Gas film damping fan blade with vibration absorption sheet covered by throttling orifices

A technology of fan blades and orifices, which is applied to components of pumping devices for elastic fluids, non-variable pumps, machines/engines, etc., can solve the problem of lack of vibration damping mechanism for wide-chord fan blades and fan blade vibration , fan blade fatigue failure and other problems, to achieve obvious vibration reduction effect, reduce vibration level, and reduce structural strength

Inactive Publication Date: 2018-10-16
CIVIL AVIATION UNIV OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] As the size of wide-chord fan blades increases and the thrust of aero-engines increases, the aerodynamic force and other unsteady excitation forces on the fan blades are also increasing. Due to the lack of sufficient and

Method used

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  • Gas film damping fan blade with vibration absorption sheet covered by throttling orifices
  • Gas film damping fan blade with vibration absorption sheet covered by throttling orifices
  • Gas film damping fan blade with vibration absorption sheet covered by throttling orifices

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Embodiment Construction

[0027] The air film damping fan blade provided by the present invention with an orifice covered with a shock-absorbing thin plate will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0028] Such as figure 1 — image 3 As shown, the air film damping fan blade with a throttle hole covered with a vibration-absorbing thin plate provided by the present invention includes a blade body 1, a vibration-absorbing thin plate 8, a blade leading edge 4, and a blade disc 6; wherein the blade body 1 is a large-sized wide chord without a shoulder The fan blade structure is composed of the blade back 2 and the blade pot 3 through diffusion welding, and the lower end is fixed on the blade disc 6; in the middle of the blade back 2, an open cavity 12 is formed extending from the front edge to the rear edge of the blade body , the upper and lower ends of the open cavity 12 are respectively equipped with an upper support 9 and a lower support 10...

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PUM

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Abstract

The invention discloses a gas film damping fan blade with a vibration absorption sheet covered by throttling orifices. The gas film damping fan blade comprises a blade body, the vibration absorption sheet, a blade front edge and a blade disk; the blade body is of a large-size wide-chord raised-shoulder-free fan blade structure, which is connected with into a whole by conducting diffusion welding on a blade back and a blade basin; the lower end of the blade body is fixed to the blade disk; an open cavity is formed by extending from the front edge to the rear edge of the blade body at the middlepart of the blade back; the vibration absorption sheet is arranged on the open cavity; the blade front edge is arranged at the front edge of the blade body; and the lower end of the blade front edgeis fixed to the blade disk. The fan blade exists various vibration reduction energy dissipation mechanisms, the vibration reduction frequency domain range is wide, the application scope is wide, a gasfilm damping structure is easy to realize, and the vibration level of the fan blade can be inhibited effectively.

Description

technical field [0001] The invention belongs to the technical field of fan blade design in aeroengines and gas turbines, and in particular relates to a gas film damping fan blade with an orifice covering a shock-absorbing thin plate. Background technique [0002] Fan blades are the most representative parts of aero-engines. In order to meet the performance requirements of modern aero-engines, many scholars have continuously improved fan blades in terms of materials and structural design. However, the fatigue failure caused by the vibration of fan blades is an The key factor for the structural reliability of aero-engines, only by suppressing the vibration level of fan blades to the greatest extent can the further development of aero-engine vibration reduction technology be promoted. [0003] The early aero-engine fan blades were mostly solid and narrow-chord structures. In order to reduce the vibration fatigue failure of the fan blades, a shoulder damping structure was set in...

Claims

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Application Information

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IPC IPC(8): F04D29/38F04D29/66
CPCF04D29/388F04D29/666F04D29/668
Inventor 张鸿崔东泽李湘萍孔庆国
Owner CIVIL AVIATION UNIV OF CHINA
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