Patent ID: 9732411
Date: 2017-08-15
CPC Classifications: B22D,B23P,C23C,F01D,F05D,Y10T

Claim:
1. A method for manufacturing a gas turbine blade, comprising the steps of: producing a gas turbine blade having a cooling pass inside thereof; and partially coating an inner surface of the cooling pass with Al; wherein the step of partially coating an inner surface of the cooling pass with Al comprising: a sample-substrates-preparing step of preparing a sample substrate A which comprises same composition of an actual machine of the gas turbine blade and preparing a sample substrate B which is applied an Al coating to the sample substrate A; a first step of specifying a temperature range which satisfies both of oxidation resistance and fatigue strength based on an examination result of a temperature dependency of each of the oxidation resistance and fatigue strength of each of the sample substrates A and B, and further specifying the temperature distribution of the inner surface of the cooling pass based on an examination result or result of a numerical analysis; a second step of setting an Al-coating-applying portion of the inner surface of the cooling pass as the temperature range specified at the first step; and a third step of applying Al coating only into the set Al-coating-applying portion.