CN112855343A - Aviation power system, liquid nitrogen expansion assembly, aircraft and driving method thereof - Google Patents
Aviation power system, liquid nitrogen expansion assembly, aircraft and driving method thereof Download PDFInfo
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- CN112855343A CN112855343A CN201911190365.4A CN201911190365A CN112855343A CN 112855343 A CN112855343 A CN 112855343A CN 201911190365 A CN201911190365 A CN 201911190365A CN 112855343 A CN112855343 A CN 112855343A
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- 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
- F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
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Abstract
The invention relates to an aviation power system, a liquid nitrogen expansion assembly, an aircraft and a driving method of the aircraft. The liquid nitrogen expansion assembly comprises an expansion chamber and a guide piece; the expansion chamber comprises a first inlet, a second inlet and an expansion space, the first inlet is used for injecting liquid nitrogen output from a liquid nitrogen storage container to the expansion space, the second inlet is used for inputting pressurized air to the expansion space, the liquid nitrogen is in direct contact with the pressurized air in the expansion space and is violently gasified, the volume of the liquid nitrogen expands to form expanded nitrogen, the expanded nitrogen is guided by the guide piece to be output from the expansion chamber to the power assembly, the expanded nitrogen pushes a turbine of the power assembly to do work, and power is output. The aviation power system has the advantages of zero emission, low operation cost and the like.
Description
Technical Field
The invention relates to the field of energy power, in particular to an aviation power system, a liquid nitrogen expansion assembly, an aircraft and a driving method thereof.
Background
The aeronautical power device relates to various disciplines of pneumatics, thermotechnical, structure and strength, control, test, computer, manufacturing technology and material, etc., and its working conditions such as temperature, pressure, stress, rotating speed, vibration, clearance and corrosion, etc. are far more complex and severer than other subsystems of the airplane, and have extremely high requirements for performance, weight, applicability, reliability, durability and environmental characteristics, etc. Therefore, the conventional development process is a process of multiple iterations of designing, manufacturing, testing, and modifying the design.
A conventional aviation power system is shown in fig. 1 and 2, that is, a gas turbine power system 10 includes a fan 100, a compressor unit 200, a combustion chamber 300, and a turbine 400, air enters the combustion chamber 300 after passing through the fan 100 and the compressor unit 200, and undergoes a combustion reaction with fuel injected into the combustion chamber 300 through a fuel nozzle, and the reacted high-temperature gas pushes the turbine 400 to do work to output power. One of the core components of the gas turbine power system 10 is a gas generator, i.e., combustor 300. The fuel of the gas generator is aviation kerosene, the problems of pollution and emission cannot be avoided when the kerosene is combusted, namely the problem of environmental pollution is very prominent, and particularly, if pollution and emission indexes of a civil aviation engine do not reach the standard, the airworthiness can not be obtained. With the progress of related technical means, the existing civil aircraft engine has remarkable progress on performance indexes, such as fuel consumption and pollutant emission indexes, which are greatly reduced compared with the prior art. On the other hand, however, with the increasingly high economic and environmental requirements of the international society and civil aviation organization on civil aviation engines, how to make the aviation engines meet the increasing high performance index requirements remains an important issue to face for a long time.
At present, although the increase of the engine pressure ratio and the outlet temperature of the combustion chamber can improve the thermal efficiency of the whole machine and reduce the fuel consumption, the increase is limited by the design level, the processing level, the material capability and the cooling technology level, and the turbine front temperature of the prior aeroengine is close to the limit value for safe use, so that the improvement is difficult to be obvious. In the prior art, a technical scheme of adopting a low-pollution combustion chamber is adopted, but because an aero-engine uses fossil fuel, generally aviation kerosene, as a power source of the fossil fuel, pollutants such as NOx, CO and UHC are difficult to completely avoid in combustion, and therefore certain environmental pollution can be caused. Meanwhile, the aviation kerosene is high in cost, non-renewable and not easy to store and has high danger.
