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    METHOD AND APPARATUS FOR MACHINE LEARNING BASED INLET DEBRIS MONITORING
    3.
    发明公开
    METHOD AND APPARATUS FOR MACHINE LEARNING BASED INLET DEBRIS MONITORING 审中-公开

    公开(公告)号：EP4266140A1

    公开(公告)日：2023-10-25

    申请号：EP23164835.3

    申请日：2023-03-28

    申请人： Raytheon Technologies Corporation

    发明人： LEE, Jeremiah C. ,  GAVRILOVSKI, Alek ,  HERATH, Parakrama ,  McMENAMIN, Daniel

    IPC分类号： G05B23/02

    摘要： A method of inlet debris monitoring for a gas turbine engine includes: obtaining a data set of electrostatic charge data from an output signal of at least one electrostatic sensor, the output signal indicative of an electrostatic charge in a nacelle of a particular gas turbine engine, the data set having initial dimensions corresponding to a window size and a sampling frequency of the output signal; utilizing a dimensional reduction technique to obtain a first set of basis vectors that represent the data set in a reduced dimensional space that is reduced with respect to the initial dimensions; utilizing the first set of basis vectors or a second set of reference basis vectors, which are based on historical electrostatic charge data for one or more reference gas turbine engines, to project the data set onto the reduced dimensional space and obtain a reduced dimensional representation of the data set; utilizing machine learning to determine whether the reduced dimensional representation of the data set indicates foreign object debris in the particular gas turbine engine; and based on the determination indicating detection of foreign object debris, providing a foreign object debris notification. A system is also provided.

    NON-CONTACT SEAL WITH SEAL DEVICE AXIAL LOCATOR(S)
    5.
    发明公开
    NON-CONTACT SEAL WITH SEAL DEVICE AXIAL LOCATOR(S) 审中-公开

    公开(公告)号：EP4257852A1

    公开(公告)日：2023-10-11

    申请号：EP23155672.1

    申请日：2023-02-08

    申请人： Raytheon Technologies Corporation

    发明人： CHUONG, Conway ,  WILSON, Ross C.

    IPC分类号： F16J15/44 ,  F01D11/02

    摘要： An assembly (20) is provided for rotational equipment. This assembly (20) includes a seal device (38), a ring structure (48) and a fastener (122). The seal device (38) includes a plurality of seal shoes (61), a seal base (60) and a plurality of spring elements. The seal shoes (61) are arranged around a centerline (22) in an annular array. The seal shoes (61) include a first seal shoe (61). The seal base (60) circumscribes the annular array. The spring elements include a first spring element. The first spring element connects and extends between the first seal shoe (61) and the base (60). The ring structure (48) is axially adjacent the seal device (38). The ring structure (48) includes a fastener aperture (124) extending axially through the ring structure (48). The fastener (122) is mated with the fastener aperture (124) and abutted axially against the seal device (38).

    INSPECTION DATA MANAGEMENT SYSTEMS AND METHODS
    6.
    发明公开
    INSPECTION DATA MANAGEMENT SYSTEMS AND METHODS 审中-公开

    公开(公告)号：EP4257800A1

    公开(公告)日：2023-10-11

    申请号：EP23166863.3

    申请日：2023-04-05

    申请人： Raytheon Technologies Corporation

    发明人： SAWYERS-ABBOTT, Nigel D. ,  PHAN, Uyen ,  KERNOZICKY, Garrett

    IPC分类号： F01D5/00 ,  B23P6/00 ,  F01D5/34

    摘要： A method can comprise: receiving, via a processor (286), scanner data from an inspection system (285) for a bladed rotor (100), the scanner data including a point cloud defining an inspected bladed rotor, the scanner data including a first data size; generating, via the processor (286), a data set including section files spaced apart along a span of a blade (103) based on the point cloud; determining, via the processor (286), a defect (140) on the blade (103) of the inspected bladed rotor based on the data set; and determining whether the defect (140) meets serviceable limits.

