CN112431675B - Combined scramjet engine cooling circulation system - Google Patents
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- CN112431675B CN112431675B CN202011332119.0A CN202011332119A CN112431675B CN 112431675 B CN112431675 B CN 112431675B CN 202011332119 A CN202011332119 A CN 202011332119A CN 112431675 B CN112431675 B CN 112431675B
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- 238000001816 cooling Methods 0.000 title claims abstract description 114
- 239000000446 fuel Substances 0.000 claims abstract description 36
- 229910001338 liquidmetal Inorganic materials 0.000 claims abstract description 22
- 238000002485 combustion reaction Methods 0.000 claims abstract description 16
- 239000002828 fuel tank Substances 0.000 claims abstract description 12
- 239000003350 kerosene Substances 0.000 claims abstract description 11
- 238000002955 isolation Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 4
- 238000005192 partition Methods 0.000 claims description 4
- 238000007789 sealing Methods 0.000 claims description 4
- 229910001152 Bi alloy Inorganic materials 0.000 claims description 3
- DGAQECJNVWCQMB-PUAWFVPOSA-M Ilexoside XXIX Chemical compound C[C@@H]1CC[C@@]2(CC[C@@]3(C(=CC[C@H]4[C@]3(CC[C@@H]5[C@@]4(CC[C@@H](C5(C)C)OS(=O)(=O)[O-])C)C)[C@@H]2[C@]1(C)O)C)C(=O)O[C@H]6[C@@H]([C@H]([C@@H]([C@H](O6)CO)O)O)O.[Na+] DGAQECJNVWCQMB-PUAWFVPOSA-M 0.000 claims description 3
- 229910000799 K alloy Inorganic materials 0.000 claims description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 3
- 229910000978 Pb alloy Inorganic materials 0.000 claims description 3
- 229910052792 caesium Inorganic materials 0.000 claims description 3
- TVFDJXOCXUVLDH-UHFFFAOYSA-N caesium atom Chemical compound [Cs] TVFDJXOCXUVLDH-UHFFFAOYSA-N 0.000 claims description 3
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- JWZCKIBZGMIRSW-UHFFFAOYSA-N lead lithium Chemical compound [Li].[Pb] JWZCKIBZGMIRSW-UHFFFAOYSA-N 0.000 claims description 3
- 229910052744 lithium Inorganic materials 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 3
- BITYAPCSNKJESK-UHFFFAOYSA-N potassiosodium Chemical compound [Na].[K] BITYAPCSNKJESK-UHFFFAOYSA-N 0.000 claims description 3
- 229910052701 rubidium Inorganic materials 0.000 claims description 3
- IGLNJRXAVVLDKE-UHFFFAOYSA-N rubidium atom Chemical compound [Rb] IGLNJRXAVVLDKE-UHFFFAOYSA-N 0.000 claims description 3
- 229910052708 sodium Inorganic materials 0.000 claims description 3
- 239000011734 sodium Substances 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 claims description 2
- 239000000956 alloy Substances 0.000 claims description 2
- 230000008929 regeneration Effects 0.000 abstract description 9
- 238000011069 regeneration method Methods 0.000 abstract description 9
- 238000004939 coking Methods 0.000 abstract description 7
- 238000005336 cracking Methods 0.000 abstract description 6
- 239000002918 waste heat Substances 0.000 abstract description 6
- 238000012546 transfer Methods 0.000 abstract description 5
- 230000006866 deterioration Effects 0.000 abstract description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 12
- 239000007788 liquid Substances 0.000 description 6
- 229910052757 nitrogen Inorganic materials 0.000 description 6
- 239000002826 coolant Substances 0.000 description 4
- 239000000295 fuel oil Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 230000001172 regenerating effect Effects 0.000 description 2
- 229910000846 In alloy Inorganic materials 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000009412 basement excavation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009835 boiling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000000197 pyrolysis Methods 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
Images
Classifications
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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
- 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
- F02C7/22—Fuel supply systems
-
- 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
-
- 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
- F02C7/22—Fuel supply systems
- F02C7/224—Heating fuel before feeding to the burner
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/005—Combined with pressure or heat exchangers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention relates to a combined scramjet engine cooling circulation system, belonging to the technical field of air-breathing scramjet engine heat protection; the cooling system comprises a fuel tank, a fuel pump, a heat exchanger, a first cooling channel, a second cooling channel, a fuel injector and an electromagnetic pump; an annular cavity is formed between the inner wall surface and the outer wall surface of the engine outer shell and is divided into a first cooling channel and a second cooling channel; the fuel tank, the fuel pump, the heat exchanger, the first cooling channel and the fuel injector are sequentially connected through pipelines to form an open cooling circulation system, and the working medium is kerosene; the electromagnetic pump, the second cooling channel and the heat exchanger are sequentially connected through pipelines to form a closed cooling circulation system, and the working medium is liquid metal. The invention not only utilizes the waste heat of the wall surface of the combustion chamber of the engine, retains the advantages of an active regeneration cooling system, but also solves the problems of heat transfer deterioration, cracking coking and the like of the traditional cooling working medium, and constructs a high-efficiency energy management circulating system.
