公开(公告)号：US20140245741A1

公开(公告)日：2014-09-04

申请号：US14192363

申请日：2014-02-27

Applicant: ROLLS-ROYCE PLC

Inventor： Li HE ,  Amir RAHIM ,  Bidur KHANAL ,  Eduardo ROMERO

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D5/145 ,  F01D5/146 ,  F05D2250/38 ,  F05D2250/73

Abstract: In a gas turbine engine, each vane has pressure and suction surfaces extending radially from an inner to outer endwall of an annular working gas engine passage, and extending axially from a leading to a trailing edge of the vane. Each vane has transverse sections providing respective aerofoil sections. Neighbouring vanes are arranged in unequally-shaped pairs in which either: (i) the first vane of each pair exhibits compound lean, and the second vane of the pair exhibits reverse compound lean or has substantially no tangential lean, (ii) the first vane of each pair has substantially no tangential lean, and the second vane of the pair exhibits reverse compound lean, or (iii) the first vane of each pair exhibits reverse compound lean, and the second vane of the pair exhibits greater reverse compound lean. Within each unequally-shaped pair the first vane is on the pressure surface side of the second vane.

Abstract translation: 在燃气涡轮发动机中，每个叶片具有从环形工作燃气发动机通道的内壁到外端壁的径向延伸的压力和吸力表面，并从叶片的导向到后缘轴向延伸。 每个叶片具有提供相应机翼部分的横截面。 相邻叶片布置成不均匀的对，其中：（i）每对的第一叶片表现出复合稀薄，并且该对的第二叶片表现出相反的复合物倾斜或基本上没有切向倾斜，（ii）第一叶片 每对的基本上没有切向倾斜，并且该对的第二叶片显示相反的复合稀薄，或（iii）每对的第一叶片表现出相反的复合稀薄，并且该对的第二叶片显示更大的反向化合物浓度。 在每个不相等的对中，第一叶片在第二叶片的压力表面侧上。

公开(公告)号：US20230250776A1

公开(公告)日：2023-08-10

申请号：US18093091

申请日：2023-01-04

Applicant: ROLLS-ROYCE PLC

Inventor： Ashley POWELL ,  Andrew WILKINSON ,  Eduardo ROMERO

IPC: F02K3/10 ,  F23R3/20

CPC classification number: F02K3/10 ,  F23R3/20 ,  F05D2220/323 ,  F05D2240/35

Abstract: A reheat assembly for a gas turbine engine includes; a jetpipe casing defining a reheat core section configured to duct a core flow of air and a reheat bypass section configured to duct a bypass flow of air. The reheat bypass section is disposed radially outward of the reheat core section, and the reheat core section and the reheat bypass section are at least partially separated by a support duct. An integrated flameholder is mounted to the jetpipe casing, and a fuel pipe is configured to convey fuel to the integrated flameholder. The integrated flameholder includes a flameholder body extending radially inward from the jetpipe casing through the reheat bypass section and into the reheat core section to promote a wake-stabilised region downstream of the body; and an integrated atomiser configured to atomise fuel provided to the integrated flameholder and to discharge the atomised fuel into the wake stabilised region.

公开(公告)号：US20230250757A1

公开(公告)日：2023-08-10

申请号：US18149895

申请日：2023-01-04

Applicant: ROLLS-ROYCE PLC

Inventor： Ashley POWELL ,  Andrew WILKINSON ,  Eduardo ROMERO

IPC: F02C7/10 ,  F02C7/22

CPC classification number: F02C7/10 ,  F02C7/22 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213

Abstract: A reheat assembly for a gas turbine engine includes: a jetpipe casing including: a reheat core section configured to convey a core flow of air from a reheat core inlet to a reheat core outlet; and a reheat bypass section configured to convey a bypass flow of air from a reheat bypass inlet to a reheat bypass outlet radially outward of the reheat core section, wherein the reheat core and reheat bypass sections are radially separated at the reheat core and reheat bypass inlets by a support duct within the jetpipe casing; a reheat arrangement including a radially extending flameholder and a plurality of fuel injection ports including a plurality of core fuel injection ports, wherein: the flameholder is configured to promote a formation of a core flow wake-stabilised region within the core flow of air downstream of the flameholder; and each of the plurality of core fuel injection ports are: circumferentially aligned with the flameholder upstream of the core flow wake-stabilised region, configured to discharge a respective flow of fuel into the reheat core section for mixing with the core flow of air, and offset with respect to one another along a radial direction of the jetpipe casing.

公开(公告)号：US20200224875A1

公开(公告)日：2020-07-16

申请号：US16720412

申请日：2019-12-19

Applicant: ROLLS-ROYCE plc

Inventor： Alexander V. MURRAY ,  Peter T. IRELAND ,  Eduardo ROMERO ,  Anthony J. RAWLINSON

IPC: F23R3/00

Abstract: There is disclosed wall cooling system 50 having a double-wall geometry. A first wall 55 and a second wall 60 extend over a plan area with the second wall spaced from the first wall by a gap. The first wall 55 has multiple upstanding members 65 spanning the gap and contacting the second wall 60 such that the first and second walls are mechanically and thermally connected. The first wall 55 is shaped so as to provide a two-dimensional array of crests 85 and recesses 90. The crests 85 are spaced from the second wall 60. The first wall 55 has a plurality of through-holes 70 for flow of coolant through the first wall and into the gap. The cooling system 50 is suitable for use in a gas turbine engine 10, for example in the turbine 17, 19.

公开(公告)号：US20190323359A1

公开(公告)日：2019-10-24

申请号：US16378800

申请日：2019-04-09

Applicant: ROLLS-ROYCE plc

Inventor： Peter T. IRELAND ,  Nicholas Russell GREEN ,  Eduardo ROMERO ,  Gladys C. NGETICH

IPC: F01D5/18 ,  F01D25/12 ,  B23P15/02

Abstract: Disclosed herein is a method of manufacturing a double walled section of an aerofoil (701) of a gas turbine engine (10), the method comprising: forming a plurality of columns (402) on an outer surface of a first structure; forming a plurality of columns (402) on a surface of each of a plurality of parts of a second structure; and forming a double walled section of an aerofoil (701) by attaching the ends of columns (402) on each part of the second structure to the ends of columns (402) on the first structure such that the first structure is an inner wall (401) of the section of the aerofoil (701) and the second structure is an outer wall (501) of the section of the aerofoil (701).