Abstract: A shroud for supporting the vanes in the hot sections of a gas turbine engine is comprised of composite segments retained in a metal ring. The metal ring has a positive coefficient of expansion, while the segments have a zero (or much smaller) coefficient. When the ring is heated and grows, it carries the segments with it, so that there is an apparent corresponding growth of the segments.

Abstract: An engine nozzle construction having a flap nozzle at the end of an engine exhaust duct, said flap nozzle variably controlling exhaust flow providing a primary flow path, said flap nozzle being movable to a position to direct the exhaust flow from said exhaust duct into a peripheral chamber, said chamber having exit openings around it providing for a secondary flow path for the exhaust flow.

Abstract: A system to assist flap actuation of a convergent-divergent exhaust nozzle to overcome the high air loads on the flaps, so that the nozzle flaps can be properly positioned by the actuators. The structural members of the system are operatively associated with a controlled, air-pressurized, cavity positioned in the exhaust nozzle section. Pressurized air from the cavity acts against the flaps, and helps to overcome the load required to move them. The system is useful in any exhaust nozzle, and most particularly where the exhaust nozzle is two-dimensional, i.e., rectangularly shaped.

Abstract: A paired vane structure for the first stator stage of a gas turbine, having the vane structure of each vane pair cast in two matching parts which are then assembled and held together by means of bolts passing through flanges on the vane inner and outer platforms. The paired vanes are assembled into the gas turbine structure in the same manner as the prior art paired vane sections.