratio of fuel oil after,
Wherein:
When fuel oil temperature after cooling is lower than oil storage temperature, increase the fuel oil stream for leading to the cooling circuit of conventional heat pipe reason system
Amount, control strategy be to try to reduce the fuel oil temperature at the mixing point until stablize in a predetermined temperature, if having it is extra
Cooling after fuel oil then make the latter through pressure difference turbine (10) return hot oil case (2).
6. based on a kind of aircraft thermal management algorithm of aircraft heat management system, the aircraft heat management system includes:
Conventional heat pipe manages system (300), and
Hot oil case circuit is assisted,
It includes: fuel reserve tank (101), thermal force component (102) that conventional heat pipe, which manages system (300),
Auxiliary hot oil case circuit includes: reflux steering control valve (1), hot oil case (2), hot oil transfer tube (3), check valve
(4), engine flue radiator (5), first flow control valve (6), covering radiator for engine flue radiator (5)
(7), it is used for second flow control valve (8), distributing T-pipe control valve (9), the pressure difference turbine (10) of covering radiator (7), it is special
Sign is
Reflux steering control valve (1) setting on the return line of conventional heat pipe reason system (300), make the steering control valve that flows back
(1) two outlet ends pass through pipeline respectively and are connected to fuel reserve tank (101) and hot oil case (2), and according to the temperature of return fuel
The steering of adjustment reflux steering control valve (1)；
The engine air duct radiation of the outlet of the hot oil case (2), pressurization transfer tube (3), check valve (4) and parallel connection
Device (5), covering radiator (7) are sequentially connected with by the road；
First flow control valve (6) is arranged in the upstream of the engine flue radiator (5), control flows through air duct radiation
The flow of the cooled fuel oil of device；
Second flow control valve (8) is arranged in the upstream of the covering radiator (7), control flows through the quilt of covering radiator
Cooling fuel flow；
It is controlled by the aperture of first flow control valve (6) and second flow control valve (8) and is always flowed by the fuel oil that hot oil case (2) flows out
Amount；
The entrance of the distributing T-pipe control valve (9) and the fuel outlet of engine flue radiator (5) and covering are dissipated
The fuel outlet of hot device (7) is connected to, and the first outlet of distributing T-pipe control valve (9) is passed through pipeline through pressure difference turbine (10) and heat
The second outlet of distributing T-pipe control valve (9) is passed through pipeline in thermal force component (102) upstream end by the connection of fuel tank (2) entrance
The fuel oil cooling circuit of mixing point and conventional heat pipe reason system (300) be connected to.
7. aircraft thermal management algorithm according to claim 6, it is characterised in that:
The auxiliary hot oil case circuit further comprises: passing in the first temperature of reflux steering control valve (1) inlet setting
Sensor (11) is exported in the second temperature sensor (12) of hot oil case (2) exit setting, in engine flue radiator (6)
Locate interior the 4th temperature sensor (14) being arranged of third temperature sensor (13), engine flue radiator (5) of setting, covering
Interior the 6th temperature sensor being arranged of the 5th temperature sensor (15), covering radiator 7 of skin radiator (7) exit setting
(16), in the 7th temperature sensor (17) of distributing T-pipe control valve (9) inlet setting；
Conventional heat pipe reason system (300) further comprises: in the 8th temperature sensor of fuel reserve tank (101) exit setting
(103) and in the 9th temperature sensor (104) that thermal force component (102) upstream end is arranged, it is used for hot oil case subsidiary loop
Control.
8. aircraft thermal management algorithm according to claim 6, it is characterised in that further comprise:
Use a fuel tank close to the center of gravity of airplane in airplane fuel tank system as the hot oil case (2), to avoid being arranged
Additional components increase take-off weight.
9. aircraft thermal management algorithm according to claim 6, it is characterised in that:
The reflux steering control valve (1) includes three-way diverter valve and controller, for according to the first temperature sensor (11)
The return fuel temperature of measurement and the fuel reserve tank fuel oil temperature of the 8th temperature sensor (103) measurement control return fuel stream
Road,
First flow control valve (6) includes flow valve and controller, for according to second and third temperature sensor (12 and 13)
The flue radiator inlet and outlet fuel oil temperature of measurement and the air duct air themperature of the 4th temperature sensor (14) measurement, control stream
Fuel flow through flue radiator,
The engine flue radiator (5) is located in the outer culvert air duct of engine (200), belongs to annular radiator；
The aircraft thermal management algorithm further comprises:
When return fuel temperature is higher than one predetermined value of oil storage temperature or more, with reflux steering control valve (1) control reflux combustion
Oil stream enters in hot oil case (2),
When return fuel temperature is not above one predetermined value of oil storage temperature or more, controlled back with reflux steering control valve (1)
Fuel oil is flowed to flow into fuel reserve tank (101),
When the temperature of air duct air is lower than hot oil temperature, with the aperture regulation fuel flow of control flow valve (6), dissipate air duct
Hot device heat exchange efficiency is stablized 80%.
