阅读说明：本技术 一种火箭发动机换热器及航天飞行器 (Rocket engine heat exchanger and aerospace vehicle ) 是由 张玺 魏一 彭小波 于 2019-09-18 设计创作，主要内容包括：本发明公开了一种火箭发动机换热器及航天飞行器,该火箭发动机包括具有燃烧腔的燃烧室本体,所述燃烧室本体外壁设有外层结构,所述外层结构与所述燃烧室本体之间形成允许增压工质与所述燃烧腔进行热交换的换热空间；还包括与所述换热空间连通以进出所述增加工质的入口结构和出口结构。本发明通过设于燃烧室本体外壁的外层结构和燃烧室本体之间形成允许增压工质与燃烧腔进行热交换的换热空间,省去了发动机上为火箭贮箱增压系统专门设计的换热器装置,减轻了发动机的结构质量,从而提高了发动机的推质比性能。简化发动机的部件,提高换热器的结构可靠性。(The invention discloses a rocket engine heat exchanger and a space shuttle, wherein the rocket engine comprises a combustion chamber body with a combustion chamber, the outer wall of the combustion chamber body is provided with an outer layer structure, and a heat exchange space allowing a pressurizing working medium to exchange heat with the combustion chamber is formed between the outer layer structure and the combustion chamber body; the heat exchanger also comprises an inlet structure and an outlet structure which are communicated with the heat exchange space to enter and exit the increased working medium. According to the invention, the heat exchange space allowing the supercharged working medium to exchange heat with the combustion cavity is formed between the outer layer structure arranged on the outer wall of the combustion chamber body and the combustion chamber body, so that a heat exchanger device specially designed for a rocket tank supercharging system on the engine is omitted, the structural quality of the engine is reduced, and the boost ratio performance of the engine is improved. The parts of the engine are simplified, and the structural reliability of the heat exchanger is improved.)

1. A rocket engine heat exchanger, wherein the rocket engine comprises a combustion chamber body with a combustion chamber (1), characterized in that an outer layer structure (3) is arranged on the outer wall of the combustion chamber body, and a heat exchange space allowing a pressurized working medium to exchange heat with the combustion chamber (1) is formed between the outer layer structure (3) and the combustion chamber body; the heat exchanger also comprises an inlet structure (6) and an outlet structure (10) which are communicated with the heat exchange space to enter and exit the pressurized working medium.

2. A rocket engine heat exchanger according to claim 1, wherein a plurality of spacing structures (11) extending in the direction of extension of the combustion chamber body are arranged in the heat exchanging space, said spacing structures (11) being arranged between the outer structure (3) and the combustion chamber body to space the heat exchanging space into a plurality of heat exchanging grooves (5).

3. A rocket engine heat exchanger according to claim 2, characterized by comprising a first collector (4) and a second collector (9), said first collector (4) communicating with all said heat exchange slots (5) at one end and with said inlet structure (6) at the other end; one end of the second collector (9) is communicated with all the heat exchange grooves (5), and the other end of the second collector is communicated with the outlet structure (10).

4. A rocket engine heat exchanger according to claim 3, wherein said first collector (4) and said second collector (9) are respectively disposed at both ends of said heat exchange slot (5) with respect to the extension direction of said combustion chamber body.

5. A rocket engine heat exchanger according to claim 2, wherein the flow direction of said pressurized working medium in said heat exchange slot (5) is opposite to the flow direction of the combustion gas in said combustion chamber (1).

6. A rocket engine heat exchanger according to claim 3 wherein said first collector (4) is provided with flow control elements controlling the flow of said pressurized working medium.

7. A rocket engine heat exchanger according to claim 3 wherein said second manifold (9) is provided with pressure control elements for controlling the pressure of said pressurized working medium.

8. A rocket engine heat exchanger according to any one of claims 1-7, wherein said outer layer structure (2) is arranged at the circumferential periphery of said combustion chamber body, and said heat exchanging space surrounds an annular space arranged in the direction of extension of said combustion chamber body.

9. A rocket engine heat exchanger as recited in claim 1, wherein: the combustion chamber body is made of copper, copper alloy, stainless steel or high-temperature alloy.

10. An aerospace vehicle comprising a rocket engine heat exchanger as recited in any one of claims 1-9.

Technical Field

The invention relates to the technical field of aerospace, in particular to a rocket engine heat exchanger and an aerospace craft.

