Patent ID: 9140196
Filing Date: 2015-09-22
Classification: F02C,F05D

Abstract:
1. A method for controlling a gas turbine, wherein the gas turbine comprises a compressor for compressing inducted combustion air, a combustion chamber for generating hot gas by combusting a fuel with the aid of the compressed combustion air, and a multistage turbine for expanding the generated hot gas and performing work, wherein the method comprises: controlling the gas turbine in accordance with a hot gas temperature which is derived from a plurality of other measured operating variables of the gas turbine, wherein a derivation of the hot gas temperature is formed exclusively through pressure measurements at different spatial points in a flow direction in a region of hot gas flow of the gas turbine, wherein the pressure measurements are carried out in the hot gas flow which is generated in the combustion chamber, and wherein the pressure measurements include a pressure loss measurement in a main flow of the gas turbine.