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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：US11808154B2
公开(公告)日：2023-11-07
申请号：US17952693
申请日：2022-09-26
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： San Quach , Bryan P. Dube , Erik R. Granstand , Michael G. McCaffrey , Stephen G. Pixton
CPC classification number: F01D11/005 , F01D5/147 , F01D9/042 , F05D2240/12 , F05D2300/6033
Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure having an axial portion and a radial portion and an outer portion arranged between the support structure. The outer portion defines a gap between the outer portion and the axial portion of the support structure. A flange is positioned relative to the gap.
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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：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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Patent Agency Ranking
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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公开(公告)号：US20230024792A1
公开(公告)日：2023-01-26
申请号：US17379233
申请日：2021-07-19
Applicant: Raytheon Technologies Corporation
Inventor： Stephen G. Pixton , Karl L. Hasel
IPC: F02C7/36
Abstract: A gas turbine engine includes a fan drive turbine driving a low pressure compressor, and driving a gear reduction to in turn drive a fan rotor at a speed slower than the fan drive turbine. The turbine section further includes a high pressure turbine driving the high pressure compressor. The fan drive turbine and low pressure compressor are connected by a shaft and the fan drive turbine, the shaft and the low pressure compressor define a low pressure spool. The gas turbine engine is rated to provide an amount of thrust at maximum takeoff, and a low spool thrust ratio defined as a ratio of a torque on the low pressure spool at maximum takeoff in ft-lbs and the maximum takeoff thrust being defined in lbf, with the low spool torque ratio being greater than or equal to 0.70 ft-lb/lbf, and less than or equal to 1.2 ft-lb/lbf.
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公开(公告)号：US11814968B2
公开(公告)日：2023-11-14
申请号：US17379202
申请日：2021-07-19
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Stephen G. Pixton , Gary Collopy , Ozhan Turgut
CPC classification number: F01D15/12 , F02C3/00 , F02C7/32 , F05D2220/323
Abstract: A gas turbine engine according to an example of the present disclosure may include, among other things, a fan section including a fan having a plurality of fan blades and including an outer housing surrounding the fan blades to establish a bypass duct, a geared architecture, a first spool including a first shaft that interconnects a first compressor and a fan drive turbine, the fan drive turbine driving the fan through the geared architecture. The gas turbine engine is rated to provide an amount of thrust at ground idle, and the gas turbine engine is rated to provide an amount of thrust at maximum takeoff. A thrust ratio is defined as a ratio of the amount of thrust at ground idle divided by the amount of thrust at maximum takeoff. The thrust ratio can be less than or equal to 0.050.
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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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