CN113236426B - Transcritical based CO2Multi-mode combined power cycle system and method - Google Patents
Transcritical based CO2Multi-mode combined power cycle system and method Download PDFInfo
- Publication number
- CN113236426B CN113236426B CN202110600051.8A CN202110600051A CN113236426B CN 113236426 B CN113236426 B CN 113236426B CN 202110600051 A CN202110600051 A CN 202110600051A CN 113236426 B CN113236426 B CN 113236426B
- Authority
- CN
- China
- Prior art keywords
- air
- turbine
- combustion chamber
- afterburner
- main combustion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 11
- 238000002485 combustion reaction Methods 0.000 claims abstract description 41
- 239000007788 liquid Substances 0.000 claims abstract description 21
- 239000007921 spray Substances 0.000 claims abstract description 15
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims abstract description 13
- 239000007789 gas Substances 0.000 claims description 16
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 6
- 239000001301 oxygen Substances 0.000 claims description 6
- 229910052760 oxygen Inorganic materials 0.000 claims description 6
- 230000001105 regulatory effect Effects 0.000 claims description 6
- 239000000446 fuel Substances 0.000 claims description 5
- 239000001307 helium Substances 0.000 abstract description 7
- 229910052734 helium Inorganic materials 0.000 abstract description 7
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 abstract description 7
- 238000011084 recovery Methods 0.000 abstract description 3
- 238000009833 condensation Methods 0.000 abstract 1
- 230000005494 condensation Effects 0.000 abstract 1
- 230000001276 controlling effect Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000003350 kerosene Substances 0.000 description 2
- 108091053398 TRIM/RBCC family Proteins 0.000 description 1
- 102000011408 Tripartite Motif Proteins Human genes 0.000 description 1
- 102100040255 Tubulin-specific chaperone C Human genes 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002309 gasification Methods 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000001502 supplementing effect Effects 0.000 description 1
- 108010093459 tubulin-specific chaperone C Proteins 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
Images
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
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
-
- 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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
-
- 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
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
A transcritical CO2 multi-mode combined power circulation system and a method belong to the field of aviation power propulsion. The invention couples the turbine engine, the ramjet engine and the supercritical CO2 Brayton cycle, so that the hypersonic aircraft can be switched under various modes, thereby achieving the purpose of working in a wider area. The system comprises an air inlet channel (1), an inner duct (2), an outer duct (3), a precooler (4), an air compressor (5), a main combustion chamber (6), an air turbine (7), an afterburner (8), a spray pipe (9), a CO2 turbine (12), a condenser (13), a pump (14), a liquid CO2 tank (10), a liquid oxygen tank (15), a first switch (11) and a second switch (16). According to the combined power cycle provided by the invention, a transcritical CO2 closed type heat energy cascade recovery Brayton cycle is adopted in an ultra-precooling flight mode, and liquid oxygen is utilized for condensation, so that the energy utilization of the system is maximized. In addition, the supercritical CO2 is adopted as the precooling working medium to replace the traditional helium, so that the system is more compact in structure and higher in thrust, and can quickly meet the requirement of wider-area work.
Description
Technical Field
The invention relates to a transcritical CO2 multi-mode combined power circulation system and a method, and belongs to the field of improvement of combined power circulation systems of aero-engines.
