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    Combustion staging system
    191.
    发明授权
    Combustion staging system 有权

    公开(公告)号：US11549687B2

    公开(公告)日：2023-01-10

    申请号：US16916589

    申请日：2020-06-30

    Applicant: ROLLS-ROYCE plc

    Inventor： Michael Griffiths ,  Daniel J. Bickley

    IPC: F23R3/34 ,  F02C7/228 ,  F02C7/232 ,  F02C7/36 ,  F02C9/26

    Abstract: A combustion staging system for fuel injectors of a multi-stage combustor of a gas turbine engine. The system includes plural fuel injectors, each having respective pilot and mains injection stages. It further includes a splitting unit which, to perform staging control of the combustor, receives a metered fuel flow and, for pilot and mains operation, controllably splits the received fuel flow into a pilot flow for injecting at the pilot stages of the injectors and a mains flow for injecting at the mains stages of the injectors, and for pilot-only operation, controllably splits the received fuel flow into a first part of the pilot flow for injecting at the pilot stages of a first portion of the injectors and a second part of the pilot flow for injecting at the pilot stages of a second portion of the injectors.

    Heat exchanger
    192.
    发明授权
    Heat exchanger 有权

    公开(公告)号：US11549438B2

    公开(公告)日：2023-01-10

    申请号：US17494523

    申请日：2021-10-05

    Applicant: ROLLS-ROYCE plc

    Inventor： Stephen J Bradbrook ,  Martin N Goodhand ,  Paul M Hield ,  Andrew Parsley ,  Natalie C Wong ,  Robert J Corin ,  Thomas S Binnington

    IPC: F02C7/12 ,  F25B11/00

    Abstract: A turbofan gas turbine engine includes heat exchanger module, fan assembly, compressor, turbine and exhaust modules. The fan includes a plurality of fan blades. The heat exchanger in fluid communicates with the fan assembly by an inlet duct, and the heat exchanger includes a plurality of radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger is divided between a set of vane airflows and a set of channel airflows. Each vane airflow has a vane mass flow rate FlowVane, and each channel air flow has a channel mass flow rate FlowChan. Each hollow vane includes, an inlet, heat transfer, and exhaust portions, with the inlet portion comprising a diffuser element and the heat transfer portion including at least one heat transfer element. The diffuser element causes FlowVane to be lower than FlowChan.

    Gearboxes for aircraft gas turbine engines
    193.
    发明授权
    Gearboxes for aircraft gas turbine engines 有权

    公开(公告)号：US11542873B2

    公开(公告)日：2023-01-03

    申请号：US17827214

    申请日：2022-05-27

    Applicant: ROLLS-ROYCE plc

    Inventor： Mark Spruce

    IPC: F02C7/36 ,  F02C7/06

    Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

    METHOD OF ELECTROPOLISHING
    195.
    发明申请
    METHOD OF ELECTROPOLISHING 有权

    公开(公告)号：US20220411954A1

    公开(公告)日：2022-12-29

    申请号：US17842447

    申请日：2022-06-16

    Applicant: ROLLS-ROYCE plc

    Inventor： Daniel CLARK

    IPC: C25F3/16 ,  B22F10/62 ,  B33Y40/20

    Abstract: A method of electropolishing an internal passageway of a component, wherein the passageway has an inlet and an outlet; including: providing an electrode assembly including a flexible electrode, a shuttle and a guide cable extending between the flexible electrode and the shuttle; inserting the shuttle into the inlet; causing fluid to flow through the passageway to transport the shuttle through the passageway from the inlet towards the outlet; pulling the guide cable through the passageway to position the electrode in the passageway adjacent to a region of the passageway to be polished; and electropolishing the passageway using the electrode while moving the electrode within the passageway. Also, an electrode assembly for electropolishing an internal passageway of a component, including: a flexible electrode, a shuttle, and a guide cable extending between the flexible electrode and the shuttle.

    Staged combustion
    196.
    发明授权
    Staged combustion 有权

    公开(公告)号：US11530651B2

    公开(公告)日：2022-12-20

    申请号：US17189650

    申请日：2021-03-02

    Applicant: ROLLS-ROYCE plc

    Inventor： Christopher P. Madden ,  Peter Swann

    IPC: F02C9/28 ,  F23R3/34 ,  F02C9/26 ,  F02C9/40 ,  F02C3/30

    Abstract: A gas turbine engine for an aircraft. The gas turbine comprises a staged combustion system having pilot injectors and main injectors, a fuel metering system configured to control fuel flow to the pilot injectors and the main injectors, and a fuel system controller. The controller is configured to identify an atmospheric condition, determine a ratio of pilot fuel flow rate for the pilot injectors to main fuel flow rate for the main injectors in response to the atmospheric condition, and inject fuel by the pilot injectors and the main injectors in accordance with said ratio to control an index of soot emissions caused by combustion of fuel therein.

    GEARED GAS TURBINE ENGINE
    198.
    发明申请
    GEARED GAS TURBINE ENGINE 有权

    公开(公告)号：US20220389875A1

    公开(公告)日：2022-12-08

    申请号：US17889158

    申请日：2022-08-16

    Applicant: ROLLS-ROYCE plc

    Inventor： Craig W BEMMENT

    IPC: F02C7/36 ,  F01D15/12 ,  F01L15/12

    Abstract: The present disclosure relates to a geared gas turbine engine for an aircraft. Example embodiments include a gas turbine engine for an aircraft including: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox that receives an input from the core shaft to drive the fan at a lower rotational speed than the core shaft, the gearbox having a gear ratio of around 3.4 or higher, wherein the gas turbine engine is configured such that a jet velocity ratio between a first jet velocity exiting from a bypass duct of the engine and a second jet velocity exiting from an exhaust nozzle of the engine core is within a range from around 0.75 to around 0.82.

    Oil pipe assembly
    199.
    发明授权
    Oil pipe assembly 有权

    公开(公告)号：US11519297B2

    公开(公告)日：2022-12-06

    申请号：US16828102

    申请日：2020-03-24

    Applicant: ROLLS-ROYCE plc

    Inventor： Michael Booth ,  Andrew Smith ,  Ajay Patel

    IPC: F01D25/18 ,  F01M1/10 ,  F01M1/20 ,  F01D9/06

    Abstract: An oil pipe assembly for a gas turbine engine. The oil pipe assembly includes a first pipe that defines a first fluid passage between an oil supply and a bearing chamber, and a second pipe that houses the first pipe and defines a second fluid passage between the first pipe and the second pipe that is supplied with cooling air. The oil pipe assembly also includes a restrictor that extends from the second pipe and restricts the passage of fluid from the second fluid passage before it flows into a breather. Pressure and temperature sensors) are located adjacent the restrictor to detect and measure changes in air pressure and air temperature adjacent the restrictor from which a controller identifies whether a leak has occurred in the first pipe or the second pipe. A method for detecting a leak in the oil pipe assembly, and a gas turbine are also described.

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