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公开(公告)号：US20250035046A1
公开(公告)日：2025-01-30
申请号：US18361075
申请日：2023-07-28
Inventor： Jeffrey Lawrence , Peter Schenk , Jacob Ward Harral , Brian Joseph Huber
Abstract: An example system includes a first gas-turbine engine configured to propel an aircraft, the first gas-turbine engine comprising: a first air-turbine starter, the first air-turbine starter configured to rotate a spool of the first gas-turbine engine; and a first electric starter, the first electric starter configured to rotate the spool of the first gas-turbine engine; and one or more controllers collectively configured to: cause, during a time period, the first-air turbine starter and the first electric starter to start the first gas-turbine engine while the aircraft is on the ground; measure, during the time period, values of one or more parameters of the first gas-turbine engine; and determine, based on the values of the one or more parameters, whether the first electric starter is available for use in performing mid-air restart of the first gas-turbine engine.
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公开(公告)号：US12209502B1
公开(公告)日：2025-01-28
申请号：US18758996
申请日：2024-06-28
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Jonathan M. Rivers
Abstract: A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.
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公开(公告)号：US12203686B2
公开(公告)日：2025-01-21
申请号：US18543612
申请日：2023-12-18
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Eugene Charles Jansen
Abstract: A cooling apparatus includes a first fluid flowpath and a second fluid flowpath. The first fluid flowpath includes a subcooler having a first side in fluid communication with the first fluid flowpath; a flow control valve; a primary evaporator assembly including at least one evaporator configured to be disposed in thermal communication with a heat load; and a pressure regulator operable to control a saturation pressure within the at least one evaporator. The second fluid flowpath is in fluid communication with a second side of the subcooler.
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公开(公告)号：US12180910B1
公开(公告)日：2024-12-31
申请号：US18371810
申请日：2023-09-22
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Curtlan C. Betchley , Kenneth M. Pesyna , Bryan H. Lerg , Steven T. Berenyi , Andrew M. Simonich , Victor L. Oechsle
IPC: F02K1/82
Abstract: An infrared suppressor adapted for use with a gas turbine engine includes a first ring arranged circumferentially around a central axis, a second ring arranged circumferentially around the central axis, and a strut that extends radially between and interconnects the first ring and the second ring. A portion of the second ring extends radially toward the first ring such that the portion of the second ring cooperates with the first ring to block line-of-sight into the infrared suppressor.
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公开(公告)号：US20240352872A1
公开(公告)日：2024-10-24
申请号：US18304037
申请日：2023-04-20
Inventor： Govindaraj Kalyanasamy , Peter Schenk
Abstract: An example system includes one or more heaters configured and positioned to add thermal energy to one or more portions of a gas turbine engine after the gas turbine engine was in operation, wherein the thermal energy minimizes or prevents undesired contact or seizing of a rotor of the gas turbine engine with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The system further includes a controller configured to control operation of the one or more heaters.
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Patent Agency Ranking
公开(公告)号：US12110820B2
公开(公告)日：2024-10-08
申请号：US18241447
申请日：2023-09-01
Inventor： Steven Mazur , Rex M. Little
Abstract: A gas turbine engine includes a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the compressor and a fan, shaft, or propeller.
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公开(公告)号：US20240322646A1
公开(公告)日：2024-09-26
申请号：US18417938
申请日：2024-01-19
Inventor： Daniel E. Molnar, JR. , Robert W. Heeter , Brian S. Maners
CPC classification number: H02K7/1823 , F02C7/36 , F05D2220/76
Abstract: A turbine engine includes a core section comprising at least one compressor and at least one turbine that both rotate about a longitudinal axis of the turbine engine; a core vane assembly coupled to the core section, wherein the core vane assembly comprises a plurality of core vanes configured to modify core fluid flow; a fan connected to the core section and configured to be rotated by the at least one turbine, rotation of the fan providing thrust to a vehicle that includes the turbine engine; and an electrical generator integrated into the core vane assembly and positioned in the core section aft of the fan and fore of the at least one compressor, wherein the electrical generator comprises: a rotor mechanically rotated via the fan or a shaft that is rotationally coupled to the fan, wherein the rotor rotates about the longitudinal axis; and a stator.
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公开(公告)号：US12078103B1
公开(公告)日：2024-09-03
申请号：US18230442
申请日：2023-08-04
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Rex M. Little
Abstract: A thermal management system for a gas turbine engine includes an inlet, a compressor, a mixing unit, and a fuel source. The compressor includes a low pressure stage and a high pressure stage. The mixing unit includes a first valve port fluidically connected to a low pressure bleed line of the compressor and a high pressure bleed line of the compressor and having an adjustable inlet gate on each of these lines and an outlet fluidically connected to the inlet of the engine to prevent ice accretion in the inlet or de-ice the inlet. The fuel source is configured to provide fuel to the mixing unit to actuate the adjustable inlet gates to regulate the amounts of low pressure bleed air and high pressure bleed air directed to the outlet.
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公开(公告)号：US12071861B1
公开(公告)日：2024-08-27
申请号：US18371857
申请日：2023-09-22
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Michael D. Wood , Matthew T. Kush , Timothy P. Fuesting , Douglas D. Dierksmeier
CPC classification number: F01D5/048 , F01D5/046 , F01D5/187 , F01D5/282 , F01D5/284 , F05D2230/237 , F05D2240/20 , F05D2300/6033
Abstract: A multi-piece radial turbine rotor includes a hub, turbine blades, and a flowpath ring that couples the turbine blades to the hub. Joints between the components of the rotor are adapted for inspection during manufacture to identify potential defects in the joints.
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公开(公告)号：US12065258B2
公开(公告)日：2024-08-20
申请号：US18101567
申请日：2023-01-25
Inventor： Robert W. Heeter , Daniel E. Molnar, Jr. , Kathryn A. Sontag , Michael G. Meyer
IPC: B64D33/02
CPC classification number: B64D33/02 , B64D2033/0226 , B64D2033/0286
Abstract: An aircraft includes a duct system configured to receive a flow of air therethrough and a gas turbine engine. The duct system includes a main duct and inlet ducts arranged fluidly upstream of the main duct so as to conduct the flow of air from the inlet ducts into the main duct. The gas turbine engine in downstream fluid communication with the main duct.
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