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    ENHANCED ENGINE MODEL FOR CONTROL AND HEALTH MONITORING
    1.
    发明公开
    ENHANCED ENGINE MODEL FOR CONTROL AND HEALTH MONITORING 审中-公开

    公开(公告)号：US20240229724A1

    公开(公告)日：2024-07-11

    申请号：US18151939

    申请日：2023-01-09

    Applicant: Raytheon Technologies Corporation

    Inventor： Liang Tang ,  Danbing Seto

    IPC: F02C9/00

    CPC classification number: F02C9/00 ,  F05D2260/80 ,  F05D2270/71 ,  F05D2270/802

    Abstract: An engine model calibration system includes a gas turbine engine, a sensor, a nominal engine estimation module for FD&I, and a self-tuning engine estimation module for engine parameter estimation. The nominal engine estimation module includes an open-loop nominal engine model configured to output estimated nominal engine parameters indicative of the one or more engine operating parameters, and selectively updates the open-loop nominal engine model based on one or more identified engine operating conditions. The engine model calibration system can perform calibration of a nominal engine model and a self-tuning engine model as they are used for FD&I and engine parameter estimation. The self-calibrating dynamic model also can separate the long-term tuning parameters and the short-term tuning parameters from one another so that the self-tuning capability for the self-tuning engine model is not compromised or diminished as the engine deteriorates.

    OIL DEBRIS MONITOR TO DETECT MECHANICAL FAILURES IN HIGH NOISE ENVIRONMENTS
    2.
    发明申请
    OIL DEBRIS MONITOR TO DETECT MECHANICAL FAILURES IN HIGH NOISE ENVIRONMENTS 有权

    公开(公告)号：US20220155257A1

    公开(公告)日：2022-05-19

    申请号：US17666009

    申请日：2022-02-07

    Applicant: Raytheon Technologies Corporation

    Inventor： Edward Thomas Rocco ,  Danbing Seto

    IPC: G01N27/74 ,  G01N33/28

    Abstract: A method to effectively utilize an oil debris monitor to provide advanced warning to mechanical system failures in a high noise system by adapting detection and annunciation algorithms to the background noise in a system that includes collecting I and Q channel data from a sensor; processing the I and Q channel data to both calculate a noise based (RMS adjusted) detection threshold and to identify a ferrous and nonferrous signal; processing the ferrous and nonferrous signals to determine signal peaks above the RMS adjusted detection threshold; adjusting a detection threshold if more signal peaks observed than allowable particles in a given time window; transmitting the detection threshold previously determined to particle detection, rate limit adjustment, detectability algorithms, and estimated mass loss accumulation.

    METHOD AND APPARATUS FOR FAULT DETECTION IN A GAS TURBINE ENGINE AND AN ENGINE HEALTH MONITORING SYSTEM
    4.
    发明公开
    METHOD AND APPARATUS FOR FAULT DETECTION IN A GAS TURBINE ENGINE AND AN ENGINE HEALTH MONITORING SYSTEM 审中-公开

    公开(公告)号：US20230349300A1

    公开(公告)日：2023-11-02

    申请号：US17733396

    申请日：2022-04-29

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Danbing Seto ,  Edward Thomas Rocco

    IPC: F01D21/00

    CPC classification number: F01D21/003 ,  F05D2260/80 ,  F05D2270/334 ,  F05D2270/709 ,  F05D2270/803 ,  F05D2270/807

    Abstract: A method for fault identification for a gas turbine engine includes receiving sensor data from at least one health monitoring sensor of a health monitoring system for a gas turbine engine; utilizing a pre-filter to filter the sensor data and obtain filtered data based on a plurality of signatures of fault conditions of the health monitoring system and the gas turbine engine; utilizing at least one transfer function to extract features from the filtered sensor data based on the plurality of signatures; utilizing a machine learning technique to analyze the extracted features, and determine whether any of the extracted features are indicative of a fault condition in the health monitoring system or the gas turbine engine; and based on the analysis indicating the presence of a fault condition, providing a fault detection notification. A health monitoring system for a gas turbine engine is also disclosed.

    PROPULSOR BLADE IMAGING ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM
    6.
    发明公开
    PROPULSOR BLADE IMAGING ASSEMBLY FOR AN AIRCRAFT PROPULSION SYSTEM 审中-公开

    公开(公告)号：US20240352869A1

    公开(公告)日：2024-10-24

    申请号：US18137756

    申请日：2023-04-21

    Applicant: Raytheon Technologies Corporation

    Inventor： Scott Goyette ,  Janet Shaw ,  Gregory S. Hagen ,  David L. Lincoln ,  Zaffir A. Chaudhry ,  Danbing Seto

    IPC: B64F5/60 ,  B64D27/10 ,  F01D21/00 ,  H04N23/90

    CPC classification number: F01D21/003 ,  B64D27/10 ,  H04N23/90 ,  F05D2260/83

    Abstract: An assembly for an aircraft propulsion system includes a propulsor section for the aircraft propulsion system, a plurality of imaging devices, and a controller. The propulsor section includes a propulsor. The propulsor includes a plurality of propulsor blades. The plurality of imaging devices are mounted in the propulsor section. Each imaging device includes a camera. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to: control the camera of each imaging device of the plurality of imaging devices to capture image data of each propulsor blade of the plurality of propulsor blades and identify a presence or an absence of damage for each propulsor blade of the plurality of propulsor blades using the image data from the camera of two or more imaging devices of the plurality of imaging devices.

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