초록 ▼

A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actu

A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the flaps through a linkage. A supply of pressurized air is also provided to the sync ring to assist the actuator in resisting forces from high pressure gases within the nozzle. When those forces are lower than normal the flow of air to the rear of the sync ring is reduced or blocked. A ring rotates with another ring to control both this air flow, and a supply of cooling air to an interior of the nozzle.

대표청구항 ▼

What is claimed is: 1. A nozzle for a gas turbine engine comprising: a plurality of flaps which may move to provide a desired cross-sectional area for a nozzle outlet; an actuator structure for driving said flaps through a linkage, said actuator structure including at least one actuator member movi

What is claimed is: 1. A nozzle for a gas turbine engine comprising: a plurality of flaps which may move to provide a desired cross-sectional area for a nozzle outlet; an actuator structure for driving said flaps through a linkage, said actuator structure including at least one actuator member moving the flaps through an intermediate structure; an air supply for supplying pressurized air to a rear surface of said intermediate structure, said pressurized air assisting said actuator member in holding said flap at a desired position, and resisting a force from pressure within said nozzle; a liner ring for being rotated to control the flow of cooling air to an inner periphery of said nozzle, and a valve comprising of an outer ring with valve closures for controlling flow of pressurized air to said rear surface of said intermediate member, said valve being controlled to reduce the flow of air when certain system conditions are sensed, said liner ring rotating with said valve. 2. The nozzle as set forth in claim 1, wherein a pressure ratio between the air pressure within said nozzle, and an ambient pressure is utilized to control said valve. 3. The nozzle as set forth in claim 2, wherein the flow of pressurized air to said rear surface is reduced when said ratio is less than three. 4. The nozzle as set forth in claim 1, wherein said valve is an outer ring which rotates with said liner ring, but is separate from said liner ring such that it can move axially relative to said liner ring. 5. The nozzle as set forth in claim 4, wherein a spring is placed between surfaces on said outer ring and said liner ring and biases said outer ring against a member with a plurality of ports which are selectively opened or closed by said outer ring to control the flow of air to said rear surface of said intermediate member. 6. The nozzle as set forth in claim 4, wherein a rotating linkage drives said liner ring to rotate, said liner ring having a plurality of spaced openings, said openings being selectively aligned with openings in a fixed surface to allow or block the flow of cooling air into said nozzle. 7. The nozzle as set forth in claim 6, wherein a bearing on said linkage is received within a slot in said liner ring. 8. The nozzle as set forth in claim 1, wherein said intermediate member is a sync ring defining a chamber for receiving pressurized air, and being connected to said actuator. 9. A method of operating a nozzle in a gas turbine engine comprising the steps of: (1) providing a plurality of flaps that may move to provide a desired cross-sectional area for a nozzle outlet, and providing an actuator structure having at least one intermediate member that moves the flaps; and (2) rotating a rotatable structure to control the flow of air flow to a rear surface of said intermediate structure, to either block or allow the flow of air to the intermediate structure dependent on system conditions, and further rotating said rotatable structure to control a flow of cooling air into an interior of said nozzle. 10. The method as set forth in claim 9, wherein said rotatable structure includes a liner ring controlling the flow of cooling air to the interior of the nozzle, and an outer ring for controlling the flow of cooling air to the rear surface of the intermediate member, said outer ring being constrained to rotate with said inner ring. 11. The nozzle as set forth in claim 8, wherein said sync ring drives a plurality of said flaps. 12. The nozzle as set forth in claim 11, wherein said sync ring can move independently from said flaps.