Abstract: The invention comprises a cooled turbine rotor blade having an improved blade tip structure. A recessed tip is provided at the leading edge end of the blade tip on downstream turbine blades which are too narrow to support a blade tip cavity over the entire exterior surface of the blade tip without interfering with cooling airflow from apertures in the exterior surface. The recessed tip structure protects apertures therein from blockage by a blade tip smear and does not substantially reduce the performance efficiency of the blade.

Abstract: A replaceable tip cap for attachment to the end of a rotor blade. The tip cap includes a plurality of walls defining a compartment which, if desired, can be divided into a plurality of subcompartments. The tip cap can include inlet and outlet holes in walls thereof to permit fluid communication of a cooling fluid therethrough. Abrasive material can be attached with the radially outer wall of the tip cap.

Abstract: Means and a method are provided whereby liquid coolant flows radially outward through coolant passages in a liquid cooled turbine bucket under the influence of centrifugal force while in contact with countercurrently flowing coolant vapor such that liquid is entrained in the flow of vapor resulting in an increase in the wetted cooling area of the individual passages.

Abstract: A blade or vane structure for a gas turbine engine comprises a hollow aerofoil member and a cooling air entry tube within the hollow aerofoil member, the aerofoil member and the tube comprising a unitary cast structure. To make this structure it is proposed that a lost wax casting process should be utilized, with the internal cavities formed using ceramic cores formed with the aid of temporary, disposable pieces which define the space eventually occupied by the tube.

Abstract: Turbine buckets are designed for use in an environment of ultra-high temperatures by incorporating therein water cooling channels using preformed tubes which are located beneath an outer protective layer. This layer is preferrably composed of an inner skin which provides high thermal conductivity and an outer skin which provides protection from hot corrosion.

Abstract: An improved cooling system for a gas turbine is disclosed. A plurality of V-shaped notch weirs are utilized to meter a coolant liquid from a pool of coolant into a plurality of platform and airfoil coolant channels formed in the buckets of the turbine. The V-shaped notch weirs are formed in a separately machined cylindrical insert and serve to desensitize the flow of coolant into the individual platform and airfoil coolant channels to design tolerances and non-uniform flow distribution.

Abstract: An improved trap seal for open circuit liquid cooled turbines is disclosed. The trap seal of the present invention includes an annular recess formed in the supply conduit of cooling channels formed in the airfoil of the turbine buckets. A cylindrical insert is located in the annular recesses and has a plurality of axial grooves formed along the outer periphery thereof and a central recess formed in one end thereof. The axial grooves and central recess formed in the cylindrical insert cooperate with the annular recess to define a plurality of S-shaped trap seals which permit the passage of liquid coolant but prohibit passage of gaseous coolant.

Abstract: Methods are disclosed for more practical construction of liquid-cooled buckets able to efficiently transport heat energy from the inside of the airfoil skin surface in contact with hot gas to the outer surface of preformed tubes recessed into the bucket core, through which tubes liquid coolant is passed during operation. The bucket is made of a series of preformed solid components, which are assembled, consolidated and then converted into a unified structure. In each arrangement illustrated one of the preformed solid components is a flat bimetallic sheet comprising an erosion, corrosion resistant layer and a layer of high thermal conductivity, these layers being joined by an optimized metallurgical bond.

Abstract: Turbine buckets are designed for use in an environment of ultra-high temperatures by incorporating therein water cooling channels using preformed tubes which are located beneath an outer protective layer. This layer is preferably composed of an inner skin which provides high thermal conductivity and an outer skin which provides protection from hot corrosion.

Abstract: An ultra-high temperature gas turbine bucket is shown with subsurface cooling channels extending from a bucket platform to a manifold in the tip region of the bucket. A liquid trap is disposed radially outward from the manifold and is in communication therewith, the trap under conditions of normal operation remaining filled with liquid coolant. A liquid coolant discharge orifice communicates with the trap at the blade tip generally adjacent the leading edge thereof. Liquid coolant substantially free of entrained vaporized coolant is discharged from the trap through the discharge orifice and collected in a collection slot in the turbine casing. Vaporized coolant is discharged from a nozzle disposed at the trailing edge of the bucket in communication with the manifold.

Abstract: A hollow turbomachinery blade is formed by way of casting or the like with an open tip end except for a bridge which is formed integrally with the blade side walls at a central position with respect to the leading and trailing edges. Also formed integrally with the blade side walls, proximate the tip end openings near the leading and trailing edges, are a plurality of supporting and retaining bosses, the supporting bosses being in substantially the same plane as the bridge, and the retaining bosses being disposed radially outward thereof. Each of the forward and rear tip caps is installed by placing it over the bridge and then sliding it either forward or rearward to be captured by the supporting and retaining bosses and to thereby close the respective tip opening. Each of the tip caps is then brazed into position so as not to allow its sliding back out.