公开(公告)号：US12055048B2

公开(公告)日：2024-08-06

申请号：US18251761

申请日：2021-10-22

申请人： AECC SHANGHAI COMMERCIAL AIRCRAFT ENGINE MANUFACTURING CO., LTD. ,  AECC COMMERCIAL AIRCRAFT ENGINE CO., LTD.

发明人： Jiaguang Wang ,  Shuhui Hu ,  Wen Qin ,  Chuanjun Cao ,  Zhiqing Wu

IPC分类号： F01D11/22 ,  B23P15/00 ,  B23P15/02 ,  F01D5/02 ,  F01D5/14 ,  F01D11/14 ,  F01D21/00 ,  F04D19/00 ,  F04D27/00 ,  F04D29/32

CPC分类号： F01D11/22 ,  B23P15/006 ,  B23P15/02 ,  F01D5/021 ,  F01D11/14 ,  F01D21/003 ,  F04D19/002 ,  F04D27/001 ,  F04D29/324 ,  F01D5/14 ,  F05D2220/323 ,  F05D2230/80 ,  F05D2240/55 ,  F05D2260/83 ,  Y10T29/49336 ,  Y10T29/49771

摘要： A rotor blade tip clearance control method and a rotor blade manufactured using same. The control method includes: coinciding, along an axial direction of an aircraft engine, a center of gravity of a rotor blade with a center of gravity of a rotor wheel disk supporting the rotor blade; rotating the rotor wheel disk to measure a leading edge deformation amount of the rotor blade; measuring a trailing edge deformation amount of the rotor blade; comparing the deformation amounts; and adjusting the center of gravity of the rotor wheel disk until the leading edge deformation amount tends to be approximately equal to the trailing edge deformation amount. The method can effectively improve or even solve the problem of inconsistent radial displacements of a leading edge and a trailing edge during the operation.

公开(公告)号：US11834200B2

公开(公告)日：2023-12-05

申请号：US16874747

申请日：2020-05-15

申请人： Sikorsky Aircraft Corporation

发明人： Scott Oren Smith ,  David Littlejohn ,  Sven Roy Lofstrom

IPC分类号： B64F5/10 ,  B23P15/04 ,  B23P6/00 ,  B64C27/473 ,  B23Q3/06 ,  B23Q3/00 ,  B64C27/48

CPC分类号： B64F5/10 ,  B23P15/04 ,  B23Q3/00 ,  B23Q3/06 ,  B23Q3/062 ,  B23Q3/064 ,  B64C27/473 ,  B23P6/002 ,  B23Q3/063 ,  B64C27/48 ,  Y10T29/49321 ,  Y10T29/49336

摘要： A method of bonding a blade cuff to a rotor blade includes installing the blade cuff to a root end of the rotor blade. The method includes mounting the rotor blade within a plurality of supports. The method includes coupling the blade cuff to a first fixture. The method includes installing a second fixture about the blade cuff. The method further includes applying localized and constant heat and pressure to the blade cuff via the second fixture.

公开(公告)号：US09931689B2

公开(公告)日：2018-04-03

申请号：US13822703

申请日：2011-10-05

申请人： Lenz Simon Zeller ,  Maik Gunther

发明人： Lenz Simon Zeller ,  Maik Gunther

IPC分类号： F03D1/06 ,  B29C33/12 ,  B29C70/44 ,  B29C70/88 ,  B21K3/04 ,  B29C65/54 ,  B29C65/00 ,  B29L31/08 ,  F16B11/00

CPC分类号： B21K3/04 ,  B29C65/542 ,  B29C66/112 ,  B29C66/114 ,  B29C66/1162 ,  B29C66/131 ,  B29C66/301 ,  B29C66/3242 ,  B29C66/43441 ,  B29C66/532 ,  B29C66/5326 ,  B29C66/54 ,  B29C66/61 ,  B29C66/836 ,  B29L2031/085 ,  F03D1/065 ,  F03D1/0675 ,  F16B11/006 ,  Y02E10/721 ,  Y02P70/523 ,  Y10T29/49336

摘要： A method and manufacturing unit for producing a rotor blade (5) of a wind turbine (1) from at least a first rotor blade element (11, 11′, 12, 12′) and a second rotor blade element (11, 11′, 12, 12′). The first rotor blade element (11, 11′, 12, 12′) and the second rotor blade element (11, 11′, 12, 12′) are positioned in the desired relative arrangement with respect to each other such that a joint gap (13) remains between the first rotor blade element (11, 11′, 12, 12′) and the second rotor blade element (11, 11′, 12, 12′). Adhesive is introduced into the joint gap (13) for joining the first rotor blade element (11, 11′, 12, 12′) and the second rotor blade element (11, 11′, 12, 12′).