Description
Technical Field
The invention belongs to the technical field of heat protection of an air-breathing scramjet engine, and particularly relates to a combined scramjet engine cooling circulation system.
Background
The development of the advanced hypersonic flight vehicle is an important symbol of national comprehensive strength, and has great significance to military strategy, national economy and social life, while the Mach number Ma is currently>The aircraft of 5 is a product of human pursuit for higher flight speeds. However, as the demand for flight mach number and cruise time increases, the combustor thermal environment is extremely harsh due to high enthalpy incoming flow and combustion heat release, and the problem of advanced aircraft engine wall cooling becomes more and more pronounced. For example, when the flying height of the scramjet engine is 25km and the Mach number reaches 6.5, the aircraft can bear inlet incoming air of over 1800KGas temperature, wall gas temperature up to 2800K and 10MW/m 2 The heat flux density of (1). Research shows that even if the wall temperature is 1000K, the wall temperature still bears the heat flux density of megawatt level, if the wall temperature of the engine rises sharply, the wall material is corroded by heat, and the heat protection fails.
In the thermal protection technology of many scramjet engines, a regenerative cooling mode which takes aviation kerosene as a coolant and adopts a waste heat recycling technology is widely concerned. However, due to the limitation of the technology, the regenerative cooling faces many challenges, such as coking by pyrolysis of fuel, insufficient heat sink, uneven heat load of the asymmetrically heated wall surface, complex dynamic characteristics of the system, and the like, which are directly related to the single use of one fuel cooling source. How to get rid of the restraint of the traditional kerosene regeneration cooling thinking, another advanced cooling working medium is found to be used as an auxiliary cold source, and the two are reasonably arranged to hope that the combined cycle improves the thermal protection capability, which is very important.
The patent "scramjet water cooling plant" (CN 205955856U) provides a water-cooling scheme, adopts devices such as water tank, atomizing nozzle and exhaust nozzle, can effectively absorb scramjet unnecessary heat, and global equipment device simple structure has just improved system security moreover. However, the storage of water is relatively difficult, the boiling point is very small, and the fluid is easy to have two phase changes, which is not favorable for further excavation of the heat exchange capability in the regeneration cooling channel. The patent "scramjet liquid nitrogen cooling system" (CN 201510433952.7) discloses a scheme that adopts liquid nitrogen to cool the wall temperature of scramjet, and the related device that matches has equipment such as liquid nitrogen supply, high-pressure air supply, high-pressure gas collection, aims at effectively cooling the wall temperature, and the system is safer and more reliable moreover. On one hand, even if the liquid nitrogen has larger heat sink capacity and can not generate cracking coking problem, the liquid nitrogen can be used as a coolant in a circulating system, but the working medium needs to be in a high-pressure state and needs to be collected by waste gas, a complex matching device is additionally added, and the quality punishment of an aircraft is brought. On the other hand, the liquid nitrogen coolant belongs to the traditional cooling working medium, and along with the rapid development of the hypersonic air-breathing aircraft, an advanced new coolant working medium with high heat exchange performance needs to be further excavated, so that the cooling system is simpler in structure, and the cooling performance is greatly improved.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides a combined scramjet cooling circulation system, which combines open circulation and closed circulation, adopts liquid metal to exchange heat in the closed circulation, solves the problems of difficult regeneration cooling of the scramjet, excessive cracking and coking of cooling fuel, serious deficiency of heat sink and cold source, and is used for constructing the combined circulation system by an advanced auxiliary cooling working medium different from the traditional kerosene so as to improve the heat protection capability of the system.
