阅读说明：本技术 一种宽速域多工质功效匹配组合动力系统 (Wide-speed-range multi-working-medium efficiency matching combined power system ) 是由 刘建 许梦瑶 许德泉 任蒙飞 袁运飞 席文雄 宋佳文 于 2021-10-13 设计创作，主要内容包括：一种宽速域多工质功效匹配组合动力系统,属于动力装置技术领域,包括筒身管道、动力装置,动力装置内置于筒身管道内部,筒身管道的一端管道连接有进气管道,另一端连接有喷管；动力装置包括依照气体输送方向依次设置的涡轮动力发动机、粉末火箭发动机和超燃冲压发动机,且进气管道内置有预冷管道,预冷管道尾端伸入筒身管道的内部将涡轮动力发动机容纳于预冷管道的内部,且预冷管道位于进气管道的部分管体内部内置有引流件,本发明充分利用各发动机的特点,以最小的质量代价、空间代价,实现动力系统全流道一体化紧凑设计,实现动力系统宽范围稳定可靠工作,同时,结合各发动机的燃料不同,实现其多工质的特点。(A wide-speed-domain multi-working-quality-effect matching combined power system belongs to the technical field of power devices and comprises a cylinder body pipeline and a power device, wherein the power device is arranged in the cylinder body pipeline, one end of the cylinder body pipeline is connected with an air inlet pipeline, and the other end of the cylinder body pipeline is connected with a spray pipe; the power device comprises a turbine power engine, a powder rocket engine and a scramjet which are sequentially arranged according to the gas conveying direction, a precooling pipeline is arranged in a gas inlet pipeline, the tail end of the precooling pipeline extends into a barrel pipeline to accommodate the turbine power engine in the precooling pipeline, and a drainage piece is arranged in part of the barrel body of the precooling pipeline.)

1. A wide-speed-domain multi-working-quality-effect matching combined power system comprises a cylinder body pipeline (1) and a power device, wherein the power device is arranged in the cylinder body pipeline (1), one end of the cylinder body pipeline (1) is connected with an air inlet pipeline (2), and the other end of the cylinder body pipeline is connected with a spray pipe (3); the method is characterized in that: the power device comprises a turbine power engine (S1), a powder rocket engine (S3) and a scramjet engine (S2) which are sequentially arranged according to the gas conveying direction, a pre-cooling pipeline (4) is arranged in a gas inlet pipeline (2), the tail end of the pre-cooling pipeline (4) extends into the interior of a barrel pipeline (1) to accommodate the turbine power engine (S1) in the pre-cooling pipeline (4), the pre-cooling pipeline (4) is located in a partial pipe body of the gas inlet pipeline (2) and is internally provided with a drainage piece (5), a first heat exchanger (103) is fixedly arranged at the air outlet end of the drainage piece (5), the first heat exchanger (103) is connected with a gas compressor (7) through a pipeline, wherein gaps between the drainage piece (5) and the pre-cooling pipeline (4) form an inner culvert channel, and gaps between the gas inlet pipeline (2) and the barrel pipeline (1) form an outer culvert channel, the front end of the precooling pipeline (4) is provided with an adjustable baffle (41), when the front end of the adjustable baffle (41) abuts against the inner wall of the air inlet pipeline (2), the culvert channel is closed, and when the front end of the adjustable baffle (41) abuts against the outer surface of the drainage piece (5), the culvert channel is closed.

2. The wide-speed-range multi-working-quality power matching combined power system as claimed in claim 1, wherein: still include circulation system (6), the circulation system includes precooler storage tank (100), the exit conduit of precooler storage tank (100) is connected with pressure reducer (101) pipe connection has compressor (102), compressor (102) pipe connection is to first heat exchanger (103), just the export of compressor (102) is still pipe connection has first route and second route, first route pipe connection has second heat exchanger (104), second heat exchanger (104) pipe connection has kerosene storage tank (105), kerosene storage tank (105) pipe connection is to turbine power engine, second route pipe connection is to powder rocket engine.

