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公开(公告)号：US20240352872A1
公开(公告)日：2024-10-24
申请号：US18304037
申请日：2023-04-20
摘要： An example system includes one or more heaters configured and positioned to add thermal energy to one or more portions of a gas turbine engine after the gas turbine engine was in operation, wherein the thermal energy minimizes or prevents undesired contact or seizing of a rotor of the gas turbine engine with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The system further includes a controller configured to control operation of the one or more heaters.
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公开(公告)号：US12116929B2
公开(公告)日：2024-10-15
申请号：US17578795
申请日：2022-01-19
CPC分类号： F02C6/08 , B64D13/06 , F02C9/00 , F02C9/18 , F02K3/04 , B64D2013/0603 , B64D2013/0607 , B64D2013/0618 , B64D2013/0648 , F05D2220/32 , F05D2220/76
摘要： A gas turbine engine includes a turbomachine, the turbomachine defining a core flow therethrough during operation. A first heat exchange assembly is in fluid communication with the turbomachine for receiving a first bleed flow from the turbomachine. A second heat exchange assembly is in fluid communication with the turbomachine for receiving a second bleed flow from the turbomachine. A first flow outlet is provided for receiving the first bleed flow from the first heat exchange assembly and providing the first bleed flow to a first aircraft flow assembly. A second flow outlet is provided for receiving the second bleed flow and providing the second bleed flow from the second heat exchange assembly to a second aircraft flow assembly.
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公开(公告)号：US12060838B2
公开(公告)日：2024-08-13
申请号：US18099490
申请日：2023-01-20
申请人： ROLLS-ROYCE PLC
发明人： Peter Swann , David M Beaven , Craig W Bemment , Alastair G Hobday , Benjamin J Keeler , Christopher P Madden , Martin K Yates
IPC分类号： G01N21/33 , B64D27/10 , B64D47/00 , F02C9/00 , G01N21/3577 , G01N21/64 , G01N33/28 , B64D37/00 , G01N21/35
CPC分类号： F02C9/00 , B64D27/10 , B64D47/00 , G01N21/33 , G01N21/3577 , G01N21/64 , G01N33/287 , B64D37/00 , G01N2021/3595
摘要： A method of generating a maintenance schedule for an aircraft including one or more gas turbine engines powered by an aviation fuel. The method includes: determining one or more fuel characteristics of the fuel; and generating a maintenance schedule according to the one or more fuel characteristics. Also disclosed is a method of maintaining an aircraft, a maintenance schedule generation system and an aircraft.
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公开(公告)号：US12037939B2
公开(公告)日：2024-07-16
申请号：US17657358
申请日：2022-03-30
申请人： ZeroAvia, Ltd.
发明人： Ritish Tejpal
摘要： A system and method for dynamic optimization of system efficiency for an integrated hydrogen-electric engine is disclosed. The system includes an elongated shaft of an integrated hydrogen-electric engine and a plurality of motors to drive the elongated shaft of the integrated hydrogen-electric engine. The system also includes at least one sensor to monitor a first torque of each motor of the plurality of motors and a computer with a memory and one or more processors. The one or more processors receive from the sensor, a first set of torque data for the first torque of each motor of the plurality of motors, utilize the first set of torque data to determine an overall efficiency of the plurality of motors, and selectively idle at least one motor of the plurality of motors based on a result of the determination.
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公开(公告)号：US20240229724A1
公开(公告)日：2024-07-11
申请号：US18151939
申请日：2023-01-09
发明人： Liang Tang , Danbing Seto
IPC分类号： F02C9/00
CPC分类号： F02C9/00 , F05D2260/80 , F05D2270/71 , F05D2270/802
摘要： 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.
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公开(公告)号：US20240218836A1
公开(公告)日：2024-07-04
申请号：US18089845
申请日：2022-12-28
IPC分类号： F02C9/00 , B64D13/06 , G06F1/3206 , G06F1/329
CPC分类号： F02C9/00 , B64D13/06 , G06F1/3206 , G06F1/329 , B64D2013/0618 , F05D2220/323 , F05D2260/81 , F05D2270/335 , F05D2270/44
摘要： An integrated system and methods therefore are provided. An integrated system has individual power and/or thermal systems and a coordinated control system. The coordinated control system receives mission demands and priorities from an upstream system. The coordinated control system also receives a status and a prediction from each individual system, such as an individual system's operating mode status and its capability margin. The coordinated control system performs a conflict of interest check and generates a relative status for each individual system based on the status and predictions associated with the individual systems. The coordinated control system determines an operating mode and an allowed demand for each individual system based on the relative statuses and the mission demands and priorities. The coordinated control system outputs the operating modes to the individual systems and maps the allowed demands to individual system demands. The individual system demands are output to the individual systems.
