CN113944568A - Powder fuel support plate ejection rocket-based combined cycle engine based on HAN monopropellant - Google Patents
Powder fuel support plate ejection rocket-based combined cycle engine based on HAN monopropellant Download PDFInfo
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- CN113944568A CN113944568A CN202111190960.5A CN202111190960A CN113944568A CN 113944568 A CN113944568 A CN 113944568A CN 202111190960 A CN202111190960 A CN 202111190960A CN 113944568 A CN113944568 A CN 113944568A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/26—Burning control
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to a supporting plate ejection rocket base combined cycle power engine based on monopropellant, which comprises an air inlet, a central supporting plate monopropellant rocket, a powder fuel supply system, a hydroxylamine nitrate base propellant supply system, a high-pressure air source, a combustion chamber and a spray pipe. The hydroxylamine nitrate based mono-propellant which has good normal-temperature storage performance and can be quickly catalytically started at normal temperature is used as the propellant of the support plate rocket in the engine, the structure of the support plate rocket system is simplified, and the reliability of the engine is improved; the aluminum powder is adopted to replace the traditional hydrocarbon fuel, the density specific impulse of the engine is improved, the fuel dissociation phenomenon under the scramjet mode is overcome, and the performance of the engine is maintained. The engine realizes mode conversion in the flight process by adjusting the flow of hydroxylamine nitrate based propellant.
Description
Technical Field
The invention belongs to the technical field of aerospace power, and relates to a powder fuel support plate ejection rocket-based combined cycle engine based on HAN monopropellant.
Background
The working process of the rocket-based combined cycle power system comprises four modes, namely an injection mode, a sub-combustion mode, a super-combustion mode and a rocket mode, and the respective advantages of the rocket engine and the ramjet can be fully exerted by adjusting the working mode of the engine, so that the aircraft is always in the optimal thermodynamic cycle state under different flight parameters, and the rocket-based combined cycle power system has high specific impulse and high thrust-weight ratio.
The rocket-based combined cycle power system realizes the interconversion between different modes mainly by controlling the ejection rocket oxygen-fuel ratio in the working process, and the current propulsion system is mainly based on aviation kerosene and liquid oxygen systems (Zhanqian, etc., rocket propulsion 2014,40(5): 1-7). Because the boiling point temperature of oxygen is very low, the oxygen can be heated and evaporated in the working process of the aircraft, and the oxygen is difficult to store for a long time. When the low-temperature liquid oxygen is evaporated to a certain degree, the pressure in the storage tank is increased, the safety of the storage tank is threatened greatly (Chengjie and the like, low-temperature engineering, 2012, (06):46-50), and the reliability of the aircraft is further reduced. When the flight speed of the aircraft is more than 7Ma, the aircraft is influenced by the total temperature of incoming flow, so that the hydrocarbon fuel is subjected to irreversible dissociation, and the fuel utilization rate is reduced (Chen et al, propulsion technology, 2013,34(10): 1345-; in addition, the high total temperature of the incoming flow can also raise the temperature of the combustion chamber of the engine to be higher than the adiabatic combustion temperature of hydrocarbon fuel, so that the ram air flow cannot expand continuously to work, and the performance of the engine is reduced.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a novel power combination mode with excellent performance, simple structure and high reliability for a rocket-based combined cycle power system.
In order to solve the problem that the performance of an engine is reduced due to the dissociation of a rocket-based combined cycle power system in a scramjet mode fuel, the invention provides a powdery fuel support plate ejection rocket-based combined cycle engine based on hydroxylamino nitrate (HAN) monopropellant, and the HAN monopropellant and aluminum powder are respectively used as a fuel and an oxidant in the power system, so that the efficient application of the powdery fuel in the rocket-based combined cycle power system is realized.
