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公开(公告)号：US20240018901A1
公开(公告)日：2024-01-18
申请号：US18364422
申请日：2023-08-02
Applicant: RTX CORPORATION
Inventor： Daniel Bernard Kupratis , Paul R. Hanrahan , Arthur M. Salve, JR.
Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.
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公开(公告)号：US20230407817A1
公开(公告)日：2023-12-21
申请号：US18461709
申请日：2023-09-06
Applicant: RTX CORPORATION
Inventor： Daniel Bernard Kupratis , Paul R. Hanrahan
Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor including a row of blades extending in a radial direction outwardly from a hub. The row of blades deliver flow to a bypass flow path, an intermediate flow path, and a core flow path. A first case surrounds the row of blades to establish the bypass flow path. A first flow splitter divides flow between the bypass flow path and a second duct. An aftmost row of guide vanes extends in the radial direction across the bypass flow path. A second flow splitter radially inboard of the first flow splitter divides flow from the second duct between the intermediate flow path and the core flow path. A bypass port interconnects the intermediate and bypass flow paths.
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公开(公告)号：US12258135B2
公开(公告)日：2025-03-25
申请号：US18103935
申请日：2023-01-31
Applicant: RTX CORPORATION
IPC: F02C6/14 , B64D27/10 , B64D27/24 , F01D15/10 , F02C7/36 , H02K7/18 , B64D27/02 , F02C3/107 , F02C6/02
Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.
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公开(公告)号：US11840958B2
公开(公告)日：2023-12-12
申请号：US17393508
申请日：2021-08-04
Applicant: RTX Corporation
Inventor： Daniel Bernard Kupratis , Paul R. Hanrahan , Christopher J. Hanlon
Abstract: A gas turbine engine includes a fan positioned at an engine central longitudinal axis, and a fan drive turbine located at the engine central longitudinal axis and configured to drive rotation of the fan. A gas generator is non-coaxial with the fan drive turbine and operably connected to the fan drive turbine such that exhaust from the gas generator drives rotation of the fan drive turbine. An auxiliary power core is located at the engine central longitudinal axis, and one or more bleed passages connect the gas generator and the auxiliary power core. The one or more bleed passages are configured to selectably combine a bleed airflow from the gas generator and an auxiliary core airflow at the auxiliary power core to direct the combined airflow to the fan drive turbine to increase output of the fan drive turbine.
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公开(公告)号：US20250163823A1
公开(公告)日：2025-05-22
申请号：US19033023
申请日：2025-01-21
Applicant: RTX Corporation
Inventor： Neil Terwilliger , Daniel Bernard Kupratis , Michael Romero
Abstract: A method of operating an aircraft hybrid gas turbofan during an idle mode of operation includes reducing a fuel flow to a primary gas turbine engine and boosting a high spool of the primary gas turbine engine using a secondary gas turbine engine via a first power linkage connecting the primary and secondary gas turbine engines, such that a net fuel reduction is achieved. The net fuel reduction accounts for fuel flow to the primary gas turbine engine and fuel flow to the secondary gas turbine engine.
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Patent Agency Ranking
6.发明申请公开(公告)号：US20240401500A1
公开(公告)日：2024-12-05
申请号：US18420862
申请日：2024-01-24
Applicant: RTX CORPORATION
Inventor： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, propulsor means, first compression means, second compression means, reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input, first expansion means, and second expansion means. The reduction means includes an epicyclic gear system with a gear reduction. The gear system is straddle-mounted by first and second bearings on opposite sides of the gear reduction relative to an engine longitudinal axis.
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公开(公告)号：US12123309B2
公开(公告)日：2024-10-22
申请号：US18485980
申请日：2023-10-12
Applicant: RTX Corporation
Inventor： Dmitriy B. Sidelkovskiy , Pitchaiah Vijay Chakka , Michael Winter , Daniel Bernard Kupratis , Nathan L. Messersmith
IPC: F01D15/10 , B64D27/02 , B64D27/10 , B64D27/24 , B64D41/00 , F01D15/12 , F02C6/06 , F02K3/065 , H02K7/116 , H02K7/18 , H02K7/20 , H02K11/00
CPC classification number: F01D15/10 , B64D27/10 , B64D27/24 , B64D41/00 , F01D15/12 , F02C6/06 , F02K3/065 , H02K7/116 , H02K7/1823 , H02K7/20 , H02K11/0094 , B64D27/026 , F05D2220/50 , F05D2220/76
Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.
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公开(公告)号：US11970984B2
公开(公告)日：2024-04-30
申请号：US18107126
申请日：2023-02-08
Applicant: RTX CORPORATION
Inventor： Frederick M. Schwarz , Daniel Bernard Kupratis
CPC classification number: F02C7/36 , F01D1/26 , F01D15/12 , F02C3/107 , F02K3/06 , F05D2260/40311 , F05D2270/051
Abstract: A gas turbine engine includes a propulsor section including a propulsor, a compressor section including a first compressor and a second compressor, a geared architecture, a turbine section including a first turbine and a drive turbine, and a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section.
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公开(公告)号：US20240035392A1
公开(公告)日：2024-02-01
申请号：US18485980
申请日：2023-10-12
Applicant: RTX Corporation
Inventor： Dmitriy B. Sidelkovskiy , Pitchaiah Vijay Chakka , Michael Winter , Daniel Bernard Kupratis , Nathan L. Messersmith
IPC: F01D15/10 , B64D27/10 , B64D27/24 , B64D41/00 , F01D15/12 , F02C6/06 , F02K3/065 , H02K7/116 , H02K7/18 , H02K7/20 , H02K11/00
CPC classification number: F01D15/10 , B64D27/10 , B64D27/24 , B64D41/00 , F01D15/12 , F02C6/06 , F02K3/065 , H02K7/116 , H02K7/1823 , H02K7/20 , H02K11/0094 , B64D2027/026
Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.
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公开(公告)号：US12173644B2
公开(公告)日：2024-12-24
申请号：US18364422
申请日：2023-08-02
Applicant: RTX CORPORATION
Inventor： Daniel Bernard Kupratis , Paul R. Hanrahan , Arthur M. Salve, Jr.
Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.
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