公开(公告)号：US10294810B2

公开(公告)日：2019-05-21

申请号：US15134723

申请日：2016-04-21

Applicant: ROLLS-ROYCE plc

Inventor： Mark T Mitchell

IPC: F01D11/08 ,  F16J15/16 ,  F01D9/04 ,  F01D11/14

Abstract: Described is a seal segment (310) for a gas turbine engine, comprising: a gas facing wall (312) having a gas facing surface (314) and a first internal surface (316); an outboard wall (318) having an outboard facing surface (320) and a second internal surface (322) which is radially separated from the first internal surface with a gap therebetween; a first conduit (324) located between the first and second internal surfaces; and, a second conduit (326) located between the first and second internal surfaces, wherein the first and second conduits are radially separated by a party wall (328).

公开(公告)号：US20190078457A1

公开(公告)日：2019-03-14

申请号：US15700264

申请日：2017-09-11

Applicant: United Technologies Corporation

Inventor： Jonathan Jeffery Eastwood ,  Joseph F. Englehart ,  Christopher Carter Venable ,  Michael G. McCaffrey

IPC: F01D11/14 ,  F16J15/16

Abstract: A gas turbine engine sealing system includes a case including forward and aft hooks. The aft hook arranged radially outward of the forward hook. A blade outer air seal has a J-hook that receives the aft hook and includes an end received by the forward hook.

公开(公告)号：US10047626B2

公开(公告)日：2018-08-14

申请号：US14910035

申请日：2014-08-05

Applicant: Siemens Aktiengesellschaft

Inventor： Fathi Ahmad ,  Michael Händler ,  Kevin Kampka ,  Christian Kowalski ,  Christian Kowalzik ,  Nihal Kurt ,  Stefan Schmitt ,  Peter Schröder

IPC: F01D11/08 ,  F02C3/04 ,  F01D5/14 ,  F01D11/14 ,  F01D25/28

Abstract: A gas turbine includes an insert element for fastening to a ring segment body of a turbine of the gas turbine. The ring segment body has a recess on a hot gas side. The insert element is designed to cover the recess. The insert element includes a cover plate, which has a concavely shaped front side and a back side, and at least one foot arranged on the back side for positioning on the ring segment body. A mounting method includes mounting the insert element where the insert element is fixed to a recess of a ring segment body of a turbine of a gas turbine.

公开(公告)号：US09995167B2

公开(公告)日：2018-06-12

申请号：US15329381

申请日：2015-07-28

Applicant: BAE Systems plc

Inventor： David John Shepard

IPC: F01D21/00 ,  G01S13/00 ,  G01S13/88 ,  G01S7/41 ,  F01D11/14 ,  B64D27/16 ,  B64D45/00

CPC classification number: F01D21/003 ,  B64D27/16 ,  B64D45/00 ,  B64D2045/0085 ,  F01D11/14 ,  F01D17/06 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/80 ,  F05D2270/821 ,  G01S7/354 ,  G01S7/412 ,  G01S7/415 ,  G01S13/003 ,  G01S13/505 ,  G01S13/536 ,  G01S13/88 ,  G01S2007/358

Abstract: A blade monitoring system and method for a turbine assembly comprising rotating blades (14), the system comprising at least one sensor (10, 12) for transmitting a signal towards said rotating blades and detecting a time-varying return signal therefrom, and one or more processors (20) configured to calculate the time derivative of said return signal, generate a phase variation signal for said time derivative, determine minima points within said phase variation signal and measure said signal at said minima points so as to identify data representative of respective minimum path lengths, each said minimum path length corresponding to the returned signal as each respective blade passes said sensor, and generate, using said minimum path lengths, a time series of data representing the returned signal from individual blades as they pass the sensor.

公开(公告)号：US09945288B2

公开(公告)日：2018-04-17

申请号：US15083782

申请日：2016-03-29

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA

Inventor： Shohei Naruoka ,  Hisatoyo Arima

IPC: F02B33/40 ,  F01D25/16 ,  F01D25/28 ,  F01D11/14 ,  F02B39/04 ,  F02B39/12 ,  F01D5/02 ,  F02D23/00 ,  F01D5/04 ,  F02C6/12

CPC classification number: F02B39/04 ,  F01D5/025 ,  F01D5/027 ,  F01D5/04 ,  F01D11/14 ,  F01D25/16 ,  F01D25/28 ,  F02B33/40 ,  F02B39/12 ,  F02C6/12 ,  F02D23/005 ,  F05D2220/40 ,  F05D2260/40311

Abstract: A rotary unit is rotatably accommodated within a supercharger casing of a supercharger for pressurizing an intake air of an engine. The rotary unit includes a supercharger rotary shaft, an impeller fixed to a tip end portion of the supercharger rotary shaft, a rotating component rotatable together with the supercharger rotary shaft independently of the impeller, and a nut member for pressing the impeller and the rotating component in a direction axially of the supercharger rotary shaft to thereby fix them to the supercharger rotary shaft. The nut member is formed with an adjustment portion for the rotational balance adjustment.

公开(公告)号：US20180073381A1

公开(公告)日：2018-03-15

申请号：US15563285

申请日：2016-03-30

Applicant: Siemens Aktiengesellschaft

Inventor： Senthil Krishnababu

IPC: F01D11/14 ,  F01D5/20 ,  F04D29/52 ,  F04D29/16 ,  F01D5/14

CPC classification number: F01D11/14 ,  F01D5/142 ,  F01D5/20 ,  F01D11/08 ,  F04D17/08 ,  F04D29/164 ,  F04D29/526

Abstract: A fluid flow engine, in particular compressor or turbine of a gas turbine engine, having a stationary engine casing and a rotor assembly rotatable supported in the engine casing, the rotor assembly having at least one circumferentially extending rotor blade row with a plurality of radially extending unshrouded rotor blades, an inner surface of the engine casing with at least one circumferentially extending slot arranged radially outside of the rotor blade row, wherein a gap is provided between tips of the rotor blades and a base of the slot, whereby the depth of the slot is less than the gap height of the gap.

