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公开(公告)号：US20220112843A1
公开(公告)日：2022-04-14
申请号：US17484897
申请日：2021-09-24
Applicant: ROLLS-ROYCE plc
Inventor： Natalie C. WONG , Thomas S BINNINGTON , David A. JONES , Daniel BLACKER
Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D), and the heat exchanger module comprises a plurality of heat exchanger elements.
The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, with the heat exchanger module having an axial length along a central axis between an upstream-most face of the heat exchanger elements and a downstream-most face of the heat exchanger elements. The axial length is in the range of 0.1*D to 5.0*D.-
公开(公告)号：US20220112842A1
公开(公告)日：2022-04-14
申请号：US17484622
申请日：2021-09-24
Applicant: ROLLS-ROYCE plc
Inventor： Natalie C. WONG , Thomas S. BINNINGTON , David A. JONES , Daniel BLACKER
Abstract: An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid cooling flow prior to an entry of the entire fluid cooling flow into the fan module.
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公开(公告)号：US20220112841A1
公开(公告)日：2022-04-14
申请号：US17484873
申请日：2021-09-24
Applicant: ROLLS-ROYCE plc
Inventor： Natalie C. WONG , Thomas S. BINNINGTON , David A. JONES , Daniel BLACKER
IPC: F02C7/14
Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes a plurality of fan blades defining a fan diameter, and the heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The heat exchanger module includes a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. At full-power condition, the engine produces a maximum thrust T (N), the heat exchanger module transfers a maximum heat rejection H (W) from the first fluid to the airflow, and a Heat Exchanger Performance parameter PEX (W/N) defined as PEX=H/T is 0.4 to 6.0.
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公开(公告)号：US11300293B2
公开(公告)日：2022-04-12
申请号：US16903456
申请日：2020-06-17
Applicant: ROLLS-ROYCE plc
Inventor： Luca Tentorio , Juan Carlos Roman Casado , Giacomo Di Chiaro , Jonathan Knapton , Filippo Zambon , Radu Irimia
Abstract: A fuel injector comprising a first air swirler passage and a second air swirler passage extending axially through the fuel injector and arranged to direct air through the fuel injector, a splitter arranged between the first air swirler passage and the second air swirler passage and comprising a first splitter surface having a first divergent portion which is divergent in the downstream direction, a second splitter surface located radially inward of the first splitter surface and having a second divergent portion which is divergent in the downstream direction, a third splitter surface located radially inward of the first and second splitter surface, and a first connecting surface extending between the second and third splitter surfaces, wherein a first cavity is formed between the first and second splitter surfaces, and the second divergent portion comprises at least one opening in fluid communication with the first cavity.
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公开(公告)号：US11292605B2
公开(公告)日：2022-04-05
申请号：US16396923
申请日：2019-04-29
Applicant: ROLLS-ROYCE plc
Inventor： Joseph B. Cooper
Abstract: A system for mounting a gas turbine engine to a pylon on a wing of an aircraft. A temporary forward link, being length-adjustable, and at least one temporary rearward link, being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine to the pylon. The temporary forward link and the temporary rearward link are each adapted to resist tension and compression, to maintain a positional relationship between the gas turbine engine and the pylon in the absence of adjustment of the lengths of the temporary forward link and the temporary rearward link. Adjustment of the length of the temporary links brings engine mounts into alignment with pylon mounts for service attachment of the gas turbine engine to the pylon.
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Patent Agency Ranking
公开(公告)号：US20220099035A1
公开(公告)日：2022-03-31
申请号：US17466086
申请日：2021-09-03
Applicant: ROLLS-ROYCE PLC
Inventor： Craig W BEMMENT , Pascal DUNNING
Abstract: A gas turbine engine for an aircraft includes an engine core including a first, lower pressure, turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor; and a second, higher pressure, turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, and a fan located upstream of the engine core and including a plurality of fan blades extending from a hub. A turbine to fan tip temperature change ratio of a low pressure turbine temperature change to a fan tip temperature rise is in the range from 1.46 to 2.0.
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公开(公告)号：US11286798B2
公开(公告)日：2022-03-29
申请号：US16545791
申请日：2019-08-20
Inventor： Michael J. Whittle , Daniel K. Vetters , Ted J. Freeman , Eric Koenig , Jeff Crutchfield , Jeffrey A. Walston , David J. Thomas
Abstract: An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform. Force loads caused by gases interacting with the airfoil are configured to be transmitted from the airfoil assembly to a case arranged around the airfoil assembly.
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公开(公告)号：US11286792B2
公开(公告)日：2022-03-29
申请号：US16526274
申请日：2019-07-30
Applicant: Rolls-Royce plc
Inventor： Anthony Razzell , Michael J. Whittle , Ian M. Edmonds
Abstract: An airfoil for a gas turbine engine is made from ceramic matrix composite materials. The airfoil has an inner surface that defines a cooling cavity in the body and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a suction side of the body. The airfoil is formed with a hollow tube that extends through the body to define a cooling passage that extends from the cooling cavity through the airfoil to provide fluid communication between the cooling cavity and a gas path environment surrounding the airfoil.
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公开(公告)号：US11286784B2
公开(公告)日：2022-03-29
申请号：US17149128
申请日：2021-01-14
Applicant: ROLLS-ROYCE PLC
Inventor： Soumyik Bhaumik , Rohit Chouhan
IPC: F01D5/14
Abstract: An aerofoil assembly includes a platform and one or more aerofoils extending radially outward from the platform. The platform has a first edge, a second edge, and a platform surface disposed between the first edge and the second edge. The one or more aerofoils are disposed between the first edge and the second edge. Each of the one or more aerofoils has a leading edge proximal to the first edge and a trailing edge distal to the first edge. The platform defines one or more recesses disposed between the leading edge of each of the one or more aerofoils and the first edge.
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公开(公告)号：US20220090541A1
公开(公告)日：2022-03-24
申请号：US17544660
申请日：2021-12-07
Applicant: ROLLS-ROYCE plc
Inventor： Mark SPRUCE
Abstract: An engine core including a turbine, compressor, and a core shaft connecting the turbine and compressor; a fan located upstream of the engine core including a plurality of fan blades; and a gearbox. The gearbox is arranged to receive an input from the core shaft and to output drive to the fan to drive the fan at a lower rotational speed than the core shaft. The gearbox is an epicyclic gearbox and includes a sun gear, a plurality of planet gears, ring gear, and planet carrier to the mounted planet gears. The planet carrier has an effective linear torsional stiffness and the gearbox has a gear mesh stiffness between the planet gears and the ring gear. A carrier to ring mesh ratio of: the effective linear torsional stiffness of the planet carrier gear mesh stiffness between the planet gears and the ring gear is greater than or equal to 0.2.
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