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公开(公告)号：US20220010731A1
公开(公告)日：2022-01-13
申请号：US17308715
申请日：2021-05-05
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Anthony R. Bifulco , Duncan R.C. Lee
Abstract: A system for dampening noise generated by a gas turbine engine is disclosed. In various embodiments, the system includes a fan exit guide vane having a leading edge, a trailing edge and a pocket that extends in a chordwise direction between the leading edge and the trailing edge; and an acoustic panel configured to be received within the pocket, the acoustic panel including a back sheet, a face sheet and a core disposed between the back sheet and the face sheet, the core having a first cavity extending between a first wall and a second wall and a second cavity disposed within the first cavity.
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公开(公告)号：US20210254500A1
公开(公告)日：2021-08-19
申请号：US17155876
申请日：2021-01-22
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Anthony R. Bifulco
Abstract: A fluid wash system for a gas turbine engine is disclosed, the gas turbine engine defining an axial direction and comprising a borescope port that provides access to a component within a core flow path of the gas turbine engine. In various embodiments, the fluid wash system includes a wash line fluidly connected to a pump configured to provide a pressurized flow of wash liquid; a spray nozzle connected to the wash line and configured for extending into the borescope port to provide the pressurized flow of wash liquid to the component within the core flow path; and an attachment mechanism configured to releasable mount the spray nozzle to the borescope port, the attachment mechanism including an alignment mechanism configured to orient the spray nozzle and direct the pressurized flow of wash liquid in a predetermined direction toward the component.
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公开(公告)号：US20240295178A1
公开(公告)日：2024-09-05
申请号：US18176542
申请日：2023-03-01
Applicant: Raytheon Technologies Corporation
Inventor： Anthony R. Bifulco
IPC: F01D25/12
CPC classification number: F01D25/12 , F05D2220/32 , F05D2260/232
Abstract: A compressor frame of a gas turbine engine includes a radially outer ring, and a radially inner ring located radially inboard of the radially outer ring. The radially outer ring and the radially inner ring at least partially define a core flowpath of a gas turbine engine therebetween. A plurality of struts extend between the radially outer ring and the radially inner ring. At least one strut of the plurality of struts includes one or more cooling airflow nozzles configured to inject a cooling airflow into the core flowpath to cool a compressor rotor fluidly downstream of the plurality of struts.
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14.发明公开公开(公告)号：US20230151741A1
公开(公告)日：2023-05-18
申请号：US17701010
申请日：2022-03-22
Applicant: Raytheon Technologies Corporation
Inventor： Anthony R. Bifulco , David A. Topol
CPC classification number: F01D25/24 , F01D25/28 , F01D9/041 , F05D2240/14 , F05D2250/11 , F05D2260/30 , F05D2260/606 , F05D2260/96
Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection is between the fan case and the core engine includes three triangular-frame connecting members rigidly connected to the fan case at a fan case connection point, and to the core engine at a core engine connection point. The triangular-frame connecting members each are defined by two rigid legs which extend between the fan case and to the core engine, along directions each have a component extending radially inwardly and a component in opposed circumferential directions to each other. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.
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公开(公告)号：US20230127925A1
公开(公告)日：2023-04-27
申请号：US18088196
申请日：2022-12-23
Applicant: Raytheon Technologies Corporation
Inventor： Anthony R. Bifulco , David A. Topol
Abstract: A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A fan case surrounds the fan rotor. A core engine has a compressor section and includes a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of aft connecting members rigidly connected to the fan case, and to the core engine. A plurality of fan exit guide vanes are rigidly connected to the fan case, with the fan exit guide vanes including structural fan exit guide vanes which are rigidly connected to the core engine, and non-structural fan exit guide vanes, and the non-structural fan exit guide vanes being provided with an acoustic feature to reduce noise.
