公开(公告)号：US20140093392A1

公开(公告)日：2014-04-03

申请号：US14044527

申请日：2013-10-02

Applicant: ROLLS-ROYCE PLC

Inventor： Ian TIBBOTT ,  Dougal Richard JACKSON

IPC: F01D5/18

CPC classification number: F01D5/188 ,  B33Y80/00 ,  F01D5/189 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/30 ,  Y10T29/49332 ,  Y10T29/49336

Abstract: Described is a gas turbine engine component (100), comprising a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises multiple separate parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; wherein the assembled insert includes at least one retention part, the retention part engaging with a wall of the cavity and at least one other insert part so as to retain the assembled insert within the cavity.

Abstract translation: 描述了一种燃气涡轮发动机部件（100），其包括具有用于接收多部件插入件的内部空腔的壳体; 多部分插入件位于空腔内，其中多部件插入件包括在空腔内以彼此相邻的关系组装的多个分离部件，以提供多部件插入件; 其中所述组装的插入件包括至少一个保持部件，所述保持部件与所述腔体的壁接合，以及与所述至少一个其它插入部件接合，以将所述组装的插入件保持在所述腔体内。

公开(公告)号：US20140093379A1

公开(公告)日：2014-04-03

申请号：US14044460

申请日：2013-10-02

Applicant: Rolls-Royce PLC

Inventor： Ian TIBBOTT ,  Dougal Richard JACKSON

IPC: F01D5/18

CPC classification number: F01D5/188 ,  B33Y80/00 ,  F01D5/189 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/30 ,  Y10T29/49332 ,  Y10T29/49336

Abstract: A gas turbine engine component is described which (100), comprises: a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises separate insert parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; an insertion aperture within a wall of the shell which is sized to receive each of the insert parts individually and wherein the multi-part insert cannot be withdrawn from the cavity through the insertion aperture when assembled.

Abstract translation: 描述了一种燃气涡轮发动机部件，其中（100）包括：壳体，具有用于容纳多部件插入件的内部空腔; 多部分插入件位于空腔内，其中多部件插入件包括在空腔内以彼此邻接的方式组装成分开的插入部件以提供多部件插入件; 壳体的壁内的插入孔，其尺寸设计成分别容纳每个插入件，并且其中当组装时，多部件插入件不能通过插入孔从空腔中抽出。

公开(公告)号：US20170356296A1

公开(公告)日：2017-12-14

申请号：US15687960

申请日：2017-08-28

Applicant: ROLLS-ROYCE PLC

Inventor： Ian TIBBOTT ,  Dougal Richard JACKSON

IPC: F01D5/18 ,  B33Y80/00

CPC classification number: F01D5/188 ,  B33Y80/00 ,  F01D5/189 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/30 ,  Y10T29/49332 ,  Y10T29/49336

Abstract: Described is a gas turbine engine component (100), comprising a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises multiple separate parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; wherein the assembled insert includes at least one retention part, the retention part engaging with a wall of the cavity and at least one other insert part so as to retain the assembled insert within the cavity.

公开(公告)号：US20150044029A1

公开(公告)日：2015-02-12

申请号：US14333033

申请日：2014-07-16

Applicant: ROLLS-ROYCE PLC

Inventor： Ian TIBBOTT ,  Dougal Richard JACKSON

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/18 ,  F01D5/187 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/22141

Abstract: An aerofoil component of a gas turbine engine has an aerofoil portion which spans, in use, a working gas annulus of the engine. The aerofoil portion has a pressure side outer wall and a suction side outer wall, each extending from the leading edge to the trailing edge of the aerofoil portion. The aerofoil portion further has one or more main passages which extend in the annulus-spanning direction of the aerofoil portion and which receive, in use, a flow of coolant. The aerofoil portion further has one or more suction wall passages which extend in the annulus-spanning direction of the aerofoil portion and which receive, in use, a flow of coolant, each suction wall passage being bounded on opposing first sides by the suction side outer wall and an inner wall of the aerofoil portion, the inner wall separating the suction wall passages from the main passages.

