A gas-liquid composite drive pre-compression turbo pump structure and pre-compression turbo pump driving method
The technology of a turbo pump and a pre-pressing pump is applied in the field of the structure of a gas-liquid composite drive pre-pressing turbo pump, which can solve the problems of reducing the working reliability of the engine, and achieve the effects of improving the starting quality, ensuring the feasibility and improving the working reliability.
Active Publication Date: 2020-06-30
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology
For high-altitude two-stage engines, since the engine inlet pressure is lower, the inlet pressure of the main pump will drop even lower during the start-up period, which reduces the reliability of the engine operation
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[0023] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.
[0024] Such as figure 1 , figure 2 as shown, figure 1 It is a partial view of the structure of the gas-liquid composite drive pre-compression turbo pump of the present invention, figure 2 yes figure 1 Front view of Part 1. The structure of a gas-liquid compound driven pre-compression turbo pump proposed by the present invention is an annular nozzle ring, and the pre-compression turbine is behind the nozzle ring.
[0025] The pre-compression turbo pump structure includes a nozzle ring (1) and a pre-compression turbine blade (2), and the nozzle ring (1) is provided with a gas nozzle (3) and a liquid nozzle (4), respectively injecting high-pressure gas and high-pressure liquid; The gas nozzle (3) is a contraction expansion nozzle, and the liquid nozzle (4) is a contraction nozzle;
[0026] The high-pressure liquid and the high-pre...
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The invention relates to a gas-liquid combined driving pre-pressure turbine pump structure and a pre-pressure turbine pump driving method. The gas-liquid combined driving pre-pressure turbine pump structure and the pre-pressure turbine pump driving method are suitable for a self-starting pump pressure type liquid rocket engine. By means of the gas-liquid combined driving pre-pressure turbine pumpstructure and the pre-pressure turbine pump driving method, a pre-pressure turbine pump can be started in advance in the starting stage of the engine, and inlet pressure of a main pump in the startingstage of the engine is improved, so that the starting characteristic of the low inlet pressure of the engine is improved. The gas-liquid combined driving pre-pressure turbine pump is characterized inthat a pre-pressure turbine is driven by a high-pressure liquid and high-temperature fuel gas to drive a pre-pressure pump to rotate and realize pressurizing. A gas turbine and a liquid turbine shareone turbine rotor. In the starting stage of the engine, the high-pressure liquid after the main pump is used to start the pre-pressure turbine in advance, the inlet pressure of the main pump is increased, the cavitation degree of the main pump is reduced, and after the pre-pressure turbine pump reaches a certain rotating speed, a driving liquid path is closed, the high-temperature fuel gas startsto drive the pre-pressure turbine pump, and the working reliability of the engine starting stage is improved. The pre-pressure turbine pump structure is already verified and tested on a product witha good effect.
Description
technical field [0001] The invention relates to a gas-liquid composite drive pre-compression turbine pump structure, which belongs to the technical field of fluid machinery. Background technique [0002] my country's new generation of liquid rocket engines generally adopt propellant delivery pre-compression technology. The propellant is pre-pressurized by the pre-compression pump to ensure that the main pump does not suffer from cavitation under the lower pressure of the storage tank. When the engine is in the starting stage, the speed of the pre-pressure turbo pump is a process of gradual increase, and it exists as a flow resistance element within a certain period of time, and its flow resistance will cause the inlet pressure of the main pump to decrease. For high-altitude two-stage engines, since the engine inlet pressure is lower, the inlet pressure of the main pump will drop even lower during the start-up period, which reduces the reliability of engine operation. Cont...
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IPC IPC(8): F02K9/46F02K9/52
CPCF02K9/46F02K9/52
Inventor 袁伟为王晓锋苗旭升李惠敏李春乐毛凯蒋建园王飞
Owner XIAN AEROSPACE PROPULSION INST