CN118188220A - Full flow channel for ejection mode of RBCC engine - Google Patents

Full flow channel for ejection mode of RBCC engine Download PDF

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Publication number
CN118188220A
CN118188220A CN202410384552.0A CN202410384552A CN118188220A CN 118188220 A CN118188220 A CN 118188220A CN 202410384552 A CN202410384552 A CN 202410384552A CN 118188220 A CN118188220 A CN 118188220A
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CN
China
Prior art keywords
rocket
inlet
outlet
combustion chamber
air inlet
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Pending
Application number
CN202410384552.0A
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Chinese (zh)
Inventor
叶进颖
林翔宇
戴淼
秦飞
魏祥庚
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Northwestern Polytechnical University
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Northwestern Polytechnical University
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Filing date
Publication date
Application filed by Northwestern Polytechnical University filed Critical Northwestern Polytechnical University
Priority to CN202410384552.0A priority Critical patent/CN118188220A/en
Publication of CN118188220A publication Critical patent/CN118188220A/en
Pending legal-status Critical Current

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Classifications

    • 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
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • 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
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • 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
    • F02K9/97—Rocket nozzles

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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 discloses a full flow passage for an ejection mode of an RBCC engine, which consists of an air inlet passage, an isolation section, a combustion chamber and a spray pipe which are sequentially communicated from front to back; a fuel support plate is arranged at the position of the isolation section close to the air inlet channel; the communication part of the isolation section and the combustion chamber is provided with a rocket ejector; an external rocket is arranged at the communication part of the combustion chamber and the spray pipe; the invention has higher injection ratio and secondary combustion efficiency while taking multiple modes into consideration, thereby improving the thrust and specific impulse of the engine.

