公开(公告)号：US12129765B2

公开(公告)日：2024-10-29

申请号：US18388567

申请日：2023-11-10

Applicant: General Electric Company

Inventor： Krzysztof Andrzej Woszczak ,  William Patrick Rusch ,  Samuel Nathan Merrill ,  Ejiro Anthony Oruaga ,  David John Nelmes ,  Justyna Ludwika Wojdyło ,  John Francis Nolan

IPC: F01D25/24 ,  F01D21/00 ,  F01D25/02 ,  F01D25/28

CPC classification number: F01D25/243 ,  F01D21/003 ,  F01D25/02 ,  F01D25/28 ,  F05D2230/644 ,  F05D2240/14 ,  F05D2250/11 ,  F05D2260/30

Abstract: A method and system for aligning a component within a turbine casing, and a related turbine casing, are disclosed. In a top-on position, a location of a reference point and another, vertically spaced reference point on the lower casing are measured. After removing at least the upper casing, the reference points' locations are measured again, and the locations of a reference point on an upper surface of the HJ flange are measured. A prediction offset value is calculated for the component support position in the top-on position based on the locations. The prediction offset value may include a vertical adjustment based, in part, on a translation of a triangular spatial relationship of a number of the reference points and/or a tilt angle, a horizontal adjustment, and a HJ flange surface distortion adjustment. The component support position is adjusted by the prediction offset value to improve alignment.

公开(公告)号：US20240318574A1

公开(公告)日：2024-09-26

申请号：US18736906

申请日：2024-06-07

Applicant: LORD Corporation

Inventor： Russell E. Altieri ,  Victor Zaccardo ,  Paul R. Black ,  Douglas Swanson ,  Daniel E. Kakaley

IPC: F01D21/00 ,  F01D11/12 ,  G01B7/14

CPC classification number: F01D21/003 ,  F01D11/122 ,  G01B7/14 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/305 ,  F05D2270/802 ,  F05D2270/807 ,  F05D2270/821

Abstract: Systems and methods for measuring a clearance between a rotating machine component and a sensor unit are disclosed. In some aspects, a system includes a sensor unit oriented to detect the rotating machine component as the rotating machine component rotates past the sensor unit, the sensor unit including at least a first sensing element and a second sensing element spaced apart from the first sensing element. The system includes a sensor processing unit in electrical communication with the sensor unit. The sensor processing unit is configured for receiving a first waveform from the first sensing element; receiving a second waveform from the second sensing element; and determining, based on a comparison between the first waveform and the second waveform, a distance between the blade tip and the sensor unit.

公开(公告)号：US12098652B2

公开(公告)日：2024-09-24

申请号：US18252753

申请日：2021-11-17

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Tony Alain Roger Joël Lhommeau ,  Damien Bruno Lamouche ,  Mattéo Minervino ,  Julie Valérie Clara Lavigne

IPC: F01D5/28 ,  F01D21/00

CPC classification number: F01D5/282 ,  F01D21/003 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/80 ,  F05D2300/6034

Abstract: A part made of composite material, in particular for an aircraft turbine engine, includes a body produced from fibers woven in three dimensions and immersed in a resin, in particular an organic or polymer resin. The part has at least one crack sensor capable of detecting a crack in the part, at least one link element connected to the sensor and configured to transmit a signal(S), in particular to a member outside of the part, when a crack in the part is detected. The crack sensor has at least one conductive wire woven with the fibers of the body, and the link element is configured to measure the resistance of the conductive wire and to wirelessly transmit the signal.

公开(公告)号：US12085029B2

公开(公告)日：2024-09-10

申请号：US18084083

申请日：2022-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Peter Swann ,  Craig W Bemment ,  Alastair G Hobday ,  Benjamin J Keeler ,  Christopher P Madden

IPC: F02C9/40 ,  F01D21/00 ,  F02C9/28

CPC classification number: F02C9/40 ,  F01D21/003 ,  F02C9/28 ,  F05D2220/323 ,  F05D2260/83 ,  F05D2270/07 ,  F05D2270/71

Abstract: A method of operating an aircraft that includes a propulsion system. The propulsion system includes a gas turbine engine and a fuel tank arranged to provide fuel to the gas turbine engine. The method includes: determining at least one fuel characteristic of the fuel arranged to be provided to the gas turbine engine; and controlling the propulsion system based on the at least one fuel characteristic.

公开(公告)号：US12077279B2

公开(公告)日：2024-09-03

申请号：US17241915

申请日：2021-04-27

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jagoda Krzywon

IPC: B64C11/38 ,  B64C11/30 ,  B64D45/00 ,  F01D7/02 ,  F01D21/00

CPC classification number: B64C11/385 ,  B64C11/301 ,  B64D45/00 ,  F01D7/02 ,  F01D21/003 ,  B64D2045/0085

Abstract: There is provided a method and a system for detecting and mitigating a propeller failure condition. An actual value of a rotational speed of the propeller and/or of a pitch angle of blades of the propeller is obtained. In response to determining that the speed is below a reference rotational speed for the propeller and/or determining that the pitch angle is above a pitch angle threshold, an actuator operatively connected to the blades is commanded to decrease the pitch angle to increase the speed towards the reference speed. After commanding of the actuator to decrease the pitch angle, a subsequent value of the speed and/or a subsequent value of the pitch angle is obtained. The actuator is commanded to hold the pitch angle in response to determining that the speed has failed to increase towards the reference speed and/or determining that the pitch angle has failed to decrease.

