The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disc.

A housing assembly comprising a housing that has at least one first connection opening and one second connection opening, a first connecting piece with a first flange and a second connecting piece with a second flange. The first connecting piece is connected to the first connection opening and the second connecting piece is connected to the second connection opening. The housing additionally has a projection with an overhang. The A locking part of the first flange is arranged in locking engagement with the overhang, and the first flange and the second flange are configured in such a way and arranged with respect to one another that a turning of the first flange is prevented by the second flange. A corresponding method of fixing multiple connections to a housing is also provided.

According to one embodiment, a mini-disk of a gas turbine engine having an axis is provided. The mini-disk includes a bore, a web extending radially with respect to the axis of the gas turbine engine from the bore, a base extending axially with respect to the axis of the gas turbine engine from the bore, a connector located on an end of the base, the connector configured to connect with a hub arm of the gas turbine engine, and an expansion feature configured in the base and located between the bore and the connector, the expansion feature configured to reduce an axial stiffness of the base.

A heat shield includes a first wall defined between a first end and a second end; a second wall defined between the first end and the second end, the second wall connected to the first wall at the first and second ends; a space defined between the first wall and the second wall; and thermal insulation disposed in the space. A gas turbine engine and a method of installing a heat shield in a gas turbine engine are also disclosed.

A turbomachine subassembly including a first component forming a portion of a wall of a combustion chamber of the turbomachine and a second component forming a connecting member connecting the first component to a structural element of the combustion chamber, wherein the two components are made from materials having different coefficients of expansion, and wherein the two components are elements of revolution coaxial with a main axis A of the subassembly, and each including an annular radial wall, the radial walls facing one another and bearing against one another axially in a first direction, wherein the second component includes a plurality of clamping tabs, with the clamping tabs collaborating with the first component in order to produce an axial force causing the radial walls to bear against one another.

An inflator includes a housing, an impeller, and an airflow guide. The housing includes a intake port and a outlet port. A volute is defined between the first and outlet ports. The impeller is coupled to the housing and is in airflow communication with the volute. The impeller generates an airflow through the volute. The airflow guide is disposed in the housing and includes an air intake portion. A cutwater is monolithically formed with the air intake portion. The air intake portion is disposed flush with a portion of the volute and defines the first and port and a passageway extending from the intake port along an airflow axis. The cutwater extends from the air intake portion and is disposed between the passageway and the outlet port adjacent a circumferential edge of the impeller.

A borescope plug assembly includes a housing, a plug, and a spring. The housing extends between a first housing end and a second housing end. The housing includes a plug aperture, an internal chamber, and a bayonet interface. The plug aperture is located at the second housing end. The internal chamber extends from the plug aperture toward the first housing end. The plug includes a shaft, a first sealing surface, and at least one tab. The shaft extends between a first shaft end and a second shaft end. The first sealing surface is disposed at the first shaft end. The at least one tab projects radially outward from the shaft. The plug extends through the plug aperture with the second shaft end and the at least one tab disposed within the internal chamber. The spring is positioned within the internal chamber between the first housing end and the at least one tab.

A borescope plug assembly includes a housing, a plug, and a spring. The housing extends between a first housing end and a second housing end. The housing includes a plug aperture, an internal chamber, and a bayonet interface. The plug aperture is located at the second housing end. The internal chamber extends from the plug aperture toward the first housing end. The plug includes a shaft, a first sealing surface, and at least one tab. The shaft extends between a first shaft end and a second shaft end. The first sealing surface is disposed at the first shaft end. The at least one tab projects radially outward from the shaft. The plug extends through the plug aperture with the second shaft end and the at least one tab disposed within the internal chamber. The spring is positioned within the internal chamber between the first housing end and the at least one tab.

A turbocharger for an internal combustion engine is provided. The turbocharger includes at least three connections for respective lines. The at least three connections are arranged on the same side of the turbocharger. The turbocharger is designed in such a manner that the lines can be mounted with a common screw to the at least three connections.

The invention relates to a fan, in particular for a small turbine engine such as a jet engine, having a hub ratio corresponding to the ratio of the diameter of the inner limit of the air intake section (26) at the radially internal ends of the leading edges of the fan blades (10), divided by the diameter of the circle through which the outer ends of the fan blades pass, which has a value of 0.25 to 0.27.