Description

Full flow channel for ejection mode of RBCC engine
Technical Field
The invention belongs to the technical field of rocket-based combined cycle power, and particularly relates to a full flow passage for an ejection mode of a RBCC engine.
Background
Rocket-based combined cycle (RBCC) engines organically combine rocket engines with ramjet engines, wherein rocket engines have a high thrust-to-weight ratio, but carry a large amount of oxidizer so that the specific impact is low; the ramjet engine has a simple structure, can utilize oxygen in the atmosphere, has higher specific impulse performance, but has low engine performance and even can not work normally when flying at a low speed. Therefore, the advantages of the two propulsion modes are fully utilized, so that the engine can work in an optimal mode at different heights and Mach numbers, and the engine has the characteristics of high thrust-weight ratio and high specific impulse. In addition, the RBCC engine can take into account a plurality of working modes, realizes stable transition among the modes, has the working characteristics of autonomous horizontal take-off and landing and wide-area multitasking, and is one of main power for future air-to-day transportation.
The RBCC engine is operated in an ejector mode from zero speed to the stage of starting the air inlet passage. The ejection mode is a key link for determining whether the RBCC engine can be started at zero speed, and mainly comprises the steps of ejecting and sucking ambient air into a combustion chamber through main rocket jet flow, and performing secondary combustion on tissues in the combustion chamber to obtain thrust gain so as to improve the engine performance. Aiming at the characteristics of the RBCC engine with multiple modes, the injection mode needs to be matched with the sub-combustion/super-combustion mode, but the larger air inlet channel contraction ratio and the jet pipe expansion ratio required by the sub-combustion/super-combustion mode and the combustion chamber with pure expansion type can reduce the performance of the injection mode, and the flow channel design of the injection mode is limited, so that the matching principle of the stamping flow channel still needs to be further studied. In addition, the position and mode of injecting secondary fuel can influence the air quantity ejected by the rocket and further influence the thrust and specific flushing performance, so that a proper secondary combustion organization strategy is an important problem of ejection mode design work. Aiming at the two problems, a great deal of research is carried out in the industry. The combination of a large number of previous engine configurations still has a number of problems: the single-stage rocket is adopted to eject and contact with air, so that the air is weak in function, and the air ejecting and sucking capacity of the engine is insufficient; the shrinkage ratio of the air inlet channel is not good when multi-mode is considered, so that the aerodynamic resistance is large and the injection ratio is small; the secondary combustion generates higher combustion chamber pressure, so that the pressure is transmitted forward, and the overflow of the air inlet channel is serious; insufficient mixing of secondary fuel and incoming air results in low secondary combustion efficiency; the channel area of the combustion chamber is too small, the suction effect of rocket jet flow is weakened, and the injection air quantity is reduced; the spray pipe configuration of the fixed structure cannot meet the working requirements of all modes.
Disclosure of Invention
The invention aims to provide a full flow channel for the ejection mode of an RBCC engine, which has higher ejection ratio and secondary combustion efficiency while taking multiple modes into consideration, thereby improving the thrust and specific impulse of the engine.
The invention adopts the following technical scheme: a full flow channel for RBCC engine injection mode comprises an air inlet channel, an isolation section, a combustion chamber and a spray pipe which are communicated from front to back in sequence;
A fuel support plate is arranged at the position of the isolation section close to the air inlet channel;
The communication part of the isolation section and the combustion chamber is provided with a rocket ejector;
An external rocket is arranged at the communication part of the combustion chamber and the spray pipe;
When the Mach number of the incoming flow is 0-1.5, the injection rocket and the external rocket are opened to enable the engine to start at zero speed, and in the process that the Mach number of the incoming flow is continuously increased from 1.5 to 2, the flow of the injection rocket is continuously reduced, the injection quantity of fuel support plate fuel is increased, and the fuel and the incoming flow air are fully mixed in an isolation section and enter a combustion chamber to be ignited and combusted through the injection rocket.
Further, the injection port of the fuel support plate is positioned on the isolation section, and the inlet of the fuel support plate is communicated with an external fuel system.
Further, the expansion ratio of the outlet to the inlet of the isolation section was 1.4.
Further, the expansion ratio of the combustion chamber outlet to inlet was 1.98.
Further, the expansion ratio of the position of the combustion chamber where the rocket is installed to the inlet of the combustion chamber is 1.14.
Further, the air inlet is composed of a first air inlet and a second air inlet which are sequentially communicated, the first air inlet is obliquely upwards and is close to the air inlet of the aircraft, the contraction ratio of the outlet to the inlet is 0.38, the inlet of the second air inlet is communicated with the outlet of the first air inlet, and the contraction ratio of the outlet to the inlet is 0.54.
Further, the spray pipe comprises the fixed casing that is located the upside and the movable shrouding that is located the downside, and fixed casing is "n" shape, and the movable shrouding is located the downside opening part of fixed casing, and with combustion chamber swing joint, the movable shrouding can follow its articulation point and reciprocate, and then changes the exit area of spray pipe to be applicable to different inflow Mach numbers.
