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Title:
ROTOR BLADE TIP CLEARANCE CONTROL METHOD AND ROTOR BLADE MANUFACTURED USING SAME
Document Type and Number:
WIPO Patent Application WO/2022/095720
Kind Code:
A1
Abstract:
A rotor blade tip clearance control method and a rotor blade manufactured using same. The control method comprises the following steps: coinciding, along an axial direction (D) of an aircraft engine, the center of gravity (GB) of a rotor blade (20) with the center of gravity (GD) of a rotor wheel disk (10) supporting the rotor blade (20); rotating the rotor wheel disk (10) to measure a leading edge deformation amount (Δ1) of a leading edge (21) of the rotor blade (20); measuring a trailing edge deformation amount (Δ2) of a trailing edge (22) of the rotor blade (20); comparing the leading edge deformation amount (Δ1) with the trailing edge deformation amount (Δ2); and adjusting the center of gravity (GD) of the rotor wheel disk (10) until the leading edge deformation amount (Δ1) tends to be approximately equal to the trailing edge deformation amount (Δ2). 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 of a rotor blade tip.

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Inventors:
WANG JIAGUANG (CN)
HU SHUHUI (CN)
QIN WEN (CN)
CAO CHUANJUN (CN)
WU ZHIQING (CN)
Application Number:
PCT/CN2021/125466
Publication Date:
May 12, 2022
Filing Date:
October 22, 2021
Export Citation:
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Assignee:
AECC SHANGHAI COMMERCIAL AIRCRAFT ENGINE MFG CO LTD (CN)
AECC COMMERCIAL AIRCRAFT ENGINE CO LTD (CN)
International Classes:
F04D29/32; F04D29/38
Domestic Patent References:
WO2016063604A12016-04-28
Foreign References:
US5725354A1998-03-10
CN112032105A2020-12-04
CN111306111A2020-06-19
GB1215300A1970-12-09
GB659163A1951-10-17
US20140112757A12014-04-24
CN201580032222A2015-08-18
Attorney, Agent or Firm:
SHANGHAI PATENT & TRADEMARK LAW OFFICE, LLC (CN)
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