Abstract translation: 燃气涡轮发动机的机翼部件具有在使用中跨越发动机的工作气体环空的机翼部分。 机翼部分具有压力侧外壁和吸力侧外壁，每个从机翼部分的前缘延伸到后缘。 机翼部分还具有沿着机翼部分的环形跨越方向延伸并且在使用中接收冷却剂流的一个或多个主通道。 机翼部分还具有一个或多个抽吸壁通道，其在机翼部分的环形跨越方向上延伸，并且在使用中接收冷却剂流，每个吸入壁通道由相对的第一侧由吸力侧外部限定 壁和机翼部分的内壁，内壁将吸力壁通道与主通道分开。

公开(公告)号：US20160097286A1

公开(公告)日：2016-04-07

申请号：US14846284

申请日：2015-09-04

Applicant: ROLLS-ROYCE PLC

Inventor： Ian TIBBOTT ,  Peter Thomas IRELAND ,  Anthony John RAWLINSON ,  Irene CRESCI

IPC: F01D5/18 ,  F01D9/06

CPC classification number: F01D5/188 ,  F01D5/189 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2260/201 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine component, especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber for passage of cooling air, the chamber including leading edge portion and one inlet portion via which cooling air may enter the chamber from feed source, wherein the component includes a partitioning element, e.g. curved or scoop-shaped partitioning plate or wall, provided in the chamber inlet portion and defining within the inlet portion a sub-chamber adjacent the leading edge portion, and wherein partitioning element is configured so the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of inlet portion. The reduced velocity of the cooling air in the sub-chamber adjacent the leading edge serves to increase pressure therein, thereby maintaining desired backflow pressure margin between the feed pressure of the cooling air delivered to the showerhead holes and the gas-path from the combustor.

Abstract translation: 一种燃气涡轮发动机部件，特别是翼型截面喷嘴引导叶片（NGV），其具有用于冷却空气通过的至少一个内部冷却室，所述内部冷却室包括前缘部分和一个入口部分，冷却空气可通过该入口部分从冷却空气进入室 进料源，其中所述组件包括分隔元件，例如 弯曲或铲形的分隔板或壁，设置在室入口部分中，并且在入口部分内限定与前缘部分相邻的子室，并且其中分隔元件被构造成使得子室中的冷却空气速度较小 比进口部分的剩余部分中的冷却风速快。 靠近前缘的副室中的冷却空气的减小的速度用于增加其中的压力，从而在输送到喷头孔的冷却空气的进料压力和来自燃烧器的气体路径之间保持期望的回流压力裕度。

公开(公告)号：US20180230836A1

公开(公告)日：2018-08-16

申请号：US15895068

申请日：2018-02-13

Applicant: ROLLS-ROYCE plc

Inventor： Ian TIBBOTT ,  Roderick M. TOWNES ,  Andrew KING

IPC: F01D9/04 ,  F01D25/12

CPC classification number: F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/80 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/205

Abstract: There is disclosed a stator vane section for a gas turbine engine. The stator vane comprises an aerofoil, a first platform at a radial end of the aerofoil, a cooling chamber within the aerofoil and a guide duct within the cooling chamber. An impingement chamber is defined between the first platform and a perforated impingement plate provided on the first platform to receive cooling air through the impingement plate. The guide duct is coupled to the first platform so that a collecting chamber extending around the guide duct is defined between the guide duct and the first platform and the collecting chamber is configured to receive cooling air from the impingement chamber via a plurality of collecting channels, and is configured to direct cooling air to the cooling chamber.