Background

Disclosure of Invention

Therefore, the invention aims to solve the technical problem of overcoming the defects that when the heat exchanger is arranged at the exhaust outlet of the turbine of the rocket engine in the prior art, the whole structure of the rocket engine is complex, the weight is heavy, and the thrust-mass ratio performance of the rocket engine is poor, so that the heat exchanger of the rocket engine and the aerospace craft are provided.

The embodiment of the invention provides a heat exchanger of a rocket engine, wherein the rocket engine comprises a combustion chamber body with a combustion chamber, and the heat exchanger is characterized in that an outer layer structure is arranged on the outer wall of the combustion chamber body, and a heat exchange space allowing a pressurized working medium to exchange heat with the combustion chamber is formed between the outer layer structure and the combustion chamber body; the heat exchanger also comprises an inlet structure and an outlet structure which are communicated with the heat exchange space to enter and exit the pressurized working medium.

Optionally, a plurality of spacing structures extending along the extending direction of the combustion chamber body are arranged in the heat exchange space, and the spacing structures are arranged between the outer layer structure and the combustion chamber body to space the heat exchange space into a plurality of heat exchange grooves.

Optionally, the heat exchanger comprises a first collector and a second collector, one end of the first collector is communicated with all the heat exchange slots, and the other end of the first collector is communicated with the inlet structure; one end of the second collector is communicated with all the heat exchange grooves, and the other end of the second collector is communicated with the outlet structure.

Optionally, the first collector and the second collector are respectively disposed at two ends of the heat exchange slot relative to the extending direction.

Optionally, the flow direction of the pressurized working medium in the heat exchange groove is opposite to the flow direction of the fuel gas in the combustion chamber.

Optionally, the first collector is provided with a flow control element for controlling the flow of the pressurized working medium.

Optionally, a pressure control element for controlling the pressure of the pressurized working medium is arranged on the second collector.

Optionally, the outer layer structure is arranged on the circumferential periphery of the combustion chamber body, and the heat exchange space surrounds an annular space arranged in the extending direction of the combustion chamber.

Optionally, the exterior of the combustion chamber body is made of copper, copper alloy, stainless steel or high temperature alloy.

The embodiment of the invention also provides a space craft which comprises the rocket engine heat exchanger.

Compared with the prior art, the technical scheme of the invention has the following advantages:

1. the embodiment of the invention provides a heat exchanger of a rocket engine, wherein the rocket engine comprises a combustion chamber body with a combustion chamber, the outer wall of the combustion chamber body is provided with an outer layer structure, and a heat exchange space allowing a pressurized working medium to exchange heat with the combustion chamber is formed between the outer layer structure and the combustion chamber body; the heat exchanger also comprises an inlet structure and an outlet structure which are communicated with the heat exchange space to enter and exit the increased working medium. According to the embodiment of the invention, the heat exchange space allowing the supercharged working medium to exchange heat with the combustion cavity is formed between the outer layer structure arranged on the outer wall of the combustion chamber body and the combustion chamber body, so that a heat exchanger device specially designed for a rocket tank supercharging system on the engine is omitted, the structural quality of the engine is reduced, and the thrust ratio performance of the engine is improved. The parts of the engine are simplified, and the structural reliability of the heat exchanger is improved.

2. According to the embodiment of the invention, the heat exchange space for heat exchange is formed between the outer layer structure of the outer wall of the combustion chamber body and the combustion chamber body, so that the resonance problem caused by the adoption of a spiral tube structure in the traditional rocket engine heat exchanger is fundamentally eliminated, and the reliability of the heat exchanger structure is greatly enhanced.

3. According to the embodiment of the invention, the heat exchange space and the combustion chamber are combined to form the heat exchanger, so that the temperature resistance of the combustion chamber is improved, the pressure resistance of the cavity is enhanced, and the structural strength is better.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

FIG. 1 is a cross-sectional view of a heat exchanger according to an embodiment of the present invention;

FIG. 2 is a cross-sectional view of a heat exchanger according to an embodiment of the present invention;

fig. 3 is a schematic structural view of a gas generator according to an embodiment of the present invention.

Description of reference numerals:

1-a combustion chamber; 2-combustion chamber wall; 3-outer layer structure; 4-a first collector; 5-a heat exchange tank; 6-inlet structure; 7-a gas injector; 8-a gas turbine; 9-a second collector; 10-an outlet configuration; 11-spacer structure.

