A blade includes: an airfoil portion having a pressure surface and a suction surface each of which extends between a base end and a tip end along a blade height direction between a leading edge and a trailing edge; and an internal passage passing through an inside of the airfoil portion, the internal passage having a first opening end opening to one of the pressure surface or the suction surface and a second opening end which is positioned closer to the tip end than the first opening end in the blade height direction and opening to a surface of the airfoil portion. When L is a length from the base end to the tip end in the blade height direction, a distance from the base end to the first opening end in the blade height direction is not less than zero and not greater than 0.3 L.

This vehicular cleaner is provided with: an air blowing portion having an intake port through which air is taken in, the air being ejected to a cleaning object; and a filter which is provided at the air intake port, prevents foreign matter from entering the air blowing portion, and allows air to pass through the filter.

An airfoil for a gas turbine engine is disclosed. In various embodiments, the airfoil includes a cooling passage; an outer wall separating a core flow path from the cooling passage; a diffuser in fluid communication with the cooling passage and opening into the core flow path, the diffuser being characterized by a linear ridge on a downstream end of the diffuser; and a thermal barrier coating covering the outer wall and the linear ridge.

A turbine vane assembly adapted for use with a gas turbine engine includes an airfoil and a spar. The airfoil is formed to define a cavity that extends into the airfoil. The spar is located in the cavity to define a cooling passage that extends around the spar between the spar and the airfoil. The turbine vane assembly includes cooling features to aid heat transfer of the turbine vane assembly during operation in the gas turbine engine.

An assembly for a gas turbine engine includes ceramic material containing (i.e. ceramic matrix composite) segments and joints that couple the segments together.

A structure for improving performance of cooling a blade of a gas turbine is provided in which interaction vortexes are generated between working fluid flowing along a surface of the blade and cooling fluid discharged onto the surface from an internal flow passage of the blade. The blade includes a surface structure formed by a gas hole having an outlet communicating with the surface of the blade to discharge the cooling fluid; and a vortex relief generator disposed so as to protrude from an inner periphery of the outlet and configured to generate counter vortexes having directionality opposite to the interaction vortexes so that the interaction vortexes are relieved by collision with the counter vortexes. The vortex relief generator includes a pair of opposing fins disposed in a path of the cooling fluid, each of which has a first surface to change a flow direction of the cooling fluid.

An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.

An exhaust device for a combined cycle power plant, includes a diffuser and a plenum. The diffuser includes a first wall, a second wall, a diffuser inlet, a diffuser outlet, and a diffuser flow path. The first and second walls extend circumferentially about a centerline axis of the exhaust device. The second wall is spaced from the first wall. The diffuser flow path is defined between the first and second walls, and extends from the diffuser inlet to outlet. The plenum includes an inlet wall portion and a non-circular plenum outlet, where the inlet wall portion is coupled to the diffuser outlet. The non-circular plenum outlet is spaced from the diffuser outlet along an axial direction of the exhaust device.

A fan includes an impeller including a boss serving as a center of rotation and a plurality of blades provided on an outer circumferential surface of the boss, and a structure member installed on an upstream side of the impeller in an airflow direction. The plurality of blades each have a plurality of recesses disposed only on a side of a suction surface of a leading edge. The plurality of recesses each have a rectangular shape having two longitudinal sides. Consequently, it is possible to reduce fluctuations of lift on the plurality of blades and thereby reduce discrete frequency noise.

An assembly comprising a lubricating wheel and lubricant nozzles for a planetary gear speed reducer of a turbomachine, the wheel having a lubricator configured to supply lubricant to the nozzles and the bearings of the planetary carriers of the reducer, the wheel being intended to be mounted coaxially on an annular wall of an axis of rotation X of a planetary carrier of the reducer, the wheel having a bearing and attachment surface on the annular wall of the planetary carrier, the lubricant nozzles being distributed around the axis and each having a generally elongated shape, the nozzles having first longitudinal ends for fluidly connecting to the lubricator of the wheel, wherein the first ends of the nozzles being configured to be attached to the wheel before mounting the wheel on the annular wall of the planetary carrier.