Background
In hypersonic speed remote cruise flight, a power system needs to meet the requirement that the performance in a Ma 0-5 flight envelope is optimal, and the traditional engine in a single form is difficult to stably work in a full-speed domain range. However, when the flight speed is increased, the total temperature of the inlet airflow of the air inlet channel is increased, and is limited by materials, and the total temperature of the inlet of the air turbine has an upper limit, so that the increase of the total temperature of the incoming flow gradually reduces the heating capacity of the air, and the thrust in the mode switching stage is small. To solve this problem, a composite precooling scheme has come into use, and the most popular scheme is a "bent blade" engine. The engine with the bent blades has two working modes, namely a low-speed mode and a high-speed mode. Thrust is mainly provided through the bypass turbofan engine in the low-speed mode (0-2.5), and the bypass channel is closed in the high-speed mode (2.5-5), and the precooling system is opened to apply work through the turbine ramjet engine. The 'bent blade' engine combines the characteristics of a turbine engine and a ramjet engine, so that the working speed range of the 'bent blade' engine is wider, the working airspace of the 'bent blade' engine is wider, the problem of 'thrust gap' of a mode conversion point of a TBCC engine is avoided, the problem of insufficient injection mode thrust gain of a low-speed section of the RBCC engine is avoided, all parts of the engine in a whole working area can realize high-efficiency work, but the 'bent blade' engine selects helium as a cooling medium, because the characteristics of low density and effective utilization of sensible heat exchange capability will bring about insufficient precooling capability and huge and complex structure of a precooling system, the method puts high requirements on the thermal management technology of the aircraft, simultaneously, the reduction of the oxygen content in an afterburner also becomes one of the key factors that the engine cannot further improve the Mach number, therefore, the aircraft with strong precooling capability and simple precooling system structure becomes an important direction for the next development of the turbo-stamping combined engine.
Disclosure of Invention
The invention aims to provide a transcritical CO2 multi-mode combined power cycle system and a method thereof.
A transcritical CO2 multi-mode combined power cycle system is characterized by comprising an air inlet channel, an inner duct, an outer duct, a precooler, an air compressor, a main combustion chamber, an air turbine, an afterburner, a spray pipe, a liquid CO2 tank, a first switch, a CO2 turbine, a condenser, a pump, a liquid oxygen tank, a second switch and fuel; the outlet of the air inlet channel is divided into a first outlet branch and a second outlet branch, the first outlet branch is connected with the inlet of the hot side of the precooler through an inner duct, the outlet of the hot side of the precooler is connected with the inlet of the hot side of the main combustion chamber through the compressor, the outlet of the hot side of the main combustion chamber is connected with the inlet of the hot side of the afterburner after the air turbine applies work, and the air in the outlet of the hot side of the afterburner is discharged after passing through the spray pipe; the second outlet branch is connected with the inlet at the hot side of the main combustion chamber through an outer duct; an outlet of the liquid CO2 tank is connected with a cold side inlet of the precooler after passing through a first switch, the cold side outlet of the precooler is connected with a cold side inlet of the main combustion chamber, the cold side outlet of the main combustion chamber is connected with a hot side inlet of the condenser after doing work through a CO2 turbine, and the hot side outlet of the condenser is connected with an inlet of the liquid CO2 tank through a pump; an outlet of the liquid oxygen tank is connected with a cold side inlet of a condenser through a second switch, the cold side outlet of the condenser is connected with a cold side inlet of the afterburner, and the cold side outlet of the afterburner is connected with a hot side inlet of the afterburner; the air inlet channel is an adjustable air inlet channel.
The working method of the transcritical CO2 multi-mode combined power cycle system comprises the following steps: can be divided into 3 modes (a turbine mode, a transonic speed mode and a super precooling mode);
turbine mode: the flight Mach number is 0-0.9; the first switch and the second switch are closed, the outer duct is opened by regulating and controlling the air inlet channel, air enters the air inlet channel and then is divided into the inner duct and the outer duct, the air in the outer duct directly enters the main combustion chamber, the air in the inner duct enters the air compressor to be boosted, high-pressure air enters the main combustion chamber to be combusted, high-temperature and high-pressure air does work through the air turbine to provide work required by the air compressor, and the high-temperature and high-pressure air after doing work directly passes through the spray pipe to generate required thrust;
transonic mode: the flight Mach number is 0.9-2.5; on the basis of a turbine mode, high-temperature and high-pressure air which does work through an air turbine (7) firstly enters an afterburner (8) for further combustion, and then air with higher temperature and higher pressure passes through a spray pipe (9) to generate huge thrust;
super-precooling mode: the flight Mach number is 2.5-8.0; opening the first switch and the second switch, enabling liquid CO2 in a liquid CO2 tank to enter a precooler for preheating, introducing primarily heated CO2 gas into a main combustion chamber for heat exchange, heating, introducing high-temperature and high-pressure CO2 gas into a CO2 turbine for work, increasing thrust, condensing CO2 gas after work through a condenser, and then changing the gas into high-pressure liquid CO2 through pressurization of a pump to be stored in a liquid CO2 tank again; meanwhile, the outer duct is closed by regulating and controlling the air inlet channel, air enters the inner duct after entering the air inlet channel, and air in the inner duct passes throughCooling the precooler, entering the compressor for boosting, entering high-pressure air into the main combustion chamber for combustion, providing work required by the compressor by the high-temperature high-pressure air through the air turbine, introducing the high-temperature high-pressure air after acting into the afterburner for further combustion, and then performing acting on the air with higher temperature and higher pressure through the spray pipe; the liquid oxygen in the liquid oxygen tank is evaporated by the condenser to become O2The gas is introduced into the afterburner, the oxygen content in the afterburner is increased, the combustion is more sufficient, and higher thrust is obtained, so that higher flight speed is realized.
