公开(公告)号：US10401161B2

公开(公告)日：2019-09-03

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 ,  G01B21/32 ,  F01D11/14 ,  G01B21/24

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.

公开(公告)号：US10378374B2

公开(公告)日：2019-08-13

申请号：US14672561

申请日：2015-03-30

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Nathan Snape

IPC: F01D11/14 ,  F01D25/24 ,  F01D25/14 ,  F01D17/00 ,  F02C5/12 ,  F01D11/24 ,  F02C7/25

Abstract: A gas turbine engine includes a fluid intake. A turbine section includes a turbine case. A firewall is located upstream of the turbine section. A conduit is configured to direct a fluid from the fluid intake to the turbine case. A valve is located on a first side of the firewall opposite from the turbine section and is configured to regulate a flow of the fluid through the conduit.

公开(公告)号：US10371497B2

公开(公告)日：2019-08-06

申请号：US15832184

申请日：2017-12-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Eli Cole Warren ,  Peter J. Walsh

IPC: G01B7/02 ,  G01B7/14 ,  F01D11/14 ,  F01D11/12

Abstract: A fully integral epoxy cap probe may comprise a body having a cavity disposed radially outward of a fan blade and comprising a first material, a frame disposed within the cavity and comprising a second material, a first sensor element and a ground plane disposed within the frame, the first sensor element and the ground plane comprising a third material, and a first soft lead in electronic communication with the first sensor element and the ground plane.

公开(公告)号：US20190170495A1

公开(公告)日：2019-06-06

申请号：US15832184

申请日：2017-12-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Eli Cole Warren ,  Peter J. Walsh

IPC: G01B7/02 ,  G01B7/14 ,  F01D11/12 ,  F01D11/14

CPC classification number: G01B7/023 ,  F01D11/12 ,  F01D11/14 ,  F01D17/02 ,  F05D2270/80 ,  F05D2300/44 ,  G01B7/14

Abstract: A fully integral epoxy cap probe may comprise a body having a cavity disposed radially outward of a fan blade and comprising a first material, a frame disposed within the cavity and comprising a second material, a first sensor element and a ground plane disposed within the frame, the first sensor element and the ground plane comprising a third material, and a first soft lead in electronic communication with the first sensor element and the ground plane.

公开(公告)号：US20190017405A1

公开(公告)日：2019-01-17

申请号：US16141372

申请日：2018-09-25

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Nathan Snape

IPC: F01D11/14 ,  F02C7/25 ,  F01D11/24 ,  F01D17/00 ,  F01D25/14 ,  F01D25/24 ,  F02C5/12

Abstract: An active clearance control assembly for a gas turbine engine includes a firewall, a fluid intake and an active clearance control manifold. A conduit is configured to direct a fluid from the fluid intake on a first axial side of the firewall through the firewall to at least one active clearance control manifold on a second axial side of the firewall. A valve is located on the first axial side of the firewall and is configured to regulate the flow of the fluid through the conduit.

公开(公告)号：US10161259B2

公开(公告)日：2018-12-25

申请号：US14878862

申请日：2015-10-08

Applicant: General Electric Company

Inventor： Nathan Evan McCurdy Gibson ,  Rahul Anil Bidkar ,  Azam Mihir Thatte ,  Narayana Shastry ,  Hariharan Manickavasagam Sarojini

IPC: F01D11/00 ,  F16J15/44 ,  F01D11/02 ,  F01D11/16 ,  F01D11/14 ,  F01D11/08 ,  F01D11/04 ,  F01D11/10 ,  F01D11/12

Abstract: A seal apparatus for a rotary machine, including a plurality of sealing assembly segments surrounding a rotor element which is mounted for rotation about a longitudinal axis and has an outer surface. Each of the segments includes a shoe with one or more labyrinth teeth facing the outer surface and a shoe plate disposed downstream of the one or more labyrinth seal teeth and configured to generate an aerodynamic force between the shoe plate and the outer surface of the rotor element. The shoe is further configured to be flexible in a radial-axial plane in response to fluid film forces generated by interaction of the sealing assembly segment and the rotor element, and an axially-oriented beam spring connects the shoe to a stationary seal body.

