Method and tool for measuring axial clearance between adjacent moving blades and stationary blades of turbomachinery of aero-engine
A technology of aero-engine and axial clearance, applied in the field of aero-engine, which can solve the problems of difficult measurement and difficult detection area.
Pending Publication Date: 2021-12-31
AECC COMML AIRCRAFT ENGINE CO LTD
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Problems solved by technology
Since the blades of the turbomachinery of the aero-engine are dense and the surface of the blades is an irregular curved surface, it is difficult for conventional measuring tools to pass through the blades to reach the detection area between the adjacent moving blades and stationary blades, and it is difficult to perform accurate measurement after reaching the detection area. Measurement
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[0023] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0024] The relative arrangements of components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. At the same time, it should be understood that, for the convenience of descriptio...
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The invention discloses a method and a tool for measuring the axial clearance between adjacent moving blades and stationary blades of turbomachinery of an aero-engine, and the method comprises the steps: feeding a first spherical measurement part into a detection area between the adjacent moving blades and stationary blades, and trying to enable the first spherical measurement part to pass through the detection area, wherein the diameter of the first spherical measuring part is equal to the maximum qualified value of the axial clearance of the adjacent moving blade and static blade in the detection area; sending a second spherical measuring part to a detection area between the adjacent moving blade and the fixed blade, and trying to allow the second spherical measuring part to pass through the detection area, wherein the diameter of the second spherical measuring part is equal to the minimum qualified value of the axial clearance of the adjacent moving blade and the fixed blade in the detection area; and if the first spherical measuring part cannot pass through the detection area and the second spherical measuring part can pass through the detection area, determining that the axial clearance of the adjacent moving blade and static blade in the detection area is qualified.
Description
technical field [0001] The invention relates to the technical field of aero-engines, in particular to a method for measuring axial gaps between adjacent moving blades and stationary blades of a turbomachinery of an aero-engine and an axial gap measuring tool. Background technique [0002] Aeroengine turbomachinery, such as low-pressure compressors, high-pressure compressors, high-pressure turbines, low-pressure turbines, etc., include moving blades and stationary blades. During the assembly process, it is often necessary to judge whether the moving blade and the stationary blade are assembled in place, and it is necessary to judge whether the axial clearance between the moving blade and the stationary blade is qualified. The measuring tool needs to pass through the gap between two adjacent moving blades (or stationary blades) to reach the axial gap between the adjacent moving blades and stationary blades. Since the blades of the turbomachinery of the aero-engine are dense a...
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IPC IPC(8): G01B5/14
CPCG01B5/14
Inventor 胡一廷母文省任家海周宇乾
Owner AECC COMML AIRCRAFT ENGINE CO LTD