Abstract: According to an aspect, a support structure is integrally formed with a bearing compartment. The support structure includes a plurality of vertical supports and horizontal supports. The vertical supports and horizontal supports include one or more features to support machining of the bearing compartment and removal of the support structure from the bearing compartment.

Abstract: A method of additive manufacturing of a component is provided and includes building up the component to have a first uppermost layer and a foundation to have a second uppermost layer below the first uppermost layer, evacuating powder from around the component and the foundation to expose the second uppermost layer, disposing, on the second uppermost layer, a forged flange having an upper surface coplanar with the first uppermost layer, backfilling powder about the component and the forged flange and completing a building up of the component by building up on the forged flange.

Abstract: A method of additive manufacturing of a component is provided. The method includes building up the component to have a first uppermost layer and a foundation to have a second uppermost layer below the first uppermost layer, evacuating powder from around the component and the foundation to expose the second uppermost layer, disposing, on the second uppermost layer, a forged flange having an upper surface coplanar with the first uppermost layer, backfilling powder about the component and the forged flange, applying a thin additive manufacturing layer to the upper surface and completing a building up of the component by building up on the thin additive manufacturing layer.

Abstract: A method of manufacturing an (AM) component includes generating a computer-aided design (CAD) model of target AM component, and determining a target machining area on the target AM component. The target machining area is designated to receive a machining process. The method further comprises determining a witness line region corresponding to the target machining area of the component, and performing an AM component build to build the AM component and form a plurality of textured witness lines in the witness line region.

Abstract: According to an aspect, a support structure is integrally formed with a bearing compartment. The support structure includes a plurality of vertical supports and horizontal supports. The vertical supports and horizontal supports include one or more features to support machining of the bearing compartment and removal of the support structure from the bearing compartment.

Abstract: An oil distributor is provided for a bearing chamber. The oil distributor includes an outer annular manifold, which is integrally formed with an interior surface of the bearing chamber and which defines a first interior cavity receptive of pressurized oil which defines a first interior cavity receptive of pressurized oil, an inner annular manifold, which defines a second interior cavity and comprises an interior facing surface defining holes respectively communicative with the second interior cavity and one or more support struts by which the inner annular manifold is supported within the outer annular manifold. Each of the one or more support struts defines interior lines by which the pressurized oil flows from the first interior cavity to the second interior cavity and to the holes.

Abstract: According to an aspect, a bearing compartment includes a housing and a spring integrally formed with the housing. An oil passage is internally fabricated within the housing, and the oil passage extends into the spring. Further aspects can include a gas turbine engine with a bearing system and a method of manufacturing a bearing compartment.

Abstract: A method of additively manufacturing a component is provided and includes generating a three-dimensional (3D) model of the component, generating a heat map of the 3D model which is illustrative of thermal effects the component is expected to experience, updating the 3D model to include 3D heat exchange fin models for reducing the thermal effects and updating the 3D model with the 3D heat exchange fin models to include 3D weight reduction cavity models for weight-neutralizing the 3D heat exchange fin models.

Abstract: A method of manufacturing an (AM) component includes generating a computer-aided design (CAD) model of target AM component having a target physical profile, and predicting deformation of a target area that is expected to realize deformation. The method further includes determining a pre-deformed profile of witness lines that are to be formed in the target area based on the predicted deformation of the target area and that are expected to deform into a target profile indicating the target physical profile is met. The method further includes performing an AM component build to build the AM component and form pre-deformed witness lines having the pre-deformed profile in the target area.

Abstract: According to an aspect, a bearing compartment includes a body, one or more oil cooling channels integrally formed within the body, and one or more oil nozzles coupled to the one or more oil cooling channels. At least one of the one or more oil nozzles is oriented to direct oil toward a thermal zone with a predicted hot spot within the bearing compartment.

Abstract: A method of additively manufacturing a component is provided. The method includes generating a three-dimensional (3D) model of the component, generating a first heat map of the 3D model which is illustrative of first thermal effects the component is expected to experience during additive manufacturing, generating a second heat map of the 3D model which is illustrative of second thermal effects the component is expected to experience during operational use, updating the 3D model to include 3D heat exchange fin models for reducing each of the first and second thermal effects and updating the 3D model with the 3D heat exchange fin models to include 3D weight reduction cavity models for weight-neutralizing the 3D heat exchange fin models.

