CN101602407A - Cooling system of hypersonic aircraft based on the ammoniacal liquor Rankine cycle - Google Patents
Cooling system of hypersonic aircraft based on the ammoniacal liquor Rankine cycle Download PDFInfo
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- CN101602407A CN101602407A CNA200910072452XA CN200910072452A CN101602407A CN 101602407 A CN101602407 A CN 101602407A CN A200910072452X A CNA200910072452X A CN A200910072452XA CN 200910072452 A CN200910072452 A CN 200910072452A CN 101602407 A CN101602407 A CN 101602407A
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Abstract
Based on the cooling system of hypersonic aircraft of ammoniacal liquor Rankine cycle, it relates to a kind of cooling system of hypersonic aircraft.The objective of the invention is for solve existing hypersonic aircraft especially the scramjet engine cooling difficulty, cooling is big with flow fuel and the problem of insufficient heat sink.One end of center shaft is connected with electrical generator, and the other end of center shaft is connected with petrolift with circulation pump respectively, and steam turbine is contained on the center shaft and between circulation pump and electrical generator, cooling-gallery is arranged on the outside wall surface on driving engine top.The present invention is used for the thermal protection of hypersonic aircraft and the cooling of scramjet engine.
Description
Technical field
The present invention relates to a kind of cooling system of hypersonic aircraft.
Background technology
Flight Mach number is a big focus of current research greater than 5 hypersonic aircraft, comprises development single-stage or two-stage enter the orbit aerospace plane, world shuttle working device and hypersonic cruise missile etc.One of the gordian technique that with the scramjet engine is the air suction type hypersonic aircraft of propulsion system is the thermal protection of aircraft, wherein engine cooling is wherein the most difficult part, even because adopt composite material also to be difficult to bear the huge thermal load that produces at engine interior.It is generally acknowledged that fuel is best cooling system conditioner, yet theoretical analysis and practice show, coolant flow will be used fuel flow greater than advancing after reaching a certain flight Mach number, have to carry extra fuel, and unnecessary cooling can only be abandoned with fuel, and the unnecessary fuel that flies for a long time carries and will bring serious quality punishment to aircraft.
In order to improve the fuel cooling power, the heat absorbing type hydrocarbon fuel all is devoted to develop in countries in the world, because the reaction of hydrocarbon fuel generation heat absorbing type can provide higher heat sink (cooling power).At present, also do not develop conversion ratio height, long catalysts of life-span both at home and abroad, the coking carbon deposit is insoluble always bottleneck problem.Can't improve again by other approach and hydrogen fuel is heat sink.Therefore, the fuel insufficient heat sink is limiting the development of hypersonic aircraft always.
Summary of the invention
The objective of the invention is to have proposed a kind of cooling system of hypersonic aircraft based on the ammoniacal liquor Rankine cycle for the scramjet engine cooling difficulty that solves existing hypersonic aircraft, the problem of cooling off and insufficient heat sink big with flow fuel.
The present invention solves the problems of the technologies described above the technical scheme of taking to be: described cooling system comprises aircraft, driving engine, cooling-gallery, Fuel Tank and petrolift, described cooling system also comprises circulation pump, steam turbine, condenser, electrical generator and center shaft, one end of described center shaft is connected with electrical generator, the other end of described center shaft is connected with petrolift with circulation pump respectively, described steam turbine is contained on the center shaft and between circulation pump and electrical generator, described cooling-gallery is arranged on the outside wall surface on driving engine top; Described circulation delivery side of pump is connected by the input end of pipeline with the aircraft cooling-gallery, the mouth of described aircraft cooling-gallery is connected with the input end of cooling-gallery in the driving engine by pipeline, the mouth of cooling-gallery is connected with the input end of steam turbine by pipeline, the mouth of described steam turbine is connected by the input end of pipeline with the condenser high temperature side, and the mouth of described condenser high temperature side connects and composes the ammoniacal liquor Rankine cycle by the input end of pipeline and circulation pump; The input end of described petrolift is connected with Fuel Tank by pipeline, the fuel delivery side of pump is connected by the input end of pipeline with the condenser low temperature side, the mouth of condenser low temperature side is connected with driving engine by pipeline, the working medium of described ammoniacal liquor Rankine cycle is as the cooling system conditioner of hypersonic aircraft, the fuel of described ammoniacal liquor Rankine cycle is as indirect cooling system conditioner, and the working medium of described ammoniacal liquor Rankine cycle is ammoniacal liquor.
The present invention has following beneficial effect: system of the present invention finishes the cooling of hypersonic aircraft and scramjet engine by the ammoniacal liquor Rankine cycle, and working medium is ammoniacal liquor, belongs to non-azeotropic mixed working medium, and the hot working fluid physical property changes with the change of ammonia concentration.Fuel is not re-used as the direct quenching agent, and as the low-temperature heat source at ammoniacal liquor Rankine cycle condenser place, is used to cool off ammonia vapor.Because the fuel absorbed heat is the outwards heat of discharging of ammoniacal liquor Rankine cycle, it only is the part of whole hypersonic aircraft and scramjet engine heat dissipation capacity, needing fuel to absorb the heat of taking away reduces greatly, this part heat of heat sink enough absorptions of fuel greatly reduces the demand of cooling with fuel flow.Simultaneously, the used heat of hypersonic aircraft and scramjet engine has obtained effective utilization, steam turbine drives electrical generator work, has realized that heat energy is finally to the conversion of electric energy.
