CN1259219C - Liquid hydrogen fuel carrying and heat exchanging system of hydrogenfuel high speed airplane - Google Patents
Liquid hydrogen fuel carrying and heat exchanging system of hydrogenfuel high speed airplane Download PDFInfo
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- CN1259219C CN1259219C CNB2003101216077A CN200310121607A CN1259219C CN 1259219 C CN1259219 C CN 1259219C CN B2003101216077 A CNB2003101216077 A CN B2003101216077A CN 200310121607 A CN200310121607 A CN 200310121607A CN 1259219 C CN1259219 C CN 1259219C
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- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
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Abstract
The present invention relates to a liquid hydrogen carrying heat exchanging system for a hydrogen fueled high-speed plane, which mainly comprises a main liquid hydrogen storing box, wing liquid hydrogen storing box groups, fuselage liquid hydrogen storing box groups, stop valves, a liquid hydrogen main pipe, a first evaporator, a second evaporator, an engine combustion chamber, a hydraulic oil heat exchanger, a lubricating oil heat exchanger, a hydraulic system, a fan and a lubrication system. A proposal of multi-unit liquid hydrogen energy storage is adopted, the liquid hydrogen storing box groups are manufactured according to the shape of the fuselage and the wings of a plane, and the liquid hydrogen storing box groups are connected through the stop valves. Liquid hydrogen fuel in the system transfers cooling capacity to the lubrication system and the hydraulic system, and air cooled by the lubrication system and the hydraulic system can cool the wing surfaces of the front edges of the wings. The system of the present invention fully utilizes space. Thus, the volume of the plane is not increased, and the integral safety and the flight state of the plane can not be obviously influenced. The take-off weight of the plane is greatly reduced, and the push-to-mass ratio of the plane is improved. Atmospheric pollution caused by the combustion of engines can be eliminated, and the pressure of energy shortage can be alleviated.
Description
Technical field
The present invention relates to a kind of Liquid Hydrogen fuel and carry and heat-exchange system, particularly a kind of Liquid Hydrogen fuel that fires the hydrogen high-speed aircraft carries and heat-exchange system, belongs to the vehicle technology field.
Background technology
Aero-engine is power with the conventional fuel at present, and the source is shortage day by day, and causes atmospheric contamination.The unit mass calorific value of conventional fuel is limited, carry fuel and cause the significantly increase of take-off weight, the patent No. is that 97235783.1 " green type variable aero-engine " proposes to provide power with the driving engine of sustainable power generation assembly in the prior art, to reduce environmental pollution, but, scheme can not be put into practice because of not possessing high-power, free of contamination portability power supply at present to promote aero-engine.The use of hydrogen fuel both can be exempted atmospheric contamination, can slow down conventional energy resources pressure in short supply again, but the unit volume calorific value of liquid hydrogen is low, and it is big to carry volume, and temperature is low during storage, can not directly use, and did not still have technology at present and overcame above difficulty.
Summary of the invention
For deficiency and the defective that overcomes prior art, the invention provides a kind of Liquid Hydrogen fuel that fires the hydrogen high-speed aircraft carries and heat-exchange system, adopt multiple-unit liquid hydrogen energy storage scheme, comply with the fuselage of aircraft and the outer shape of wing and making a plurality of liquid hydrogen tank unit, they can be divided into wing liquid hydrogen storage tank group and fuselage liquid hydrogen storage tank group, in addition, also have a main liquid hydrogen storage tank, carry system with forming Liquid Hydrogen fuel.Though the proportion of liquid hydrogen is less, cause volume big, with each tank unit dispersed placement, just can make full use of the space, do not increase the volume of aircraft.Each tank unit all connects by shutoff valve each other, fuses with main liquid hydrogen storage tank.Simultaneously, each tank unit links to each other with the Liquid Hydrogen fuel house steward with the shutoff valve that main liquid hydrogen storage tank all passes through separately.Like this, can make things convenient for can liquid hydrogen continuously, can be aircraft fuel supplying continuously again, simultaneously each hydrogen storing unit can be closed because the unit internal pressure descends suddenly and being connected of house steward at any time naturally, in case certain part of aircraft meets accident or breakage, leak and catch fire even cause tank unit, also can not produce obviously influence the general safety and the state of flight of aircraft.
