A method for forming a coated turbine component and a coated turbine component is provided. The method includes a step of providing a component having a substrate including a trailing edge face. The method further includes a step of applying a thermal barrier coating or environmental barrier coating selectively to the substrate to form a discontinuous transition from a hot gas path surface at the trailing edge face to discourage hot gas flow along the trailing edge face.

In a turbine rotor blade assembly 1 of the present invention, each turbine rotor blade 10 includes a platform 11 having a blade root 12 fixed to a turbine disk 30, a profile 13 rising from the platform 11, and a shroud 14 provided at a top end of the profile 13. The shroud 14 of the present invention includes a first contact end part 15 that comes into contact with an adjacent shroud adjacent to one end side in a circumferential direction, a second contact end part 16 that comes into contact with an another adjacent shroud adjacent to the other end side in the circumferential direction, and a main body part disposed between the first and second contact end parts 15 and 16. One or both of the first and second contact end parts 15 and 16 are lower in rigidity than the main body part.

A boundary layer turbomachine (100) can include a housing (110) defining an interior space (115) and having an inlet opening (112) and an outlet (113) opening to facilitate movement of a fluid through the housing (110). The boundary layer turbomachine (100) can also include a rotor assembly (120) disposed in the rotor chamber (117) and configured to rotate about an axis of rotation (101). The rotor assembly (120) can have a plurality of disks (121) spaced apart along the axis of rotation (101) and defining an interior opening along the axis of rotation (101). The fluid can pass through gaps between the disks (121) and the interior opening as the fluid moves through the housing (110). Corresponding rotor assembly and partition are also provided.

Wind funnel and gas combustion turbine systems are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a compression section of a gas combustion turbine that is fueled by a hydrocarbon fuel source such as natural gas. Compressed air from the wind funnel may enter the compression section at selected locations. The compression section may have a front relatively low compression section and a downstream relatively higher compression section, and the compressed air from the wind funnel may be selectively delivered to one or both of the lower and higher compression sections. In addition, ambient air may be introduced into the lower compression section. During periods when compressed air from the wind funnel is delivered to the downstream higher compression section, the front lower compression section may be decoupled from the downstream section.

Wind funnel and gas combustion turbine systems are disclosed. Air travels through a wind funnel where it is compressed, and then flows into a compression section of a gas turbine that is fueled by a hydrocarbon fuel source such as natural gas. Compressed air from the wind funnel enters the compression section of the gas turbine through one or more air inlets toward multiple rotating turbine blades in an air feed direction having a component normal to air impact surfaces of the turbine blades. In addition to the compressed air from the wind funnel, ambient air may be introduced into the compression section of the gas combustion turbine.

A gas turbine engine blade according to an example of the present disclosure includes a blade including internal walls defining a blade cooling passage and a tip section at a radially outer end of the blade. The tip section includes a pocket protruding into the tip section from a radially outermost end of the tip section to a pocket floor. The blade further includes a pocket wall defined between the pocket floor and the radially outermost end of the tip section and including a tapered wall cooling passage.

An airfoil for a gas turbine engine comprises at least three successive sections defined between a root and a tip. A first decrease of maximum thickness-to-chord ratios defined by a difference between a maximum thickness-to-chord ratio at the root and a maximum thickness-to-chord ratio at a first spanwise position, a second decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the first spanwise position and a maximum thickness-to-chord ratio at a second spanwise position, a third decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the second spanwise position and a maximum thickness-to-chord ratio at the tip, the second decrease being greater than the corresponding first and third decreases.

A ceiling fan or similar air-moving device can include a motor for rotating one or more blades to drive a volume of air about a space. The blade can include a body having an outer surface with a flat top surface and a flat bottom surface, and a side edge. A curved transition can extend between one of the flat top surface or the flat bottom surface, and the side edge. The curved transition can include an elliptical curvature.

A containment structure for surrounding a rotatable machine includes a double-walled inner shell having a forward end, an aft end, and a substantially cylindrical body extending therebetween. The inner shell includes an inner wall at least partially surrounding a bladed portion of the bladed rotor, and an outer portion that branches radially outward from the inner wall. The containment structure also includes a substantially cylindrical back sheet coupled to the outer portion and disposed radially outward of the inner wall.

A fan blade includes an arc-shaped body and a connecting portion. The arc-shaped body has a main portion and an end portion connected to the main portion, wherein a width of the end portion is gradually decreased in a direction away from the main portion. The connecting portion is connected to the main portion, and the end portion and the connecting portion are respectively located at two opposite sides of the main portion. A fan structure is also provided.