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公开(公告)号：US11834991B2
公开(公告)日：2023-12-05
申请号：US17967335
申请日：2022-10-17
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Russell B. Witlicki
CPC classification number: F02C7/06 , F01D25/18 , F02C7/32 , F05D2220/76 , F05D2260/98
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes an electric machine, a turbine engine component and a lubrication system. The electric machine includes a rotor and a stator. The turbine engine component is discrete from the electric machine. The lubrication system includes a first lubricant circuit, a second lubricant circuit and a lubricant source fluidly coupled in parallel with the first lubricant circuit and the second lubricant circuit. The first lubricant circuit includes a machine volume for the electric machine. The second lubricant circuit includes a component volume for the turbine engine component.
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公开(公告)号：US11821362B2
公开(公告)日：2023-11-21
申请号：US17719458
申请日：2022-04-13
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon
Abstract: An assembly of a gas turbine engine includes a low pressure compressor, a high pressure compressor, an intermediate case between the low pressure compressor and the high pressure compressor, and a cleaning apparatus having an annular arrangement about the intermediate case. A core flow path is defined through the low pressure compressor, the intermediate case, and the high pressure compressor. The annular arrangement includes a scroll portion configured to extract debris from an airstream at an outer diameter wall of the core flow path and return the airstream to the core flow path.
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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：US20230212979A1
公开(公告)日：2023-07-06
申请号：US17967360
申请日：2022-10-17
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Russell B. Witlicki
CPC classification number: F02C6/20 , F02C7/268 , F02C7/06 , F01D25/04 , F05D2220/323 , F05D2220/70 , F05D2220/76 , F05D2260/85 , F05D2240/54 , F05D2260/96
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a stationary structure, a rotating structure and an electric machine. The rotating structure is rotatably mounted to the stationary structure by a first bearing and a second bearing. The electric machine is between the first bearing and the second bearing. The electric machine includes a rotor and a stator circumscribing the rotor. The rotor is connected to the rotating structure. The stator is connected to the stationary structure.
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公开(公告)号：US20230121939A1
公开(公告)日：2023-04-20
申请号：US17504869
申请日：2021-10-19
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon
Abstract: A gas turbine engine includes a fan section including 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. The gear reduction is a planetary gear system. 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. A first low spool support bearing is located axially between the low pressure compressor and the gear reduction. A second low spool support bearing is located axially between the low pressure compressor and the high pressure compressor.
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Patent Agency Ranking
公开(公告)号：US20230120797A1
公开(公告)日：2023-04-20
申请号：US17967335
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 an electric machine, a turbine engine component and a lubrication system. The electric machine includes a rotor and a stator. The turbine engine component is discrete from the electric machine. The lubrication system includes a first lubricant circuit, a second lubricant circuit and a lubricant source fluidly coupled in parallel with the first lubricant circuit and the second lubricant circuit. The first lubricant circuit includes a machine volume for the electric machine. The second lubricant circuit includes a component volume for the turbine engine component.
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公开(公告)号：US20230090152A1
公开(公告)日：2023-03-23
申请号：US17483210
申请日：2021-09-23
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Michael E. McCune , Keith B. Allyn
IPC: F01D9/04
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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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：US20220403776A1
公开(公告)日：2022-12-22
申请号：US17351876
申请日：2021-06-18
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Michael D. Greenberg , Nancy Poisson , Martin Richard Amari
Abstract: An engine system of an aircraft includes a gas turbine engine comprising at least one spool and at least one electric machine operably coupled with the at least one spool. A controller is configured to detect if the at least one spool of the gas turbine engine is in or is approaching an overspeed condition and apply a load to the at least one spool via the at least one electric machine.
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公开(公告)号：US20220396363A1
公开(公告)日：2022-12-15
申请号：US17345619
申请日：2021-06-11
Applicant: Raytheon Technologies Corporation
Inventor： Arnab Roy , Marc J. Muldoon , Neil Terwilliger , Nancy Poisson
Abstract: Examples described herein provide a computer-implemented method for managing battery usage for a hybrid electric engine of an aircraft. The method includes receiving a flight plan comprising flight plan data for a flight of an aircraft. The method further includes receiving battery data about a battery system of the aircraft. The method further includes determining waypoints for when to apply electric power from the battery system based at least in part on the flight plan data and the battery data. The method further includes controlling, based at least in part on the waypoints, an electric motor while the flight plan is executed. The method further includes updating, while the flight plan is executed, the waypoints based at least in part on data received during the flight.
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