Abstract: A fluid flow assembly may include an orifice plate having a set of orifices and a plenum defined by a blade outer air seal. The set of orifices may be aligned with and in fluid communication with the plenum. A gas turbine engine may include a vane outer support having an orifice plate, wherein the orifice plate includes a plurality of sets of orifices. The gas turbine engine may also include a blade outer air seal defining a plurality of plenums. Each set of orifices of the plurality of sets of orifices may be forward relative to and substantially axially aligned with a respective plenum of the plurality of plenums.

Abstract: A multi-air stream cooling system is provided. The multi-air stream cooling system may comprise an inner vane support, a flow guide, and a fastened inner duct. The inner vane support may partially define a first airflow path. The flow guide may couple to the inner vane support and may partially define a second airflow path. The fastened inner duct may couple to the flow guide and may partially define a third airflow path. The inner vane support may comprise a discharge slot to allow a first airflow into a blade rim cavity. The flow guide may comprise a tangential onboard injector (TOBI) to provide a second airflow through a cover plate. The flow guide may also comprise a bypass passage configured to enable a third airflow from the third airflow path.

Abstract: A combustor assembly for a gas turbine engine comprises a vane support ring; an annular combustor extending around a central axis and being located radially inwards of the vane support ring, the annular combustor including an aft end, a forward end with at least one opening through which at least one fuel nozzle is received, and an annular outer shell and an annular inner shell that define an annular combustion chamber there between, the annular outer shell including a radially-outwardly extending flange including at least one scallop cut; and a stop member integrally formed with the vane support ring.

Abstract: A seal ring includes a disk having a radially outer end and an orifice at a center forming a radially inner end, a plurality of holes extending through the disk, and a rail having an annular shape extending axially away from the disk at a position that is between the radially outer end and the plurality of holes extending through the disk with the rail being configured to direct the flow of fluid.

Abstract: A retention device includes a retention block including an opening extending through the retention block in a first direction. A tab also extends from the retention block in the first direction. A fastener extends through the opening and includes a head configured to engage the retention block. A clinch nut is coupled to the fastener with an interface surface of the clinch nut configured to engage the tab of the retention block.

Abstract: A suspension pad for suspending a workpiece with respect to a corrugated enclosure having a closure flap that is moveable between an open position, wherein an opening is defined in the corrugated enclosure, and a closed position, wherein the opening is obstructed by the closure flap. The suspension pad has a mid-section that is engageable with the workpiece, and at least one end portion moveable between a raised position, wherein the end portion is disposed within the corrugated enclosure, and a lowered position, wherein the end portion extends through the opening to hold the closure flap in the open position.

Abstract: Aspects of the disclosure are directed to a seal comprising: a first leg that emanates from a center point of the seal and is configured to contact a first component, a second leg that emanates from the center point and is configured to contact a second component that is operative at a temperature that is within a range of 648 degrees Celsius to 1093 degrees Celsius, and a third leg that emanates from the center point.

Abstract: A retention member for a component of a gas turbine engine and methods of using the same are provided. The retention member includes an annular body having a first side, a second side, a first end, and a second end, a retention element configured at the first end of the annular body and on the first side, the retention element configured to releasably engage with an interior surface of a case of the gas turbine engine, and a support element configured at the second end of the annular body, the support element configured to engage with a surface of at least one of a blade outer air seal or a blade outer air seal support.

Abstract: A suspension pad for suspending a workpiece with respect to a corrugated enclosure having a closure flap that is moveable between an open position, wherein an opening is defined in the corrugated enclosure, and a closed position, wherein the opening is obstructed by the closure flap. The suspension pad has a mid-section that is engageable with the workpiece and at least one end portion moveable between a raised position, wherein the end portion is disposed within the corrugated enclosure, and a lowered position, wherein the end portion extends through the opening to hold the closure flap in the open position.

Abstract: A corrugated container with integral dunnage for securing a cargo element with respect to the interior of the corrugated container, including at least one wall panel having a substantially planar surface, an aperture defined in the substantially planar surface, and a flap portion connected to the substantially planar surface adjacent to the aperture. The flap portion is subdivided into a plurality of sections that cooperate to define a dunnage element.