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公开(公告)号：US20230323818A1
公开(公告)日：2023-10-12
申请号：US18202550
申请日：2023-05-26
Applicant: Raytheon Technologies Corporation
Inventor： Stephen G. Pixton , Matthew R. Feulner , Marc J. Muldoon , Xinwen Xiao
IPC: F02C7/36
CPC classification number: F02C7/36 , F05D2220/36 , F05D2260/40311
Abstract: A fan section includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor is a four-stage low pressure compressor. The low pressure turbine is a three-stage low pressure turbine. A high spool including a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine-stage high pressure compressor. The high pressure turbine is a two-stage high pressure turbine. An exhaust gas exit temperature of greater than 900 degrees Fahrenheit and less than 1000 degrees Fahrenheit at maximum take-off.
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公开(公告)号：US20230022122A1
公开(公告)日：2023-01-26
申请号：US17379308
申请日：2021-07-19
Applicant: Raytheon Technologies Corporation
Inventor： Stephen G. Pixton , Matthew R. Feulner , Marc J. Muldoon , Xinwen Xiao
IPC: F02C7/36
Abstract: A fan section includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor is a four-stage low pressure compressor. The low pressure turbine is a three-stage low pressure turbine. A high spool including a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine-stage high pressure compressor. The high pressure turbine is a two-stage high pressure turbine. An exhaust gas exit temperature of greater than 900 degrees Fahrenheit and less than 1000 degrees Fahrenheit at maximum take-off.
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公开(公告)号：US11754000B2
公开(公告)日：2023-09-12
申请号：US17379308
申请日：2021-07-19
Applicant: Raytheon Technologies Corporation
Inventor： Stephen G. Pixton , Matthew R. Feulner , Marc J. Muldoon , Xinwen Xiao
IPC: F02C7/36
CPC classification number: F02C7/36 , F05D2220/36 , F05D2260/40311
Abstract: A fan section includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor is a four-stage low pressure compressor. The low pressure turbine is a three-stage low pressure turbine. A high spool including a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine-stage high pressure compressor. The high pressure turbine is a two-stage high pressure turbine. An exhaust gas exit temperature of greater than 900 degrees Fahrenheit and less than 1000 degrees Fahrenheit at maximum take-off.
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公开(公告)号：US20230026997A1
公开(公告)日：2023-01-26
申请号：US17379270
申请日：2021-07-19
Applicant: Raytheon Technologies Corporation
Inventor： Stephen G. Pixton , Ronald S. Walther , Matthew R. Feulner , Fuhua Ma , Ozhan Turgut
Abstract: A gas turbine engine includes a fan section that includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. A high spool includes a high pressure turbine that drives a high pressure compressor. The high pressure compressor includes a pressure ratio of greater than 6.5 and less than 11.5. A ratio of a product of a pressure ratio of the fan with a pressure ratio of the low pressure compressor pressure to the pressure ratio of the high pressure compressor is greater than 0.35 and less than 0.90. An exhaust gas exit temperature is greater than 900 degrees Fahrenheit and less than 1000 degrees Fahrenheit at maximum take-off.
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公开(公告)号：US11674407B2
公开(公告)日：2023-06-13
申请号：US17688094
申请日：2022-03-07
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Matthew R. Feulner
CPC classification number: F01D11/20 , F02K3/06 , F05D2220/323 , F05D2240/307 , F05D2240/55 , F05D2260/80 , F05D2270/20 , F05D2270/42
Abstract: A system for controlling blade tip clearances in a gas turbine engine may comprise an active clearance control system and a controller in operable communication with the active clearance control system. The controller may be configured to identify a cruise condition, reduce a thrust limit of the gas turbine engine to a de-rated maximum climb thrust, determine a first target tip clearance based on the de-rated maximum climb thrust, and send a command signal correlating to the first target tip clearance to the active clearance control system.
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Patent Agency Ranking
公开(公告)号：US20220341340A1
公开(公告)日：2022-10-27
申请号：US17688094
申请日：2022-03-07
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Matthew R. Feulner
Abstract: A system for controlling blade tip clearances in a gas turbine engine may comprise an active clearance control system and a controller in operable communication with the active clearance control system. The controller may be configured to identify a cruise condition, reduce a thrust limit of the gas turbine engine to a de-rated maximum climb thrust, determine a first target tip clearance based on the de-rated maximum climb thrust, and send a command signal correlating to the first target tip clearance to the active clearance control system.
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公开(公告)号：US20230258192A1
公开(公告)日：2023-08-17
申请号：US18141049
申请日：2023-04-28
Applicant: Raytheon Technologies Corporation
Inventor： Stephen G. Pixton , Matthew R. Feulner , Marc J. Muldoon , Xinwen Xiao
CPC classification number: F04D25/02 , F02C7/36 , F02C9/18 , F02K3/06 , F05D2220/32 , F05D2260/4031
Abstract: A gas turbine engine includes a fan section that includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor includes a greater number of stages than the low pressure turbine. A high spool includes a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine stage high pressure compressor and includes a pressure ratio per stage of greater than or equal to 1.20 and less than or equal to 1.33.
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公开(公告)号：US11719245B2
公开(公告)日：2023-08-08
申请号：US17379329
申请日：2021-07-19
Applicant: Raytheon Technologies Corporation
Inventor： Stephen G. Pixton , Matthew R. Feulner , Marc J. Muldoon , Xinwen Xiao
CPC classification number: F04D25/02 , F02C7/36 , F02C9/18 , F02K3/06 , F05D2220/32 , F05D2260/4031
Abstract: A gas turbine engine includes a fan section that includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor includes a greater number of stages than the low pressure turbine. A high spool includes a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine stage high pressure compressor and includes a pressure ratio per stage of greater than or equal to 1.20 and less than or equal to 1.33.
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公开(公告)号：US20230028763A1
公开(公告)日：2023-01-26
申请号：US17379329
申请日：2021-07-19
Applicant: Raytheon Technologies Corporation
Inventor： Stephen G. Pixton , Matthew R. Feulner , Marc J. Muldoon , Xinwen Xiao
Abstract: A gas turbine engine includes a fan section that includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor includes a greater number of stages than the low pressure turbine. A high spool includes a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine stage high pressure compressor and includes a pressure ratio per stage of greater than or equal to 1.20 and less than or equal to 1.33.
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公开(公告)号：US20230027726A1
公开(公告)日：2023-01-26
申请号：US17379291
申请日：2021-07-19
Applicant: Raytheon Technologies Corporation
Inventor： Stephen G. Pixton , Matthew R. Feulner , Marc J. Muldoon , Xinwen Xiao
Abstract: A gas turbine engine includes a fan section that includes a fan with fan blades. The fan section drives air along a bypass flow path in a bypass duct. A gear reduction is in driving engagement with the fan and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool includes a low pressure turbine that drives a low pressure compressor and drives the gear reduction to drive the fan at a speed slower than the low pressure turbine. The low pressure compressor is a five-stage low pressure compressor. The low pressure turbine is four-stage low pressure turbine. A high spool includes a high pressure turbine that drives a high pressure compressor. The high pressure compressor is a nine-stage high pressure compressor. The high pressure turbine is a two-stage high pressure turbine.
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