Abstract: A gas turbine includes a rotor having a rotor groove and a rotor bore extending through the rotor, the rotor bore having a diffuser-shaped rotor bore exit. A blade is attached to the rotor and includes a blade tip having at least one dust hole. An airfoil has a leading edge and a trailing edge extending along a longitudinal axis of the blade between a lower end of the airfoil and the blade tip. A blade root is disposed at the lower end of the airfoil and is configured to be removably disposed in the rotor groove. The blade root includes a blade inlet having a cross sectional area that exceeds a cross sectional area of the rotor bore in at least one direction. A hollow blade core is disposed in the airfoil and extends along the longitudinal axis of the blade between the blade root and the blade tip.

Abstract: The invention relates to a method for producing and repairing a part comprising at least two joined metal components, especially components of a gas turbine. In said method, corresponding joining surfaces of the components are joined together and connected by means of a pressure welding process, a machining allowance in the area of a joining zone of the two joining surfaces is upset during the joining process, and once the two components have been joined together, the machining allowance is machined by means of a precise electrochemical machining (PECM) process until a predefined final contour of the part has been obtained. The invention further relates to a gas turbine part obtained by means of the disclosed method.

Abstract: The present invention relates to an oil-free turbocharger assembly using an airfoil bearing that may be useful in high speed conditions. The assembly can be cooled easily. A heat-proof coating can also be easily applied to the turbo charger's rotating shaft. In one embodiment, an oil-free turbocharger assembly has a constant distance between a journal portion and a rotating shaft so that the mass of the rotating body can be minimized and the rotating body assembly can have a small moment of inertia. The turbocharger in some embodiments of the invention may be cooled by a refrigerant which improves cooling efficiency. Each part of the rotating body assembly in some embodiments may be individually treated with a heat-proof process so that productivity can be improved.

Abstract: An airfoil according to an exemplary embodiment of the present disclosure can include an airfoil body having a plurality of film cooling holes that extend through an exterior surface of the airfoil body. Each of the plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the airfoil.

Abstract: A mechanism for synchronously varying pitch of a multi-blade rotor, such as rotors used in wind or hydraulic generator and helicopter is provided in the present invention.

Abstract: A turbine nozzle for a turbomachine, the nozzle including two coaxial platforms interconnected by radial vanes, an inner platform being connected to an annular partition that is festooned or crenellated and on which there is fastened an annular support carrying elements made of abradable material. The support is capable of sliding circumferentially over the partition between a mounting-and-dismounting position and a position for locking the support on the partition.

Abstract: A gas turbine engine airfoil shaped component is disclosed including in one form a compressor blade or vane having a tip portion capable of producing a relatively low pressure near the leading edge of the tip to induce a local jet of stream-wise momentum flow. In one form the tip portion includes a camber angle distribution that produces relatively large change in camber angle near the leading edge but relatively flat distribution for remainder of blade. In one form the tip portion includes relatively large change in camber angle near trailing edge.

Abstract: A transverse axis fluid turbine with controllable display components thereof is disclosed. The turbine has a base structure, rotor rotatably attached to the base structure and at least three blades rotatably attached to the rotor. A matrix array of light reflective or emitting elements is mounted on the flat blade surface. The light reflective or emitting elements are controlled by a control unit in such a way that the light reflecting or emitting provides stable still or moving image(s) to its viewer(s) while the turbine is in operation.

Abstract: A steam turbine 3 includes: a turbine rotor 4; a rotor blade 5 implanted to the turbine rotor 4; a stator blade 6 provided at an upstream side of the rotor blade 5; and a turbine casing 13 supporting the stator blade 6 and including the turbine rotor 4, the rotor blade 5 and the stator blade 6, and have a constitution in which a stage 7 is formed by a pair of the rotor blade 5 and the stator blade 6, and a steam passage 8 is formed by arranging plural stages 7 in an axial direction of the turbine rotor 4. A surface treatment to suppress an increase of a surface roughness caused by oxidation is performed for at least a part of a surface of the stator blade 6 and a surface of the rotor blade 5.

