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公开(公告)号：US11999492B2
公开(公告)日：2024-06-04
申请号：US17748324
申请日：2022-05-19
Applicant: Textron Aviation Inc.
Inventor： Robert Glynn Wiegers , Clinton Lee Thompson
CPC classification number: B64D13/08 , B64D2013/064 , B64D2013/0644 , B64D2013/0688
Abstract: An electric temperature control system for unpressurized aircraft and methods for operating are disclosed. The electric temperature control system may be electrically powered and used on all-electric aircraft or hybrid aircraft. The electric temperature control system may comprise a vapor cycle cooling system for cooling air and an electric heater for heating air. The electric heater may be a PTC electric heater with individually-controllable heating elements. Various input devices may be disposed in the aircraft allowing an operator to set a compartment temperature, an air source, and a fan speed. A controller controls operations of the electric temperature control system based on feedback received from a plurality of feedback devices and the operator inputs.
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公开(公告)号：US20250108909A1
公开(公告)日：2025-04-03
申请号：US18477984
申请日：2023-09-29
Applicant: Textron Aviation Inc.
Inventor： Kelly Ray Laflin , Robert Glynn Wiegers
Abstract: A low drag nacelle and pylon fairing for an aircraft includes a fairing configured to provide a low drag connection between a pylon and a nacelle. The fairing includes an aft-facing face formed between the nacelle and a trailing edge of the pylon with the aft-facing face being configured with a vent for exhausting air in the same direction as engine jet exhaust flow. The fairing includes aerodynamically formed curves providing a larger aft-facing face compared with traditional fairing arrangements. A substantial improvement in drag reduction is achieved by venting air into the space immediately beyond the aft-facing face.
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公开(公告)号：US12129037B2
公开(公告)日：2024-10-29
申请号：US18054624
申请日：2022-11-11
Applicant: Textron Aviation Inc.
Inventor： Robert Glynn Wiegers , Clinton Lee Thompson , Robin L. Young
CPC classification number: B64D13/08 , B60H1/0073 , G05D23/1931 , B64D2013/0618
Abstract: A method for heating an unpressurized aircraft includes receiving a desired air temperature, calculating a target duct air temperature based on the desired air temperature, determining an actual duct air temperature via a duct air temperature sensor, calculating a target modulation of one or more ram air valves based on a difference between the target duct air temperature and the actual duct air temperature, modulating one or more of the ram air valves based on the target modulation, introducing a bleed air from a turbine engine to a heat exchanger, introducing a temperature control air from one of the one or more ram air valves to the heat exchanger for cooling the bleed air to provide a temperature-controlled air, mixing the temperature-controlled air from the heat exchanger with an ejector ram air in an ejector, and providing air from the ejector to an occupied compartment of the unpressurized aircraft.
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公开(公告)号：US11312500B2
公开(公告)日：2022-04-26
申请号：US15708411
申请日：2017-09-19
Applicant: Textron Aviation Inc.
Inventor： Robert Glynn Wiegers , Cristopher Robert Schroeder
IPC: B64D15/16
Abstract: An electro-pneumatic de-icer for an airfoil includes an electrically-powered compressor for compressing air, an air-storage tank for storing compressed air, a source of negative pressure, an airfoil pneumatic boot, and a control valve located between 1) the air-storage tank, 2) the source of negative pressure, and 3) the pneumatic boot for cycling between compressed air to inflate the pneumatic boot and negative pressure to deflate the pneumatic boot for cracking accumulated ice on the airfoil. An airfoil de-icing method lacking engine bleed air extraction includes compressing air with an electrically-powered compressor, storing high-pressure air from the compressor in an air-storage tank, delivering high-pressure air from the air-storage tank to inflate a pneumatic boot located along an airfoil, providing a negative-pressure source, deflating the pneumatic boot with the negative-pressure source, and alternating between inflating and deflating the pneumatic boot for cracking accumulated ice on the airfoil.
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公开(公告)号：US20230142953A1
公开(公告)日：2023-05-11
申请号：US18054624
申请日：2022-11-11
Applicant: Textron Aviation Inc.
Inventor： Robert Glynn Wiegers , Clinton Lee Thompson , Robin L. Young
CPC classification number: B64D13/08 , G05D23/1931 , B60H1/0073 , B64D2013/0618
Abstract: A method for heating an unpressurized aircraft includes receiving a desired air temperature, calculating a target duct air temperature based on the desired air temperature, determining an actual duct air temperature via a duct air temperature sensor, calculating a target modulation of one or more ram air valves based on a difference between the target duct air temperature and the actual duct air temperature, modulating one or more of the ram air valves based on the target modulation, introducing a bleed air from a turbine engine to a heat exchanger, introducing a temperature control air from one of the one or more ram air valves to the heat exchanger for cooling the bleed air to provide a temperature-controlled air, mixing the temperature-controlled air from the heat exchanger with an ejector ram air in an ejector, and providing air from the ejector to an occupied compartment of the unpressurized aircraft.
