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Turbine blade margin plate damper, turbine blade and aero-engine

A technology for aero-engines and turbine blades, applied in the direction of machines/engines, engine components, blade support components, etc., can solve problems such as unsatisfactory vibration reduction effects, achieve improved vibration reduction effects, increase friction, and increase contact area Effect

Pending Publication Date: 2021-12-17
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The current damper has the problem of unsatisfactory damping effect

Method used

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  • Turbine blade margin plate damper, turbine blade and aero-engine
  • Turbine blade margin plate damper, turbine blade and aero-engine
  • Turbine blade margin plate damper, turbine blade and aero-engine

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Embodiment Construction

[0032] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Apparently, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts fall within the protection scope of the present invention.

[0033] In describing the present invention, it should be understood that the terms "center", "transverse", "longitudinal", "front", "rear", "left", "right", "upper", "lower", " The orientations or positional relationships indicated by "vertical", "horizontal", "top", "bottom", "inner" and "outer" are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and Simplif...

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Abstract

The invention relates to a turbine blade margin plate damper, a turbine blade and an aero-engine. The turbine blade margin plate damper comprises a damper body (10), wherein the damper body (10) comprises a first damping block (11) and a second damping block (12), the first damping block (11) is arranged in a groove (21) formed in a margin plate (20) of a turbine blade, and the second damping block (12) is connected with the first damping block (11) and arranged outside the groove (21); and the damper body (10) is movably arranged on the margin plate (20), and the damper body (10) is configured to be capable of moving to the position where the first damping block (11) makes contact with the inner wall of the groove (21) and the second damping block (12) makes contact with the outer wall of the groove (21) at the same time. The turbine blade comprises the turbine blade margin plate damper. The aero-engine comprises the turbine blade. According to the turbine blade margin plate damper, the turbine blade and the aero-engine, the contact area of the damper and the margin plate can be increased, so that the friction force is increased, and the vibration reduction effect is improved.

Description

technical field [0001] The invention relates to the technical field of aero-engines, in particular to a turbine blade edge plate damper, a turbine blade and an aero-engine. Background technique [0002] The turbine of an aero-engine works in a harsh environment of high temperature and high speed, and is susceptible to large vibration loads under working conditions, which will affect the life of the blades. Therefore, it is necessary to design vibration reduction for the turbine blades. [0003] The turbine blade includes a blade body, an edge plate, an extension root and a tenon, and the edge plate is used to connect the blade body and the extension root. At present, for the vibration reduction of turbine blades, methods such as arranging a shroud on the blade, an anti-vibration boss on the blade body, or a damper on the edge plate are usually adopted. Crowned blades will introduce large centrifugal loads, which will cause strength problems; and setting vibration-damping bo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/16F01D5/18F01D5/14
CPCF01D5/16F01D5/147F01D5/186
Inventor 江有为范慧茹郑李鹏郭洪宝
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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