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A variable geometry combustor having a combustor liner that defines at least one dilution port in order to provide air to a dilution zone within the combustor. At least one valve is positioned adjacent the dilution port for controlling the flow of air through the dilution port wherein the valve is s

A variable geometry combustor having a combustor liner that defines at least one dilution port in order to provide air to a dilution zone within the combustor. At least one valve is positioned adjacent the dilution port for controlling the flow of air through the dilution port wherein the valve is settable to maintain one of a plurality of different open configurations.

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We claim: 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

We claim: 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. 2. A gas turbine variable geometry combustor as claimed in claim 1 wherein each valve has a spring to bias the valve away from the respective dilution port and to bias the cam follower into contact with the camming surface. 3. A gas turbine variable geometry combustor as claimed in claim 2 wherein the cam follower of each valve is a roller. 4. A gas turbine variable geometry combustor as claimed in claim 1 wherein each camming surface comprises a slot in the actuating ring and each valve has a cam follower arranged to locate on a respective one of the plurality of camming surfaces. 5. A gas turbine variable geometry combustor as claimed in claim 2 wherein the cam follower of each valve is a peg. 6. A gas turbine variable geometry combustor as claimed in claim 5 wherein the peg is held in the respective slot. 7. A gas turbine variable geometry combustor as claimed in claim 1 wherein the combustor liner is cylindrical, the dilution ports are circumferentially spaced around the combustor liner and each valve is arranged for radial reciprocating movement. 8. A gas turbine variable geometry combustor as claimed in claim 1, wherein each of the different open configurations of the valve has an associated different air flow through the dilution port. 9. A gas turbine variable geometry combustor as claimed in claim 1, wherein the valve has only open configurations. 10. A gas turbine variable geometry combustor as claimed in claim 1, further comprising an air conduit for directing air over the dilution ports to a fuel injector of the combustor, wherein the valves are positioned within the air conduit for controlling the flow of air through the dilution port. 11. A gas turbine variable geometry combustor as claimed in claim 1, further comprising a variable geometry pre-mixing fuel injector, and means for varying the geometry of the pre-mixing zone, downstream of a fuel inlet, of the pre-mixing fuel injector. 12. A gas turbine variable geometry combustor as claimed in claim 1 wherein the control means further comprises a plurality of linear actuators, each linear actuator is arranged to move a respective one of the valves.