公开(公告)号：US10100842B2

公开(公告)日：2018-10-16

申请号：US14904880

申请日：2014-07-17

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Alain Marc Lucien Bromann ,  Kamel Benderradji ,  Pamela Dominique Daniele Reichert

IPC: F04D29/42 ,  F04D17/10 ,  F04D29/62 ,  F01D25/24 ,  F01D11/14 ,  F02C6/08 ,  F01D5/00

Abstract: A cover of a centrifugal compressor intended to be rigidly connected to a turbomachine housing, which includes a plurality of ports, is provided. The cover further includes a fastening device for fastening the cover to the housing. A portion of the fastening device is located upstream relative to the ports and can be accessed by a fastening tool through at least one of the ports of the cover. A turbomachine uses this cover to form a sealed space, in particular with a view to collecting air.

公开(公告)号：US10053999B2

公开(公告)日：2018-08-21

申请号：US14781263

申请日：2014-04-07

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Brandon T. Rouse ,  Mark Borja ,  Igor S. Garcia ,  John R. Farris ,  Thomas Almy ,  Brian R. Pelletier

IPC: F01D9/04 ,  F01D11/08 ,  F01D11/22 ,  F01D11/12 ,  F01D11/14 ,  F01D11/20 ,  F01D11/24 ,  F01D25/24

CPC classification number: F01D11/08 ,  F01D9/04 ,  F01D11/12 ,  F01D11/14 ,  F01D11/20 ,  F01D11/22 ,  F01D11/24 ,  F01D25/24 ,  Y02T50/672

Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure.

公开(公告)号：US20180187570A1

公开(公告)日：2018-07-05

申请号：US15908210

申请日：2018-02-28

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Richard IVAKITCH ,  Czeslaw WOJTYCZKA ,  Andreas ELEFTHERIOU

IPC: F01D25/24 ,  F04D29/02 ,  F01D11/14 ,  F01D21/04 ,  F04D29/52 ,  F01D11/12 ,  F02C7/045 ,  F01D25/00

CPC classification number: F01D25/24 ,  F01D11/122 ,  F01D11/14 ,  F01D21/045 ,  F01D25/005 ,  F02C7/045 ,  F04D29/023 ,  F04D29/526 ,  F05D2220/36 ,  F05D2300/121 ,  F05D2300/171

Abstract: A steel soft wall fan case assembly according to one embodiment configured with a thin-walled steel support structure shell including a plurality of annular axial walls of thin sheet metal reinforced by a plurality of rings interconnecting axially adjacent annular axial walls. The steel support structure shell is structurally integrated with honeycomb materials and an annular metallic inner wall. A fabric containment layer may be wrapped around one of the annular axial walls of the steel support structure shell.

公开(公告)号：US09957829B2

公开(公告)日：2018-05-01

申请号：US14890939

申请日：2014-05-12

Applicant: Siemens Aktiengesellschaft

Inventor： Andrew Shepherd

IPC: F01D11/12 ,  F01D11/14 ,  F01D5/02 ,  F01D5/12 ,  F01D9/04 ,  F01D25/24

CPC classification number: F01D11/122 ,  F01D5/02 ,  F01D5/12 ,  F01D9/041 ,  F01D11/14 ,  F01D25/24 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2240/12 ,  F05D2240/307 ,  F05D2240/55 ,  F05D2300/611

Abstract: A method of setting a clearance between a rotor and a stator of a rotor assembly for a turbine engine. The rotor assembly has a plurality of rotor-to-stator stages and the stator has a nominal centerline. Typically the stator is a casing or an array of vane tips. The method includes (i) correlating in-service rotor-to-stator rub patterns for a rotor-to-stator stage of a number of turbine engines, (ii) setting a position of a machining centerline relative to the nominal centerline of the stator, the position being towards a heavy rub, (iii) machining the stator about the machining centerline, (iv) repeating steps (i) to (ii) for each rotor-to-stator stage of the plurality of the rotor-to-stator stages, wherein the machined stator having been formed by at least two machining steps having different center-lines.