Closed combustion chamber air exhaust circulation liquid rocket engine

Abstract

The invention discloses a closed combustion chamber air exhaust circulation liquid rocket engine which comprises a thrust chamber, a turbine pump and an electric pump. The thrust chamber is composed of an inner wall and an outer wall, a cooling channel of the cavity is formed between the inner wall and the outer wall, and a thermoelectric power generation piece is arranged in the cooling channel. According to the invention, the great temperature difference between liquid oxygen and the high-temperature thrust chamber is utilized, so that the thermoelectric power generation sheet provides lasting electric energy for the electric pump, effective recycling of waste heat is realized, heat energy is directly converted into electric energy, the energy utilization efficiency is remarkably improved, and the dependence on an external power supply is reduced; efficient energy interaction circulation is formed among the turbine pump, the electric pump and the thermoelectric power generation piece, the requirement for external energy is reduced, the overall mass of a rocket is reduced, the compactness and reliability of an engine system are improved, and light-weight and high-reliability system design is achieved.

Description

Technical Field

[0001] The invention relates to a liquid rocket engine, in particular to an electric flame cooker. Background Art

[0002] The main components of the existing gas generator cycle liquid rocket engine are: gas generator and accessories, combustion chamber and turbo pump. The gas generator is equivalent to a small liquid rocket engine, which requires special valves, pipelines, injectors, combustion chambers and igniters, etc. The structure is complex and the reliability is poor.

[0003] The invention patent with application number 202211018754.0 abandoned the gas generator and made further improvements, directly taking out the gas from the combustion chamber to drive the turbine. At present, this technical solution is applied to open rockets. However, the rich fuel gas of open rockets drives the turbine and is directly discharged to the outside, which causes energy waste and affects the improvement of rocket specific impulse. At the same time, the rich fuel gas is discharged to the outside, which is also prone to accidental ignition risk.

[0004] Therefore, how to reintroduce these seemingly exhaust-rich fuel gases into the high-pressure combustion chamber for re-combustion is a technical problem that needs to be solved at this stage. At the same time, how to achieve rocket lightweighting is also a technical problem that technicians in this field need to solve at this stage. Summary of the invention

[0005] In order to overcome the above-mentioned shortcomings, the present invention aims to provide a technical solution that can solve the above-mentioned problems.

[0006] A closed combustion chamber exhaust circulation liquid rocket engine, comprising: a thrust chamber, a turbo pump, and an electric pump; the thrust chamber is composed of an inner wall and an outer wall, a cooling channel with a cavity is formed between the inner wall and the outer wall, and the cooling channel is connected to the oxygen pump outlet through an oxygen pipe; a thermoelectric power generation sheet is arranged in the cooling channel, the hot end of the thermoelectric power generation sheet is attached to the inner wall, and the input end of the cooling channel is connected to the oxygen pump output end of the turbo pump; the thermoelectric power generation sheet is electrically connected to the electric pump to provide a stable power supply for the electric pump; the thrust chamber is arranged from top to bottom according to the The second is a fuel injector, a combustion chamber and a tail nozzle. The fuel injector is composed of a shell with an internal cavity, a rich-fuel nozzle penetrating the upper and lower parts of the shell, and an air extraction port. The air extraction port is also provided with a plurality of fuel injection holes, which connect the air extraction port with the inside of the shell, and the shell input end is connected with the fuel pump output end of the turbine pump. The air extraction port output end is connected with the vortex inlet of the turbine pump through an electric pump, and the turbine in the vortex is driven by the rich-fuel gas led out of the air extraction port. After the gas drives the turbine, it is injected into the combustion chamber through the rich-fuel nozzle on the fuel injector. Preferably, the combustion chamber is also equipped with an oxidant injector communicated with the cooling channel; Preferably, an inverter circuit is connected in series between the temperature difference power generation sheet and the electric pump to provide driving AC power for the electric pump; Preferably, the temperature difference power generation sheet is a ring-shaped structure, which is arranged around the inner wall of the thrust chamber; Preferably, thermal conductive silicone grease is provided between the hot end of the temperature difference power generation sheet and the inner wall, so as to improve the thermal conductivity effect; Preferably, the cold end of the thermoelectric generator sheet is provided with a plurality of heat dissipation fins, thereby increasing the contact area between the cold end of the thermoelectric generator sheet and the liquid oxygen in the cooling channel, thereby improving the heat dissipation capacity.