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Patent Agency Ranking
公开(公告)号：US11161616B2
公开(公告)日：2021-11-02
申请号：US15956201
申请日：2018-04-18
Applicant: Textron Aviation Inc.
Inventor： Robert Glynn Wiegers , Leland Merle Peterson
Abstract: A pneumatic flow-control system and method for an aircraft provide efficient mixing of high-pressure engine bleed air with one or both of low-pressure engine bleed air and ambient air. A controller determines an amount of high- and low-pressure air and ambient air to provide based on ambient air temperature and pressure and a flow rate and temperature of the mixed air for improving engine performance during different phases of flight and for reducing a burden on an environmental control subsystem of the aircraft.
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公开(公告)号：US20180105277A1
公开(公告)日：2018-04-19
申请号：US15708411
申请日：2017-09-19
Applicant: Textron Aviation Inc.
Inventor： Robert Glynn Wiegers , Cristopher Robert Schroeder
IPC: B64D15/16
CPC classification number: B64D15/166
Abstract: An electro-pneumatic de-icer for an airfoil includes an electrically-powered compressor for compressing air, an air-storage tank for storing compressed air, a source of negative pressure, an airfoil pneumatic boot, and a control valve located between 1) the air-storage tank, 2) the source of negative pressure, and 3) the pneumatic boot for cycling between compressed air to inflate the pneumatic boot and negative pressure to deflate the pneumatic boot for cracking accumulated ice on the airfoil. An airfoil de-icing method lacking engine bleed air extraction includes compressing air with an electrically-powered compressor, storing high-pressure air from the compressor in an air-storage tank, delivering high-pressure air from the air-storage tank to inflate a pneumatic boot located along an airfoil, providing a negative-pressure source, deflating the pneumatic boot with the negative-pressure source, and alternating between inflating and deflating the pneumatic boot for cracking accumulated ice on the airfoil.
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公开(公告)号：US20240270390A1
公开(公告)日：2024-08-15
申请号：US18644964
申请日：2024-04-24
Applicant: Textron Aviation Inc.
Inventor： Robert Glynn Wiegers , Clinton Lee Thompson
CPC classification number: B64D13/08 , B64D2013/064 , B64D2013/0644 , B64D2013/0688
Abstract: An electric temperature control system for unpressurized aircraft and methods for operating are disclosed. The electric temperature control system may be electrically powered and used on all-electric aircraft or hybrid aircraft. The electric temperature control system may comprise a vapor cycle cooling system for cooling air and an electric heater for heating air. The electric heater may be a PTC electric heater with individually-controllable heating elements. Various input devices may be disposed in the aircraft allowing an operator to set a compartment temperature, an air source, and a fan speed. A controller controls operations of the electric temperature control system based on feedback received from a plurality of feedback devices and the operator inputs.
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公开(公告)号：US20180312262A1
公开(公告)日：2018-11-01
申请号：US15956201
申请日：2018-04-18
Applicant: Textron Aviation Inc.
Inventor： Robert Glynn Wiegers , Leland Merle Peterson
Abstract: A pneumatic flow-control system and method for an aircraft provide efficient mixing of high-pressure engine bleed air with one or both of low-pressure engine bleed air and ambient air. A controller determines an amount of high- and low-pressure air and ambient air to provide based on ambient air temperature and pressure and a flow rate and temperature of the mixed air for improving engine performance during different phases of flight and for reducing a burden on an environmental control subsystem of the aircraft.
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公开(公告)号：US20230373640A1
公开(公告)日：2023-11-23
申请号：US17748324
申请日：2022-05-19
Applicant: Textron Aviation Inc.
Inventor： Robert Glynn Wiegers , Clinton Lee Thompson
IPC: B64D13/08
CPC classification number: B64D13/08 , B64D2013/064
Abstract: An electric temperature control system for unpressurized aircraft and methods for operating are disclosed. The electric temperature control system may be electrically powered and used on all-electric aircraft or hybrid aircraft. The electric temperature control system may comprise a vapor cycle cooling system for cooling air and an electric heater for heating air. The electric heater may be a PTC electric heater with individually-controllable heating elements. Various input devices may be disposed in the aircraft allowing an operator to set a compartment temperature, an air source, and a fan speed. A controller controls operations of the electric temperature control system based on feedback received from a plurality of feedback devices and the operator inputs.
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