Further, the shrinkage ratio of the outlet to the inlet of the spray pipe is 0.75 in the injection mode; the expansion ratio of the nozzle outlet to the nozzle inlet in the sub-combustion/super-combustion mode was 1.17.
The engine structure of the full flow passage comprises a connecting plate, an air inlet shell, an isolation shell, a combustion shell and a spray pipe which are sequentially connected from front to back;
The connecting plate is used for extending into a precursor of the aircraft and is matched with an air inlet groove of the aircraft to form an air inlet channel, and the rear end of the air inlet channel is an air inlet channel;
The fuel support plate is arranged on the isolation shell, the outlet of the fuel support plate is positioned in the inner cavity of the isolation shell, and the inlet of the fuel support plate is close to the air inlet channel;
The combustion shell is provided with a rocket ejector, and an outlet of the rocket ejector is positioned at an inlet of the combustion shell; an external rocket is arranged on the spray pipe, and an outlet of the external rocket is positioned at an inlet of the spray pipe.
Further, the fuel support plates are arranged in two and parallel to each other.
The beneficial effects of the invention are as follows:
the air inlet of the invention consists of two sections of the first air inlet and the second air inlet, the contraction ratio of the outlet and the inlet of the first air inlet is 0.38, so that the incoming air can be better captured, and the injected air quantity is increased; the second air inlet channel contraction ratio is 0.54, so that the incoming air is decelerated and pressurized;
According to the invention, the first air inlet is obliquely upwards arranged, and the upper side inlet is longer than the lower side inlet, so that more air can be captured, and the injected air quantity is increased.
The expansion ratio of the isolation section is 1.40, so that the pre-combustion shock wave string is prevented from moving forward to damage the air inlet channel, and the back pressure forward of the combustion chamber is effectively prevented, so that the air inlet channel overflows; in addition, the incoming air is further decelerated and pressurized;
The secondary fuel is scattered and injected into the flow channel by the fuel support plate, and the total temperature of the incoming flow is low and insufficient to ignite the secondary fuel because the working state of the engine is in an injection mode, so that the secondary fuel and the incoming flow air can be mixed in advance by injecting the secondary fuel into the isolation section, the secondary combustion efficiency is improved, and the length of the engine is shortened;
The expansion ratio of the combustion chamber of the present invention is 1.98, which is to match the sub/super combustion mode; the length of the combustion chamber is properly prolonged, so that the air flow area can be increased, and the rocket can fully exert the ejector suction effect;
According to the invention, the injection rocket is arranged at the position with the expansion ratio of 1.14 in the combustion chamber, the inside of the injection rocket is communicated with a fuel system, the injection rocket outlet is communicated with the inlet of the combustion chamber, and high-temperature and high-pressure fuel gas is injected into the combustion chamber through the injection rocket outlet to perform shearing and entrainment with air in a flow passage, so that the aim of injecting air is fulfilled;
the movable sealing plate of the spray pipe can swing up and down, and in the injection mode, the movable sealing plate is positioned at the upper position to form a shrinkage type spray pipe, and the shrinkage ratio is 0.75; the movable sealing plate is positioned at the lower position during the sub-combustion/super-combustion mode to form an expansion type spray pipe, and the expansion ratio is 1.17;
the external rocket outlet is communicated with the nozzle inlet, so that high-temperature and high-pressure gas generated by the external rocket enters the nozzle through the external rocket outlet to further expand, larger auxiliary thrust can be generated, zero-speed starting of the engine is facilitated, and injection mode performance is improved.
Drawings
FIG. 1 is a front view of a full flow channel of the present invention;
FIG. 2 is a schematic diagram of an engine configuration of the full flow path of the present invention.
Wherein: 1. an air inlet channel; 2. a fuel support plate; 3. an isolation section; 4. ejecting a rocket; 5. a combustion chamber; 6. an external rocket; 7. a spray pipe; 8. a connecting plate; 9. an isolation case; 10. a combustion housing; 11. an air intake housing.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more. "strike" in the present invention is a strike description in the state of fig. 1 according to the present invention.
The invention discloses a full flow passage for an ejection mode of an RBCC engine, which is shown in figure 1 and consists of an air inlet passage 1, an isolation section 3, a combustion chamber 5 and a spray pipe 7 which are sequentially communicated from front to back.
The isolation section 3 is provided with a fuel support plate 2 near the air inlet channel 1; the communication part of the isolation section 3 and the combustion chamber 5 is provided with a rocket injector 4; an external rocket 6 is arranged at the communication part of the combustion chamber 5 and the spray pipe 7; when the Mach number of the incoming flow is 0-1.5, the ejector rocket 4 and the external rocket 6 are both opened to enable the engine to start at zero speed, and in the process that the Mach number of the incoming flow is continuously increased from 1.5 to 2, the flow of the ejector rocket 4 is continuously reduced, the injection quantity of fuel of the fuel support plate 2 is increased, and the fuel and the incoming flow air are fully mixed in the isolation section 3 and enter the combustion chamber 5 to be ignited and combusted through the ejector rocket 4.
