CN111594343B - Method for rapidly recovering restart of air inlet passage of rocket-based combined cycle engine - Google Patents
Method for rapidly recovering restart of air inlet passage of rocket-based combined cycle engine Download PDFInfo
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- CN111594343B CN111594343B CN202010367480.0A CN202010367480A CN111594343B CN 111594343 B CN111594343 B CN 111594343B CN 202010367480 A CN202010367480 A CN 202010367480A CN 111594343 B CN111594343 B CN 111594343B
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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
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/18—Composite ram-jet/rocket engines
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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
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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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
- F02C7/26—Starting; Ignition
- F02C7/262—Restarting after flame-out
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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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
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- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
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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)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
Abstract
The invention provides a method for rapidly recovering restarting of an air inlet passage of a rocket-based combined cycle engine, which comprises the following steps: the device comprises an air inlet channel, an isolation section, a combustion chamber and a built-in rocket, wherein the initial mass flow rate of the built-in rocket is 0.3kg/s, and the outlet back pressure of the combustion chamber is 0.15MPa; the mass flow rate of the built-in rocket is increased to 0.4kg/s from the initial mass flow rate, the outlet back pressure of the combustion chamber is increased to 0.2MPa, and the air inlet channel is in a non-starting state; the mass flow rate of the built-in rocket is reduced to 0.2kg/s from 0.4kg/s, the back pressure of the outlet of the combustion chamber is reduced to 0.1MPa, and the air inlet passage is restored to the starting state from the non-starting state; after the air inlet is recovered to the starting state, the mass flow rate of the built-in rocket is recovered to 0.3kg/s and the outlet back pressure of the combustion chamber is recovered to 0.15MPa, so that the air inlet is controlled to be recovered to the starting state from the non-starting state by reducing the fuel quantity of the built-in rocket, the spanwise expansion radius of the jet flow of the built-in rocket is reduced, the pressure of the combustion chamber is reduced, the air inlet is controlled to be rapidly recovered to the starting state, and the self-starting capability is improved.
Description
Technical Field
The invention relates to the field of air-breathing combined propulsion systems, in particular to a rocket-based combined cycle engine.
Background
A Rocket-Based Combined Cycle (RBCC) engine organically integrates a Rocket engine with a high thrust-weight ratio and an air-breathing ramjet engine with a high specific impulse into the same runner, can be compatible with injection, sub-combustion, super-combustion and pure Rocket modes, and realizes high-performance work in a wide speed range and a large airspace. When designing an RBCC power system, researchers expect that the Mach number corresponding to an air inlet starting point and an engine injection/sub-combustion mode transition point is as low as possible, so that wide compatibility is obtained, and the overall performance of the engine is improved. When the air inlet is just started, the back pressure resistance of the air inlet is weak, in addition, the engine needs to finish mode transition as soon as possible, the working parameters and the state change violently, and the air inlet is easy to fall into an un-starting state due to strong disturbance of jet flow of a built-in rocket, pressure of a combustion chamber and the like. The normal work of the RBCC engine in a stamping mode can be seriously influenced by the fact that the air inlet channel is not started, so that the performance of the engine is greatly reduced, and even the flight mission fails. Aiming at the extreme condition that the air inlet is not started due to some strong disturbance, a reasonable emergency regulation and control scheme is formulated, the starting of the air inlet and the normal and stable operation of the engine are recovered as soon as possible, and the method has very important influence on the completion of the whole flight task. Because the RBCC air inlet channel is closely coupled with the built-in rocket, how to change the working states of the air inlet channel and the whole RBCC engine by utilizing a method for adjusting the state of the built-in rocket so as to realize the restart of the air inlet channel is a key technology for ensuring the normal operation of the RBCC engine.
At present, research is only carried out on a restarting method of a conventional supersonic air inlet, and because a conventional ramjet is not influenced by a built-in rocket, the restarting control method mainly reduces the pressure of a combustion chamber by reducing the injection of the combustion chamber or realizes the restarting of the air inlet by adjusting the posture of an aircraft. However, considering the important influence of the built-in rocket in the RBCC engine on the performance of the whole engine state, the adjustment capability of the existing method for adjusting only by reducing the pressure of the combustion chamber is limited, so that a method for recovering the restart of the air inlet as soon as possible by adjusting the state of the built-in rocket can be found, and the method is matched with the variable geometry air inlet to effectively improve the regulation capability of the restart of the air inlet, which is a technical problem to be solved by those skilled in the art.