[0007] Compared with the prior art, the advantages of the present invention are: The present invention utilizes the great temperature difference between liquid oxygen and the high-temperature thrust chamber to enable the thermoelectric generator to provide long-lasting electric energy for the electric pump, thereby realizing the effective recovery and reuse of waste heat, directly converting thermal energy into electric energy, and significantly improving energy utilization efficiency. The invention forms a highly efficient energy interactive cycle between the turbo pump, electric pump and temperature difference power generation sheet, reduces the demand for external energy through the rational distribution and utilization of energy, reduces the overall mass of the rocket, improves the compactness and reliability of the engine system, and realizes a lightweight and high-reliability system design.

[0008] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0010] Figure 1 It is a structural schematic diagram of the present invention.

[0011] Figure 2 It is a cross-sectional schematic diagram of the fuel injector of the present invention.

[0012] Figure 3 It is a schematic diagram of the structure of the temperature difference power generation sheet of the present invention. DETAILED DESCRIPTION

[0013] The technical solutions in the embodiments of the present invention are described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0014] In the description of the present invention, it should be noted that the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention.

[0015] In addition, in the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", etc. should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, it can also be the internal communication of two components, it can be a wireless connection, or it can be a wired connection. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0016] In addition, the technical features involved in the different embodiments of the present invention described later can be combined with each other as long as they do not conflict with each other.

[0017] See also Figure 1 to Figure 3 In the embodiment of the present invention, a closed combustion chamber 12 exhaust cycle liquid rocket engine includes: a thrust chamber 1, a turbo pump 2, and an electric pump 3; the thrust chamber 1 is composed of an inner wall 15 and an outer wall 17, a cooling channel 16 with a cavity is formed between the inner wall 15 and the outer wall 17, and the cooling channel 16 is connected to the outlet end of the oxygen pump 21 through an oxygen pipe; a thermoelectric power generation sheet 4 is provided in the cooling channel 16, the hot end of the thermoelectric power generation sheet 4 is attached to the inner wall 15, and the input end of the cooling channel 16 is connected to the output end of the oxygen pump 21 of the turbo pump 2; the thermoelectric power generation sheet 4 is electrically connected to the electric pump 3, and the electric pump 3 Provide stable electric energy; inside the thrust chamber 1 are, from top to bottom, a fuel injector 11, a combustion chamber 12 and a tail nozzle 13; the fuel injector 11 consists of a shell 111 with an internal cavity, a rich-fuel nozzle 112 penetrating the upper and lower parts of the shell 111, and an air suction port 113; the air suction port 113 is also provided with a plurality of fuel spray holes 1131, and the fuel spray holes 1131 connect the air suction port 113 with the inside of the shell 111, and the input end of the shell 111 is connected with the output end of the fuel pump 22 of the turbopump 2; the output end of the air suction port 113 is connected with the inlet of the vortex tube 23 of the turbopump 2 through the electric pump 3.

[0018] During the operation of the rocket engine of the present invention, the oxygen pump 21 inside the turbo pump 2 pressurizes the cryogenic liquid oxygen (usually at a low temperature of -183 degrees Celsius) and delivers it to the cooling channel 16 of the thrust chamber 1. The cooling channel 16 is composed of the inner wall 15 and the outer wall 17 of the thrust chamber 1, forming a cooling space for the thrust chamber 1 to dissipate heat and gasify the liquid oxygen.

[0019] Thermoelectric power generation sheets 4 are arranged around the inner wall 15 of the thrust chamber 1 in the cooling channel 16. Based on the Seebeck effect, electromotive force is generated at both ends of the thermoelectric power generation sheet 4 due to the significant temperature gradient (the hot end contacts the high-temperature combustion gas, the temperature can reach thousands of degrees Celsius, and the cold end contacts the low-temperature liquid oxygen), and then direct current is output. This direct current needs to be converted into alternating current that meets the working requirements of the electric pump 3 by the inverter circuit to provide a stable power drive for the electric pump 3.

[0020] At the same time, the fuel pump 22 delivers the fuel to the inner cavity of the fuel injector 11. The air extraction port 113 on the fuel injector 11 is provided with a plurality of fuel injection holes 1131. When the high-temperature and high-pressure gas flows through the air extraction port 113, the fuel is ejected from the injection holes. Based on the heat exchange principle, the fuel quickly absorbs the heat of the gas, realizes its own gasification process, and forms a room-temperature fuel-rich gas.