The injection port of the fuel support plate 2 is positioned on the isolation section 3, and the inlet of the fuel support plate is communicated with an external fuel system. The expansion ratio of the outlet to the inlet of the isolation section 3 is 1.4. The expansion ratio of the outlet to the inlet of the combustion chamber 5 was 1.98. The expansion ratio of the position of the combustion chamber 5 where the rocket ejector 4 is arranged to the inlet of the combustion chamber 5 is 1.14.
The air inlet channel 1 is composed of a first air inlet channel and a second air inlet channel which are sequentially communicated, wherein the first air inlet channel is obliquely upwards and is close to an air inlet of an aircraft, the contraction ratio of an outlet to the inlet is 0.38, the inlet of the second air inlet channel is communicated with the outlet of the first air inlet channel, and the contraction ratio of the outlet to the inlet is 0.54.
The spray pipe 7 comprises a fixed shell positioned at the upper side and a movable sealing plate positioned at the lower side, wherein the fixed shell is in an n shape, the movable sealing plate is positioned at the lower side opening of the fixed shell and is movably connected with the combustion chamber 5, and the movable sealing plate can move up and down along the movable connecting point of the movable sealing plate so as to change the outlet area of the spray pipe 7, so that the spray pipe is suitable for different incoming flow Mach numbers. The shrinkage ratio of the outlet to the inlet of the spray pipe 7 is 0.75 in the injection mode; the expansion ratio of the outlet to the inlet of the lance 7 in the sub-combustion/super-combustion mode is 1.17.
The invention also discloses a full flow passage for the ejection mode of the RBCC engine, as shown in fig. 2, the engine structure of the full flow passage comprises a connecting plate 8, an air inlet shell 11, an isolation shell 9, a combustion shell 10 and a spray pipe 7 which are sequentially connected from front to back.
The connecting plate 8 is used for extending into a precursor of the aircraft and is matched with an air inlet groove of the aircraft to form an air inlet channel, and the rear end of the air inlet channel is provided with an air inlet channel 1; the isolation shell 9 is provided with a fuel support plate 2, an outlet of the fuel support plate 2 is positioned in the inner cavity of the isolation shell 9, and an inlet of the fuel support plate is close to the air inlet channel 1.
The combustion shell 10 is provided with a rocket ejector 4, and an outlet of the rocket ejector 4 is positioned at an inlet of the combustion shell 10; an external rocket 6 is arranged on the spray pipe 7, and an outlet of the external rocket 6 is positioned at an inlet of the spray pipe 7. The fuel support plates 2 are provided in two and parallel to each other.
The air inlet channel 1 compresses incoming air to enable the incoming air to be subjected to speed reduction and pressurization, and in the injection mode, a low-pressure environment is formed at the outlet of the air inlet channel 1 to inject and suck the incoming air into the combustion chamber 5. The isolation section 3 connects the air inlet channel 1 and the combustion chamber 5 and is mainly responsible for matching the pressure intensity of the two. The combustion chamber 5 is a critical component in the engine that organizes post combustion heat release. The spray pipe 7 mainly expands and accelerates high-temperature high-pressure gas generated in the combustion chamber 5, so that thrust is obtained, and different working modes have different profile requirements. The rocket injector 4 in the runner is responsible for injecting the secondary combustion heat release of the flowing air tissue in the injection mode, improves the back pressure resistance of the engine, plays the roles of ignition and flame stabilization in the sub-combustion mode, and is closed or works at a small flow rate in the super-combustion mode to play the role of on-duty flame.
Under the injection-suction stage, the Mach number of the incoming flow is between 0 and 1.5, the injection rocket 4 and the external rocket 6 are opened, the engine is started at zero speed, and the suction effect of the injection rocket 4 plays a leading role in the injection air flow rate; in the ejection-stamping stage, the flow of the ejection rocket 4 becomes smaller, the external rocket 6 is opened, and in the process, the stamping effect plays a leading role in the air flow entering the combustion chamber 5; in the process of continuously increasing the Mach number of incoming flow from 1.5 to 2, the flow of the rocket 4 is continuously reduced, the injection quantity of fuel of the fuel support plate 2 is increased, the incoming flow pressure and Mach number are lower, the incoming flow temperature is insufficient to ignite secondary fuel because the air inlet channel 1 belongs to an unactuated state, so that the secondary fuel is injected at the inlet of the isolation section 3, the secondary fuel can be mixed with incoming flow air in advance, the mixture is more sufficient, then the secondary fuel enters the combustion chamber 5, the rocket 4 is injected for ignition, the fuel-rich fuel gas and the mixed air flow are fully combusted, the combustion efficiency is greatly improved, the pressure of the combustion chamber 5 is established to be higher, and the higher thrust gain is obtained.
Example 1
For the flow channel of the invention, a ground zero-speed injection test is carried out, and the embodiment adopts the rich-combustion external rocket 6, namely a secondary rocket, to verify the injection and suction effect of jet flow of the injection rocket 4 and the over-expansion flow state of air flow of the spray pipe 7 under the ground zero-speed state.
Through verification, the deviation between the pressure of the external rocket 6 chamber and the design value is 0.4%, and the time of the pressure platform meets the test requirement. Experiments show that in the zero-speed take-off stage, as the external rocket 6 is far away from the air inlet channel 1 and has weak injection and suction capacity on air, in practical application, the external rocket 6 works at a large flow rate and mainly provides thrust required by the flight of an aircraft.
The foregoing is only illustrative of the present invention and is not to be construed as limiting thereof, but rather as various modifications, equivalent arrangements, improvements, etc., within the spirit and principles of the present invention.

