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公开(公告)号：US20240141835A1
公开(公告)日：2024-05-02
申请号：US17978629
申请日：2022-11-01
发明人： Daniel Alan Niergarth , Jeffrey Donald Clements , Jeffrey S. Spruill , Daniel Endecott Osgood , Erich Alois Krammer , Matthew Kenneth MacDonald , Scott Alan Schimmels
CPC分类号： F02C9/16 , F02C7/18 , F05D2260/20 , F05D2270/303
摘要： A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT/(AHPCExit2×1000).
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公开(公告)号：US20240254922A1
公开(公告)日：2024-08-01
申请号：US18500517
申请日：2023-11-02
发明人： Daniel Alan Niergarth , Jeffrey Donald Clements , Jeffrey S. Spruill , Daniel Endecott Osgood , Erich Alois Krammer , Matthew Kenneth MacDonald , Scott Alan Schimmels
摘要： A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT/(AHPCExit2×1000).
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公开(公告)号：US12078107B2
公开(公告)日：2024-09-03
申请号：US18500517
申请日：2023-11-02
发明人： Daniel Alan Niergarth , Jeffrey Donald Clements , Jeffrey S. Spruill , Erich Alois Krammer , Matthew Kenneth MacDonald , Scott Alan Schimmels
摘要： A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT/(AHPCExit2×1000).
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