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US 6,202,399 B1Granted
Method for regulating a gas turbo-generator set
AssigneeAsea Brown Boveri AG
InventorHans Ulrich Frutschi
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AssigneeAsea Brown Boveri AG
InventorHans Ulrich Frutschi
Estimating the term…
In a method for regulation a gas turbo-generator set operated with sequential combustion, the fuel quantity necessary for operating the first combustion changer is first controlled as a function of a pressure prevailing at the outlet of the compressor. The ratio between this fuel quantity and this pressure is continuously updated by means of a factor reproducing the deviation of a temperature at the inlet into the first turbine from the desired value of this temperature. A fuel quantity necessary for operating the second combustion chamber is controlled as a function of a pressure prevailing at the inlet into the second turbine, and the ratio between this fuel quantity and this pressure is likewise continually updated by means of a factor reproducing the deviation of the inlet temperature into the second turbine from the desired value of this temperature. The inertias in the system are neutralized by means of this pressure backup regulation.
A method for regulating a gas turbo-generator set, comprising a compressor unit, a first combustion chamber following the compressor unit, a first turbine following the first combustion chamber, a second combustion chamber which follows the first turbine and operates by autoignition and the hot gases of which act upon a second turbine, and at least one generator, controlling a fuel quantity FH necessary for operating the first combustion chamber as a function of a pressure P3 prevailing at the outlet of the compressor, wherein the ratio between the fuel quantity FH and the pressure P3 is continuously updated by means of a factor K1 which is a measure for the deviation of a temperature T7 at the inlet into the first turbine from the desired value of this temperature T7des, wherein a fuel quantity FL necessary for operating the second combustion chamber is controlled as a function of a pressure P11 prevailing at the inlet into the second turbine, and wherein the ratio between this fuel quantity FL and this pressure P11 is likewise continuously updated by means of a second factor K2 which is a measure for deviation of the inlet temperature T11 into the second turbine from the desired value of this temperature T11des.
A method for regulating a gas turbo-generator set, comprising a compressor unit, a first combustion chamber following the compressor unit, a first turbine following the first combustion chamber, a second combustion chamber which follows the first turbine and operates by autoignition and the hot gases of which act upon a second turbine, and at least one generator, controlling a fuel quantity FH necessary for operating the first combustion chamber as a function of a pressure relevant for the mass throughput of the gas turbo-generator set, wherein the ratio between the fuel quantity FH and the pressure is continuously updated by means of a factor K1 which is a measure for the deviation of a temperature T7 at the inlet into the first turbine from the desired value of this temperature T7des, wherein a fuel quantity FL necessary for operating the second combustion chamber is controlled as a function of a pressure P11 prevailing at the inlet into the second turbine, and wherein the ratio between this fuel quantity FL and this pressure P11 is likewise continuously updated by means of a second factor K2 which is a measure for deviation of the inlet temperature T11 into the second turbine from the desired value of this temperature T11des.
A method for regulating a gas turbo-generator set, comprising a compressor unit, a first combustion chamber following the compressor unit, a first turbine following the first combustion chamber, a second combustion chamber which follows the first turbine and operates by autoignition and the hot gases of which act upon a second turbine, and at least one generator, controlling a fuel quantity FH necessary for operating the first combustion chamber as a function of a pressure P3 prevailing at the outlet of the compressor, wherein the ratio between the fuel quantity FH and the pressure P3 is continuously updated by means of a factor K1 which is a measure for the deviation of a temperature T7 at the inlet into the first turbine from the desired value of this temperature T7des, wherein a fuel quantity FL necessary for operating the second combustion chamber is controlled as a function of a pressure relevant for the mass throughput of the gas turbo-generator set, and wherein the ratio between this fuel quantity FL and the pressure relevant to the mass throughput is likewise continuously updated by means of a second factor K2 which is a measure for deviation of the inlet temperature T11 into the second turbine from the desired value of this temperature T11des.
Dependencies are inferred from the claim text.