公开(公告)号：US12071893B2

公开(公告)日：2024-08-27

申请号：US17595283

申请日：2020-04-21

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Jacques Russmann ,  Clément Dupays ,  Jean-Marc Blan

IPC: F02C7/047 ,  F01D25/02

CPC classification number: F02C7/047 ,  F01D25/02 ,  F05D2220/323 ,  F05D2270/301 ,  F05D2270/303 ,  F05D2270/304

Abstract: A turbomachine comprising a cone positioned at an upstream end and secured in rotation to the low-pressure shaft, a system for deicing said cone, comprising resistive heating elements positioned in the cone, an energy transfer system, an electrical power source coupled to the high-pressure shaft and connected to the energy transfer system by a set of switches, and a computer configured so as to define a power set point for deicing the cone depending on ambient temperature and pressure data, and on an operating speed of the low-pressure shaft, and, depending on the electrical power supplied by the electrical power source, define a duty cycle of the set of switches to deliver electrical power to the resistive heating elements.

公开(公告)号：US20240254894A1

公开(公告)日：2024-08-01

申请号：US18428881

申请日：2024-01-31

Applicant: Rohr, Inc.

Inventor： Pratap Mallampati

IPC: F01D25/02 ,  B64D33/02 ,  F02C7/057

CPC classification number: F01D25/02 ,  B64D33/02 ,  F02C7/057 ,  B64D2033/0233 ,  F05D2220/323

Abstract: An anti-icing system for an aircraft nacelle structure is provided that includes a controllable PRSOV, a circumferentially extending duct, a bleed air duct segment, at least one PRV, and a controller. The PRSOV may be disposed in a closed or an open configuration. The PRV is disposed downstream of the PRSOV and in fluid communication with the bleed air duct segment. The PRV may be disposed in a closed or in an open configuration. The controller is in communication with a memory storing instructions. The instructions when executed cause the system controller to control the PRSOV to maintain bleed air within the anti-icing system within a predetermined range of operating pressures by selectively controlling the PRSOV into at least one of the one or more PRV open configurations, and control the PRV to open to maintain the bleed air below the maximum pressure.

公开(公告)号：US11814973B2

公开(公告)日：2023-11-14

申请号：US17568555

申请日：2022-01-04

Applicant: General Electric Company

Inventor： Li Zheng ,  Changjie Sun ,  Nicholas J. Kray

IPC: F01D25/06 ,  F01D9/04 ,  F01D5/18 ,  F01D25/02 ,  F01D5/04

CPC classification number: F01D25/06 ,  F01D5/18 ,  F01D9/041 ,  F01D25/02 ,  F01D5/046 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2260/96

Abstract: Methods, apparatus, systems, and articles of manufacture to provide damping of an airfoil are disclosed. An example airfoil is disposed in a flow path, the airfoil including a shell defining an exterior surface of the airfoil and forming a cavity in an interior surface of the airfoil, and a lattice damper disposed in the cavity, the lattice damper to reduce vibrational loads exerted on the airfoil.

公开(公告)号：US20190186360A1

公开(公告)日：2019-06-20

申请号：US16211360

申请日：2018-12-06

Applicant: ROLLS-ROYCE plc

Inventor： Benjamin J. SELLERS

IPC: F02C7/057 ,  B64D31/00 ,  B64D27/10 ,  B64F5/60 ,  F01D25/02 ,  F02C7/047

CPC classification number: F02C7/057 ,  B64D15/12 ,  B64D27/10 ,  B64D31/00 ,  B64D2221/00 ,  B64F5/60 ,  F01D15/10 ,  F01D25/02 ,  F02C7/047 ,  F02C7/32 ,  F02C9/00 ,  F05D2220/76 ,  F05D2270/101 ,  F05D2270/309 ,  F05D2270/335

Abstract: A method of controlling electrical power supplied to a component of a vehicle, the method comprising: receiving a signal comprising information associated with an operating condition of a gas turbine engine; determining whether a parameter exceeds a predetermined threshold value using the information in the received signal; and controlling a reduction in electrical power supplied to a component of a vehicle from a generator of the gas turbine engine if the parameter exceeds the predetermined threshold value.

公开(公告)号：US20180216528A1

公开(公告)日：2018-08-02

申请号：US15748252

申请日：2016-07-27

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Guillaume Claude Georges Philippe LINASSIER ,  Morgan BALLAND ,  Helene MAZET ,  Christophe SCHOLTES ,  Antoine Robert Alain BRUNET ,  Simon AMOEDO

IPC: F02C7/047 ,  F01D9/04 ,  F01D25/02

CPC classification number: F02C7/047 ,  F01D9/041 ,  F01D25/02 ,  F05D2240/14

Abstract: An anti-icing system for a turbine engine vane extending between an outer casing and an inner casing defining a passage, the system includes an injector device for injecting a jet of air into the passage upstream from the vane, the injector device including a first injection orifice for injecting the jet of air, the first orifice passing through one member selected from the outer casing and the inner casing, and being located in such a manner that, at a first speed of the engine wherein a stream of air flows generally in the passage along a first direction, the first orifice and a leading edge of the vane are substantially in alignment along the first direction, the first orifice is spaced apart from the junction between the leading edge of the vane and the member through which the first orifice passes by a distance of at least 10 mm, and preferably of about 15 mm.

