阅读说明：本技术 一种用于火箭发动机涡轮泵的循环预冷系统及火箭 (Circulating precooling system for rocket engine turbine pump and rocket ) 是由 张玺 魏一 彭小波 于 2019-09-12 设计创作，主要内容包括：本发明提供一种用于火箭发动机涡轮泵的循环预冷系统,通过起动器向涡轮通入高压气体以吹动涡轮旋转,从而带动第一泵和第二泵旋转,使第一泵、燃料贮箱及相关的输送通道内部产生压力差,第二泵、助燃剂贮箱及相关的输送通道内部产生压力差。在压力差的作用下,低温燃料从燃料贮箱进入第一泵,预冷完成后返回至燃料贮箱；低温助燃剂从助燃剂贮箱进入第二泵进行预冷,预冷完成后返回至助燃剂贮箱。本发明利用火箭内部原有装置对涡轮泵进行预冷,没有额外设置预冷循环泵或电机等其他设备,使涡轮泵充分预冷的同时,降低了系统的复杂性和制造成本,并有利于火箭减重,从而提高火箭的总体性能。(The invention provides a circulating precooling system for a rocket engine turbine pump, which is characterized in that high-pressure gas is introduced into a turbine through a starter to blow the turbine to rotate, so that a first pump and a second pump are driven to rotate, pressure difference is generated in the first pump, a fuel storage tank and a related conveying channel, and pressure difference is generated in the second pump, a combustion improver storage tank and the related conveying channel. Under the action of pressure difference, low-temperature fuel enters a first pump from a fuel storage tank, and returns to the fuel storage tank after precooling is completed; and the low-temperature combustion improver enters the second pump from the combustion improver storage tank for precooling, and returns to the combustion improver storage tank after precooling is finished. The invention utilizes the original device in the rocket to pre-cool the turbopump, and other devices such as a pre-cooling circulating pump or a motor are not additionally arranged, so that the complexity and the manufacturing cost of the system are reduced while the turbopump is fully pre-cooled, and the weight of the rocket is reduced, thereby improving the overall performance of the rocket.)

1. A circulating precooling system for a rocket engine turbo pump comprises a first pump, a second pump and a turbine which are arranged in a rocket engine, wherein the turbine is used for driving the first pump and the second pump to operate, and is characterized by also comprising,

the starter is provided with an air outlet which is communicated with the air inlet end of the turbine so that the high-pressure gas in the starter pushes the turbine to rotate;

the fuel storage tank is provided with a first outlet and a first inlet, the first outlet is communicated with a first liquid inlet end of the first pump, and a first liquid outlet end of the first pump is communicated with the first inlet;

and the combustion improver storage box is provided with a second outlet and a second inlet, the second outlet is communicated with a second liquid inlet end of the second pump, and a second liquid outlet end of the second pump is communicated with the second inlet.

2. The system according to claim 1, wherein the first pump includes a first housing, a first central rotating shaft disposed in the first housing, and a plurality of first vanes disposed on the first central rotating shaft, the first liquid inlet end is disposed on the first housing and located on an axial direction of the first central rotating shaft, and the first liquid outlet end is disposed on the first housing near an edge of the first vanes.

3. The system according to claim 1 or 2, wherein the second pump includes a second housing, a second central rotating shaft disposed in the second housing, and a plurality of second blades disposed around the second central rotating shaft, the second liquid inlet end is disposed on the second housing and located in an axial direction of the second central rotating shaft, and the second liquid outlet end is disposed on the second housing near an edge of the second blade.

4. The system according to any one of claims 1 to 3, wherein the turbine includes a third housing, a third central rotating shaft disposed in the third housing, and a plurality of third blades disposed thereon around the third central rotating shaft, and the air inlet end is disposed on the third housing near an edge of the third blades.

5. The system of claim 4, wherein the turbine further comprises a gas outlet disposed on the third housing and axially located with respect to the third central rotational axis, so as to allow high-pressure gas to be discharged from the turbine.

6. The cyclical pre-cooling system of claim 4, wherein the first, second and third central rotational axes are a same central rotational axis;

the first shell, the second shell and the third shell are not communicated with each other.

7. The system according to any one of claims 1 to 6, wherein a first temperature detecting unit is disposed in the first housing to measure a temperature of the first pump;

and a second temperature detection unit is arranged in the second shell to measure the temperature of the second pump.

