公开(公告)号：US12110116B1

公开(公告)日：2024-10-08

申请号：US18217228

申请日：2023-06-30

Applicant: Raytheon Technologies Corporation

Inventor： Ryan A. Mitchell ,  Robert B. Fowler

IPC: B64D13/06 ,  B64D13/08 ,  B64D27/10 ,  F02C3/13 ,  F02C6/08 ,  F02C6/18 ,  F02C7/08 ,  F02C9/42 ,  F02K3/12

CPC classification number: B64D13/06 ,  B64D13/08 ,  B64D27/10 ,  F02C3/13 ,  F02C6/08 ,  F02C6/18 ,  F02C7/08 ,  F02C9/42 ,  F02K3/12

Abstract: A method of operation is provided during which a heating fluid is directed through a first passage into a combustor section to heat a component within the combustor section when an aircraft engine is in a first standby mode. The aircraft engine includes a flowpath, a compressor section, the combustor section, a turbine section and an exhaust section. The flowpath extends through the compressor section, the combustor section, the turbine section and the exhaust section from an inlet into the flowpath to an exhaust from the flowpath. The heating fluid is directed through a second passage into the exhaust section when the aircraft engine is in a second mode. The heating fluid is directed through the second passage bypasses the turbine section.

公开(公告)号：US12103689B2

公开(公告)日：2024-10-01

申请号：US17762426

申请日：2019-09-23

Applicant: SAFRAN CABIN GERMANY GMBH

Inventor： Christian Will ,  Alexander Kusch ,  Samuel Klassen

IPC: B64D13/08 ,  B64D11/04 ,  F25B21/04 ,  B64D13/06

CPC classification number: B64D13/08 ,  B64D11/04 ,  F25B21/04 ,  B64D2013/0629 ,  F25B2321/023 ,  F25B2321/0251

Abstract: The invention relates to An aircraft on-board kitchen module (1) comprising at least one heater and/or cooler with at least one first compartment (2) for drinks and/or food and whose temperature can be conditioned by at least one thermoelectric element (5) having a first and a second heat exchanger (8, 9), one of the heat exchangers (8, 9) forming a cold side and the other heat exchanger (8, 9) forming a hot side of the thermoelectric element (5) such that heat generated by the thermoelectric element (5) is dissipated by a primary coolant from a central cooling system (11) of the aircraft, the primary coolant being supplied via a coolant duct (10) that is selectively supplied with ambient air from the cabin and/or conditioned cold air from the central cooling system (11) of the aircraft.

公开(公告)号：US20240318883A1

公开(公告)日：2024-09-26

申请号：US18188220

申请日：2023-03-22

Applicant: Honeywell International Inc.

Inventor： Sung-Han Jung ,  Siamak Nikbin ,  Daniel R. Robles

IPC: F25B49/02 ,  B64D13/08 ,  F25B5/02 ,  F25B40/02 ,  F25B40/04 ,  F25B41/385 ,  F25B43/00

CPC classification number: F25B49/022 ,  B64D13/08 ,  F25B5/02 ,  F25B40/02 ,  F25B40/04 ,  F25B41/385 ,  F25B43/003 ,  B64D2013/064 ,  F25B2400/06 ,  F25B2600/0253

Abstract: A vapor cycle cooling system includes first and second compressor systems in parallel with one another, each compressor system including a motor, a motor controller, and a first compressor in series with a second compressor; a condenser fluidically coupled to each compressor system; a filter drier, in series with, and fluidically coupled to the condenser; a first expansion device in series with, and fluidically coupled to, a flash heat exchanger, the flash heat exchanger fluidically coupled to a second expansion device, the second expansion device fluidically coupled to a first evaporator, the first evaporator fluidically coupled to each compressor system; a system controller electrically coupled to each motor controller; and a motor and motor controller cooling loop fluidically coupled to the filter drier and each motor, wherein the vapor cycle cooling system is configured to cool one or more thermal loads for a vehicle.

公开(公告)号：US20240278921A1

公开(公告)日：2024-08-22

申请号：US18169910

申请日：2023-02-16

Applicant: THE BOEING COMPANY

Inventor： Ralph E. Chestine

IPC: B64D13/08

CPC classification number: B64D13/08 ,  B64D2013/0618 ,  B64D2013/0651 ,  B64D2013/0674

Abstract: A heat exchanger system and method includes a securing frame, a heat transfer core having heat transfer panels removably secured to the securing frame, the heat transfer panels optionally including a plurality of segment modules coupled together, and one or more filter screens removably secured to the securing frame at one or both of an inlet end or an outlet end. The heat transfer core is disposed between the inlet end and the outlet end.

