CN111692013A - Axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine and control method - Google Patents
Axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine and control method Download PDFInfo
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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
- F02K7/16—Composite ram-jet/turbo-jet engines
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Abstract
The invention provides an axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine, which adopts an axisymmetric layout form, wherein a turbine engine is positioned in the middle, the rotary detonation ramjet engine is positioned in an outer ring flow channel, and an air inlet lip cover moves in parallel to adjust the contraction ratio and the flow capture of an air inlet; the conversion among the three modes of the engine is realized through the parallel movement mode conversion device. The front edge of the modal converter is positioned at the downstream of the throat of the air inlet, an expansion type stamping flow channel and a turbine flow channel are constructed, the tail shock waves can be limited in the flow channels, and the coupling interference between the cross flow channel of the rotary detonation stamping engine and the cross flow channel of the turbine engine under the common working state is shielded. The adjusting mode of the parallel movement of the lip cover and the mode conversion device has the advantages of simple operation, easy realization, strong operability/reliability, convenient sealing and the like.
Description
Technical Field
The invention relates to the field of aircraft design, in particular to a combined engine.
Background
The Combined propulsion device Based on multiple types of power is generated under the promotion of the demand, and comprises a Turbine-Based Combined Cycle engine (turbo Based Combined Cycle-TBCC), a Rocket-Based Combined Cycle engine (Rocket Based Combined Cycle-RBCC), a Turbine/Rocket-Based Combined Cycle engine (turbo/Rocket Based Combined Cycle-T/RBCC) and the like. The core of the combined cycle engine is to exert the performance advantages of various engines in the Mach number working range, expand the working range of the whole engine and improve the efficiency of the engine.
The turbine-based combined cycle engine (TBCC) can realize horizontal take-off and landing of an aircraft, is reusable and has good economical efficiency, and is a research hotspot. However, under the influence of the working characteristics of the turbine engine and the ramjet engine, the thrust of the turbine-based combined cycle engine in the Ma2-2.5+ modal region is low, and a 'thrust trap' exists, so that the bottleneck for limiting whether the engine can provide power for Ma0-5+ flight is formed. The working characteristics of the ramjet based on the isobaric combustion are greatly influenced by the total pressure of the incoming flow, and generally Ma is more than 3.0, so that the ramjet can work efficiently. In order to fill the thrust trap, the main technical idea at present is to widen the mach number working range of the turbine engine, but the technical difficulty of the development of the turbine engine is greater from the current research progress situation. The engine technology is strong in realizability, but high in integration level and complex in structure and control system.
In addition, the conversion of chemical energy into heat energy is realized by adopting slow combustion in both rocket engines, turbine engines and ramjet engines. The slow combustion is a chemical reaction heat release process which is dominated by a diffusion phenomenon, the slow combustion wave propagation speed is determined to be low by the smaller component diffusion speed and the thermal diffusion speed, the slow combustion wave propagation speed is generally m/s magnitude, the isobaric heat release process is an entropy increase process, and the thermal efficiency is not high.
Therefore, a novel combined power scheme needs to be developed, which can effectively fill up the thrust defect of the turbine-based combined cycle engine and avoid the problems of high integration level and complex structure and control system of the turbine-assisted rocket reinforced ram combined cycle engine. The efficiency of the combined engine is improved, and a new power selection is provided for wide-speed-range, wide-airspace and high-efficiency flight.
Disclosure of Invention
In order to solve the problems, the invention provides an axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine, which widens the lower limit of the working Mach number of the ramjet by utilizing the self-supercharging effect of the rotary detonation ramjet, increases the thrust in the mode conversion process, effectively integrates the high specific impulse advantages of the turbine engine and the rotary detonation ramjet, and fills the thrust trap commonly existing in the design scheme of the conventional turbine-based combined engine.
The invention also provides a control method of the engine.
