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    Heating Methods to Facilitate Engine In-Flight Restarts
    3.
    发明申请
    Heating Methods to Facilitate Engine In-Flight Restarts 有权

    公开(公告)号：US20250043737A1

    公开(公告)日：2025-02-06

    申请号：US18362953

    申请日：2023-07-31

    Applicant: Textron Innovations Inc.

    Inventor： Thomas Dewey Parsons ,  Marc Ouellet ,  Daniel Carrier

    IPC: F02C9/42 ,  F02C7/06 ,  F02C7/268

    Abstract: Embodiments are directed to operating a multi-engine aircraft during a cruise flight condition. A first engine is put off-line during flight while allowing a second engine to continue operating. The second engine provides sufficient power to maintain the multi-engine aircraft in the cruise flight condition. An outside air temperature, a first engine temperature, and/or an engine oil temperature is monitored and, when the temperature is below a predetermined threshold, the engine oil for the off-line first engine is warmed. The off-line engine oil may be warmed by continuously or periodically cranking the first engine without restarting the first engine. Alternatively, the engine oil may be warmed using a heat exchanger, such as an air-to-oil or oil-to-oil heat exchanger, or by using electronic heaters on an oil tank.

    Pulse modulation technique for gas turbine engines
    4.
    发明授权
    Pulse modulation technique for gas turbine engines 有权

    公开(公告)号：US12215636B2

    公开(公告)日：2025-02-04

    申请号：US17942529

    申请日：2022-09-12

    Applicant: Textron Innovations Inc.

    Inventor： Joshua Andrew Emrich ,  Thomas Dewey Parsons

    IPC: F02C9/32 ,  B64D31/00 ,  B64D45/00

    Abstract: Various implementations described herein are related to an aircraft having a multi-engine configuration with multiple engines. The aircraft may have a flight control system coupled to the multiple engines with a multi-engine interface. The flight control system may be configured to reduce fuel consumption of at least one engine of the multiple engines during reduced-engine operation by pulse modulating fuel delivery to the at least one engine of the multiple engines.

    Optimizing usage of supplemental engine power
    6.
    发明授权
    Optimizing usage of supplemental engine power 有权

    公开(公告)号：US12054245B2

    公开(公告)日：2024-08-06

    申请号：US17867231

    申请日：2022-07-18

    Applicant: Textron Innovations Inc.

    Inventor： Thomas Dewey Parsons ,  Charles Eric Covington ,  Kent E. Donaldson ,  Andrew Thomas Carter

    IPC: B64C27/12 ,  B64D31/06

    CPC classification number: B64C27/12 ,  B64D31/06

    Abstract: In an embodiment, an aircraft includes a drive system, a main engine coupled to the drive system to provide first power, and a supplemental engine coupled to the drive system to provide second power additive to the first power. The aircraft also includes a control system to control the main engine and the supplemental engine to optimize usage of the supplemental engine. The control system is operable to maintain the supplemental engine in a reduced power state at least until a determination is made that supplemental power is needed to satisfy a total power demand of the drive system. The control system is also operable to determine that supplemental power is needed to satisfy the total power demand of the drive system. The control system is further operable to increase a power level of the supplemental engine in response to the determination that supplemental power is needed.

    FAN CLUTCH FOR CONVERTIBLE ENGINE
    8.
    发明申请
    FAN CLUTCH FOR CONVERTIBLE ENGINE 有权

    公开(公告)号：US20220194619A1

    公开(公告)日：2022-06-23

    申请号：US17686347

    申请日：2022-03-03

    Applicant: Textron Innovations Inc.

    Inventor： Alan Hisashi Steinert ,  Thomas Dewey Parsons ,  Troy Cyril Schank

    IPC: B64D35/02 ,  B64D27/20 ,  F02C7/36 ,  F02K3/06 ,  F02K3/075 ,  F04D25/16

    Abstract: Systems and methods include providing an aircraft with a fuselage and a convertible engine disposed within the fuselage. The convertible engine is operable as a turbofan engine in a thrust mode and a turboshaft engine in a shaft power mode. The convertible engine includes a housing, an engine core having a low pressure turbine shaft, and a bypass fan system. The bypass fan system includes a bypass fan having a fan clutch. The fan clutch selectively couples at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode and decouples at least a portion of the bypass fan from the low pressure turbine shaft when the convertible engine is operated in the shaft power mode.

    Lubrication management systems for tiltrotor aircraft
    9.
    发明授权
    Lubrication management systems for tiltrotor aircraft 有权

    公开(公告)号：US11280398B2

    公开(公告)日：2022-03-22

    申请号：US16025147

    申请日：2018-07-02

    Applicant: Textron Innovations Inc.

    Inventor： Thomas Dewey Parsons ,  Troy Cyril Schank

    IPC: F16H57/04 ,  B64C29/00 ,  B64C11/28 ,  B60K11/02

    Abstract: A drive system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The drive system includes an engine to provide rotational energy and a proprotor assembly to receive rotational energy from the engine when the tiltrotor aircraft is in the rotary flight mode. The proprotor assembly is disengaged from the engine in the non rotary flight mode. The drive system includes a proprotor gearbox including one or more gears mechanically interposed between the engine and the proprotor assembly. The proprotor gearbox transfers rotational energy from the engine to the proprotor assembly when the tiltrotor aircraft is in the rotary flight mode. The drive system includes a lubricant operable to reduce friction between the gears and a lubrication management system to affect a temperature of the lubricant to enhance lubrication between the gears in the proprotor gearbox in the rotary flight mode.

    Rotorcraft engine inlet configuration to optimize performance in both hover and high speed flight
    10.
    发明授权
    Rotorcraft engine inlet configuration to optimize performance in both hover and high speed flight 有权

    公开(公告)号：US10889384B2

    公开(公告)日：2021-01-12

    申请号：US15710622

    申请日：2017-09-20

    Applicant: Textron Innovations Inc.

    Inventor： Thomas Dewey Parsons

    IPC: B64D33/02 ,  B64C33/02 ,  F02C7/057 ,  F02C7/04 ,  F02C7/042 ,  B64C27/04

    Abstract: The present invention achieves technical advantages as a rotorcraft engine inlet configuration to optimize performance in both hover and high-speed flight. A rotorcraft fuselage with a ram air intake and a side air intake allows airflow into the engine inlet plenum. A door can be operably coupled to the fuselage, wherein the door is in an open position when the airspeed is below a first threshold and is in a closed position when the airspeed exceeds a second threshold. Additionally, control logic, compares the rotorcraft airspeed with a stored airspeed to operate an actuator to open and close the door to modulate the airflow into the engine inlet plenum. The present invention realizes the advantages of eliminating the inlet spillage drag due to inlet ram airflow in forward flight and increasing the available engine power by mitigating the loss of inlet air pressure recovery.

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