Large-flow and high-power pre-pressing pump axial force balance structure and method
A technology of balanced structure and pre-pressurized pump, which is applied to parts, pumps, pump components, etc. of the pumping device used for elastic fluid. It can solve the problems of rotor structure damage, bearing damage, and affecting the normal operation of the engine, etc., and achieve the adjustment method Effective, good flow matching effect
Active Publication Date: 2020-05-08
XIAN AEROSPACE PROPULSION INST
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Problems solved by technology
After the pre-pressure pump spins, the rotor structure will generate a certain axial force under the action of the pressure field. If the axial force is too large, the rotor structure will be damaged and the bearing will be damaged, which will affect the normal operation of the engine.
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[0030] The present invention will be further described in detail through the drawings and examples below. Through these descriptions, the features and advantages of the present invention will become more apparent.
[0031] According to the first aspect of the present invention, such as figure 1 As shown, the present invention provides a large-flow and high-power preload pump axial force balance structure, the balance structure is located in the preload pump casing, including casing ribs 1, radial bearings 2, thrust bearings 5, And the preload pump rotor 6; wherein,
[0032] The preload pump is an axial flow pump. After the preload pump rotor 6 spins up, the propellant pressure at the inlet of the preload pump rotor is increased to the pressure at the outlet of the preload pump rotor. The two-point support of the radial bearing 2 and the thrust bearing 5 on the side, wherein the thrust bearing 5 bears the residual axial force of the preload pump rotor 6; the propellant at the...
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The invention provides a large-flow and high-power pre-pressing pump axial force balance structure and method. The balance structure is located in a pre-pressing pump casing and comprises a shell ribbed plate (1), a radial bearing (2), a thrust bearing (5) and a pre-pressing pump rotor (6), and can further comprise a balance drum (3) and a dual labyrinth seal part (4). The balance structure and method are provided in order to solve the problem that the residual axial force of the large-flow and high-power pre-pressing pump rotor is too large, and the balance structure and method are suitable for a large-thrust pumping type liquid-propellant rocket engine; through adjusting on the structural layout of the pre-pressing pump, flowing circulation in the pre-pressing pump can be actively controlled, bearing cooling flow is guaranteed, and meanwhile pressure distribution of the rotor of the large-flow and high-power pre-pressing pump under different conditions is effectively controlled; andtherefore the residual axial force of the pre-pressing pump is adjusted, and the work reliability of the engine is improved.
Description
technical field [0001] The invention belongs to the field of fluid machinery, and relates to an axial force balance structure and method, in particular to an axial force balance structure and method of a large-flow and high-power pre-pressure pump. Background technique [0002] The pump booster system of liquid rocket engine generally adopts the structure of pre-pressure pump. The engine's demand for tank pressure. After the pre-pressure pump spins, the rotor structure will generate a certain axial force under the action of the pressure field. Excessive axial force will cause damage to the rotor structure and bearings, affecting the normal operation of the engine. For a large flow and high power preload pump, due to the large outer diameter of the rotor, the axial force of the rotor is particularly sensitive to the pressure field. How to effectively adjust the axial force of the preload pump directly affects the working reliability of the engine. [0003] Therefore, it is ...
Claims
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IPC IPC(8): F04D29/66F04D29/18F04D29/08F04D29/046F02K9/46
CPCF02K9/46F04D29/046F04D29/086F04D29/181F04D29/669
Inventor 王晓锋袁伟为李惠敏李昌奂李爱民于晴蒋建园
Owner XIAN AEROSPACE PROPULSION INST