10. the aircraft thermal management algorithm according to one of claim 6-9, it is characterised in that:
The covering radiator (7) is located on the inside of aircraft skin (300), is integrated in one by fine and closely woven pipeline and stressed-skin construction
It rises,
Second flow control valve (8) includes flow valve and controller, for according to second and the 5th temperature sensor (12 and 15)
The covering radiator inlet and outlet fuel oil temperature of measurement and the stressed-skin construction temperature of the 6th temperature sensor (16) measurement, control stream
Fuel flow through radiator,
The distributing T-pipe control valve (9) includes three-way flow divider valve and controller, for according to the 7th to the 9th temperature sensing
Fuel oil temperature after the temperature, oil storage temperature and mixed flow of hot oil after the cooling that device (17,103 and 104) measures respectively, control combustion
The shunt ratio of oil,
The aircraft thermal management algorithm further comprises:
When stressed-skin construction temperature is lower than hot oil temperature, the aperture of first flow control valve (6) is controlled to adjusting fuel flow,
Control target is to stablize covering radiator heat exchange efficiency 80%,
When fuel oil temperature after cooling is lower than oil storage temperature, increase the fuel oil stream for leading to the cooling circuit of conventional heat pipe reason system
Amount, control strategy be to try to reduce the fuel oil temperature at the mixing point until stablize in a predetermined temperature, if having it is extra
Cooling after hot oil then make the latter through pressure difference turbine (10) return hot oil case (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811327729.4A CN109515728B (en) | 2018-11-08 | 2018-11-08 | Aircraft thermal management system and method with auxiliary hot oil tank loop |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811327729.4A CN109515728B (en) | 2018-11-08 | 2018-11-08 | Aircraft thermal management system and method with auxiliary hot oil tank loop |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109515728A true CN109515728A (en) | 2019-03-26 |
| CN109515728B CN109515728B (en) | 2021-03-09 |
Family
ID=65773813
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811327729.4A Active CN109515728B (en) | 2018-11-08 | 2018-11-08 | Aircraft thermal management system and method with auxiliary hot oil tank loop |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109515728B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920915A (en) * | 2019-12-17 | 2020-03-27 | 南京航空航天大学 | Self-adaptive thermal management control device and method for aircraft fuel system |
| CN112555028A (en) * | 2020-12-11 | 2021-03-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft fuel cooling system |
| CN112693617A (en) * | 2019-10-22 | 2021-04-23 | 南京航空航天大学 | Fuel oil heat sink composite modal pump drive two-phase flow cooling system and method |
| CN113716055A (en) * | 2021-08-17 | 2021-11-30 | 南京航空航天大学 | Fuel oil comprehensive heat management system and working method thereof |
| CN114441180A (en) * | 2020-11-02 | 2022-05-06 | 中国航发商用航空发动机有限责任公司 | Low-temperature durability test system and test method |
| CN114435582A (en) * | 2022-01-10 | 2022-05-06 | 南京理工大学 | Nearby-exhausting aircraft skin cooling system based on wind-liquid comprehensive cooling structure |
| CN114537686A (en) * | 2022-02-28 | 2022-05-27 | 中国科学技术大学 | Bimodal aircraft fuel tank system and use method |
| CN115535268A (en) * | 2022-11-28 | 2022-12-30 | 中国民用航空飞行学院 | Aircraft fuel cooling system based on flight safety guarantee |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4505124A (en) * | 1983-09-22 | 1985-03-19 | The United States Of America As Represented By The Secretary Of The Air Force | Heat management system for aircraft |
| CN1644892A (en) * | 2004-01-20 | 2005-07-27 | 联合工艺公司 | Thermal management system for an aircraft |
| CN203439266U (en) * | 2013-01-05 | 2014-02-19 | 中国航空工业集团公司西安飞机设计研究所 | An aircraft thermal management system guaranteeing reliable fuel supply for an engine |
| US20140216088A1 (en) * | 2013-02-06 | 2014-08-07 | Raytheon Company | Aircraft thermal management system for cooling using expendable coolants |
| CN104061762A (en) * | 2014-06-11 | 2014-09-24 | 建德市云峰碳酸钙有限公司 | Pre-drying device |
| CN106917684A (en) * | 2015-12-08 | 2017-07-04 | 通用电气公司 | Heat management system |
-
2018
- 2018-11-08 CN CN201811327729.4A patent/CN109515728B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4505124A (en) * | 1983-09-22 | 1985-03-19 | The United States Of America As Represented By The Secretary Of The Air Force | Heat management system for aircraft |
| CN1644892A (en) * | 2004-01-20 | 2005-07-27 | 联合工艺公司 | Thermal management system for an aircraft |
| CN203439266U (en) * | 2013-01-05 | 2014-02-19 | 中国航空工业集团公司西安飞机设计研究所 | An aircraft thermal management system guaranteeing reliable fuel supply for an engine |
| US20140216088A1 (en) * | 2013-02-06 | 2014-08-07 | Raytheon Company | Aircraft thermal management system for cooling using expendable coolants |
