Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.

Abstract: A cartridge for a ceramic matrix composite (CMC) seal segment of a segmented turbine shroud of a gas turbine engine is provided. The cartridge comprises a carrier segment and a CMC seal segment. A surface of the carrier segment and a surface of the CMC seal segment form a mating region proximate the entire perimeter of the CMC seal segment. The carrier segment surface may comprise a channel, and a compressible mating element may be disposed within the channel. Air may be supplied to a cavity, formed by the carrier and CMC seal segment, and the mating region.

Abstract: Approaches discussed herein enable a computing device to be tested to determine whether light from an emitter is bleeding through the device, which can be indicative of an assembly failure. A light blocking member can be placed over a camera in order to prevent a camera from capturing light coming from outside the device. At least one light source of the device then can be caused to emit light, and the camera can capture at least one image to determine whether any of the light is bleeding through the device and being detected by the camera. If so, the device can be determined to fail the test, and can be sent for reassembly or another remedial action. In some cases, a type of failure might be able to be determined, and information for the failure can be logged for purposes such as quality assurance and failure rate monitoring.

Abstract: An article includes an abradable ceramic coating with an arrangement of features selected such that the coating has a porosity of about 5% to about 90%.

Abstract: The disclosure describes a gas turbine engine blade that includes a dovetail portion comprising a first ceramic matrix composite, an airfoil portion comprising the first ceramic matrix composite, a transition portion between the airfoil portion and the dovetail portion, and a platform portion that substantially surrounds the transition portion. The airfoil portion may define a capture feature that is configured to engage with and mechanically restrain the platform portion from moving beyond the capture feature toward a tip of the airfoil portion.

Abstract: A number of variations may comprise a method comprising: a lubrication system for a transfer case comprising: actively managing an oil level in a plurality of sumps in a transfer case by rotating at least one rotating element in the transfer case to transfer oil through the transfer case to lubricate the transfer case.

Abstract: A lift device is disclosed that can be used to provide vertical lift to an aircraft or other vehicle. The lift device can include a fan that produces an airflow and a vane box that can direct the airflow. In one form the fan can be oriented at an angle relative to a reference plane in the aircraft. In another form the vane box can be oriented at an angle. The vane box can be structured to provide a maximum flow area between an aft flow vector and a forward flow vector.

Abstract: A cart for collecting and unloading agricultural bales, the cart including a cart body; a hitch, wherein the hitch includes a first end that is configured to operatively connect to a baler and a second end that is configured to operatively connect to the cart body, wherein the hitch provides a pitch degree of freedom to the cart relative to the baler, and wherein the hitch provides a roll degree of freedom to the cart relative to the baler; an automated conveyor device operatively connected to the cart body and configured to move the agricultural bales to a back end of the cart body; and at least one swivel wheel operatively connected to the cart body. In some embodiments, the automated conveyor device includes an apron-chain conveyor powered by a hydraulic motor controlled by hydraulic valves in a cab of a tractor being used to pull the baler and cart.

Abstract: One embodiment of the present invention is a unique aircraft propulsion gas turbine engine. Another embodiment is a unique gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines with heat exchange systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A gas turbine engine is disclosed having an air injection system useful to supply a relatively pressurized air to a flow path of a compressor. The air injection system includes a port cover operable to open and close a port through which the air can flow to the compressor from a relatively pressurized source. The port cover extends circumferentially around the gas turbine engine and can include a portion that is anchored and an opposite portion coupled to an actuator. Movement of the actuator causes the port cover to open and close the port. Biasing members can be used to urge the port cover into one of an open and closed position against the movement of the actuator.

Abstract: A gas turbine engine is disclosed having a thermoelectric device capable of changing a tip clearance in a turbomachinery component. In one non-limiting form the turbomachinery component is a compressor. The thermoelectric device can be used in some forms to harvest power derived from a waste heat. The tip clearance control system can include a sensor used to determine a clearance between a tip and a wall of the turbomachinery component.

Abstract: A vacuum induced aquatic environment comprising two or more compartments, each adapted to receive aquatic fluid; the two or more compartments disposed sufficiently proximal to each other to allow the aquatic fluid to partially or completely fill the two or more compartments; at least one of the two or more compartments operatively engaging one or more vacuum tubes; and the one or more vacuum tubes operatively engaging one or more motive means capable of creating a vacuum in the at least one of the two or more compartments. Alternatively, a vacuum induced aquatic environment further comprising one or more removable vacuum tubes.

Abstract: One embodiment of the present invention is a damping system for rotating machinery such as gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for damping systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: An aircraft propulsion system is disclosed herein. The aircraft propulsion system includes a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis. The aircraft propulsion system also includes a nacelle surrounding the core engine. The aircraft propulsion system also includes at least one free power turbine driven to rotate by exhaust gases exiting the turbine section. The aircraft propulsion system also includes at least one rotor module driven to rotate by at least one free power turbine. The aircraft propulsion system also includes first and second pylons extending away from the nacelle and operable to mount the core engine to an aircraft. The first and second pylons are spaced from one another on opposite sides of at least one plane containing the centerline axis and mirror one another across the at least one plane.

Abstract: A rotor blade assembly is disclosed herein. The rotor blade assembly includes a composite blade portion extending a length from a root to a tip. A leading edge of the composite blade portion extends from the tip to an end point along the length between the tip and the root. The rotor blade assembly also includes a base portion fixed to the composite blade portion proximate to the root. The rotor blade assembly also includes a sheath extending around the composite blade portion. The sheath is positioned along the length adjacent to the base portion and between the root and the end point of the leading edge.

Abstract: One form of the present invention contemplates an apparatus including a gas turbine engine core, wherein a gearbox accessory is mounted to the engine core and is substantially enclosed by an inner fairing. The apparatus can further include a nacelle having a plurality of panels, wherein the nacelle panels substantially enclose and overlap at least a portion of the inner fairing. The apparatus can further include a bypass duct defined between an exterior surface of the inner fairing and an interior surface of at least some of the nacelle panels. In additional and/or alternative forms a number of frame rods can also be used internal to the nacelle or nacelle panel. In some forms the frame rods can be connected between a front and rear frame.

Abstract: A method and device for coding and marking printing including defining a print image in dot formation of various sizes and locations; determining and providing a set of individual print control instructions for individually controlling a plurality of dot image print head nozzles to form the defined print image at absolute dot positions; and undertaking the individual control instructions to provide a printed image on a printing substrate corresponding to the defined print image, whereby the system allows for calculated adjustment of each dot position without computational limitation during the printing cycle.

Abstract: An electrical power generation apparatus is embedded in a contra-rotating propulsion system that includes overlapping first and second shafts operatively connected for counter-rotation about a common axis. The electrical power generation apparatus includes a winding mounted to one of the shafts and a field array mounted to the other of the shafts adjacent to the winding. Relative rotation of the winding and the field array induces electrical current in the winding.

Abstract: Embodiments of the present invention include a method and system for carrying out vapor-phase lubrication of a component, such as a bearing for example. The method and apparatus can be applied to a turbine engine. The method includes the step of directing a first stream of fluid containing atomized lubricant to the component at a first velocity. The system provides a first fluid injection system configured to perform the first step. The method also includes the step of directing a second stream of fluid at a second velocity less than the first velocity to the component. The second stream is for controlling a temperature of the component. The system provides a second fluid injection system configured to perform the second step. Both of the directing steps are carried out concurrently.

Abstract: One embodiment of the present invention is a unique thrust augmented gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for thrust augmented gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.