In addition, for the oxygen supply system of the airplane, the liquid oxygen source system is adopted, the weight of the liquid oxygen source system is 60-70% lighter than that of the high-pressure oxygen source system, and the volume of the liquid oxygen source system is 60-80% smaller than that of the high-pressure oxygen source system. However, the liquid oxygen system generally directly produces liquid oxygen from the ground and stores the liquid oxygen in a liquid oxygen storage tank of the aircraft, but the problem of volatilization of the liquid oxygen causes the ground oxygen storage equipment to be complicated and the maintenance cost to be high.
Therefore, there is a need in the art for an aviation power system, a liquid nitrogen expansion assembly, an aircraft and a driving method thereof, so as to overcome the above-mentioned disadvantages of environmental pollution, high cost, non-regeneration, and difficult storage danger of aviation kerosene, and complicated ground oxygen storage equipment and high maintenance cost caused by oxygen supply of the existing aircraft liquid oxygen source system.
Disclosure of Invention
The invention aims to provide an aviation power system.
It is also an object of the present invention to provide a liquid nitrogen expansion assembly.
It is also an object of the invention to provide an aircraft.
The invention also aims to provide a driving method of the aircraft.
An aircraft power system according to an aspect of the invention includes an air intake portion from which air enters the power system; the supercharging assembly comprises a compressor unit, wherein a part of air of the air entering from the air inlet part enters the supercharging assembly, forms supercharging air through the supercharging of the compressor unit and is output from the compressor unit; the air separation component comprises an air separation part and a liquid nitrogen storage container, wherein the air separation part is used for separating liquid nitrogen from another part of air entering from the air inlet part and outputting the air to the liquid nitrogen storage container; the liquid nitrogen expansion assembly comprises an expansion chamber and a guide piece; the expansion chamber comprises a first inlet, a second inlet and an expansion space, wherein the first inlet is used for injecting liquid nitrogen output from the liquid nitrogen storage container to the expansion space, the second inlet is used for inputting the pressurized air to the expansion space, the liquid nitrogen is in direct contact with the pressurized air in the expansion space and is vigorously gasified, so that the volume of the liquid nitrogen is expanded to form expanded nitrogen, and the expanded nitrogen is guided to be output from the expansion chamber through the guide; and the power assembly comprises a turbine and is driven by the expanded nitrogen to do work and output power
In one or more embodiments of the aeronautical power system, the air separation assembly further comprises a liquid oxygen storage container, and the air separation part is used for separating liquid nitrogen and liquid oxygen from the other part of air and outputting the liquid nitrogen and the liquid oxygen to the liquid nitrogen storage container and the liquid oxygen storage container respectively; the aircraft power system also includes an oxygen supply assembly for outputting liquid oxygen from the liquid oxygen storage vessel to an aircraft cabin via the oxygen supply assembly.
In one or more embodiments of the aeronautical power system, the aeronautical power system further includes a first conduit that transports the liquid nitrogen from the air separation member to a liquid nitrogen storage container, a second conduit that transports the liquid nitrogen from the liquid nitrogen storage container to a first inlet of the expansion chamber, and a second flow valve that controls a flow rate of the liquid nitrogen transported to the first inlet; a third conduit for conveying the liquid oxygen from the air separator to a liquid oxygen storage container, a fourth conduit for conveying the liquid oxygen from the liquid oxygen storage container to the oxygen supply assembly, and a fourth flow valve controlling the flow rate of the liquid oxygen conveyed to the fourth conduit.
In one or more embodiments of the aeronautical power system, the aeronautical power system further includes a first safety valve disposed in the liquid nitrogen storage container, and a third safety valve disposed in the liquid oxygen storage container.
