公开(公告)号：US20180195404A1

公开(公告)日：2018-07-12

申请号：US15844745

申请日：2017-12-18

Applicant: ROLLS-ROYCE plc

Inventor： Simon PITT

IPC: F01D11/24

Abstract: A turbine case cooling system comprises a manifold (21) radially adjacent a portion of a radially outer surface of the turbine case (26) and in fluid communication with one or more of radially inwardly directed outlets (25). The manifold (21) has a first inlet (22) and a second inlet (23). The first inlet (22) is obstructed by a first flow restrictor (22a) and the second inlet (23) is obstructed by a second flow restrictor (23a). The first inlet (22) includes a valve (24) upstream of the first flow restrictor (22a) and the valve is adjustable to control flow of fluid supply entering the first inlet (22).

公开(公告)号：US20180291763A1

公开(公告)日：2018-10-11

申请号：US15945753

申请日：2018-04-05

Applicant: ROLLS-ROYCE plc

Inventor： Simon PITT

IPC: F01D25/12 ,  F01D9/04

CPC classification number: F01D25/12 ,  F01D9/02 ,  F01D9/023 ,  F01D9/041 ,  F01D9/06 ,  F01D9/065 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/201 ,  Y02T50/675

Abstract: A vane cooling system for a gas turbine engine comprises a vane (21) arranged on a stator and having a chamber (23) extending continuously from a radially inner end to a radially outer end of the vane. The vane (21) has; a radially inner inlet (24) and a radially outer inlet (25), a first cooling fluid feed (39) in communication with the radially inner inlet (24) and a second cooling fluid feed (28) in communication with the radially outer inlet (25), The first cooling fluid feed (39) has a higher pressure than the second cooling feed (28). A flow adjustment device (30) is arranged for adjusting a flow of the second cooling fluid feed into the radially outer inlet (25).

公开(公告)号：US20240167393A1

公开(公告)日：2024-05-23

申请号：US18386049

申请日：2023-11-01

Applicant: ROLLS-ROYCE plc

Inventor： Simon PITT

IPC: F01D21/00 ,  G01B13/18

CPC classification number: F01D21/003 ,  G01B13/18 ,  F05D2270/80

Abstract: A probe for determining the swirl angle of the exhaust gasses of a turbine engine, has an elongate body with a fastener, the elongate body having a tip at its proximal end and a head at its distal end, the elongate body having at least two passageways extending from the tip to the head, each passageway having an aperture at the tip and a port at the head which is connectable to a pressure sensor.

公开(公告)号：US20170107842A1

公开(公告)日：2017-04-20

申请号：US15268306

申请日：2016-09-16

Applicant: ROLLS-ROYCE plc

Inventor： Simon PITT

IPC: F01D11/12 ,  F01D25/24 ,  F01D25/12 ,  F01D21/00

CPC classification number: F01D11/122 ,  F01D9/04 ,  F01D17/02 ,  F01D21/003 ,  F01D25/12 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/31

Abstract: An assembly for mounting a circumferential shroud to a casing, including a plurality of arcuate shroud segments collectively forming the circumferential shroud. Each segment includes a circumferentially extending wall and a channel extending from the wall. The channel is receivable in a hole passing through a circumferential casing and has a first connector. A fastener has a head and a shank, which is receivable in the channel and has a second connector that engages with the first connector. A first spacer receives the channel and a second spacer receives the shank and sit adjacent the head of the fastener on either side of the casing. The spacers can be selected to adjust for optimal radial positioning of the shroud and of probes received within a space defined between the casing and the shroud for monitoring rotor speed and the tip air gap of a turbine rotor contained in the casing.

公开(公告)号：US20180347391A1

公开(公告)日：2018-12-06

申请号：US15995525

申请日：2018-06-01

Applicant: ROLLS-ROYCE plc

Inventor： Leo V. LEWIS ,  Simon PITT

IPC: F01D11/24 ,  F01D25/14

CPC classification number: F01D11/24 ,  F01D11/005 ,  F01D11/10 ,  F01D25/246 ,  F05D2240/11

Abstract: A clearance control arrangement (26) for a rotor (28), the arrangement comprising a rotor and a casing (32) radially outside the rotor. An annular array of segment assemblies (33) mounted to the casing and radially spaced from the rotor by a clearance (42). Each segment assembly comprising a heat transfer cavity (48) radially adjacent to the casing. A birdmouth cavity (66) towards the rear of the segment assembly. A bypass hole (68) configured to deliver air to the birdmouth cavity to reduce the amount of air which leaks from the heat transfer cavity to the birdmouth cavity.

公开(公告)号：US20180291747A1

公开(公告)日：2018-10-11

申请号：US15945755

申请日：2018-04-05

Applicant: ROLLS-ROYCE plc

Inventor： Simon PITT

IPC: F01D5/18 ,  F01D9/04

Abstract: A vane cooling system for a gas turbine engine comprises a vane (20a) arranged on a stator and having a chamber (27,28) extending continuously from a radially inner end to a radially outer end of the vane. The vane (20a) has a first inlet (41) and a second inlet (42). A first cooling fluid feed (54) in communication with the first inlet (41) and a second cooling fluid feed (43) in communication with the second inlet (42). The first cooling fluid feed (54) has a higher pressure than the second cooling fluid feed (43). A flow adjustment device (45) is arranged for adjusting a flow of the second cooling fluid feed (43) into the second inlet (42). The chamber is divided by a restrictor plate (25, 26) to provide an inner chamber (27) and a wall-side chamber (28) bordering the inner chamber (27). The first inlet (41) enters the wall-side chamber (28) and the second inlet (42) enters the central chamber (27).