Abstract: A turbine blade that includes a tip shroud and one or more cooling cavities formed within the tip shroud. At least one of the cooling cavities may include a plurality of ribs and a first interior wall that generally opposes a second interior wall across the cooling cavity. The ribs may be configured such that some of the ribs originate on the first interior wall of the cooling cavity and extend toward the second interior wall of the cooling cavity and some of the ribs originate on the second interior wall of the cooling cavity and extend toward the first interior wall of the cooling cavity. And, the ribs that originate on the first interior wall of the cooling cavity and the ribs that originate on the second interior wall of the cooling cavity may have an alternating arrangement.

Abstract: The crossover tube conducts fluid from the exhaust nozzle of a gas turbine engine to a blind receiver mounted in the sidewall of the airframe when assembled and deployed and includes a rigidly affixed forward ball and joint and a ball attached to the ends of each of a pair of tubes mounted in telescopic relationship with a clip secured to the coverplate covering the ball at the forward end cooperating with a pair of end to end mounted coil springs surrounding the tubes to hold the crossover tube in an erect and extended position to be guided into the receiver of the sidewall when deployed. In another embodiment bellows are utilized in place of the coil springs to provent leakage of fluid flowing in the crossover tube.

Abstract: The nacelle of the aircraft is purged and the sidewall of the vector nozzles of the gas turbine engine in the nacelle is cooled by utilizing the engine fan air to drive ejector pumps mounted in series flow relationship, a rectangular mixing zone and a diffuser with a rectangular cross section and a step in the exhaust nozzle gaspath. This results in minimizing the amount of fan air for driving the system and enhancing engine thrust and enhanced sidewall cooling because the temperature of the mixed air is lower than heretofore known systems.

Abstract: Tip shroud segments (26) are supported in support ring (24). The ring has at its downstream end conical surface (32) mating and in interference fit with conical surface (16). When flange (20) is torqued, face (22) aligns and forces support ring (24) into the interference fit. Concentricity and rigidity of the shroud support is obtained in a structure easily assembled and disassembled.

Abstract: The performance of a TOBI for a gas turbine engine is improved by providing bypass apertures in the housing of said TOBI for directing a stream of air into the seal sealing the TOBI compartment and bypassing the nozzles of the TOBI to reduce the size of the plume of the TOBI cooling air.