In one or more embodiments of the aircraft power system, the aircraft power system further comprises a fifth distribution valve coupled to the air intake for distributing a ratio of air delivered to a plenum assembly to air delivered to the air separation member, and a fifth conduit through which the portion of air is delivered to the plenum assembly and a sixth conduit through which the other portion of air is delivered to the air separation member.
In one or more embodiments of the aeronautical power system, the compressor train includes a low-pressure compressor and a high-pressure compressor, the turbine includes a low-pressure turbine and a high-pressure turbine, the low-pressure compressor is coaxially coupled to the low-pressure turbine, and the high-pressure compressor is coaxially coupled to the high-pressure turbine.
An aircraft according to an aspect of the invention comprises a nacelle and an aeronautical power system according to any of the above.
A liquid nitrogen expansion assembly according to one aspect of the present invention includes an expansion chamber and a guide; the expansion chamber is provided with a first inlet and a second inlet, liquid nitrogen is injected into the expansion chamber through pressurization at the first inlet, pressurized air is input into the expansion chamber at the second inlet, and the liquid nitrogen is directly contacted with the pressurized air in the expansion chamber to be violently gasified, so that the volume of the liquid nitrogen is expanded to form expanded nitrogen, and work is output from the expansion chamber through the guide piece.
A driving method according to an aspect of the present invention includes:
step S1: pressurizing a part of air to obtain pressurized air;
step S2: separating the other part of air to separate liquid nitrogen, injecting the liquid nitrogen to be directly contacted with the pressurized air, gasifying the liquid nitrogen by utilizing the temperature of the pressurized air, and expanding the volume of the liquid nitrogen to form expanded nitrogen;
step S3: and introducing the expanded nitrogen into the turbine, and performing work by expansion to drive the turbine to rotate to provide power.
In one or more implementations of the method of driving, in step S2, another portion of the air is separated to separate liquid nitrogen and liquid oxygen, and the liquid oxygen is output to a cabin of the aircraft.
The beneficial effects of the invention include but are not limited to:
1. the expansion chamber of the liquid nitrogen expansion assembly replaces a combustion chamber, and combustion does not occur, so that pollution and zero emission are avoided; the safety of the liquid nitrogen is higher than that of aviation kerosene, the liquid nitrogen can be obtained from the air, the source is wide, and the defect of dangerous storage is avoided;
2. compared with a gas turbine power system, the aviation power system adopting liquid nitrogen has low system temperature due to no combustion, improves the working condition of an engine, reduces the performance requirement of the power system on materials, and reduces the material cost of the power system;
3. the power system provides power, and simultaneously, the online preparation of the liquid oxygen and the liquid nitrogen is realized, so that the problems of complex equipment, high maintenance cost and the like caused by the ground preparation of the liquid oxygen and the ground storage of the liquid oxygen are solved.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic diagram of a gas turbine power system;
FIG. 2 is a block schematic diagram of a gas turbine power system;
FIG. 3 is a block schematic diagram of an aircraft power system in accordance with one or more embodiments.
FIG. 4 is a block diagram illustration of a liquid oxygen storage component and a liquid nitrogen storage component of an aircraft power system in accordance with one or more embodiments.
Fig. 5 is a flow diagram of a method of driving an aircraft in accordance with one or more embodiments.
Some of the reference numbers:
1-aeronautical power system
11-air intake part
12-supercharging assembly
121-gas compressor set
13-air separation module
131-air separation element
132-liquid nitrogen storage container
133-liquid oxygen storage container
14-liquid nitrogen expansion assembly
141-expansion chamber
1410-expansion space
1411-first inlet
1412-second inlet
142-guide
15-power assembly
151-turbine
1000. 1001, 1002-air
1011-charge air
2000-liquid nitrogen
2001-expanding nitrogen gas
2002-liquid oxygen
Detailed Description
The present invention is further described in the following description with reference to specific embodiments and the accompanying drawings, wherein the details are set forth in order to provide a thorough understanding of the present invention, but it is apparent that the present invention can be embodied in many other forms different from those described herein, and it will be readily appreciated by those skilled in the art that the present invention can be implemented in many different forms without departing from the spirit and scope of the invention.