Disclosure of Invention
To achieve the above object, the present invention provides a method for rapidly recovering an intake port restart of a rocket-based combined cycle engine, which is applied to a rocket-based combined engine, the rocket-based combined engine including: intake duct, isolation section, combustion chamber and built-in rocket, wherein:
the air inlet channel, the isolation section and the combustion chamber are sequentially connected, and air flow flows in from the air inlet channel, passes through the isolation section, works in the combustion chamber and then is discharged outwards from the tail end of the combustion chamber;
the internal rocket is communicated with the combustion chamber and is provided with combustion energy by fuel contained in the combustion chamber;
configuring the initial mass flow rate of the built-in rocket to be 0.3kg/s and the outlet back pressure of the combustion chamber to be 0.15MPa;
raising the mass flow rate of the built-in rocket to 0.4kg/s from the initial mass flow rate and raising the outlet back pressure of the combustion chamber to 0.2MPa, wherein the air inlet channel is in a non-starting state;
reducing the mass flow rate of the built-in rocket from 0.4kg/s to 0.2kg/s and reducing the outlet back pressure of the combustion chamber to 0.1MPa, wherein the air inlet passage is recovered from the non-starting state to the starting state;
after the air inlet channel is restarted, the mass flow rate of the built-in rocket is recovered to 0.3kg/s and the outlet back pressure of the combustion chamber is recovered to 0.15MPa.
Furthermore, the air inlet channel is a mixed pressure air inlet channel.
Further, the built-in rocket is positioned at the outlet of the isolation section and is arranged on the side surface of the isolation section.
Further, the built-in rocket is a liquid fuel rocket.
Compared with the prior art, the invention provides a method for rapidly recovering the restart of an air inlet passage of a rocket-based combined cycle engine, which is applied to the rocket-based combined engine and comprises the following steps: the device comprises an air inlet channel, an isolation section, a combustion chamber and a built-in rocket, wherein the initial mass flow rate of the built-in rocket is 0.3kg/s, and the outlet back pressure of the combustion chamber is 0.15MPa; the mass flow rate of the built-in rocket is increased to 0.4kg/s from the initial mass flow rate, the outlet back pressure of the combustion chamber is increased to 0.2MPa, and the air inlet channel is controlled not to be started; the mass flow rate of the built-in rocket is reduced to 0.2kg/s from 0.4kg/s, the outlet back pressure of the combustion chamber is reduced to 0.1MPa, and the air inlet passage is controlled to be recovered to a starting state from non-starting. After the air inlet channel is started, the mass flow rate of the built-in rocket is recovered to 0.3kg/s from 0.2kg/s, the pressure of a combustion chamber is recovered to 0.15MPa from 0.1MPa, and the chamber pressure of the built-in rocket is reduced by reducing the fuel quantity of the built-in rocket, so that the spanwise expansion radius of the jet flow of the built-in rocket is reduced, the pressure of the RBCC combustion chamber is reduced, and the air inlet channel is quickly recovered to the starting state. After the air inlet channel is started, the high-chamber pressure state of the rocket is quickly recovered, and at the moment, the air inlet channel can work normally.
Drawings
FIG. 1 is a schematic diagram of a rocket-based compound engine in an embodiment of the present invention;
FIG. 2 is another schematic view of a rocket-based compound engine in accordance with an embodiment of the present invention;
FIG. 3 is a schematic diagram showing the relationship between the mass flow coefficient and the state of a built-in rocket in the process from the non-starting state to the starting state of an air inlet passage;
FIG. 4 is a schematic diagram showing the relation between the total pressure recovery coefficient and the built-in rocket state in the process from the non-starting state to the starting state of the air inlet passage.
Detailed Description
The invention is described in further detail below with reference to the drawings and the detailed description.
Referring to fig. 1-4, the present invention provides a method for rapidly recovering an inlet port restart of a rocket-based combined cycle engine, which is applied to a rocket-based combined engine, and the rocket-based combined engine includes: the device comprises an air inlet channel 1, an isolation section 2, a combustion chamber 3 and a built-in rocket 4.
The air inlet 1, the isolation section 2 and the combustion chamber 3 are sequentially connected, air flow flows in from the air inlet 1, passes through the isolation section 2, works in the combustion chamber 3 and then is discharged outwards from the tail end of the combustion chamber 3; the built-in rocket 4 is positioned at the outlet of the isolation section 2 and is arranged at the side surface of the isolation section 2, and the built-in rocket 4 is communicated with the combustion chamber 3 and provides combustion energy for the built-in rocket 4 by fuel contained in the combustion chamber 3. The static pressure of the rocket-based combined engine is 32000-38000Pa. The air inlet 1 is a mixed pressure type air inlet 1. The built-in rocket 4 is a liquid fuel rocket.