The idea of the invention is as follows: aluminum powder and hydroxylamine nitrate based single-component propellant are used as fuel and oxidant of the rocket based combined cycle engine, and the propellant can be stably stored at normal temperature. Compared with hydrocarbon fuel, the aluminum powder is used as the fuel, most of combustion products of the aluminum powder are mainly condensed-phase aluminum oxide, the structure is stable, the dissociation effect cannot occur under the high-temperature condition, the stable combustion and heat release of the fuel can be guaranteed to be maintained under the full-mode state, the volume heat value of the aluminum powder is far higher than that of the traditional hydrocarbon fuel, the density specific impulse of an engine can be obviously improved, in addition, the adiabatic combustion temperature of the aluminum powder is higher than that of the hydrocarbon fuel under the same equivalence ratio, and the influence caused by the high incoming flow total temperature can be overcome. The hydroxylamine nitrate based monopropellant can realize catalytic ignition in a catalyst bed, and the propellant can realize stable decomposition and heat release of the propellant at normal temperature, so that an engine does not need to carry an additional ignition system. The temperature of decomposed fuel gas of the hydroxylamine nitrate propellant can reach more than about 1500K, and the hydroxylamine nitrate propellant contains a large amount of water vapor, nitrogen dioxide and other oxidizing atmospheres required by combustion of aluminum powder, so that a high-temperature oxidizing agent is provided for the combustion of the aluminum powder, and the rapid ignition and the efficient combustion of the aluminum powder in high-speed airflow are promoted. Under the injection mode, the flow rate of the engine fuel and the oxidant is determined according to the chemical reaction equivalent ratio of oxidizing atmosphere in the complete decomposition product of the aluminum powder and the HAN-based propellant; in the secondary combustion and super combustion stamping modes, aluminum powder fuel is mainly used, and a small amount of hydroxylamine nitrate propellant is supplied to pre-combust with the aluminum powder, so that the combustion efficiency of the fuel in a combustion chamber is improved; in a pure rocket mode, an aluminum powder fuel supply system is closed, and a hydroxylamine nitrate-based single-component rocket engine is used for providing power for the aircraft. The hydroxylamine nitrate based propellant can be used as an oxidizer and an aluminum powder ignition heat source, can also be used as an attitude control power propellant of an aircraft, can finish rocket modes, oxidizers, fuel ignition heat sources and attitude control power of the aircraft by using a single propellant, can greatly reduce the passive quality of an engine, and improves the reliability.
The invention is realized by the following technical scheme:
a powder fuel support plate ejection rocket-based combined cycle engine based on an HAN monopropellant is characterized in that the combined cycle engine consists of an air inlet 1, a center support plate monopropellant 2, a powder fuel supply system 3, a hydroxylamine nitrate-based propellant supply system 4, a combustion chamber 5, a spray pipe 6 and a high-pressure air source 7;
the central support plate single-component rocket 2 comprises a propellant inlet 8, a capillary 9, a front bed 10, a rear bed 11 and a convergent nozzle 12 which are sequentially arranged from the front end to the back end; the powder fuel supply system 3 comprises a driving cavity 14, a piston 15, a powder storage box 16, a fluidizing cavity 17 and a pressure reduction element 18 for controlling the high-pressure gas source which are arranged in sequence from the inlet of the high-pressure gas source, and a powder switch valve 19 is arranged at the outlet of the fluidizing cavity;
an air inlet 1 is positioned at the front end of the engine and leads to a central support plate single-component rocket 2, one path of the high-pressure air source 7 is connected with an inlet of a hydroxylamine nitrate based propellant supply system 4, an outlet of the hydroxylamine nitrate based propellant supply system 4 is connected with a propellant inlet 8 of the central support plate single-component rocket 2, and a convergent nozzle 12 of the central support plate single-component rocket is communicated with a combustion chamber 5; the other path of the high-pressure air source 7 is connected with a driving cavity 14 of the powder fuel supply system 3 through an electromagnetic valve 13, and the powder switch valve 19 is connected with the combustion chamber 5; a lance 6 is located downstream of the combustion chamber 5.
Advantageous effects
The structure of the engine is suitable for using hydroxylamine nitrate as a propellant and using aluminum powder as a fuel. The device can be started by catalytic ignition at normal temperature without carrying an ignition component, improves the reliability of the engine, and can be used as an attitude and orbit control power system of an aircraft to reduce the passive quality of the aircraft; meanwhile, the dissociation of the traditional hydrocarbon fuel in the scramjet mode can be effectively inhibited, and the density specific impulse of the engine is improved.