公开(公告)号：US20170362945A1

公开(公告)日：2017-12-21

申请号：US15608491

申请日：2017-05-30

申请人： ALSTOM Renewable Technologies

发明人： Luca Feigl

IPC分类号： F01D5/30 ,  F03D1/06

CPC分类号： F01D5/30 ,  F03D1/0658 ,  F05B2250/232 ,  F05B2260/30 ,  Y02E10/721 ,  Y02P70/523 ,  Y10T29/49336

摘要： A blade for a wind turbine comprising a blade root portion is described. The blade root portion defines a mounting surface for coupling to a hub or extender of the wind turbine and comprises a plurality of first holes provided with an insert, the blade root portion further comprises a mounting flange arranged in the periphery of the mounting surface and provided with second holes, wherein the inserts comprise a first end embedded in the blade root portion and a second end opposite to the first end, the second end protruding beyond the mounting surface of the blade root portion, and wherein the second ends are fitted in the second holes of the mounting flange and the mounting flange is attached to the blade by means of the inserts. Furthermore, a wind turbine rotor comprising such a blade is described. Methods of manufacturing half a wind turbine blade and a whole wind turbine blade are also described.

公开(公告)号：US09810230B2

公开(公告)日：2017-11-07

申请号：US14642844

申请日：2015-03-10

申请人： Nuovo Pignone SrL

发明人： Iacopo Giovannetti ,  Massimo Giannozzi ,  Dino Bianchi ,  Leonardo Tognarelli ,  Manuele Bigi ,  Andrea Massini

IPC分类号： F04D17/10 ,  F04D29/28 ,  F04D29/42 ,  F04D29/62 ,  F04D29/02 ,  F04D29/22

CPC分类号： F04D29/023 ,  B23P15/006 ,  F04D17/10 ,  F04D29/2227 ,  F04D29/284 ,  F04D29/4206 ,  F04D29/624 ,  F05D2230/23 ,  F05D2300/20 ,  F05D2300/43 ,  Y10T29/49325 ,  Y10T29/49329 ,  Y10T29/49336 ,  Y10T29/49337

摘要： An impeller for a turbo-machine is provided. The impeller includes a metallic base having a back surface and a front surface opposite to the back surface; at least one blade extending on the front surface of the metallic base; a composite shroud attached to the at least one blade such that plural closed paths are formed by the front surface of the metallic base, the at least one blade and the composite shroud; and a connector configured to attach the composite shroud to the metallic base or the at least one blade.

公开(公告)号：US09784286B2

公开(公告)日：2017-10-10

申请号：US14181098

申请日：2014-02-14

申请人： HONEYWELL INTERNATIONAL INC.

发明人： Cristina White

IPC分类号： F04D29/66 ,  F04D29/32 ,  F04D19/00 ,  B23P15/02

CPC分类号： F04D29/668 ,  B23P15/02 ,  F01D5/16 ,  F04D19/002 ,  F04D21/00 ,  F04D29/324 ,  F04D29/328 ,  F05D2220/36 ,  F05D2260/81 ,  F05D2260/96 ,  Y10T29/49336

摘要： Flutter-resistant transonic turbomachinery blades and methods for reducing transonic turbomachinery blade flutter are provided. The flutter-resistant transonic turbomachinery blade comprises a transonic turbomachinery blade that includes opposite pressure and suction surfaces extending longitudinally in span from a root to an opposite tip, and extending axially in chord between opposite leading and trailing edges. The flutter-resistant transonic turbomachinery blade includes a local positive camber in or proximate a predicted local region of supersonic flow over the transonic turbomachinery blade. The method comprises predicting a local region of supersonic flow over the transonic turbomachinery blade and inducing the local positive camber to the transonic turbomachinery blade in or proximate the predicted region of supersonic flow.

