公开(公告)号：US20170089358A1

公开(公告)日：2017-03-30

申请号：US15256099

申请日：2016-09-02

Applicant: ROLLS-ROYCE plc

Inventor： Steven A. RADOMSKI ,  Simon READ

IPC: F04D29/52 ,  F04D29/66 ,  F04D29/64 ,  F04D29/58

CPC classification number: F04D29/522 ,  F01D21/045 ,  F01D25/24 ,  F04D29/526 ,  F05B2220/302 ,  F05B2230/232 ,  F05B2230/60 ,  F05B2280/6012 ,  F05D2230/51 ,  F05D2230/54 ,  F05D2250/75 ,  F05D2260/36 ,  F05D2300/612 ,  Y02T50/671

Abstract: A gas turbine engine casing 2 comprising: an inner circumferential wall 12; an outer circumferential wall 14 spaced radially outwardly from the inner wall 12; wherein the inner and outer circumferential walls 12, 14 are formed by an axially repeating profile comprising an inner wall portion 6 and an outer wall portion 8 connected to one another by an intermediate portion 10, the axially repeating profile being arranged such that the inner wall portion 6 abuts against and is connected to an adjacent inner wall portion 6 to form the inner circumferential wall 12 and the outer wall portion 8 abuts against and is connected to an adjacent outer wall portion 8 to form the outer circumferential wall 14.

公开(公告)号：US20160003057A1

公开(公告)日：2016-01-07

申请号：US14728618

申请日：2015-06-02

Applicant: ROLLS-ROYCE PLC

Inventor： Simon READ ,  Matthew D. CURREN

IPC: F01D5/20

CPC classification number: F01D5/20 ,  F05D2220/36 ,  F05D2260/37 ,  F05D2260/38 ,  F05D2300/501 ,  F05D2300/506

Abstract: A rotary blade tip insert for incorporation into a rotary blade, for example, a rotary fan blade in a gas turbine engine. The tip insert comprises a sleeve for insertion into a recess provided in said rotary blade. The sleeve has a radially outer end defining an opening, a radially inner end and opposing wall portions extending between said ends. The tip insert further comprises a tip element having a crown portion and a root portion for insertion into the opening of said sleeve.

Abstract translation: 用于结合到旋转刀片中的旋转刀片刀片插入件，例如在燃气涡轮发动机中的旋转风扇叶片。 尖端插入物包括用于插入设置在所述旋转叶片中的凹部中的套筒。 套管具有限定开口的径向外端，径向内端和在所述端部之间延伸的相对壁部。 尖端插入件还包括具有冠状部分和用于插入到所述套筒的开口中的根部的尖端元件。

公开(公告)号：US20150104306A1

公开(公告)日：2015-04-16

申请号：US14505956

申请日：2014-10-03

Applicant: ROLLS-ROYCE PLC

Inventor： Steven Aleksy RADOMSKI ,  Simon READ

IPC: F04D29/64 ,  F04D19/00 ,  F04D29/02

CPC classification number: F01D25/24 ,  F01D11/122 ,  F01D21/045 ,  F02C7/04 ,  F04D19/002 ,  F04D29/023 ,  F05D2220/36 ,  F05D2250/25 ,  F05D2300/522 ,  F05D2300/615 ,  Y10T29/49245

Abstract: A fan casing arrangement for a gas turbine engine having a propulsive fan, the arrangement having a fan case and a fan track liner and being configured to circumscribe the fan, wherein the fan track liner is provided around the inside of fan case so as to adopt a radial position between the fan and the fan case. The fan track liner includes an elongate member which is helically-wound against the inside of the fan case in a plurality of turns. A method of installing a fan track liner in a fan casing arrangement for a gas turbine engine having a propulsive fan, the method involving: providing a fan case to circumscribe the fan, providing a flexible and elongate liner member, and helically winding the liner member against the inside of the fan case in a plurality of turns to define at least part of the fan track liner.

Abstract translation: 一种用于具有推进风扇的燃气涡轮发动机的风扇壳体装置，该装置具有风扇壳体和风扇轨道衬套，并且构造成围绕风扇，其中，风扇履带衬套围绕风扇壳体的内部设置，以便采用 风扇和风扇外壳之间的径向位置。 风扇履带板包括细长构件，其以多个匝螺旋缠绕在风扇壳体的内部。 一种在具有推进风扇的燃气涡轮发动机的风扇壳体装置中安装风扇轨道衬套的方法，所述方法包括：提供风扇壳体以包围风扇，提供柔性和细长的衬垫构件，以及螺旋地卷绕衬套构件 以多个匝相对于风扇壳体的内部限定至少一部分风扇轨道衬套。

公开(公告)号：US20170022826A1

公开(公告)日：2017-01-26

申请号：US15204694

申请日：2016-07-07

Applicant: ROLLS-ROYCE plc

Inventor： Simon READ ,  Steven A. RADOMSKI

IPC: F01D5/28 ,  F01D9/02

CPC classification number: F01D5/28 ,  F01D5/147 ,  F01D5/288 ,  F01D9/02 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/30 ,  F05D2230/31 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2300/17 ,  F05D2300/50 ,  F05D2300/605 ,  Y02T50/672 ,  Y02T50/673

Abstract: A blade or a vane for a gas turbine engine. The blade or vane comprising an aerofoil and a leading edge member attached to the aerofoil. The leading edge comprises an electrically conductive support member and a nano-coating formed on the support member.

Abstract translation: 用于燃气涡轮发动机的叶片或叶片。 叶片或叶片包括机翼和连接到机翼的前缘部件。 前缘包括形成在支撑构件上的导电支撑构件和纳米涂层。

公开(公告)号：US20160169043A1

公开(公告)日：2016-06-16

申请号：US14941095

申请日：2015-11-13

Applicant: ROLLS-ROYCE PLC

Inventor： Simon READ ,  Steven A. RADOMSKI

IPC: F01D25/24 ,  F01D11/12 ,  F01D21/04

CPC classification number: F01D25/24 ,  F01D11/125 ,  F01D11/127 ,  F01D21/045 ,  F04D29/522 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/55 ,  F05D2250/283 ,  F05D2260/37 ,  F05D2300/43 ,  F05D2300/501 ,  F05D2300/603

Abstract: There is proposed a fan casing arrangement for a gas turbine engine (10) of a type having a propulsive fan (12), the fan casing arrangement being configured to circumscribe the fan (12) and having a fan case (24) and a fan track liner. The fan track liner is provided around the inside of the fan case (24) so as to adopt a radial position between the fan (12) and the fan case (24), and the arrangement is configured such that the fan track liner includes a liner ring (25) which is radially outwardly biased against the inside of the fan case (24). A related method of installing a fan track liner in a gas turbine engine is also disclosed.

Abstract translation: 提出了一种用于具有推进风扇（12）类型的燃气涡轮发动机（10）的风扇壳体装置，风扇壳体装置被配置为围绕风扇（12）并具有风扇壳体（24）和风扇 轨道班轮 风扇导轨衬套设置在风扇壳体24的内部周围，以便在风扇12和风扇壳体24之间采用径向位置，并且该结构构造成使得风扇履带衬板包括一个 衬套环（25），其径向向外偏压抵靠风扇壳体（24）的内部。 还公开了一种在燃气涡轮发动机中安装风扇轨道衬套的相关方法。