In order to achieve the purpose, the axial symmetry internal parallel turbine-based rotary knocking and punching combined engine adopts the following technical scheme:
an axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine comprises a rotary detonation ramjet engine, a turbine engine positioned in the rotary detonation ramjet engine, an annular rotary detonation ramjet flow channel annular wall positioned at the front end of the turbine engine, and a central body positioned in front of the inner annular wall surface of the rotary detonation ramjet flow channel;
the rotary detonation ramjet engine is provided with an annular engine outer wall, a space formed between the turbine engine and the engine outer wall is a rotary detonation ramjet flow passage extending from front to back, the center of the turbine engine is provided with a turbine flow passage extending from front to back, the front of the engine outer wall is an air inlet lip cover surrounding a central body, and the air inlet lip cover and the central body form an air inlet; the front end of the rotary detonation stamping runner annular wall is provided with a slot which is concavely arranged from front to back, and a modal converter is arranged in the slot;
the mode converter is an annular moving device, the front end of the mode converter extends outwards to form a horn shape, the mode converter moves forwards to the foremost end and is connected with the central body, at the moment, an inlet of the air inlet channel is communicated with the rotary detonation stamping runner, and the inlet of the air inlet channel is sealed with the turbine runner; the modal converter is connected with the inner side of the outer wall of the engine when moving backwards to the rearmost end, at the moment, an inlet of the air inlet channel is communicated with the turbine runner, and the inlet of the air inlet channel and the rotary detonation stamping runner are sealed; when the mode converter moves to the intermediate state, the mode converter is positioned between the central body and the outer wall of the engine, and at the moment, the inlet of the air inlet channel is simultaneously communicated with the turbine flow channel and the rotary detonation punch flow channel.
Further, the air inlet lip cover moves back and forth along the outer wall of the engine.
Furthermore, the tail end of the turbine engine is provided with an adjustable tail nozzle.
Further, the modal converter leading edge is located downstream of the inlet throat.
The invention also provides a technical scheme of the control method of the engine, which comprises the following steps: the Mach number working range of the engine is Mach number 0-5+, the flight Mach number is M0, and M0 is more than or equal to 0 and less than or equal to 5 +;
when M0 is more than 0 and less than or equal to 2.0, the mode converter is located at the last position, and the front edge of the mode converter is contacted with the outer wall of the engine;
when M0 is more than 0 and less than or equal to 2.0, adjusting the lip cover according to the flow demand of the turbojet engine as the Mach number increases, and translating from the last position to the upstream, wherein the engine is in a turbine mode at the moment;
when M0 is more than or equal to 2.0 and less than or equal to 3.0, the lip cover moves horizontally upstream according to the flow demand of the engine, meanwhile, the mode converter moves horizontally upstream, and the engine is in a transition mode;
when M0 is more than or equal to 3.0 and less than or equal to 5.0+, the lip cover moves horizontally upstream according to the flow demand of the engine, meanwhile, the mode converter moves horizontally upstream to be in contact with the central body, and the engine enters a rotary knocking stamping mode.