Liquid Hydrogen fuel through heat exchange, passed to lubricating system and hydraulic efficiency pressure system with its cold that carries earlier before entering engine chamber.Then, the oily first inflow heat exchanger in lubricating system and the hydraulic efficiency pressure system, coolant air, and then enter lubricating system and hydraulic efficiency pressure system.Cooled air can cool off the leading edge of a wing aerofoil of giving birth to heat because of Pneumatic friction after entering the wing inner chamber.In evaporator, liquid hydrogen at first flashes to hydrogen, and is heated to suitable temperature, enters combustion chamber at last.
The invention has the beneficial effects as follows the take-off weight that can alleviate aircraft significantly, improve the thrust-mass ratio of aircraft, and can eliminate the atmospheric contamination that engine combustion causes, do not re-use conventional fuel and slow down energy starved pressure; The boiling temperature of hydrogen is 20.38K, can not freezing in the air of any height; Because of Pneumatic friction causes heat-producing leading edge of a wing aerofoil, lubricating oil and hydraulic oil that simultaneously can cooled engine make the aircraft safety high-speed flight when cold that Liquid Hydrogen fuel carries can cool off high-speed flight.The present invention has remarkable economic efficiency and social benefit.
Description of drawings
Fig. 1 is the structural principle scheme drawing of system of the present invention
1 is main liquid hydrogen storage tank among the figure, the 2nd, and wing liquid hydrogen storage tank group, the 3rd, fuselage liquid hydrogen storage tank group, 4, the 5, the 6th, shutoff valve, the 7th, the liquid hydrogen house steward, 8 is first evaporators, 9 is second evaporators, the 10th, engine chamber, the 11st, hydraulic oil heat exchanger, the 12nd, lubricating oil heat exchanger, the 13rd, hydraulic efficiency pressure system, 14, the 15th, fan, the 16th, lubricating system.
The specific embodiment:
Below in conjunction with accompanying drawing concrete enforcement of the present invention is further described.
As shown in Figure 1, the present invention mainly comprises: main liquid hydrogen storage tank 1, wing liquid hydrogen storage tank group 2, fuselage liquid hydrogen storage tank group 3, shutoff valve 4,5,6, liquid hydrogen house steward 7, first evaporator 8, second evaporator 9, engine chamber 10, hydraulic oil heat exchanger 11, lubricating oil heat exchanger 12, hydraulic efficiency pressure system 13, fan 14,15, lubricating system 16.
Main liquid hydrogen storage tank 1 is placed in the aircraft fuel cabin, and wing liquid hydrogen storage tank group 2 and fuselage liquid hydrogen storage tank group 3 are respectively one group of casings making according to wing profile and fuselage appearance, are placed in wing and the fuselage.Wing liquid hydrogen storage tank group 2 and fuselage liquid hydrogen storage tank group 3 are formed by shutoff valve bonded assembly liquid hydrogen tank unit by a plurality of.Wing liquid hydrogen storage tank group 2 and fuselage liquid hydrogen storage tank group 3 are connected with main liquid hydrogen storage tank 1 by shutoff valve 6 respectively, get along in main liquid hydrogen storage tank 1 import shutoff valve 4 is installed, main liquid hydrogen storage tank 1, wing liquid hydrogen storage tank group 2 and fuselage liquid hydrogen storage tank group 3 link to each other with liquid hydrogen house steward 7 imports by shutoff valve 5 respectively.Liquid hydrogen house steward 7 outlet links to each other with the shell side import of first evaporator 8, and the shell side outlet of first evaporator 8 links to each other with the shell side import of second evaporator 9, and the shell side outlet of second evaporator 9 links to each other with the import of engine chamber 10; The tube side outlet of first evaporator 8 links to each other with the tube side import of hydraulic oil heat exchanger 11, and the