Title:
STATIC BLADE AND AIRCRAFT GAS TURBINE ENGINE
Document Type and Number:
WIPO Patent Application WO/2021/199802
Kind Code:
A1
Abstract:
A static blade (30) provided in the rear of a rotor blade (21) comprises a blade main body (32) having a blade-shaped cross-section (31). The maximum blade thickness position (M) of the blade main body (32) in the blade-shaped cross-section (31) fulfills the following conditions on at least the tip (30b) side of the blade main body (32): (a) in a developed plane in the circumferential direction (CD) in which the static blade (30) is disposed, the position is in a first area close to a trailing edge (32b) of the blade main body (32), from an intersection (IP) between the blade main body (32) and a line (26) parallel to a line that passes through a line of extension (28) of a camber line (7) for the rotor blade (21) in the rear edge (21b) and passing through a leading edge (40a) of the other static blade (40) adjacent to the circumferential direction (CD); and (b) the position is in a second area (34) having a cord ratio of 0.2–0.8.
Inventors:
KUSUDA SHINYA (JP)
Application Number:
PCT/JP2021/007122
Publication Date:
October 07, 2021
Filing Date:
February 25, 2021
Export Citation:
Assignee:
IHI CORP (JP)
International Classes:
F01D9/02; F02K3/06; F04D29/54
Foreign References:
| JP2003172206A | 2003-06-20 | |||
| JP2016530440A | 2016-09-29 | |||
| US20190024581A1 | 2019-01-24 |
Attorney, Agent or Firm:
MIYOSHI Hidekazu et al. (JP)
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