1–11 von 11 Ergebnissen
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    GAS TURBINE ENGINE WITH LIFING CALCULATIONS BASED UPON ACTUAL USAGE

    Freier Zugriff
    SCHWARZ FREDERICK M / RIZO MARNIE A / HOUSTON DAVID P et al. | Europäisches Patentamt | 2019

    A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft

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      Gas turbine engine with lifing calculations based upon actual usage

      Freier Zugriff
      SCHWARZ FREDERICK M / RIZO MARNIE A / HOUSTON DAVID P et al. | Europäisches Patentamt | 2020

      A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft

       ...

      Gas turbine engine with lifing calculations based upon actual usage

      Freier Zugriff
      SCHWARZ FREDERICK M / RIZO MARNIE A / HOUSTON DAVID P et al. | Europäisches Patentamt | 2019

      A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft

       ...

    Propulsion system cooling control

    Freier Zugriff
    SCHWARZ FREDERICK M / WINTER MICHAEL | Europäisches Patentamt | 2022

    A propulsion system includes an electric fan propulsion motor with a plurality of propulsion motor windings. The propulsion system also

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      PROPULSION SYSTEM COOLING CONTROL

      Freier Zugriff
      SCHWARZ FREDERICK M / WINTER MICHAEL | Europäisches Patentamt | 2024

      A system for an aircraft (100) includes an engine bleed source (251) of a gas turbine engine (20). The system also includes a means for

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      PROPULSION SYSTEM COOLING CONTROL

      Freier Zugriff
      SCHWARZ FREDERICK M / WINTER MICHAEL | Europäisches Patentamt | 2022

    Hybrid electric aircraft system with distributed propulsion

    Freier Zugriff
    SCHWARZ FREDERICK M / BAIG ZUBAIR AHMED | Europäisches Patentamt | 2020

    A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to

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      HYBRID ELECTRIC AIRCRAFT SYSTEM WITH DISTRIBUTED PROPULSION

      Freier Zugriff
      SCHWARZ FREDERICK M / BAIG ZUBAIR AHMED | Europäisches Patentamt | 2019

      A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to

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    AIRCRAFT SYSTEM WITH DISTRIBUTED PROPULSION

    Freier Zugriff
    SCHWARZ FREDERICK M / SHERIDAN WILLIAM G | Europäisches Patentamt | 2019

    A propulsion system for an aircraft includes at least two gas turbine engines and at least one auxiliary propulsion fan. The at least

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      Aircraft system with distributed propulsion

      Freier Zugriff
      SCHWARZ FREDERICK M / SHERIDAN WILLIAM G | Europäisches Patentamt | 2021

      A propulsion system for an aircraft includes at least two gas turbine engines and at least one auxiliary propulsion fan. The at least

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    Aircraft hybrid propulsion fan drive gear system DC motors and generators

    Freier Zugriff
    KUPRATIS DANIEL BERNARD / SCHWARZ FREDERICK M / SHERIDAN WILLIAM G et al. | Europäisches Patentamt | 2021

    An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear

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      AIRCRAFT HYBRID PROPULSION FAN DRIVE GEAR SYSTEM DC MOTORS AND GENERATORS

      Freier Zugriff
      KUPRATIS DANIEL BERNARD / SCHWARZ FREDERICK M / SHERIDAN WILLIAM G et al. | Europäisches Patentamt | 2021

      An aircraft propulsion system is disclosed and includes a first gas turbine engine (20A) including a first input shaft (72) driving a

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      AIRCRAFT HYBRID PROPULSION FAN DRIVE GEAR SYSTEM DC MOTORS AND GENERATORS

      Freier Zugriff
      KUPRATIS DANIEL BERNARD / SCHWARZ FREDERICK M / SHERIDAN WILLIAM G et al. | Europäisches Patentamt | 2021

      An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear

       ...

      AIRCRAFT HYBRID PROPULSION FAN DRIVE GEAR SYSTEM DC MOTORS AND GENERATORS

      Freier Zugriff
      KUPRATIS DANIEL BERNARD / SCHWARZ FREDERICK M / SHERIDAN WILLIAM G et al. | Europäisches Patentamt | 2020

      An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear

       ...

