-
公开(公告)号：US11542872B2
公开(公告)日：2023-01-03
申请号：US17501051
申请日：2021-10-14
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , John P. Virtue
IPC: F02C7/268 , B64D27/10 , B64D27/24 , F02C9/54 , F02K5/00 , F02C6/14 , B64D27/02 , B64D31/06 , B64D33/00 , F02C9/26
Abstract: An aspect includes a hybrid gas turbine engine system of a hybrid electric aircraft. The hybrid gas turbine engine system includes a gas turbine engine having a low speed spool and a high speed spool, a generator operably coupled to the low speed spool, a high spool electric motor operably coupled to the high speed spool, and a controller. The controller is configured to control the hybrid gas turbine engine system in a powered warm-up state to add heat to one or more components of the gas turbine engine by operating the gas turbine engine with a higher engine power setting above idle to drive rotation of the generator, transfer power from the generator to the high spool electric motor, and produce thrust. The gas turbine engine transitions from the powered warm-up state after reaching a target temperature of the one or more components in the powered warm-up state.
-
公开(公告)号：US20220412290A1
公开(公告)日：2022-12-29
申请号：US17355327
申请日：2021-06-23
Applicant: Raytheon Technologies Corporation
Inventor： Lance L. Smith , Neil Terwilliger
Abstract: A hybrid electric gas turbine engine system includes a first compressor and an auxiliary compressor. The first compressor is configured to output first compressed air. The auxiliary compressor is configured to operate in parallel with the first compressor to output second compressed air. A controller is configured to selectively activate the first compressor or the auxiliary compressor based on an operating condition of the hybrid electric gas turbine engine system.
-
公开(公告)号：US20220412255A1
公开(公告)日：2022-12-29
申请号：US17897995
申请日：2022-08-29
Applicant: Raytheon Technologies Corporation
Inventor： Steven M. O'Flarity , Neil Terwilliger
Abstract: A gas turbine engine includes a compressor. A turbine is mechanically connected to the compressor by a shaft. An air-driven auxiliary turbine is in fluid communication with the compressor and is configured to receive pressurized air from the compressor. An auxiliary generator is operably connected to the auxiliary turbine. The auxiliary generator is configured to generate electrical energy in response to an operation of the auxiliary turbine. An energy storage device is in electrical communication with the auxiliary generator.
-
14.发明申请公开(公告)号：US20230136475A1
公开(公告)日：2023-05-04
申请号：US17866841
申请日：2022-07-18
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , Christopher J. Hanlon , Sorin Bengea , Zubair Ahmed Baig
IPC: F01D11/24
Abstract: A method for active bi-directional control of an outer structure of a gas turbine engine comprises sending, by a controller, a first control signal to a power electronics for varying an electric current supplied to a heating element to cause the outer structure to move in a first radial direction, and sending, by the controller, a second control signal to a valve assembly for varying a cooling air flow supplied to the outer structure to cause the outer structure to move in a second radial direction. The first radial direction is opposite the second radial direction.
-
公开(公告)号：US20230042497A1
公开(公告)日：2023-02-09
申请号：US17396077
申请日：2021-08-06
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , Keith J. Kucinskas
Abstract: Examples described herein provide a computer-implemented method that includes providing the hybrid electric engine, the hybrid electric engine having a gas generating core and an electric machine powered by electric energy. The method further includes determining, by a processing device, whether a use of the electric energy will increase time on wing of the hybrid electric engine of the aircraft a threshold amount. The method further includes, responsive to determining that the use of energy will increase time on wing the threshold amount, apportioning the electric energy from a battery system of the aircraft to increase the time on wing.
-
Patent Agency Ranking
公开(公告)号：US11548651B2
公开(公告)日：2023-01-10
申请号：US16936595
申请日：2020-07-23
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger
IPC: B64D27/24 , F01D15/10 , F02C7/36 , F02C9/42 , F02K3/06 , B64D27/02 , B60W10/06 , B60W10/08 , B60K6/48
Abstract: A system of a hybrid aircraft includes a first gas turbine engine including a fan, a high speed spool, and a low spool motor configured to drive rotation of the fan. The system also includes a second gas turbine engine and a controller. The controller is operable to determine an operating mode of the hybrid aircraft, control the low spool motor to drive rotation of the fan of the first gas turbine engine responsive to a thrust command while the second gas turbine engine is driven by commanding fuel combustion based on the operating mode, and accelerate the high speed spool of the first gas turbine engine and command fuel combustion at the first gas turbine engine based on a transition of the operating mode to perform a starting operation of the first gas turbine engine.
-
公开(公告)号：US11415065B2
公开(公告)日：2022-08-16
申请号：US16912110
申请日：2020-06-25
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , Marc J. Muldoon
IPC: F02C7/36 , F02C6/00 , F02C7/32 , F02K5/00 , F02C3/04 , F02C7/20 , F01D15/10 , B64D27/02 , F02C6/14
Abstract: Hybrid electric propulsion systems are described. The hybrid electric propulsion systems include a gas turbine engine including a low speed spool and a high speed spool, the low speed spool including a low pressure compressor and a low pressure turbine, and the high speed spool including a high pressure compressor and a high pressure turbine, a mechanical power transmission configured to at least one of extract power from and supply power to at least one of the low speed spool and the high speed spool, an electric motor configured to augment rotational power of at least one of the low speed spool and the high speed spool, and a controller operable to control a power augmentation of at least one of the low speed spool and the high speed spool during an operational stress state of operation of the gas turbine engine.
-
公开(公告)号：US20210222629A1
公开(公告)日：2021-07-22
申请号：US16936595
申请日：2020-07-23
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger
Abstract: A system of a hybrid aircraft includes a first gas turbine engine including a fan, a high speed spool, and a low spool motor configured to drive rotation of the fan. The system also includes a second gas turbine engine and a controller. The controller is operable to determine an operating mode of the hybrid aircraft, control the low spool motor to drive rotation of the fan of the first gas turbine engine responsive to a thrust command while the second gas turbine engine is driven by commanding fuel combustion based on the operating mode, and accelerate the high speed spool of the first gas turbine engine and command fuel combustion at the first gas turbine engine based on a transition of the operating mode to perform a starting operation of the first gas turbine engine.
-
公开(公告)号：US20210025339A1
公开(公告)日：2021-01-28
申请号：US16936602
申请日：2020-07-23
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , Gary Collopy
Abstract: A system includes a gas turbine engine having a low speed spool, a high speed spool, and a combustor. The system also includes a low spool motor configured to augment rotational power of the low speed spool. The system further includes a controller configured to cause fuel flow. The controller is operable to control the low spool motor to drive rotation of the low speed spool responsive to a thrust command while the controller does not command fuel flow to the combustor.
-
公开(公告)号：US12031480B2
公开(公告)日：2024-07-09
申请号：US17897995
申请日：2022-08-29
Applicant: Raytheon Technologies Corporation
Inventor： Steven M. O'Flarity , Neil Terwilliger
CPC classification number: F02C6/14 , H02K7/116 , H02K7/1823 , H02K11/0094
Abstract: A gas turbine engine includes a compressor. A turbine is mechanically connected to the compressor by a shaft. An air-driven auxiliary turbine is in fluid communication with the compressor and is configured to receive pressurized air from the compressor. An auxiliary generator is operably connected to the auxiliary turbine. The auxiliary generator is configured to generate electrical energy in response to an operation of the auxiliary turbine. An energy storage device is in electrical communication with the auxiliary generator.
-
-
-
-
-
-
-
-
-
Search Results
25
records
(took 0.018 seconds)
