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公开(公告)号：US20230304439A1
公开(公告)日：2023-09-28
申请号：US17860756
申请日：2022-07-08
Applicant: Raytheon Technologies Corporation
Inventor： Brian M. Holley , Joseph B. Staubach , Marc J. Muldoon , Charles E. Lents
Abstract: Aircraft propulsion systems and aircraft are described. The aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and an expander, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the expander, prior to being injected into the burner for combustion.
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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：US20230250754A1
公开(公告)日：2023-08-10
申请号：US17666754
申请日：2022-02-08
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon
CPC classification number: F02C3/22 , F02C7/224 , F02C7/32 , F05D2220/323 , F05D2240/36 , F05D2260/20
Abstract: Aircraft propulsion systems and methods of operation thereof, include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and a turbo expander assembly. The main engine core includes a compressor section, a combustor section having a burner, and a turbine section. Fuel is supplied from the at least one fuel tank through a fuel flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and selectively through the turbo expander assembly, prior to being injected into the burner for combustion. The turbo expander assembly is operably coupled to at least two load sources through a selective coupler and configured to selectively drive operation of the at least two load sources.
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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：US20230220781A1
公开(公告)日：2023-07-13
申请号：US18187796
申请日：2023-03-22
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Michael E. McCune , Keith B. Allyn
CPC classification number: F01D9/041 , F01D25/162 , F01D25/28 , F05D2220/32
Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction. An inner core engine has an inner core engine housing surrounding a compressor section, including a low pressure compressor. A rigid connection between a fan case and the inner core engine includes A-frames rigidly connected at a connection point to the fan case. Fan exit guide vanes rigidly connect to the fan case, and to the inner core engine. A fan intermediate case is positioned forward of a first rotor stage in the low pressure compressor. A rigid structure is connected to the inner core engine and to the fan exit guide vanes. The rigid structure defines a structure moment stiffness. The fan intermediate case defines an intermediate case moment stiffness. A ratio of the structure moment stiffness to the intermediate case moment stiffness is between 5 and 15.
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Patent Agency Ranking
公开(公告)号：US20230138442A1
公开(公告)日：2023-05-04
申请号：US17976326
申请日：2022-10-28
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon
Abstract: A hybrid-electric aircraft system is provided and includes first and second hybrid-electric engines, first and second ducting systems fluidly communicative with each other and with the first and second hybrid-electric engines, respectively, and a control system. The control system is operably coupled to each of the first and second hybrid-electric engines and to each of the first and second ducting systems. The control system is configured to run the first hybrid-electric engine normally, to run the second hybrid-electric engine in a lower power mode and to control each of the first and second ducting systems to direct bleed air from the first hybrid-electric engine to the second hybrid-electric engine.
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公开(公告)号：US20230117331A1
公开(公告)日：2023-04-20
申请号：US17967345
申请日：2022-10-17
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Russell B. Witlicki
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating structure, a stationary structure and an electric machine. The rotating structure is configured to rotate about a rotational axis. The stationary structure circumscribes the rotating structure. The electric machine includes a rotor and a stator. The rotor circumscribes the rotating structure and is coupled to the rotating structure through a spline connection. The stator is connected to the stationary structure.
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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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公开(公告)号：US20220381185A1
公开(公告)日：2022-12-01
申请号：US17329501
申请日：2021-05-25
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Carroll V. Sidwell
Abstract: Aircraft hydrogen fuel systems and methods and systems of starting such systems are described. The aircraft hydrogen fuel systems include a hydrogen burning main engine, a main tank configured to contain liquid hydrogen to be supplied to the main engine during a normal operation, and a starter tank configured to contain gaseous hydrogen to be used during a startup operation of the main engine. Methods and processes for starting and/or restarting such systems are described.
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