Method for rotor blade tip clearance control and rotor blade manufactured by the method

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United States of America Patent

PATENT NO 12055048
APP PUB NO 20240011409A1
SERIAL NO

18251761

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ATTORNEY / AGENT: (SPONSORED)

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Abstract

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A rotor blade tip clearance control method and a rotor blade manufactured using same. The control method includes: coinciding, along an axial direction of an aircraft engine, a center of gravity of a rotor blade with a center of gravity of a rotor wheel disk supporting the rotor blade; rotating the rotor wheel disk to measure a leading edge deformation amount of the rotor blade; measuring a trailing edge deformation amount of the rotor blade; comparing the deformation amounts; and adjusting the center of gravity of the rotor wheel disk until the leading edge deformation amount tends to be approximately equal to the trailing edge deformation amount. The method can effectively improve or even solve the problem of inconsistent radial displacements of a leading edge and a trailing edge during the operation.

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Patent Owner(s)

Patent OwnerAddress
AECC COMMERCIAL AIRCRAFT ENGINE CO LTDROOM 301 NO 1 WORKSHOP NO 600 XINYUAN SOUTH ROAD LINGANG NEW TOWN PUDONG NEW AREA SHANGHAI 201306 SHANGHAI CITY SHANGHAI CITY 201306
AECC SHANGHAI COMMERCIAL AIRCRAFT ENGINE MANUFACTURING CO LTDNO 77 HONGYIN ROAD NICHENG TOWN PUDONG DISTRICT SHANGHAI 201306

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Cao, Chuanjun Shanghai, CN 3 0
Hu, Shuhui Shanghai, CN 11 300
Qin, Wen Shanghai, CN 3 28
Wang, Jiaguang Shanghai, CN 2 0
Wu, Zhiqing Shanghai, CN 8 22

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