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Turbine guide blade, turbine guide blade assembly and core engine

A technology of turbine guide vanes and turbine casings, applied in mechanical equipment, engine components, machines/engines, etc., can solve the problems of complex installation structure and unfavorable installation.

Active Publication Date: 2019-07-19
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

[0006] In addition, the installation structure of the existing turbine guide vanes is complicated, which is not conducive to the installation

Method used

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  • Turbine guide blade, turbine guide blade assembly and core engine
  • Turbine guide blade, turbine guide blade assembly and core engine
  • Turbine guide blade, turbine guide blade assembly and core engine

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Embodiment Construction

[0031] The technical solutions of the present invention will be described in further detail below with reference to the accompanying drawings and embodiments.

[0032] The specific embodiments of the present invention are for the convenience of further description of the concept of the present invention, the technical problems to be solved, the technical features constituting the technical solution and the technical effects brought about. It should be noted that the description of these embodiments does not constitute a limitation of the present invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

[0033] In an exemplary embodiment of the turbine guide vane of the present invention, as figure 2 and image 3 As shown, the turbine guide vane 1 includes an airfoil 11 and an upper edge plate 13 and a lower edge plate 12 respectively ar...

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Abstract

The invention relates to a turbine guide blade, a turbine guide blade assembly and a core engine. The turbine guide blade comprises a blade body, an upper edge plate and a lower edge plate, wherein the upper edge plate and the lower edge plate are arranged at the top and the bottom of the blade body respectively, the upper edge plate is provided with a C-like-shaped groove structure used for beingconnected with a turbine case, and the lower edge plate is provided with a C-like-shaped groove structure used for being connected with a turbine inner ring. According to the turbine guide blade, theC-like-shaped groove structures are designed on the upper edge plate and the lower edge plate correspondingly so that the turbine guide blade can be conveniently installed between the turbine case and the turbine inner ring, which is especially suitable for a turbine guide blade made of a ceramic matrix composite material, so that the turbine guide blade made of the ceramic matrix composite material is prevented from generating additional subsidiary stress.

Description

technical field [0001] The invention relates to the technical field of turbine guide vane assemblies, in particular to a turbine guide vane, a turbine guide vane assembly and a core machine. Background technique [0002] Aeroengines have higher requirements on processing materials. For future civil aeroengines, the temperature before the turbine is getting higher and higher, and the life expectancy is also getting longer. For example, in modern commercial aeroengines, the design life of hot-end components is not less than 10,000 flight cycles. (20,000 hours), the gas temperature before the high-temperature take-off turbine has reached 1978K. At present, for high-temperature turbine stator parts, under the condition of using traditional cooling technology and thermal barrier coating technology, the service temperature and service performance of traditional superalloy materials are close to the limit, and it is difficult to meet the design requirements of the next generation o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/04
CPCF01D9/041F01D9/042
Inventor 齐晓东李杰陈亚龙
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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