A cavity turbine rotor blade structure

By setting cavities inside the turbine blades and connecting them with bosses of insert-type blade crowns, the problem of blade crown bending and deformation is solved, blade stress is reduced and maintenance is facilitated, thereby improving the performance and economy of turbine blades.

CN115638029BActive Publication Date: 2026-04-24QINGHANG AEROSPACE (BEIJING) TECH CO LTD
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
QINGHANG AEROSPACE (BEIJING) TECH CO LTD
Filing Date
2022-10-19
Publication Date
2026-04-24

AI Technical Summary

Technical Problem

Existing turbine blades are prone to bending and deformation under high temperature, high pressure and high speed conditions, which leads to stress concentration at the blade tip, affecting performance and lifespan. In addition, traditional designs are difficult to assemble and maintain.

Method used

The blade adopts a cavity turbine rotor structure with a cavity inside the blade body. The insertable blade crown has a boss. The adjacent blade crown bosses are inserted into the cavity and pressed against the inner wall to form a stable connection, reducing the bending deformation of the blade crown.

Benefits of technology

It effectively reduces stress at the blade tip, improves blade performance and lifespan, reduces assembly difficulty, and supports individual blade crown maintenance, thus improving economic efficiency.

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    Figure CN115638029B_ABST
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Abstract

The application provides a cavity turbine rotor blade structure and belongs to the technical field of turbine rotor components of an aero-engine. Specifically, the cavity turbine rotor blade structure comprises a blade body and an inserted crown. The blade body is internally provided with a cavity. The cavity penetrates the end surface of the blade connecting the crown. The inserted crown is provided with a boss inserted into the cavity. After the end surfaces of adjacent inserted crowns are butted, two bosses close to each other are inserted into the same cavity, and the two bosses are in abutment with the inner wall of the cavity. Through the processing scheme, the bending deformation of the crown is reduced, and the stress of the blade tip is reduced.
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Citation Information

Patent Citations

  • Combined blade structure of turbine rotor

    CN114991877A

  • improvements in the construction of turbine blades

    FR336322A