US 7,500,347 B2
Variable geometry combustor
Noel A Sanders, Derby (United Kingdom); Carl C Bourne, Derby (United Kingdom); Anthony J Moran, Nuneaton (United Kingdom); Paul Fletcher, Rugby (United Kingdom); and Philip P Walsh, Solihull (United Kingdom)
Assigned to Rolls-Royce plc, London (United Kingdom)
Filed on Aug. 10, 2004, as Appl. No. 10/914,072.
Claims priority of application No. 0319329.9 (GB), filed on Aug. 16, 2003.
Prior Publication US 2005/0095542 A1, May 05, 2005
Int. Cl. F02C 7/057 (2006.01)
U.S. Cl. 60—39.23  [60/754; 60/794] 12 Claims
OG exemplary drawing
 
1. A gas turbine variable geometry combustor, comprising: a combustor liner defining a plurality of dilution ports for providing air to a dilution zone of the gas turbine combustor; and
a plurality of valves, each valve being positioned adjacent a respective one of the dilution ports for controlling the flow of air through the dilution ports, each valve being settable to maintain one of a plurality of different open configurations, each valve being arranged for reciprocating movement and said combustor further comprising control means for variably controlling the setting of the valves wherein the control means comprises a rotatable actuating ring, the actuating ring has a plurality of camming surfaces and each valve has a cam follower arranged to rest on a respective one of the plurality of camming surfaces.