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A turbine rotor blade, a rotating assembly and a turbine engine

A technology for turbine rotors and rotating components, applied in the direction of engine components, machines/engines, blade support components, etc., can solve problems such as stress concentration, difficulty in blade crown processing, and reduced service life of turbine rotor blades to achieve machinability Improved effect

Active Publication Date: 2016-12-14
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, it is obvious that such a blade shroud with a Z-shaped profile is difficult to machine, and in addition, the mass distribution is not uniform resulting in a large local structure cantilever and causing stress concentrations, thus reducing the service life of the turbine rotor blades

Method used

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  • A turbine rotor blade, a rotating assembly and a turbine engine
  • A turbine rotor blade, a rotating assembly and a turbine engine
  • A turbine rotor blade, a rotating assembly and a turbine engine

Examples

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Embodiment Construction

[0021] Such as figure 1 and figure 2 As shown, among them, figure 1 A schematic diagram showing three turbine rotor blades arranged adjacently in pairs, figure 2 for figure 1 A schematic diagram of the shroud portion of a turbine rotor blade. The three turbine rotor blades are represented by reference numerals 100, 200 and 300 respectively. The turbine rotor blade shown in the figure is a preferred embodiment of the present invention. Below, one of the turbine rotor blades 100 is taken as an example for illustration . Turbine rotor blade 100 includes an airfoil portion 102 and a shroud portion 104 . Wherein, the airfoil portion 102 has a blade leading edge 102a, a blade trailing edge 102b, a pressure surface 102c, and a suction surface 102d; 102, which has a shroud leading edge 106 and a shroud trailing edge 108. Here, the airfoil portion 102 and the shroud portion 104 are integrally formed. Both the front edge 106 of the shroud and the trailing edge 108 of the shrou...

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PUM

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Abstract

A turbine rotor blade comprising an airfoil portion and a shroud portion formed on the free end of the airfoil portion extending substantially circumferentially and axially along the center of the turbine rotor, having a shroud leading edge and a shroud The trailing edge, wherein, the leading edge of the crown and the trailing edge of the crown are arcs with a smooth transition. The front edge and trailing edge of the shroud are designed to be arc-shaped, and the manufacturability of the shroud part is improved. At the same time, the arc-shaped front edge and trailing edge of the shroud make the mass distribution of the shroud part more uniform, thereby reducing stress concentration.

Description

technical field [0001] The invention relates to a turbine rotor blade, a rotating assembly and a turbine engine. Background technique [0002] Gas turbines are used in many fields to drive electrical generators or working machines, especially in aircraft. Here, the energy of the fuel is used to rotate the turbine shaft. For this purpose, the fuel is burned in a combustion chamber into which the air compressed by the compressor is also fed. In the combustion chamber, the high-temperature and high-pressure working medium formed by the combustion of fuel expands and works through a turbine unit connected behind the combustion chamber. [0003] Turbine rotor blades are an important component in a turbine unit for converting thermal energy from the combustion chamber into mechanical work for the turbine rotor. Turbine performance can be enhanced by sealing the turbine blade tips, preventing combustion gases from escaping from the airflow into the gap between the blade tips and...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/14
Inventor 陈亚龙万明学齐晓东
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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