公开(公告)号：US20180111332A1

公开(公告)日：2018-04-26

申请号：US15568337

申请日：2016-04-26

Applicant: Composite Technology and Applications Limited

Inventor： Andrew Collis ,  Nolan Richmond

IPC: B29C65/00 ,  B29C65/48 ,  B29C65/78 ,  F01D5/14 ,  F16B11/00 ,  G01B7/16 ,  G01B7/287 ,  G01L1/20 ,  G01L1/16 ,  G01B7/28

CPC classification number: B29C66/92211 ,  B29C65/48 ,  B29C65/782 ,  B29C66/1122 ,  B29C66/301 ,  B29C66/346 ,  B29C66/532 ,  B29C66/721 ,  B29C66/73112 ,  B29C66/742 ,  B29L2031/082 ,  F01D5/147 ,  F01D5/282 ,  F01D17/02 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2230/31 ,  F05D2260/407 ,  F05D2260/83 ,  F16B11/006 ,  G01B7/22 ,  G01B7/285 ,  G01B7/287 ,  G01L1/16 ,  G01L1/205

Abstract: Methods and apparatus are described for improving fit checking at the bonding interface of a first component, such as a fan blade (1), and a second component, such as an edge guard (2) for the fan blade (1), to be bonded by adhesive. A bondline thickness profile over the area of the bonding interface is determined by interposing a compressible, flexible sensor layer between the components before they are bonded. The sensor layer contains an array of piezoelectric elements which indicate local bondline thickness by signalling pressure due to compression of the layer. The bondline thickness profile can be processed by a programmed control processor to produce an adhesive application schedule prescribing the shapes of pieces of adhesive film which, when applied over the bonding interface, will build up an adhesive layer corresponding in thickness to the bondline thickness. The sensor layer can be prepared as a kit of shaped panels or as a contoured preform (55) matching the form of the bonding interface.

公开(公告)号：US09932842B2

公开(公告)日：2018-04-03

申请号：US14776382

申请日：2014-03-12

Applicant: United Technologies Corporation

Inventor： Thomas B. Hyatt ,  Carl Brian Klinetob

IPC: F01D5/28 ,  F01D25/00 ,  F01D5/14 ,  F01D5/16 ,  F01D25/16 ,  F02C7/20

CPC classification number: F01D5/288 ,  F01D5/147 ,  F01D5/16 ,  F01D25/005 ,  F01D25/007 ,  F01D25/162 ,  F02C7/20 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/90 ,  F05D2240/121 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2300/611 ,  Y02T50/671 ,  Y02T50/673

Abstract: A structural guide vane for use in a gas turbine engine has a leading edge section, a trailing edge, a pressure surface and a suction surface. An erosion coating such as polyurethane resin is on the pressure surface and the suction surface. The leading edge of the vane is without the erosion coating and is bare metal. The vane is formed to include a plurality of pockets and bond shelves in the pressure surface side, and an epoxy bond line on the bond shelves holding a cover plate protected by the erosion coating.

公开(公告)号：US20180080332A1

公开(公告)日：2018-03-22

申请号：US15707428

申请日：2017-09-18

Applicant: Safran Aircraft Engines

Inventor： Marc-Antoine Anatole GOT ,  Cédric ZACCARDI

IPC: F01D9/04 ,  F01D5/28

CPC classification number: F01D9/041 ,  F01D5/282 ,  F01D5/3069 ,  F01D9/042 ,  F01D25/246 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2260/31 ,  F05D2300/603 ,  Y02T50/672

Abstract: An OGV wheel comprising guide vanes made of polymer matrix composite material reinforced by fibers, each having a vane root and a vane tip, the vane roots being fastened on a hub of the wheel by first connection means and the vane tip being fastened on an outer shroud of the wheel by second connection means, the first connection means including a bearing plane secured to the hub and a first backing plate for securing to the hub, the vane roots being sandwiched between the bearing plane and the first backing plate, and the second connection means including a second backing plate for securing to the shroud, the vane tip being sandwiched between the shroud and the second backing plate.