公开(公告)号：US20180195408A1

公开(公告)日：2018-07-12

申请号：US15405016

申请日：2017-01-12

Applicant: General Electric Company

Inventor： David William Crall ,  Charles Daniel Califf ,  Craig William Higgins ,  Erich Alois Krammer

IPC: F01D25/02 ,  F02C9/18 ,  F01D9/02 ,  F01D17/14 ,  F01D25/28

CPC classification number: F01D25/02 ,  F02C7/047 ,  F02C9/18

Abstract: A method and icing effects mitigation system are provided. The icing effects mitigation system includes a fluid duct configured to channel a first flow of fluid through the fluid duct from a duct opening to a rotatable member at least partially positioned within the fluid duct. The rotatable member includes a radially inner rotatable portion and a radially outer rotatable portion. The icing effects mitigation system also includes a duct member extending through the fluid duct in a direction approximately orthogonal to a direction of the first flow of fluid. The duct member is configured to channel a second flow of a second fluid therethrough that causes ice accreted on the duct member to shed on a trajectory that impacts the rotatable member at the radially inner portion.

公开(公告)号：US09976481B2

公开(公告)日：2018-05-22

申请号：US14791085

申请日：2015-07-02

Applicant: ROHR, Inc.

Inventor： Galdemir Botura

IPC: F02C7/047 ,  F02C7/08 ,  F01D25/08 ,  F01D25/02 ,  F01D11/24 ,  F02C6/08

CPC classification number: F02C7/047 ,  F01D11/24 ,  F01D25/02 ,  F01D25/08 ,  F02C6/08 ,  F02C7/08 ,  Y02T50/672

Abstract: A deicing system for an aircraft may comprise a dual pressure regulating valve. The dual pressure regulating valve may comprise a low pressure setting and a high pressure setting. The low pressure setting may supply a relatively lesser supply of bleed air to an aircraft component, and the high pressure setting may supply a relatively greater supply of bleed air to the aircraft component. The dual pressure regulating valve may be switched between the low pressure setting and the high pressure setting based on aircraft or atmospheric conditions to prevent heat damage to the aircraft component.

公开(公告)号：US20180093785A1

公开(公告)日：2018-04-05

申请号：US15284052

申请日：2016-10-03

Applicant: ROHR, INC.

Inventor： Keith T. Brown

IPC: B64F5/00 ,  B64D15/12 ,  B64D29/00 ,  F02C7/047

CPC classification number: F02C7/047 ,  B64D15/12 ,  B64D2033/0233 ,  B64F5/40 ,  F01D25/02 ,  F05D2230/80 ,  F05D2270/54

Abstract: An ice protection system for an aircraft may comprise an electric heater embedded within a composite aircraft component. In the event of malfunction of the embedded heater, a secondary heater may be attached to an interior surface of the composite aircraft component. The wiring may be detached from the embedded heater and attached to the secondary heater. The secondary heater may be used to provide ice protection to the composite aircraft component.

公开(公告)号：US09915164B2

公开(公告)日：2018-03-13

申请号：US14688080

申请日：2015-04-16

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

IPC: F01D15/10 ,  F01D25/02 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F02C3/107

CPC classification number: F01D15/10 ,  F01D25/02 ,  F02C3/107 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/76 ,  F05D2230/72 ,  F05D2260/40311 ,  F05D2260/60 ,  Y02T50/671

Abstract: A gas turbine engine comprises a fan rotor, a lower speed compressor rotor and a higher speed compressor rotor, and a lower speed turbine rotor and a higher speed turbine rotor. The lower speed turbine rotor rotates the lower speed compressor rotor, and rotates a gear reduction to, in turn, rotate the fan rotor. The higher speed turbine rotor rotates the higher speed compressor rotor. An electrical generator is driven to rotate with one of the lower speed turbine rotor and the fan rotor.

公开(公告)号：US20180066537A1

公开(公告)日：2018-03-08

申请号：US15667115

申请日：2017-08-02

Applicant: ROLLS-ROYCE plc

Inventor： Steven A RADOMSKI ,  Matthew D CURREN

IPC: F01D25/10 ,  F01D9/04 ,  F01D25/00 ,  F01D25/02

CPC classification number: F01D25/10 ,  F01D9/041 ,  F01D9/065 ,  F01D25/005 ,  F01D25/02 ,  F02C3/04 ,  F02C7/047 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2260/208 ,  F05D2260/22141 ,  F05D2260/40311 ,  F05D2260/98 ,  F05D2300/121 ,  F05D2300/20 ,  F05D2300/43 ,  F05D2300/605 ,  F05D2300/611 ,  Y02T50/671 ,  Y02T50/675

Abstract: A vane for a gas turbine engine has a pressure surface and a suction surface. The vane comprises an arrangement of internal channels and a plurality of conducting members extends from the channels towards the suction surface and/or the pressure surface.