CN104092409A - Combined thermoelectric conversion device - Google Patents
Combined thermoelectric conversion device Download PDFInfo
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- CN104092409A CN104092409A CN201410341676.7A CN201410341676A CN104092409A CN 104092409 A CN104092409 A CN 104092409A CN 201410341676 A CN201410341676 A CN 201410341676A CN 104092409 A CN104092409 A CN 104092409A
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Abstract
The invention discloses a combined thermoelectric conversion device suitable for heat protection and heat utilization of a hypersonic flight vehicle and combined with thermoelectric conversion and Rankine thermoelectric conversion. A hot end of the thermoelectric conversion absorbs aerodynamic heat of the skin of the flight vehicle, a cold end of the thermoelectric conversion transfers heat to an evaporator of a Rankine thermoelectric conversion system capable of adopting R141b organic working media, and heat of a condenser of the Rankine thermoelectric conversion system is taken away by a vehicle-mounted cold source of the flight vehicle. By fully utilizing the aerodynamic heat on the surface of the hypersonic flight vehicle, on one hand, the temperature on the surface of the flight vehicle is reduced, and certain heat protection on the flight vehicle is achieved; on the other hand, the thermoelectric power generation technology with a wide temperature range is combined with Rankine cycle with low operation temperature, energy is made full use of, efficiency of energy use is increased, and the whole thermoelectric conversion efficiency of the system is increased.
Description
Technical field
The present invention relates to a kind of combined thermoelectric conversion device, belongs to aircraft Evolution of Thermal Control Technique field.
Background technology
Hypersonic aircraft flight Mach number is high, and aircraft surface can produce high temperature because of Aerodynamic Heating effect
[1].About Aerodynamic Heating thermoelectric generation technology, have no report, the thermoelectric generation technology in other field can be divided into two large classes: directly change class and thermodynamic cycle class.Directly conversion class technology can realize heat energy to the direct conversion of electric energy, mainly contains semiconductor temperature differential generating technology
[2], alkali metal thermo-electric switch technology
[3-4]and magnetic fluid generating technology
[5]; Circulation class thermoelectric generation technology is first mechanical energy by thermal power transfer by thermodynamic cycle, then drives generator to generate electricity, and mainly contains Rankine cycle
[6-7], brayton cycle
[8]circulate with Stirling
[9].
But all there is self drawback in every kind of thermoelectric generation technology: semiconductor temperature differential generating technical development is comparatively ripe, but conversion efficiency of thermoelectric lower (generally lower than 10%); In alkali metal thermo-electric technology, serious, the poor stability of the performance degradation of core apparatus BASE material, applies still immature; Magnetic fluid technique needs huge superconducting magnet, is not suitable for being applied to aircraft; Rankine cycle technology comparative maturity, but be mainly applicable to the environment that temperature is lower (300 ℃ are following); Brayton cycle and stirling cycle system parts are comparatively complicated.
List of references
[1] Zhang Chunxue, the break rising sun. affordable Long-range precision strike hypersonic missile [J]. cruising missile .2006 (12) .6
[2]D.M.Rowe,M.Sc.Thermoelectric?Power?Generation[J].Electrical?Engineers,1978,V125(11):1113–1136
[3] Zhang Laifu, Li Bin. two key issues [J] that alkali metal thermo-electric converter is practical. energy technology, 2004,6 (25)
[4] Zhang Laifu, Ni Qiuya, Tong Jianzhong. the electrode polarization process analysis procedure analysis of alkali metal thermo-electric converter (AMTEC). solar energy journal. the 26th volume the 6th phase .2005.12
[5] Kong Qingyi, Li Shuying, Li Xiaoming. simple analysis magnetic fluid generating technology [J]. Tohoku Electric Power technology .2009.9
[6]Tuo,H.F.,Energy?and?exergy-based?working?fluid?selection?for?organic?Rankine?cycle?recovering?waste?heat?from?high?temperature?solid?oxide?fuel?cell?and?gas?turbine?hybrid?systems,International?Journal?of?Energy?Research,37(14)(2013):1831-1841.
[7]Tuo,H.F.,Thermal-Economic?Analysis?of?a?Transcritical?Rankine?Power?Cycle?with?Reheat?Enhancement?for?a?Low-Grade?Heat?Source,International?Journal?of?Energy?Research,37(8)(2013):857-867.
