Abstract: A cargo management system can include a receptacle and a removable storage device. The receptacle can be formed relative to an exterior panel of the vehicle and can have a rear wall spaced apart from an outer surface of the exterior panel. The outer surface can have a first contour. The removable storage device can be removably received in the receptacle and selectively secured to the vehicle. The storage device can include an upper portion, a lower portion and a latch mechanism. The upper portion can be pivotable relative to the lower portion to provide access to an interior of the storage device. The latch mechanism can selectively secure the storage device to the vehicle when in a stored position in the receptacle. An outer surface of the upper portion and the lower portion can include a second contour, where the second contour can substantially match the first contour.

Abstract: A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.

Abstract: A cargo management system can include a receptacle and a removable storage device. The receptacle can be formed relative to an exterior panel of the vehicle and can have a rear wall spaced apart from an outer surface of the exterior panel. The outer surface can have a first contour. The removable storage device can be removably received in the receptacle and selectively secured to the vehicle. The storage device can include an upper portion, a lower portion and a latch mechanism. The upper portion can be pivotable relative to the lower portion to provide access to an interior of the storage device. The latch mechanism can selectively secure the storage device to the vehicle when in a stored position in the receptacle. An outer surface of the upper portion and the lower portion can include a second contour, where the second contour can substantially match the first contour.

Abstract: A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.

Abstract: A gas turbine engine component, typically either a turbine blade or vane or combustor, comprising a wall (40) with a first surface (39) which is adapted to be supplied with a flow of cooling air, and a second surface (38) which is adapted to be exposed to a hot gas stream (50). The wall (40) further having defined therein a plurality of passages (57), the passages (57) defined by passage walls (54), which interconnect a passage inlet (31) in said first surface (39) to a passage outlet (32) in said the second surface (38). The passages (57), cooling air and the hot gas stream (50) arranged such that in operation a flow (52) of cooling air is directed through said passages (57) to provide a flow (36) of cooling air over at least a portion of the second surface (39). The cross sectional area of each of the passages (57) progressively decreasing overall, in the direction of cooling air flow (52) through the passage (57), such that in use the flow of cooling air (52) through the passage (57) is accelerated.