Abstract: There is provided a wind turbine apparatus which comprises blades having an aerofoil profile. The apparatus is arranged to start up even in light wind conditions and to act as a lift type device at higher rotational speeds. The apparatus may comprise wind deflectors to concentrate wind through the apparatus. Further, the blades may be orientated at less than 90° to a radius line which leads to improved performance. Still further, the apparatus may be arranged to heat water by means of solar energy.

Abstract: The present disclosure provides an improved first stage airfoil for a compressor blade having a unique chord length (CD), stagger angle (?) and camber angle (??). The stagger angle (?) and camber angle (??) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight.

Abstract: A retention assembly for securing a main rotor shaft in a wind turbine relative to a pillow block is provided. A main rotor shaft extends through a pillow block, and a ring groove is defined in an outer circumferential surface of the main rotor shaft axially offset from the pillow block. A snap ring is engaged within the ring groove, wherein the snap ring and ring groove are designed to achieve a design axial load capacity.

Abstract: A turbine engine fan case assembly includes a structural case and a liner assembly. A radially accommodating attachment system connects the liner assembly to the structural case. The attachment system comprises a circumferentially-distributed plurality of longitudinally elongate radially outwardly open channels mounted to the liner assembly. The attachment system further comprises an associated plurality of inwardly-projecting tongues mounted to the structural case. Each tongue is accommodated in an associated such channel.

Abstract: A method for repairing a shroud tile of a gas turbine is disclosed. The method may generally include removing a portion of the shroud tile along at least one of a first side and a second side of the shroud tile and securing at least one side rail to the shroud tile in place of the removed portion of the shroud tile.

Abstract: A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion for providing structural support for a row of vanes in the engine section, an aft hook, a forward wall, and a strong back plate. The aft hook extends from an aft side of the main body portion and is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The forward wall extends generally radially outwardly from a forward side of the main body portion. The strong back plate spans between the forward wall and the aft hook and effects a reduction in dynamic displacement between the forward wall and the aft hook during operation of the engine.

Abstract: A nose cone assembly 102 is disclosed, comprising a one piece nose cone 104 and a support ring 106 on which the nose cone 104 is mounted. The support ring 106 comprises a plurality of circumferentially distributed resilient attachment tabs 114, via which the nose cone 104 is mounted on the support ring 106. The support ring 106 further comprises a load spreader 122, and each of the resilient attachment tabs 114 is operably connected to the load spreader 122, such that deflections and forces experienced by any one attachment tab 114 are distributed to other attachment tabs 114 via the load spreader 122.

Abstract: An air inlet assembly comprising an entrance region configured to receive an airflow, an exit region configured to output the airflow, and an attenuation region disposed between the entrance region and the exit region. The attenuation region has a cross section aspect ratio of at least about 5-to-1, and comprises acoustic absorbing material.

Abstract: A vibration damper between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel, the damper including a peg having a substantially spherical portion at each of its two ends, and two hollow inserts for being received in tangential cavities that are provided facing each other in outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel, each spherical portion of the peg coming to bear with point contact against the inside of one of the inserts.

Abstract: A film cooling structure formed in a component wall of a turbine engine and a method of making the film cooling structure. The film cooling structure includes a plurality of individual diffusion sections formed in the wall, each diffusions section including a single cooling passage for directing cooling air toward a protuberance of a wall defining the diffusion section. The film cooling structure may be formed with a masking template including apertures defining shapes of a plurality of to-be-formed diffusion sections in the wall. A masking material can be applied to the wall into the apertures in the masking template so as to block outlets of cooling passages exposed through the apertures. The masking template can be removed and a material may be applied on the outer surface of the wall such that the material defines the diffusion sections once the masking material is removed.

Abstract: A hydraulic machine having a hydro turbine runner which has a crown at a center and a band along an outer periphery, and is formed around the axis of rotation, long blades which are arranged along the circumferential direction of the axis of rotation, and whose center-side ends are supported by the crown, and periphery-side ends are supported by the band, and short blades which are arranged between the long blades, and whose center-side ends are supported by the crown, periphery-side ends are supported by the band, and rear edges are curved in a rotation direction of the hydro turbine runner in turbine operation, on a plane of projection perpendicular to the axis of rotation.