Also, this application uses specific language to describe embodiments of the application. The terms "inside" and "outside" refer to the inner and outer parts relative to the outline of each part itself, and the terms "first", "second", "third", and the like are used to define the parts, and are used only for the convenience of distinguishing the corresponding parts, and unless otherwise stated, the terms have no special meaning, and therefore, the scope of the present invention should not be construed as being limited. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.
As shown in fig. 3, in one embodiment, the aircraft power system 1 includes an air intake 11, a pressure boosting assembly 12, an air separation assembly 13, a liquid nitrogen expansion assembly 14, and a power assembly 15. Wherein air 1000 enters power system 1 from air intake 11, a portion of air 1001 enters plenum assembly 12, and another portion of air 1002 enters air separation assembly 13. The booster assembly 12 includes a compressor block 121, and air 1001 enters the booster assembly 12 and is pressurized by the compressor block 111 to form pressurized air 1011, which is output from the compressor block 111 to the liquid nitrogen expansion assembly 14. The air separation assembly 13 includes an air separation member 131 and a liquid nitrogen storage container 132, the air 1002 is separated into liquid nitrogen 2000 by the air separation member 131 and output to the liquid nitrogen storage container 132, and the liquid nitrogen storage container 132 may be a liquid nitrogen storage tank, but not limited thereto. The liquid nitrogen 2000 in the liquid nitrogen storage vessel 132 is output to the liquid nitrogen expansion assembly 14. The liquid nitrogen expansion assembly 14 comprises an expansion chamber 141 and a guide member 142, the expansion chamber 141 comprises a first inlet 1411, a second inlet 1412 and an expansion space 1410, the liquid nitrogen 2000 output from the liquid nitrogen storage container 132 is injected into the expansion space 1410 at the first inlet 1411, the pressurized air 1011 is input into the expansion space 1410 at the second inlet 1412, the liquid nitrogen 2000 is directly contacted with the pressurized air 1011 with high temperature in the expansion space 1410 to be violently gasified, so that the volume of the liquid nitrogen 2000 is expanded to form expanded nitrogen 2001, the expanded nitrogen 2001 is output from the expansion chamber 141 to the power assembly 15 through the guide of the guide member 142, and the expanded nitrogen 2001 pushes a turbine 151 of the power assembly 15 to do work to output power. The beneficial effect of such setting lies in, inject liquid nitrogen 2000 into expansion space 141, mix with high temperature pressurized air 1011 and expand and do work, because the volume of the liquid nitrogen of unit mass is about 700 times of nitrogen (nitrogen is under 21 ℃), the volume of liquid nitrogen 2000 in the expansion space 141 of finite volume expands rapidly, causes the surge of pressure, effectively controls the export direction and the area of discharge expansion chamber 141 through guide 142, promotes turbine 151 rotation and does work. The liquid nitrogen expansion assembly 14 replaces the combustion chamber 300 of the gas turbine power system 10 shown in fig. 1 and 2, and combustion does not occur in the aeronautical power system 1, so that no pollution and zero emission exist; and the safety of the liquid nitrogen is higher than that of the aviation kerosene, the liquid nitrogen can be obtained from the air, the source is wide, and the defect of dangerous storage is avoided. Moreover, compared with the gas turbine power system 10, the aero-power system 1 has low system temperature due to no combustion, improves the working condition of the engine, reduces the performance requirement of the power system on materials, and reduces the material cost of the power system. In an embodiment, similar to the structure of the gas turbine power system of fig. 1 and 2, the compressor unit 121 may include a low-pressure compressor and a high-pressure compressor, and the turbine 151 may include a low-pressure turbine and a high-pressure turbine, the low-pressure compressor is coaxially coupled to the low-pressure turbine, and the high-pressure compressor is coaxially coupled to the high-pressure turbine, so that the turbine 151 outputs power outwards and simultaneously delivers power for compressing air by the compressor unit 121 to the interior of the aero-power system 1.