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公开(公告)号：US11867128B2
公开(公告)日：2024-01-09
申请号：US16959835
申请日：2019-01-04
发明人： Cedrik Djelassi
CPC分类号： F02C9/00 , H03H21/0025 , F05D2270/122 , F05D2270/304 , F05D2270/71
摘要： The invention relates to a method for filtering an input signal (3b, 4b, 5b) relative to a physical variable of a turbine engine (9), the input signal being digitised, the method implementing frequency filtering of said signal in a computer (6) of a control system (7) of said turbine engine (9), said signal being provided at the input of the computer, a digital derivative of said signal being intended for being used by the control system (7), characterised in that it involves: —detecting an amplitude variation of said variable on said input signal, by a step of generating a second derivative signal (S) of the input signal and a step of comparing a value of the second derivative value of the input signal with at least one predetermined threshold (S1 . . . Sn); and —adapting the frequency filtering of said input signal as a function of the detected amplitude variation of said variable, by a step of controlling a controlled filter (PB11) capable of applying frequency filtering to the input signal, so that the controlled filter applies or does not apply the frequency filtering as a function of a result of the comparison step.
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公开(公告)号：US11835944B2
公开(公告)日：2023-12-05
申请号：US17056240
申请日：2019-06-24
发明人： Koji Imakita
IPC分类号： G05B23/02 , G06Q10/04 , G06Q50/06 , G06Q30/0283 , F02C9/00
CPC分类号： G05B23/02 , F02C9/00 , G05B23/0294 , G06Q10/04 , G06Q30/0283 , G06Q50/06
摘要： Provided is an upgrade evaluation device for calculating cost in relation to the introduction effects of an upgrade menu. The present invention has: a performance data acquisition step for acquiring the performance data of an apparatus; and an effect calculation step for calculating, on the basis of the performance data, introduction effects based on a difference in performance when an improvement function for improving the performance of the apparatus is introduced and when the improvement function is not introduced; the introduction effects being calculated for each of a plurality of points in time in a prescribed period in the effect calculation step. There may also be calculated a cost exchanged between an improvement-function-supply side and the supplied side, the cost being based on the introduction effects calculated in the effect calculation step.
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公开(公告)号：US20230374945A1
公开(公告)日：2023-11-23
申请号：US18366129
申请日：2023-08-07
申请人： RTX Corporation
CPC分类号： F02C9/00 , G06F8/65 , H04W12/06 , F05D2270/44 , F05D2270/54
摘要： A communication adapter of a gas turbine engine of an aircraft includes a communication interface configured to wirelessly communicate with an offboard system and to communicate with an engine control of the gas turbine engine. The communication adapter also includes a memory system and processing circuitry configured to receive one or more configuration items from the offboard system, apply a cryptographic algorithm using one or more parameters received and cryptographic information to decrypt the one or more configuration items, wherein the cryptographic information includes a combination of received cryptographic information and previously stored cryptographic information, and transfer the one or more configuration items to the engine control after applying the cryptographic algorithm.
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公开(公告)号：US11754003B2
公开(公告)日：2023-09-12
申请号：US17232797
申请日：2021-04-16
申请人： PowerPHASE LLC
CPC分类号： F02C9/50 , F02C3/30 , F02C9/00 , F05D2260/99 , F05D2270/083 , F05D2270/30 , F05D2270/303
摘要： Systems and methods to control gas turbine firing temperatures during air injection. A method of achieving a desired firing temperature of a gas turbine engine during air injection comprises injecting compressed air into the gas turbine engine using an external source. The external source includes a compressor and a recuperator. The method comprises using a controller of the gas turbine engine to: (a) determine an air injection exhaust bias gain using an inlet temperature of the gas turbine engine; (b) calculate, based on the determined air injection exhaust bias gain and a flow rate of the injected compressed air, an air injection exhaust curve bias; and (c) change a fuel flow of the gas turbine engine by adding the air injection exhaust curve bias to an existing exhaust curve of the gas turbine engine to thereby achieve the desired firing temperature during air injection.
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