The divergence angle of the combustion chamber 3 is 0 °, wherein the divergence angle is an angle between a tangent to the inner wall surface of the combustion chamber 3 and an axis of the combustion chamber 3, that is, an angle between a tangent to the inner wall surface of the combustion chamber 3 and the axis of the combustion chamber 3 is 0 °.
The initial mass flow rate of the built-in rocket 4 is set to be 0.3kg/s and the outlet back pressure of the combustion chamber 3 is set to be 0.15MPa, the mass flow rate of the built-in rocket 4 is increased to be 0.4kg/s from the initial mass flow rate, the outlet back pressure of the combustion chamber 3 is increased to be 0.2MPa, and the air inlet 1 is controlled to be in a non-starting state.
Because the lag phenomenon exists in the working process of the air inlet 1, when the built-in rocket 4 is recovered to the initial working state, namely the initial mass flow rate is 0.3kg/s and the outlet back pressure of the combustion chamber 3 is 0.15MPa, the air inlet 1 is still in the non-starting state.
When the built-in rocket 4 works, the incoming flow sucked by the air inlet 1 is further compressed by the rocket jet flow, so that the actual internal contraction ratio of the air inlet 1 is larger than the internal contraction ratio of the air inlet 1 when the rocket jet flow radius is large to a certain degree, and the large internal contraction ratio of the air inlet 1 is not beneficial to the starting of the air inlet 1. The internal contraction ratio is the ratio of the sectional area at the inlet of the air inlet channel 1 to the minimum aerodynamic sectional area in the channel.
The mass flow rate of the built-in rocket 4 is reduced to 0.2kg/s from 0.4kg/s, the outlet back pressure of the combustion chamber 3 is reduced to 0.1MPa, and the air inlet passage 1 is controlled to be recovered to a starting state from a non-starting state.
In the present embodiment, the principle of enabling the air intake duct 1 to restart is to change the rocket jet radius of the internal rocket 4 by changing the operating state of the internal rocket 4, specifically, recovering the mass flow rate of the internal rocket 4, so as to reduce the actual equivalent internal contraction ratio of the air intake duct 1, and at the same time, the pressure in the combustion chamber 3 is correspondingly reduced due to the reduction of the fuel flow, so that a rapid restart can be achieved. After restarting, the rocket and the injection regulation of the combustion chamber 3 are gradually recovered, and then the original normal working state is recovered, and in the process, the air inlet 1 keeps the starting state.
In this example, the mass flow coefficient and the total pressure recovery coefficient may be used as a basis for determining whether the intake duct 1 is started. The mass flow coefficient is the ratio of the mass flow rate of the air actually entering the air inlet channel 1 to the mass flow rate of the air in the area with the same size of the cross section area of the inlet of the air inlet channel 1; the total pressure recovery coefficient is the ratio of the total pressure of the air flow passing through the outlet of the air inlet channel 1 to the total pressure of the free incoming flow.
As shown in FIG. 3, when the flow rate of the rocket launcher 4 is increased from 0.3kg/s to 0.4kg/s and the back pressure of the combustion chamber 3 is increased from 0.15MPa to 0.20MPa during operation, the mass flow coefficient (a) and the total pressure recovery coefficient (b) are both significantly reduced, i.e. the air inlet 1 is changed from start to no start. After the built-in rocket 4 is restored to the initial state (mass flow rate 0.3kg/s, back pressure of the combustion chamber 3 0.15 MPa), the intake duct 1 cannot be restarted from the graph of the mass flow rate coefficient and the total pressure recovery coefficient. In order to restart the intake port 1, the mass flow rate is continuously reduced by reducing the fuel and oxidant supply of the internal rocket 4, and it is found that when the mass flow rate is reduced to 0.2kg/s and the back pressure of the combustion chamber 3 is 0.1MPa, the mass flow coefficient and the total pressure recovery coefficient are both restored to be consistent with the normal operating state, and the intake port 1 is restarted. Or the built-in rocket 4 can be directly and completely closed, and the air inlet 1 can be restored to the starting state. No matter the mass flow of the built-in rocket 4 is reduced to 0.2kg/s, the back pressure of the combustion chamber 3 is 0.1MPa until the starting of the air inlet channel 1 is recovered, or the built-in rocket 4 is directly closed to the starting of the air inlet channel 1, the built-in rocket 4 can be adjusted back to the state of the mass flow rate of 0.3kg/s and the back pressure of the combustion chamber 3 of 0.15MPa after the air inlet channel 1 is started, and at the moment, the air inlet channel 1 still keeps the starting state.