The technical scheme of the invention is as follows: a combined scramjet engine cooling circulation system comprises a cooling channel, wherein the cooling channel is positioned in an annular cavity between the inner wall surface and the outer wall surface of an engine outer shell; the method is characterized in that: the fuel injection device also comprises a fuel tank, a fuel pump, a heat exchanger, a fuel injector and an electromagnetic pump;
an annular partition plate is arranged in the cooling channel along the radial direction, and the cooling channel is divided into a first cooling channel and a second cooling channel which are mutually independent; the annular cavity at the position opposite to the air inlet channel and the isolation section of the scramjet engine is a first cooling channel, and the annular cavity at the position opposite to the combustion chamber and the tail nozzle of the scramjet engine is a second cooling channel;
the fuel tank, the fuel pump, the heat exchanger, the first cooling channel and the fuel injector are sequentially connected through pipelines to form an open cooling circulation system, and a working medium of the open cooling circulation system is kerosene; the electromagnetic pump, the second cooling channel and the heat exchanger are sequentially connected through pipelines to form a closed cooling circulation system, and the circulating working medium in the closed cooling circulation system is liquid metal.
The further technical scheme of the invention is as follows: the liquid metal is one or a combination of more of lead, sodium, lithium, cesium, rubidium, sodium-potassium alloy, lead-bismuth alloy, lithium-lead alloy and indium-doped alloy.
The further technical scheme of the invention is as follows: the flow of the liquid metal can be automatically controlled by an electromagnetic pump, so that the temperature of the cooled wall surface is far lower than the temperature limit of the wall surface material of the combustion chamber.
The further technical scheme of the invention is as follows: the annular partition plate is located at a corresponding position between the isolation section and the combustion chamber of the scramjet engine.
The further technical scheme of the invention is as follows: the inner wall surface of the first cooling channel is provided with a through hole which is used as an outlet of the first cooling channel and is in sealing connection with a pipeline connected with a fuel injector; and the outer wall surface of the second cooling channel is provided with a through hole which is used as an inlet of the second cooling channel and is connected with a pipeline connected with the electromagnetic pump in a sealing way.
Advantageous effects
The invention has the beneficial effects that: 1) the Plantt number of the liquid metal is very small, and the thickness of the temperature boundary layer is far larger than that of the speed boundary layer, so that the convection heat transfer of the liquid metal is mainly carried out through the heat conduction of molecules in the layer, the liquid metal has stronger heat exchange performance, the heat load of a high heat flow density wall surface area is easy to take away, the wall surface temperature is greatly weakened, the heat transfer deterioration extreme working condition similar to the supercritical fluid can be effectively avoided, and the cracking coking problem is avoided; 2) the liquid metal auxiliary cooling circulation system effectively relieves the condition of cracking coking caused by heat absorption and temperature rise of kerosene, and the liquid metal closed cooling circulation and the kerosene regeneration open cooling circulation are respectively arranged in a high heat flow density wall area and a low heat flow density wall area, so that the condition that a cooling channel is blocked due to overhigh temperature rise of the kerosene can be effectively avoided; 3) the invention not only utilizes the waste heat of the wall surface of the combustion chamber of the engine, retains the advantages of an active regeneration cooling system, but also solves the problems of heat transfer deterioration, cracking coking and the like of the traditional cooling working medium, and constructs a high-efficiency energy management circulating system. According to the working process and the wall heat transfer analysis of the scramjet engine under the same working condition, the extreme heat flow density under the scheme of the invention is far lower than that of the traditional kerosene cooling regeneration scheme and is far lower than the limit temperature of the engine wall material of 1200K.