3. The wide-speed-range multi-working-quality power matching combined power system as claimed in claim 2, wherein: turbine power engine includes turbine combustion chamber (8), be equipped with a plurality of through-hole on the inner wall of turbine combustion chamber (8), just turbine combustion chamber (8) pipe connection has defeated oil pipe way (91), defeated oil pipe way (91) pipe connection in kerosene storage tank (105), wherein, the tail end of turbine combustion chamber (8) is equipped with turbine spray tube (9), turbine spray tube (9) embeds there is turbine (81).

4. The wide-speed-range multi-working-quality power matching combined power system as claimed in claim 3, wherein: defeated oil pipe way (91) with the junction pipe connection of turbine combustion chamber (8) has the atomising head, just defeated oil pipe way (91) is including female pipe and a plurality of root sub-pipes, a plurality of root sub-pipe evenly distributed in all sides of turbine combustion chamber (8) surface, and the output of a plurality of root sub-pipes with the inner space of turbine combustion chamber (8) is linked together, and pipe connection and atomising head, a plurality of root sub-pipes all connect in on the female pipe.

5. The wide-speed-range multi-working-quality power matching combined power system as claimed in claim 4, wherein: the powder rocket engine is arranged in the turbine nozzle (9) and comprises a magnesium powder storage tank (10), a powder discharging device is arranged in the magnesium powder storage tank (10), a valve (11) is connected to the magnesium powder storage tank (10) through a pipeline, the valve (11) is connected to a working body (12) of the powder rocket engine through a pipeline, and a flame stabilizer (13) is arranged at the tail end of the working body (12) of the powder rocket engine.

6. The wide-speed-range multi-working-quality power matching combined power system as claimed in claim 5, wherein: the powder discharging device comprises a motor, the motor is in power connection with a telescopic assembly, a push plate is fixedly arranged at the telescopic end of the telescopic assembly, and the push plate is accommodated in the magnesium powder storage tank (10) in a sliding mode.

7. The wide-speed-range multi-working-quality power matching combined power system as claimed in claim 3, wherein: the scramjet engine comprises a ramjet combustion chamber (20), wherein a front end pipeline of the ramjet combustion chamber (20) is connected to the tail end of a turbine nozzle (9), and a tail end pipeline of the ramjet combustion chamber (20) is connected to a nozzle (3).

8. The power system of any of claims 1-7, wherein the power system comprises: the pre-refrigerant is supercritical。

Technical Field

The invention belongs to the technical field of power devices, and particularly relates to a wide-speed-range multi-working-medium power matching combined power system.

Background

The ramjet is the first-choice propulsion system of missile and other hypersonic aircrafts, and is mainly divided into a liquid fuel ramjet, a solid fuel ramjet and a solid rocket ramjet at present. The liquid fuel ramjet has mature technology, easy fuel flow regulation, high specific impulse and high engine combustion efficiency. The solid fuel ramjet has the advantages of high specific thrust, good performance in a high-speed flight state, small volume, low cost, simple structure and the like. The solid rocket ramjet has good reliability, convenient maintenance and use and short combat response time, thereby being more suitable for airborne launching. Accordingly, these engines also have some disadvantages. The liquid fuel ramjet engine has the defects of low propellant safety, low volume specific impulse, long preparation time, complex system structure and the like. The solid fuel ramjet can not realize the fuel flow and actively adjust, and because the combustion is carried out on the fuel surface, the phenomena of agglomeration and the like are caused, thereby causing the problems of difficult combustion organization, low combustion efficiency and the like. Most of the fuels of the solid rocket ramjet are composite propellant grains, and contain an oxidant, so that the specific impulse is reduced; moreover, the fuel is easy to age, the storage condition is severe, the grains can crack and even break, and the adjustment is difficult, so the safety is very poor.

Combined cycle power system design is the leading edge and difficulty of current push-forward technology development. Most of the current combined power designs are based on the idea of directly combining and binding structures and functions, and only structurally combine mechanically on the basis of independent work of various engines, so that the ideal working efficiency is difficult to achieve due to the lack of deep fusion between working cycle parameters of various engines and full utilization of fuel and working media. The design concept is difficult to realize, and the structural design of movable hot components, the combination of various engine units (modes) and working systems, the layout design of an aircraft body and engines and the like face huge challenges.

