公开(公告)号：US09719365B2

公开(公告)日：2017-08-01

申请号：US14031695

申请日：2013-09-19

Applicant: ROLLS-ROYCE PLC

Inventor： Marko Bacic ,  Timothy John Scanlon ,  Ronald William Daniel

IPC: F01D11/10 ,  F01D11/24 ,  F01D11/06 ,  F01D11/20

CPC classification number: F01D11/10 ,  F01D11/06 ,  F01D11/20 ,  F01D11/24 ,  F05D2260/16 ,  F05D2270/172 ,  F05D2270/62

Abstract: A clearance control device including a segment having a passage to deliver fluid towards a component rotating past the segment. Also a fluid flow device having a first fluid path coupled to the passage and a second fluid path that is decoupled from the passage. A first plasma generator is located in the fluid flow device that directs fluid towards the first fluid path; a second plasma generator is located in the fluid flow device that directs fluid towards the second fluid path; and a control arrangement is configured to alternately energize the first and second plasma generators at an energizing frequency to deliver fluid to the passage at a frequency coincident with the passing frequency of the component.

公开(公告)号：US09879603B2

公开(公告)日：2018-01-30

申请号：US14458593

申请日：2014-08-13

Applicant: ROLLS-ROYCE PLC

Inventor： Alan Robert Maguire ,  Timothy John Scanlon ,  Colin Young

IPC: F02C7/18 ,  F01D5/08 ,  F02C6/08 ,  F01D5/04 ,  F01D9/06 ,  F01D25/08 ,  F02C7/12 ,  F01D25/12 ,  F02C3/00

CPC classification number: F02C7/18 ,  F01D5/046 ,  F01D5/08 ,  F01D5/081 ,  F01D5/082 ,  F01D9/06 ,  F01D25/08 ,  F01D25/12 ,  F02C3/00 ,  F02C6/08 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/205 ,  Y02T50/676

Abstract: This invention concerns a system for cooling components in a gas turbine engine, the gas turbine engine including a compressor for driving a primary gas flow to a combustor and a turbine arranged to be driven by combustion gases from the combustor, wherein the system includes: an annular cooling flow passage arranged for fluid communication between the compressor and the turbine, the flow passage having a first inlet arranged to receive gas from the primary gas flow downstream of compressor, and a second inlet located upstream of the first inlet, wherein the annular cooling flow passage has at least one internal wall for guiding airflow from the first inlet towards the airflow from the second inlet, the airflow from the first and second inlets coalesce within the annular flow passage prior to passing along the passage in a direction from the compressor to the turbine.