Title:
タービン翼の設計方法、タービン翼の製造方法及びタービン翼
Document Type and Number:
Japanese Patent JP6685800
Kind Code:
B2
Abstract:
A turbine blade designing method is for designing a turbine blade formed using a metal material in which creep including diffusion creep and dislocation creep occurs by heating. The turbine blade designing method includes: acquiring temperature distribution data relating to temperature distribution in the turbine blade to be heated; acquiring creep strength distribution data relating to distribution of the creep strength required for the turbine blade to be heated; from the correlation data, based on the temperature distribution data and the creep strength distribution data, setting the crystal grain size of a high-temperature portion that is the diffusion creep temperature range of the turbine blade to a size coarser than the reference crystal grain size, and setting the crystal grain size of a low-temperature portion that is the dislocation creep temperature range of the turbine blade to a size finer than the reference crystal grain size.
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Inventors:
Hideaki Kaneko
Kenji Yamamoto
Takanori Karato
Kenji Hirata
Naoya Fujita
Kenji Yamamoto
Takanori Karato
Kenji Hirata
Naoya Fujita
Application Number:
JP2016071250A
Publication Date:
April 22, 2020
Filing Date:
March 31, 2016
Export Citation:
Assignee:
MITSUBISHI HEAVY INDUSTRIES,LTD.
International Classes:
F01D5/28; B22D27/04; F01D9/02; F01D25/00; F02C7/00
Domestic Patent References:
| JP3004301B2 | ||||
| JP8200001A | ||||
| JP10317105A | ||||
| JP55057369A | ||||
| JP2002331353A |
Foreign References:
| US3790303 |
Attorney, Agent or Firm:
Sakai International Patent Office