    BLADED ROTOR INSPECTION, ANALYSIS AND REPAIR SYSTEMS AND METHODS
    7.
    发明公开
    BLADED ROTOR INSPECTION, ANALYSIS AND REPAIR SYSTEMS AND METHODS 审中-公开

    公开(公告)号：EP4257799A1

    公开(公告)日：2023-10-11

    申请号：EP23164852.8

    申请日：2023-03-28

    申请人： Raytheon Technologies Corporation

    发明人： ROBERTS, Lawrence P. ,  VANDENBOSCH, Ross A. ,  PHAN, Uyen ,  PRIHAR, Ron I. ,  KERNOZICKY, Garrett

    IPC分类号： F01D5/00 ,  G06F30/23 ,  F01D5/34

    摘要： A method can comprise: determining, via a processor (286, 602, 292), whether serviceable limits are met for an inspected bladed rotor (100); generating, via the processor (286, 602, 292), a three-dimensional model including a repair blend profile for a defect in response to determining the inspected bladed rotor (100) does not meet the serviceable limits; performing, via the processor (286, 602, 292), a first set of simulations on the three-dimensional model; determining, via the processor (286, 602, 292), whether a first set of results of the first set of simulations meet an experience based criteria; performing, via the processor (286, 602, 292), a second set of simulations on the three-dimensional model in response to a first result in the first set of results not meeting a first objective parameter in the experience based criteria; and determining, via the processor (286, 602, 292), whether a second set of results and the first set of results meet a deterministic criteria.

    ADJUSTABLE PRIMARY AND SUPPLEMENTAL POWER UNITS
    9.
    发明公开
    ADJUSTABLE PRIMARY AND SUPPLEMENTAL POWER UNITS 审中-公开

    公开(公告)号：EP4253743A1

    公开(公告)日：2023-10-04

    申请号：EP23154040.2

    申请日：2023-01-30

    申请人： Raytheon Technologies Corporation

    发明人： MacDONALD, Malcolm P. ,  TAYLOR, Stephen H.

    IPC分类号： F02C6/18

    摘要： A propulsion system (18) for an aircraft includes a core flow path (C) in communication with a compressor section (24), combustor section (26) and a turbine section (28). A first bottoming cycle system (62) includes a bottoming working fluid flow in thermal communication with a high energy exhaust gas flow that is generated by the combustion section (24). The first bottoming cycle system (62) is configured to recover power from the high energy exhaust gas flow in a first engine operating condition and in a second engine operating condition. A second bottoming cycle system (64) is configured to recover power from the high energy exhaust gas flow in the first engine operating condition and not to recover power in a second engine operating condition.

    EFFICIENT TURBINE ENGINE USING INTEGRATED AMMONIA FUEL PROCESSING
    10.
    发明公开
    EFFICIENT TURBINE ENGINE USING INTEGRATED AMMONIA FUEL PROCESSING 审中-公开

    公开(公告)号：EP4253739A1

    公开(公告)日：2023-10-04

    申请号：EP23154075.8

    申请日：2023-01-30

    申请人： Raytheon Technologies Corporation

    发明人： SMITH, Lance L. ,  LEI MA, David ,  STAUBACH, Joseph B. ,  HOLLEY, Brian M. ,  EMERSON, Sean C.

    IPC分类号： F02C3/22 ,  F02C7/143 ,  F02C7/18 ,  F02C7/224

    摘要： A gas turbine engine (20) includes a core engine that includes a core flow path (C) where air is compressed in a compressor section (22), communicated to a combustor section (24), mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow (46) that is expanded through a turbine section (26). The turbine section (26) is mechanically coupled to drive the compressor section (22). An ammonia flow path communicates an ammonia flow (42) to the combustor section (24). A cracking device (48) is disposed in the ammonia flow path. The cracking device (48) is configured to decompose the ammonia flow (42) into a fuel flow (58) containing hydrogen (H2). At least one heat exchanger (62, 64, 50) is upstream of the cracking device (48) that provides thermal communication between the ammonia flow (42) and a working fluid flow (44, 60, 66) such that the ammonia fluid flow accepts thermal energy from the working fluid flow (44, 60, 66).