An assembly for a turbomachine extending along an axis includes a combustion chamber having, at its downstream end, a downstream flange having a radially extending part. The assembly further includes a distributor disposed downstream of the combustion chamber and having a platform from which at least one vane extends radially. The platform includes an upstream flange extending radially and delimiting, with the radial part of the downstream flange disposed opposite it. An annular space for the circulation of cooling air opens into the combustion chamber at its radially internal end and has, at its radially external end, means of sealing attached to the distributor.

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

A method of providing an engine family includes providing a first engine having a low pressure turbine driving a low pressure compressor at a first speed ratio, and a high pressure turbine driving a high pressure compressor. The method includes providing a second engine by changing the first speed ratio of the first engine to a second speed ratio.

A method of providing an engine family includes providing a first engine having a low pressure turbine driving a low pressure compressor at a first speed ratio, and a high pressure turbine driving a high pressure compressor. The method includes providing a second engine by changing the first speed ratio of the first engine to a second speed ratio.

An airfoil for a gas turbine engine, which has an airfoil body extending in a spanwise direction and in a chordwise direction, a platform located at an inner end and/or an outer end of the airfoil body, and a fillet at a junction between the airfoil body and the platform. The fillet has a radius distribution at a given chordwise location, the radius distribution varying from the platform to the airfoil body in the spanwise direction. The radius distribution defines a local minimum, the radius of the fillet at the given chordwise location increasing from the local minimum along the spanwise direction toward both of the airfoil and the platform. A local maximum of the radius distribution is offset from the local minimum along the spanwise direction, the radius decreasing from the local maximum along the spanwise direction toward both of the airfoil and the platform.

An airfoil for a gas turbine engine, which has an airfoil body extending in a spanwise direction and in a chordwise direction, a platform located at an inner end and/or an outer end of the airfoil body, and a fillet at a junction between the airfoil body and the platform. The fillet has a radius distribution at a given chordwise location, the radius distribution varying from the platform to the airfoil body in the spanwise direction. The radius distribution defines a local minimum, the radius of the fillet at the given chordwise location increasing from the local minimum along the spanwise direction toward both of the airfoil and the platform. A local maximum of the radius distribution is offset from the local minimum along the spanwise direction, the radius decreasing from the local maximum along the spanwise direction toward both of the airfoil and the platform.

A nozzle is provided for increasing the velocity of a fluid flowing therethrough, such as steam or other working fluid. The nozzle generally includes a body portion with a conical helical passage formed through the body portion to define an unlet port and an outlet orifice. The passage diameter can decreases continuously from the inlet port to the outlet orifice. Further, the conical helical passage can be a right-handed helix. To aid in manufacture and repair, the body can be divided into quadrants, where each plane of division passes through the center axis of the body portion. The present nozzle can be, for example, inserted into a steam turbine nozzle box as s retrofit for increasing the velocity of the steam incident on the turbine blades to increase turbine efficiency.

A nozzle is provided for increasing the velocity of a fluid flowing therethrough, such as steam or other working fluid. The nozzle generally includes a body portion with a conical helical passage formed through the body portion to define an unlet port and an outlet orifice. The passage diameter can decreases continuously from the inlet port to the outlet orifice. Further, the conical helical passage can be a right-handed helix. To aid in manufacture and repair, the body can be divided into quadrants, where each plane of division passes through the center axis of the body portion. The present nozzle can be, for example, inserted into a steam turbine nozzle box as s retrofit for increasing the velocity of the steam incident on the turbine blades to increase turbine efficiency.

A turbine includes: a turbine blade wheel housed in a housing unit; two turbine scroll flow paths wound radially outward with respect to the turbine blade wheel and connected at positions different from each other in a circumferential direction in an outer circumferential portion of the housing unit; and two scroll outlets each communicating one of the two turbine scroll flow paths with the housing unit, the two scroll outlets formed along the circumferential direction, at least one of the two scroll outlets having a height distribution in which a height in an axial direction is lower than a surrounding height at at least one of an upstream end or a downstream end.

A steam turbine member has suppressed adhesion of scale for a long time without deterioration of corrosion resistance and the like of a turbine. A steam turbine member includes a hard layer 2 and a deposited amorphous carbon film 3 on a base material 1, in that order.