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Turbine rear support plate blade and aero-engine thereof

A blade and turbine technology, applied in the field of turbine rear support plate blades and aero-engines, can solve the problems of airflow blockage and large weight of the engine turbine rear support plate, so as to reduce weight, improve thrust-to-weight ratio and structure compactness, reduce The effect of overall weight

Pending Publication Date: 2020-12-04
AECC SICHUAN GAS TURBINE RES INST
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  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

[0007] The purpose of the present invention is to provide a turbine rear strut blade, which solves the technical problem that the engine turbine rear strut is heavy and easily causes airflow blockage in the prior art

Method used

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  • Turbine rear support plate blade and aero-engine thereof
  • Turbine rear support plate blade and aero-engine thereof
  • Turbine rear support plate blade and aero-engine thereof

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Embodiment Construction

[0030] Embodiments of the present invention are described below through specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. Apparently, the described embodiments are only some of the embodiments of the present invention, but not all of them. The present invention can also be implemented or applied through other different specific implementation modes, and various modifications or changes can be made to the details in this specification based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that, in the case of no conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scop...

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Abstract

The invention discloses a turbine rear support plate blade, and belongs to the technical field of gas turbine blades. The turbine rear support plate blade solves the technical problems that an engineturbine rear support plate in the prior art is heavy in weight and easily causes airflow blockage. The blade is installed on a rear bearing casing, first blades are arranged in the circumferential direction of the rear bearing casing at intervals, second blades are arranged between the adjacent first blades at intervals, the axial length of the second blades is smaller than that of the first blades, the radial height of the first blades is the same as that of the second blades, and the invention further discloses an aero-engine provided with the turbine rear support plate blades. The turbine rear support plate blade is used for perfecting the use function of the turbine rear support plate blade, and meets the requirements of people on light weight of the engine turbine rear support plate blade and difficulty in causing airflow blockage.

Description

technical field [0001] The invention belongs to the technical field of gas turbine blades, in particular to a turbine rear strut blade and an aeroengine thereof. Background technique [0002] In an aero-engine, the inlet of the turbine rear strut is connected to the outlet of the turbine stage, and the outlet is connected to the afterburner or tail nozzle, which plays a pivotal role in the rectification of the turbine outlet and engine support. The turbine rear strut of a high Mach number engine must have high flow capacity and rectification, and meet the requirements of no flow separation in a wide range of angle of attack. [0003] The turbine rear strut in the prior art can fulfill the functions of oil inlet, oil return, ventilation, support and rectification, which are realized by increasing the number of blades of the rear strut and the maximum thickness of the strut. However, the larger maximum thickness and more The traditional turbine rear strut with the number of b...

Claims

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Application Information

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IPC IPC(8): F01D9/04
CPCF01D9/041
Inventor 朱兰张剑
Owner AECC SICHUAN GAS TURBINE RES INST
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