Abstract: A cooling air flow ejector has a primary nozzle position to entrain air from a secondary nozzle. Mixed air is provided into a downstream flow conduit to be directed to an exhaust liner for a gas turbine engine. A variable area device controls a volume of air passing through a primary nozzle. A control for the variable area device to control the size of an orifice within the variable area device controls the volume of air reaching the exhaust liner to be cooled.

Abstract: 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.

Abstract: A nozzle system includes a multitude of circumferentially distributed convergent flaps and seals that circumscribe an engine centerline. A cooling liner body cooperates with a cooling liner panel attached to respective convergent flaps and convergent seals to define an annular cooling airflow passageway which is movable therewith. Each cooling liner panels includes an arcuate cooling liner leading edge with a multiple of openings to distribute cooling airflow over both the inner “cold-side” and outer “hot-side” surfaces thereof. Through this backside cooling, thermal gradients are controlled at the attachment interface between the arcuate cooling liner leading edge and the main cooling liner body.

Abstract: A cooled exhaust duct for use in gas turbine engines is provided. The cooled exhaust duct includes an axial centerline, a circumference, an annulus, and a plurality of radially expandable bands. The annulus is disposed between a first wall and a second wall, and extends along the axial centerline. The first wall is disposed radially inside of the second wall. Each of the plurality of radially expandable bands extends circumferentially within the annulus. The bands are axially spaced apart from one another. Each band includes a first portion attached to the first wall, a second portion attached to the second wall and an intermediate portion connected to the first and second portions. The bands create circumferentially extending compartments that inhibit axial travel of the cooling air within the annulus.

Abstract: A nozzle system includes a multitude of circumferentially distributed convergent flaps and seals that circumscribe an engine centerline. A cooling liner body cooperates with a cooling liner panel attached to respective convergent flaps and convergent seals to define an annular cooling airflow passageway which is movable therewith. Each cooling liner panels includes an arcuate cooling liner leading edge with a multiple of openings to distribute cooling airflow over both the inner “cold-side” and outer “hot-side” surfaces thereof. Through this backside cooling, thermal gradients are controlled at the attachment interface between the arcuate cooling liner leading edge and the main cooling liner body.

Abstract: 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.

Abstract: 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.

Abstract: The exhaust in a gas turbine engine is lined with stacks of hollow cooling blocks made of a composite material. Air is pumped into each stack and escapes into the exhaust flow from a slot between the blocks in each stack. In addition, the blocks contain passages so that some of the airflow escapes to a space between the stacks. The blocks are attached using special fasteners that does not create mechanical stresses on the composite material.

Abstract: A spherical exhaust nozzle for a gas turbine engine having gimbal mounted convergent-divergent flaps in which cooling air for the flaps is ducted through the convergent flap pivots and the convergent flaps are actuated by actuators connected to the gimbal structure.