A spherical turbine housing and turbopump for liquid rocket engines

Abstract

In order to guarantee that a turbopump stably and reliably works, and improve the working efficiency of the turbopump, the invention provides a spherical turbine shell for a liquid-propellant rocket engine and the turbopump for the liquid-propellant rocket engine. The spherical turbine shell comprises a shell assembly, an inlet pipe, a turbine stator, an inner baffle and a corrugated pipe. The shell assembly comprises a spherical shell, a connecting sleeve and an outlet pipe. The turbine stator comprises an outer ring body, stator blades and an inner ring body. A radial air inlet, an axial exhaust opening and an axial installation opening are formed in the spherical shell. One end of the outlet pipe is set to be of a V-shaped structure, one side of the V-shaped structure is connected withthe axial exhaust opening of the spherical shell, and the other side of the V-shaped structure is connected with the outer ring body of the turbine stator. The connecting sleeve is connected with theaxial installation opening of the spherical shell, and the inlet pipe communicates with the radial air inlet of the spherical shell. The corrugated pipe is arranged in the spherical shell, one end ofthe corrugated pipe is connected with the inner ring body, and the other end of the corrugated pipe is connected with the connecting sleeve. The inner baffle sleeves the corrugated pipe, one end of the inner baffle is connected with the inner ring body, and the other end of the inner baffle is connected with the connecting sleeve.

Description

technical field [0001] The invention relates to the field of liquid rocket engines, in particular to a spherical turbine casing and a turbine pump for liquid rocket engines. Background technique [0002] As the "heart" component of the liquid rocket engine, the turbo pump pressurizes the propellant through a high-speed pump and delivers it to the combustion chamber. Because the high-speed pump has a very high power, it is generally driven by a high-temperature, high-pressure gas turbine. For more complex low-temperature afterburning cycle liquid rocket engines, in order to ensure a compact engine structure, the turbine and the high-speed pump are generally coaxial to achieve an integrated design. The gas used to drive the turbine has a temperature of over 900K, and the working medium at the low temperature end is a propellant with a temperature as low as 90K. The two are directly connected through the shell. Therefore, when designing this type of engine, the main problem is...

AI Technical Summary

Problems solved by technology

The invention optimizes the structure of the turbine housing of the turbo pump to ensure the stable and reliable operation of the turbine housing in a high-pressure environment. On the one hand, it provides excellent air intake and exhaust conditions for the turbine components, and improves the turbine efficiency. Increase the working ability of the turbine, on the other hand, it solves the problem of the sharp change of the temperature gradient between the low temperature part and the high temperature part of the pump, and ensures the overall working reliability of the turbo pump

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