CN109989832A - A kind of expansion pre-cooling cycle system for aerospace engine - Google Patents
A kind of expansion pre-cooling cycle system for aerospace engine Download PDFInfo
- Publication number
- CN109989832A CN109989832A CN201910333757.5A CN201910333757A CN109989832A CN 109989832 A CN109989832 A CN 109989832A CN 201910333757 A CN201910333757 A CN 201910333757A CN 109989832 A CN109989832 A CN 109989832A
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- Prior art keywords
- heat exchange
- pipeline
- expansion
- heat
- expansion cell
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03B—MACHINES OR ENGINES FOR LIQUIDS
- F03B3/00—Machines or engines of reaction type; Parts or details peculiar thereto
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel Cell (AREA)
Abstract
The invention discloses a kind of expansion pre-cooling cycle systems for aerospace engine, including the expansion cell that exchanges heat, heat is absorbed from the external world by heat exchanger in single basic heat exchange expansion cell, using low temp fuel as the outside output power of the turbine expansion of working medium acting, it is continuously absorbed heat in multiple basic heat exchange expansion cells being formed by connecting by low temp fuel working medium, acting, it makes full use of heat sink big using low temp fuel, heat sink the characteristics of further increasing after heat absorption working medium expansion work, make whole device that there is bigger caloric receptivity under limited low temp fuel flow, so that cooling required low temp fuel dosage is no more than burning dosage, and it can outside output power, after this expansion cooling recirculation system is used for aerospace flight vehicle dynamical system, cooling capacity of the low temp fuel as cold source can be given full play to, meet supersonic speed to fly Row device, hypersonic aircraft and mono-/bis-grade are entered the orbit the requirement of spacecraft.
Description
Technical field
The present invention relates to field of aerospace technology more particularly to a kind of expansion pre-cooling for aerospace engine to follow
Loop system.
Background technique
Military-civil field is for high-speed aircraft and to reduce space launch cost needs urgent therefore supersonic speed, superb
Velocity of sound aircraft and mono-/bis-grade spacecraft of entering the orbit have become one of research hotspot of aerospace field.
Currently, the main problem of above-mentioned aircraft is the high temperature due to high-speed flow stagnation generation during high-speed flight,
Existing aircraft and its power can not be fully met due to respective supersonic aircraft, hypersonic aircraft and single/
Twin-stage is entered the orbit the requirement of spacecraft.And by using low temp fuel used in aircraft as cold source to incoming flow high temperature gas flow into
Row cooling, can overcome the defect of existing aircraft and its power, be supersonic aircraft, hypersonic aircraft and mono-/bis-grade
The brand new technical path for spacecraft dynamical system of entering the orbit.
However for the prior art, current forecooler mostly uses aerospace to use low temp fuel as cold source, by
Temperature is high after incoming flow high-speed flow stagnation, and heat is big, leads to cool down required low temp fuel dosage greater than burning dosage, largely
Fuel the serious waste of fuel is directly caused by direct emission, this outer fuel always flows the heat absorbed in high temperature air also simultaneously
It is not fully used.Therefore poor using the aircraft power performance of existing Pre-cooling Mode, power specific impulse and thrust ratio
It is smaller, it is unable to satisfy supersonic aircraft, hypersonic aircraft and mono-/bis-grade and enters the orbit the requirement of spacecraft.
Therefore, a kind of expansion pre-cooling cycle system for aerospace engine how is provided, to give full play to low temperature
Cooling capacity of the fuel as cold source is current those skilled in the art technical problem urgently to be resolved.
Summary of the invention
In view of this, the purpose of the present invention is to provide a kind of expansion pre-cooling cycle systems for aerospace engine
System, to give full play to low temp fuel as the cooling capacity of cold source.