Compared with the prior art, the invention has at least the following advantages: compared with the traditional helium gas which is super-precooled by sensible heat, the invention adopts the supercritical CO2 as a precooling working medium, fully utilizes the latent heat of vaporization of CO2, enhances the precooling effect, makes the combined cycle have larger thrust in a super-precooling mode, and simultaneously makes up the defect of low helium gas density by the characteristics of high pressure and high density of the supercritical CO2, makes the carrying and the storage more convenient, reduces the space occupancy rate and further reduces the structural complexity; in the system, CO2 is preheated in a precooler and then is further heated in a main combustion chamber, so that the cascade energy recovery of CO2 is realized, the energy recovered by the cascade energy recovery is utilized to do work by a turbine, and the energy utilization maximization of the whole process is realized. Compared with the most advanced engine with the curved blade at present, the invention adds the oxygen supplementing system, solves the problem of difficult ignition due to low oxygen content in the afterburner, improves the combustion efficiency, improves the combustion temperature, increases the thrust, and simultaneously condenses CO2 as an evaporant, so that the whole structure is more compact. The fuel used by the engine in the invention is aviation kerosene, while the fuel adopted in the 'bent blade' engine is liquid hydrogen, and the aviation kerosene has the advantages of high availability, low acquisition cost and high safety factor.
The transcritical-based CO2 multi-mode combined power cycle system is characterized in that: the wall surfaces of the main combustion chamber and the afterburner are respectively provided with a heat exchanger, and the heat exchangers and the condensers both adopt a dividing wall type heat exchanger structure, so that the wall surface of the combustion chamber is effectively cooled, and meanwhile, part of high-grade heat energy can be recovered to improve the thrust of CO2 Brayton cycle; the precooler adopts a wound tube type heat exchanger structure, and the wound tube type heat exchanger has the advantages of compact structure, quick cooling, smaller weight and high heat exchange efficiency, and can effectively avoid blocking an air inlet channel.
The transcritical-based CO2 multi-mode combined power cycle system is characterized in that: the super-precooling working mode adopts CO2 as a working medium. Compared with the traditional helium, the CO2 is used as a working medium, sensible heat exchange with the helium is distinguished, the better precooling effect can be achieved by fully utilizing the gasification potential of the CO2, larger thrust is generated, and the carried supercritical CO2 has the characteristics of high density and high pressure, is more convenient to carry and store compared with the helium, occupies smaller space, and can enable the structure of the whole system to be more compact.
Drawings
FIG. 1 is a transcritical based CO2 multi-modal combined power cycle system;
number designation in the figures: 1. The system comprises an air inlet channel, 2, an inner duct, 3, an outer duct, 4, a precooler, 5, a compressor, 6, a main combustion chamber, 7, an air turbine, 8, an afterburner, 9, a spray pipe, 10, a liquid CO2 tank, 11, a first switch, 12, a CO2 turbine, 13, a condenser, 14, a pump, 15, a liquid oxygen tank, 16, a second switch, 17 and fuel.
Detailed Description
The operation of the transcritical CO2 based multi-modal combined power cycle system is described below with reference to fig. 1.
FIG. 1 is a transcritical based CO2 multi-mode combined power cycle system proposed by the present invention. The working process of the system is as follows: it can be divided into 3 modes (low speed mode, high speed mode and ultra high speed mode).
