A liner for a combustor includes a support member, an intermediate member, and a liner member. The intermediate member is positioned intermediate the support member and the liner member and has a plurality of protrusions and a plurality of recesses. The support member is coupled to the intermediate member at a tangent of each protrusion. Additionally, the liner member is comprised of a ceramic matrix composite material. The liner member is coupled to the intermediate member at a tangent of each recess.

A system includes a gas turbine engine that includes a combustor section having one or more combustors configured to generate combustion products and a turbine section having one or more turbine stages between an upstream end and a downstream end. The one or more turbine stages are driven by the combustion products. The gas turbine engine also includes an exhaust section disposed downstream from the downstream end of the turbine section. The exhaust section has an exhaust passage configured to receive the combustion products as an exhaust gas. The gas turbine engine also includes a mixing device disposed in the exhaust section. The mixing device is configured to divide the exhaust gas into a first exhaust gas and a second exhaust gas, and to combine the first and second exhaust gases in a mixing region to produce a mixed exhaust gas.

According to various embodiments, disclosed is a fixed support and gutter system for a ring gear of a turbine engine gear train, the fixed support and gutter system comprising a support structure having an undulating path which forms at least a portion of a gutter structure for capturing oil shed off the gear train.

An aircraft nacelle comprising an air intake configured to channel an air flow in the direction of an engine assembly which comprises a fan with an axis of rotation, said air intake comprising, according to a flow direction of the air flow, a lip with a leading edge and an internal conduit which extends said lip towards the fan, wherein the air intake comprises a plurality of protrusions distributed over the circumference of the air intake and following each protrusion, a concave form configured in order to achieve compression of the air flow.

An engine component for a gas turbine engine generating hot combustion gas flow is provided. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The hot combustion gas flow defines an upstream direction and a downstream direction relative to the hot surface. The substrate also defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The passage comprises a metering section; and a diffusing section, with the diffusing section including a shelf, a first outer lobe and a second outer lobe.

An engine component for a gas turbine engine generating hot combustion gas flow is provided. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component also includes a flow conditioning structure provided upstream of the outlet on the hot surface. The flow conditioning structure can include a ridge extending from the hot surface.

A method for machining a workpiece is provided. An electrode is moved linearly in the direction of the workpiece to cause material to be removed from the workpiece, at least one end of a surface of the workpiece running obliquely to a guide edge of the electrode machining this surface. The electrode is moved at least partially with the electrode surface parallel to the surface, so that during the approach to the workpiece, areas of the workpiece having an irregular edge machined at a different intensity are formed, the difference in intensity of machining on the edge of the surface to be machined being compensated in that the surface to be machined is provided with a height profile adapted to the shape of the end of the surface to be machined. A blade ring segment and blade ring is also disclosed.

An impeller for an exhaust gas turbocharger may include a hub main body and blades arranged thereon. The hub main body may be configured as a polygon with a number of segments that may be tilted with respect to one another, the number of the segments corresponding to a number of the blades. Alternatively, the hub main body may have a main surface that faces the blades and undulates in a circumferential direction, a number of the undulations corresponding to the number of the blades.

A compressor wheel of a charging device may include a hub, a plurality of blades and a wheel back. The wheel back may have an undulating profile which extends from the hub in a radial direction. The undulating profile may include a plurality of regions. The plurality of regions may adjoin one another and may include a first concave region, a second convex region, a third concave region, and a fourth convex region. The second convex region may adjoin the first concave region. The third concave region may adjoin the second convex region. The fourth convex region may adjoin the third concave region.

An engine assembly for an aircraft, comprising a mast. The engine assembly comprises an engine with a horizontal engine axis, an engine shaft having a first end rigidly connected to the engine and a second end, and a reducer having an input shaft meshing with the second end, and an output shaft to which a propeller is fixed. The engine assembly is configured such that the engine is fixed to the mast by a rigid connection, the reducer is fixed to the mast by means of flexible fasteners, the rotation between the engine shaft and the input shaft being driven via a slide link, the engine shaft has a first part and a second part and, therebetween, a flexible part assuring a tolerance to an angular misalignment between the axis of the second part and the axis of the first part.