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公开(公告)号：US12123311B1
公开(公告)日：2024-10-22
申请号：US18202743
申请日：2023-05-26
Applicant: Raytheon Technologies Corporation
Inventor： Brian D. Shockey , Joseph B. Phelps
CPC classification number: F01D17/02 , F01D5/02 , F01D21/003 , F05D2220/32
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 and a stack nut threaded onto the engine shaft. The stack nut includes a castellated periphery. The sensor is configured to measure fluctuations in a magnetic field induced by the castellated periphery during rotation of the rotating assembly about the axis.
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公开(公告)号：US12104492B1
公开(公告)日：2024-10-01
申请号：US18372438
申请日：2023-09-25
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Brett Hartnagel , Brandon R. Snyder
CPC classification number: F01D11/24 , F01D17/02 , G01B21/16 , F05D2220/32 , F05D2240/55 , F05D2260/20 , F05D2260/80
Abstract: A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and an internally-cooled tip clearance system. The internally-cooled tip clearance system includes a sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.
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公开(公告)号：US12065936B2
公开(公告)日：2024-08-20
申请号：US17409943
申请日：2021-08-24
Applicant: GE Avio S.r.l.
Inventor： Cristian Lizzer , Maciej Slawinski , Wojciech Lukasz Staszynski , Jan Biskupski
CPC classification number: F01D17/02 , F01D9/041 , F05D2220/323 , F05D2240/12 , F05D2260/80
Abstract: An inter-turbine duct is positioned between a high pressure turbine and a low pressure turbine of a gas turbine engine. The inter-turbine duct includes an inner annular wall and an outer annular wall spaced apart from the inner annular wall along a radial direction to define an annular flow passage. The inter-turbine duct includes a plurality of circumferentially spaced vanes positioned within the flow passage and at least one temperature probe is positioned upstream of the vanes at a circumferential location that is between thirty and seventy percent of a circumferential distance between the leading edges of adjacent vanes.
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公开(公告)号：US20240167887A1
公开(公告)日：2024-05-23
申请号：US17992101
申请日：2022-11-22
Applicant: Raytheon Technologies Corporation
Inventor： Paul F. Croteau , Andrew A. Consiglio , Kevin Rivera , Otto Gregory
CPC classification number: G01K1/14 , F01D17/02 , F02C7/00 , G01K7/02 , G01K7/16 , F05D2220/32 , F05D2260/80
Abstract: The present disclosure provides for electrical connectivity to high temperature film sensor devices (e.g., temperature sensor devices). More particularly, the present disclosure provides for high temperature, thin film sensor devices (e.g., temperature sensor devices) having connection of wires and cabling from the cold side to the thin film sensor on the hot side. The disclosure provides assemblies and methods for that electrical connection to the leads or traces of the thin film sensor device (e.g., thin film temperature sensor device such as a thermocouple or a resistance temperature detector device) at the hot-cold barrier that exists in high temperature components (e.g., high temperature components in aero turbine engine applications). The assemblies and methods of the disclosure can be applied to any thin film device (e.g., sensor devices, such as, for example, strain gauges, heat flux sensors, etc.) that can be applied to the surface of a high temperature component.
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公开(公告)号：US20240060426A1
公开(公告)日：2024-02-22
申请号：US17892799
申请日：2022-08-22
Applicant: Pratt & Whitney Canada Corp.
Inventor： Martin Drolet
IPC: F01D17/02
CPC classification number: F01D17/02 , F05D2220/323 , F05D2260/80
Abstract: A system for a gas turbine engine includes an engine control system. The engine control system includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to: obtain a current engine installation configuration for the gas turbine engine, determine a normalized value of the engine parameter for an uninstalled gas turbine engine based on the current engine installation configuration and one or more of a normalized engine power (SHPN) of the gas turbine engine, an airspeed, or an altitude, determine a fully deteriorated engine (FDE) value of the engine parameter using the normalized value of the engine parameter, determine a current value of the engine parameter for the gas turbine engine, and determine the engine operating margin for the engine parameter based on the FDE value of the engine parameter and the current value of the engine parameter.
