公开(公告)号：US20250012202A1

公开(公告)日：2025-01-09

申请号：US18347722

申请日：2023-07-06

Applicant: Rolls-Royce North American Technologies Inc.

Inventor： Eric Engebretsen ,  Aaron Weishaar ,  Jonathan Acker ,  Brett Hartnagel

IPC: F01D25/02 ,  F01D5/18 ,  F02C7/047

Abstract: A gas turbine engine includes: an inlet guide vane; an inlet channel extending from a location downstream of the inlet guide vane to a stem manifold; and an outlet channel extending to an outlet port, the outlet port configured to dump anti-ice air overboard, wherein the inlet guide vane includes an anti-ice cavity in fluid communication with the inlet channel and the outlet channel such that anti-ice air, flowing from a downstream location within a core flow of the gas turbine, flows from the inlet channel, through the inlet guide vane, and to the outlet channel.

公开(公告)号：US20240367802A1

公开(公告)日：2024-11-07

申请号：US18141820

申请日：2023-05-01

Applicant: Rohr, Inc.

Inventor： Brian A. Sherman

IPC: B64D15/12 ,  B64D33/02 ,  F01D25/02 ,  H05B3/14 ,  H05B3/18

Abstract: An assembly for an aircraft propulsion system includes a first lip segment and a second lip segment. The first lip segment includes a first lip skin, a first mount and a first electric heater. The first mount is disposed at a first side of the first lip segment and connected to the first lip skin. The first electric heater is disposed at the first side of the first lip segment and integrated with the first lip skin. The second lip segment includes a second lip skin, a second mount and a second electric heater. The second mount is disposed at a second side of the second lip segment and connected to the second lip skin. The second mount is removably attached to the first mount. The second electric heater is disposed at the second side of the second lip segment and integrated with the second lip skin.

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：US20230045400A1

公开(公告)日：2023-02-09

申请号：US17969826

申请日：2022-10-20

Applicant: ROLLS-ROYCE PLC

Inventor： Ian J. BOUSFIELD ,  Duncan A. MACDOUGALL

IPC: F01D25/02 ,  F01D5/14 ,  F04D29/32

Abstract: A gas turbine engine includes a fan mounted to rotate about a main longitudinal axis; an engine core, including a compressor, a combustor, and turbine coupled to the compressor through a shaft; and reduction gearbox; wherein the compressor includes a plurality of stages, each stage including a respective rotor and stator, a first stage of the plurality of stages being arranged at an inlet and including a first rotor with a plurality of blades; each blade extending chordwise from a leading edge to a trailing edge, and from root to tip for a span height, wherein 0% of the span height corresponds to the root and 100% of span height corresponds to tip; wherein a ratio of a leading edge radius of each of the plurality of first rotor blades at 0% span height to a minimum leading edge radius is comprised between 1 and 1.50.

公开(公告)号：US20220235670A1

公开(公告)日：2022-07-28

申请号：US17596405

申请日：2020-06-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Baptiste Rene Roger BATONNET ,  Alban Francois LOUIS

IPC: F01D25/02 ,  F01D5/02 ,  F02C7/047 ,  B64C11/14 ,  B64D15/16

Abstract: The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.

公开(公告)号：US11236632B2

公开(公告)日：2022-02-01

申请号：US15882051

申请日：2018-01-29

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge

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

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：US20210388762A1

公开(公告)日：2021-12-16

申请号：US17287457

申请日：2019-10-22

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Rémi Roland Robert MERCIER ,  Fabrice Michel François René AUBERT ,  Arnaud LANGLOIS

IPC: F02C7/047 ,  F02K3/06 ,  F01D9/04 ,  F01D25/02

Abstract: The invention relates to a de-icing device designed to supply de-icing air to a turbomachine separation nozzle extending along a longitudinal axis, the turbomachine comprising:—the separation nozzle which is designed to be positioned downstream from a turbomachine fan and comprises an internal casing and an external casing which form a separation between a primary flow vein for a primary stream and a secondary flow vein for a secondary stream, said streams issuing from the fan, the internal casing and the external casing defining an inter-vein space;—turbomachine guide vanes designed to be secured by screws to the internal casing such that the screws extend into the inter-vein space, the de-icing device being intended to be positioned in the inter-vein space and comprising—an air inlet;—an air outlet;—a plurality of channels extending from the air inlet toward the air outlet; the channels being arranged in relation to one another such that they are designed to extend from the air inlet toward the air outlets, passing between the screws for securing the guide vanes.

公开(公告)号：US11199133B2

公开(公告)日：2021-12-14

申请号：US16222599

申请日：2018-12-17

Applicant: Hamilton Sundstrand Corporation

Inventor： Peter A T Cocks

IPC: F01D25/02 ,  F02C7/14 ,  F02C7/047 ,  F02C7/232 ,  F02C9/26 ,  F02C9/30 ,  B64D15/02 ,  F02C7/22

Abstract: An aircraft fuel system can include a fuel line configured to transport fuel therein, an exposed aircraft structure in direct or indirect thermal communication with the fuel in the fuel line to receive heat from the fuel to provide a deicing or anti-icing heat to the exposed aircraft structure. The exposed aircraft structure can include at least one internal fuel channel in fluid communication with the fuel line for direct thermal communication with the fuel. The system can include a fuel/fluid heat exchanger in fluid communication with the fuel line to transfer heat from the fuel to a fluid to provide indirect thermal communication between the fuel and the exposed aircraft structure.