公开(公告)号：US09903218B2

公开(公告)日：2018-02-27

申请号：US14827698

申请日：2015-08-17

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Matthew Troy Hafner ,  Victor John Morgan ,  Frederic Woodrow Roberts

IPC: F01D11/22 ,  F01D25/04 ,  F01D25/00 ,  F01D25/08 ,  F01D11/20 ,  F01D11/14

CPC classification number: F01D11/22 ,  F01D11/14 ,  F01D11/20 ,  F01D25/005 ,  F01D25/04 ,  F01D25/08 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/52 ,  F05D2260/96 ,  F05D2300/17 ,  F05D2300/171 ,  F05D2300/502 ,  F05D2300/6033

Abstract: A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, a damper block disposed between the inner shroud and the outer shroud, a first biasing apparatus, and a second biasing apparatus. The first biasing apparatus provides a first biasing force to the inner shroud, biasing the inner shroud a first deflection distance in a direction toward the hot gas path and away from the outer shroud. The second biasing apparatus provides a second biasing force to the damper block, biasing the damper block a second deflection distance in a direction toward the hot gas path and away from the outer shroud. The second deflection distance is greater than the first deflection distance.

公开(公告)号：US09856740B2

公开(公告)日：2018-01-02

申请号：US14973943

申请日：2015-12-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Alexandre Ayers

IPC: F01D7/02 ,  F01D11/14 ,  F01D11/16 ,  F01D11/22 ,  F01D5/34 ,  F01D5/02 ,  F01D5/22 ,  F01D5/30

CPC classification number: F01D7/02 ,  F01D5/02 ,  F01D5/225 ,  F01D5/3069 ,  F01D5/34 ,  F01D11/16 ,  F01D11/22 ,  F05D2220/32 ,  F05D2240/20 ,  F05D2300/501

Abstract: An integrally bladed rotor for a gas turbine engine includes a hub, a plurality of blades radially extending from the hub and being integrally formed therewith. The hub having a rim from which the blades project and a pair of axially opposed split hub members extending at least radially inward from the rim. Each of the split hub members has a radially outer flex arm portion extending form the hub and a radially inner moment flange portion. At least one moment inducing element separately formed from the hub is mounted axially between the opposed split hub members and acts on the moment flange portions of the opposed split hub members to generate an inward bending moment on the flex arm portions of the opposed split hub members during rotation of the rotor, thereby deflecting the rim and the blades of the rotor radially inwardly.

公开(公告)号：US09760748B2

公开(公告)日：2017-09-12

申请号：US14820736

申请日：2015-08-07

Applicant: General Electric Company

Inventor： Joseph Alfred Iannotti ,  William Chester Platt ,  Trang Thuy Thai

IPC: G06K7/10 ,  G01R35/00 ,  F01D11/14 ,  F01D21/04 ,  G01B7/14 ,  G01L5/00 ,  H04Q9/02

CPC classification number: G06K7/10198 ,  F01D11/14 ,  F01D21/04 ,  G01B7/14 ,  G01L5/00 ,  G01M11/0207 ,  G01M11/0228 ,  G01M11/0264 ,  G01R35/005 ,  G06K7/10207 ,  G06K7/10217 ,  H04Q9/02

Abstract: A calibration circuit includes a single-wire memory and a transmission line. The single-wire memory includes a power/interrogation terminal and a ground terminal. The single-wire memory is configured to store calibration data for a sensor. The transmission line is configured to be coupled between the sensor and a sensor reader. The transmission line includes first and second conductors. The first conductor is coupled to the power/interrogation terminal and is configured to provide the calibration data and a sensor output signal to the sensor reader. The second conductor is coupled to the ground terminal and is configured to provide a ground reference for the first conductor, the single-wire memory, and the sensor.

公开(公告)号：US20170160083A1

公开(公告)日：2017-06-08

申请号：US15316484

申请日：2015-06-03

Applicant: SAFRAN AIRCRAFT ENGINES ,  ECOLE CENTRALE DE LYON ,  CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) ,  ECOLE NATIONALE D'INGENIEURS DE SAINT ETIENNE

Inventor： Marie-Oceane PARENT ,  Fabrice Joel Luc CHEVILLOT ,  Fabrice Hugues Jean Pierre THOUVEREZ

IPC: G01B21/04 ,  G01B21/22 ,  F01D11/14

CPC classification number: G01B21/04 ,  F01D11/14 ,  F05D2260/81 ,  G01B21/22 ,  G01B21/24 ,  G01B21/32

Abstract: The present invention relates to a method for dimensioning a turbomachine comprising a casing and a disc to which at least one blade is secured, said disc being rotationally driven by a shaft about a turbomachine axis (z), comprising:—acquisition (E1) of the coordinates (P) of the ends of the leading edge and of the trailing edge of the blade in a frame of reference connected with the disc;—expression (E2) of the coordinates (P′) of the ends of the leading edge and of the trailing edge of the blade in a frame of reference connected with the casing;—calculation (E3) of the distance (g) between the casing and the ends of the leading edge and trailing edge of the blade from the coordinates (P′) expressed in the frame of reference connected with the casing;—calculation (E4) of the contact pressures between the blade and the casing along the end of the blade from the calculated distance (g);—calculation (E5) of the reaction forces and moments resulting from contact between the blade and the casing from the calculated pressures;—dimensioning (E6) of the turbomachine as a function of the calculated distances, pressures, forces and moments.