中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

9 records (took 0.017 seconds)

    FAN DESIGN
    1.
    发明申请
    FAN DESIGN 审中-公开

    公开(公告)号：US20200018169A1

    公开(公告)日：2020-01-16

    申请号：US16566383

    申请日：2019-09-10

    Applicant: ROLLS-ROYCE PLC

    Inventor： Stephane M M BARALON ,  Christopher BENSON ,  Benedict R. PHELPS

    IPC: F01D5/14 ,  F01D5/28 ,  F04D29/38

    Abstract: A gas turbine engine has a quasi-non-dimensional mass flow rate in a defined range and a specific thrust in a defined range to achieve improved overall performance, taking into account fan operability and/or bird strike requirements as well as engine efficiency. The defined ranges of quasi-non-dimensional mass flow rate and specific thrust may be particularly beneficial for gas turbine engines in which the fan is driven by a turbine through a gearbox.

    GAS TURBINE ENGINE
    3.
    发明公开
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20240337218A1

    公开(公告)日：2024-10-10

    申请号：US18406296

    申请日：2024-01-08

    Applicant: ROLLS-ROYCE plc

    Inventor： Benedict R. PHELPS

    IPC: F02C7/36

    CPC classification number: F02C7/36 ,  F05D2220/36

    Abstract: A gas turbine engine for an aircraft comprises: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a bypass duct delimited by a bypass duct inner wall and a bypass duct outer wall and located radially outwardly from the engine core and downstream of the fan; and an outlet guide vane assembly, located within the bypass duct and, comprising a plurality of outlet guide vanes distributed circumferentially within the bypass duct, each outlet guide vane extending radially along a span between the bypass duct inner wall and the bypass duct outer wall, wherein a space-chord ratio of at least one outlet guide vane, at 50% of the span length from the bypass duct inner wall, is less than 0.72.

    AIRCRAFT ENGINE FAN
    5.
    发明申请
    AIRCRAFT ENGINE FAN 审中-公开

    公开(公告)号：US20200011273A1

    公开(公告)日：2020-01-09

    申请号：US16411294

    申请日：2019-05-14

    Applicant: ROLLS-ROYCE plc

    Inventor： Stephane M. M. BARALON ,  Mark J. WILSON ,  Benedict R. PHELPS

    IPC: F02K3/06 ,  F02K3/02

    Abstract: A gas turbine engine system has an engine core and a bypass duct. A fan drives the flow through the bypass duct. A bypass efficiency is defined as the efficiency of the fan compression of the bypass flow. The bypass efficiency is a function of the bypass flow rate at a given set of conditions. The fan bypass inlet mass flow rate at the reference operating point is appreciably higher than the mass flow rate through the bypass duct at the peak bypass efficiency at a given fan reference rotational speed and cruise conditions. This results in increased design flexibility and improved overall engine performance.

    LOW SPEED FAN TIP CAMBER
    7.
    发明申请
    LOW SPEED FAN TIP CAMBER 有权

    公开(公告)号：US20210404342A1

    公开(公告)日：2021-12-30

    申请号：US17352468

    申请日：2021-06-21

    Applicant: ROLLS-ROYCE plc

    Inventor： Benedict R. PHELPS ,  Stephane M M BARALON ,  Mark J. WILSON

    IPC: F01D5/14 ,  F02K3/06

    Abstract: A fan blade for a gas turbine engine has a covered passage. A cross section through the fan blade at a point along the blade span is defined as having particular change in angle (α3−α1) of the camber line between the leading edge and the trailing edge and/or between the leading edge and the point on the camber line that corresponds to the start of the covered passage.

Patent Agency Ranking