Disclosure of Invention

The invention aims to provide a wide-speed-domain multi-working-quality power matching combination system to solve the problems in the background technology.

In order to achieve the purpose, the invention provides the following technical scheme:

a wide-speed-domain multi-working-quality-effect-matching combined power system comprises a cylinder body pipeline and a power device, wherein the power device is arranged in the cylinder body pipeline, one end of the cylinder body pipeline is connected with an air inlet pipeline, and the other end of the cylinder body pipeline is connected with a spray pipe; the power device comprises a turbine power engine, a powder rocket engine and a scramjet which are sequentially arranged according to the gas conveying direction, a precooling pipeline is arranged in the gas inlet pipeline, the tail end of the precooling pipeline extends into the barrel pipeline to accommodate the turbine power engine in the precooling pipeline, a drainage piece is arranged in part of the barrel of the precooling pipeline, a first heat exchanger is fixedly arranged at the air outlet end of the drainage piece, a gas compressor is connected with the first heat exchanger through a pipeline, a gap between the drainage piece and the precooling pipeline forms an inner culvert channel, a gap between the gas inlet pipeline and the barrel pipeline forms an outer culvert channel, an adjustable baffle is arranged at the front end of the precooling pipeline, and when the front end of the adjustable baffle is abutted against the inner wall of the gas inlet pipeline, the outer culvert channel is closed, when the front end of the adjustable baffle abuts against the outer surface of the drainage piece, the culvert channel is closed.

Compared with the prior art, the technical scheme has the following effects:

(1) compare in traditional driving system, through carrying out the precooling to the air, and need not to liquefy the air, eliminated the problem of pinch, reduced the problem of cooling process in-process consumption, in the practical application scene, there is a large amount of problems in the precooling scheme of adoption, if: the pre-cooling device has the advantages of high processing requirement, complex operation and maintenance, multiple system accessories, high cost, difficulty in repeated use and the like, and the pre-cooling device is simple in structure, effectively guarantees the pre-cooling effect and solves the problems.

(2) The combination of the turbine engine, the powder rocket engine and the ramjet engine is adopted, meanwhile, the inflow of air is divided into an inner duct and an outer duct, the inner duct is a low-speed channel and provides an oxidant for the turbine engine, the outer duct is a high-speed channel and provides the oxidant for the ramjet engine, and the distribution of the air flow of the inner duct and the air flow of the outer duct is controlled by combining an adjustable baffle plate, so that the high efficiency, the stability and the like of the power system are realized.

(3) The characteristics of each engine are fully utilized, the integrated compact design of the whole flow channel of the power system is realized at the minimum quality cost and space cost, the wide-range stable and reliable work of the power system is realized, and the propulsion performance as high as possible is obtained; meanwhile, because the fuels of the engines are different, the characteristic of multiple working media is realized.

Preferably, the powder rocket engine further comprises a circulating system, the circulating system comprises a precooler storage tank, an outlet pipeline of the precooler storage tank is connected with a pressure reducer, a pressure reducer pipeline is connected with a compressor, a compressor pipeline is connected to a first heat exchanger, an outlet of the compressor is further connected with a first passage and a second passage through pipelines, the first passage is connected with a second heat exchanger through a pipeline, the second heat exchanger is connected with a kerosene storage tank through a pipeline, the kerosene storage tank is connected to the turbine power engine through a pipeline, and the second passage is connected to the powder rocket engine through a pipeline.

Preferably, turbine power engine includes the turbine combustion chamber, be equipped with a plurality of through-hole on the inner wall of turbine combustion chamber, just turbine combustion chamber pipe connection has defeated oil pipe way, defeated oil pipe way connect in the kerosene storage tank, wherein, the tail end of turbine combustion chamber is equipped with the turbine spray tube, the turbine spray tube embeds there is the turbine.

As preferred, defeated oil pipe way with the junction pipe connection of turbine combustion chamber has the atomising head, just defeated oil pipe way includes female pipe and a plurality of root sub-pipes, and a plurality of root sub-pipe evenly distributed are at the week side surface of turbine combustion chamber, and the output of a plurality of root sub-pipes with the inner space of turbine combustion chamber is linked together, and pipe connection and atomising head, a plurality of root sub-pipes all connect in on the female pipe.

