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    Concentric introduction of the waste-gate mass flow into a flow-optimized axial diffusor
    2.
    发明授权
    Concentric introduction of the waste-gate mass flow into a flow-optimized axial diffusor 有权

    公开(公告)号：US11879389B2

    公开(公告)日：2024-01-23

    申请号：US17641357

    申请日：2020-09-09

    申请人： Turbo Systems Switzerland Ltd.

    发明人： Christoph Mathey ,  Stephan Senn

    IPC分类号： F02C6/12 ,  F01D25/30 ,  F02C6/02

    CPC分类号： F02C6/02 ,  F01D25/30 ,  F05D2220/40

    摘要： An exhaust turbine includes a turbine wheel having a plurality of rotor blades, an exhaust outlet where the exhaust outlet is arranged downstream of the rotor blades and is delimited radial to the outside by an axial turbine diffusor. An exhaust mass flow can be output in an axial flow direction by the exhaust outlet duct and the axial turbine diffusor opens downstream, radially to the outside at a non-constant diffusor-opening angle, such that at a first diffusor-opening angle deviates from a second diffusor-opening angle by at least 1°. The exhaust turbine further includes a waste gate duct, the outlet region of which opens into the diffusor or directly downstream of the diffusor into the exhaust outlet duct. The waste gate duct is designed to generate a substantially axial flow direction of a waste gate mass flow at the outlet region of the waste gate duct.

    Gas turbine engine with low-pressure compressor bypass
    3.
    发明授权
    Gas turbine engine with low-pressure compressor bypass 有权

    公开(公告)号：US11814969B2

    公开(公告)日：2023-11-14

    申请号：US17381446

    申请日：2021-07-21

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Daniel Coutu

    IPC分类号： F02C9/18 ,  F01D17/14 ,  F01D17/16 ,  F02C6/02 ,  F02C9/22

    CPC分类号： F01D17/145 ,  F01D17/162 ,  F02C6/02 ,  F02C9/18 ,  F02C9/22 ,  F05D2220/323 ,  F05D2260/606 ,  F05D2270/053 ,  F05D2270/335

    摘要： An aircraft engine, has: a low-pressure compressor and a high-pressure compressor located downstream of the low-pressure compressor; a gaspath valve upstream of the high-pressure compressor, the gaspath valve movable between an open configuration and a closed configuration; and a bypass flow path having in flow series a bypass inlet, a bypass valve, and a bypass outlet, the bypass inlet fluidly communicating with the gaspath upstream of at least one stage of the low-pressure compressor, the bypass valve having an open configuration in which the bypass valve allows a bypass flow and a closed configuration in which the bypass valve blocks the bypass flow, the bypass outlet fluidly communicating with the bypass inlet via the bypass valve and with the gaspath at a location in the gaspath fluidly downstream of the gaspath valve, downstream of the low-pressure compressor, and upstream of the high-pressure compressor.

    System and method for exiting an asymmetric engine operating regime
    5.
    发明授权
    System and method for exiting an asymmetric engine operating regime 有权

    公开(公告)号：US11725597B2

    公开(公告)日：2023-08-15

    申请号：US16656764

    申请日：2019-10-18

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Patrick Manoukian

    IPC分类号： F02D29/02 ,  F02C6/02

    CPC分类号： F02D29/02 ,  F02C6/02 ,  F05D2220/323 ,  F05D2270/04 ,  F05D2270/13

    摘要： Methods and systems for operating an aircraft having two or more engines are described. The method comprises operating the two or more engines of the aircraft in an asymmetric operating regime, wherein a first of the engines is in an active mode to provide motive power to the aircraft and a second of the engines is in a standby mode to provide substantially no motive power to the aircraft, receiving a request to exit the asymmetric operating regime, the request having at least one parameter associated therewith, selecting one of a plurality of available exit protocols as a function of the at least one parameter, and applying the exit protocol by commanding the engines accordingly.

    MULTI-ENGINE SYSTEM AND POWER TRANSFER BETWEEN ENGINES THEREOF
    7.
    发明申请
    MULTI-ENGINE SYSTEM AND POWER TRANSFER BETWEEN ENGINES THEREOF 有权

    公开(公告)号：US20230034946A1

    公开(公告)日：2023-02-02

    申请号：US17390205

    申请日：2021-07-30

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Daniel COUTU

    IPC分类号： F02C7/32 ,  F02C6/02 ,  F01D15/10 ,  B64D27/10 ,  B64C27/12

    摘要： A multi-engine system for an aircraft, has: a first engine having a first output shaft, a first core shaft, and a first electric machine drivingly engaged by the first output shaft or the first core shaft; a second engine having a second output shaft, a second core shaft, and a second electric machine drivingly engaged to the second core shaft; a reduction gearbox drivingly engaged by the first output shaft and by the second output shaft for driving a common load; and a transmission path between the first engine and the second engine, the transmission path being independent from the reduction gearbox and being one or more of: a torque-transfer connection between the second core shaft and the first core shaft or the first output shaft via a coupling gearbox, and an electrical connection between the generator and the electric motor to transmit electrical power to the electric motor.

    Crossover cooling flow for multi-engine systems
    9.
    发明授权
    Crossover cooling flow for multi-engine systems 有权

    公开(公告)号：US11530646B2

    公开(公告)日：2022-12-20

    申请号：US17176803

    申请日：2021-02-16

    申请人： RAYTHEON TECHNOLOGIES CORPORATION

    发明人： Daniel Bernard Kupratis

    IPC分类号： F02C7/18 ,  F02C3/13 ,  F02C6/02

    摘要： A multi-engine system includes a first gas turbine engine that includes a first compressor and a first turbine. The multi-engine system may further include a second gas turbine engine that has a second compressor and a second turbine. Still further, the multi-engine system may include a first crossover cooling network configured to route a first crossover airflow from the first compressor of the first gas turbine engine to the second turbine of the second gas turbine engine and a second crossover cooling network configured to route a second crossover airflow from the second compressor of the second gas turbine engine to the first turbine of the first gas turbine engine.

    DEVICE FOR TEMPORARILY INCREASING TURBOMACHINE POWER
    10.
    发明申请
    DEVICE FOR TEMPORARILY INCREASING TURBOMACHINE POWER 有权

    公开(公告)号：US20210102491A1

    公开(公告)日：2021-04-08

    申请号：US16498273

    申请日：2018-03-27

    申请人： SAFRAN HELICOPTER ENGINES

    发明人： Frédéric POUSSE ,  Lionel NAPIAS ,  Laurent MINEL ,  Bertrand MOINE

    IPC分类号： F02C3/30 ,  F02C9/00 ,  F02C7/143 ,  F02C6/02 ,  B64D35/08

    摘要： A device for temporarily increasing power in order to increase the power from at least one first turbine engine and from at least one second turbine engine, the device including a tank of coolant liquid, a first injection circuit connected to the tank and leading to at least one injection nozzle configured to be installed upstream from the first turbine engine, a second injection circuit connected to the tank and leading to at least one injection nozzle configured to be installed upstream from the second turbine engine, each of the first and second injection circuits including at least one first valve and at least one second valve arranged upstream from said at least one first valve, and a bridge pipe connecting together the first injection circuit and the second injection circuit upstream from their respective first valves and downstream from their respective second valves.