A compressor wheel assembly for a forced induction device includes an impeller member and a plate member. The impeller member is formed of a polymer material, and includes a hub portion and a plurality of blades extending from an outer surface of the hub portion. The hub portion includes an outer peripheral portion formed therewith. The plate member is connected to the outer peripheral portion of the impeller member to be rotationally fixed thereto. The plate member being formed of a metal material.

Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

A guide vane includes an airfoil with a first end and a second end. A platform is disposed at a first end of the airfoil, and a K-gusset is disposed on the platform opposite the airfoil. The K-gusset includes four bosses and ribs extending between the bosses in a K configuration.

A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.

A method of monitoring a component includes providing the component which includes a body having an exterior surface and a plurality of passive strain indicators configured on the exterior surface. The method includes directly measuring the component with at least one three-dimensional data acquisition device. The direct measurement generates a first point cloud and a plurality of second point clouds. The first point cloud corresponds to the exterior surface and includes a plurality of first data points, each data point having an X-axis coordinate, a Y-axis coordinate, and a Z-axis coordinate. Each second point cloud corresponds to one of the plurality of passive strain indicators and includes a plurality of second data points, each data point having an X-axis coordinate, a Y-axis coordinate, and a Z-axis coordinate. A second data point density of each second point cloud is greater than a first data point density of each first point cloud.

Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

A turbomachine component with a stress relief cavity includes an airfoil and a platform. The airfoil has a trailing edge. The platform has a trailing edge region, a seal strip slot and a stress relief cavity. The trailing edge region supports at least a part of the trailing edge. The stress relief cavity extends inside the platform into the trailing edge region and is an extension of the seal strip slot.

An exhaust flue includes an exhaust chimney body, and an open end multi-hole area. The exhaust chimney body defines a passage for discharging exhaust gas. The open end multi-hole area is an area in which multiple holes are defined around a total circumference of an open end of the exhaust chimney body.

A structure providing compliance and sealing between ceramic or ceramic composite (CMC) part and a metallic part has an interface component for centering the CMC part in the metallic part, thus reducing thermal stress motion of the CMC component. In gas turbine engine applications, the structure comprises a CMC blade track inserted in a clip placed within a metallic hanger. The clip provides for radial compliance and secures controlled leakage of cooling air required to ensure that acceptable temperatures are maintained for the metallic structures. A washer is positioned adjacent to the clip provide for axial orientation of the blade track.

A rotor disc configured to reduce the likelihood of fractures developing in spindle bolts in gas turbine engines is disclosed. The spindle bolts extend axially through the rotor disc to retain the rotor assembly in place in the gas turbine engine. The rotor disc may be formed from a rotor disc body having a plurality of circumferentially positioned spindle bolt holes sized to house a spindle bolts within each spindle bolt hole. One or more relief channels, which also may be referred to as scallops, may extend radially outward from one of the spindle bolt holes. The relief channels may foster removal of condensation and debris from the space between the spindle bolt and the surface forming the spindle bolt hole and may be configured to discourage the ingress of air through the relief channel and into space between the spindle bolt and the surface forming the spindle bolt hole.