Aeroengine and method for on-wing assessment of tip clearance of an aeroengine
A technology for aero-engines and compressors, which is applied in the direction of machines/engines, mechanical clearance measurement, liquid fuel engines, etc. It can solve the problems of inability to understand the change of blade tip clearance, difficulty in measuring rotor blade tip and casing, etc.
Active Publication Date: 2021-03-26
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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Problems solved by technology
[0007] However, in the existing field of aero-engines, it is difficult to measure the tip clearance between the rotor blade tip and the casing of the aero-engine during wing operation, and then it is impossible to understand the blade tip clearance during wing operation. changes in conditions
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[0034] In order to facilitate understanding of the present invention, the following will be combined with the attached Figure 2-4 Preferred embodiments of the present invention are described in detail. It should be understood that what is shown in the drawings is only a preferred embodiment of the present invention, which is not intended to limit the scope of the present invention. Those skilled in the art can make various obvious modifications, variations, and equivalent replacements to the present invention on the basis of the embodiments shown in the drawings, and these all fall within the protection scope of the present invention.
[0035] figure 2 A partial cross-sectional view of a portion of the aeroengine of the present invention is shown. An aero-engine includes a compressor part, which is generally composed of a rotor and a stator, wherein the rotor refers to the general term of the parts that can rotate in the compressor part, and the stator refers to the genera...
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A compressor part of an aero-engine includes a rotor and a stator, the rotor includes rotor blades, the stator includes a casing, and an abrasion-resistant coating is coated on the inner surface of the casing. At least two grooves are provided on the blade tip of at least one of the rotor blades, and the depth of each groove is different from that of any other groove. At least two marker pieces are provided at the portion of the abradable coating facing the rotor blade, wherein the thickness of each marker piece is different from the thickness of any other marker piece. Probe holes are also provided on the aero-engine to allow the monitoring device to be inserted into the interior of the aero-engine via the probing hole, and the monitoring device is aimed at the area of the marking block and the groove to obtain images of the marking block and the groove . The aeroengine with this structure helps to evaluate the change trend of the blade tip clearance and guide the subsequent optimization design. It also relates to a method for on-wing assessment of the tip clearance of an aeroengine.
Description
technical field [0001] The present invention relates to the field of aero-engines, in particular to the design of blade structures such as rotor blades in compressors of aero-engines, and to a method for on-wing evaluation of the tip clearances of these blades. Background technique [0002] The aeroengine is an important part of the aircraft, which provides power for the flight of the aircraft. In the existing aero-engine structure, it generally includes a rotor part and a stator part, wherein the rotor part is a part, assembly, etc. that can rotate around a fixed axis in the aero-engine, and the stator part is a non-rotating part, assembly, etc. [0003] figure 1 A partial schematic diagram of an existing aero-engine structure is shown. In this adaptive structure, the aeroengine comprises a hub 1 and a casing 2 arranged around the hub 1 on the outside of the hub 1, and an air passage for the airflow A to flow through is defined between the hub 1 and the casing 2 5. The ...
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IPC IPC(8): F04D29/16F04D27/00G01B5/14G01N19/00G06T7/00
CPCF04D27/001F04D29/161G01B5/14G01N19/00G06T7/0002
Inventor 陆晓锋童辉秦文吴志青曹传军李继保
Owner AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD