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A liquid rocket engine turbo pump helium flame retardant sealing structure

A liquid rocket and sealing structure technology, applied in liquid fuel engines, rocket engine devices, machines/engines, etc., can solve problems such as explosion, oxidant and fuel contact combustion, achieve safe and reliable isolation, avoid difficult processing, and improve work safety sexual effect

Active Publication Date: 2021-06-11
BEIJING AEROSPACE PROPULSION INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the sealing sleeve and the rotating shaft are in a clearance fit, and oxidizer and fuel also exist in the fit gap, which will cause destructive failures such as oxidant and fuel contact combustion or even explosion

Method used

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  • A liquid rocket engine turbo pump helium flame retardant sealing structure
  • A liquid rocket engine turbo pump helium flame retardant sealing structure
  • A liquid rocket engine turbo pump helium flame retardant sealing structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] A liquid rocket engine turbopump helium flame-retardant sealing structure, including a rotating shaft 1, a sealing shell 2, a floating ring 3, a wave spring 4, a cover plate 5, a first bushing 7, a second bushing 8, and a sealing bushing 9. Aluminum pad10.

[0029] The first shaft sleeve 7, the sealing shaft sleeve 9, and the second shaft sleeve 8 are sequentially set on the rotating shaft 1, and the sealing shaft sleeve 9 is sealed and connected with the first shaft sleeve 7 and the second shaft sleeve 8; the sealing The shaft sleeve 9 is provided with an annular groove on the surface close to the rotating shaft 1. When the sealing sleeve 9 is set on the rotating shaft 1, an annular cavity 14 is formed between the annular groove and the rotating shaft 1; The annular groove is provided with 4-6 radial holes in total, and the 4-6 radial holes 13 are distributed along the circumference of the sealing sleeve 9 .

[0030] The sealing housing 2 is sleeved on the sealing sha...

Embodiment 2

[0034] A liquid rocket engine turbopump helium flame-retardant sealing structure, including a rotating shaft 1, a sealing shell 2, a floating ring 3, a wave spring 4, a cover plate 5, a screw 6, a first bushing 7, a second bushing 8, a seal Shaft sleeve 9, aluminum pad 10; Wherein floating ring 3 has two roads, as figure 1 shown.

[0035] Four radial holes 13 are arranged in the middle position of the floating ring 3 corresponding to the back-to-back installation of the sealing sleeve 9, and sealing teeth 19 are arranged at both ends of the sealing sleeve 9, such as Figure 2~3 shown. The inner surface of the sealing shaft sleeve 9 is processed with an annular groove. After assembly, the sealing sleeve 9 forms an annular cavity 14 with the rotating shaft 1 . When working, the helium in the dynamic seal isolation cavity 12 enters the annular cavity 14 from the middle gap of the floating ring 3 through the radial hole 13 of the seal sleeve 9 to form a helium isolation cavity ...

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Abstract

A liquid rocket engine turbo pump helium flame-retardant sealing structure, belonging to the technical field of rocket engines, including a rotating shaft (1), a sealing shell (2), a floating ring (3), a wave spring (4), and a cover plate (5) , the first shaft sleeve (7), the second shaft sleeve (8), and the sealing shaft sleeve (9); the first shaft sleeve (7), the sealing shaft sleeve (9), and the second shaft sleeve (8) are sequentially set on the rotating shaft On (1); the surface of the sealing sleeve (9) close to the rotating shaft (1) is provided with an annular groove, and an annular cavity (14) is formed between the annular groove and the rotating shaft (1); the sealing sleeve (9) is provided at the annular groove There are radial holes (13); the sealing shell (2) is set on the sealing sleeve (9), and there are interconnected helium inlet holes (11) and isolation chambers (12); the cover plate (5) and After the sealing shell (2) is connected, the floating ring (3) is located in the isolation cavity (12); the wave spring (4) is used to apply axial preload to the floating ring (3), and at the same time, the isolation cavity (12) is in contact with the diameter Connect to hole (13). The invention realizes the isolation of the oxidant and the fuel, and greatly improves the safety of the turbo pump.

Description

technical field [0001] The invention relates to a helium flame-retardant sealing structure of a liquid rocket engine turbo pump, which belongs to the technical field of rocket engines. Background technique [0002] When oxidant and fuel exist in the turbopump of liquid rocket engine, the contact combustion of the two media is a typical catastrophic failure, which is extremely harmful. Once the oxidant comes into contact with the fuel, it will develop fission combustion, causing turbine blade ablation, casing burn-through, and even the entire engine explosion. Therefore, it is necessary to completely isolate the oxidizer and fuel when the turbo pump is working. At present, turbopumps often use dynamic seals in the form of floating rings or labyrinth seals, and a certain pressure of helium is introduced into the middle of the floating ring or labyrinth seal to isolate the oxidant and fuel in the chambers on both sides. Usually, a sealing sleeve is installed on the rotating s...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/10F02K9/46
CPCF02K9/46F04D29/106
Inventor 沈文金黄克松蒋文山崔垒柴皓李小芬刘恒金志磊林奇燕叶小强
Owner BEIJING AEROSPACE PROPULSION INST