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    AIRCRAFT ENGINE FUEL SYSTEM
    1.
    发明公开
    AIRCRAFT ENGINE FUEL SYSTEM 审中-公开

    公开(公告)号：US20240228055A9

    公开(公告)日：2024-07-11

    申请号：US18483106

    申请日：2023-10-09

    Applicant: ROLLS-ROYCE plc

    Inventor： Marko BACIC ,  John COULL

    IPC: B64D37/30 ,  B64D37/34 ,  F02C7/22

    CPC classification number: B64D37/30 ,  B64D37/34 ,  F02C7/22

    Abstract: An aircraft propulsion system fuel system comprises a fuel line configured to receive liquid hydrogen fuel from a fuel tank, a vaporizer configured to vaporize liquid hydrogen fuel from the fuel line to generate a supercritical or gaseous fuel, a main fuel pump configured to receive and to pump the gaseous or supercritical fuel from the vaporizer during operation of the propulsion system, and a heater provided downstream in fuel flow to the main fuel pump, and configured to raise the temperature of the gaseous or supercritical fuel to a propulsion system delivery temperature.

    VERTICAL TAKE-OFF AND LANDING AIRCRAFT
    2.
    发明申请
    VERTICAL TAKE-OFF AND LANDING AIRCRAFT 审中-公开

    公开(公告)号：US20200023963A1

    公开(公告)日：2020-01-23

    申请号：US16451734

    申请日：2019-06-25

    Applicant: ROLLS-ROYCE plc

    Inventor： Darren JAMES ,  Anmol A. MANOHAR ,  David FILLINGHAM ,  Marko BACIC

    IPC: B64C29/00 ,  B64D27/10

    Abstract: An aircraft defining longitudinal, lateral and vertical directions the aircraft comprising: a main wing and a tail, each being pivotable about the lateral direction (B); a plurality of main propellers mounted to the main wing, and configured to pivot with the main wing; at least one cruise propeller mounted to the tail, and configured to pivot with the tail; each main propeller being stowable from a deployed position to a stowed position; wherein each main propeller has a fixed pitch, and each cruise propeller has a variable pitch.

    AIRCRAFT COMPRISING A CABIN BLOWER SYSTEM
    4.
    发明申请
    AIRCRAFT COMPRISING A CABIN BLOWER SYSTEM 有权

    公开(公告)号：US20250002160A1

    公开(公告)日：2025-01-02

    申请号：US18754879

    申请日：2024-06-26

    Applicant: ROLLS-ROYCE plc

    Inventor： Marko BACIC ,  Vasileios PACHIDIS ,  Chana A SAIAS

    IPC: B64D13/06 ,  B64D41/00 ,  F02C7/32 ,  F04D17/10 ,  F04D25/02 ,  F04D25/06

    Abstract: An aircraft includes a turbofan engine, a cabin blower system and a PEM fuel cell stack. The cabin blower system includes a cabin blower compressor arranged to be driven by mechanical power derived from a shaft of the turbofan engine. A ducting system delivers respective portions of the mass flow rate of compressed air output by the cabin blower system to a cabin space of the aircraft via an air-conditioning unit and to the cathode input of the fuel cell stack. An electric motor receives electrical power from the fuel cell stack and provides mechanical power to the compressor via a drive arrangement of the cabin blower system. Power associated with excess capacity of the cabin blower system is recovered to the cabin blower compressor, thereby mitigating or eliminating the fuel consumption penalty on the turbofan engine associated with the excess capacity.

    COMPUTER-IMPLEMENTED METHODS FOR CONTROLLING THE OPERATION OF ELECTRIC AND HYBRID ELECTRIC AIRCRAFT
    5.
    发明申请
    COMPUTER-IMPLEMENTED METHODS FOR CONTROLLING THE OPERATION OF ELECTRIC AND HYBRID ELECTRIC AIRCRAFT 有权

    公开(公告)号：US20220291683A1

    公开(公告)日：2022-09-15

    申请号：US17672385

    申请日：2022-02-15

    Applicant: ROLLS-ROYCE plc

    Inventor： Marko BACIC ,  Peter A. BEECROFT

    IPC: G05D1/00 ,  G08G5/00 ,  B64D27/24 ,  B64D13/06 ,  B64D43/00 ,  B60L50/60 ,  B60L50/70 ,  B64C29/00 ,  G05D1/10

    Abstract: Computer-implemented methods for controlling the operation of aircraft, particularly electric or hybrid electric aircraft, are described. One such method, which may be implemented on a Flight Management System (FMS) of the aircraft, comprises: obtaining flight path data for the aircraft, the flight path defining a three-dimensional path from an origin to a destination; receiving weather data indicative of weather conditions along the flight path; and determining an amount of energy required to fly the aircraft along the flight path. The determination uses an aircraft energy usage model whose inputs include the flight path data and the weather data. Based on the determination and a comparison with an amount of stored energy available to the aircraft, the FMS may validate the flight path for flight or reject the flight path.

    GAS TURBINE ENGINE FLOW CONTROL
    6.
    发明申请
    GAS TURBINE ENGINE FLOW CONTROL 有权

    公开(公告)号：US20210062732A1

    公开(公告)日：2021-03-04

    申请号：US16945061

    申请日：2020-07-31

    Applicant: ROLLS-ROYCE plc

    Inventor： Cerith DAVIES ,  Marko BACIC

    IPC: F02C9/54 ,  F02C7/36 ,  F02C3/06

    Abstract: A method of controlling a gas turbine engine including receiving an instantaneous thrust demand for current operation of the engine, determining the inlet flow rate and/or the pressure ratio within the compressor of the engine and determining whether the inlet flow rate and/or the pressure ratio match the working line for the compressor. The angle of one or more vane of the compressor is adjusted according to a closed control loop if the inlet flow rate and/or pressure ratio lie outside said desired range in order to adjust the inlet inflow rate and/or pressure ratio to meet the working line. The fuel flow to the engine combustor is adjusted concurrently in order to meet the thrust demand.

    TURBINE TIP CLEARANCE
    8.
    发明申请
    TURBINE TIP CLEARANCE 审中-公开
    涡轮提示间隙

    公开(公告)号：US20160326901A1

    公开(公告)日：2016-11-10

    申请号：US15133883

    申请日：2016-04-20

    Applicant: ROLLS-ROYCE plc

    Inventor： Arthur Laurence ROWE ,  Marko BACIC

    IPC: F01D11/24

    CPC classification number: F01D11/24 ,  F01D21/12 ,  F01D21/14 ,  F05D2270/021 ,  F05D2270/112 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/705

    Abstract: A method of controlling turbine tip clearance includes measuring turbine speed; measuring turbine temperature; measuring parameters indicative of current operating conditions; determining limits for the turbine speed and turbine temperature; calculating target tip clearance from the turbine speed, turbine temperature and parameters, to optimise turbine efficiency within the turbine speed and turbine temperature limits; and controlling turbine tip clearance apparatus to the calculated target tip clearance.

    Abstract translation: 控制涡轮机顶端间隙的方法包括测量涡轮机速度; 测量涡轮机温度; 测量指示当前操作条件的参数; 确定涡轮机转速和涡轮机温度的限制; 从涡轮转速，涡轮机温度和参数计算目标叶尖间隙，以优化涡轮机转速和涡轮机温度极限内的涡轮机效率; 以及将涡轮机顶端间隙装置控制到所计算的目标顶端间隙。

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