Turbine mode: the flight Mach number is 0-0.9; closing the first switch 11 and the second switch 16, simultaneously opening the outer duct 3 by regulating the air inlet channel 1, dividing the air into the inner duct 2 and the outer duct 3 after entering the air inlet channel 1, directly entering the air in the outer duct 3 into the main combustion chamber 6, entering the air in the inner duct 2 into the air compressor 5 for boosting, entering the high-pressure air into the main combustion chamber 6 for combustion, applying work to the high-temperature and high-pressure air through the air turbine 7 to provide the work required by the air compressor, and directly passing the high-temperature and high-pressure air after applying work through the spray pipe 9 to generate the required thrust; (ii) a
Transonic mode: the flight Mach number is 0.9-2.5; on the basis of a turbine mode, high-temperature and high-pressure air which does work through an air turbine 7 firstly enters an afterburner 8 for further combustion, and then air with higher temperature and higher pressure passes through a spray pipe 9 to generate huge thrust;
super-precooling mode: the flight Mach number is 2.5-8.0; the first switch 11 and the second switch 16 are opened, liquid CO2 in the liquid CO2 tank 10 enters the precooler 4 to be preheated, the primarily heated CO2 gas is introduced into the main combustion chamber 6 to exchange heat, the temperature is raised, the high-temperature and high-pressure CO2 gas is introduced into the CO2 turbine 12 to do work, the thrust is increased, the CO2 gas after doing work is condensed by the condenser 13, and then the gas is changed into high-pressure liquid CO2 through the pressurization of the pump 14 to be stored in the liquid CO2 tank 10 again; meanwhile, the outer duct 3 is closed by regulating the air inlet channel 1, air enters the air inlet channel 1 and then enters the inner duct 2, the air in the inner duct 2 enters the air compressor 5 through the cooling of the precooler 4 to be boosted, high-pressure air enters the main combustion chamber 6 to be combusted, high-temperature and high-pressure air provides work required by the air compressor through the air turbine 7, the high-temperature and high-pressure air after acting is introduced into the afterburner 8 to be further combusted, and then the air with higher temperature and higher pressure acts through the spray pipe 9; the liquid oxygen in the liquid oxygen tank 15 is evaporated to O by the condenser 132Gas is introduced into the afterburner 8, and the oxygen content in the afterburner 8 is increased, so that combustion is more sufficient, and higher thrust is obtained, and higher flight speed is realized.
Claims (4)
1. A transcritical CO2 multi-mode combined power cycle system is characterized by comprising an air inlet channel (1), an inner duct (2), an outer duct (3), a precooler (4), an air compressor (5), a main combustion chamber (6), an air turbine (7), an afterburner (8), a spray pipe (9), a liquid CO2 tank (10), a first switch (11), a CO2 turbine (12), a condenser (13), a pump (14), a liquid oxygen tank (15), a second switch (16) and fuel (17); the outlet of the air inlet channel (1) is divided into a first outlet branch and a second outlet branch, the first outlet branch is connected with the hot-side inlet of the precooler (4) through an inner duct (2), the hot-side outlet of the precooler (4) is connected with the hot-side inlet of the main combustion chamber (6) through the air compressor (5), the hot-side outlet of the main combustion chamber (6) is connected with the hot-side inlet of the afterburner (8) after acting through the air turbine (7), and air in the hot-side outlet of the afterburner (8) is discharged after passing through the spray pipe (9); the second outlet branch is connected with a hot side inlet of the main combustion chamber (6) through an outer duct (3); an outlet of a liquid CO2 tank (10) is connected with a cold side inlet of a precooler (4) after passing through a first switch (11), the cold side outlet of the precooler (4) is connected with a cold side inlet of a main combustion chamber (6), the cold side outlet of the main combustion chamber (6) is connected with a hot side inlet of a condenser (13) after acting through a CO2 turbine (12), and the hot side outlet of the condenser (13) is connected with the inlet of a liquid CO2 tank (10) through a pump (14); an outlet of the liquid oxygen tank (15) is connected with a cold side inlet of the condenser (13) through a second switch (16), a cold side outlet of the condenser (13) is connected with a cold side inlet of the afterburner (8), and a cold side outlet of the afterburner (8) is connected with a hot side inlet of the afterburner (8); the air inlet (1) is an adjustable air inlet.