8. The system according to any one of claims 1 to 7, wherein at least a first rotating unit comprising a plurality of second blades and a second rotating unit comprising a plurality of second blades are disposed at intervals on the second central rotating shaft along an axial direction of the second central rotating shaft, the second liquid inlet end is disposed near the second rotating unit, and the second liquid outlet end is disposed near edges of the blades in the first rotating unit.

9. The system according to claim 1 or 2, wherein a first valve is disposed between the turbine and a starter to control the high-pressure gas to enter the turbine from the starter;

the starter is also provided with an inflation inlet so that gas can be inflated into the starter through the inflation inlet.

10. A rocket comprising a recirculating precooling system of any one of claims 1-9.

Technical Field

The invention relates to the field of circulating refrigeration of space equipment, in particular to a circulating precooling system for a turbo pump of a rocket engine and a rocket.

Background

The pump rocket engine is a jet engine with propellant and no outside air. The propellant is converted into the kinetic energy of the working medium in the rocket engine to form high-speed jet flow to be discharged so as to generate thrust. The turbo pump is the heart part of the rocket engine and consists of a turbine and a pump. The turbine and the pump are generally directly connected, and the turbine drives the pump to rotate so as to pressurize the liquid propellant.

The pump type rocket engine needs to be precooled before starting, namely, the engine (mainly a turbopump) and a conveying system thereof are cooled by using a propellant or other low-temperature media so as to reach the temperature required by starting the engine and ensure the safe operation of the turbopump. When precooling is not carried out or precooling is not sufficient, the propellant is heated in a conveying pipeline and an engine flow passage and is strongly vaporized, so that a turbine pump of the engine generates cavitation and flying rotation, fluctuation of pressure and flow, stall operation, oxygen-enriched combustion and the like are caused, the starting time and the thrust climbing time of the engine are prolonged, and complete failure of starting can be caused in severe cases. It is therefore important to adequately warm up the engine and its delivery system before ignition of the engine.

The precooling mode of the turbopump mainly comprises discharge precooling or circulating precooling, and the circulating precooling can be divided into natural circulating precooling and forced circulating precooling. The effect of forced circulation precooling is best, so that forced circulation precooling is generally performed by arranging a precooling circulating pump at present. The pre-cooling circulating pump is an independent component specially arranged for pre-cooling, is only used before the engine is started, and needs to be additionally provided with a motor or a turbine as power, so that the complexity of the system is increased.

Disclosure of Invention

Therefore, the technical problem to be solved by the invention is to overcome the defect that the complexity of the system is increased because additional equipment needs to be arranged for circulating precooling of the turbopump of the rocket engine, so that the circulating precooling system for the turbopump of the rocket engine and the rocket are provided.

Therefore, the technical proposal adopted by the application is that,

the application provides a circulating precooling system for a rocket engine turbine pump, which comprises a first pump, a second pump and a turbine which are arranged in a rocket engine, wherein the turbine is used for driving the first pump and the second pump to operate, and the circulating precooling system also comprises a first pump, a second pump and a turbine,

the starter is provided with an air outlet which is communicated with the air inlet end of the turbine so that the high-pressure gas in the starter pushes the turbine to rotate;

the fuel storage tank is provided with a first outlet and a first inlet, the first outlet is communicated with a first liquid inlet end of the first pump, and a first liquid outlet end of the first pump is communicated with the first inlet;

and the combustion improver storage box is provided with a second outlet and a second inlet, the second outlet is communicated with a second liquid inlet end of the second pump, and a second liquid outlet end of the second pump is communicated with the second inlet.

Further, first pump includes first casing, set up in first central axis of rotation in the first casing and center on first central axis of rotation sets up a plurality of first blades on it, first feed liquor end set up in be located on the first casing in the axial of first central axis of rotation, first play liquid end is close to the edge setting of first blade on the first casing.

Further, the second pump includes the second casing, set up in second center axis of rotation in the second casing and center on the central axis of rotation of second sets up a plurality of second blades on it, the second feed liquor end set up in on the second casing and be located in the axial of the central axis of rotation of second, the second goes out the liquid end and is close to the edge setting of second blade on the second casing.

Further, the turbine comprises a third shell, a third central rotating shaft arranged in the third shell and a plurality of third blades arranged on the third central rotating shaft in a surrounding mode, and the edge, close to the third blades, of the air inlet end is arranged on the third shell.

Further, the turbine further comprises an air outlet end, wherein the air outlet end is arranged on the third shell and is positioned in the axial direction of the third central rotating shaft, so that high-pressure air is discharged from the turbine.

