Abstract: A method for reducing vortex promotion of a rotor blade used in high core PR fans comprises shifting a curvature distribution of a blade section immediately adjacent to the hub such that a major turning of the suction side of the section is located near a trailing edge of the blade.

Abstract: A new high-strength titanium-based alloy bucket specifically suited for use as the last stage buckets in steam turbine engines having vane lengths of about 40 inches or greater and the method for forming such bucket. Exemplary buckets according to the invention are formed from a titanium-based alloy containing up to about 6.25% aluminum; (b) about to 3.5% vanadium; (c) about 2.25% tin, (d) about 2.25% zirconium, (e) about 1.75% molybdenum, (f) about 2.25% chromium, (g) about 0.7% silicon; and (h) about 2.3% iron, with the balance being titanium. After forming, the bucket can be heat treated to provide stress relief and then machined in a conventional manner.

Abstract: A Francis turbine with an improved shape of blades, which can reduce a circumferential velocity component generated in the flow downstream of the blades in a condition of a partial load operation, or reduce the secondary flow around the blades, is provided. A Francis turbine comprises a crown, a plurality of blades, and a band. The crown can rotate around a rotating axis. The blades are circumferentially arranged on the crown, each of which including an inner end as a trailing edge. The band is coaxially coupled with the crown by the blades. A distance Rc can be defined as a distance between the rotation axis and an end by the crown side of the trailing edge. A distance Rb can be defined as a distance between the rotation axis and an end by the band side of the trailing edge. The distance Rc and the distance Rb satisfy 0.2 ? R c R b ? 0.4 .

Abstract: An air turbine driven rotary machine tool having a tool casing, a turbine rotor mounted within the casing for rotation, a stator mounted in fixed position in the tool casing coaxially aligned with the turbine rotor, a annular cavity defined within the casing and coaxially aligned with the stator and rotor for supplying air to the stator blades, a cylindrical spindle coaxially mounted with the turbine rotor in the tool casing for rotation with the turbine rotor, and a tool holder mounted coaxially to the spindle for rotation therewith and having an end thereof for operably receiving a cutting tool.

Abstract: A hollow component for gas turbine engine, for example an outlet guide vane, is assembled from a body having at recessed pocket formed therein, and an aerodynamic cover bonded over the pocket. Both the cover and the body are constructed from materials which are not readily fusion weldable. The cover is attached to the body by a solid state bonding process, for example friction stir welding. The hollow component may also be built up from multiple individual components which are bonded to each other by a solid state bonding process such as friction stir welding.

Abstract: A radial seal is provided for installation within a centrifugal pump of the type having an impeller, a pump casing having a suction inlet, a sealing ring groove formed in the pump casing, and means for supplying flushing water to the sealing ring groove. The radial seal comprises a seal body, including a sealing end, a water inlet end, and opposed sides. The sealing end has an outwardly extending lip portion. The seal is adapted for installation within the sealing ring groove, with openings formed through the seal body for the passage of water.

Abstract: A centrifugal impeller particularly for a turbo-charger includes a circular disc member, a boss portion formed at a central portion of the disc member and having a central through hole into which a rotational shaft is inserted, an impeller blade integrally formed on one surface side of the disc member, and a ring-shaped rib member arranged on the other surface side of the disc member so as to be coaxial with a center axis of the boss portion. A thickness reduced portion is formed to the disc member so as to have a thickness smaller than that of another portion of the disc member, and the thickness reduced portion is arranged adjacent to the rib member.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S–16S, 1R–17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: A dual rotation paddlewheel includes tangs that are equally effective in either direction of rotation. The paddlewheel includes tangs disposed around an outer periphery of a body. The dual rotation paddlewheel includes a primary face for use in a first direction and a secondary face for use in a second rotation direction. The tangs may also include a crossbar for increased shear strength. The increased cross sectional area eliminates problems associated with breaking tangs off of the paddlewheel and entering the product stream. Existing product engagement areas in existing designs have been preserved with the dual direction design. The dual direction paddlewheel allows for the consolidation of rotation specific designs into a single part, thereby eliminating costs associated with carrying multiple single direction paddlewheels as well as tooling and manufacturing costs for multiple paddlewheel designs.

Abstract: A turbine wall includes a plurality of first and second film cooling holes arranged in a common row. The holes have multiple forms and alternate in the row for collectively providing film cooling performance therefrom.