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Patent Agency Ranking
公开(公告)号：US20240026838A1
公开(公告)日：2024-01-25
申请号：US18456628
申请日：2023-08-28
Applicant: ICE Thermal Harvesting, LLC
Inventor： Adrian Benjamin Bodishbaugh , Carrie Jeanne Murtland
IPC: F02G1/055 , F02G1/05 , F02G5/04 , F01K23/02 , F01K25/08 , F01D17/02 , F01D19/00 , F01D21/00 , F24T50/00 , F03G4/00
CPC classification number: F02G1/055 , F02G1/05 , F02G5/04 , F01K23/02 , F01K25/08 , F01D17/02 , F01D19/00 , F01D21/00 , F24T50/00 , F03G4/00 , F02G2280/50 , F02G2256/00 , F02G2275/00 , F02G2280/20 , F03G4/035
Abstract: Systems and generating power in an organic Rankine cycle (ORC) operation to supply electrical power. In embodiments, an inlet temperature of a flow of gas from a source to an ORC unit may be determined. The source may connect to a main pipeline. The main pipeline may connect to a supply pipeline. The supply pipeline may connect to the ORC unit thereby to allow gas to flow from the source to the ORC unit. Heat from the flow of gas may cause the ORC unit to generate electrical power. The outlet temperature of the flow of the gas from the ORC unit to a return pipe may be determined. A bypass valve, positioned on a bypass pipeline connecting the supply pipeline to the return pipeline, may be adjusted to a position sufficient to maintain temperature of the flow of gas above a threshold based on the inlet and outlet temperature.
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公开(公告)号：US10060830B2
公开(公告)日：2018-08-28
申请号：US14662404
申请日：2015-03-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Arthur W. Utay
CPC classification number: G01M15/14 , F01D17/02 , F01D21/003 , F05D2260/80 , G01N21/35 , G01N25/72
Abstract: The present disclosure relates generally to a method of operating an inspection system, including a sensor and heating element operably coupled to a control module, to determine in-situ a coating integrity for a turbomachinery component within a turbomachinery system, the method comprising the steps of: placing the sensor and heating element at a distance from the desired turbomachinery component to be examine, operating the heating element for a predetermined amount of time, operating the sensor to detect an output from a surface of the turbomachinery component, and operating the control module to compare the output with at least one integrity parameter.
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公开(公告)号：US20180156694A1
公开(公告)日：2018-06-07
申请号：US15366714
申请日：2016-12-01
Applicant: General Electric Company
Inventor： Andrew Joseph Colletti , Bryan Joseph Germann , Gregory Lee Hovis
CPC classification number: G01M15/14 , F01D17/02 , G01M5/0025 , G01M5/0091 , G01M11/081
Abstract: This disclosure provides systems, components, and methods for visual creep inspection of rotating components, such as those in a gas turbine. A component is provided with an external surface and an axis of rotation. The external surface has a circumference and a plurality of three dimensional reference marks forming a reference pattern along the circumference. An optical data capture device generates a data signal based on the plurality of three dimensional reference marks. A data analysis system processes the data signal to calculate a deviation in spacing of the reference pattern along the circumference and determines a strain or creep measurement.
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公开(公告)号：US20180156654A1
公开(公告)日：2018-06-07
申请号：US15577235
申请日：2016-05-27
Applicant: Safran Aircraft Engines
Inventor： Eloïse Pauline Roux
Abstract: The oil level sensor is associated with a tank containing oil and comprises a float movable along guide means and which can float on the oil of the tank, so as to move with the oil level, a permanent magnet movable with the float, and an electronic card provided with magnetic switches sensitive to said magnet. The guide means of the spherical float are positioned about the float and the contacts thereof with said float are limited to three substantially linear zones.
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公开(公告)号：US20180156058A1
公开(公告)日：2018-06-07
申请号：US15814089
申请日：2017-11-15
Applicant: Hamilton Sundstrand Corporation
Inventor： Gregory Di Vincenzo , Francis P. Marocchini , Bhupindar Singh
CPC classification number: F01D17/02 , F01D17/14 , F01D17/20 , F01D21/003
Abstract: A measuring system for sensing vane positions that comprises a turbine, a target, and a sensor. The turbine includes a plurality of articulating vanes, with each vane being coupled to a sync ring that is configured to position the plurality of articulating vanes in accordance with a degree of rotation by the sync ring. The target is coupled to a first position of the turbine within a first region that is associated with a first vane of the plurality of articulating vanes. The sensor is coupled via a bracket to a second position of the turbine within the first region. The sensor is configured to detect an orientation of the target that corresponds to a vane position of the first vane.
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