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Patent Agency Ranking
公开(公告)号：US11566564B2
公开(公告)日：2023-01-31
申请号：US17308715
申请日：2021-05-05
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Anthony R. Bifulco , Duncan R. C. Lee
Abstract: A system for dampening noise generated by a gas turbine engine is disclosed. In various embodiments, the system includes a fan exit guide vane having a leading edge, a trailing edge and a pocket that extends in a chordwise direction between the leading edge and the trailing edge; and an acoustic panel configured to be received within the pocket, the acoustic panel including a back sheet, a face sheet and a core disposed between the back sheet and the face sheet, the core having a first cavity extending between a first wall and a second wall and a second cavity disposed within the first cavity.
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公开(公告)号：US20210317785A1
公开(公告)日：2021-10-14
申请号：US16844683
申请日：2020-04-09
Applicant: Raytheon Technologies Corporation
Inventor： Enzo DiBenedetto , Anthony R. Bifulco , William K. Ackermann , Paul E. Coderre , John H. Mosley , Stephen K. Kramer
Abstract: A cooling system includes an inlet, a passageway, and a feed passage. The inlet is defined by a strut of a diffuser case that extends between a first case portion and a second case portion. The inlet extends from a leading surface towards a trailing surface along a first axis. The passageway is defined by the strut and extends from the inlet towards the second case portion along a second axis that is disposed transverse to the first axis. The feed passage is defined between a body of a tangential onboard injection system that extends between and is connected to an inner vane platform of a guide vane and the second case portion. The feed passage extends along an axis that is disposed parallel to the first axis.
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公开(公告)号：US20210277829A1
公开(公告)日：2021-09-09
申请号：US16863218
申请日：2020-04-30
Applicant: Raytheon Technologies Corporation
Inventor： Daniel K. Van Ness , Anthony R. Bifulco , David A. Topol , David A. Knaul , Michael Raymond LaFavor
Abstract: Disclosed is an acoustic liner for a gas turbine engine, having: a face sheet; a first plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the first plurality of resonator chamber cavities defining a first aggregated volume that is configured to target noise attenuation at a first frequency, the first plurality of resonator chamber cavities include first and second resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other; and a second plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the second plurality of resonator chamber cavities define a second aggregated volume that differs from the first aggregated volume and is configured to target noise attenuation at a second frequency, the second plurality of resonator chamber cavities include third and fourth resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other.
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公开(公告)号：US20240280050A1
公开(公告)日：2024-08-22
申请号：US18171092
申请日：2023-02-17
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , William K. Ackermann , Anthony R. Bifulco
CPC classification number: F02C6/08 , F01D9/02 , F05D2220/323 , F05D2240/126 , F05D2260/60
Abstract: A gas turbine engine includes a compressor section having a downstream most location and more upstream locations. A compressor housing surrounds the compressor rotors. A combustor is downstream of the compressor and a turbine section is downstream of the combustor. At least one bleed inlet passage bleeds air compressed from the compressor section, and delivers the air for use on an associated aircraft. A baffle plate is intermediate the at least one bleed inlet passage and a bleed exit port from the gas turbine engine. The baffle plate has a plurality of holes for allowing the air to flow from the bleed inlet passage to the bleed exit port, with an area of the holes increasing from a location adjacent the at least one bleed inlet passage and in a circumferential direction away from the at least one bleed inlet passage. An aircraft air supply system and an aircraft are also disclosed.
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公开(公告)号：US11708772B2
公开(公告)日：2023-07-25
申请号：US17701010
申请日：2022-03-22
Applicant: Raytheon Technologies Corporation
Inventor： Anthony R. Bifulco , David A. Topol
CPC classification number: F01D25/24 , F01D9/041 , F01D25/28 , F05D2240/14 , F05D2250/11 , F05D2260/30 , F05D2260/606 , F05D2260/96
Abstract: A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection is between the fan case and the core engine includes three triangular-frame connecting members rigidly connected to the fan case at a fan case connection point, and to the core engine at a core engine connection point. The triangular-frame connecting members each are defined by two rigid legs which extend between the fan case and to the core engine, along directions each have a component extending radially inwardly and a component in opposed circumferential directions to each other. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.
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