Patent ID: 9422869
Filing Date: 2016-08-23
CPC Classification: F02C,F05D

Claim Text:
1. A method of tuning a gas turbine engine, said method comprising: (a) operating the gas turbine engine at a first operating state wherein the gas turbine engine is operated at a nominal firing temperature, and measuring a first set of values for a plurality of operating parameters of the gas turbine engine at the first operating state; (b) operating the gas turbine engine at a second operating state wherein the gas turbine engine is operated at a nominal power output, and measuring a second set of values for the plurality of operating parameters at the second operating state; (c) operating the gas turbine engine at a third operating state wherein the gas turbine engine is operated at a nominal value for a selected measureable output of the gas turbine engine, wherein the selected measurable output correlates to an actual firing temperature of the gas turbine engine, and measuring a third set of values for the plurality of operating parameters at the third operating state; (d) generating a firing temperature correction factor based on the first, second, and third sets of values for the plurality of operating parameters; and (e) adjusting the operation of the gas turbine engine based on the firing temperature correction factor.