Drawings
FIG. 1 is a schematic view of a system configuration in embodiment 1 of the present invention;
FIG. 2 is a schematic view of the combined cooling cycle operation of the present invention;
description of reference numerals: 1. the fuel injection device comprises a fuel tank, 2. a fuel pump, 3. a heat exchanger, 4. a first cooling channel, 5. a fuel injector, 6. an electromagnetic pump, 7. a second cooling channel, 8. an air inlet, 9. an isolation section, 10. a combustion chamber and 11. a tail nozzle.
Detailed Description
The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
Referring to fig. 1, the combined scramjet cooling circulation system of the invention comprises an open cooling circulation system and a closed cooling circulation system; the working medium in the open cooling circulation system is kerosene; the working medium in the closed cooling circulation system is liquid metal, and the liquid metal is one or a combination of more of lead, sodium, lithium, cesium, rubidium, sodium-potassium alloy, lead-bismuth alloy, lithium-lead alloy and indium alloy.
The open cooling circulation system belongs to a fuel flowing cooling side and comprises a fuel tank 1, a fuel pump 2, a heat exchanger 3, a first cooling channel 4 and a fuel injector 5, wherein all the components are connected through pipelines. The fuel tank 1 is connected to the inlet of the fuel pump 2, the heat exchanger 3 is connected between the outlet of the fuel pump 2 and a first cooling channel 4, the first cooling channel 4 is positioned at the outer side wall surface of the intake passage and the isolation section, and the fuel injector is positioned in the combustion chamber 10 and is connected to the outlet of the first cooling channel 4. The closed cooling circulation system belongs to a liquid metal flowing cooling side, and important parts are connected through a pipeline. The second cooling channel 7 is located on the outer side wall face of the combustion chamber and the tail nozzle, the electromagnetic pump is connected between the outlet of the heat exchanger and the second cooling channel 7, and the heat exchanger 3 is connected between the outlet of the second cooling channel 7 and the electromagnetic pump 6.
The specific principles of the embodiment are illustrated in connection with fig. 2 as follows: 1) open fuel cooling cycle side. Fuel oil is injected into the combustion chamber 10 for combustion after passing through an open cooling cycle from the fuel tank 1, wherein a cold source in the system is the fuel oil carried in the fuel tank 1, and a heat source is a heat load in the first cooling channel 4; wherein, the fuel pump 2 is positioned behind the fuel tank 1 and provides adjustable flow for the heat exchanger 3 and the first cooling channel 4; the fuel is firstly injected into a heat exchanger 3 to exchange heat with high-temperature liquid metal, the temperature of the fuel is raised to finish primary regeneration waste heat utilization, the fuel enters a first cooling channel 4 to absorb waste heat to finish the second-step regeneration utilization, and the atomized fuel is injected into a combustion chamber 10 to be combusted through a fuel injector 5 to finish the side-open cooling circulation of the fuel; 2) closed cooling cycle side. In the circulation, a cold source is low-temperature liquid metal, a heat source is a heat load in a cooling channel 7, and the liquid metal is a heat-carrying circulating working medium; the low-temperature liquid metal passes through the electromagnetic pump 6 and then is injected into the second cooling channel 7 with high heat load on the wall surface to absorb waste heat in the combustion chamber 10, the liquid metal with temperature rise enters the heat exchanger 3 to exchange heat with fuel oil, heat is transferred to the fuel oil to achieve the purpose of temperature reduction, and the liquid metal is injected into the second cooling channel 7 again through the electromagnetic pump 6 to complete closed cooling circulation.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (5)
1. A combined scramjet engine cooling circulation system comprises a cooling channel, wherein the cooling channel is positioned in an annular cavity between the inner wall surface and the outer wall surface of an engine outer shell; the method is characterized in that: the fuel injection device also comprises a fuel tank, a fuel pump, a heat exchanger, a fuel injector and an electromagnetic pump;
an annular partition plate is arranged in the cooling channel along the radial direction, and the cooling channel is divided into a first cooling channel and a second cooling channel which are mutually independent; the cooling channel in the annular cavity at the position opposite to the air inlet channel and the isolation section of the scramjet engine is a first cooling channel, and the cooling channel in the annular cavity at the position opposite to the combustion chamber and the tail nozzle of the scramjet engine is a second cooling channel;
the fuel tank, the fuel pump, the heat exchanger, the first cooling channel and the fuel injector are sequentially connected through pipelines to form an open cooling circulation system, and a working medium of the open cooling circulation system is kerosene; the electromagnetic pump, the second cooling channel and the heat exchanger are sequentially connected through pipelines to form a closed cooling circulation system, and the circulating working medium in the closed cooling circulation system is liquid metal.
