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1. (WO2017168777) TURBINE BLADE DESIGNING METHOD, TURBINE BLADE MANUFACTURING METHOD, AND TURBINE BLADE

Pub. No.:    WO/2017/168777    International Application No.:    PCT/JP2016/074367
Publication Date: Fri Oct 06 01:59:59 CEST 2017 International Filing Date: Tue Aug 23 01:59:59 CEST 2016
IPC: F01D 5/28
B22D 27/04
C21D 9/00
C22F 1/10
F01D 25/00
Applicants: MITSUBISHI HEAVY INDUSTRIES, LTD.
三菱重工業株式会社
Inventors: KANEKO, Hideaki
金子 秀明
YAMAMOTO, Kenji
山本 賢二
KARATO, Takanori
唐戸 孝典
HIRATA, Norifumi
平田 憲史
FUJITA, Naoya
藤田 直也
Title: TURBINE BLADE DESIGNING METHOD, TURBINE BLADE MANUFACTURING METHOD, AND TURBINE BLADE
Abstract:
Provided is a turbine blade designing method for designing a turbine blade, wherein: correlation data associating heating temperature range, creep strength, and crystal grain size is prepared in advance; and the method is provided with a temperature distribution acquisition step S11 in which temperature distribution data relating to temperature distribution in a heated turbine blade is acquired, a creep strength acquisition step S12 in which creep strength distribution data relating to the distribution of creep strength required of the heated turbine blade is acquired, and a crystal grain size setting step S13 in which, on the basis of the temperature distribution data and the creep strength distribution data, the crystal grain size in a high-temperature site that is in the diffusion creep temperature range for the turbine blade is set to be coarser than a reference crystal grain size used as a reference, and the crystal grain size in a low-temperature site that is in the dislocation creep temperature range for the turbine blade is set to be finer than the reference crystal grain size.