Claims (10)

1. The full flow passage for the ejection mode of the RBCC engine is characterized by comprising an air inlet passage (1), an isolation section (3), a combustion chamber (5) and a spray pipe (7) which are sequentially communicated from front to back;
a fuel support plate (2) is arranged at the position, close to the air inlet channel (1), of the isolation section (3);
A rocket ejector (4) is arranged at the communication part of the isolation section (3) and the combustion chamber (5);
an external rocket (6) is arranged at the communication part of the combustion chamber (5) and the spray pipe (7);
When the Mach number of the incoming flow is 0-1.5, the ejector rocket (4) and the external rocket (6) are opened to enable the engine to start at zero speed, the flow of the ejector rocket (4) is continuously reduced in the process that the Mach number of the incoming flow is continuously increased from 1.5 to 2, the fuel injection quantity of the fuel support plate (2) is increased, and the fuel and the incoming flow air are fully mixed in the isolation section (3) and enter the combustion chamber (5) to be ignited and combusted through the ejector rocket (4).
2. A full flow channel for RBCC engine injection modes according to claim 1, characterized in that the injection port of the fuel strip (2) is located on the separation section (3) with its inlet in communication with the external fuel system.
3. A full flow channel for RBCC engine injection modes according to claim 1, wherein the expansion ratio of the outlet to the inlet of the isolation section (3) is 1.4.
4. A full flow channel for RBCC engine injection modes according to claim 1, characterized in that the expansion ratio of the outlet to the inlet of the combustion chamber (5) is 1.98.
5. A full flow channel for the ejector mode of a RBCC engine according to claim 1, characterized in that the expansion ratio of the position of the combustion chamber (5) where the ejector rocket (4) is mounted to the inlet of the combustion chamber (5) is 1.14.
6. A full flow channel for RBCC engine injection modes according to claim 1, characterized in that the inlet channel (1) consists of a first inlet channel and a second inlet channel in sequential communication, the first inlet channel being arranged obliquely upwards and close to the aircraft inlet with an outlet to inlet constriction ratio of 0.38, the second inlet channel being in communication with the outlet of the first inlet channel with an outlet to inlet constriction ratio of 0.54.
7. The full flow passage for the ejection mode of the RBCC engine according to claim 1, wherein the nozzle (7) is composed of a fixed shell positioned at the upper side and a movable sealing plate positioned at the lower side, the fixed shell is n-shaped, the movable sealing plate is positioned at the lower side opening of the fixed shell and is movably connected with the combustion chamber (5), and the movable sealing plate can move up and down along the movable connecting point of the movable sealing plate so as to change the outlet area of the nozzle (7) and be suitable for different incoming flow mach numbers.
8. A full flow channel for RBCC engine ejection mode according to claim 1, wherein the nozzle (7) outlet to inlet constriction ratio is 0.75 in ejection mode; the expansion ratio of the outlet to the inlet of the lance (7) in the sub-combustion/super-combustion mode is 1.17.
9. The full flow passage for the ejection mode of the RBCC engine is characterized in that the engine structure of the full flow passage comprises a connecting plate (8), an air inlet shell (11), an isolation shell (9), a combustion shell (10) and a spray pipe (7) which are sequentially connected from front to back;
The connecting plate (8) is used for extending into a precursor of the aircraft and is matched with an air inlet groove of the aircraft to form an air inlet channel, and the rear end of the air inlet channel is an air inlet channel (1);
The fuel support plate (2) is arranged on the isolation shell (9), an outlet of the fuel support plate (2) is positioned in an inner cavity of the isolation shell (9), and an inlet of the fuel support plate is close to the air inlet channel (1);
The combustion shell (10) is provided with a rocket ejector (4), and an outlet of the rocket ejector (4) is positioned at an inlet of the combustion shell (10); an external rocket (6) is mounted on the spray pipe (7), and an outlet of the external rocket (6) is positioned at an inlet of the spray pipe (7).
10. A full flow channel for RBCC engine injection modes according to claim 9, characterized in that said fuel support plates (2) are provided in two and mutually parallel.
CN202410384552.0A 2024-04-01 2024-04-01 Full flow channel for ejection mode of RBCC engine Pending CN118188220A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202410384552.0A CN118188220A (en) 2024-04-01 2024-04-01 Full flow channel for ejection mode of RBCC engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202410384552.0A CN118188220A (en) 2024-04-01 2024-04-01 Full flow channel for ejection mode of RBCC engine

Publications (1)

Publication Number Publication Date
CN118188220A true CN118188220A (en) 2024-06-14

Family

ID=91414054

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202410384552.0A Pending CN118188220A (en) 2024-04-01 2024-04-01 Full flow channel for ejection mode of RBCC engine

Country Status (1)

Country Link
CN (1) CN118188220A (en)

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