公开(公告)号：US12055053B1

公开(公告)日：2024-08-06

申请号：US18136132

申请日：2023-04-18

Applicant: Raytheon Technologies Corporation

Inventor： Scott Goyette ,  Janet Shaw ,  Gregory S. Hagen ,  Zaffir A. Chaudhry ,  David L. Lincoln ,  Jeffrey P. King

IPC: F01D21/00 ,  F01D25/00

CPC classification number: F01D21/003 ,  F01D25/002 ,  F05D2220/36 ,  F05D2270/02 ,  F05D2270/8041

Abstract: An inspection system for fan rotor blades in a gas turbine engine is provided. The gas turbine engine has a sensor that provides a fan rotor stage speed signal. The system includes a plurality of cameras and light sources and a system controller. The cameras are controllable to image a leading edge of a fan rotor blade. Each respective camera and light source is mounted with a static structure disposed forward of the fan rotor blade stage. The system controller is in communication with stored instructions that when executed cause the system controller to monitor the speed of the fan rotor stage during an engine shutdown; upon the fan rotor stage speed reaching a first value, control the light sources to selectively illuminate the fan rotor blades, and control the cameras to image the fan rotor blades, and provide inspection information using signals representative of the captured images.

公开(公告)号：US20240254893A1

公开(公告)日：2024-08-01

申请号：US18629412

申请日：2024-04-08

Applicant: RTX Corporation

Inventor： Jeremiah C. Lee ,  Daniel McMenamin ,  Alek Gavrilovski

IPC: F01D21/00

CPC classification number: F01D21/003 ,  F05D2260/80 ,  F05D2270/306 ,  F05D2270/80

Abstract: A method is provided for an engine. During this method, a saturation current of a gas flow is measured. The gas flow includes combustion products generated by the engine. The saturation current is monitored to determine presence of debris entrained within the gas flow.

公开(公告)号：US12037914B1

公开(公告)日：2024-07-16

申请号：US18202754

申请日：2023-05-26

Applicant: Raytheon Technologies Corporation

Inventor： Joseph B. Phelps

IPC: F01D21/00 ,  F02C7/06 ,  G01P3/481

CPC classification number: F01D21/003 ,  F02C7/06 ,  G01P3/481 ,  F05D2270/304 ,  F05D2270/80

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a rotating assembly and a sensor. The rotating assembly is configured to rotate about an axis. The rotating assembly includes an engine shaft, a phonic wheel and a lubricant scoop. The phonic wheel is mounted onto the engine shaft. The phonic wheel includes an outer surface and a plurality of apertures arranged circumferentially about the axis. Each of the apertures projects at least partially radially into the phonic wheel from the outer surface. The lubricant scoop is radially outboard of and axially overlaps the outer surface. The sensor is configured to measure fluctuations in a magnetic field induced by the phonic wheel during rotation of the rotating assembly about the axis.

公开(公告)号：US20240229666A9

公开(公告)日：2024-07-11

申请号：US17972883

申请日：2022-10-25

Applicant: General Electric Company

Inventor： Rahul Anil Bidkar ,  Deepak Trivedi ,  Bugra H. Ertas ,  Pei-Hsin Kuo ,  Joseph Herbert Fields ,  Andrew Kevin Winn ,  Eric R. Westervelt

IPC: F01D11/00 ,  F01D21/00

CPC classification number: F01D11/003 ,  F01D21/003 ,  F05D2260/80

Abstract: A seal monitoring apparatus is provided. The seal monitoring apparatus includes a temperature sensor and a controller in communication with the temperature sensor. The temperature sensor is mounted at a seal of a device. The controller is configured to receive measured temperature data from the temperature sensor and calculate expected temperature data for the seal based at least in part on operating conditions of the device. The controller is configured to determine a condition of the seal based at least in part on a temperature difference of the measured temperature data from the expected temperature data.

公开(公告)号：US12018570B2

公开(公告)日：2024-06-25

申请号：US18252799

申请日：2021-10-29

Applicant: Rolls-Royce Deutschland Ltd & Co KG

Inventor： Bernd Becker ,  Henner Schrapp

IPC: F01D21/00 ,  F01D5/20 ,  F01D5/30 ,  F01D9/04 ,  F01D17/14 ,  F01D17/18

CPC classification number: F01D21/003 ,  F01D9/041 ,  F01D5/20 ,  F01D5/30 ,  F01D5/303 ,  F01D17/14 ,  F01D17/18 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/301 ,  F05D2270/804

Abstract: A guide vane wheel of a turbomachine, has a plurality of guide vanes, forming a blade row extending radially inward in a flow path of the turbomachine, and two borescope accesses. The guide vanes form two segments each with a plurality of guide vanes circumferentially spaced apart, with the two segments having the same, constant cascade pitch and the two segments spaced such that the respective outermost guide vane adjacent to the respective other segment has an enlarged spacing in the circumferential direction from the adjacent guide vane of the other segment equal to 1.3 to 1.7 times the cascade pitch, the sum of the increased spacings being equal to 3 times the cascade pitch. The increased distance between the respective two adjacent outermost guide vanes of the two segments creates an enlarged vane passage between these guide vanes where the borescope accesses are formed.