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Circumferential sectioned helium sealing device for oxygen turbine pump of hydrogen oxygen engine

A sealing device and engine technology, applied in the direction of machines/engines, liquid fuel engines, pumping devices for elastic fluids, etc., to achieve the effects of improving dynamic pressure capacity, reducing possibility, and small leakage

Inactive Publication Date: 2016-09-28
BEIJING AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The above face seals, labyrinth seals and hydrodynamic floating ring seals are no longer satisfactory

Method used

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  • Circumferential sectioned helium sealing device for oxygen turbine pump of hydrogen oxygen engine
  • Circumferential sectioned helium sealing device for oxygen turbine pump of hydrogen oxygen engine
  • Circumferential sectioned helium sealing device for oxygen turbine pump of hydrogen oxygen engine

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Embodiment Construction

[0028] The circumferential segmented helium sealing device of a hydrogen-oxygen rocket engine oxygen turbo pump according to the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0029] A circumferentially segmented helium sealing device for an oxygen turbopump of a hydrogen-oxygen engine according to the present invention comprises two sets of circumferentially segmented helium seal rings 1 and 2, a sealing case 3, a cover plate 4, a hoop spring 6, Preload spring 7, pin 8, sealing washer 9, bolt 10, washer 11 and sealing bushing 5, etc. The two sides of the circumferential segmented helium seal device are oxygen chamber and hydrogen-rich gas chamber. During operation, a certain pressure of helium is supplied from the helium supply channel to ensure that the pressure of the helium seal chamber is higher than the pressure of the oxygen chamber and hydrogen-rich gas chamber on both sides. , which...

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Abstract

The invention discloses a circumferential sectioned helium sealing device for an oxygen turbine pump of a hydrogen oxygen engine. According to the circumferential sectioned helium sealing device, a circumferential sectioned sealing ring I and a circumferential sectioned sealing ring II are placed in a cavity formed by a cover plate and a sealing shell; sealing shaft sleeves are placed in rings of the circumferential sectioned sealing ring I and the circumferential sectioned sealing ring II; the circumferential sectioned sealing ring I and the circumferential sectioned sealing ring II are oppositely placed and pre-tensioned by virtue of pre-tensioning springs; and each of the circumferential sectioned sealing ring I and the circumferential sectioned sealing ring II is formed by connecting a plurality of fan-shaped arc sections with the same structure end to end, and constrained on an excircle surface through garter springs. According to the circumferential sectioned helium sealing device, each sealing ring is composed of the plurality of fan-shaped arc sections, a hydrodynamic groove structure is introduced, and a hydrodynamic effect of a sealing clearance fluid is adequately utilized, thus the helium sealing device reliably works under an extremely small clearance, and a low leakage amount is maintained.

Description

technical field [0001] The invention relates to a sealing device, in particular to a circumferential segmented helium sealing device for an oxygen turbopump of a hydrogen-oxygen engine. Background technique [0002] Since the new century, the world has ushered in a wave of aerospace technology development. All major aerospace countries in the world have proposed a series of major projects to revitalize aerospace, such as landing on Mars, exploring the moon, etc., and high-thrust rockets are an indispensable means of transportation to complete these plans. The hydrogen-oxygen rocket engine has the advantages of high specific impulse, high reliability, good adaptability, and no pollution, and is widely used in the new generation of launch vehicles at home and abroad. The oxygen turbo pump is one of the core components of the hydrogen-oxygen rocket engine. It uses a hydrogen-rich gas turbine to drive the high-pressure oxygen pump. In order to ensure the safe and reliable opera...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/10F04D29/12
CPCF04D29/102F04D29/122
Inventor 叶小强夏德新金志磊陶瑞峰沈文金孙晓伟张玺张召磊黄克松
Owner BEIJING AEROSPACE PROPULSION INST
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