In order to achieve the above object, the invention provides the following technical scheme:
A kind of expansion pre-cooling cycle system for aerospace engine, including heat exchange expansion cell, the heat exchange are swollen
Swollen unit includes heat exchanger, first pipe, second pipe, third pipeline, valve and medium turbine, wherein
The outlet of the cold side of the heat exchanger has the first pipe, and the outlet of the medium turbine has described
Third pipeline,
The entrance of the second pipe is connected to the first pipe, the outlet of the second pipe and the third pipeline
Connection, the valve are arranged on the second pipe,
The entrance of the medium turbine is connected to the first pipe,
The working medium of the cold side of the heat exchanger is aerospace low temp fuel.
Preferably, above-mentioned heat exchange expansion cell is multiple.
Preferably, multiple heat exchange expansion cell serial communications, wherein the heat exchange expansion cell of adjacent two
In, the third pipeline of a upper heat exchange expansion cell is connected to the entrance of the cold side of next heat exchanger, shape
At serial communication.
Preferably, the above-mentioned expansion pre-cooling cycle system for aerospace engine further includes the 4th pipeline and the 5th
Pipeline, multiple heat exchange expansion cell parallel communications, wherein the cold side of the heat exchanger of each heat exchange expansion cell
Entrance be connected to the 4th pipeline, it is each it is described heat exchange expansion cell the third pipeline with the 5th pipeline
Connection.
Preferably, above-mentioned heat exchange expansion cell includes group unit and series connection group unit in parallel,
In the series connection group unit, multiple heat exchange expansion cell serial communications, wherein two adjacent heat exchange
In expansion cell, the third pipeline and next the described of expansion cell that exchange heat of a upper heat exchange expansion cell
The entrance of the cold side of heat exchanger is connected to, and forms serial communication,
It further include the 4th pipeline and the 5th pipeline in the group unit in parallel, multiple heat exchange expansion cell parallel connections connect
It is logical, wherein
The entrance of the cold side of the heat exchanger of each heat exchange expansion cell is connected to the 4th pipeline, each
The third pipeline of the heat exchange expansion cell is connected to the 5th pipeline,
Third pipeline and the in parallel group of unit of the last one heat exchange expansion cell in the series connection group unit
In the 4th pipeline connection.
Preferably, above-mentioned aerospace low temp fuel is liquid methane.
Preferably, above-mentioned heat exchanger is multiple.
Preferably, above-mentioned second pipe and the valve are multiple.
Provided by the present invention for the expansion pre-cooling cycle system of aerospace engine, including heat exchange expansion cell, institute
Stating heat exchange expansion cell includes heat exchanger, first pipe, second pipe, third pipeline, valve and medium turbine, wherein described
The outlet of the cold side of heat exchanger has the first pipe, and the outlet of the medium turbine has the third pipeline, institute
The entrance for stating second pipe is connected to the first pipe, and the outlet of the second pipe is connected to the third pipeline, described
Valve be arranged on the second pipe, the entrance of the medium turbine is connected to the first pipe, the heat exchanger it is cold
The working medium of side is aerospace low temp fuel.
Heat is absorbed, using low temp fuel as the whirlpool of working medium from the external world by heat exchanger in single basic heat exchange expansion cell
The outside output power of expansion work is taken turns, it is continuous in multiple basic heat exchange expansion cells being formed by connecting by low temp fuel working medium
Heat absorption, acting made full use of using heat sink the characteristics of further increasing after heat sink big, the heat absorption working medium expansion work of low temp fuel,
Make whole device that there is bigger caloric receptivity under limited low temp fuel flow, so that cooling required low temp fuel dosage is not more than
Burn dosage, and can outside output power, this expansion cooling recirculation system is used for aerospace flight vehicle dynamical system
Afterwards, cooling capacity of the low temp fuel as cold source can be given full play to, meet supersonic aircraft, hypersonic aircraft and
Mono-/bis-grade is entered the orbit the requirement of spacecraft.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is the present invention
Some embodiments for those of ordinary skill in the art without creative efforts, can also basis
These attached drawings obtain other attached drawings.
