BLADE EDGE PLATES, BLADE RING, IMPELLER DISK, AND GAS TURBINE ENGINE

WIPO Patent Application WO/2022/105823

A1

Blade edge plates (6, 7, 8), a blade ring (100), an impeller disk, and a gas turbine engine. The blade edge plate (7) comprises a pair of side edges (71, 72) and a pair of bottom edges (73, 74); in the extension direction thereof, the first side edge (71) comprises a straight line segment (700) and an arc segment (800); the straight line segment (700) comprises a first straight line segment (701) and a second straight line segment (702); the arc segment (800) comprises a first arc segment (801) and a second arc segment (802); the first straight line segment (701) and the second straight line segment (702) are respectively connected to two ends of the arc segment (800), and are tangential to the arc segment (800); the slopes of the first arc segment (801) and the second arc segment (802) of the arc segment (800) are the same; and the first arc segment (801) and the second arc segment (802) are externally tangentially connected.

WU ZHIQING (CN)
LU XIAOFENG (CN)
YAN DONGQING (CN)
JIANG BEN (CN)
LI JIBAO (CN)
YIN ZEYONG (CN)
LIU HAO (CN)

PCT/CN2021/131424

May 27, 2022

November 18, 2021

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AECC SHANGHAI COMMERCIAL AIRCRAFT ENGINE MFG CO LTD (CN)
AECC COMMERCIAL AIRCRAFT ENGINE CO LTD (CN)

F04D29/26; F01D5/14; F01D5/30; F04D29/60

CN112096653A	2020-12-18
CN105814281A	2016-07-27
US3897171A	1975-07-29
US5242270A	1993-09-07
DE102016219837A1	2018-04-12
DE102016211344A1	2017-12-28
CN105473824A	2016-04-06
CN106593545A	2017-04-26
CN208546354U	2019-02-26

SHANGHAI PATENT & TRADEMARK LAW OFFICE, LLC (CN)

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