Abstract: One aspect of the present application provides an apparatus comprising a shape operable as a gas turbine engine component, an internal cavity within the shape including a radius, a trench on an external surface of the shape including a rear face tangential to an arc centered on the radius of the internal cavity, and a cooling hole extending from the internal cavity and exiting to the trench through the rear face of the trench wherein a cooling fluid introduced to the internal cavity flows through the cooling hole and into the trench during operation of the gas turbine engine component.

Abstract: A modular mounting structure is described which allows for the easy installation and removal of various payloads from a vehicle structure. An embedded electrical bus feature further supports the installation of the various payloads into the vehicle structure.

Abstract: A method for making a gas turbine engine ceramic matrix composite airfoil is disclosed. The method includes fabricating an airfoil preform that has a slotted forward end and a continuous trailing end. The slotted forward end of the airfoil preform is coupled to an airfoil core insert. A ceramic matrix composite covering is applied to cover the slots of the airfoil perform. The continuous trailing end of the airfoil preform is removed to expose the slots. A gas turbine engine airfoil is also disclosed.

Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A clamp mechanism couples the inner platform and the outer platform to the ceramic-containing airfoil.

Abstract: A turbine shroud or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter.

Abstract: One aspect of present application provides an intermediate structure in a gas turbine engine. The intermediate structure is positioned between a first component and another component. The first component may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure.

Abstract: A turbine shroud for a gas turbine engine includes a carrier and a blade track segment. The carrier is formed to include an inwardly opening blade track channel and the blade track segment is positioned in the blade track channel to couple the blade track segment with the carrier.

Abstract: A blade and method for producing the blade for a gas turbine engine are described herein. The blade may include a composite airfoil. The airfoil may comprise a ceramic material, and a distal end. A tip may extend from the distal end of the airfoil. The tip of the airfoil may comprise a substantially porous structure and may comprise infiltrated material extending from an airfoil preform to a tip preform to join the airfoil preform and the tip preform.

Abstract: A technique is directed to launching an unmanned aerial vehicle (UAV). The technique involves positioning a UAV launcher over a ground location. The technique further involves installing, after the UAV launcher is positioned over the ground location and prior to launching the UAV, an anchor into the ground location to anchor the UAV launcher to the ground location. The technique further involves operating, after the UAV launcher is anchored to the ground location, the UAV launcher to impart launching force onto the UAV to launch the UAV, the anchor holding the UAV launcher substantially in place at the ground location to minimize energy loss as the UAV launcher imparts launching force onto the UAV. In some arrangements, the UAV launcher is capable of pivoting while remaining anchored between launches to accommodate changes in wind direction while maintaining substantial connection to the ground location for enhanced consistency and performance.

Abstract: An apparatus and method for attachment of a payload or store to the external surface of an aerial vehicle includes a single point release feature. The apparatus includes an elongated base having a first distal end and a second distal end. A retention receptacle including a hollow tube is disposed adjacent the first distal end and is configured to removably receive and retain the store or payload. In addition, a release receptacle housing a release mechanism assembly is disposed adjacent said second distal end. When the release mechanism assembly is in the closed and locked position, the store or payload is retained to the vehicle via a spring loaded lock pin advanced into the retention receptacle. When the release mechanism assembly is in the open and unlocked position, the store or payload may be disengaged from the vehicle.

Abstract: A modular mounting structure is described which allows for the easy installation and removal of various payloads from a vehicle structure. An embedded electrical bus feature further supports the installation of the various payloads into the vehicle structure.

Abstract: An aircraft camera system provides visibility to a vehicle's environment. The vehicle has a set of vehicle surface portions (e.g., aircraft sections, panels, surfaces, combinations thereof, etc.) which defines a shape of the vehicle. The aircraft camera system includes a set of cameras integrated with the set of vehicle surface portions to avoid adding fluid drag force on the vehicle as the vehicle moves within the vehicle's environment. The aircraft camera system further includes a controller coupled to the set of cameras. The controller is constructed and arranged to obtain a set of camera signals from the set of cameras and output a set of electronic signals based on the set of camera signals. The set of electronic signals provides a set of images of the vehicle's environment from a perspective of the vehicle.

Abstract: The present disclosure provides for a turbine wheel having a blade platform disposed to compliantly secure ceramic turbine blades to a rotatable disk. The platform includes opposing ends to engage a portion of an airfoil of each turbine blade and radial extensions to engage a portion of a root of each turbine blade.

Abstract: A method and apparatus for attachment of a payload/store to the external surface of an aerial vehicle is disclosed. The method and apparatus comprises a single point release feature that simplifies the installation and removal of the payload.

Abstract: A level sensing device is disclosed that provides a lightweight but robust design and incorporates the use of an LVDT to determine the level of a fluid in a container.

Abstract: A blade for a gas turbine engine comprises a blade portion having a first end and a second end and an engagement portion including a first surface coupled to the second end of the blade portion and a second surface coupled to the second end of the blade portion, the first and second surfaces arranged to extend divergently away from one another. The engagement portion is adapted for coupling to a wheel included in a gas turbine engine wheel.

Abstract: A turbine vane for a gas turbine engine may include a composite airfoil structure. The composite airfoil structure may have an opening. The turbine vane may include a spar. The spar may have a body, which may be disposed within the opening. A standoff structure may be disposed within the opening. In some non-limiting embodiments, a cooling air gap may be defined between the body and an internal surface of the composite airfoil structure.

Abstract: In one embodiment, a gas turbine engine component includes a foam based core and a composite skin member. Both the foam based core and the composite skin member can be used to structurally support the gas turbine engine component. The composite skin member can be a CMC material and is used to partially encapsulate the foam core. The gas turbine engine component can take the form of an airfoil member such as a blade or a vane, a combustor liner, etc. A first portion of the composite skin member includes a first surface extending past an edge of the component creating a step approximate an edge section. In another embodiment, composite skin members can be used to form a continuous shape for the edge section such that the foam core forms part of a gas path surface.

Abstract: A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed.

Abstract: One aspect of present application provides an intermediate structure in a gas turbine engine. The intermediate structure is positioned between a first component and another component. The first component may be a composite component. The components may be interlocking. The intermediate structure may be load bearing. Also disclosed is a method using the intermediate structure.