公开(公告)号：US20170022817A1

公开(公告)日：2017-01-26

申请号：US15202120

申请日：2016-07-05

Applicant: ROLLS-ROYCE plc

Inventor： Bogachan ALPAN ,  Keith C. SADLER ,  David J. HUNT

IPC: F01D5/08 ,  F01D5/18 ,  F02K3/06

CPC classification number: F01D5/081 ,  F01D5/082 ,  F01D5/187 ,  F01D5/3015 ,  F01D11/006 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/301

Abstract: A turbine blade having labyrinth of internal channels for circulation of coolant, the novel labyrinth geometry includes; inlet arranged on axially upstream face of terminal portion leading to an upstream duct portion having first section adjacent the inlet and a second section, the second section having reduced cross section compared to first section; a first passage intersecting first section and extending through the blade body towards tip of the blade, a proximal end of leading edge passage arranged to capture incoming air flow; a main blade passage intersecting a downstream duct portion, the downstream duct portion arranged in axial alignment with the upstream duct portion but separate from upstream duct portion; and a restrictor passage intersecting with the mid-blade passage and extending towards a mid-blade duct portion, the mid-blade duct portion in axial alignment with the upstream and downstream duct portions and in fluid communication with the upstream duct portion.

Abstract translation: 具有用于冷却剂循环的内部通道迷宫的涡轮机叶片，该新颖的迷宫几何形状包括： 入口布置在端子部分的轴向上游面上，通向具有与入口相邻的第一部分的上游管道部分和第二部分，第二部分与第一部分相比具有减小的横截面; 第一通道与第一部分相交并且延伸穿过叶片本体朝向叶片的尖端，前缘通道的近端布置成捕获进入的空气流; 与下游管道部分相交的主叶片通道，下游管道部分与上游管道部分轴向对准，但与上游管道部分分离; 以及与所述中叶通道相交并且朝向中间叶片管道部分延伸的限流器通道，所述中间叶片管道部分与所述上游管道部分和所述下游管道部分轴向对准并且与所述上游管道部分流体连通。

公开(公告)号：US20200263553A1

公开(公告)日：2020-08-20

申请号：US16700335

申请日：2019-12-02

Applicant: Rolls-Royce Deutschland Ltd & Co KG ,  Rolls-Royce plc

Inventor： Hamish SWEIDAN ,  Keith C. SADLER ,  Roderick M. TOWNES

IPC: F01D5/18 ,  F01D5/08

Abstract: A cooled turbine rotor blade for a gas turbine engine includes an airfoil and a profiled root radially inward of the airfoil, a platform between the airfoil and the root, and a cooling air supply channel extending through the platform into an interior of the airfoil and therein up to an outlet opening. An inlet opening of the cooling air supply channel is located at the rear side of the rotor blade, and an inlet part of the cooling air supply channel with the inlet opening is angled into the direction of rotation of the rotor blade and curved into a radially outward direction. Further, a rotor-stator stage for a gas turbine includes a rotor blade as above, and an air cavity radially inwards of sealing features between the rotor stage and a neighboring downstream stator stage to form a source of cooling air for the rotor blade.

公开(公告)号：US20190309681A1

公开(公告)日：2019-10-10

申请号：US16352014

申请日：2019-03-13

Applicant: ROLLS-ROYCE plc

Inventor： Roderick M. TOWNES ,  Keith C. SADLER

IPC: F02C3/13 ,  F02C7/36 ,  F02C3/10 ,  F02C7/268 ,  F02K3/06 ,  F02C9/16

Abstract: A turbine arrangement for gas turbine engine, the arrangement comprising a high pressure turbine mounted on a high pressure shaft and a low pressure turbine mounted on a low pressure shaft, wherein the high pressure turbine comprises a single stage turbine rotor configured to rotate in a first direction, and wherein the low pressure turbine comprises three or more rotors (19a, b, c) configured to rotate in a second direction opposite to the first direction. The low pressure turbine is closely coupled to the high pressure turbine with no stator vanes provided between the two.

公开(公告)号：US20160305248A1

公开(公告)日：2016-10-20

申请号：US15082416

申请日：2016-03-28

Applicant: ROLLS-ROYCE plc

Inventor： Keith C. SADLER ,  Frederic GOENAGA ,  Andrew J. MYLREA

IPC: F01D5/08 ,  F01D25/12

CPC classification number: F01D5/082 ,  F01D5/081 ,  F01D25/12 ,  F05D2260/14 ,  F05D2260/20

Abstract: A coolant feed arrangement for delivering coolant to an axially facing surface of a rotor disc configured for carrying a row of turbine blades on its radially outer surface, the coolant delivered through a conduit upstream of the rotor disc, which has an outlet arranged radially inwardly of the blades and directed at the axially facing surface, the arrangement including two or more impediments; at least one impediment including a work extractor device arranged in the conduit to extract work from the coolant on route to a last impediment arranged at or adjacent the outlet, the last impediment including a row of static nozzles configured for accelerating the flow of coolant circumferentially in the direction of rotation of the axially facing surface of the disc whereby to match the speed and direction of rotation of the axially facing surface as the coolant is delivered to the axially facing surface.

Abstract translation: 一种冷却剂供给装置，用于将冷却剂输送到转子盘的面向轴向的表面，所述转子盘构造成用于在其径向外表面上承载一排涡轮叶片，所述冷却剂通过转子盘上游的导管输送， 叶片并且指向轴向面向的表面，该装置包括两个或更多个障碍物; 至少一个障碍物，其包括布置在导管中的工作提取器装置，用于在布置在出口处或邻近出口处的路线上从冷却剂中提取工作，最后一个障碍物包括一排静止喷嘴，其被配置用于加速周向冷却剂中的冷却剂流 盘的轴向面向表面的旋转方向，从而当冷却剂被输送到面向轴向的表面时，以匹配轴向面向表面的旋转速度和方向。

公开(公告)号：US20180202361A1

公开(公告)日：2018-07-19

申请号：US15869165

申请日：2018-01-12

Applicant: ROLLS-ROYCE plc

Inventor： Keith C. SADLER

IPC: F02C7/18 ,  F02C9/18 ,  F02C9/20 ,  F01D11/24 ,  F16K31/126

CPC classification number: F02C7/18 ,  F01D5/081 ,  F01D11/24 ,  F02C6/08 ,  F02C9/18 ,  F02C9/20 ,  F05D2260/201 ,  F05D2260/606 ,  F05D2270/42 ,  F05D2270/58 ,  F16K17/087 ,  F16K31/126

Abstract: There is disclosed a pressure responsive valve 352 for controlling a cooling flow through an orifice 320 in a gas turbine assembly 300. The valve 352 comprises an attachment point 360, a valve element 358, and a compressible valve body 354 defining a chamber 355 for sealing a volume of compressible gas. The valve body 354 is configured to act between the attachment point 360 and the valve element 358 so that in use expansion or contraction of the valve body 354 in response to external pressure causes the valve element 358 to move relative the orifice 320. A corresponding kit, method of installation and gas turbine assembly are disclosed.