An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.

A seal assembly includes a rotating seal runner having an outer radial surface, and one or more rotationally stationary seal rings located radially outboard of the seal runner. Each seal ring has an inner radial surface, with the inner radial surface and the outer radial surface defining a sealing interface therebetween. An axially extending shape of the inner radial surface is selected utilizing a predicted shape of the outer radial surface at a selected operating condition of the seal assembly.

A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier. The turbine outer case is arranged circumferentially around an axis. The blade track segment includes an arcuate runner that extends circumferentially partway around the axis to define a gas path boundary of the turbine shroud assembly and an attachment feature that extends radially outward from the runner. The carrier is configured to couple the blade track segment to the turbine outer case.

A turbine wheel for a turbine of an exhaust gas turbocharger. The turbine wheel has a base body comprising a back wall and a plurality of turbine blades, connected to the base body, which each comprise a leading edge. The leading edges are designed to be wave shaped.

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.

A single-crystal turbine blade and a method of making such single-crystal turbine blade are disclosed. During manufacturing, a secondary crystallographic orientation of the material of the single-crystal turbine blade is controlled based on a parameter of a root fillet between an airfoil of the single-crystal turbine blade and a platform of the single-crystal turbine blade. The parameter can be a location of peak stress in the root fillet expected during use of the turbine blade.

A vane assembly for use with a gas turbine engine includes an outer wall, an inner wall, and a plurality of airfoils. The outer wall and the inner wall extend at least partway about an axis. At least one of the airfoils is coupled with the outer end wall and the inner end wall to transmit force loads through the vane assembly.

A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier assembly. The carrier assembly includes a forward carrier segment and an aft carrier segment, and each of the forward carrier segment and aft carrier segment include integrated pins. The carrier assembly is configured to couple the blade track segment to the turbine outer case.

A turbine housing for a turbocharger includes an inlet passage and an outlet passage connected to a turbine housing body. The outlet passage has a longitudinal axis and comprises a first section and a second section downstream of the first section. The first section includes a first inlet opening having a first cross-sectional area, a first outlet opening downstream of the first inlet opening, and a first length between the first inlet opening and the first outlet opening, wherein the first section has an opening angle between 0° and 10° relative to the longitudinal axis along the first length. The second section downstream of the first section includes a second inlet opening, a second outlet opening downstream of the second inlet opening, a second cross-sectional area at least 1.8 times greater than the first cross-sectional area, and a second length between the second inlet opening and the second outlet opening that is less than 50% of the first length.

Turbomachine components and compressors are provided. The turbomachine component includes a platform and a mounting portion that extends from the platform. The mounting portion includes a dovetail received by a slot defined in the turbomachine. The slot includes a floor and a ceiling. The dovetail includes an inner surface and an outer surface. A hole is defined in the dovetail from an inlet at the inner surface to an end wall. The hole has a cylindrical portion and a tapered portion. A mechanical spring is disposed within the hole and in contact with the floor and the end wall such that the outer surface of the dovetail is forced into contact with the ceiling of the slot.