With continued reference to fig. 3, in one embodiment, the aircraft power system 1 may be configured such that the air separation module 13 further includes a liquid oxygen storage tank 133, which may be configured as a liquid oxygen storage tank; the air separator 131 is used for separating liquid nitrogen 2000 and liquid oxygen 2002 from air 1002, and respectively outputs the liquid nitrogen 2000 to the liquid nitrogen storage container 132 and outputs the liquid oxygen 2002 to the liquid oxygen storage container 133, and the aircraft power system further comprises an oxygen supply assembly 16 for outputting the liquid oxygen 2002 in the liquid oxygen storage container 133 to a cabin of the aircraft, wherein the cabin comprises a passenger cabin containing passengers and/or a cockpit containing a driver. The beneficial effect that so sets up lies in, aviation driving system 1 had both realized the expanded zero release operation of liquid nitrogen, had also realized the oxygen system that online preparation liquid oxygen was used for the aircraft simultaneously in the lump, had provided one kind promptly and had provided power of can the zero release, can make the miniaturized, lightweight driving system of oxygen system again, had avoided the equipment that the liquid oxygen that current liquid oxygen system prepared liquid oxygen on ground brought is complicated on ground storage, and the problem such as maintenance cost height, has achieved two birds with one stone.
With continued reference to fig. 3 and 4, in some embodiments, the specific structure of the aeronautical power system 1 may further include a first conduit 171 that delivers liquid nitrogen 2000 from the air separation member 131 to the liquid nitrogen storage container 132, a second conduit 172 that delivers liquid nitrogen 2000 from the liquid nitrogen storage container 132 to the expansion chamber 141 at the first inlet 1411, and a second flow valve 182 that controls the flow rate of the liquid nitrogen 2000 delivered to the first inlet 1411; a third line 173 that delivers liquid oxygen 2002 from the air separator 131 to the liquid oxygen storage container 133, a fourth line 174 that delivers liquid oxygen 2002 from the liquid oxygen storage container 133 to the oxygen supply assembly 16, and a fourth flow valve 184 that controls the flow rate at which liquid oxygen 2002 is delivered to the fourth line 174. Further, with continued reference to fig. 3 and 4, in one or more embodiments, the aircraft power system 1 may further include a first relief valve 181 disposed in the liquid nitrogen storage vessel 132, and a third relief valve 183 disposed in the liquid oxygen storage vessel 133, so as to further ensure the safety of the power system. Referring to fig. 3, in an embodiment, the aircraft power system 1 may further include a fifth distribution valve 185 and a fifth pipeline 175 and a sixth pipeline 176, the fifth distribution valve 185 being coupled to the intake portion 11 for distributing a ratio of air 1001 delivered from the intake portion 11 to the plenum assembly 12 to air 1002 delivered to the air separator 131, the air 1001 being delivered to the plenum assembly 12 through the fifth pipeline 175, and the air 1002 being delivered to the air separator 131 through the sixth pipeline 176. The beneficial effect of setting up above valve and pipeline lies in, can be so that the transport of liquid nitrogen and liquid oxygen is easily controlled, realizes the control to liquid nitrogen and liquid oxygen supply under the different operating modes of aviation driving system, for example take-off, landing, cruise, acceleration etc. operating mode.
It will be appreciated that the steam power system 1 described above, similar to the gas turbine power system 10 shown in fig. 1 and 2, can be used in an aircraft, such as a civil aircraft, so as to achieve the goal of zero emission of the aircraft and save the use cost. Meanwhile, the structure of the aircraft of the existing gas turbine power system can be simply transformed and applied to the aircraft of the aviation power system 1, so that the structural design difficulty of adopting a new power system is reduced.
