公开(公告)号：US20180347392A1

公开(公告)日：2018-12-06

申请号：US15995779

申请日：2018-06-01

Applicant: ROLLS-ROYCE plc

Inventor： Leo V. LEWIS ,  Vinod GOPALKRISHNA

IPC: F01D11/24 ,  F01D11/02

CPC classification number: F01D11/10 ,  F01D11/005 ,  F01D11/24 ,  F01D25/246 ,  F05D2240/11 ,  F05D2260/231

Abstract: A clearance control arrangement (26) for a rotor (28) comprising a segment assembly (33) spaced radially inwards from a casing (32) and defining a radial clearance (42) between the rotor (28) and the segment assembly (33). A front carrier (35a) and a rear carrier (35b) supporting the segment assembly (33). A heat transfer cavity (48) formed between the carriers (35a, 35b), the segment assembly (33) and the casing (32). A settling chamber (60) formed adjacent to the casing (32) and upstream of the heat transfer cavity (48). The clearance control arrangement (26) is configured to receive air into the settling chamber (60) and thence to deliver it to the heat transfer cavity (48).

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：US20180340442A1

公开(公告)日：2018-11-29

申请号：US16055466

申请日：2018-08-06

Applicant: ROLLS-ROYCE plc

Inventor： Leo V. LEWIS

IPC: F01D11/24 ,  F01D25/12 ,  F01D25/24 ,  F01D5/12 ,  F01D5/02 ,  F01D25/10

Abstract: An arrangement for a gas turbine engine that includes a turbine blade configured to rotate about an axis, a casing radially outside of the turbine blade, and a carrier segment mounted to the casing so as to define a first impingement space therebetween. The carrier segment is positioned radially outside the turbine blade and includes a first impingement carrier wall, a main carrier wall, and a cooling chamber. The first impingement carrier wall is adjacent to and radially inside of the first impingement space, and the first impingement carrier wall includes a first aperture. The main carrier wall is radially inside of the first impingement carrier wall. The cooling chamber is radially inside of the main carrier wall. Additionally, an intermediate chamber is disposed radially between the cooling chamber and the first impingement space. A second aperture is configured to allow ingress of air into the intermediate chamber.

公开(公告)号：US20170114725A1

公开(公告)日：2017-04-27

申请号：US15277599

申请日：2016-09-27

Applicant: ROLLS-ROYCE plc

Inventor： Jonathan E. HOLT ,  Leo V. LEWIS

IPC: F02C9/18 ,  F01D25/24 ,  F02C7/18 ,  F01D25/12 ,  F01D21/00 ,  F01D21/12 ,  F01D5/02 ,  F01D25/14

CPC classification number: F02C9/18 ,  F01D5/02 ,  F01D11/24 ,  F01D17/02 ,  F01D21/003 ,  F01D21/12 ,  F01D25/12 ,  F01D25/14 ,  F01D25/24 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2270/112 ,  F05D2270/303

Abstract: A case cooling calibration system for a gas turbine engine comprises a rotor casing, and a rotor stage, rotatably mounted within the rotor casing.The rotor casing comprises in series fluid communication, a duct, a flow control valve, and a manifold. The valve is operable to regulate an air flow through the duct to the manifold, with the manifold arranged radially outwardly around the casing radially coplanar with the rotor stage.A temperature sensing apparatus is positioned on the rotor casing, radially outwardly of the rotor stage. A controller is operable to regulate the valve in a stepwise manner to provide a variable cooling air flow to the rotor casing. A processor is operable to calculate a correction characteristic in dependence on a comparison between the rotor casing temperature and a predicted rotor casing temperature for a given engine power condition.An engine controller is operable to control the valve in dependence on the correction characteristic to maintain a predetermined operational radial clearance between the rotor stage and the rotor casing.