Detailed Description

The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

Rocket motors powered by liquid rocket motors require that the liquid rocket motor be supplied with propellant, typically both oxidant and fuel, from a propellant reservoir on the rocket. The propellant in the tank requires a certain pressure to supply the engine and therefore the tank requires a pressurisation system to pressurise the propellant in the tank. In two major system schemes of special working medium pressurization and autogenous pressurization which are frequently adopted at present, the pressurization working medium usually needs to exchange heat through a heat exchanger arranged in an engine system, and the temperature of the pressurization working medium is increased, the density is reduced, and the power-applying capacity is enhanced after heat exchange, so that the requirement of pressurizing a storage tank is met. The working fluid for pressurization can be propellant (including oxidant and fuel) for the engine, and can also be inert gas such as nitrogen, helium and the like. The device used for realizing the heat exchange and temperature rise of the supercharged working medium on the engine is the heat exchanger. The fuel gas generator provided by the embodiment of the invention can be suitable for any liquid rocket engine, a heat exchanger device specially designed for a rocket storage tank pressurization system on the engine is omitted, and the working reliability of the engine is improved. .

As shown in fig. 1 to 3, an embodiment of the present invention provides a rocket engine heat exchanger in which a rocket engine integrally includes a gas injector 7, a combustor, and a gas turbine 8. A gas injector 7 is provided above the combustion chamber for supplying fuel and oxidant thereto, and a gas turbine 8 is provided below the combustion chamber for converting the enthalpy and kinetic energy of the gas into mechanical energy.

The combustion chamber comprises a combustion chamber body with a combustion chamber 1, an outer structure 3, an inlet structure 6 and an outlet structure 10, as well as a first collector 4 and a second collector 9. The combustion chamber body has combustion chamber 1, and outer skin 3 locates combustion chamber body circumference periphery. The heat exchange space is an annular space which is formed by surrounding the outer structure 3 and the outer structure 3 of the combustion chamber body and surrounds the extending direction of the combustion chamber body, and is used for heat exchange between the pressurized working medium and the combustion chamber 1. The inlet structure 6 and the outlet structure 10 are both communicated with the heat exchange space and used for the inlet and outlet of the pressurizing working medium. The first collector 4 and the second collector 9 are respectively arranged at two ends of the heat exchange grooves 5 relative to the extending direction of the combustion chamber body, one end of the first collector 4 is communicated with all the heat exchange grooves 5, the other end of the first collector is communicated with the inlet structure 6, and one end of the second collector is communicated with all the heat exchange grooves 5, and the other end of the second collector is communicated with the outlet structure 10.

The embodiment of the invention is used for heat exchange between the pressurizing working medium and the combustion chamber 1 through the heat exchange space arranged between the outer layer structure and the combustion chamber body, thereby omitting a heat exchanger device specially designed for a rocket tank pressurizing system on the engine in the prior art, lightening the structural quality of the engine, improving the thrust-mass ratio performance of the engine and simplifying the parts of the engine. The heat exchange space is combined with the combustion chamber, so that the temperature resistance of the combustion chamber is improved, the combustion chamber in the prior art is usually set to be a single wall, and in the embodiment of the invention, the outer layer structure 3 is additionally arranged on the periphery of the combustion chamber body in the circumferential direction, so that the whole pressure resistance and structural strength of the combustion chamber are improved.

Be provided with a plurality of interval structures 11 that extend along combustion chamber body extending direction in the heat transfer space, interval structures 11 and outer layer structure 3 closely laminate to be a plurality of heat transfer grooves 5 with the heat transfer space interval. The flow direction of the pressurizing working medium in the heat exchange groove 5 is opposite to the flow direction of the fuel gas in the combustion cavity 1.

According to the embodiment of the invention, the plurality of spacing structures 11 extending along the extending direction of the combustion chamber body are arranged in the heat exchange space, and the spacing structures 11 are tightly attached to the outer layer structure 3, so that the spacing structures 11 can support the heat exchange space between the combustion chamber 1 and the outer layer structure 3 of the combustion chamber in the working process of the combustion chamber, the overall pressure resistance and structural strength of the combustion chamber are further improved, and the structural reliability of the heat exchange space is improved.

In the practical application process, the inlet structure 6 arranged on the first collector 4 is opened, and the outlet structure 10 arranged on the second collector 9 is closed, so that the pressurizing working medium can be introduced from the inlet structure 6 of the first collector 4 to fill the cavity of the whole heat exchange space. The pressurizing working medium can be a propellant for an engine, and can also be inert gases such as nitrogen, helium and the like.

