Turbine blisk and liquid rocket engine

Abstract

The invention discloses a turbine blisk and a liquid rocket engine. The turbine blisk structure is used for being connected with a rotating shaft to drive a turbopump to do work and comprises blades and a turbine disk. The blades are arranged on the outer side, in the radial direction, of the turbine disk, and the ends close to the turbine disc are matched with the extension face of the turbine disk in a surrounding manner. A center hole is formed in the turbine disc. In the radial direction of the turbine disk, multiple through holes are formed in the portion, outside the center hole, of theturbine disk, and the multiple through holes are formed around the center hole at equal intervals. Compared with the prior art, the structure is reasonable in design, the weight of a cantilever can beeffectively decreased, and the corresponding critical rotation speed safety margin during work of a rotor is increased.

Description

technical field [0001] The invention relates to the technical field of rocket power, in particular to a turbine blisk and a liquid rocket engine. Background technique [0002] With the rapid development of the aerospace industry, various technologies involved in the rocket field have also achieved rapid progress. As a rocket power plant, one of the important ways to improve the performance of a liquid rocket engine is to increase the head of the turbo pump to increase the pressure of the thrust chamber and ensure the specific impulse of the engine. In addition, based on the weight reduction of the rocket structure, it is necessary to increase the safe operating speed of the turbo pump as much as possible to avoid excessive structural size of the turbo pump. Therefore, it is very important to reduce the weight of the turbine blisk, which has the greatest influence on the quality of the rotor cantilever. If the moment of inertia of the turbine blisk is too large, the critica...

AI Technical Summary

Problems solved by technology

The dual-performance turbine rotor structure adopts different materials according to different mechanical requirements. It welds each CMSX-4 single crystal blade and NF3 powder disk, eliminating the tenon structure, which can effectively reduce the weight and moment of inertia of the rotor, but This kind of turbine disk is complex and expensive, and is not suitable for liquid rocket engines

Over the years, the turbine discs of liquid engines have achieved little effect in terms of weight reduction. The main method is to increase the critical speed margin by using larger-diameter bearings. However, the selection of larger-diameter bearings increases the difficulty of developing the bearing itself. Reduced bearing reliability and engine safety

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