公开(公告)号：US09920654B2

公开(公告)日：2018-03-20

申请号：US14652573

申请日：2013-12-16

Applicant: Snecma

Inventor： Margaux Justine Emma Dubois ,  Alexandre Christophe Adrien Demoulin

IPC: F01D25/24 ,  B64D27/00 ,  B64D29/06 ,  F02K3/06 ,  F02C7/20

CPC classification number: F01D25/243 ,  B64D27/00 ,  B64D29/06 ,  F01D25/24 ,  F02C7/20 ,  F02K3/06 ,  F05D2220/36 ,  Y02T50/671

Abstract: The invention relates to an extension (30) of an intermediate frame for an aircraft turbine engine, that will project downstream from an outer ring of the intermediate frame, this extension comprising a downstream annular connecting part (64) preferably forming an annular groove (66) open radially outwards, into which the nacelle cowls will fit (38), the end (64) comprising at least one first angular sector (76b). According to the invention, the extension comprises a body (77) made from a single piece comprising a junction ring (74) and at least one second angular sector (76a) of said downstream annular connecting part (64), the first angular sector being added onto the extension body (77).

公开(公告)号：US20180073377A1

公开(公告)日：2018-03-15

申请号：US15678629

申请日：2017-08-16

Applicant: ROLLS-ROYCE plc

Inventor： Cesare A. HALL ,  Ewan J. GUNN ,  Sarah E. TOOZE

IPC: F01D9/04 ,  F01D5/14 ,  F02K3/06

CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D5/142 ,  F01D5/145 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/30 ,  Y02T50/673

Abstract: A boundary layer Ingesting (BLI) fan system operates with a highly non-uniform flow field that propagates through the fan stage. The fan stage suffers from hub separations, increased wake thicknesses and casing losses. These loss sources can be reduced or eliminated by varying the inlet metal angles and/or chordal lengths of the downstream fan stators. Greater improvement can further be made by non-axisymmetrically leaning the stators

公开(公告)号：US20180066590A1

公开(公告)日：2018-03-08

申请号：US15811251

申请日：2017-11-13

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Karl L. Hasel

IPC: F02C7/36 ,  F02C7/00 ,  F02K3/06 ,  F01D1/04 ,  F02C3/04 ,  F01D25/16 ,  F01D9/04

CPC classification number: F02C7/36 ,  F01D1/04 ,  F01D9/041 ,  F01D25/162 ,  F02C3/04 ,  F02C7/00 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/50 ,  F05D2260/40311

Abstract: In one exemplary embodiment, a gas turbine engine includes a fan section having a fan with a low corrected fan tip speed less than 1400 ft/sec. A bypass ratio is greater than 11.0 and less than 22.0. A fan pressure ratio is less than 1.48. A speed reduction device includes a gear system with a gear ratio of at least 2.6 and less than or equal to 4.1. A low pressure turbine including three stages and a high pressure turbine including two stages. The low pressure turbine includes at least one rotor constrained by a first stress level. At least one of a plurality of fan blades is constrained by a second stress level and has a fan tip speed boundary condition. The gear ratio is configured such that the at least one fan blade does not exceed the fan tip speed boundary condition or the second stress level.

公开(公告)号：US09909497B2

公开(公告)日：2018-03-06

申请号：US14706748

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Matthew R. Feulner ,  Brian D. Merry ,  Jesse M. Chandler ,  Gabriel L. Suciu ,  Joseph B. Staubach

IPC: F02C6/08 ,  F04D27/02 ,  F02C7/052 ,  F04D29/52 ,  F04D29/70 ,  F02C3/10 ,  F02K3/06

CPC classification number: F02C6/08 ,  F02C3/10 ,  F02C7/052 ,  F02K3/06 ,  F04D27/0215 ,  F04D29/526 ,  F04D29/701 ,  F05D2210/12 ,  F05D2220/36 ,  F05D2260/607 ,  F05D2260/608 ,  F05D2270/101 ,  Y02T50/675

Abstract: A compressor section of a gas turbine engine includes a bleed port having a flow splitter therein so as to define a downstream bleed channel having a downstream inlet and an upstream bleed channel having an upstream inlet that is positioned radially outward from the downstream inlet.

