A compressor stator vane unit includes multiple compressor stator vanes disposed at a certain interval in a circumferential direction; and an annular joint member connected with inner ends of the multiple compressor stator vanes; wherein the annular joint member constitutes an outer diameter side surface of a leakage fluid flow path provided in an inner diameter side of the joint member to communicate a high-pressure space with a low-pressure space respectively located downstream and upstream of the multiple compressor stator vanes in a fluid flow direction, and D/P is set to 0.05≤D/P≤0.2, wherein D is defined as a distance in an axial direction between an upstream end surface of the annular joint member and an upstream edge of the multiple compressor stator vanes in the fluid flow direction and P is defined as a pitch between the adjacent compressor stator vanes in the circumferential direction.

A turbine rotor blade root is additively manufactured and includes a shank having a radially extending chamber defined therein. A blade mount is at a radial inner end of the shank. The blade mount has a hollow interior defined therein with the hollow interior in fluid communication with the radially extending chamber. A lattice support structure is disposed within the hollow interior of the blade mount.

An environmental barrier coating, comprising a substrate containing silicon; an environmental barrier layer applied to said substrate; said environmental barrier layer comprising a rare earth composition.

A rotary machine assembly for a turbomachine, such as a rotor, having a rotor wheel where a plurality of circumferentially spaced female dovetail slots are obtained. The rotary machine assembly also comprises a plurality of blades. Between each blade and the adjacent one there is an interface angle. Each blade comprises a male dovetail, configured to fit with a corresponding female dovetail slot of the rotor wheel along an insertion direction. The female dovetail slots are shaped so that the insertion direction of each male dovetail is convergent with the rotation axis of the rotor wheel, so as to form with it an insertion angle, so as to insert gradually all the male dovetails into the female dovetail slots and packing them also gradually. A method for assembling a rotary machine assembly, which does not require any specific tool, is also disclosed.

This composite-material blade formed by using a fiber-reinforced resin containing a resin and reinforcing fibers is provided with: a base material part provided on the inner surface of the composite-material blade; and a first cover part for covering the outer surface of the base material part. The base material part is formed by using a carbon fiber-reinforced resin containing a first resin and carbon fibers. The first cover part is formed from an elastic polymer fiber-reinforced resin containing a second resin and elastic polymer fibers, and has more resistance to impact than the base material part.

A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.

A wind turbine apparatus has a tower and a plurality of blades rotatably mounted relative to the tower. Each of the plurality of blades has a reflective media on a surface thereof. The reflective media has at least a pair of primary colors. Each primary color is different from each other. The reflective media on one of the plurality of blades is arranged in an order different than in order of the reflective media of an adjacent blade. The reflective media can further include a mixed color of white. The reflective media comprises bands extending across a surface of the blade.

A polymer airfoil assembly is disclosed and includes at least one cooling passage for circulating coolant to remove heat from the polymer airfoil portion.

A rotor disc for a turbomachine, the disc extending circumferentially about an axis and including a plurality of cavities configured to receive blade roots, each cavity including a downstream radial wall configured to axially block the blade root in the cavity, each downstream radial wall including a channel of ventilation of the cavity, including an inlet orifice which opens into the cavity and an outlet orifice which opens onto a downstream surface of the disc. An assembly for a turbomachine including such a disc and an upstream retention ring and a turbomachine including such an assembly.

A steam turbine blade includes a blade body (7) including blade surfaces (70) extending in a blade height direction. The blade body (7) includes a first suction port (74) extending in the blade height direction and opening in the blade surface (70), a first drain flow path (75) internally extending in the blade height direction, and first communication passages (76) internally provided away from one another in the blade height direction and independently of one another and making the first drain port (74) and the first drain flow path (75) in communication with each other.