Has the advantages that: the invention provides an axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine, which has a turbine mode in Ma0 → 2.0; ma2.0 → 3.0, transition state; ma3.0 → 5.0+, spin knock impact mode. The combination of the turbine engine and the rotary detonation ramjet effectively relieves 'thrust trap' of the turbine-based combined cycle engine, and the rotary detonation ramjet is adopted to downwards expand the Mach number working range of the ramjet and improve the engine thrust in the mode conversion process. The layout form of the middle turbine engine and the outer ring rotary knocking ramjet engine has a compact structure, and is beneficial to providing good air inlet conditions for the rotary knocking ramjet engine and the turbine engine. The flow capture and area contraction ratio of the air inlet channel is adjusted through the translation lip cover, so that the self-starting problem of the air inlet channel and the efficient compression problem of air flow under the condition of high Mach number are solved; the mode converter adopts translation adjustment, and can realize the work conversion of a pure turbine mode, a transition state and a pure rotation knocking stamping mode. The front edge of the modal converter is positioned at the downstream of the throat of the air inlet to form an expanding supersonic stamping flow channel, so that the tail shock wave can be limited in the self-supply flow channel, and the coupling interference of the rotary detonation engine and the turbine engine under the common working state can be shielded. The lip cover and the mode converter are in translational motion, and the adjusting mode has the advantages of strong operability, easiness in realization, convenience in adjustment and sealing and the like. According to the design scheme of the axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine, the detonation combustion self-pressurization effect and the isovolumetric combustion characteristic are fully utilized, the lower limit of the working Mach number of the ramjet is widened, the thrust of the engine in the mode conversion process is increased, the high specific impulse advantages of the turbine engine and the rotary detonation ramjet are effectively integrated, and the thrust trap commonly existing in the design scheme of the conventional turbine-based combined cycle engine is filled. The efficiency of the combined engine is improved, the combined engine can effectively work in a wide Mach number range, and better pneumatic performance is obtained.
Drawings
FIG. 1 is a schematic cross-sectional view of a combined engine employing rotational detonation of axisymmetric internal parallel turbines according to the present invention.
FIG. 2 is a schematic cross-sectional view of a turbine mode of an engine according to the present invention.
FIG. 3 is a schematic cross-sectional view of the transition mode of the engine according to the present invention.
FIG. 4 is a schematic cross-sectional view of an engine in a rotary detonation ramjet mode according to the present invention.
Section A in the figure1-A2An expanded supersonic flow passage representing a rotary detonation punch flow passage, C a tail generated in the punch expanded flow passageShock wave, D represents a trailing shock wave generated in the turbine flowpath expansion section.
Detailed Description
Referring to fig. 1, the present invention provides an axisymmetric internal parallel turbine-based rotational detonation ramjet combined engine, which includes a rotational detonation ramjet engine 9, a turbine engine 8 located in the rotational detonation ramjet engine, an annular rotational detonation ramjet annular wall 5 located at the front end of the turbine engine 8, and a center body 1 located in front of the annular wall 5 in the rotational detonation ramjet. The rotary detonation ramjet has an annular engine outer wall 7. The space formed between the turbine engine 8 and the engine outer wall 7 is a rotating detonation ram channel 6 extending from front to back. The turbine engine 8 is centrally provided with a turbine runner 11 extending from the front to the rear. In front of this engine outer wall 7 is a forward and aft movable inlet lip shroud 3 around the centerbody. The inlet lip 3 forms with the central body 1 an inlet 2 of the inlet duct. The front end of the rotary detonation stamping runner annular wall 5 is provided with a slot 12 which is recessed from front to back, and the slot is internally provided with a modal converter 4. At the aft end of the turbine engine is an adjustable jet nozzle 10.
In the present embodiment, the mode conversion of the entire air intake duct structure can be adjusted by the forward and backward movement of the mode converter 4. The mode converter 4 is an annular mobile device, and the front end of the mode converter 4 extends outwards to form a horn shape. The mode converter 4 is connected with the central body 1 when moving forward to the foremost end, and at the moment, the air inlet channel inlet 2 is communicated with the rotary detonation punching flow channel 6, and the air inlet channel inlet 2 and the turbine flow channel 11 are closed. The modal converter is connected with the inner side of the outer wall 7 of the engine when moving backwards to the rearmost end, at the moment, the inlet 2 of the air inlet channel is communicated with the turbine runner 11, and the space between the inlet 2 of the air inlet channel and the rotary knocking punching runner 6 is closed. When the mode converter 4 is moved to the intermediate state, the mode converter 4 is located between the central body 1 and the outer wall 7 of the engine, and the inlet 2 is simultaneously in communication with the turbine runner 11 and the rotary detonation ram runner 6.