公开(公告)号：US09909455B2

公开(公告)日：2018-03-06

申请号：US14794005

申请日：2015-07-08

Applicant: Snecma

Inventor： Jerome Etienne Robert Cameau ,  Laurent Donatien Behaghel ,  Kévin Michel Robert Contal ,  Sébastien Nicolas Juigne

IPC: F01D25/24 ,  F01D25/08 ,  F01D25/18 ,  F01D9/06 ,  F02C7/32

CPC classification number: F01D25/24 ,  F01D9/065 ,  F01D25/08 ,  F01D25/18 ,  F02C7/32 ,  F05D2220/36 ,  F05D2240/60 ,  F05D2260/606 ,  F05D2260/98

Abstract: An intermediate casing comprising an inner annular hub, an outer annular barrel and an annular part for separating flows situated between the hub and the outer barrel. A primary stream is delimited between the hub and the separation part. A secondary stream is delimited between the separation part and the outer barrel. At least one hollow arm extends radially from the hub to the outer barrel, passing through the primary and secondary streams. A transmission shaft extends radially in the hollow arm. The hollow arm comprises a hydraulic-fluid outlet situated downstream of the transmission shaft. The arm further comprises a bypass channel or pocket able to bypass the transmission shaft.

公开(公告)号：US09896964B2

公开(公告)日：2018-02-20

申请号：US14969774

申请日：2015-12-15

Applicant: United Technologies Corporation

Inventor： Steven Clarkson ,  Daniel K. Van Ness, II ,  Paul Thomas Rembish

IPC: F01D25/02 ,  F01D25/24 ,  F01D25/10 ,  F01D21/10 ,  F01D17/10 ,  B64D27/10 ,  B64D15/12 ,  B64D29/00 ,  F02C7/047 ,  F02C7/05 ,  F04D29/54 ,  F04D29/58 ,  F04D27/02

CPC classification number: F01D25/02 ,  B64D15/12 ,  B64D27/10 ,  B64D29/00 ,  F01D17/105 ,  F01D21/10 ,  F01D25/10 ,  F01D25/24 ,  F02C7/047 ,  F02C7/05 ,  F04D27/0215 ,  F04D27/023 ,  F04D29/545 ,  F04D29/584 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/20 ,  F05D2270/096

Abstract: A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structure-supporting member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structure-supporting member.

公开(公告)号：US09896949B2

公开(公告)日：2018-02-20

申请号：US14862390

申请日：2015-09-23

Applicant: United Technologies Corporation

Inventor： Thomas J. Robertson

IPC: F01D5/14 ,  F01D5/30 ,  F01D5/12 ,  F04D29/02 ,  F04D29/32 ,  F02K3/06 ,  F01D5/28 ,  F01D11/00

CPC classification number: F01D5/3069 ,  F01D5/12 ,  F01D5/147 ,  F01D5/282 ,  F01D5/3053 ,  F01D11/005 ,  F01D11/008 ,  F02K3/06 ,  F04D29/023 ,  F04D29/324 ,  F05D2220/36 ,  F05D2240/80 ,  F05D2240/81 ,  F05D2260/30 ,  F05D2260/36 ,  F05D2300/603 ,  Y02T50/676

Abstract: A fan is provided. The fan may comprise a fan blade and a blade platform coupled to the fan blade. The blade platform may be a thermoplastic. A fan blade platform is also provided. The fan blade platform may comprise a first platform half comprising a slot at a first end of the first platform half and a first receiving member at a second end of the first platform half opposite the first end of the first platform half. A second platform half may comprise a hook. The second platform half may also include a second receiving member at a second end of the second platform half opposite the first end of the second platform half with the hook configured to interface with the slot. A pin may be configured to pass through the first receiving member and the second receiving member.