Preferably, the powder rocket engine is arranged in the turbine nozzle, the powder rocket engine comprises a magnesium powder storage tank, a powder discharging device is arranged in the magnesium powder storage tank, a valve is connected to the magnesium powder storage tank through a pipeline, the valve is connected to a working body of the powder rocket engine through a pipeline, and a flame stabilizer is arranged at the tail end of the working body of the powder rocket engine.

Preferably, the powder discharging device comprises a motor, the motor is in power connection with a telescopic assembly, a push plate is fixedly arranged at the telescopic end of the telescopic assembly, and the push plate is accommodated in the magnesium powder storage tank in a sliding manner.

Preferably, the scramjet engine comprises a ramjet combustion chamber, a front end pipeline of the ramjet combustion chamber is connected to the tail end of the turbine nozzle, and a tail end pipeline of the ramjet combustion chamber is connected with the nozzle.

Preferably, the precooling agent is supercritical。

Drawings

FIG. 1 is a schematic diagram of the overall architecture of the present invention;

FIG. 2 is a schematic block diagram of a turbine engine according to the present invention;

FIG. 3 is a schematic diagram of the ramjet architecture of the present invention;

FIG. 4 is a schematic diagram of a portion of the power system of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be described below in detail and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments.

Example (b):

as shown in fig. 1-4, the wide-speed-range multi-working-medium power matching combined power system is provided with a circulating system 6, and mainly comprises a cylinder pipe 1 and a power device, wherein the power device is arranged in the cylinder pipe 1, the front end pipe of the cylinder pipe 1 is connected with an air inlet pipe 2, and the tail end of the cylinder pipe is connected with a spray pipe 3; the power device comprises a turbine power engine S1, a powder rocket engine S3 and a scramjet engine S2 which are sequentially arranged according to a gas conveying direction, and has the advantages that the characteristics of the engines are fully utilized, the integrated compact design of the full flow passage of the engines is realized at the minimum quality cost and space cost, the stable and reliable work of the engines in a wide range is realized, and the propelling performance as high as possible is obtained, a precooling pipeline 3 is arranged in an air inlet pipeline 2, the tail end of the precooling pipeline 3 extends into a barrel pipeline 1 to accommodate the turbine power engine S1 in the precooling pipeline 3, the precooling pipeline 3 is positioned in a pipe body of the air inlet pipeline 2 and is internally provided with a flow guide piece 5, a first heat exchanger 103 is fixedly arranged at the air outlet end of the flow guide piece 5, the first heat exchanger 103 is connected with a compressor 7 through a pipeline, wherein an adjustable baffle 4 is arranged at the front end of the precooling pipeline 3, precooling pipeline 3 with clearance between drainage piece 5 constitutes the culvert passageway, inlet line 2 with the clearance of stack shell pipeline 1 constitutes the culvert passageway outward, in this embodiment to adjustable baffle 4 locates the front end of precooling pipeline 3, promptly as adjustable baffle 4 the front end butt in during the inner wall of inlet line 2, the culvert passageway is sealed outward, as adjustable baffle 4 the front end butt in when the surface of drainage piece 5, the culvert passageway is sealed.

