CPC F23N 5/18 (2013.01) [F23R 3/28 (2013.01); G01F 1/42 (2013.01); F23N 2005/185 (2013.01); F23N 2241/20 (2020.01); G01F 15/002 (2013.01)] | 8 Claims |
1. A method for determining a flow rate of combustible fluid injected into a combustion chamber of a turbine, the combustible fluid being a gas mixture and injected into the combustion chamber through an orifice of at least one injector, said orifice being arranged inside the combustion chamber, the method comprising the following steps:
injecting the combustible fluid into the combustion chamber through the orifice of the at least one injector,
determining a cross section of the orifice of said at least one injector through which the combustible fluid is injected into the combustion chamber,
determining a pressure of the combustible fluid upstream of the orifice of the at least one injector,
determining a pressure downstream of the orifice of the at least one injector,
determining the flow rate of combustible fluid flowing through the orifice of said at least one injector as a function of the determined cross section of the orifice of said at least one injector, of the determined pressure of the combustible fluid upstream of the orifice of the at least one injector, and of the determined pressure downstream of the orifice of the at least one injector,
determining the flow rate of combustible fluid injected into the combustion chamber as a function of the pressure difference between the pressure of the combustible fluid upstream of the orifice and the pressure of the combustible fluid downstream of the orifice, across said at least one injector,
wherein the pressure of the combustible fluid upstream of the orifice of the at least one injector is determined indirectly by measuring the difference in pressure between a combustible-fluid line and the pressure of the compressed air leaving a compressor.
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