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Bearing seat structure with cooling inner flow passage for turbo pump

A bearing seat, turbo pump technology, applied in the direction of bearing cooling, shaft and bearing, bearing components, etc., can solve the problems of insufficient critical speed margin of turbo pump, turbo pump resonance, reducing bearing seat support stiffness, etc., to reduce excess material risk, improve reliability, and increase the effect of critical speed

Active Publication Date: 2022-03-04
XIAN AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, since part of the flow channel is located above the bearing, this design will reduce the support rigidity of the bearing seat, resulting in insufficient critical speed margin of the turbo pump, resulting in the risk of resonance in the turbo pump

Method used

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  • Bearing seat structure with cooling inner flow passage for turbo pump
  • Bearing seat structure with cooling inner flow passage for turbo pump
  • Bearing seat structure with cooling inner flow passage for turbo pump

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Embodiment Construction

[0031] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided for more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the case of no conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0032] figure 1 It is a front view of a bearing seat structure with a cooling inner flow channel for a turbo pump provided by an embodiment of the present in...

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Abstract

The invention discloses a bearing seat structure with a cooling inner flow channel for a turbo pump, comprising: the left section of the bearing seat, the bushing and the right section of the bearing seat; wherein, the right end of the left section of the bearing seat is welded to the right section of the bearing seat by electron beam welding Welding, the left section of the bearing seat is sleeved on the bushing, and the left section of the bearing seat is connected with the positioning step of the bushing; the right section of the bearing seat is a rotary structure, the right section of the bearing seat and the left section of the bearing seat are welded by electron beam welding, and the right section of the bearing seat The structure is coaxial with the left section of the bearing seat; the bush is a rotary structure, and the large end of the bush is welded to the left section of the bearing seat by electron beam welding. The bush and the left section of the bearing seat are of a coaxial structure. The space between the left sections forms the bearing coolant inlet flow path. While guaranteeing the pressure of the bearing chamber and the cooling flow of the bearing, the invention solves the problem that the engine turbo pump has a relatively low rigidity of the bearing housing with a cooling inner hole, which leads to a relatively small critical speed margin of the turbo pump.

Description

technical field [0001] The invention belongs to the field of liquid rocket engine turbopumps, in particular to a bearing seat structure with a cooling inner flow channel for the turbopump. Background technique [0002] The rocket engine turbo pump bearing seat is arranged at the turbine end, and its main function is to provide support for the bearing and provide a cooling channel for the bearing. The cooling flow comes from the centrifugal wheel and flows to the bearing through the cooling channel arranged inside the bearing seat. The bearing seat needs to provide the bearing with the largest possible support rigidity and sufficient cooling flow. If the cooling flow rate is too low, the bearing life will be shortened. At the same time, the flow channel of the bearing seat needs to ensure that the pressure in the front cavity of the bearing is greater than the pressure at the hub of the turbine disk. Otherwise, gas backflow will occur. In response to this problem, a commonly...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F16C35/00F16C37/00F04D29/056
CPCF16C35/00F16C37/00F04D29/0563
Inventor 金路许开富李惠敏任众李向阳张鹏飞蒋建园
Owner XIAN AEROSPACE PROPULSION INST
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