2. The combined scramjet engine cooling cycle system of claim 1, wherein: the liquid metal is one or a combination of more of lead, sodium, lithium, cesium, rubidium, sodium-potassium alloy, lead-bismuth alloy, lithium-lead alloy and indium-grafted alloy.
3. The combined scramjet engine cooling cycle system of claim 1, wherein: the flow of the liquid metal can be automatically controlled by an electromagnetic pump, so that the temperature of the cooled wall surface is far lower than the temperature limit of the wall surface material of the combustion chamber.
4. The combined scramjet engine cooling cycle system of claim 1, wherein: the annular partition plate is located at a corresponding position between the isolation section and the combustion chamber of the scramjet engine.
5. The combined scramjet engine cooling cycle system of claim 1, wherein: the inner wall surface of the first cooling channel is provided with a through hole which is used as an outlet of the first cooling channel and is in sealing connection with a pipeline connected with a fuel injector; and the outer wall surface of the second cooling channel is provided with a through hole which is used as an inlet of the second cooling channel and is connected with a pipeline connected with the electromagnetic pump in a sealing way.
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| CN202011332119.0A CN112431675B (en) | 2020-11-24 | 2020-11-24 | Combined scramjet engine cooling circulation system |
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| CN202011332119.0A CN112431675B (en) | 2020-11-24 | 2020-11-24 | Combined scramjet engine cooling circulation system |
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| CN113027538B (en) * | 2021-03-24 | 2022-06-28 | 北京航空航天大学 | Cooling device for aeroengine turbine guider blade |
| CN113864061B (en) * | 2021-09-03 | 2023-07-25 | 清华大学 | Solid ramjet engine wall cooling system and method |
| CN113864062B (en) * | 2021-09-03 | 2022-09-13 | 清华大学 | Solid ramjet wall surface cooling system and method with ejector |
| CN113803190B (en) * | 2021-09-26 | 2022-08-26 | 宁波天擎航天科技有限公司 | Solid fuel ramjet engine |
| CN114109651B (en) * | 2021-11-09 | 2023-05-05 | 宁波天擎航天科技有限公司 | Solid fuel rocket combined ramjet engine |
| CN114412658B (en) * | 2021-12-28 | 2023-08-15 | 北京动力机械研究所 | Ramjet engine cooled by carbon dioxide |
| CN114294679B (en) * | 2022-01-06 | 2022-09-16 | 中南大学 | Compound thermal protection concave cavity combustion chamber |
| CN114412644A (en) * | 2022-01-14 | 2022-04-29 | 北京空天技术研究所 | Liquid metal loop-based hydrocarbon fuel engine cooling method and system |
| CN114838385B (en) * | 2022-03-21 | 2023-09-19 | 西安航天动力研究所 | Self-diverting composite cooling combustion chamber |
| CN114877376B (en) * | 2022-06-02 | 2024-05-24 | 清航空天(北京)科技有限公司 | Dual-channel detonation combustion chamber |
| CN114877377B (en) * | 2022-06-02 | 2024-05-14 | 清航空天(北京)科技有限公司 | Outer ring detonation combustor |
| CN114877378A (en) * | 2022-06-02 | 2022-08-09 | 清航空天(北京)科技有限公司 | Inner ring detonation combustion chamber |
| CN115807711B (en) * | 2022-11-23 | 2024-06-04 | 西北工业大学 | Wall structure of scramjet engine capable of inhibiting heat transfer deterioration and inhibiting method |
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