中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

61 records (took 0.021 seconds)

    Low noise turbine for geared gas turbine engine
    3.
    发明授权
    Low noise turbine for geared gas turbine engine 有权

    公开(公告)号：US10605172B2

    公开(公告)日：2020-03-31

    申请号：US13970670

    申请日：2013-08-20

    Applicant: United Technologies Corporation

    Inventor： Bruce L. Morin ,  David A. Topol ,  Detlef Korte

    IPC: F02C7/24 ,  F02K3/06

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a compressor section driven by the turbine section, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.

    Three spool turbofan engine with low noise intermediate turbine rotor
    4.
    发明授权
    Three spool turbofan engine with low noise intermediate turbine rotor 有权

    公开(公告)号：US10233774B2

    公开(公告)日：2019-03-19

    申请号：US14905994

    申请日：2014-07-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Frederick M. Schwarz ,  Bruce L. Morin

    IPC: F01D25/04 ,  F04D29/32 ,  F01D15/12 ,  F01D9/06 ,  F01D5/06 ,  F01D17/10 ,  F02C3/107 ,  F01D5/14 ,  F02K3/06

    Abstract: A turbine section including a high pressure turbine, an intermediate pressure turbine and a fan drive turbine, the fan drive turbine driving a gear reduction to in turn drive a fan, and effecting a reduction in the speed of the fan relative to an input speed from the fan drive turbine and said high pressure turbine driving a high pressure compressor, and the intermediate pressure turbine driving a low pressure compressor, with the intermediate pressure turbine having a number of turbine blades in at least one row, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row, and the rotational speed being such that the following formula holds true for the at least one row of the intermediate pressure turbine: (number of blades×speed)/60?5500 Hz.

    Acoustic liner with obliquely angled slots
    7.
    发明授权
    Acoustic liner with obliquely angled slots 有权

    公开(公告)号：US11480106B2

    公开(公告)日：2022-10-25

    申请号：US16411728

    申请日：2019-05-14

    Applicant: United Technologies Corporation

    Inventor： Bruce L. Morin ,  Anthony R. Bifulco

    IPC: F02C7/24

    Abstract: An acoustic liner for a gas turbine engine includes an acoustic panel that is curved about a central axis. The acoustic panel includes a support backing, a face sheet, and a cellular structure disposed between the support backing and the face sheet. The face sheet has elongated slots that extend along respective slot centerlines in the plane of the face sheet. The slot centerlines are sloped at oblique angles to the central axis.

    Low noise turbine for geared gas turbine engine
    8.
    发明授权
    Low noise turbine for geared gas turbine engine 有权

    公开(公告)号：US10533447B2

    公开(公告)日：2020-01-14

    申请号：US14606087

    申请日：2015-01-27

    Applicant: United Technologies Corporation

    Inventor： Bruce L. Morin ,  David A. Topol ,  Detlef Korte

    IPC: F01D17/10 ,  F01D5/02 ,  F01D5/12 ,  F01D9/04 ,  F01D15/12

    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.

    Flutter inhibiting intake for gas turbine propulsion system
    9.
    发明授权
    Flutter inhibiting intake for gas turbine propulsion system 有权

    公开(公告)号：US10428685B2

    公开(公告)日：2019-10-01

    申请号：US15452627

    申请日：2017-03-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Bruce L. Morin ,  Daniel L. Gysling ,  Mani Sadeghi

    IPC: F01D25/06 ,  B64D33/02 ,  F02C7/045 ,  F02K1/82 ,  F02K3/06 ,  G10K11/172

    Abstract: Disclosed is flutter damper including a first cavity having a radially inner side in fluid communication with a flow path, and a second cavity having a radially inner side in fluid communication with a radially outer side of the first cavity, and the flutter damper having an impedance characteristic at one or more target frequencies defined as ftarget=fS,ND+Ω·ND wherein fS,ND is a resonance frequency corresponding to a structural mode of a rotating component, ND is a nodal diameter count of the structural mode, and Ω is a rotational speed of the rotating component, and wherein the flutter damper has the following impedance characteristic at the one or more targeted frequencies R≥2ρc −3ρc≤X≤−0.6ρc wherein R is the real part of the impedance characteristic, X is the imaginary part of the impedance characteristic, ρ is air density, and c is speed of sound.

    THREE SPOOL TURBOFAN ENGINE WITH LOW NOISE INTERMEDIATE TURBINE ROTOR
    10.
    发明申请
    THREE SPOOL TURBOFAN ENGINE WITH LOW NOISE INTERMEDIATE TURBINE ROTOR 审中-公开

    公开(公告)号：US20190153891A1

    公开(公告)日：2019-05-23

    申请号：US16255980

    申请日：2019-01-24

    Applicant: United Technologies Corporation

    Inventor： Frederick M. Schwarz ,  Bruce L. Morin

    IPC: F01D25/04 ,  F02K3/06 ,  F04D29/32 ,  F01D15/12 ,  F01D9/06 ,  F01D5/06 ,  F01D17/10 ,  F02C3/107 ,  F01D5/14

    Abstract: A turbine section including a high pressure turbine, an intermediate pressure turbine and a fan drive turbine, the fan drive turbine driving a gear reduction to in turn drive a fan, and effecting a reduction in the speed of the fan relative to an input speed from the fan drive turbine and said high pressure turbine driving a high pressure compressor, and the intermediate pressure turbine driving a low pressure compressor, with the intermediate pressure turbine having a number of turbine blades in at least one row, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row, and the rotational speed being such that the following formula holds true for the at least one row of the intermediate pressure turbine: (number of blades×speed)/60≥5500 Hz.

Patent Agency Ranking