2. The working method of the transcritical based CO2 multi-modal combined power cycle system according to claim 1, comprising the following processes: can be divided into 3 modes;
turbine mode: the flight Mach number is 0-0.9; the first switch (11) and the second switch (16) are closed, meanwhile, the outer duct (3) is opened by regulating the air inlet channel (1), air enters the air inlet channel (1) and then is divided into the inner duct (2) and the outer duct (3), the air in the outer duct (3) directly enters the main combustion chamber (6), the air in the inner duct (2) enters the air compressor (5) to be boosted, high-pressure air enters the main combustion chamber (6) to be combusted, high-temperature and high-pressure air does work through the air turbine (7) to provide work required by the air compressor, and the high-temperature and high-pressure air after doing work directly passes through the spray pipe (9) to generate required thrust;
transonic mode: the flight Mach number is 0.9-2.5; on the basis of a turbine mode, high-temperature and high-pressure air which does work through an air turbine (7) firstly enters an afterburner (8) for further combustion, and then air with higher temperature and higher pressure passes through a spray pipe (9) to generate huge thrust;
super-precooling mode: the flight Mach number is 2.5-8.0; the first switch (11) and the second switch (16) are opened, liquid CO2 in a liquid CO2 tank (10) enters a precooler (4) to be preheated, the primarily heated CO2 gas is introduced into a main combustion chamber (6) to exchange heat, the temperature is raised, the high-temperature and high-pressure CO2 gas is introduced into a CO2 turbine (12) to do work, the thrust is increased, the CO2 gas after doing work is condensed through a condenser (13), and then the CO 3583 is changed into high-pressure liquid CO2 through the pressurization of a pump (14) to be stored in the liquid CO2 tank (10) again; meanwhile, the outer duct (3) is closed by regulating the air inlet channel (1), air enters the inner duct (2) after entering the air inlet channel (1), the air in the inner duct (2) is cooled by the precooler (4) and enters the air compressor (5) to be boosted, high-pressure air enters the main combustion chamber (6) to be combusted, high-temperature and high-pressure air provides work required by the air compressor through the air turbine (7), the high-temperature and high-pressure air after acting is introduced into the afterburning chamber (8) to be further combusted, and then the air with higher temperature and higher pressure acts through the spray pipe (9); the liquid oxygen in the liquid oxygen tank (15) is evaporated into O through the condenser (13)2The gas is introduced into the afterburner (8), and the oxygen content in the afterburner (8) is increased, so that the combustion is more sufficient, and higher thrust is obtained, and higher flight speed is realized.
3. The transcritical based CO2 multi-modal combined power cycle system of claim 1, wherein: the wall surfaces of the main combustion chamber (6) and the afterburner (8) are respectively provided with a heat exchanger, and the heat exchangers adopt a dividing wall type heat exchanger structure; the precooler (4) and the condenser (13) both adopt a wound tube type heat exchanger structure.