公开(公告)号：US12065250B2

公开(公告)日：2024-08-20

申请号：US17116224

申请日：2020-12-09

Applicant: Hamilton Sundstrand Corporation

Inventor： Brian R. Shea ,  Peter Zywiak ,  Luke Martin

IPC: B64D13/06 ,  B64D13/02 ,  B64D13/08 ,  B64D41/00

CPC classification number: B64D13/06 ,  B64D13/02 ,  B64D13/08 ,  B64D41/00 ,  B64D2013/0611 ,  B64D2013/0618 ,  B64D2013/0688

Abstract: An aircraft air conditioning system includes a lower cooling zone and an upper cooling zone. The lower cooling zone includes a lower recirculation heat exchanger configured to receive cabin air from a cabin and convert the cabin air into lower cooled recirculated cabin air. The upper cooling zone includes an upper recirculation heat exchange configured to receive the cabin air from the cabin and convert the cabin air into upper cooled recirculated cabin air. A power system selectively delivers power to the lower cooling zone and the upper cooling zone. A controller is in signal communication with the power system. The controller determines a target temperature of the cabin and invokes a recirculation ground maintenance mode that commands the power system to deliver power to one or both of the lower cooling zone and the upper cooling zone so that a temperature of the cabin reaches the target temperature.

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

IPC: B64D13/08 ,  B64D13/06

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.

公开(公告)号：US20240218807A1

公开(公告)日：2024-07-04

申请号：US18608521

申请日：2024-03-18

Applicant: Hamilton Sundstrand Corporation

Inventor： Jeremy Clavette ,  Mark R. Gurvich

IPC: F01D21/04 ,  B64D13/08 ,  F01D5/04 ,  F04D29/28

CPC classification number: F01D21/045 ,  B64D13/08 ,  F01D5/048 ,  F04D29/284 ,  F05B2240/306

Abstract: A rotor includes a base member including a first side, a second side opposite the first side, and a central opening passing through the first side and the second side. The second side includes an outer circumferential edge having a first dimension and the central opening having an inner circumferential edge having a second dimension. A plurality of blades extend outwardly from the first side. The plurality of blades extend about the central opening. A fuse element is formed in the second side and extends along one of a radial direction and a circumferential direction. The fuse element has a length that is less than the first dimension.

公开(公告)号：US12006045B2

公开(公告)日：2024-06-11

申请号：US17190925

申请日：2021-03-03

Applicant: UNITED TECHNOLOGIES RESEARCH CENTRE IRELAND, LIMITED

Inventor： Yonghua Zhu ,  Erica Zavaglio

IPC: B64D13/08 ,  B64D13/06

CPC classification number: B64D13/08 ,  B64D13/06 ,  B64D2013/0618 ,  B64D2013/0651 ,  B64D2013/0688

Abstract: A regenerative filter system includes a regenerative filter material arranged to filter air recirculated from an aircraft interior and means for passing a regeneration air stream through the regenerative filter material to regenerate the filter material by removing adsorbed contaminant therefrom, whereby the means for passing the regeneration air stream comprises means for expanding air exhausted from the aircraft interior and using the expanded air to drive a compressor for compressing and conditioning ram air to provide the regeneration air stream to the filter material.

公开(公告)号：US20240182173A1

公开(公告)日：2024-06-06

申请号：US18075139

申请日：2022-12-05

Applicant: Hamilton Sundstrand Corporation

Inventor： Viktor Kilchyk ,  John H. Paliulis

IPC: B64D13/04 ,  B64D13/08 ,  F04D29/058

CPC classification number: B64D13/04 ,  B64D13/08 ,  F04D29/058 ,  B64D2013/0618

Abstract: An air cycle machine includes a turbine section, a compressor section, an axial flux magnetic gear system electromechanically coupling the turbine section to the compressor section, and a stabilization system for at least one shaft of the air cycle machine. The axial flux magnetic gear system includes a stator, two rotors, a winding system, and a control module. Each rotor interacts with the stator such that the rotor rotates when the axial flux magnetic gear system is exposed to an electrical current. The winding system stabilizes the position of the rotors along their rotational axes. The control module is configured to supply the electrical current to at least one of the winding system, the stator, and the rotors to drive rotation of the rotors. The stabilization system stabilizes the position of the at least one shaft of the air cycle machine along the shaft's rotational axis.

公开(公告)号：US20240166356A1

公开(公告)日：2024-05-23

申请号：US18505667

申请日：2023-11-09

Applicant: EMBRAER S.A.

Inventor： Rodolfo DA SILVA COLLARES ,  Dayvis Dias DA SILVA ,  Daniel Parrode Fraia DE SOUZA SANTOS

IPC: B64D13/08 ,  B60L50/70 ,  B64D15/04 ,  B64D27/24 ,  H01M8/04007 ,  H01M8/04014

CPC classification number: B64D13/08 ,  B60L50/70 ,  B64D15/04 ,  B64D27/24 ,  H01M8/04014 ,  H01M8/04074 ,  B64D2013/0607

Abstract: Air systems for a fuel cell powered aircraft include at least one compressor for supplying heated compressed air, at least one heat exchange system for receiving the heated compressed air and from the at least one compressor and discharging cooled compressed air, and at least one turbine for receiving the cooled compressed air from the heat exchange system and directing the cooled compressed air to on-board aircraft cabin pressurization and temperature control systems. At least one shaft operatively interconnects the at least one compressor and the at least one turbine. An electric motor is provided and adapted to being powered by electrical power supplied by an on-board fuel cell of the aircraft, the electric motor being operatively connected to the shaft interconnecting the at least one compressor and the at least one turbine so as to operatively cause the shaft to drive the at least one compressor and the at least one turbine.