[8]Bao?Wen,Qin?Jiang,Yu?Daren?Integrated?Thermal?Management?Method?of?Energy?Based?On?Closed?Brayton?Cycle?for?Scramjet.AIAA2006-4685
[9] Li Haiwei, stone forest lock, Li Yaqi. the development of Stirling engine and application. energy technology .Vol.31 No.42010.8
Summary of the invention
The present invention proposes a kind of combined thermoelectric conversion device, is applicable to the special applied environment of aircraft, efficiently solves the drawback of single thermoelectric generation technology.Pneumatic heat energy in device recovery flight device flight course, is translated into electric energy, when reducing aircraft surface temperature, playing thermal protection effect, for aircraft electrical origin system provides a part of electric energy.
A combined thermoelectric conversion device, comprises covering heat exchanger, temperature-difference power generation module, evaporator, supply pump, turbine, generator, condenser.
Covering heat exchanger obtains heat from high-temperature wall surface, transfer heat to temperature-difference power generation module, temperature-difference power generation module fits between covering heat exchanger and evaporator, covering heat exchanger is as the temperature end of temperature-difference power generation module, evaporator is as the low-temperature end of temperature-difference power generation module, temperature-difference power generation module output electric energy, turbine, supply pump, generator coaxle is installed, evaporator heats working medium, obtain HTHP working medium, the running of working medium impulse turbine, turbo driving drives generator work output electric energy, and drive supply pump to pressurize to working medium after lowering the temperature, turbine is discharged working medium and is lowered the temperature and pressurizeed with supply pump by condenser, be transported to and in evaporator, continue new round circulation.
The invention has the advantages that:
(1) the present invention adopts aircraft skin heat exchanger directly to absorb the Aerodynamic Heating that aircraft shows, Aerodynamic Heating is converted to the available electric energy of aircraft, alleviated the Aerodynamic Heating effect of aircraft outside wall surface, reduced outside wall temperature, aircraft has been played to certain thermal protection effect;
(2) in the present invention, temperature-difference power generation module fits between covering heat exchanger and evaporator, and self generating also can produce approximately 100 ℃ of temperature drops, and after cooling, temperature range is suitable for the safe operation of Rankine cycle;
(3) in the present invention, the used heat of temperature-difference power generation module passes to organic Rankine circulation as thermal source, realizes making full use of of the energy, improves entire system conversion efficiency of thermoelectric.
Difference with the prior art of the present invention is: at home and abroad in available data, have and relate to the thermoelectric conversion system that thermo-electric generation combines with organic Rankine circulation, but with difference of the present invention be: the heat of the thermo-electric generation cold junction in (1) existing waste heat utilization technology falls apart to forecooler, and the heat of evaporator is directed to used heat; In the present invention, temperature-difference power generation module directly contacts with evaporator, and the heat of evaporator comes from the heat extraction of temperature-difference power generation module cold junction, Aerodynamic Heating be indirect transfer in evaporator, the two application conditions is different; (2) because aircraft is harsh to system dimension installation requirement, compact conformation of the present invention, and the association system of prior art reclaims for exhaust heat of internal combustion engine, application component is many, physical dimension is large; In the present invention, turbine, supply pump, generator coaxle are installed, and turbine operation drives supply pump and generator, effective simplified system, and in prior art, supply pump needs separate power source to drive; (3) the present invention is applicable to the special applied environment of aircraft, and thermal source is the Aerodynamic Heating in flight course, completes heat energy to time electric energy conversion, and aircraft has been played to thermo-lag effect.
Accompanying drawing explanation
Fig. 1 is combined thermoelectric conversion device schematic diagram of the present invention;
Fig. 2 is evaporator/electricity generation module integral structure schematic diagram of the present invention.
In figure:
1. covering heat exchanger 2. temperature-difference power generation module 3. evaporators
4. supply pump 5. axle 6. turbines
7. generator 8. condenser 9. high-temperature wall surfaces
10. the airborne low-temperature receiver outlet of airborne low-temperature receiver entrance 11.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in further detail.
The present invention is a kind of combined thermoelectric conversion device, as shown in Figure 1, comprises covering heat exchanger 1, temperature-difference power generation module 2, evaporator 3, supply pump 4, turbine 6, generator 7, condenser 8.