Description of drawings
Fig. 1 is an integral structure scheme drawing of the present invention, and Fig. 2 is the principle of work scheme drawing of cooling system of the present invention.
The specific embodiment
The specific embodiment one: present embodiment is described in conjunction with Fig. 1, described cooling system comprises aircraft 2, driving engine 3, cooling-gallery 4, Fuel Tank 7 and petrolift 8, described cooling system also comprises circulation pump 1, steam turbine 5, condenser 6, electrical generator 9 and center shaft 10, one end of described center shaft 10 is connected with electrical generator 9, the other end of described center shaft 10 is connected with petrolift 8 with circulation pump 1 respectively, described steam turbine 5 is contained on the center shaft 10 and between circulation pump 1 and electrical generator 9, described cooling-gallery 4 is arranged on the outside wall surface on driving engine 3 tops; The mouth of described circulation pump 1 is connected by the input end of pipeline with aircraft 2 cooling-gallerys, the mouth of described aircraft 2 cooling-gallerys is connected with the input end of cooling-gallery 4 in the driving engine 3 by pipeline, the mouth of described cooling-gallery 4 is connected by the input end of pipeline with steam turbine 5, the mouth of described steam turbine 5 is connected by the input end of pipeline with condenser 6 high temperature sides, and the mouth of described condenser 6 high temperature sides connects and composes the ammoniacal liquor Rankine cycle by the input end of pipeline and circulation pump 1; The input end of described petrolift 8 is connected with Fuel Tank 7 by pipeline, the mouth of described petrolift 8 is connected by the input end of pipeline with condenser 6 low temperature sides, the mouth of condenser 6 low temperature sides is connected with driving engine 3 by pipeline, the working medium of described ammoniacal liquor Rankine cycle is as the cooling system conditioner of hypersonic aircraft, the fuel of described ammoniacal liquor Rankine cycle is as indirect cooling system conditioner, and the working medium of described ammoniacal liquor Rankine cycle is ammoniacal liquor.Described fuel is hydrogen or hydrocarbon fuel.
Principle of work: during initialization, starter-generator 9 plays electrical motor by electrical generator 9 and drives steam turbine 5 rotations, and steam turbine 5 drives circulation pump 1 and electrical generator 9 work respectively by center shaft 10.Circulation pump 1 enters aircraft 2 cooling-gallerys after with the supercharging of liquid ammonia aqueous mixtures aircraft is cooled off, absorb the heat that fuel sheds in driving engine 3 burnings, the 4 pairs of driving engines 3 of cooling-gallery that enter driving engine 3 cool off and are heated to the condition of high temperature, the ammonia vapor of the High Temperature High Pressure steam turbine 5 acting back temperature, pressures that expand of flowing through all reduce subsequently, promoting steam turbine 5 rotates, steam turbine 5 drives electrical generator 9 work, promptly realizes generating; Last ammoniacal liquor enters condenser 6 by initial condition that fuel is cooled to.Petrolift 8 is extracted into the fuel in the Fuel Tank 7 and is pressurized to the supercritical pressure state in the petrolift 8, and fuel enters 6 pairs of ammoniacal liquor of condenser and cools off.At last, fuel enters by the road in the driving engine 3 and burns.
Rankine cycle is a prior art, also is the modal a kind of power generation cycle in surface power station, and cycle fluid mostly is water greatly.Ammoniacal liquor also is used to Rankine cycle as cycle fluid in recent years as a kind of compound, is called as the ammoniacal liquor Rankine cycle.The ammoniacal liquor Rankine cycle has been a mature technology in the surface power station.Ammoniacal liquor is a kind of zeotrope, the isobaric phase transition process of zeotrope is an alternating temperature process, if just can reach satisfied temperature coupling with the thermal source and the low-temperature receiver of alternating temperature with its working medium as power cycle, reduce the available energy loss of evaporation and condensation process, improve the on-cycle generating efficiency, this is the maximum characteristics of ammoniacal liquor Rankine cycle.