In this embodiment, the circulation system 6 includes pre-coolingA pre-coolant tank 100, the pre-coolant stored in the pre-coolant tank 100 being supercriticalCompared with the traditional helium, the method has the problems that the manufacturing difficulty is high, the production cannot be realized at home, the helium is used as a national strategic resource, the obtaining way is narrow, the cost is high, the ordinary research is difficult to support, and the like, and the supercritical fluid is adoptedThe problem can be effectively solved, an outlet pipeline of the pre-coolant storage tank 100 is connected with a pressure reducer 101, the pressure reducer 101 is connected with a compressor 102 through a pipeline, the compressor 102 is connected with a first heat exchanger 103 through a pipeline, the compressor 102 is further connected with a first passage and a second passage through a pipeline, the first passage is connected with a second heat exchanger 104 through a pipeline, the second heat exchanger 104 is connected with a kerosene storage tank 104 through a pipeline, an output end pipeline of the kerosene storage tank 104 is connected with a two-way valve, one outlet of the two-way valve is connected to an oil supply passage B through the second heat exchanger 104, the other outlet of the two-way valve is connected to an oil supply passage A, the oil supply passage B is connected to the turbine power engine S1 through a pipeline, and the oil supply passage A is connected to the scramjet engine S2 through a pipeline; particularly supercriticalThe gas is divided into three paths after passing through the compressor 102, the first path provides power for the expansion work of the compressor 102 to realize the effect of pressurization, the second path attacks the powder fuel rocket engine S3 in a high-temperature state to be used as an oxidant, and the third path enters the second heat exchanger 104 to extrude the liquid fuel by utilizing pressure potential energy.

With reference to fig. 2, the turbine power engine S3 includes a turbine combustion chamber 8, a plurality of through holes are provided on the inner wall of the turbine combustion chamber 8, and the pipeline of the turbine combustion chamber 8 is connected with an oil pipeline 91, the oil pipeline 91 is connected to the kerosene storage tank 104, that is, the oil pipeline 91 is connected to an oil supply passage B, wherein a turbine nozzle 9 is provided at the tail end of the turbine combustion chamber 8, a turbine 8 is provided in the turbine nozzle 9, the specific working process is that, when the adjustable baffle 4 is in the intermediate state, the in-machine culvert pipeline and the out-culvert pipeline both have air entering states, at this time, the air is captured by the air inlet pipeline 2, flows through the first heat exchanger 103 via the flow guide 5 for precooling, then, is compressed by the compressor 7, is filled in the turbine combustion chamber 8 via a plurality of through holes, and at the same time, the oil supply passage B provides fuel (kerosene) via the oil pipeline 91 to the inside of the turbine combustion chamber 8, at this time, the compressed precooled air and the fuel are mixed and combusted, and the combustion gas is passed through the turbine 81 to generate an oxygen-rich combustible gas.

It is worth noting that in order to ensure that fuel is more evenly sprayed into the turbine combustion chamber 8, following mode is adopted, oil pipeline 91 with the junction pipe connection of turbine combustion chamber 8 has the atomising head, just oil pipeline 91 includes female pipe and a plurality of root sub-pipes, and a plurality of root sub-pipes evenly distributed are at the week side surface of turbine combustion chamber 8, and the output of a plurality of root sub-pipes with the inner space of turbine combustion chamber 8 is linked together, and pipe connection and atomising head, a plurality of root sub-pipes all connect in on the female pipe.

In this embodiment, the powder rocket engine is arranged in the turbine nozzle 9 and comprises a magnesium powder storage tank 10, a powder outlet device is arranged in the magnesium powder storage tank 10, the magnesium powder storage tank 10 is connected with a valve 11 through a pipeline, the valve 11 is connected with a working body 12 of the powder rocket engine through a pipeline, a flame stabilizer 13 is arranged at the tail end of the working body 12 of the powder rocket engine, and the supercritical carbon dioxide is used as fuelAs an oxidizing agent, more stable and efficient energy can be provided.

It should be noted that, in order to ensure that the magnesium powder in the magnesium powder storage tank 10 can be fed into the working body 12 of the powder rocket engine, the powder discharging device comprises a motor, the motor is in power connection with a telescopic assembly, a push plate is fixedly arranged at the telescopic end of the telescopic assembly, and the push plate is slidably accommodated in the magnesium powder storage tank 10.

In addition, the scramjet engine comprises a ramjet combustion chamber 20, the front end pipeline of the ramjet combustion chamber 20 is connected to the tail end of the turbine spray pipe 9, the tail end pipeline of the ramjet combustion chamber 20 is connected to the spray pipe 3, the wall surface pipeline of the ramjet combustion chamber 20 is connected with the oil supply passage A, therefore, the wall surface of the scramjet engine is subjected to thermal protection work, and secondly, fuel passing through the wall surface can be directly sprayed into the ramjet combustion chamber 20, so that afterburning is carried out, and the specific thrust of the power system is improved.

