Gas turbine engine temperature modulated cooling flow

A gas turbine engine cooling system comprising:

• a heat exchanger in fluid communication with a source of cooling air,
• at least a first cooling circuit including a first heat exchanger circuit in the heat exchanger,
• a first bypass circuit in the first cooling circuit including a first bypass valve for selectively bypassing at least a portion of first airflow around the first heat exchanger circuit,
• a second cooling circuit including a second heat exchanger circuit in the heat exchanger and a shutoff control valve operably disposed in the second cooling circuit upstream of the second heat exchanger circuit for modulating or shutting off and turning on a second airflow in the second cooling circuit, and
• the second cooling circuit operably connected to a heat source for cooling the heat source.

A gas turbine engine cooling system comprising:

• a heat exchanger in fluid communication with a source of cooling air,
• at least a first cooling circuit including a first heat exchanger circuit in the heat exchanger,
• a first bypass circuit in the first cooling circuit including a first bypass valve for selectively bypassing at least a portion of first airflow around the first heat exchanger circuit,
• a circuit inlet of the first cooling circuit operable for bleeding a portion of compressor discharge bleed air for the first airflow,
• the first cooling circuit including an annular flow inducer downstream of the first bypass valve and the heat exchanger,
• the flow inducer in fluid flow communication with a rotor disk and turbine blades mounted on the rotor disk,
• a second cooling circuit including a second heat exchanger circuit in the heat exchanger and a shutoff control valve operably disposed in the second cooling circuit upstream of the second heat exchanger circuit for modulating or shutting off and turning on a second airflow in the second cooling circuit, and
• the second cooling circuit operably connected to a heat source for cooling the heat source.

A gas turbine engine cooling system comprising:

• a heat exchanger in fluid communication with a source of cooling air,
• at least a first cooling circuit including a first heat exchanger circuit in the heat exchanger,
• a first bypass circuit in the first cooling circuit including a first bypass valve for selectively bypassing at least a portion of first airflow around the first heat exchanger circuit,
• a second cooling circuit including a second heat exchanger circuit in the heat exchanger,
• a second bypass circuit in the second cooling circuit, and
• a second bypass valve operably disposed in the second bypass circuit upstream of the second heat exchanger circuit for selectively bypassing at least a portion of second airflow around the second heat exchanger circuit.

An aircraft gas turbine engine comprising:

• in serial flow communication a fan, a high pressure compressor, an annular combustor, a high pressure turbine for powering the high pressure compressor, and a low pressure turbine for powering the fan,
• an annular nacelle surrounding the fan circumscribes an annular bypass duct located radially inwardly thereof,
• a gas turbine engine cooling system includes a heat exchanger in fluid communication with a source of cooling air on the engine,
• at least a first cooling circuit including a first heat exchanger circuit in the heat exchanger,
• a first bypass circuit in the first cooling circuit including a first bypass valve for selectively bypassing at least a portion of first airflow around the first heat exchanger circuit,
• the source of cooling air being the annular bypass duct,
• a second cooling circuit including a second heat exchanger circuit in the heat exchanger and a shutoff control valve operably disposed in the second cooling circuit upstream of the second heat exchanger circuit for modulating or shutting off and turning on a second airflow in the second cooling circuit, and
• the first and second heat exchanger circuits in fluid communication with the source of cooling air.

An aircraft gas turbine engine comprising:

• in serial flow communication a fan, a high pressure compressor, an annular combustor, a high pressure turbine for powering the high pressure compressor, and a low pressure turbine for powering the fan,
• an annular nacelle surrounding the fan circumscribes an annular bypass duct located radially inwardly thereof,
• a gas turbine engine cooling system includes a heat exchanger in fluid communication with a source of cooling air on the engine,
• at least a first cooling circuit including a first heat exchanger circuit in the heat exchanger,
• a first bypass circuit in the first cooling circuit including a first bypass valve for selectively bypassing at least a portion of first airflow around the first heat exchanger circuit,
• the source of cooling air being the annular bypass duct,
• a second cooling circuit including a second heat exchanger circuit in the heat exchanger and a shutoff control valve operably disposed in the second cooling circuit upstream of the second heat exchanger circuit for modulating or shutting off and turning on a second airflow in the second cooling circuit, and
• the second cooling circuit operably connected to a heat source for cooling the heat source.

An aircraft gas turbine engine comprising:

• in serial flow communication a fan, a high pressure compressor, an annular combustor, a high pressure turbine for powering the high pressure compressor, and a low pressure turbine for powering the fan,
• an annular nacelle surrounding the fan circumscribes an annular bypass duct located radially inwardly thereof,
• a gas turbine engine cooling system includes a heat exchanger in fluid communication with a source of cooling air on the engine,
• at least a first cooling circuit including a first heat exchanger circuit in the heat exchanger,
• a first bypass circuit in the first cooling circuit including a first bypass valve for selectively bypassing at least a portion of first airflow around the first heat exchanger circuit,
• the source of cooling air being the annular bypass duct,
• and a shutoff control valve operably disposed in a second cooling circuit upstream of the second heat exchanger circuit,
• a circuit inlet of the first cooling circuit operable for bleeding a portion of compressor discharge bleed air for the first airflow,
• the first heat exchanger circuit including a plurality of tube sets having heat transfer tubes between respective header sets of inlet headers and outlet headers,
• the second cooling circuit including a second heat exchanger circuit in the heat exchanger,
• a second bypass circuit in the second cooling circuit, and
• a second bypass valve operably disposed in the second bypass circuit upstream of the second heat exchanger circuit for selectively bypassing at least a portion of second airflow around the second heat exchanger circuit.

An aircraft gas turbine engine comprising:

• in serial flow communication a fan, a high pressure compressor, an annular combustor, a high pressure turbine for powering the high pressure compressor, and a low pressure turbine for powering the fan,
• an annular nacelle surrounding the fan circumscribes an annular bypass duct located radially inwardly thereof,
• a gas turbine engine cooling system includes a heat exchanger in fluid communication with the annular bypass duct,
• at least a first cooling circuit including a first heat exchanger circuit in the heat exchanger,
• a first bypass circuit in the first cooling circuit including a first bypass valve for selectively bypassing at least a portion of first airflow around the first heat exchanger circuit,
• a circuit inlet of the first cooling circuit operable for bleeding a portion of compressor discharge bleed air for the first airflow,
• the first cooling circuit including an annular flow inducer downstream of the first bypass valve and the heat exchanger,
• the flow inducer in fluid flow communication with a rotor disk and turbine blades mounted on the rotor disk,
• the first heat exchanger circuit including a plurality of tube sets having heat transfer tubes between respective header sets of inlet headers and outlet headers,
• a second cooling circuit including a second heat exchanger circuit in the heat exchanger,
• a second bypass circuit in the second cooling circuit, and
• a second bypass valve operably disposed in the second bypass circuit upstream of the second heat exchanger circuit for selectively bypassing at least a portion of second airflow around the second heat exchanger circuit.

A method for cooling gas turbine engine components comprising:

• flowing a first airflow from a compressor of a gas turbine engine through a first cooling circuit including a first heat exchanger circuit in a heat exchanger to one or more hot components,
• flowing cooling air through the heat exchanger,
• selectively bypassing at least a portion of the first airflow around the first heat exchanger circuit and the heat exchanger,
• controllably cooling a heat producing source using a second cooling circuit including a second heat exchanger circuit in the heat exchanger, and
• modulating or shutting off and turning on the second airflow with a control valve operably disposed in the second cooling circuit upstream of the second heat exchanger circuit and the heat exchanger.