Drawings
FIG. 1 is a schematic diagram of a powdered fuel plate ejector rocket based combined cycle engine based on hydroxylamino nitrate (HAN) monopropellant.
Wherein, 1: an air inlet passage, 2: central plate unit rocket, 3: pulverized fuel supply system, 4: hydroxylamine nitrate-based propellant supply system, 5: combustion chamber, 6: spray pipe, 7: and (4) a high-pressure gas source.
Fig. 2 is a schematic structural view of a central plate monopropellant rocket.
Wherein, 8: propellant inlet, 9: capillary, 10: front bed, 11: back bed, 12: a convergent nozzle.
Fig. 3 is a schematic view of the powder supply system.
Wherein, 14: drive chamber, 15: piston, 16) powder reservoir, 17: fluidizing chamber, 18: pressure drop element, 19: powder switch valve.
FIG. 4(a) is engine performance in the super-combustion mode of the Al powder fuel system,
FIG. 4(b) is engine performance in the scramjet mode of the RP-1 kerosene fuel system.
Detailed Description
The invention is further illustrated by the following description and examples and the accompanying drawings.
A powder fuel supported ejector rocket based combined cycle engine based on HAN monopropellant is shown in figures 1, 2 and 3.
Ram air enters a combustion chamber 5 from an air inlet channel 1 through channels on two sides of a central support plate single-component rocket 2; the engine oxidant is extruded and conveyed to a propellant inlet 8 of the central support plate single-component rocket 2 by a hydroxylamine nitrate based propellant supply system 4 by a high-pressure gas source 7, the propellant enters a catalytic bed through a capillary 9, contacts with a propellant decomposition catalyst in a front bed 10 and a rear bed 11 and undergoes decomposition reaction to generate oxidizing atmospheres such as high-temperature steam, carbon dioxide, nitric oxide and the like, and is discharged into a combustion chamber through an engine convergent nozzle 12; the fuel aluminum powder in the engine is conveyed to a combustion chamber 5 in a fluidized mode through a powder supply system 3 by using a high-pressure air source 7, the powder is conveyed by adopting an air pressure driving piston type powder supply scheme, firstly, the high-pressure air source flows into a driving cavity 14 through an electromagnetic valve 13 to drive a piston 15 to move forwards, the aluminum powder in a powder fuel storage tank 16 is extruded to flow 17 into a fluidized cavity, meanwhile, the fluidized gas enters the fluidized cavity 17 through a pressure drop element 18, the aluminum powder in the coiled fluidized cavity 17 enters the combustion chamber 5 through a powder switch valve 19, and the aluminum powder and a combustion product of a central support plate single-component rocket 2 are mixed and precombusted near an outlet of an engine convergent nozzle 12. The oxygen-fuel ratio of the engine can be accurately controlled by adjusting the flow of the HAN-based single-component propellant; the on-off of the aluminum powder fuel supply can be realized by controlling the powder supply switch valve 19 and the switch of the driving gas and the fluidizing gas, and the conversion of the engine under different modes can be realized by the adjustment.
Examples
In the starting process of the aircraft, the engine is supplied in an injection state according to the equivalent ratio of aluminum powder to a hydroxylamine nitrate propellant complete decomposition product, the HAN-based single-component rocket engine is started by catalysis, and the stable work of the HAN-based single-component rocket engine can be realized by directly injecting the propellant into a front bed and a rear bed. Along with the increase of the speed of an aircraft, when the flying speed reaches 2Ma, the engine enters a sub-combustion ram mode, the propellant flow of the HAN-based single-component rocket engine starts to be gradually reduced, when the pressure of a rear bed in the single-component rocket engine is lower than the ambient pressure, the single-component rocket engine is shut down, and aluminum powder and ram air are combusted in a combustion chamber. When the flying speed is higher than 5Ma, the engine enters a scramjet mode, the aircraft enters a near space, the HAN-based single-component rocket engine restarts to work, and the flow of the hydroxylamine nitrate propellant is 10% of the flow of the aluminum powder. In the stamping mode, the ratio of the aluminum powder flow to the air flow is always constant at 1: 6. And when the aircraft enters the track, closing the aluminum powder supply system, and using the HAN-based single-component rocket engine as the power of the aircraft.