Furthermore, the first central rotating shaft, the second central rotating shaft and the third central rotating shaft are the same central rotating shaft;

the first shell, the second shell and the third shell are not communicated with each other.

Further, a first temperature detection unit is arranged in the first shell to measure the temperature of the first pump; and a second temperature detection unit is arranged in the second shell to measure the temperature of the second pump.

Further, follow on the axial direction of second center axis of rotation the second center axis of rotation goes up at least the interval and sets up the first rotation unit that constitutes by a plurality of second blades and the second rotation unit that constitutes by a plurality of second blades, the second feed liquor end is close to the second rotation unit sets up, the second goes out the liquid end and is close to blade edge setting in the first rotation unit.

Further, a first valve is arranged between the turbine and a starter to control high-pressure gas to enter the turbine from the starter;

the starter is also provided with an inflation inlet so that gas can be inflated into the starter through the inflation inlet.

The application provides a rocket, and the circulating precooling system is adopted.

The technical scheme of the invention has the following advantages:

1. the invention provides a circulating precooling system for a rocket engine turbine pump, wherein a gas outlet is formed in a starter and is communicated with a gas inlet end of a turbine so as to enable high-pressure gas in the starter to push the turbine to rotate; the fuel storage tank is provided with a first outlet and a first inlet, the first outlet is communicated with a first liquid inlet end of the first pump, and a first liquid outlet end of the first pump is communicated with the first inlet; and the combustion improver storage tank is provided with a second outlet and a second inlet, the second outlet is communicated with a second liquid inlet end of the second pump, and a second liquid outlet end of the second pump is communicated with the second inlet. High-pressure gas is introduced into the turbine through the starter to blow the turbine to rotate, so that the first pump and the second pump are driven to rotate, pressure difference is generated in the first pump, the fuel storage tank and the related conveying channel, and pressure difference is generated in the second pump, the combustion improver storage tank and the related conveying channel. Under the action of pressure difference, low-temperature fuel flows out of a first outlet of the fuel storage tank and enters a first pump through a first liquid inlet end of the first pump for precooling, then flows out of a first liquid outlet end of the first pump and returns to the fuel storage tank through a first inlet of the fuel storage tank, and the first pump is enabled to precool to the temperature required by starting of the engine; and the low-temperature combustion improver flows out from a second outlet of the combustion improver storage box and enters a second pump for precooling through a second liquid inlet end of the second pump, then flows out from a second liquid outlet end of the second pump and returns to the combustion improver storage box through a second inlet of the combustion improver storage box, so that the second pump is precooled to the temperature required by the starting of the engine. Wherein, the starter, the fuel storage tank and the combustion improver storage tank are all original devices arranged in the rocket. The invention utilizes the original device in the rocket to pre-cool the turbopump, and other devices such as a pre-cooling circulating pump or a motor are not additionally arranged, so that the complexity and the manufacturing cost of the system are reduced while the turbopump is fully pre-cooled, and the weight of the rocket is reduced, thereby improving the overall performance of the rocket.

2. According to the circulating precooling system for the rocket engine turbine pump, the low-temperature fuel precools the first pump and returns the first pump to the fuel storage tank, and heat in the first pump is transferred to the fuel; similarly, the low-temperature combustion improver precools the second pump and returns the second pump to the combustion improver storage box, and heat in the second pump is transferred to the combustion improver. When the rocket engine works, fuel and combustion improver respectively flow out of the fuel storage tank and the combustion improver storage tank, enter the thrust chamber, are violently combusted and converted into high-temperature and high-pressure gas, and are accelerated into supersonic airflow to be sprayed out, so that thrust acting on the rocket engine is generated, and the rocket is pushed to advance. The invention converts the heat in the first pump and the second pump into the thrust of the engine, thereby realizing the full utilization of the heat.

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 schematic structural diagram of a circulation precooling system of a turbo pump in embodiment 1 of the invention;

FIG. 2 is a schematic structural view of a turbo pump in embodiment 1 of the invention;

reference numerals:

1-a first pump; 1-1-a first liquid inlet end; 1-2-a first liquid outlet end; 2-a second pump; 2-1-a second liquid inlet end; 2-2-second liquid outlet end; 3-a turbine; 3-1-an air inlet end; 3-2-air outlet end; 4-a starter; 4-1-gas outlet; 4-2-inflation inlet; 5-a fuel storage tank; 5-1-a first outlet; 5-2-a first inlet; 6-combustion improver storage box; 6-1-a second outlet; 6-2-a second inlet; 7-first valve.

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.