Rear casing of gas turbine engine

A gas turbine and engine technology, applied in engine components, machines/engines, mechanical equipment, etc., can solve the problems of uncoordinated thermal deformation of the rectifier support plate and the bearing frame, affecting the use of the rear casing of the turbine, and falling off of solder joints. Achieve the effect of prolonging life, improving maintainability, and reducing thermal load

Active Publication Date: 2020-02-07
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The thermal deformation of the rectifier support plate and the load-bearing frame is not coordinated, and faults such as solder joint detachment, deformation, and cracks are prone to occur, which affects the use of the turbine rear casing

Method used

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  • Rear casing of gas turbine engine
  • Rear casing of gas turbine engine
  • Rear casing of gas turbine engine

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Experimental program
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Embodiment Construction

[0026] In order to make the objectives, technical solutions and advantages of the implementation of the application clearer, the technical solutions in the implementation modes of the application will be described in more detail below with reference to the drawings in the implementation modes of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below by referring to the figures are exemplary and are intended to explain the present application, and should not be construed as limiting the present application. Based on the implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the pr...

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Abstract

The application belongs to the technical field of gas turbine design, and relates to a rear casing of a gas turbine engine. The rear casing comprises an outer casing, an inner casing and a plurality of force bearing frames arranged between the outer casing and the inner casing, wherein the inner wall of the outer casing is circumferentially provided with a heat shield, a notch which is concave tothe outer casing is arranged at the joint of the heat shield and the force bearing frames, a support plate limiting sleeve fixedly connected with the heat shield is arranged in the notch, and the support plate limiting sleeve comprises side plates extending to two sides of the force bearing frames; the outer side of each force bearing frame is wrapped with a rectification support plate, one end ofthe rectification support plate is connected with each force bearing frame, the other end of the rectification support plate is in lap joint with the outer side of each side plate of the support plate limiting sleeve, a first air cooling channel is formed between each force bearing frame and the rectification support plate, a second air cooling channel is formed in each force bearing frame, and the rectification support plate extends under the action of thermal stress, extends outwards under the guiding action of the support plate limiting sleeve, and releases the thermal stress, so that therear casing keeps good rigidity, reliability and durability.

Description

technical field [0001] The application belongs to the technical field of gas turbine design, in particular to a gas turbine engine rear casing. Background technique [0002] The turbine rear casing of a gas turbine engine is an important connection, support, load-transmitting and force-bearing component of the complete engine. It is mainly composed of an outer casing 1, an inner casing 6, a load-bearing frame 5, and a bearing seat 9. Inside the frame 5 are arranged oil inlet and outlet pipes 10, cooling air passages, etc., and a typical turbine rear case structure is as follows: figure 1 shown. [0003] The turbine rear case is subjected to very high static loads, aerodynamic loads and thermal stresses. The rear fulcrum bearing of the entire low-pressure rotor is installed on the bearing seat of the turbine rear casing, and its radial force is transmitted to the turbine rear casing, and then transmitted to the aircraft by the rear suspension point on the turbine rear casin...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D25/24F01D25/14F01D25/12
CPCF01D25/24F01D25/145F01D25/14F01D25/12
Inventor 赵家军杨守辉宋辰星李俊山赵耘墨
Owner AECC SHENYANG ENGINE RES INST
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