In order to verify the performance advantages of the invention, thermodynamic calculation is carried out on the engine performance under the conditions of the flying speed of 8Ma and the flying height of 30km, and the density specific impulse and the combustion chamber adiabatic temperature variation with the combustion equivalence ratio of the engine taking the aluminum powder as the fuel and the common engine taking the kerosene (RP-1) as the fuel are obtained respectively, as shown in FIG. 4(a) and FIG. 4 (b). As can be seen from the figure, the engine can effectively improve the density specific impulse of the rocket-based combined cycle engine, and simultaneously can improve the adiabatic combustion temperature in the combustion chamber of the engine and improve the fuel utilization rate in the scramjet mode. Compared with a traditional rocket-based combined cycle power system of a hydrocarbon fuel and liquid oxygen system, the power system provided by the invention can reduce the carrying of a low-temperature liquid oxygen storage tank and an injection rocket ignition system, reduce the passive mass of an engine and improve the reliability in actual use.
Claims (1)
1. A powder fuel support plate ejection rocket-based combined cycle engine based on an HAN monopropellant is characterized by comprising an air inlet (1), a central support plate monopropellant rocket (2), a powder fuel supply system (3), a hydroxylamine nitrate-based propellant supply system (4), a combustion chamber (5), a spray pipe (6) and a high-pressure air source (7);
the central support plate single-component rocket (2) comprises a propellant inlet (8), a capillary tube (9), a front bed (10), a rear bed (11) and a convergent nozzle (12) which are sequentially arranged from the front end to the back end; the powder fuel supply system (3) comprises a driving cavity (14), a piston (15), a powder storage box (16), a fluidizing cavity (17) and a pressure reduction element (18) for controlling a high-pressure gas source, which are sequentially arranged from an inlet of the high-pressure gas source, wherein a powder switch valve (19) is arranged at an outlet of the fluidizing cavity;
an air inlet channel (1) is positioned at the front end of an engine and communicated with a center support plate single-component rocket (2), one path of a high-pressure air source (7) is connected with an inlet of a hydroxylamine nitrate-based propellant supply system (4), an outlet of the hydroxylamine nitrate-based propellant supply system (4) is connected with a propellant inlet (8) of the center support plate single-component rocket (2), and a convergent nozzle (12) of the center support plate single-component rocket is communicated with a combustion chamber (5); the other path of the high-pressure air source (7) is connected with a driving cavity (14) of the powder fuel supply system (3) through an electromagnetic valve (13), and the powder switch valve (19) is connected with the combustion chamber (5); a lance (6) is located downstream of the combustion chamber (5).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111190960.5A CN113944568B (en) | 2021-10-13 | 2021-10-13 | HAN unit propellant-based powder fuel support plate rocket-based combined cycle engine |
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| CN202111190960.5A CN113944568B (en) | 2021-10-13 | 2021-10-13 | HAN unit propellant-based powder fuel support plate rocket-based combined cycle engine |
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| CN113944568B CN113944568B (en) | 2023-09-05 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114837849A (en) * | 2022-05-10 | 2022-08-02 | 南京航空航天大学 | Powder-liquid stamping combined engine and control method |
| IL292537B1 (en) * | 2022-04-26 | 2023-10-01 | Powder Fuels Ltd | Rocket Motor Using Powder Monopropellant |
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2021
- 2021-10-13 CN CN202111190960.5A patent/CN113944568B/en active Active
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IL292537B1 (en) * | 2022-04-26 | 2023-10-01 | Powder Fuels Ltd | Rocket Motor Using Powder Monopropellant |
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| CN114837849A (en) * | 2022-05-10 | 2022-08-02 | 南京航空航天大学 | Powder-liquid stamping combined engine and control method |
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| CN113944568B (en) | 2023-09-05 |
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