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    METHOD AND SYSTEM FOR OPERATING AN ENGINE TO PREVENT HIGH POWER ENGINE SURGES
    1.
    发明申请
    METHOD AND SYSTEM FOR OPERATING AN ENGINE TO PREVENT HIGH POWER ENGINE SURGES 有权

    公开(公告)号：US20220372920A1

    公开(公告)日：2022-11-24

    申请号：US17324404

    申请日：2021-05-19

    申请人： Pratt & Whitney Canada Corp.

    发明人： Martin Drolet ,  Yves Cloutier

    IPC分类号： F02C9/28 ,  F02C7/36

    摘要： Methods and systems for operating an aircraft engine having a compressor are described. The method comprises determining, based on actual operating parameters of the aircraft engine, a compressor mass flow limit for an aerodynamic stability of the aircraft engine; determining an actual compressor mass flow of the compressor of the aircraft engine, wherein the actual compressor mass flow is based on measured values of the aircraft engine; comparing the actual compressor mass flow to the compressor mass flow limit; and governing operation of the aircraft engine to cause an alternative compressor mass flow when the actual compressor mass flow reaches or is anticipated to reach the compressor mass flow limit.

    Method and system for determining aircraft engine inlet total pressure
    2.
    发明授权
    Method and system for determining aircraft engine inlet total pressure 有权

    公开(公告)号：US12071902B2

    公开(公告)日：2024-08-27

    申请号：US18474333

    申请日：2023-09-26

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Yves Cloutier

    IPC分类号： F02C9/00

    CPC分类号： F02C9/00 ,  F05D2220/323 ,  F05D2270/3011

    摘要： A method of determining an inlet total air pressure includes determining a first parameter indicative of a first inlet total air pressure. The method includes executing a sequence that includes: determining a mass air flow passing through the air inlet based on the first parameter, determining a Mach number of air passing through the air inlet based on the mass air flow, determining a static air pressure at the air inlet, determining an air pressure ratio based on the Mach number, generating a subsequent parameter indicative of the revised inlet total air pressure based on the air pressure ratio and the static air pressure, and substituting the subsequent parameter for the first parameter. The method includes executing at least one additional instance of the sequence with the subsequent parameter, and outputting the subsequent parameter as the inlet total air pressure.

    Method and system for determining an engine temperature
    3.
    发明授权
    Method and system for determining an engine temperature 有权

    公开(公告)号：US11898503B2

    公开(公告)日：2024-02-13

    申请号：US18070728

    申请日：2022-11-29

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Yves Cloutier

    IPC分类号： F02C9/28

    CPC分类号： F02C9/28 ,  F05D2240/35 ,  F05D2270/301 ,  F05D2270/303

    摘要： Methods and systems for determining an engine temperature for a gas turbine engine are provided. An estimated combustor temperature is determined based on at least one operating condition of the gas turbine engine and an estimated vane mass flow. A corrected vane mass flow is determined based on the estimated combustor temperature, the estimated vane mass flow, and a combustor pressure. The corrected vane mass flow is compared to a reference vane mass flow to obtain the mass flow correction factor. When a condition associated with the mass flow correction factor is not satisfied, the estimated combustor temperature is adjusted based on the mass flow correction factor to produce an adjusted combustor temperature; and the mass flow correction factor is updated based on the adjusted combustor temperature. When the condition associated with the mass flow correction factor is satisfied, the estimated combustor temperature is assigned as the engine temperature.

    Output power management for engines
    4.
    发明授权
    Output power management for engines 有权

    公开(公告)号：US11628945B2

    公开(公告)日：2023-04-18

    申请号：US17468906

    申请日：2021-09-08

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Philippe-Andre Tetrault ,  Yves Cloutier

    IPC分类号： B64D31/06 ,  F02C9/00 ,  B64F5/60

    摘要： Methods and systems for operating an engine are provided. An engine core temperature is monitored. When the engine core temperature is below an engine thermal limit adjusted for a level of deterioration of the engine, an output power of the engine is set in accordance with a reference power based on non-thermal limits of the engine. When the engine core temperature is near or above the engine thermal limit adjusted for the level of deterioration of the engine, the output power of the engine is set to a value lower than the reference power based on non-thermal limits of the engine to reduce the engine core temperature.

    Method and system for determining an engine temperature
    5.
    发明授权
    Method and system for determining an engine temperature 有权

    公开(公告)号：US11542875B2

    公开(公告)日：2023-01-03

    申请号：US16906637

    申请日：2020-06-19

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Yves Cloutier

    IPC分类号： F02C9/28

    摘要： Methods and systems for determining an engine temperature for a gas turbine engine are provided. An estimated combustor temperature is determined based on at least one operating condition of the gas turbine engine and an estimated vane mass flow. A corrected vane mass flow is determined based on the estimated combustor temperature, the estimated vane mass flow, and a combustor pressure. The corrected vane mass flow is compared to a reference vane mass flow to obtain the mass flow correction factor. When a condition associated with the mass flow correction factor is not satisfied, the estimated combustor temperature is adjusted based on the mass flow correction factor to produce an adjusted combustor temperature; and the mass flow correction factor is updated based on the adjusted combustor temperature. When the condition associated with the mass flow correction factor is satisfied, the estimated combustor temperature is assigned as the engine temperature.

    Method and system for determining aircraft engine inlet total pressure
    7.
    发明授权
    Method and system for determining aircraft engine inlet total pressure 有权

    公开(公告)号：US11859561B2

    公开(公告)日：2024-01-02

    申请号：US17643072

    申请日：2021-12-07

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Yves Cloutier

    IPC分类号： F02C9/00

    CPC分类号： F02C9/00 ,  F05D2220/323 ,  F05D2270/3011

    摘要： A method of determining an inlet total air pressure includes determining a first parameter indicative of a first inlet total air pressure. The method includes executing a sequence that includes: determining a mass air flow passing through the air inlet based on the first parameter, determining a Mach number of air passing through the air inlet based on the mass air flow, determining a static air pressure at the air inlet, determining an air pressure ratio based on the Mach number, generating a subsequent parameter indicative of the revised inlet total air pressure based on the air pressure ratio and the static air pressure, and substituting the subsequent parameter for the first parameter. The method includes executing at least one additional instance of the sequence with the subsequent parameter, and outputting the subsequent parameter as the inlet total air pressure.

    Inter-compressor cross-over pipe heat exchanger
    9.
    发明授权
    Inter-compressor cross-over pipe heat exchanger 有权

    公开(公告)号：US11333173B2

    公开(公告)日：2022-05-17

    申请号：US16406659

    申请日：2019-05-08

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Jason Nichols ,  Yves Cloutier

    IPC分类号： F04D29/58 ,  F01D9/06 ,  F04D17/12

    摘要： The gas turbine engine described includes a first centrifugal compressor, a second centrifugal compressor, and intercompressor pipes extending therebetween. The intercompressor pipes fluidly interconnect an exit of a first impeller of the first centrifugal compressor and an inlet of a second impeller of the second centrifugal compressor. The intercompressor pipes have heat transfer structures on outer surfaces thereof to increase convective heat transfer.