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Blade with built-in bed frame-type pneumatic damping device

A technology of pneumatic damping and skeleton row, which is applied to components of pumping devices for elastic fluids, non-variable pumps, jet propulsion devices, etc., to achieve the effects of suppressing vibration, improving impact resistance, and increasing local energy loss

Inactive Publication Date: 2011-09-28
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this new type of fan blade loses the traditional shoulder design, and the blade's own damping mechanism is only the mechanical damping of the blade material and its internal structure, which is not enough to effectively avoid high-cycle fatigue failure of the blade caused by forced vibration

Method used

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  • Blade with built-in bed frame-type pneumatic damping device
  • Blade with built-in bed frame-type pneumatic damping device
  • Blade with built-in bed frame-type pneumatic damping device

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Embodiment Construction

[0037] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0038] see figure 1 , Figure 1A , Figure 1B and Figure 1C As shown, a blade with a built-in row frame type aerodynamic damping of the present invention is composed of a blade body and a tenon 3, wherein the blade body includes a blade back side wall 1, a blade pot side wall 2, a leading edge 4, and a trailing edge 5 , A vibration-absorbing plate 11, B vibration-absorbing plate 12, C vibration-absorbing plate 13, A support rib 21 and B support rib 22.

[0039] exist Figure 1B Among them, point A is the center point of the arc-shaped end at the upper end of the leading edge 4, and point B is the center point of the arc-shaped end at the upper end of the trailing edge 5. The line connecting point A and point B is called the line AB, and the line AB is just The midchord line of the blade of the present invention; point C is the center point of the upper ...

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Abstract

The invention discloses a blade structure with a built-in bed frame-type pneumatic damping device; a blade comprises a blade body and a tennon, wherein the blade body comprises a blade back side wall, a blade basin side wall, a front edge, a rear edge, an A shock-absorbing plate, a B shock-absorbing plate, a C shock-absorbing plate, an A support rib and a B support rib; the blade back side wall and the blade basin side wall are arranged between the front edge and the rear edge, and a runner is arranged between the blade back side wall and the blade basin side wall; the B shock-absorbing plateis arranged between the A support rib and the B support rib, the A shock-absorbing plate is arranged in an installation groove on the other side of the A support rib, the C shock-absorbing plate is arranged in the installation groove on the other side of the B support rib, so as to form a frame-type pneumatic damping structure; and the frame-type pneumatic damping structure is arranged in the runner which is formed by the blade back side wall and the blade basin side wall. The design of the blade structure can absorb the vibration energy of a blade body wing surface within a very wide frequency domain range, reduce the vibration stress level of the blade body, so as to solve the problem of the high-cycle fatigue failure of the blade caused by the intensive mode of the blade and the failure to avoid resonance.

Description

technical field [0001] The invention relates to a high-speed rotating gas turbine blade, more particularly, a blade structure with built-in row frame type aerodynamic damping. Background technique [0002] With the rapid development of aviation technology, new technologies used in high bypass ratio turbofan engines are also increasing, and wide-chord fan blades are one of the key technologies. To some extent, it can be said that the success of the development of the wide-chord fan blade determines the possibility of the success of the high bypass ratio fan engine. Wide-chord fan blades have the advantages of increased compressor surge margin, high efficiency, resistance to foreign object damage, increased engine thrust, reduced number of blades and reduced weight, and provide the possibility to adopt advanced fan rotor blade sweep design. [0003] The early fan blades were mainly made of titanium alloy materials, and there were damping shoulders protruding to both sides at ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/38F04D29/34F02K3/04
Inventor 洪杰马艳红陈璐璐张大义朱彬
Owner BEIHANG UNIV
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