A connection structure of high temperature gas outlet end of low temperature turbo pump

Abstract

The invention relates to the field of liquid-propellant rocket engine turbine pumps, and provides a high-temperature gas outlet end connecting structure of a low-temperature turbine pump. The high-temperature gas outlet end connecting structure comprises a high-temperature gas outlet pipe and a low-temperature shell, wherein the low-temperature shell is mounted on a rotating shaft through a turbine end bearing, a turbine rotor is fixed on the rotating shaft, the high-temperature gas outlet pipe comprises an outlet flange, a transition section, a small end, a gas collecting pipe and a large end, a flow guiding support plate is arranged in the circumferential direction of the inner surface of the gas collecting pipe, the outlet flange, the transition section, the small end, the flow guidingsupport plate, the gas collecting pipe and the big end are integrally formed, and are made of high-temperature alloy materials, the large end and the small end are arranged on the two opposite sides of the gas collecting pipe, and the high-temperature gas outlet pipe and the low-temperature shell are connected through nuts and bolts. An internal profile of the high-temperature gas outlet pipe is subjected to three-dimensional optimization, the high-temperature gas outlet pipe is guaranteed to be smooth in circulation and extremely small in loss, and the working capacity and efficiency of the turbine pump are improved.

Description

technical field [0001] The invention belongs to the field of liquid rocket engine turbopumps, and in particular relates to a high-temperature gas outlet assembly structure of a rocket engine low-temperature turbopump. Background technique [0002] The turbo pump is one of the key components in the liquid rocket engine. Due to its high power, it is generally driven by a high-temperature gas turbine. Especially for post-combustion cycle engines, under the premise of ensuring engine performance, it is necessary to reduce the temperature of high-temperature gas as much as possible to ensure the reliability of the high-temperature gas circuit of the engine. The efficiency of the turbo pump is directly related to the temperature of the high-temperature gas. The calculation of the system adjustment shows that the efficiency of the turbo pump For every 1% increase, the high-temperature gas temperature can be reduced by 10K, so it is very important to design high-efficiency turbine c...

AI Technical Summary

Problems solved by technology

[0005] The technical problem solved by the present invention is to provide a connection structure for the high-temperature gas outlet end of a low-temperature turbo pump, so that the turbine has high efficiency and at the same time solves the problem that the temperature difference between the low-temperature component and the high-temperature component is extremely large and causes the deformation of the component. To ensure the reliability of the high temperature gas circuit

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