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公开(公告)号：US20220235706A1
公开(公告)日：2022-07-28
申请号：US17160742
申请日：2021-01-28
发明人： Michael Robert Millhaem , Christopher R. Bosco , Gerardo Perez , Hejie Li , Francisco Ernesto de la Pena , Alejandro Federico Medrano Perez , Andrew Campbell
摘要： A method is provided for operating a gas turbine engine. The method includes: determining data indicative of an operation of a cooling system of the gas turbine engine during a shutdown of the gas turbine engine, following the shutdown of the gas turbine engine, or both; and modifying a startup schedule of the gas turbine engine in response to the determined data indicative of the operation of the cooling system of the gas turbine engine.
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公开(公告)号：US11536198B2
公开(公告)日：2022-12-27
申请号：US17379261
申请日：2021-07-19
发明人： Michael Robert Millhaem , Christopher R. Bosco , Gerardo Perez , Hejie Li , Francisco Ernesto de la Pena , Alejandro Federico Medrano Perez , Andrew Campbell
摘要： A gas turbine engine includes a core cowl and a core contained within the core cowl. The core includes a compressor in fluid communication with a downstream combustor and a downstream turbine, the compressor including a compressor bleed port, wherein an undercowl space is defined between the core cowl and the core. The gas turbine engine further includes a cooling duct disposed at least partially in the undercowl space and having an inlet and an outlet, wherein the cooling duct is in fluid communication with a source of cooling air and is further in fluid communication with the compressor bleed port; a valve assembly including at least one valve disposed in the cooling duct; and a cooling blower disposed within the engine and operable to move an air flow from the inlet of the cooling duct towards the outlet of the cooling duct and through the compressor bleed port.
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公开(公告)号：US20220235707A1
公开(公告)日：2022-07-28
申请号：US17379261
申请日：2021-07-19
发明人： Michael Robert Millhaem , Christopher R. Bosco , Gerardo Perez , Hejie Li , Francisco Ernesto de la Pena , Alejandro Federico Medrano Perez , Andrew Campbell
摘要： A gas turbine engine includes a core cowl and a core contained within the core cowl. The core includes a compressor in fluid communication with a downstream combustor and a downstream turbine, the compressor including a compressor bleed port, wherein an undercowl space is defined between the core cowl and the core. The gas turbine engine further includes a cooling duct disposed at least partially in the undercowl space and having an inlet and an outlet, wherein the cooling duct is in fluid communication with a source of cooling air and is further in fluid communication with the compressor bleed port; a valve assembly including at least one valve disposed in the cooling duct; and a cooling blower disposed within the engine and operable to move an air flow from the inlet of the cooling duct towards the outlet of the cooling duct and through the compressor bleed port.
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公开(公告)号：US12031484B2
公开(公告)日：2024-07-09
申请号：US17160742
申请日：2021-01-28
发明人： Michael Robert Millhaem , Christopher R. Bosco , Gerardo Perez , Hejie Li , Francisco Ernesto de la Pena , Alejandro Federico Medrano Perez , Andrew Campbell
CPC分类号： F02C7/18 , F01D25/12 , F01D21/12 , F02C9/18 , F05D2220/323 , F05D2220/50 , F05D2240/35 , F05D2260/20 , F05D2270/303 , F05D2270/3032 , F05D2270/304
摘要： A method is provided for operating a gas turbine engine. The method includes: determining data indicative of an operation of a cooling system of the gas turbine engine during a shutdown of the gas turbine engine, following the shutdown of the gas turbine engine, or both; and modifying a startup schedule of the gas turbine engine in response to the determined data indicative of the operation of the cooling system of the gas turbine engine.
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