A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

A seal structure is for sealing leakage fluid flowing through a gap between a rotation member rotating about a rotation axis and a stationary member facing the rotation member. The seal structure includes seal fins projecting from a base that is one of the rotation and stationary members toward the other one, the seal fins being spaced apart from each other at a certain interval in an axial direction of the rotation axis; and a step section provided to the other one, the step section including step surfaces facing the seal fins and a riser surface between the adjacent step surfaces, the step surfaces and the riser surface defining a step portion. The seal fins are inclined upstream in a flow direction of the leakage fluid relative to a radial direction perpendicular to the rotation axis. Each seal fin and the base define a corner portion having a curved surface.

A turbine shaft used for a turbocharger including a turbine and a compressor includes a turbine impeller, and a rotor shaft joined on one end side to the turbine impeller. The rotor shaft includes a fitting region configured to fit with a compressor impeller of the compressor by inserting the other end side of the rotor shaft into a through hole formed in the compressor impeller, a fastening region formed between the fitting region and the other end side of the rotor shaft, and configured to allow fastening by a fastening part, and a tapered part having a maximum outer diameter at a position closest to the turbine impeller in the fitting region and formed such that an outer diameter of the rotor shaft decreases from the position closest to the turbine impeller toward a tip side of the compressor impeller.

A gas turbine engine component assembly is provided. The gas turbine engine comprises: a first component having a first surface and a second surface opposite the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate mitigation device extending from the first surface of the second component a selected distance wherein the particulate mitigation device has an opening therethrough in fluid connection with the cooling channel, and wherein the selected distance is selected to reduce the amount of particulate entering the cooling channel.

A turbine for a power plant unit for a hybrid power plant is arranged in a turbine housing in which a flow channel for a compressible medium is arranged. A drive shaft and at least one output impeller are arranged in the flow channel, the output impeller containing an output shaft for operating a generator, wherein the output impeller is connected in a rotationally fixed manner to the output shaft. The drive shaft is not connected to the output shaft.

An inner band assembly for at turbine nozzle of a rotary machine that includes a centerline axis, the inner band assembly comprising a platform portion, a first flange portion coupled to the platform portion and obliquely oriented with respect to the centerline axis, and a second flange coupled to the first flange and obliquely oriented with respect to the first flange. Wherein the platform portion and the first flange intersect.

TURBINE WITH SOLAR COLLECTOR OR TURBOCHARGER, which is designed to originate innovative turbine kinetic energy through solar irradiation, irradiated by heliostats, parabolic or possibly to function with other types of fuel when not no solar radiation. With a heat exchanger through which passes the residual thermal energy is achieved in a higher efficiency than conventional turbines. In this set of turbine exchanged, collector and collector, its components are located so that the drop of the thermal fluid is the minimum possible. The team has been solar collector incorporated a radial type where the sunlight is irradiated, which in the collector, the heated fluid flowing through it which comes from the compressor, through the heat exchanger, and that the empty on the blades of the turbine motor generating a kinetic energy of a mechanical element that needs a turning force or power generators. This system can be developed to produce electric power from 1 kW to 15 kW in parable and even over twenty megawatts radiated tower heliostats. At low power is designed for can use the sensor and the sensor turbine or a turbocharger. No water uses er, no pollution and low installation costs, very significantly given the simplicity and innovation of its components.

Assembly for axial turbomachine, in particular for an aircraft turbojet, the assembly comprising: an annular casing with an internal surface (40); an annular row of stator baffles (26) with at least one stator baffle (26) comprising an airfoil (50) which extends radially from a fixing platform (34), the fixing platform (34) being fixed to the casing and having a polygonal outline; characterised in that it further comprises a gasket (80) comprising a frame, the outline of which conforms to the polygonal outline of the fixing platform (34), the frame being in radial contact with the fixing platform (34) and the casing in order to ensure a seal.

An exhaust gas turbocharger includes a turbine casing (4) within which a turbine wheel (10) is rotatably arranged relative to an axis of rotation (1). A guide vane ring (22) is non-rotatably arranged which comprises variable guide vanes (44) which are arranged upstream of the turbine wheel (10) with respect to an exhaust gas flow. The guide vane ring (22) is centered by means of a matched pair of two contact surfaces (24, 26) pressed against each other with respect to the turbine casing (4), of which at least the one contact surface (24 or 26, respectively) is formed conically.

Fan blade containment system includes a composite fan case with an annular composite shell extending from forward flange downstream to aft flange, and circumferentially varying thickness portion of composite shell. Annular composite back sheet spaced radially outwardly of annular composite shell has annular filler layer disposed radially therebetween. Annular forward and aft seams between annular composite shell and composite back sheet may axially trap filler layer. Circumferentially varying thickness portion may include aftwardly extending fingers of composite back sheet in aft seam and first thickness of fingers thicker than second thickness of composite shell circumferentially between fingers. Composite shell may extend from forward flange to aft flange. Aft flange bolted to metallic flange of metallic fan casing aft of aft flange. Containment system may circumscribe and surround fan and fan blades of gas turbine engine fan section.