Nuclear heat engine system for multi-stage pump interstage flow dividing

Abstract

A nuclear heat engine system for multi-stage pump interstage flow dividing comprises a storage box, a multi-stage pump, a turbine, a shaft system, a main valve, an auxiliary control valve, a reactor and a thrust chamber. The interstage flow dividing manner is adopted in the nuclear heat engine system, part of working media flow out of the output end of a non-last-stage impeller 2a of the multi-stage pump, and the other part of working media flow out of the output end of a last-stage impeller 2b of the multi-stage pump. The pressure of working media getting of a side reflection layer 7c and thepressure of working media getting out of an auxiliary heating element 7b are almost the same at the inlet position of a gathering cavity 7d, and the absolute value of the pressure difference of two paths of working media is smaller than or equal to 0.8 MPa. The nuclear heat engine system solves the problem that in the existing nuclear heat rocket engine closed expansion circulation scheme, turbine pump shaft work waste exists; and turbine pump subsystem shaft work reduction is achieved, the chamber pressure and the specific impulse of a nuclear heat rocket engine are improved, and the vacancyof the domestic low-shaft-work nuclear heat rocket engine closed expansion circulation system scheme is filled up.

Description

technical field [0001] The invention relates to a nuclear thermal engine system with flow splitting between multistage pump stages, belonging to the field of rocket power system design. Background technique [0002] Since the beginning of the 21st century, all space powers in the world are actively discussing interstellar manned flight programs such as returning to the moon and landing on Mars. In order to realize corresponding space missions, space propulsion power systems are required to have higher propulsion performance. The nuclear thermal rocket engine replaces the combustion chamber of the liquid rocket engine with the nuclear fission reactor, uses the energy generated by nuclear fission to heat the propellant to a high temperature, and then expands through the supersonic nozzle to generate thrust. When hydrogen with the smallest molecular weight is used as the propellant of the nuclear thermal rocket engine , its specific impulse can reach 900s and above, which is ab...

AI Technical Summary

Problems solved by technology

[0005] The technical problem of the present invention is: to overcome the deficiencies of the prior art, to provide a nuclear thermal engine system with multi-stage pump stage splitting, and to solve the waste of turbine pump shaft work in the closed expansion cycle scheme of the existing nuclear thermal rocket engine problem, realized the reduction of the shaft work of the turbo pump sub-system, increased the chamber pressure and specific impulse of the nuclear thermal rocket engine, and filled the blank of the domestic low shaft work nuclear thermal rocket engine closed expansion cycle system scheme

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