The combination of the turbine engine and the rotary detonation ramjet is the first key point of the invention, the Mach number working range of the rotary detonation ramjet is expanded downwards by utilizing the characteristics of the self-supercharging effect and the isochoric combustion of the rotary detonation ramjet, the engine thrust in the mode conversion process is increased, the high specific impulse advantages of the turbine engine and the rotary detonation ramjet are effectively integrated, the thrust trap of a turbine-based combined cycle engine is filled, and the efficiency of the combined engine is improved.
The axial symmetry inner parallel connection turbine-based rotation detonation ramjet combined engine is in an axial symmetry layout form, the turbine engine 8 is located in the middle, and the rotation detonation ramjet engine 9 is located in an outer ring flow channel. The rotary detonation ramjet engine 9 is a new concept engine that uses continuous detonation combustion to generate thrust, such engines typically employing an annular combustion chamber. The layout form of the combined engine is beneficial to promoting the stable work of the rotary detonation engine, improving the working characteristics of the rotary detonation engine, having compact structure and reducing the windward resistance of the engine.
The third key point of the invention is that the inlet lip cover 3 adopts a parallel moving mode to adjust the ratio of the flow capture and the area shrinkage of the inlet, the parallel moving adjusting mode has simple operation, easy realization, strong operability/reliability and convenient sealing, and can relieve the contradiction between the self-starting and the high-efficiency compression of the inlet.
The mode conversion device 4 moves in parallel to perform the conversion of the working mode of the engine, which is the fourth key point of the invention. The parallel movement adjusting mode is simple to operate, easy to realize, strong in operability/reliability and convenient to seal. The conversion among a pure turbine mode, a transition mode and a rotary knocking stamping mode can be realized.
The fifth key point of the present invention is that the modal converter leading edge is located downstream of the inlet throat. As shown in FIG. three, section A1-A2The expansion supersonic flow passage is a rotary detonation stamping flow passage. When the two-stage combined type shock wave generator works together, a tail shock wave C is generated in the stamping expansion flow passage, a tail shock wave D is generated in the turbine flow passage expansion section, the tail shock waves are limited in the flow passages of the two-stage combined type shock wave generator, and coupling interference between the cross flow passages of the rotary detonation engine and the turbine engine under the common working state can be shielded.
The invention relates to an axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine, which specifically operates as follows in the working process of the engine under different flight Mach numbers:
the Mach number working range of the combined engine is Mach number 0-5+, and the flight Mach number is set to be M0(0≤M0≤5+)。Ma00 → 2.0, turbo mode; ma02.0 → 3.0, transition state; ma03.0 → 5.0+, rotary detonation punch mode. (1) When 0 is present<M0At ≦ 2.0, the modal converter 4 is in the last position, where the front edge of the modal converter is in contact with the outer engine wall 7, as shown in fig. 2. (2) When 0 is present<M02.0 is less than or equal to, along with the increase of Mach number, the movable lip cover 2 is adjusted according to the flow demand of the turbojet engine, and the movable lip cover is translated from the last position to the upstream, and at the moment, the engine is in a turbine mode. (3) Referring to FIG. 3, when 2.0. ltoreq.M0When the flow rate of the engine is less than or equal to 3.0, the lip cover 2 moves horizontally upstream according to the flow demand of the engine, meanwhile, the mode converter 4 moves horizontally upstream, and the engine is in a transition mode. (4) Referring to FIG. 4, when M is 3.0. ltoreq.M0When the flow rate of the engine is less than or equal to 5.0+, the lip cover 2 moves upstream horizontally according to the flow rate requirement of the engine, meanwhile, the mode converter 4 moves upstream horizontally to be in contact with the central body 1, and the engine enters a rotary knocking punching mode.
The invention has many ways to implement the technical scheme, and the above description is only one of the embodiments of the invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can be made, and these improvements and modifications should also be construed as the protection scope of the present invention. All the components not specified in the present embodiment can be realized by the prior art.