In aircraft hypersonic flight process, harsh Aerodynamic Heating causes cabin body wall surface temperature higher, by covering heat exchanger 1, from high-temperature wall surface 9, obtain heat, and this heat is passed to temperature-difference power generation module 2, covering heat exchanger 1 is as the temperature end of temperature-difference power generation module 2, the heat of temperature-difference power generation module 2 low-temperature end is transferred to evaporator 3, temperature-difference power generation module 2 fits between covering heat exchanger 1 and evaporator 3, evaporator 3 and the integrated setting of temperature-difference power generation module 2, as shown in Figure 2, temperature-difference power generation module 2 output electric energy, the working medium of 3 pairs of organic Rankine circulations of evaporator heats, obtain the working medium of HTHP, 6 runnings of working medium impulse turbine, turbine 6, supply pump 4, generator 7 adopts axle 5 coaxially to install, turbine 6 runnings drive 4 pairs of working medium of supply pump to pressurize, by converter technique, control the rotating speed of supply pump 4, turbine 6 also drives generator 7 work output electric energy, turbine 6 is discharged working medium by condenser 8 coolings and supply pump 4 pressurizations, is transported to and in evaporator 3, continues new round circulation.
The course of work of a kind of combined thermoelectric conversion device of the present invention is described in conjunction with Fig. 1:
By covering heat exchanger 1, from high-temperature wall surface 9, obtain heat, pass to temperature-difference power generation module 2 hot junctions that fit on heat exchanger, through the Rankine cycle working medium of the supply pump 4 pressurization evaporator 3 of flowing through, absorb whole used heat of temperature-difference power generation module 2 cold junctions, working medium absorbs the rising of heat temperature and becomes mutually high temperature and high pressure steam, impulse turbine 6 runnings, turbine 6, supply pump 4, generator 7 coaxial 5 is installed, turbine 6 runnings drive 4 pairs of working medium of supply pump to pressurize, turbine 6 drives generator 7 to produce electric energy, turbine 6 outlet working medium are lowered the temperature by condenser 8, be transported to after supply pump 4 pressurization again again and in evaporator 3, continue new round circulation.The heat of the working medium absorptive condenser 8 of airborne low-temperature receiver entrance 10, is discharged by airborne low-temperature receiver outlet 11.
Described temperature-difference power generation module 2 output electric energy voltages are U.
Described generator 7 output electric energy.
Described organic Rankine circulation can adopt R141b as working medium.
The present invention combines the wider thermo-electric generation technology Rankine cycle lower with operating temperature of temperature range, temperature-difference power generation module is applied to high-temperature region, as top, circulate, Rankine cycle is as bottom cycle, the cold junction of top circulation is as the thermal source of bottom cycle, thereby realize making full use of of the energy, increase efficiency of energy utilization, improve entire system conversion efficiency of thermoelectric.
Embodiment:
Hypersonic aircraft design condition: flying height 20km, flight Mach number is 5, Gas heat flux density 10kW/m
2.The working medium of selected Rankine cycle is R141b, and condensing temperature is 80 ℃, and evaporating temperature is set as 200 ℃, 10 ℃ of superheating ratios.Critical component operational factor is in Table 1, and working medium flow is 3.05 * 10
-3during kg/s, electromotive power output is 100W, system conversion efficiency of thermoelectric 12.57%.
Table 1 Rankine cycle critical component operational factor
Temperature-difference power generation module hot junction endotherm area is 0.084m
2, 300 ℃ of hot-side temperatures, 220 ℃ of cold junction temperatures, exportable electric energy 46.1W, voltage 14.4V, electric current 3.2A.
If device overall thermal photoelectric transformation efficiency is total output electric energy and the ratio of total caloric receptivity, computing formula is as follows:
Output electric energy comprises two parts: Rankine cycle output 100W, electricity generation module output 46.1W; Total caloric receptivity comprises two parts: electricity generation module conversion heat 46.1W, and electricity generation module passes to the heat 795.8W of Rankine cycle; The overall thermal photoelectric transformation efficiency that is calculated combined thermoelectric conversion device by formula 1 is 17.35%, all higher than temperature-difference power generation module conversion efficiency of thermoelectric 5.47% and Rankine cycle conversion efficiency of thermoelectric 12.57%.
Claims (4)
1. a combined thermoelectric conversion device, comprises covering heat exchanger, temperature-difference power generation module, evaporator, supply pump, turbine, generator, condenser.
Covering heat exchanger obtains heat from high-temperature wall surface, transfer heat to temperature-difference power generation module, temperature-difference power generation module fits between covering heat exchanger and evaporator, covering heat exchanger is as the temperature end of temperature-difference power generation module, evaporator is as the low-temperature end of temperature-difference power generation module, temperature-difference power generation module output electric energy, turbine, supply pump, generator coaxle is installed, evaporator heats working medium, obtain HTHP working medium, the running of working medium impulse turbine, turbo driving drives generator work output electric energy, and drive supply pump to pressurize to working medium after lowering the temperature, turbine is discharged working medium and is lowered the temperature and pressurizeed with supply pump by condenser, be transported to and in evaporator, continue new round circulation.