In summary, the present invention provides a method for rapidly resuming the restart of an intake port of a rocket-based combined cycle engine, which is applied to a rocket-based combined engine, and the rocket-based combined engine includes: the device comprises an air inlet channel, an isolation section, a combustion chamber and a built-in rocket, wherein the initial mass flow rate of the built-in rocket is 0.3kg/s, and the outlet back pressure of the combustion chamber is 0.15MPa; the mass flow rate of the built-in rocket is increased to 0.4kg/s from the initial mass flow rate and the outlet back pressure of the combustion chamber is increased to 0.2MPa so as to control the air inlet channel to be not started; the mass flow rate of the built-in rocket is reduced to 0.2kg/s from 0.4kg/s, the outlet back pressure of the combustion chamber is reduced to 0.1MPa, and the air inlet passage is controlled to be recovered to a starting state from non-starting. After the air inlet channel is started, the mass flow rate of the built-in rocket is recovered to 0.3kg/s from 0.2kg/s, the pressure of a combustion chamber is recovered to 0.15MPa from 0.1MPa, and the chamber pressure of the built-in rocket is reduced by reducing the fuel quantity of the built-in rocket, so that the spanwise expansion radius of the jet flow of the built-in rocket is reduced, the pressure of the RBCC combustion chamber is reduced, and the air inlet channel is quickly recovered to the starting state. After the air inlet channel is started, the high-chamber pressure state of the rocket is quickly recovered, and at the moment, the air inlet channel can work normally.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (4)
1. A method for rapidly recovering the restart of an air inlet of a rocket-based combined cycle engine, which is applied to the rocket-based combined engine, is characterized by comprising the following steps: intake duct, isolation section, combustion chamber and built-in rocket, wherein:
the air inlet channel, the isolation section and the combustion chamber are sequentially connected, and air flow flows in from the air inlet channel, passes through the isolation section, works in the combustion chamber and then is discharged outwards from the tail end of the combustion chamber;
the internal rocket is communicated with the combustion chamber and is provided with combustion energy by fuel contained in the combustion chamber;
configuring the initial mass flow rate of the built-in rocket to be 0.3kg/s and the outlet back pressure of the combustion chamber to be 0.15MPa;
raising the mass flow rate of the built-in rocket to 0.4kg/s from the initial mass flow rate and raising the outlet back pressure of the combustion chamber to 0.2MPa, wherein the air inlet channel is in a non-starting state;
reducing the mass flow rate of the built-in rocket from 0.4kg/s to 0.2kg/s and reducing the outlet back pressure of the combustion chamber to 0.1MPa, wherein the air inlet passage is recovered from the non-starting state to the starting state;
after the air inlet channel is restarted, the mass flow rate of the built-in rocket is recovered to 0.3kg/s and the outlet back pressure of the combustion chamber is recovered to 0.15MPa.
2. The method for rapidly resuming rocket based combined cycle engine intake restarting according to claim 1 wherein the intake is a mixed compression intake.
3. A method of rapidly resuming rocket-based combined cycle engine intake port restart of claim 1 wherein said built-in rocket is located at the exit of said isolated section and is located at the side of said isolated section.
4. A method of rapidly resuming rocket-based combined cycle engine intake port restart according to claim 1, wherein the built-in rocket is a liquid fuel rocket.
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| CN202010367480.0A CN111594343B (en) | 2020-05-01 | 2020-05-01 | Method for rapidly recovering restart of air inlet passage of rocket-based combined cycle engine |
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| CN202010367480.0A CN111594343B (en) | 2020-05-01 | 2020-05-01 | Method for rapidly recovering restart of air inlet passage of rocket-based combined cycle engine |
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| CN111594343B true CN111594343B (en) | 2023-03-10 |
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| CN113006967B (en) * | 2021-02-08 | 2022-04-19 | 中国人民解放军国防科技大学 | RBCC inner flow passage combining rocket and front edge sudden-expansion concave cavity |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101143623A (en) * | 2007-09-28 | 2008-03-19 | 大连海事大学 | Suction type rocket combination circulation engine |
| CN104295406A (en) * | 2014-05-26 | 2015-01-21 | 清华大学 | Rocket stamping combination engine with annular injection structure |
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| US20080196414A1 (en) * | 2005-03-22 | 2008-08-21 | Andreadis Dean E | Strut cavity pilot and fuel injector assembly |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101143623A (en) * | 2007-09-28 | 2008-03-19 | 大连海事大学 | Suction type rocket combination circulation engine |
| CN104295406A (en) * | 2014-05-26 | 2015-01-21 | 清华大学 | Rocket stamping combination engine with annular injection structure |
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