Compressor system and methods for reducing cooling airflow
AssigneeGeneral Electric Company
InventorRobert J. Orlando
Life of this patent
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Abstract
A cooling airflow compressor system and methods for reducing a cooling airflow is described. The cooling airflow compressor system utilizes a primary high pressure compressor in combination with a secondary high pressure compressor to further compress a primary airflow. The secondary high pressure compressor includes a rotor driven by a high pressure turbine connected by a high pressure turbine shaft to the primary high pressure compressor. A heat exchanger is connected to the secondary high pressure compressor to further cool the cooling airflow. The cooling airflow is utilized to cool the turbine and a high pressure turbine vane.
Claims20
A cooling airflow compressor system for a turbine engine, said system comprising:
- a high pressure turbine;
- a first compressor comprising a stator casing, a plurality of rotor shrouds, and a plurality of stators and rotors connected to said turbine, said first compressor configured to be in flow communication with a combustor;
- a second compressor connected to, and in flow communication with, a high pressure turbine vane and said first compressor, said second compressor further connected to and in flow communication with said turbine, said second compressor configured to divert a portion of a primary airflow from said first compressor;
- and
- at least two heat exchangers in flow communication with said second compressor and said turbine, said heat exchangers configured to cool said diverted primary airflow from said first compressor, each said heat exchanger comprises a first inlet and a first outlet and a second inlet and a second outlet, each said first inlet in flow communication with said second compressor, each said first outlet in flow communication with said high pressure turbine vane.
A turbine engine comprising:
- a turbine;
- a combustor;
- a first compressor connected to said turbine, said first compressor comprising a first passageway extending therethrough, said first passageway comprising a plurality of stators and rotors, said stators and rotors surrounded by a stator casing and rotor shrouds, said first passageway in flow communication with said combustor;
- a second compressor connected to said turbine, said second compressor in flow communication with said first compressor and said turbine, said second compressor comprising a second passageway extending therethrough, said second passageway comprising at least one stator, an inlet, and at least one rotor, said second passageway inlet located at least one of upstream from said first compressor stators adjacent said combustor and downstream from said first compressor stators adjacent said combustor, said second passageway configured to divert a portion of a primary airflow from said first passageway and bypass said combustor;
- and
- at least one heat exchanger connected downstream from and in flow communication with said second compressor.
A method for reducing a cooling airflow utilized in a turbine engine including a first compressor in flow communication with a combustor, the first compressor connected to, and in flow communication with, a second compressor, the second compressor including at least one stator and at least one rotor, the second compressor in flow communication with a high pressure turbine vane and a high pressure turbine, the high pressure turbine connected to the first compressor and the second compressor, and at least two heat exchangers connected to the second compressor, said method comprising the steps of:
- diverting a portion of a primary airflow from the first compressor through a passageway to the second compressor to generate a cooling airflow, wherein the passageway is in flow communication with the heat exchangers, and wherein at least one of the heat exchangers is downstream from the second compressor;
- and
- increasing the pressure of the cooling airflow in the second compressor with the high pressure turbine.
Dependencies are inferred from the claim text.