The selection of the working state of the adjustable baffle 41 is described in conjunction with a specific application scenario, and the content is as follows:

when the power system works in a turbine mode when Ma is not less than 0 and less than 3, the power system is in a turbine mode, at the moment, an adjustable baffle plate 41 at the inlet of an air inlet pipeline 2 closes an outer culvert channel, incoming air completely enters an inner culvert channel, high-temperature incoming air firstly enters an air compressor 7 from the air inlet pipeline 2, high-temperature air is pre-cooled by using a supercritical medium before the air compressor 7, then enters a turbine combustion chamber 8 of a turbine engine S1 for combustion, high-temperature and high-pressure gas generated by combustion does work on the turbine to drive the air compressor 7, the gas finally enters a turbine spray pipe 9 to be sprayed out to generate thrust, in the Mach number range, a powder rocket engine S2 can be started when the takeoff or transonic thrust is insufficient, the power system works in the turbine-rocket combination mode, the blades of the air compressor 7 can bear higher mach number of the incoming flow by pre-cooling the high-temperature incoming air by the supercritical medium, the operating mach number of the turbine engine S1 is increased.

When Ma is more than or equal to 4 and is more than or equal to 3, the adjustable baffle 41 is controlled, the bypass channel is opened, a part of air is distributed to enter the ramjet combustion chamber 20, the powder rocket engine S3 starts to work while the ramjet engine S2 is started, and the powder rocket engine S3 is used for supersonic combustion ejection ignition. The powder rocket motor S3 is turned off after combustion has stabilized in the ram combustion chamber 20. The high-temperature incoming air at this time enters the ram combustion chamber 20 from the inside and outside culvert channels in two paths, and is made to be in a proper position through the adjustable baffle 41 according to the flow required by the inside and outside culvert channels, so that the flow is distributed. Therefore, the ramjet engine S2 is in a turbine-rocket-ram combined mode when being started, and after the ramjet engine S2 works stably, namely Ma = 3-4, the engine works in the turbine-rocket-ram combined mode.

When Ma is larger than or equal to 10 and larger than or equal to 4, even if the supercritical medium precools high-temperature incoming flow air, the supercritical medium cannot perform deep precooling like liquid hydrogen and liquid helium, and the blades of the compressor 7 cannot bear higher incoming flow Mach number, so that the turbine engine S1 needs to be shut down. At this time, the adjustable baffle 41 is controlled to completely seal the culvert channel, so that high-temperature incoming flow air completely enters the culvert channel until the incoming flow air enters the stamping combustion chamber 20 and is mixed with kerosene which regeneratively cools the wall surface for combustion, and then the incoming flow air is ejected from the nozzle 3 to generate thrust. Therefore, when Ma =4~10, the power system works in the stamping mode. In the range, the powder rocket engine S2 can be started timely to increase the thrust to work in a rocket-stamping mode according to the high-Mach-number low-dynamic-pressure flight and maneuvering defense requirements.

When Ma >10, if the combined power system still works in the stamping mode, the kerosene for wall cooling is larger than that required for combustion, and the performance of the power system is greatly reduced by carrying redundant kerosene specially for wall cooling. Thus, when Ma >10, the combined power system is converted from ram mode to rocket mode by shutting down the ram engine S2 by cutting off the kerosene line to the ram combustion chamber 20 of the ram engine S2, and simultaneously turning on the powder rocket engine S3, essentially a high specific impulse solid powder rocket engine. At this time, the bypass passage is still in an open state, and high-temperature incoming air enters the ram combustion chamber 20 of the ram engine S2 through the air inlet duct 2, but is not combusted and is ejected together with high-temperature gas of the powder rocket, thereby providing thrust.

In the description of the present invention, it is to be understood that the terms "center", "lateral", "upper", "lower", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified. Furthermore, the term "comprises" and any variations thereof is intended to cover non-exclusive inclusions.

The present invention has been described in terms of embodiments, and several variations and modifications can be made to the device without departing from the principles of the present invention. It should be noted that all the technical solutions obtained by means of equivalent substitution or equivalent transformation, etc., fall within the protection scope of the present invention.