Claims (2)
1, a kind of cooling system of hypersonic aircraft based on the ammoniacal liquor Rankine cycle, described cooling system comprises aircraft (2), driving engine (3), cooling-gallery (4), Fuel Tank (7) and petrolift (8), it is characterized in that described cooling system also comprises circulation pump (1), steam turbine (5), condenser (6), electrical generator (9) and center shaft (10), one end of described center shaft (10) is connected with electrical generator (9), the other end of described center shaft (10) is connected with petrolift (8) with circulation pump (1) respectively, described steam turbine (5) is contained on the center shaft (10) and is positioned between circulation pump (1) and the electrical generator (9), and described cooling-gallery (4) is arranged on the outside wall surface on driving engine (3) top; The mouth of described circulation pump (1) is connected by the input end of pipeline with aircraft (2) cooling-gallery, the mouth of described aircraft (2) cooling-gallery is connected with the input end of cooling-gallery (4) in the driving engine (3) by pipeline, the mouth of described cooling-gallery (4) is connected by the input end of pipeline with steam turbine (5), the mouth of described steam turbine (5) is connected by the input end of pipeline with condenser (6) high temperature side, and the mouth of described condenser (6) high temperature side connects and composes the ammoniacal liquor Rankine cycle by the input end of pipeline and circulation pump (1); The input end of described petrolift (8) is connected with Fuel Tank (7) by pipeline, the mouth of described petrolift (8) is connected by the input end of pipeline with condenser (6) low temperature side, the mouth of described condenser (6) low temperature side is connected with driving engine (3) by pipeline, the working medium of described ammoniacal liquor Rankine cycle is as the cooling system conditioner of hypersonic aircraft, the fuel of described ammoniacal liquor Rankine cycle is as indirect cooling system conditioner, and the working medium of described ammoniacal liquor Rankine cycle is ammoniacal liquor.
2. the cooling system of hypersonic aircraft based on the ammoniacal liquor Rankine cycle according to claim 1 is characterized in that described fuel is hydrogen or hydrocarbon fuel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910072452XA CN101602407B (en) | 2009-07-02 | 2009-07-02 | Hypersonic speed aircraft cooling system based on ammonia water Rankine cycle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910072452XA CN101602407B (en) | 2009-07-02 | 2009-07-02 | Hypersonic speed aircraft cooling system based on ammonia water Rankine cycle |
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| CN101602407A true CN101602407A (en) | 2009-12-16 |
| CN101602407B CN101602407B (en) | 2011-01-19 |
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| CN200910072452XA Expired - Fee Related CN101602407B (en) | 2009-07-02 | 2009-07-02 | Hypersonic speed aircraft cooling system based on ammonia water Rankine cycle |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104989550A (en) * | 2015-07-22 | 2015-10-21 | 北京航空航天大学 | Liquid-nitrogen cooling system of scramjet engine |
| CN105888880A (en) * | 2016-05-31 | 2016-08-24 | 南京航空航天大学 | Scramjet engine water cooling device and work method thereof |
| CN107738755A (en) * | 2017-11-16 | 2018-02-27 | 中国运载火箭技术研究院 | It is a kind of to adapt to efficiently main passive heat management system and its design method that the world comes and goes |
| CN111907721A (en) * | 2020-08-18 | 2020-11-10 | 西北工业大学 | Sleeve passage for cooling high-temperature part of aircraft |
| CN112160837A (en) * | 2020-09-18 | 2021-01-01 | 中国航发四川燃气涡轮研究院 | Closed circulation heat management integrated system based on supercritical medium |
| CN112377324A (en) * | 2020-11-18 | 2021-02-19 | 中国人民解放军国防科技大学 | Active cooling and combustion decoupling system of scramjet engine |
| CN112431675A (en) * | 2020-11-24 | 2021-03-02 | 西北工业大学 | Combined scramjet engine cooling circulation system |
-
2009
- 2009-07-02 CN CN200910072452XA patent/CN101602407B/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104989550A (en) * | 2015-07-22 | 2015-10-21 | 北京航空航天大学 | Liquid-nitrogen cooling system of scramjet engine |
| CN104989550B (en) * | 2015-07-22 | 2018-01-30 | 北京航空航天大学 | Scramjet engine liquid nitrogen cooling system |
| CN105888880A (en) * | 2016-05-31 | 2016-08-24 | 南京航空航天大学 | Scramjet engine water cooling device and work method thereof |
| CN107738755A (en) * | 2017-11-16 | 2018-02-27 | 中国运载火箭技术研究院 | It is a kind of to adapt to efficiently main passive heat management system and its design method that the world comes and goes |
| CN107738755B (en) * | 2017-11-16 | 2019-08-09 | 中国运载火箭技术研究院 | It is a kind of adapt to the world it is round-trip efficiently lead passive heat management system and its design method |
| CN111907721A (en) * | 2020-08-18 | 2020-11-10 | 西北工业大学 | Sleeve passage for cooling high-temperature part of aircraft |
| CN112160837A (en) * | 2020-09-18 | 2021-01-01 | 中国航发四川燃气涡轮研究院 | Closed circulation heat management integrated system based on supercritical medium |
| CN112377324A (en) * | 2020-11-18 | 2021-02-19 | 中国人民解放军国防科技大学 | Active cooling and combustion decoupling system of scramjet engine |
| CN112431675A (en) * | 2020-11-24 | 2021-03-02 | 西北工业大学 | Combined scramjet engine cooling circulation system |
| CN112431675B (en) * | 2020-11-24 | 2022-08-02 | 西北工业大学 | Combined scramjet engine cooling circulation system |
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| Publication number | Publication date |
|---|---|
| CN101602407B (en) | 2011-01-19 |
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