Fig. 1 is the structural schematic diagram of heat exchange expansion cell provided in an embodiment of the present invention；
Structural schematic diagram when Fig. 2 is multiple heat exchange expansion cell series connection provided in an embodiment of the present invention；
Structural schematic diagram when Fig. 3 is multiple heat exchange expansion cell parallel connections provided in an embodiment of the present invention；
Fig. 4 is structural schematic diagram when multiple heat exchange expansion cells provided in an embodiment of the present invention are series-parallel；
Structural schematic diagram when Fig. 5 is three provided in an embodiment of the present invention heat exchange expansion cell series connection.
In figure 1 above -5:
Heat exchanger 1, valve 2, medium turbine 3, the 4th pipeline 4, the 5th pipeline 5, heat exchange expansion cell 6, First Heat Exchanger
11, the first valve 12, first medium turbine 13, the second heat exchanger 14, the second valve 15, second medium turbine 16, third heat exchange
Device 17.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, those of ordinary skill in the art
Every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
Fig. 1-Fig. 5 is please referred to, Fig. 1 is the structural schematic diagram of heat exchange expansion cell provided in an embodiment of the present invention；Fig. 2 is this
Structural schematic diagram when multiple heat exchange expansion cells series connection that inventive embodiments provide；Fig. 3 is provided in an embodiment of the present invention more
Structural schematic diagram when a heat exchange expansion cell parallel connection；Fig. 4 be multiple heat exchange expansion cell strings provided in an embodiment of the present invention simultaneously
Structural schematic diagram when connection；Structural schematic diagram when Fig. 5 is three provided in an embodiment of the present invention heat exchange expansion cell series connection.
Expansion pre-cooling cycle system provided in an embodiment of the present invention for aerospace engine, including heat exchange expansion are single
Member 6, heat exchange expansion cell 6 include heat exchanger 1, first pipe, second pipe, third pipeline, valve 2 and medium turbine 3,
In, the outlet of the cold side of heat exchanger 1 has first pipe, and the outlet of medium turbine 3 has third pipeline, second pipe
Entrance is connected to first pipe, and the outlet of second pipe is connected to third pipeline, and valve 2 is arranged on second pipe, passes through valve
The working medium flow of medium turbine 3 is passed through in 2 regulation of door, and the entrance of medium turbine 3 is connected to first pipe, the cold side of heat exchanger 1
Working medium is aerospace low temp fuel, and aerospace low temp fuel can be liquid methane.The expansion cell 6 that exchanges heat is multiple.
Heat is absorbed, using low temp fuel as working medium from the external world by heat exchanger 1 in single basic heat exchange expansion cell 6
The outside output power of 3 expansion work of medium turbine, it is swollen in multiple basic heat exchange being formed by connecting by low temp fuel working medium
It continuously absorbs heat, do work in swollen unit 6, make full use of using heat sink into one after heat sink big, the heat absorption working medium expansion work of low temp fuel
The characteristics of step increases makes whole device have bigger caloric receptivity under limited low temp fuel flow, so that cooling required low temperature
Firing rate no more than burning dosage, and can outside output power, this expansion cooling recirculation system is used for aerospace
After Power System of Flight Vehicle, cooling capacity of the low temp fuel as cold source can be given full play to, meets supersonic aircraft, superb
Velocity of sound aircraft and mono-/bis-grade are entered the orbit the requirement of spacecraft.
Expansion pre-cooling cycle system provided in an embodiment of the present invention for aerospace engine is a kind of suitable for boat
The expansion pre-cooling cycle system of empty airspace engine is mainly used for supersonic aircraft, hypersonic aircraft and mono-/bis-grade and enters
The propulsion system of rail spacecraft.
When it is implemented, multiple heat exchange expansion cells 6 can be series connection, it is also possible to parallel connection, is also possible to series-parallel phase
In conjunction with.
When series connection, multiple 6 serial communications of heat exchange expansion cell, wherein in two adjacent heat exchange expansion cells 6, upper one
The third pipeline of a heat exchange expansion cell 6 is connected to the entrance of the cold side of next heat exchanger 6, forms serial communication.