Abstract: A method for assembling a gas turbine engine includes providing a low-pressure turbine inner rotor that includes at least a first pair of adjacent rows of turbine blades that are configured to rotate in a first direction providing a low-pressure turbine outer rotor that includes a forward end, an aft end, and at least one row of turbine blades that is rotatably coupled between the first pair of inner rotor turbine blades, wherein the at least one row of outer rotor turbine blades is configured to rotate in a second direction that is opposite the first direction, and coupling a support assembly between the first pair of inner rotor turbine blades such that the support assembly supports the outer rotor forward end.

Abstract: A wind turbine, with: a rotatable frame; a plurality of airfoils mounted to the rotatable frame, wherein the airfoils extend parallel to an axis of rotation of the rotatable frame; a wind block positioned to restrict airflow over at least a portion of the rotatable frame; and at least one drive wheel in contact with the rotatable frame.

Abstract: A method is provided for making a repaired turbine engine stationary vane assembly including at least one airfoil bonded between spaced apart first and second platforms. The method comprises providing a first vane assembly member including at least a portion of the first platform, the airfoil, and a first segment of the second platform bonded with the airfoil. Also provided is a second vane assembly member including a second segment of the second platform with a recess of a shape and size sufficient to receive the first segment of the second platform. The first segment is placed in the recess after which the first and second segments are bonded, for example by brazing or welding. Provided is a more structurally sound repaired turbine engine stationary vane assembly including the first and second vane assembly members bonded together.

Abstract: Damper pins are disposed in circumferentially registering grooves of turbine bucket platform slash faces. The pins have a plurality of channels formed about peripheral portions thereof for flowing leakage cooling air from below the platform past the pin and groove into the interplatform gap. The channels may be staggered in an axial direction. By flowing cooling air through the channels, the slash faces are convectively cooled, opposite slash faces to the channels are impingement cooled and the exiting cooling air purges the gap between the slash faces adjacent the hot gas path. Alternatively, the channels may be formed in the grooved surfaces and a cylindrical damping pin may be inserted with similar cooling effects.

Abstract: The invention relates to a turbine blade (31) having a root region (33), a tip region (37) and a blade airfoil (35), a rounded portion (73) being formed between the root region (33) and the blade airfoil (35), and relief slots (51) passing through the blade trailing edge (41) in the region of this rounded portion (73), thermal expansions being compensated for and thus thermal stresses being minimized by these relief slots (51).

Abstract: A gas turbine diffuser assembly and a method for assembling same, includes providing a loose fit between the diffuser body and the diffuser pipes. Damper members provide a snug attachment.

Abstract: A reactive turbine, each blade of which approximates a helical shape that is constructed with readily available conventional manufacturing techniques. The blades are constructed in discrete straight sections that, when joined, approximate a helix or any other efficient turbine shape. Each section is manufactured with the well known and readily available machine shop techniques of shaping, forming, and joining with welds or fasteners.

Abstract: A compressor blade for an aircraft engine includes a blade core made of a fiber compound material and a metallic enclosing structure. The enclosing structure is of a multi-part design and includes blanks (4, 5) attached to the blade core by a metallic weave (6) on the suction side and on the pressure side, with the two blanks being firmly connected at the aerodynamically shaped leading edge of the compressor blade by to a leading-edge former (3). Depending on the specific loads applied on the pressure side and on the suction side, welds attaching the blanks to the leading-edge former (8, 9) are offset relative to each other and the material thicknesses of the components of the enveloping structure are matched to each other.

Abstract: An axial-flow fan with double impellers is provided that can produce a larger amount of air and a higher static pressure than can be achieved with conventional fans. The axial-flow fan with double impellers has a first axial-flow fan unit and a second axial-flow fan unit. The first axial-flow fan unit includes a first case, a first impeller and a plurality of webs that fix a first motor to the first case. The second axial-flow fan unit includes a second case, a second impeller and a plurality of webs that fix a second motor to the second case. The first case and the second case are coupled together to form a housing. The webs of the first axial-flow fan unit and the webs of the second axial-flow fan unit are combined together to form a plurality of stationary webs arranged in the housing. The number of front blades provided at the first impeller is set to five, the number of stationary blades is set to three, and the number of rear blades provided at the second impeller is set to four.

Abstract: A method facilitates assembling a rotor assembly for gas turbine engine. The method comprises providing a first rotor blade that includes an airfoil having a leading edge and a trailing edge including a plurality of trailing edge openings, a platform, a shank, and a dovetail, wherein the platform extends between the airfoil and the dovetail and includes a radially outer surface, a radially inner surface, and a recessed area extending at least partially between the radially outer and inner surfaces. The method also comprises coupling the first rotor blade to a rotor shaft using the dovetail, and coupling a second rotor blade to the rotor shaft such that cooling air is substantially continuously channeled through the platform recessed area during engine operation to facilitate reducing stresses induced to at least a portion of the airfoil trailing edge.