      Aircraft hybrid propulsion fan drive gear system DC motors and generators

      Freier Zugriff
      KUPRATIS DANIEL BERNARD / SCHWARZ FREDERICK M / SHERIDAN WILLIAM G et al. | Europäisches Patentamt | 2023

      An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear

       ...

      AIRCRAFT HYBRID PROPULSION FAN DRIVE GEAR SYSTEM DC MOTORS AND GENERATORS

      Freier Zugriff
      KUPRATIS DANIEL BERNARD / SCHWARZ FREDERICK M / SHERIDAN WILLIAM G et al. | Europäisches Patentamt | 2023

      An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear

       ...

    HIGH COMPRESSOR BUILD CLEARANCE REDUCTION

    Freier Zugriff
    VIRTUE JR JOHN P / SAFTLER RISHON / SCHWARZ FREDERICK M | Europäisches Patentamt | 2018
    section of the gas turbine engine. The system also includes at least two bowed rotor management systems for the gas turbine engine to prevent ...

      High compressor build clearance reduction

      Freier Zugriff
      VIRTUE JR JOHN P / SAFTLER RISHON / SCHWARZ FREDERICK M | Europäisches Patentamt | 2019
      section of the gas turbine engine. The system also includes at least two bowed rotor management systems for the gas turbine engine to prevent ...

    Cryogenic cooling system for an aircraft

    Freier Zugriff
    SCHWARZ FREDERICK M / WINTER MICHAEL / LENTS CHARLES E et al. | Europäisches Patentamt | 2023

      CRYOGENIC COOLING SYSTEM FOR AN AIRCRAFT

      Freier Zugriff
      SCHWARZ FREDERICK M / WINTER MICHAEL / LENTS CHARLES E et al. | Europäisches Patentamt | 2023

      A gas turbine engine includes a compressor section and a turbine section operably coupled to the compressor section. The gas turbine

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      CRYOGENIC COOLING SYSTEM FOR AN AIRCRAFT

      Freier Zugriff
      SCHWARZ FREDERICK M / WINTER MICHAEL / LENTS CHARLES E et al. | Europäisches Patentamt | 2023
      operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the ...

    ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO

    Freier Zugriff
    SCHWARZ FREDERICK M / MALECKI ROBERT E | Europäisches Patentamt | 2019

    A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit

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      Elongated geared turbofan with high bypass ratio

      Freier Zugriff
      SCHWARZ FREDERICK M / MALECKI ROBERT E | Europäisches Patentamt | 2019

      A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit

       ...

      ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO

      Freier Zugriff
      SCHWARZ FREDERICK M / MALECKI ROBERT E | Europäisches Patentamt | 2022

      A propulsion system (20) includes a fan (100), a gear (112), a turbine (116) configured to drive the gear (112) to, in turn, drive the

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      Elongated geared turbofan with high bypass ratio

      Freier Zugriff
      SCHWARZ FREDERICK M / MALECKI ROBERT E | Europäisches Patentamt | 2022

      A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit

       ...

    Exhaust nozzle arrangement for geared turbofan

    Freier Zugriff
    SCHWARZ FREDERICK M / MALECKI ROBERT E | Europäisches Patentamt | 2019

    A propulsion system according to an example of the present disclosure includes, among other things, a geared architecture configured to

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      Exhaust nozzle arrangement for geared turbofan

      Freier Zugriff
      SCHWARZ FREDERICK M / MALECKI ROBERT E | Europäisches Patentamt | 2019

      A propulsion system according to an example of the present disclosure includes, among other things, a geared architecture configured to

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    Exhaust nozzle for an elongated gear turbofan with high bypass ratio

    Freier Zugriff
    SCHWARZ FREDERICK M / MALECKI ROBERT E | Europäisches Patentamt | 2019

    A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit

     ...

    Non-contact seal assembly for rotational equipment with linkage between adjacent rotors

    Freier Zugriff
    SCHWARZ FREDERICK M / ACKERMANN WILLIAM K | Europäisches Patentamt | 2020

    An assembly is provided for rotational equipment such as a gas turbine engine for an aircraft propulsion system. This assembly includes

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      NON-CONTACT SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT WITH LINKAGE BETWEEN ADJACENT ROTORS

      Freier Zugriff
      SCHWARZ FREDERICK M / ACKERMANN WILLIAM K | Europäisches Patentamt | 2017

      An assembly is provided for rotational equipment such as a gas turbine engine for an aircraft propulsion system. This assembly includes

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