4. The transcritical based CO2 multi-modal combined power cycle system of claim 3, wherein: the super-precooling working mode adopts CO2 as a working medium.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202110600051.8A CN113236426B (en) | 2021-05-31 | 2021-05-31 | Transcritical based CO2Multi-mode combined power cycle system and method |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202110600051.8A CN113236426B (en) | 2021-05-31 | 2021-05-31 | Transcritical based CO2Multi-mode combined power cycle system and method |
Publications (2)
Publication Number | Publication Date |
---|---|
CN113236426A CN113236426A (en) | 2021-08-10 |
CN113236426B true CN113236426B (en) | 2022-04-08 |
Family
ID=77136066
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN202110600051.8A Active CN113236426B (en) | 2021-05-31 | 2021-05-31 | Transcritical based CO2Multi-mode combined power cycle system and method |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN113236426B (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN113738514B (en) * | 2021-08-12 | 2022-07-12 | 南京航空航天大学 | Multi-mode combined power cycle system and method for precooling/supporting combustion by using N2O |
CN113882968B (en) * | 2021-10-13 | 2022-10-11 | 中南大学 | Wide-speed-range multi-working-medium efficiency matching combined power system |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2003148112A (en) * | 2001-11-09 | 2003-05-21 | Toshiba Corp | Turbine plant |
CN105888882A (en) * | 2014-12-25 | 2016-08-24 | 王正铉 | Device utilizing liquid carbon dioxide gasification to improve thrust of aircraft |
CN107989699B (en) * | 2017-11-27 | 2019-09-27 | 北京航空航天大学 | Aircraft propulsion is combined in pre-cooling by force for punching press-based on double fuel Compound cooling |
US11193421B2 (en) * | 2019-06-07 | 2021-12-07 | Saudi Arabian Oil Company | Cold recycle process for gas turbine inlet air cooling |
CN111636977A (en) * | 2020-05-18 | 2020-09-08 | 北京航空航天大学 | Precooling and circulation-changing combined propulsion system and running mode of high-speed aircraft |
CN111577466A (en) * | 2020-06-22 | 2020-08-25 | 中国航空发动机研究院 | Ice-proof bleed air preheating and turbine cooling bleed air precooling system for aircraft engine |
-
2021
- 2021-05-31 CN CN202110600051.8A patent/CN113236426B/en active Active
Also Published As
Publication number | Publication date |
---|---|
CN113236426A (en) | 2021-08-10 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN113236426B (en) | Transcritical based CO2Multi-mode combined power cycle system and method | |
US8707701B2 (en) | Ultra-high-efficiency engines and corresponding thermodynamic system | |
US6848249B2 (en) | Coleman regenerative engine with exhaust gas water extraction | |
CN112923595B (en) | Self-condensation type compressed carbon dioxide energy storage system and method based on vortex tube | |
CN104110326B (en) | A kind of new ideas high-speed aircraft propulsion system layout method | |
CN110887278B (en) | Energy self-sufficient carbon dioxide combined cooling heating and power system for low-grade heat source | |
CN110905747B (en) | Combined power cycle power generation system utilizing high-temperature solar energy and LNG cold energy | |
CN112377324A (en) | Active cooling and combustion decoupling system of scramjet engine | |
CN107939528B (en) | Strong precooling aircraft propulsion system based on coolant and fuel composite cooling | |
CN108716783A (en) | A kind of back pressure injecting type Trans-critical cycle CO2Power cycle generating system | |
CN109630268B (en) | Hypersonic aircraft and propulsion system thereof | |
CN109026444B (en) | Combined engine | |
CN113915003B (en) | Based on NH 3 Extremely-wide-speed-domain multi-mode combined power cycle system and method | |
CN111365131A (en) | Power-cooling combined supply system driven by exhaust smoke waste heat of gas turbine and method thereof | |
US20200284478A1 (en) | Method and system for circulating combined cooling, heating and power with jet cooling device | |
CN110552750B (en) | Non-azeotropic organic Rankine-dual-injection combined cooling, heating and power system | |
CN113738514B (en) | Multi-mode combined power cycle system and method for precooling/supporting combustion by using N2O | |
CN114810253A (en) | Liquefied air energy storage system utilizing LNG cold energy and working method thereof | |
CN116733562A (en) | Carbon dioxide-shifted brayton cooling and power generation system and method coupled with a fuel heat sink | |
CN110821707A (en) | Diesel engine waste heat utilization cascade coupling system based on carbon dioxide power circulation | |
US20130105110A1 (en) | Integrated absorption-cycle refrigeration and power generation system | |
CN115773180A (en) | Combined circulation system combined with Allam circulation type power station and low-temperature circulation method | |
CN112523826B (en) | Multi-mode ship main engine waste heat utilization system and operation method | |
CN112160837A (en) | Closed circulation heat management integrated system based on supercritical medium | |
CN113882920B (en) | Open type CO2semi-Brayton cooling and power generation system |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
SE01 | Entry into force of request for substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
GR01 | Patent grant | ||
GR01 | Patent grant |