Referring to fig. 5, the method of the aircraft described in the above embodiment may be:
step S1: pressurizing a part of air to obtain pressurized air;
step S2: separating the other part of air to separate liquid nitrogen, injecting the liquid nitrogen to be directly contacted with the pressurized air, gasifying the liquid nitrogen by utilizing the temperature of the pressurized air, and expanding the volume of the liquid nitrogen to form expanded nitrogen;
step S3: and introducing the expanded nitrogen into the turbine, and performing work by expansion to drive the turbine to rotate to provide power.
Specifically, in some embodiments, in step S2, another portion of air is separated to separate liquid nitrogen and liquid oxygen, and the liquid oxygen is output to the cabin of the aircraft.
In summary, the beneficial effects of the aviation power system, the liquid nitrogen expansion assembly, the aircraft and the driving method thereof adopting the above embodiments include but are not limited to:
1. the expansion chamber of the liquid nitrogen expansion assembly replaces a combustion chamber, and combustion does not occur, so that pollution and zero emission are avoided; the safety of the liquid nitrogen is higher than that of aviation kerosene, the liquid nitrogen can be obtained from the air, the source is wide, and the defect of dangerous storage is avoided;
2. compared with a gas turbine power system, the aviation power system adopting liquid nitrogen has low system temperature due to no combustion, improves the working condition of an engine, reduces the performance requirement of the power system on materials, and reduces the material cost of the power system;
3. the power system provides power, and simultaneously, the online preparation of the liquid oxygen and the liquid nitrogen is realized, so that the problems of complex equipment, high maintenance cost and the like caused by the ground preparation of the liquid oxygen and the ground storage of the liquid oxygen are solved.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (10)
1. An aircraft power system, comprising:
an air intake from which air enters the power system;
the supercharging assembly comprises a compressor unit, wherein a part of air of the air entering from the air inlet part enters the supercharging assembly, forms supercharging air through the supercharging of the compressor unit and is output from the compressor unit;
the air separation component comprises an air separation part and a liquid nitrogen storage container, wherein the air separation part is used for separating liquid nitrogen from another part of air entering from the air inlet part and outputting the air to the liquid nitrogen storage container;
the liquid nitrogen expansion assembly comprises an expansion chamber and a guide piece; the expansion chamber comprises a first inlet, a second inlet and an expansion space, wherein the first inlet is used for injecting liquid nitrogen output from the liquid nitrogen storage container to the expansion space, the second inlet is used for inputting the pressurized air to the expansion space, the liquid nitrogen is in direct contact with the pressurized air in the expansion space and is vigorously gasified, so that the volume of the liquid nitrogen is expanded to form expanded nitrogen, and the expanded nitrogen is guided to be output from the expansion chamber through the guide;
and
and the power assembly comprises a turbine and is pushed by the expanded nitrogen to do work and output power.
2. The aeronautical power system of claim 1,
the air separation component is used for separating liquid nitrogen and liquid oxygen from the other part of air and respectively outputting the liquid nitrogen and the liquid oxygen to the liquid nitrogen storage container and the liquid oxygen storage container;
the aircraft power system also includes an oxygen supply assembly for outputting liquid oxygen from the liquid oxygen storage vessel to an aircraft cabin via the oxygen supply assembly.
3. The aircraft power system according to claim 2, further comprising a first conduit for delivering said liquid nitrogen from said air separation member to a liquid nitrogen storage vessel, a second conduit for delivering said liquid nitrogen from said liquid nitrogen storage vessel to a first inlet of said expansion chamber, and a second flow valve for controlling the flow rate of delivery of said liquid nitrogen to said first inlet; a third conduit for conveying the liquid oxygen from the air separator to a liquid oxygen storage container, a fourth conduit for conveying the liquid oxygen from the liquid oxygen storage container to the oxygen supply assembly, and a fourth flow valve controlling the flow rate of the liquid oxygen conveyed to the fourth conduit.
