Abstract: A coolable nozzle guide vane in the turbine section of a gas turbine engine is disclosed. The vane has a platform section and an airfoil section which are adapted to receive and distribute cooling air about the walls of the sections which are in contact with the hot working medium gases flowing through the turbine during operation of the engine. Impingement cooling and transpiration cooling techniques are combined to maximize the cooling effectiveness of the air supplied.

Abstract: A coolable shroud surrounding the tips of the turbine blades of a gas turbine engine is disclosed. The shroud comprises a plurality of arcuate segments which are supported by the turbine case concentrically about the axis of the engine in end to end relationship. Each segment is adapted to receive and distribute cooling air about the walls of the shroud which are exposed to the hot working medium gases flowing through the turbine during operation of the engine. A combination of impingement cooling and transpiration cooling techniques maximize the cooling effectiveness of the air supplied.

Abstract: Means for preventing the wasteful leakage of cooling air within the turbine section of a gas turbine engine is disclosed. A segmented shroud radially separates the flow path for the working medium gases from cooling air supply chambers which are disposed radially outward of the flow path. Rotatable vanes penetrate the shroud and extend into the medium flow path to control the flow of medium gases through the turbine. A ring, which is split, is urged against the vane and the adjacent shroud segments in operative response to a spring member to prevent the excess leakage of cooling air therebetween.

Abstract: Apparatus for varying the nozzle area in the turbine section of a gas turbine engine is disclosed. Nozzle guide vanes extend across the flow path for the working medium gases and are rotatable to alter the area of the nozzle. In one embodiment the rotatable vanes are cantilevered from the outer engine case and are opposed at their radially inner ends by a shroud which is affixed to the inner engine case. The outer engine case has a double wall type construction including a plurality of bearing cartridges disposed between the walls.