tube side outlet of hydraulic oil heat exchanger 11 links to each other with the import of hydraulic efficiency pressure system 13, and the outlet of hydraulic efficiency pressure system 13 links to each other with the tube side import of first evaporator 8; The tube side outlet of second evaporator 9 links to each other with the tube side import of lubricating oil heat exchanger 12, and the tube side outlet of lubricating oil heat exchanger 12 links to each other with the import of lubricating oil system 16, and the outlet of lubricating oil system 16 links to each other with the tube side import of second evaporator 9; The shell side import of hydraulic oil heat exchanger 11 and lubricating oil heat exchanger 12 all communicates with atmosphere, and the shell side outlet connects fan 14,15 respectively.In first evaporator 8 and second evaporator 9, liquid hydrogen passes to lubricating oil and hydraulic oil with the cold that carries, and liquid hydrogen rises to suitable temperature and enters engine chamber 10 internal combustion.Hydraulic oil absorbs cold in first evaporator 8 after, enter the tube side of hydraulic oil heat exchanger 11, enter hydraulic efficiency pressure system 13 work behind the coolant air again, the tube side import that enters first evaporator 8 more at last absorbs cold again.Lubricating oil absorbs cold in second evaporator 7 after, flow into the tube side of lubricating oil heat exchanger 12, enter lubricating system 16 work behind the coolant air again, the tube side import that enters second evaporator 7 more at last absorbs cold again.After being cooled in hydraulic oil heat exchanger 11 and lubricating oil heat exchanger 12 by the atmosphere suction air, blowed to leading edge of a wing aerofoil inner chamber by fan 14,15, cooling is given birth to hot leading edge of a wing aerofoil because of Pneumatic friction.
Claims (1)
1, a kind of Liquid Hydrogen fuel that fires the hydrogen high-speed aircraft carries and heat-exchange system, comprise: engine chamber (10), hydraulic efficiency pressure system (13), lubricating system (16), it is characterized in that also comprising: main liquid hydrogen storage tank (1), wing liquid hydrogen storage tank group (2), fuselage liquid hydrogen storage tank group (3), shutoff valve (4,5,6), liquid hydrogen house steward (7), first evaporator (8), second evaporator (9), hydraulic oil heat exchanger (11), lubricating oil heat exchanger (12), fan (14,15), main liquid hydrogen storage tank (1) is placed in the aircraft fuel cabin, wing liquid hydrogen storage tank group (2) and fuselage liquid hydrogen storage tank group (3) are respectively one group of casings making according to wing profile and fuselage appearance, are placed in wing and the fuselage, are communicated with by shutoff valve between each casing in wing liquid hydrogen storage tank group (2) and the fuselage liquid hydrogen storage tank group (3); Wing liquid hydrogen storage tank group (2) links to each other with main liquid hydrogen storage tank (1) by shutoff valve (6) respectively with fuselage liquid hydrogen storage tank group (3), in main liquid hydrogen storage tank (1) inflow point shutoff valve (4) is installed, main liquid hydrogen storage tank (1), wing liquid hydrogen storage tank group (2) links to each other with liquid hydrogen house steward (7) by shutoff valve (5) with fuselage liquid hydrogen storage tank group (3), liquid hydrogen house steward's (7) outlet links to each other with the shell side import of first evaporator (8), the shell side outlet of first evaporator (8) links to each other with the shell side import of second evaporator (9), and the shell side outlet of second evaporator (9) links to each other with the import of engine chamber (10); The tube side outlet of first evaporator (8) links to each other with the tube side import of hydraulic oil heat exchanger (11), the tube side outlet of hydraulic oil heat exchanger (11) links to each other with the import of hydraulic efficiency pressure system (13), and