When in parallel, the above-mentioned expansion pre-cooling cycle system for aerospace engine further includes the 4th pipeline 4 and
Five pipelines 5, multiple 6 parallel communications of heat exchange expansion cell, wherein the entrance of the cold side of the heat exchanger 1 of each heat exchange expansion cell 6
It is connected to the 4th pipeline 4, the third pipeline of each heat exchange expansion cell 6 is connected to the 5th pipeline 5.
When series-parallel, heat exchange expansion cell 6 includes in parallel group unit and series connection group unit, in series connection group unit, Duo Gehuan
Thermally expand 6 serial communication of unit, wherein in two adjacent heat exchange expansion cells 6, the third of upper heat exchange expansion cell 6
Pipeline is connected to the entrance of the cold side of next heat exchanger 1, forms serial communication, and it further includes the 4th pipeline 4 that parallel connection, which is organized in unit,
With the 5th pipeline 5, multiple 6 parallel communications of heat exchange expansion cell, wherein the cold side of the heat exchanger 1 of each heat exchange expansion cell 6
Entrance is connected to the 4th pipeline 4, and the third pipeline of each heat exchange expansion cell 6 is connected to the 5th pipeline 5, series connection group unit
In the third pipeline of the last one heat exchange expansion cell 6 organize the 4th pipeline 4 in unit in parallel and be connected to.
In order to advanced optimize above scheme, in the single expansion cell 6 that exchanges heat, heat exchanger 1 can be multiple.Second pipe
It can be multiple with valve 2.
For when connecting:
Expansion pre-cooling cycle system provided in an embodiment of the present invention for aerospace engine includes that three heat exchange are swollen
Swollen unit 6, first heat exchange expansion cell includes First Heat Exchanger 11, the first valve 12, first medium turbine 13, and second is changed
Thermally expanding unit includes the second heat exchanger 14, the second valve 15, second medium turbine 16, and the third expansion cell that exchanges heat includes the
Three heat exchangers 17,
Working medium is selected as low temp fuel liquid methane, and systematic working medium inlet pressure is 25MPa, and systematic working medium inlet temperature is
100K, working medium are 500K, first medium turbine in First Heat Exchanger 11, the second heat exchanger 14,17 outlet temperature of third heat exchanger
13 with 16 expansion ratio of second medium turbine be 5, isentropic efficiency is 0.8, then according to calculating analyze the system working medium into
Mouth 100K, exporting specific discharge working medium caloric receptivity under 500K operating condition is 1986.6kJ/kg, system unit working medium flow output power
For 566.6kJ/kg；Tradition only chooses identical working medium using heat exchanger, operating condition exchanges heat, and specific discharge working medium caloric receptivity is
1357.1kJ/kg and can not output power；In contrast, provided in an embodiment of the present invention for the swollen of aerospace engine
Swollen pre-cooling cycle system makes specific discharge working medium caloric receptivity improve 46.4%, additional output power 566.6kJ/kg.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (8)
1. a kind of expansion pre-cooling cycle system for aerospace engine, which is characterized in that including the expansion cell that exchanges heat, institute
Stating heat exchange expansion cell includes heat exchanger, first pipe, second pipe, third pipeline, valve and medium turbine, wherein
The outlet of the cold side of the heat exchanger has the first pipe, and the outlet of the medium turbine has the third
Pipeline,
The entrance of the second pipe is connected to the first pipe, and the outlet of the second pipe and the third pipeline connect
Logical, the valve is arranged on the second pipe,
The entrance of the medium turbine is connected to the first pipe,
The working medium of the cold side of the heat exchanger is aerospace low temp fuel.
2. the expansion pre-cooling cycle system according to claim 1 for aerospace engine, which is characterized in that described
The expansion cell that exchanges heat is multiple.
3. the expansion pre-cooling cycle system according to claim 2 for aerospace engine, which is characterized in that multiple
The heat exchange expansion cell serial communication, wherein
In the heat exchange expansion cell of adjacent two, it is upper one it is described heat exchange expansion cell the third pipeline with it is next
The entrance of the cold side of the heat exchanger is connected to, and forms serial communication.