公开(公告)号：US09765625B2

公开(公告)日：2017-09-19

申请号：US14283985

申请日：2014-05-21

申请人： MTU Aero Engines AG

发明人： Frank Stiehler ,  Andreas Hartung

IPC分类号： F01D5/10 ,  F01D5/14 ,  F01D5/18 ,  F01D5/22 ,  F01D5/24 ,  F01D5/26 ,  F01D9/02 ,  F01D25/06

CPC分类号： F01D5/10 ,  F01D5/14 ,  F01D5/18 ,  F01D5/22 ,  F01D5/225 ,  F01D5/24 ,  F01D5/26 ,  F01D9/02 ,  F01D25/06 ,  F05D2260/96 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/49336

摘要： A blade (1) for a turbomachine, including an impact chamber (2), a single impulse body (3) being situated in the impact chamber, a clearance (S1+S2) between the impulse body and the impact chamber being at least 10 μm and/or at most 1.5 mm in at least one direction.

公开(公告)号：US20170226874A1

公开(公告)日：2017-08-10

申请号：US15498520

申请日：2017-04-27

申请人： United Technologies Corporation

发明人： Changsheng Guo

IPC分类号： F01D5/30 ,  B23C5/10 ,  B23C3/34

CPC分类号： F01D5/3007 ,  B23C3/34 ,  B23C5/10 ,  B23C2215/52 ,  B23C2220/28 ,  B23C2220/366 ,  B24B19/022 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2250/71 ,  Y10T29/49336

摘要： A method of forming a curved slot in a turbine disk includes the steps of forming a pre-slot in the turbine disk and finishing the pre-slot to form a slot that receives a portion of a turbine blade. The turbine disk including a first face, an opposing second face, and an outer perimeter surface extending between the first face and the opposing second face. The pre-slot includes a first curved wall and a second curved wall that each extend between the first face and the opposing second face. An intersection between the outer perimeter surface and each of the first curved wall and the second curved wall is defined by a curved line.

公开(公告)号：US20170226856A1

公开(公告)日：2017-08-10

申请号：US15498045

申请日：2017-04-26

申请人： Mallen Research Limited Partnership

发明人： David Alton MCDANIEL, JR. ,  James W. NEWMAN, JR.

IPC分类号： F01C1/12 ,  F01C21/08 ,  F01C19/02

CPC分类号： F01C1/123 ,  F01C1/20 ,  F01C19/02 ,  F01C19/025 ,  F01C21/08 ,  F04C27/001 ,  F04C2230/60 ,  F04C2250/20 ,  F05B2230/60 ,  Y10T29/49229 ,  Y10T29/49336

摘要： A first rotor configured to rotate adjacent to a second rotor is disclosed. The second rotor includes a circular main body with a first axis of rotation and a vane extending radially from the main body. The first rotor includes a first curved surface that corresponds to a curve swept at a constant radius about a second axis of rotation, a second curved surface that corresponds to a curve swept by a leading edge of the vane when the second rotor is simultaneously rotated about the first axis of rotation and the second axis of rotation, a third curved surface that corresponds to a curve swept by a trailing edge of the vane when the second rotor is simultaneously rotated about the first axis of rotation and the second axis of rotation, and a vane-receiving groove disposed between the second curved surface and the third curved surface.

公开(公告)号：US09664052B2

公开(公告)日：2017-05-30

申请号：US13633928

申请日：2012-10-03

申请人： GENERAL ELECTRIC COMPANY

发明人： John McConnell Delvaux ,  Ronald Ralph Cairo ,  Jason Robert Parolini

IPC分类号： F01D5/14 ,  F01D5/28

CPC分类号： F01D5/282 ,  F01D5/288 ,  F05D2220/30 ,  F05D2260/941 ,  F05D2300/2261 ,  F05D2300/6012 ,  F05D2300/6033 ,  Y10T29/49336

摘要： A turbine component, a turbine blade, and a turbine component fabrication process are disclosed. The turbine component includes ceramic matrix composite plies and a feature configured for preventing interlaminar tension of the ceramic matrix composite plies. The feature is selected from the group consisting of ceramic matrix composite tows or precast insert tows extending through at least a portion of the ceramic matrix composite plies, a woven fabric having fiber tows or a precast insert preventing contact between a first set of the ceramic matrix composite plies and a second set of the ceramic matrix composite plies, and combinations thereof. The process includes laying up ceramic matrix composite plies in a preselected arrangement and securing a feature configured for interlaminar tension.