| CN104061762A (en) * | 2014-06-11 | 2014-09-24 | 建德市云峰碳酸钙有限公司 | Pre-drying device |
| CN106917684A (en) * | 2015-12-08 | 2017-07-04 | 通用电气公司 | Heat management system |
Non-Patent Citations (3)
| Title |
|---|
| 于喜奎等: "高超声速飞机热管理系统控制模型", 《航空动力学报》 * |
| 李楠等: "某飞机综合热能管理系统初步研究", 《民用飞机设计与研究》 * |
| 罗志会等: "新一代飞机自适应动力与热管理系统研究", 《航空科学技术》 * |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112693617A (en) * | 2019-10-22 | 2021-04-23 | 南京航空航天大学 | Fuel oil heat sink composite modal pump drive two-phase flow cooling system and method |
| CN112693617B (en) * | 2019-10-22 | 2022-04-22 | 南京航空航天大学 | Fuel oil heat sink composite modal pump drive two-phase flow cooling system and method |
| CN110920915A (en) * | 2019-12-17 | 2020-03-27 | 南京航空航天大学 | Self-adaptive thermal management control device and method for aircraft fuel system |
| CN114441180A (en) * | 2020-11-02 | 2022-05-06 | 中国航发商用航空发动机有限责任公司 | Low-temperature durability test system and test method |
| CN114441180B (en) * | 2020-11-02 | 2023-10-13 | 中国航发商用航空发动机有限责任公司 | Low-temperature endurance test system and test method |
| CN112555028B (en) * | 2020-12-11 | 2022-08-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft fuel cooling system |
| CN112555028A (en) * | 2020-12-11 | 2021-03-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft fuel cooling system |
| CN113716055A (en) * | 2021-08-17 | 2021-11-30 | 南京航空航天大学 | Fuel oil comprehensive heat management system and working method thereof |
| CN114435582A (en) * | 2022-01-10 | 2022-05-06 | 南京理工大学 | Nearby-exhausting aircraft skin cooling system based on wind-liquid comprehensive cooling structure |
| CN114537686A (en) * | 2022-02-28 | 2022-05-27 | 中国科学技术大学 | Bimodal aircraft fuel tank system and use method |
| CN114537686B (en) * | 2022-02-28 | 2024-02-06 | 中国科学技术大学 | Dual-mode aircraft fuel tank system and use method |
| CN115535268A (en) * | 2022-11-28 | 2022-12-30 | 中国民用航空飞行学院 | Aircraft fuel cooling system based on flight safety guarantee |
| CN115535268B (en) * | 2022-11-28 | 2023-03-14 | 中国民用航空飞行学院 | Aircraft fuel cooling system based on flight safety guarantee |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109515728B (en) | 2021-03-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109515728A (en) | Aircraft heat management system and method with auxiliary hot oil case circuit | |
| CN109969411B (en) | Aircraft fuel oil thermal management system and method with cold accumulation capacity | |
| US9869232B2 (en) | Variable-speed pump control for engine coolant system with variable restriction | |
| EP2651763B1 (en) | Method and device for controlling an aircraft air conditioning system | |
| CN103383121B (en) | Regional air conditioner dispersion secondary pumping system | |
| CN109582057B (en) | Environmental wind tunnel temperature control system | |
| US10358221B2 (en) | Hybrid method and aircraft for pre-cooling an environmental control system using a power generator four wheel turbo-machine | |
| CN109642499A (en) | The Enhancement Method and aircraft of environmental control system are precooled using the two-wheel turbine with supplement heat exchanger | |
| CN109863085A (en) | The advanced method and aircraft of environmental control system are precooled using the four wheeled turbine of double-compressor | |
| CN103562067B (en) | For the a/c system of aircraft passenger compartment | |
| CN109850168B (en) | Oil tank cooling subsystem of aircraft thermal management system | |
| US20100101251A1 (en) | Method And System For Controlling An Aircraft Air Conditioning System With Optimised Fuel Consumption | |
| CN104460790A (en) | Dynamic aviation thermal power testing system and rapid temperature and pressure control method | |
| CN106449036A (en) | Intelligent cooling system for traction transformer of electric multiple unit | |
| CN109731624A (en) | A kind of scientific experiment cupboards high-precision twin-stage temperature-controlling system based on thermoelectric heat pump | |
| CN203732277U (en) | Depth cold and hot impact testing system of medium-heavy diesel engine | |
| CN106882390A (en) | Airplane air entraining precooling heat regenerative system | |
| CN108190035A (en) | A kind of Inerting Aircraft Fuel Tanks device | |
| CN108194156A (en) | A kind of zero output heating system of low pressure (LP) cylinder and method of no cooling steam bypass | |
| CN103487101A (en) | Laboratory diesel consumption measuring and controlling system | |
| CN205825522U (en) | A kind of air energy heat pump water chiller-heater unit with automatic temp controller | |
| CN203240279U (en) | Vortex self-heating natural gas pressure regulating system | |
| US20150096288A1 (en) | Systems and Methods for Heat Balance and Transport for Aircraft Hydraulic Systems | |
| CN206040369U (en) | Electric multiple unit traction transformer intelligent cooling system | |
| CN106150658A (en) | Cooling control method in diesel engine of diesel locomotive cooling water system separate type |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |