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Connecting device, gas turbine engine, connecting piece and turbine outer ring

A connecting device and connecting piece technology, applied in the direction of engine components, machines/engines, mechanical equipment, etc., can solve problems such as differences in thermal expansion coefficients, affecting the safety and reliability of components themselves and connecting structures, and achieve higher temperature limits and higher connection strength. and reliability, improving overall performance

Active Publication Date: 2020-09-04
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

However, the difference in thermal expansion coefficient between CMC and superalloy materials will cause significant thermal mismatch stress in the connection and installation structure between the CMC turbine outer ring component and the engine metal case during the temperature change process, which will affect the safety of the component itself and the connection structure reliability

Method used

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  • Connecting device, gas turbine engine, connecting piece and turbine outer ring
  • Connecting device, gas turbine engine, connecting piece and turbine outer ring
  • Connecting device, gas turbine engine, connecting piece and turbine outer ring

Examples

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Embodiment Construction

[0029] A variety of different implementations or examples for implementing the described subject technical solutions are disclosed below. In order to simplify the disclosure, the following describes the specific examples of each component and arrangement, of course, these are only examples, not limiting the protection scope of the present invention. For example, the description that the first feature described later in the description is formed on or above the second feature may include an embodiment in which the first and second features are formed through direct contact, and may also include an embodiment in which the first and second features are formed between the first and second features. Embodiments of additional features such that there may be no direct relationship between the first and second features. Additionally, reference numerals and / or letters may be repeated in different instances in these disclosures. This repetition is for brevity and clarity and does not i...

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Abstract

The invention relates to a connecting device, a gas turbine engine, a connecting piece and a turbine outer ring. The connecting device includes a first component, a second component and connecting pieces. The first component is equipped with annular ribs arranged on the outer circumference of the first component, and each annular rib is equipped with a plurality of first grooves in the circumferential direction; the second component is arranged around the outer circumference of the first component; each connecting piece includes a rod part and a block part; wherein a connecting piece is arranged corresponding to each first groove; and the block part of each connecting piece is placed in the first groove. The connecting device has the advantage of reliable connection, and the gas turbine engine has the advantage of good overall performance.

Description

technical field [0001] In particular, the invention relates to a connection device, a gas turbine engine, a connection piece and a turbine outer ring structure. Background technique [0002] Components of gas turbine engines often need to withstand extremely high temperatures, such as the outer ring of the turbine, which is the main stationary part of the turbine of an aeroengine, and it is subjected to high ambient temperature in service. At present, the outer ring components of the turbine are mainly made of superalloy materials, but the strength and stiffness of the superalloy materials will decrease significantly under high temperature environment, which will affect the upper limit of the service temperature of the outer ring components of the turbine, and ultimately limit the improvement of the overall performance of the aeroengine. Using ceramic matrix composites (CMC) instead of superalloy materials to prepare aero-engine turbine outer ring components can give full pl...

Claims

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Application Information

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IPC IPC(8): F01D9/00F01D9/04
CPCF01D9/00F01D9/04Y02T50/60
Inventor 郭洪宝谢骏梅文斌
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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