During high-temperature operation of the combustion chamber, the pressurized working medium flows in continuously from the first collector 4 located below the combustion chamber and flows out continuously from the second collector 9 located above the combustion chamber. Because the flow direction of the pressurizing working medium in the heat exchange groove 5 is opposite to the flow direction of the fuel gas in the combustion chamber 1, the heat emitted by fuel combustion can be fully absorbed through the wall 2 of the combustion chamber in the flowing process of the pressurizing working medium, and the temperature of the pressurizing working medium is increased, the density is reduced and the acting capacity is enhanced after heat exchange, so that the requirement of pressurizing the storage tank is met.

In conclusion, the embodiment of the invention adopts the rocket engine combustion chamber, so that the problem of resonance caused by the adoption of a spiral tube structure in the heat exchanger of the traditional rocket engine can be fundamentally solved, and the reliability of the heat exchanger is greatly enhanced. The heat exchanger specially designed for the rocket tank supercharging system on the engine in the prior art is omitted, the structural mass of the engine is reduced, the weight of the engine can be reduced by 2 kg-10 kg, and the mass-to-mass ratio performance of the engine is improved. The pressurizing working medium is introduced into the heat exchange space between the combustion chamber body and the outer layer structure 3, so that the temperature resistance of the combustion chamber of the gas generator is improved, the limit range of the gas temperature is increased, and the gas temperature can be increased to more than 1500K. Therefore, the working capacity of the fuel gas is enhanced, and the overall performance of the engine is improved.

The embodiment of the invention is also provided with a first filler neck at the inlet structure 6 and a second filler neck at the outlet structure 10, wherein the first filler neck and the second filler neck are used for connecting with pipelines of other equipment. The first collector 4 is provided with a flow control element for controlling the flow of the pressurizing working medium, and the second collector 9 is provided with an air pressure element for controlling the pressure of the pressurizing working medium, so as to ensure that the pressure of the pressurizing working medium in the heat exchange space is higher than the critical pressure of the pressurizing working medium.

The wall of the combustion chamber is made of metal materials with high heat conductivity, such as copper and copper alloy, or stainless steel, high-temperature alloy and the like. The thickness of the combustion chamber wall 2 is generally 0.5 mm-1 mm, the width of the spacing structure 11 is generally 2 mm-6 mm, and the height is generally 2 mm-8 mm. The outer layer structure 3 can be made of stainless steel or high-temperature alloy materials, and the thickness is generally 2 mm-6 mm.

The embodiment of the invention also provides a space craft which comprises the rocket engine heat exchanger provided in the embodiment.

The embodiment of the invention also provides a technological method of the rocket engine heat exchanger, and the specific technological method parameters are as follows:

1. before the diffusion brazing of the combustion cavity wall 2 and the outer layer structure 3 of the combustion chamber, silver is plated on the outer surface of the spacing structure 11, and the thickness is 2-3 mu m;

2. plating nickel on the inner surface of the outer layer structure 3 with the thickness of 2 mu m, and plating copper with the thickness of 2 mu m-3 mu m;

3. aligning and assembling the combustion chamber and the outer layer structure 3, and plugging two ends by argon arc welding;

4. welding the first collector 4 and the second collector 9 on corresponding positions of the outer layer structure 3 in an argon arc welding mode;

5. respectively welding a first filler neck and a second filler neck on corresponding positions of a first collector 4 and a second collector 9 in an argon arc welding mode;

6. and (3) feeding the product into a vacuum brazing furnace, vacuumizing the heat exchange space through the first filler pipe nozzle and the second filler pipe nozzle, wherein the vacuum degree is 1-2 x 10 < -2 > mmHg, and keeping the pressure in the vacuum brazing furnace at 1-2 x 10 < -1 > mmHg.

7. The vacuum furnace was pressurized with argon and heated. Keeping the pressure at 0.45 +/-0.01 MPa, gradually raising the temperature from the normal temperature to 760 ℃, raising the temperature for 70min, raising the temperature to 960 ℃ after 40min, keeping the temperature at 960 +/-10 ℃ for 30 min-35 min;

8. gradually cooling from 960 deg.C to 200 deg.C for 50min, and air cooling to room temperature;

9. and carrying out 30MPa hydraulic test on the heat exchange space through the first filler neck and the second filler neck, wherein the hydraulic test time is not less than 10 min. And after the hydraulic test, a heat exchange space water flow resistance test can be carried out according to the use requirement, and the product production is completed after the test is qualified.

Heat exchanger heat balance formula: q is Q_w＝Q_g，Q_lFor convective heat transfer density, Q, in the heat transfer space_wIs the heat-conducting heat flux, Q, of the combustion chamber wall_gThe heat flux density is the convective heat transfer of the fuel gas.

It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.