公开(公告)号：US20160032764A1

公开(公告)日：2016-02-04

申请号：US14810551

申请日：2015-07-28

Applicant: ROLLS-ROYCE PLC

Inventor： Ian TIBBOTT ,  Dougal Richard JACKSON

IPC: F01D25/12 ,  F01D9/04

CPC classification number: F01D25/12 ,  F01D5/186 ,  F01D5/187 ,  F01D9/023 ,  F01D9/041 ,  F01D9/047 ,  F05D2220/32 ,  F05D2240/128 ,  F05D2240/81 ,  F05D2250/14 ,  F05D2250/18 ,  F05D2250/184 ,  F05D2260/202

Abstract: An end-wall component of the mainstream gas annulus of a gas turbine engine having an annular arrangement of vanes, the component including a cooling arrangement having ballistic cooling holes (33) through which, in use, dilution cooling air is jetted into the mainstream gas upstream of the vanes to reduce the mainstream gas temperature adjacent the end-wall, wherein the cooling holes are arranged in one or more circumferentially extending rows and wherein the axial position of the cooling holes in the or each row varies.

Abstract translation: 具有叶片环形布置的燃气涡轮发动机的主流气体环的端壁部件，该部件包括具有弹道冷却孔（33）的冷却装置，在使用中将稀释冷却空气喷射到主流气体 在叶片的上游，以减少邻近端壁的主流气体温度，其中冷却孔布置在一个或多个沿圆周方向延伸的行中，并且其中每排中的冷却孔的轴向位置变化。

公开(公告)号：US20140140860A1

公开(公告)日：2014-05-22

申请号：US13734491

申请日：2013-01-04

Applicant: ROLLS-ROYCE PLC

Inventor： Ian TIBBOTT ,  Dougal Richard JACKSON

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F01D5/188 ,  F05D2250/15 ,  F05D2250/25

Abstract: An aerofoil component of a gas turbine engine is provided. The component has a longitudinally extending aerofoil portion which spans, in use, a working gas annulus of the engine. The aerofoil portion contains an internal chamber for a flow of coolant. The chamber includes a helical passage which spirals in a plurality of turns around an axis that extends in the length direction of the aerofoil portion.

Abstract translation: 提供燃气涡轮发动机的机翼部件。 该部件具有在使用中跨越发动机的工作气体环的纵向延伸的机翼部分。 机翼部分包含用于冷却剂流动的内部室。 该腔室包括螺旋通道，螺旋通道围绕在机翼部分的长度方向上延伸的轴线以多个匝旋转。

公开(公告)号：US20140086724A1

公开(公告)日：2014-03-27

申请号：US14033900

申请日：2013-09-23

Applicant: ROLLS-ROYCE PLC

Inventor： Ian TIBBOTT ,  Dougal Richard JACKSON

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  F05D2260/22141 ,  Y10T29/49336

Abstract: An internally cooled gas turbine engine component has a line of cooling air discharge holes, an internal cooling channel, an internal feed cavity for feeding cooling air from the channel to the discharge holes, and flow disrupting pedestals arranged in rows. A method of configuring the component includes:determining angles α and β of the directions of cooling air flow into the first and Nth rows, respectively;defining a change in angle φ of the direction of cooling air flow between rows as φ=(β−α)/N; andpositioning the pedestals such that a line extending forward from the centre of each pedestal in the ith row at an angle {α+φ(i−1)} intersects the (i −1)th row at a location which is midway between two neighbouring pedestals of the (i−1)th row, i being an integer from 2 to N.

Abstract translation: 内部冷却的燃气涡轮发动机部件具有一排冷却空气排出孔，内部冷却通道，用于将冷却空气从通道供给到排出孔的内部进料腔和排列成行的流动中断基座。 配置组件的方法包括：确定角度α和＆bgr; 分别进入第一和第N行的冷却空气流的方向; 定义角度变化 行（=（＆bgr;-α）/ N）之间的冷却空气流动方向; 并且将所述基座定位成使得从第i行中的每个基座的中心向前延伸的线以一定角度{α+＆phgr（i-1）}）与第（i-1）行相交，位于第 （i-1）行的两个相邻基座，i是从2到N的整数。