the outlet of hydraulic efficiency pressure system (13) links to each other with the tube side import of first evaporator (8); The tube side outlet of second evaporator (9) links to each other with the tube side import of lubricating oil heat exchanger (12), the tube side outlet of lubricating oil heat exchanger (12) links to each other with the import of lubricating oil system (16), and the outlet of lubricating oil system (16) links to each other with the tube side import of second evaporator (9); The shell side import of hydraulic oil heat exchanger (11) and lubricating oil heat exchanger (12) all communicates with atmosphere, and the shell side outlet connects fan (14,15) respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2003101216077A CN1259219C (en) | 2003-12-30 | 2003-12-30 | Liquid hydrogen fuel carrying and heat exchanging system of hydrogenfuel high speed airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2003101216077A CN1259219C (en) | 2003-12-30 | 2003-12-30 | Liquid hydrogen fuel carrying and heat exchanging system of hydrogenfuel high speed airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1556009A CN1556009A (en) | 2004-12-22 |
| CN1259219C true CN1259219C (en) | 2006-06-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB2003101216077A Expired - Fee Related CN1259219C (en) | 2003-12-30 | 2003-12-30 | Liquid hydrogen fuel carrying and heat exchanging system of hydrogenfuel high speed airplane |
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| CN (1) | CN1259219C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4187071A1 (en) * | 2021-11-29 | 2023-05-31 | Airbus SAS | Combined dihydrogen heating and fluid cooling system for an aircraft, and aircraft comprising such a system |
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| FR2923462B1 (en) * | 2007-11-14 | 2010-04-02 | Airbus France | METHOD FOR MANAGING THERMAL REJECTIONS GENERATED BY AN AIRCRAFT AND COOLING DEVICE FOR AN AIRCRAFT FOR CARRYING OUT SAID METHOD. |
| CN102261968B (en) * | 2011-06-14 | 2013-03-27 | 南京工业大学 | Method and device for predicting node temperature of shell-and-tube heat exchanger |
| WO2014105333A1 (en) | 2012-12-28 | 2014-07-03 | General Electric Company | Aircraft and method of managing evaporated cryogenic fuel |
| CN105083569B (en) * | 2015-09-09 | 2018-11-23 | 中国商用飞机有限责任公司 | Enhanced heat exchange device for aircraft fuel and enhanced heat exchange method thereof |
| CN107972877B (en) * | 2017-12-26 | 2024-03-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Hydrogen fuel aircraft |
| CN109367801B (en) * | 2018-10-09 | 2020-09-18 | 北京航空航天大学 | Distributed airplane thermal management system and method based on airplane hydraulic system and micro evaporative refrigeration cycle |
| CN109573074A (en) * | 2018-11-30 | 2019-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of oil cooling system for aircraft auxiliary power plant |
| CN114275169A (en) * | 2021-12-28 | 2022-04-05 | 北京动力机械研究所 | Low-boiling-point working medium pressurization supply system and supply method |
| CN115583349B (en) * | 2022-12-13 | 2023-04-18 | 中国民用航空飞行学院 | Aircraft self-adaptation emergency system based on meteorological big data |
| FR3143558A1 (en) * | 2022-12-20 | 2024-06-21 | Airbus Operations | WARMING INSTALLATION FOR AN AIRCRAFT COMPRISING A DIHYDROGEN TANK, AN ENGINE AND DIHYDROGEN WARMING SYSTEMS |
-
2003
- 2003-12-30 CN CNB2003101216077A patent/CN1259219C/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4187071A1 (en) * | 2021-11-29 | 2023-05-31 | Airbus SAS | Combined dihydrogen heating and fluid cooling system for an aircraft, and aircraft comprising such a system |
| FR3129661A1 (en) * | 2021-11-29 | 2023-06-02 | Airbus | COMBINED DIHYDROGEN HEATING AND FLUID COOLING SYSTEM FOR AIRCRAFT, AND AIRCRAFT COMPRISING SUCH SYSTEM |
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| Publication number | Publication date |
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| CN1556009A (en) | 2004-12-22 |
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