2. a kind of combined thermoelectric conversion device according to claim 1, described covering heat exchanger contacts well with temperature-difference power generation module hot end surface, guarantees that the hot junction of temperature-difference power generation module absorbs the heat of covering heat exchanger.
3. a kind of combined thermoelectric conversion device according to claim 1, the integrated setting of described evaporator and temperature-difference power generation module.
4. a kind of combined thermoelectric conversion device according to claim 1, the low-temperature receiver of described condenser is airborne low-temperature receiver.
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| CN201410341676.7A CN104092409A (en) | 2014-07-17 | 2014-07-17 | Combined thermoelectric conversion device |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443394A (en) * | 2014-10-31 | 2015-03-25 | 北京航空航天大学 | Novel airplane environment control system with organic Rankine cycle applied |
| CN109519242A (en) * | 2018-11-29 | 2019-03-26 | 郭刚 | A kind of AMTEC/ORC combined generating system |
| CN110065618A (en) * | 2019-03-25 | 2019-07-30 | 西北工业大学 | A kind of multifunction structure device and its working method for hypersonic aircraft |
| CN110967369A (en) * | 2019-11-25 | 2020-04-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Device and method for testing heat insulation capability of high-temperature thermoelectric material |
| CN114370336A (en) * | 2022-01-07 | 2022-04-19 | 中国人民解放军国防科技大学 | Rankine cycle-thermoelectric drive coupling waste heat recovery energy management system |
| CN114583207A (en) * | 2022-03-23 | 2022-06-03 | 西安交通大学 | Three-stage circulation power generation system based on solid oxide fuel cell |
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|---|---|---|---|---|
| US5149018A (en) * | 1990-05-17 | 1992-09-22 | The Boeing Company | Cooling system for a hypersonic aircraft |
| US8127555B2 (en) * | 2007-12-13 | 2012-03-06 | Pratt & Whitney Rocketdyne, Inc. | Flowpath heat exchanger for thermal management and power generation within a hypersonic vehicle |
| CN102444439A (en) * | 2011-11-14 | 2012-05-09 | 天津大学 | Waste heat cycling heating power circulating system device of engine |
| CN103061856A (en) * | 2011-10-24 | 2013-04-24 | 通用电气航空系统有限公司 | Thermal electrical power generation for aircraft |
-
2014
- 2014-07-17 CN CN201410341676.7A patent/CN104092409A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5149018A (en) * | 1990-05-17 | 1992-09-22 | The Boeing Company | Cooling system for a hypersonic aircraft |
| US8127555B2 (en) * | 2007-12-13 | 2012-03-06 | Pratt & Whitney Rocketdyne, Inc. | Flowpath heat exchanger for thermal management and power generation within a hypersonic vehicle |
| CN103061856A (en) * | 2011-10-24 | 2013-04-24 | 通用电气航空系统有限公司 | Thermal electrical power generation for aircraft |
| CN102444439A (en) * | 2011-11-14 | 2012-05-09 | 天津大学 | Waste heat cycling heating power circulating system device of engine |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443394A (en) * | 2014-10-31 | 2015-03-25 | 北京航空航天大学 | Novel airplane environment control system with organic Rankine cycle applied |
| CN104443394B (en) * | 2014-10-31 | 2016-06-08 | 北京航空航天大学 | The plane environmental control system of application organic Rankine bottoming cycle |
| CN109519242A (en) * | 2018-11-29 | 2019-03-26 | 郭刚 | A kind of AMTEC/ORC combined generating system |
| CN110065618A (en) * | 2019-03-25 | 2019-07-30 | 西北工业大学 | A kind of multifunction structure device and its working method for hypersonic aircraft |
| CN110967369A (en) * | 2019-11-25 | 2020-04-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Device and method for testing heat insulation capability of high-temperature thermoelectric material |
| CN114370336A (en) * | 2022-01-07 | 2022-04-19 | 中国人民解放军国防科技大学 | Rankine cycle-thermoelectric drive coupling waste heat recovery energy management system |
| CN114370336B (en) * | 2022-01-07 | 2023-08-18 | 中国人民解放军国防科技大学 | Rankine cycle-thermoelectric drive coupling waste heat recovery energy management system |
| CN114583207A (en) * | 2022-03-23 | 2022-06-03 | 西安交通大学 | Three-stage circulation power generation system based on solid oxide fuel cell |
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