Gas turbine and a method for controlling a gas turbine
AssigneeVolvo Aero Corporation
InventorLars Sundin
Life of this patent
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Abstract
Method and arrangement for providing and controlling a gas turbine (1) at least one turbine (11, 20, 20′), at least one compressor (2, 5) driven by the turbine and a combustion chamber (16) arranged between the compressor and the turbine in the airflow path. The gas turbine includes devices (8) for direct measurement of the air mass flow at a position upstream of the combustion chamber in the airflow path, with the aim of regulating the quantity of fuel that is delivered to the combustion chamber (16) on the basis of the measured air mass flow.
Claims10
A gas turbine (1), comprising:
- at least one turbine (11,20, 20′), at least one compressor (2,5) driven by the turbine and a combustion chamber (16) arranged between the compressor and the turbine in an airflow path of the gas turbine (1);
- and
- said gas turbine further comprising measurement means (8) for directly measuring the air mass flow at a position upstream of the combustion chamber (16) in the airflow path and a regulating means that regulates the quantity of fuel delivered to the combustion chamber in dependence on the measured air mass flow;
- wherein the measurement means (8) further comprises one of (1) hot-film and (2) hot-wire for measurement taking.
A gas turbine (1), comprising:
- at least one turbine (11,20, 20′), at least one compressor (2,5) driven by the turbine and a combustion chamber (16) arranged between the compressor and the turbine in an airflow path of the gas turbine (1);
- and
- said gas turbine further comprising measurement means (8) for directly measuring the air mass flow at a position upstream of the combustion chamber (16) in the airflow path and a regulating means that regulates the quantity of fuel delivered to the combustion chamber in dependence on the measured air mass flow;
- wherein the gas turbine (1) further comprises a heat exchanger (14) arranged between the compressor (2,5) and the combustion chamber (16) for recovering exhaust gas heat.
A gas turbine (1), comprising:
- at least one turbine (11,20, 20′), at least one compressor (2,5) driven by the turbine and a combustion chamber (16) arranged between the compressor and the turbine in an airflow path of the gas turbine (1);
- and
- said gas turbine further comprising measurement means (8) for directly measuring the air mass flow at a position upstream of the combustion chamber (16) in the airflow path and a regulating means that regulates the quantity of fuel delivered to the combustion chamber in dependence on the measured air mass flow;
- wherein the gas turbine (1) further comprises temperature measuring means (28) for measuring the temperature of the air at a position upstream of the combustion chamber (16) in the airflow path and a fuel regulating means for regulating the quantity of fuel that is delivered to the combustion chamber in dependence on the measured temperature.
A method for controlling a gas turbine, comprising:
- directly measuring an air mass flow in the airflow path of the gas turbine at a position upstream of a combustion chamber (16) thererof, and
- regulating the quantity of fuel that is delivered to the combustion chamber based on the measured air mass flow;
- wherein the airflow is measured using one of (1) a hot-film and (2) hot-wire technology.
A method for controlling a gas turbine, comprising:
- directly measuring an air mass flow in the airflow path of the gas turbine at a position upstream of a combustion chamber (16) thererof, and
- regulating the quantity of fuel that is delivered to the combustion chamber based on the measured air mass flow;
- wherein the temperature of the air is measured at a position upstream of the combustion chamber (16) of the gas turbine in the airflow path and the quantity of fuel that is delivered to the combustion chamber is regulated on the basis of the measured air temperature.
Dependencies are inferred from the claim text.