4. the expansion pre-cooling cycle system according to claim 2 for aerospace engine, which is characterized in that also wrap
The 4th pipeline and the 5th pipeline are included,
Multiple heat exchange expansion cell parallel communications, wherein
The entrance of the cold side of the heat exchanger of each heat exchange expansion cell is connected to the 4th pipeline, each described
The third pipeline of heat exchange expansion cell is connected to the 5th pipeline.
5. the expansion pre-cooling cycle system according to claim 2 for aerospace engine, which is characterized in that described
The expansion cell that exchanges heat includes group unit and series connection group unit in parallel,
In the series connection group unit, multiple heat exchange expansion cell serial communications, wherein the heat exchange expansion of adjacent two
In unit, the heat exchange of the third pipeline and next heat exchange expansion cell of a upper heat exchange expansion cell
The entrance of the cold side of device is connected to, and forms serial communication,
It further include the 4th pipeline and the 5th pipeline in the group unit in parallel, multiple heat exchange expansion cell parallel communications,
In,
The entrance of the cold side of the heat exchanger of each heat exchange expansion cell is connected to the 4th pipeline, each described
The third pipeline of heat exchange expansion cell is connected to the 5th pipeline,
In the series connection group unit the last one it is described heat exchange expansion cell third pipeline in the in parallel group of unit
The connection of 4th pipeline.
6. the expansion pre-cooling cycle system according to claim 1 for aerospace engine, which is characterized in that described
Aerospace low temp fuel is liquid methane.
7. the expansion pre-cooling cycle system according to claim 1 for aerospace engine, which is characterized in that described
Heat exchanger is multiple.
8. the expansion pre-cooling cycle system according to claim 1 for aerospace engine, which is characterized in that described
Second pipe and the valve are multiple.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910333757.5A CN109989832A (en) | 2019-04-24 | 2019-04-24 | A kind of expansion pre-cooling cycle system for aerospace engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910333757.5A CN109989832A (en) | 2019-04-24 | 2019-04-24 | A kind of expansion pre-cooling cycle system for aerospace engine |
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| CN109989832A true CN109989832A (en) | 2019-07-09 |
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| CN201910333757.5A Pending CN109989832A (en) | 2019-04-24 | 2019-04-24 | A kind of expansion pre-cooling cycle system for aerospace engine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112377325A (en) * | 2020-11-09 | 2021-02-19 | 北京航空航天大学 | Hypersonic strong precooling turbine-based stamping combined engine |
| CN114542289A (en) * | 2021-12-31 | 2022-05-27 | 北京动力机械研究所 | Precooling engine energy cascade system and design method thereof |
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| US6799417B2 (en) * | 2003-02-05 | 2004-10-05 | Aerojet-General Corporation | Diversion of combustion gas within a rocket engine to preheat fuel |
| CN109372657A (en) * | 2018-08-31 | 2019-02-22 | 西安航天动力研究所 | A kind of novel precooled air combined engine |
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| US3747339A (en) * | 1961-11-13 | 1973-07-24 | Texaco Inc | Reaction propulsion engine and method of operation |
| US4707982A (en) * | 1981-06-26 | 1987-11-24 | Rockwell International Corporation | Thermal regenerative injector |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112377325A (en) * | 2020-11-09 | 2021-02-19 | 北京航空航天大学 | Hypersonic strong precooling turbine-based stamping combined engine |
| CN112377325B (en) * | 2020-11-09 | 2022-06-03 | 北京航空航天大学 | Hypersonic strong precooling turbine-based stamping combined engine |
| CN114542289A (en) * | 2021-12-31 | 2022-05-27 | 北京动力机械研究所 | Precooling engine energy cascade system and design method thereof |
| CN114542289B (en) * | 2021-12-31 | 2024-04-09 | 北京动力机械研究所 | Precooling engine energy cascade system and design method thereof |
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