Claims (5)
1. The utility model provides an axial symmetry internal parallel turbine base rotation detonation punching press combination engine which characterized in that: the device comprises a rotary detonation ramjet engine, a turbine engine positioned in the rotary detonation ramjet engine, an annular rotary detonation ramjet flow passage annular wall positioned at the front end of the turbine engine, and a central body positioned in front of the inner annular wall surface of the rotary detonation ramjet flow passage;
the rotary detonation ramjet engine is provided with an annular engine outer wall, a space formed between the turbine engine and the engine outer wall is a rotary detonation ramjet flow passage extending from front to back, the center of the turbine engine is provided with a turbine flow passage extending from front to back, the front of the engine outer wall is an air inlet lip cover surrounding a central body, and the air inlet lip cover and the central body form an air inlet; the front end of the rotary detonation stamping runner annular wall is provided with a slot which is concavely arranged from front to back, and a modal converter is arranged in the slot;
the mode converter is an annular moving device, the front end of the mode converter extends outwards to form a horn shape, the mode converter moves forwards to the foremost end and is connected with the central body, at the moment, an inlet of the air inlet channel is communicated with the rotary detonation stamping runner, and the inlet of the air inlet channel is sealed with the turbine runner; the modal converter is connected with the inner side of the outer wall of the engine when moving backwards to the rearmost end, at the moment, an inlet of the air inlet channel is communicated with the turbine runner, and the inlet of the air inlet channel and the rotary detonation stamping runner are sealed; when the mode converter moves to the intermediate state, the mode converter is positioned between the central body and the outer wall of the engine, and at the moment, the inlet of the air inlet channel is simultaneously communicated with the turbine flow channel and the rotary detonation punch flow channel.
2. The axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine of claim 1, characterized in that: the inlet lip covers move back and forth along the outer wall of the engine.
3. The axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine of claim 2, characterized in that: the tail end of the turbine engine is provided with an adjustable tail nozzle.
4. The axisymmetric internal parallel turbine-based rotary detonation ramjet combined engine of claim 1, or 2 or 3, characterized in that: the modal converter leading edge is located downstream of the inlet throat.
5. A control method of an engine according to any one of claims 1 to 4, characterized in that: the Mach number working range of the engine is Mach number 0-5+, the flight Mach number is M0, and M0 is more than or equal to 0 and less than or equal to 5 +;
when M0 is more than 0 and less than or equal to 2.0, the mode converter is located at the last position, and the front edge of the mode converter is contacted with the outer wall of the engine;
when M0 is more than 0 and less than or equal to 2.0, adjusting the lip cover according to the flow demand of the turbojet engine as the Mach number increases, and translating from the last position to the upstream, wherein the engine is in a turbine mode at the moment;
when M0 is more than or equal to 2.0 and less than or equal to 3.0, the lip cover moves horizontally upstream according to the flow demand of the engine, meanwhile, the mode converter moves horizontally upstream, and the engine is in a transition mode;
when M0 is more than or equal to 3.0 and less than or equal to 5.0+, the lip cover moves horizontally upstream according to the flow demand of the engine, meanwhile, the mode converter moves horizontally upstream to be in contact with the central body, and the engine enters a rotary knocking stamping mode.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114753930A (en) * | 2022-04-19 | 2022-07-15 | 南京航空航天大学 | Combined power mode conversion method based on axisymmetric air inlet channel configuration characteristics |
| CN114837811A (en) * | 2022-04-19 | 2022-08-02 | 南京航空航天大学 | Combined power mode conversion method for extended outer casing |
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| CN114837811A (en) * | 2022-04-19 | 2022-08-02 | 南京航空航天大学 | Combined power mode conversion method for extended outer casing |
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| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Wang Weixing Inventor after: Luo Longkang Inventor after: Li Youchen Inventor after: Zhang Rentao Inventor before: Wang Weixing Inventor before: Li Youchen Inventor before: Luo Longkang Inventor before: Zhang Rentao |
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200922 |