Abstract: According to an aspect, a bearing compartment includes a housing integrally formed with a spring configured to deform in response to a force. The housing includes an overhang region that is supported by the spring during an additive manufacturing build process. The spring includes a plurality of struts that extend axially within the housing.

Abstract: According to an aspect, a bearing compartment includes a housing having an upper housing portion and a lower housing portion, and a support structure fabricated within the bearing compartment. The support structure includes an upper portion within the upper housing portion and a spring section within the lower housing portion. The spring section includes a plurality of struts and is separable from the support structure for use as a spring within the housing.

Abstract: A bearing chamber is provided. The bearing chamber includes an interior surface comprising a terminal block defining a keyway and a conduit terminating at the keyway and an oil nozzle defining an internal channel. The oil nozzle includes a base tightly fittable in the keyway. When the base is tightly fit in the keyway, the internal channel is communicative with the conduit and an orientation of the keyway and a configuration of the oil nozzle are cooperatively established to aim the oil nozzle at a predefined target within the bearing chamber.

Abstract: A method of additive manufacturing of a component is provided. The method includes building up the component to have a first uppermost layer and a foundation to have a second uppermost layer below the first uppermost layer, evacuating powder from around the component and the foundation to expose the second uppermost layer, disposing, on the second uppermost layer, a forged flange having an upper surface coplanar with the first uppermost layer, backfilling powder about the component and the forged flange, applying a thin additive manufacturing layer to the upper surface and completing a building up of the component by building up on the thin additive manufacturing layer.

Abstract: A method of additive manufacturing of a component is provided and includes building up the component to have a first uppermost layer and a foundation to have a second uppermost layer below the first uppermost layer, evacuating powder from around the component and the foundation to expose the second uppermost layer, disposing, on the second uppermost layer, a forged flange having an upper surface coplanar with the first uppermost layer, backfilling powder about the component and the forged flange and completing a building up of the component by building up on the forged flange.

Abstract: A hybrid electric engine of an aircraft includes a compressor, a turbine operably connected to the compressor via a variable gear ratio gearbox and a combustor configured to drive the turbine via a flow of combustion products. An electric motor is operably connected to the variable gear ratio rear box and configured to input rotational energy into the gearbox. The input of rotational energy into the gearbox from the electric motor changes a rotational speed of one of the compressor or the turbine relative to the other of the compressor or the turbine.

Abstract: Examples described herein provide a computer-implemented method that includes monitoring a hybrid electric turbine engine of an aircraft, the hybrid electric turbine engine including a first electric machine associated with a high speed spool and a second electric machine associated with a low speed spool. The method further includes receiving an indication of a failed electric machine, the failed electric machine being an electric machine on another hybrid electric turbine engine of the aircraft. The method further includes, responsive to detecting the failed electric machine, distributing power from one or more of the first electric machine or the second electric machine to a spool associated with the failed electric machine.

Abstract: Disclosed is an inlet system for a gas turbine engine that extends along a longitudinal axial centerline, the inlet system comprising: an inner dome, a shroud located axially aft and radially outward of the inner dome with respect to the centerline, a splitter nose located radially inward of the shroud with respect to the centerline, a first plurality of struts radially disposed between the shroud and the splitter nose with respect to the centerline, a second plurality of struts radially disposed between the splitter nose and a bearing with respect to the centerline, a plurality of inlet guide vanes radially disposed between the splitter nose and the bearing with respect to the centerline, and the plurality of inlet guide vanes axially aft of the plurality of second struts with respect to the centerline.

Abstract: Disclosed is an inlet system for a gas turbine engine that extends along a longitudinal axial centerline, the inlet system comprising: an inner dome, a shroud located axially aft and radially outward of the inner dome with respect to the centerline, a splitter nose located radially inward of the shroud with respect to the centerline, a first plurality of struts radially disposed between the shroud and the splitter nose with respect to the centerline, a second plurality of struts radially disposed between the splitter nose and a bearing with respect to the centerline, a plurality of inlet guide vanes radially disposed between the splitter nose and the bearing with respect to the centerline, and the plurality of inlet guide vanes axially aft of the plurality of second struts with respect to the centerline.