[0021] Driven by the pressure provided by the electric pump 3, the rich fuel gas enters the vortex tube 23, driving the turbine to rotate at a high speed. The rich fuel gas after doing work is injected into the combustion chamber 12 through the rich fuel nozzle 112.

[0022] At the same time, the gasified oxygen in the cooling passage 16 is injected into the combustion chamber 12 through the oxidant injector 14 and is mixed with the fuel-rich gas to burn.

[0023] The present invention realizes the effective recovery and reuse of waste heat of the inner wall 15, directly converts thermal energy into electrical energy, significantly improves energy utilization efficiency, and reduces dependence on external power sources.

[0024] The closed design of the present invention effectively reduces heat loss in the combustion chamber 12 and prevents leakage of combustible gases, provides a stable combustion environment, enables fuel and oxidant to be mixed and burned in a nearly ideal state, improves combustion efficiency, and enhances the overall performance of the engine.

[0025] The mixed combustion of the combustible gas and the combustion-supporting gas in the combustion chamber 12 is the most efficient mixed combustion mode.

[0026] In the next embodiment, the arrangement of the annular structure of the thermoelectric power generation sheet 4 and the heat dissipation fins 41 arranged at its cold end increase the contact area with the liquid oxygen, strengthen the convection heat transfer process, improve the heat dissipation efficiency, ensure the stability and reliability of the thermoelectric power generation sheet 4, and ensure the continuous and stable power generation process.

[0027] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above and that the present invention can be implemented in other specific forms without departing from the spirit or essential features of the present invention. Therefore, the embodiments should be considered exemplary and non-restrictive in all respects, and the scope of the present invention is defined by the appended claims rather than the above description, and it is intended that all changes falling within the meaning and scope of the equivalent elements of the claims be included in the present invention.

Claims

1. A closed combustion chamber exhaust cycle liquid rocket engine, comprising: Thrust chamber, turbine pump, electric pump, characterized in that: The thrust chamber is composed of an inner wall and an outer wall, a cooling channel of a cavity is formed between the inner wall and the outer wall, and the cooling channel is connected to the outlet end of the oxygen pump through an oxygen pipe; A thermoelectric power generation sheet is provided in the cooling channel, the hot end of the thermoelectric power generation sheet is attached to the inner wall, the input end of the cooling channel is connected to the oxygen pump output end of the turbo pump; the thermoelectric power generation sheet is electrically connected to the electric pump to provide a stable power supply for the electric pump; The inside of the thrust chamber is composed of a fuel injector, a combustion chamber and a tail nozzle from top to bottom. The fuel injector is composed of a shell with an internal cavity, a rich fuel nozzle and an air extraction port that penetrate the upper and lower parts of the shell; The air suction port is also provided with a plurality of fuel injection holes, which connect the air suction port with the interior of the shell, and the shell input end is connected with the fuel pump output end of the turbine pump; the air suction port output end is connected with the vortex inlet of the turbine pump through an electric pump, and the turbine in the vortex is driven by the rich fuel gas led out of the air suction port, and the fuel gas drives the turbine and is injected into the combustion chamber through the rich fuel nozzle on the fuel injector.

2. The closed combustion chamber exhaust cycle liquid rocket engine according to claim 1, characterized in that: The combustion chamber is also equipped with an oxidant injector which is in communication with the cooling channel.

3. The closed combustion chamber exhaust cycle liquid rocket engine according to claim 1, characterized in that: An inverter circuit is connected in series between the temperature difference power generation sheet and the electric pump to provide driving alternating current for the electric pump.

4. The closed combustion chamber exhaust cycle liquid rocket engine according to claim 1, characterized in that: The temperature difference power generation sheet is a ring-shaped structure, which is arranged around the inner wall of the thrust chamber.

5. The closed combustion chamber exhaust cycle liquid rocket engine according to claim 1, characterized in that: Thermal conductive silicone grease is also provided between the hot end of the temperature difference power generation sheet and the inner wall, thereby improving the thermal conductive effect.

6. The closed combustion chamber exhaust cycle liquid rocket engine according to claim 1, characterized in that: The cold end of the thermoelectric generator sheet is provided with a plurality of heat dissipation fins, thereby increasing the contact area between the cold end of the thermoelectric generator sheet and the liquid oxygen in the cooling channel, thereby improving the heat dissipation capacity.

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