公开(公告)号：US20170044934A1

公开(公告)日：2017-02-16

申请号：US15209161

申请日：2016-07-13

Applicant: ROLLS-ROYCE plc

Inventor： Mark J. HICKLIN ,  Stephen O. OSIYEMI ,  Ewan F. THOMPSON

IPC: F01D25/24 ,  B29C65/48

CPC classification number: F01D25/243 ,  B29C65/18 ,  B29C65/48 ,  B29C65/4835 ,  B29C66/1122 ,  B29C66/53241 ,  B29C66/612 ,  B29C66/634 ,  B29C66/7212 ,  B29C66/72525 ,  B29C66/81433 ,  B29C66/81455 ,  B29C66/81457 ,  B29C66/82421 ,  B29C66/8322 ,  B29L2031/3076 ,  B29L2031/7504 ,  F01D11/127 ,  F01D21/045 ,  F01D25/24 ,  F01D25/285 ,  F02C7/045 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2230/23 ,  F05D2230/68 ,  F05D2260/962 ,  B29K2309/08

Abstract: A method is provided of bonding a first component to a second component. The method includes: locating the first component against the second component to form an interface between the components, a curable adhesive being provided at the interface; locating a pressurisable, fluid-filled bladder against the first component such that the first component is sandwiched between the second component and the bladder; locating a backing member against the bladder such that the bladder is sandwiched between the backing member and the first component; pressurising the bladder such that a consolidating pressure is exerted by the bladder on the first component to conform the first component to the second component; and curing the adhesive while the first component is conformed to the second component by the consolidating pressure.

Abstract translation: 提供了将第一组分结合到第二组分的方法。 该方法包括：将第一组件定位在第二组件上以形成组件之间的界面，在界面处设置可固化粘合剂; 将可加压流体填充的气囊定位在所述第一部件上，使得所述第一部件夹在所述第二部件和所述囊之间; 将支撑构件定位抵靠所述囊，使得所述囊被夹在所述背衬构件和所述第一构件之间; 对气囊进行加压，使得气囊在第一部件上施加固结压力以使第一部件与第二部件一致; 并且通过合并压力使第一部件与第二部件一致地固化粘合剂。

公开(公告)号：US20180094531A1

公开(公告)日：2018-04-05

申请号：US15699314

申请日：2017-09-08

Applicant: ROLLS-ROYCE plc

Inventor： Mark J. HICKLIN ,  Neil A. SHIPLEY ,  Daniel J. SWAN

IPC: F01D11/00

CPC classification number: F01D11/006 ,  F01D11/008 ,  F05D2240/304 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2240/55 ,  Y02T50/672

Abstract: A rotatable arrangement for a gas turbine engine comprises a plurality of blades having an aerofoil profile with a suction side, a pressure side, a leading edge and a trailing edge. A plurality of annulus fillers are provided between adjacent blades. A pressure side seal extends between a blade and an annulus filler on the pressure side of the blade, and a suction side seal extends between the blade and an annulus filler on the suction side of the blade. The suction side seal comprises a blocking member provided at an end of the suction side seal proximal to the trailing edge of the blade, the blocking member being configured to restrict recirculation of flow along the suction side of the blade.