Inlet stage blade assembly for gas compressor and axial flow gas compressor comprising same

An axial flow compressor and a technology of compressors, which are applied in the components of pumping devices for elastic fluids, machines/engines, pump elements, etc., can solve the problems of uneven radial deformation of the leading edge and trailing edge, etc. The effect of improving stall margin, radial deformation coordination, and improving workability

Active Publication Date: 2021-09-03
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The technical problem to be solved by the present invention is how to improve the working capacity of the blade tip of the first-stage moving blade of the compressor, improve its stall margin, and at the same time

Method used

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  • Inlet stage blade assembly for gas compressor and axial flow gas compressor comprising same
  • Inlet stage blade assembly for gas compressor and axial flow gas compressor comprising same
  • Inlet stage blade assembly for gas compressor and axial flow gas compressor comprising same

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Embodiment Construction

[0053] In the following, the present invention will be more clearly and completely described by means of an embodiment in conjunction with the accompanying drawings, but the present invention is not limited to the scope of the embodiment.

[0054] It should be understood that the use of words such as "first" and "second" to define technical features is only for the convenience of distinguishing corresponding technical features. Limitations on the scope of protection of the present invention. For example, "one embodiment", "another embodiment" means a certain feature, structure or feature related to at least one embodiment of the present application. In addition, certain features, structures or characteristics of one or more embodiments of the present application may be properly combined.

[0055] It should be noted that these and other subsequent drawings are only examples, which are not drawn according to the same scale, and should not be taken as limitations on the protecti...

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Abstract

The invention discloses an inlet stage blade assembly for a gas compressor and an axial flow gas compressor comprising the same. The inlet stage blade assembly comprises an inlet guide blade and a first stage moving blade, wherein the position of the inlet guide blade with the largest trailing edge metal angle is a first position, and the relative blade height T at the first position is larger than or equal to 0.8 and smaller than or equal to 0.9; the blade-shaped section of the first-stage moving blade at the blade tip has a first chord length, the blade-shaped section of the first-stage moving blade at the second position with the relative blade height being T has a second chord length, and the first chord length is 3%-10% larger than the second chord length; and between the second position and the blade tip of the first-stage moving blade, the sweepforward or sweepback degree of the stacking shaft of the first-stage moving blade does not exceed 1% of the absolute blade height of the first-stage moving blade. By the adoption of the structure, the stall margin of the blade tip of the first-stage movable blade can be improved, and radial deformation of the front edge and the tail edge of the first-stage movable blade from the static state to the running state is more coordinated.

Description

technical field [0001] The invention relates to an inlet-stage blade assembly for a compressor and an axial compressor comprising the same. Background technique [0002] Inlet guide vanes are a common component in compressor components for aero-engines, gas turbines, and ground-based axial flow compressors. The inlet guide vane is the first row of stator blades at the compressor inlet. Its function is usually to deflect the axial flow, so that it has a certain tangential component velocity, and the direction of the tangential component velocity is the same as the rotor rotation direction. In this way, the incoming Mach number of the first-stage moving blades (rotor blades) will be lower than that without guide vanes, so the loss is smaller and the efficiency is higher. In addition, the inlet guide vane is usually designed to be adjustable, and its installation angle will be changed as the operating conditions of the compressor change, so as to keep the first-stage rotor bla...

Claims

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Application Information

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IPC IPC(8): F04D29/54F04D29/38
CPCF04D29/541F04D29/384
Inventor 刘天一王进春曹传军
Owner AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD
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