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 stator vane capable of use in the high temperature environment of a gas turbine engine is disclosed. Various construction details implement vane cooling concepts which are designed to prolong the service life of the vane. An effective leading edge cooling system is built around the uniform flow of film cooling air over the exterior surface of the leading edge from a cavity within the airfoil section of the vane.

Abstract: An improved transpiration cooled turbine blade has a porous wall for the passage of coolant fluid therethrough; the wall comprising an outer porous layer, a second layer with relatively large holes, and a third layer with metering holes for the cooling fluid. There is provision for the direct passage of coolant to the edges of the blade, which edges are single layered. Slots near the trailing edge of the blade direct a portion of the cooling fluid outwardly at a right angle to the blade's concave surface to reduce drag losses due to flow separation under conditions of high blade loading.

Abstract: A turbomachinery vane or blade with cooled platforms including provision for film cooling the inner and outer surfaces of the platform forward portion, including cooling fluid cavities in the platform on both the pressure and suction sides of the vane or blade airfoil for cooling this region of the platform by a combination of impingement, convection and film cooling, and a selective array of drilled holes extending through the platform trailing edge for convection cooling thereof.

Abstract: A turbomachinery vane or blade with a cooled platform including a coolant cavity in said platform into which a plurality of cooling fluid impingement jets are projected to impinge against the platform wall and then flow along the platform wall after impingement for cooling thereof and eventual discharge from the cooling cavity along the platform surface. A plurality of dam members extend into the cooling cavity adjacent the impingement jets so as to isolate the impingement jets from cross-flow and channel flow effects from the cooling fluid passing through the cooling cavity following impingement.

Abstract: An engine is shown having a system for providing cooling fluid flowing radially inward to turbine blades on a disk while providing sealing means between the blade roots and cooperating disk slots and providing means for retaining the turbine blades on their disk. The cooling system includes stationary passageway means for directing a coolant flow from a source through an annular axial passageway where it is given a swirling velocity in the direction of rotation in the bladed rotor by means of grooves. The cooling fluid is then discharged from substantially radial passageways in the stationary passageway which are directed at an angle so that the coolant peripheral velocity essentially matches that of the rotating shaft on which the bladed rotor is located. Openings in the rotating shaft located radially inward from the substantially radial passageways in the stationary passageway means permit this flow to enter an annular passageway in this member where it is directed to the blades.

Abstract: The impingement baffle insert of a turbomachinery blade is provided with a plurality of collars around a portion thereof so as to ensure a proper impingement distance between the baffle and the inside wall of the airfoil and act as a wear surface against the inside wall to thereby prevent wear to the insert wall surface. The collars are affixed to the insert in preselected positions and frictionally engage the blade inner wall in close fit relationship to position the inserts and assume any wear that may result from vibration of the insert within the chamber. The inserts may have grooves formed therein to allow equalization of pressure on both sides thereof, and they may further have chamfered edges on one end thereof so as to facilitate installation into the turbine blades.

Abstract: An air-cooled turbine blading whose blade consists of a blade core provided with longitudinal ribs and cross ribs and of a blade jacket abutting against the ribs; the jacket is provided with air discharge apertures for the discharge of the cooling air out of the hollow spaces formed by the respective longitudinal and cross ribs; the cross ribs are provided with apertures for the flow of air which are constructed as throttling places.

Abstract: A turbine blade having a porous hollow sheet metal airfoil and a base defining a platform, stalk, and root. The airfoil portion is integral with an extension which lies within the blade stalk, the base being cast around this extension. The cast metal lies around the blade wall and also through tubes welded from wall to wall of the extension. The stalk also includes an opening to admit air to the interior of the blade for transpiration through the blade wall.