4. The aircraft power system of claim 3, further comprising a first relief valve disposed in said liquid nitrogen storage vessel, and a third relief valve disposed in said liquid oxygen storage vessel.
5. The aircraft power system according to claim 1, further comprising a fifth distribution valve coupled to the air intake for distributing a ratio of air delivered to a plenum assembly to the air separation member, and a fifth conduit through which the portion of air is delivered to the plenum assembly and a sixth conduit through which the other portion of air is delivered to the air separation member.
6. The aircraft power system of claim 1 wherein said compressor assembly comprises a low pressure compressor and a high pressure compressor, said turbines comprising a low pressure turbine and a high pressure turbine, said low pressure compressor being coaxially coupled to said low pressure turbine and said high pressure compressor being coaxially coupled to said high pressure turbine.
7. An aircraft comprising a nacelle and a power system, wherein the power system is according to any of claims 1-6.
8. The liquid nitrogen expansion assembly is characterized by comprising an expansion chamber and a guide piece; the expansion chamber is provided with a first inlet and a second inlet, liquid nitrogen is injected into the expansion chamber through pressurization at the first inlet, pressurized air is input into the expansion chamber at the second inlet, and the liquid nitrogen is directly contacted with the pressurized air in the expansion chamber to be violently gasified, so that the volume of the liquid nitrogen is expanded to form expanded nitrogen, and work is output from the expansion chamber through the guide piece.
9. A method for driving an aircraft, comprising:
step S1: pressurizing a part of air to obtain pressurized air;
step S2: separating the other part of air to separate liquid nitrogen, injecting the liquid nitrogen to be directly contacted with the pressurized air, gasifying the liquid nitrogen by utilizing the temperature of the pressurized air, and expanding the volume of the liquid nitrogen to form expanded nitrogen;
step S3: and introducing the expanded nitrogen into the turbine, and performing work by expansion to drive the turbine to rotate to provide power.
10. The driving method according to claim 9, wherein in step S2, another portion of air is separated to separate liquid nitrogen and liquid oxygen, and the liquid oxygen is output to a cabin of the aircraft.
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| CN201911190365.4A CN112855343B (en) | 2019-11-28 | 2019-11-28 | Aviation power system, liquid nitrogen expansion assembly, aircraft and driving method thereof |
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| CN108625916A (en) * | 2017-03-21 | 2018-10-09 | 广州市谷城科研技术有限公司 | A kind of double drive engines of liquid nitrogen |
| CN109441637A (en) * | 2018-09-03 | 2019-03-08 | 北京航空航天大学 | A kind of aircraft using nitrogen supercharging fuel tank is had more than needed electric integrated system and method |
| CN109736911A (en) * | 2019-03-05 | 2019-05-10 | 贵州康德农业科技有限公司 | A kind of liquid nitrogen power regenerating recycles vaporization electricity-generating method and generating equipment |
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2019
- 2019-11-28 CN CN201911190365.4A patent/CN112855343B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE69004773D1 (en) * | 1989-09-25 | 1994-01-05 | Air Liquide | Cooling process, the cooling circuit used and its application in air separation. |
| CN201635781U (en) * | 2010-03-12 | 2010-11-17 | 罗晨嘉 | Liquid nitrogen engine device |
| CN106740403A (en) * | 2017-03-21 | 2017-05-31 | 西北工业大学 | A kind of liquid nitrogen power output system and hybrid power cold chain transportation car |
| CN108625916A (en) * | 2017-03-21 | 2018-10-09 | 广州市谷城科研技术有限公司 | A kind of double drive engines of liquid nitrogen |
| CN109441637A (en) * | 2018-09-03 | 2019-03-08 | 北京航空航天大学 | A kind of aircraft using nitrogen supercharging fuel tank is had more than needed electric integrated system and method |
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| CN112855343B (en) | 2022-05-06 |
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