A gas turbine engine blade includes a blade portion having a leading edge and a trailing edge. A first surface connects the leading edge to the trailing edge and a second surface connects the leading edge to the trailing edge. A tip section is located at a first end of the blade portion and includes a pocket protruding into the tip section from an outermost end of the tip section. The pocket has a first side wall adjacent the first surface and a second side wall adjacent the second surface. At least one of the first side wall and the second side wall have a curve distinct from a curve of the corresponding adjacent surface.

A turbine bucket includes a leading edge, a trailing edge, a root portion, and a tip portion. The turbine bucket also includes one or more cooling passages extending through a body of the turbine bucket from an inlet to an outlet. The cooling passages are configured to route a cooling flow of fluid through the turbine bucket. The turbine bucket further includes a plenum defined within the tip portion to receive the fluid from the outlet of the cooling passages for expulsion of the cooling flow of fluid into a main flow path via at least one outlet hole proximate the trailing edge of the turbine bucket.

A propeller blade comprises a root, a tip distal from the root, a trailing edge extending from the root to the tip, a trailing edge, e.g. foam, insert, a shell forming an outer surface of the propeller blade and a plurality of stitches of yam extending through two parts of the shell adjacent the trailing edge, wherein the yarns do not extend through the trailing edge insert.

The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.

A system and method for records management and classification of files in a content management system having a server system that stores the files. A system detects when at least one of the files is classified by a user of a client computing system as a classified file, and based on the detecting of the classification of the one or more files, each classified file is removed from the client computing system. The system further detects when at least one of the files is declared as a permanent record by the user of the client computing system, and based on the detecting of the declaration as a permanent record, prevents editing by the client computing system of each file declared as a permanent record.

An airfoil arrangement for a gas turbine engine may include a support device using a shape memory alloy to support and control the airfoil. The support device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

An impeller associated with a compressor of a gas turbine engine includes a plurality of impeller blades. Each impeller blade of the plurality of impeller blades has a leading edge and a trailing edge opposite the leading edge in a streamwise direction. Each impeller blade of the plurality of impeller blades extends in a spanwise direction from a hub at 0% span to a tip at 100% span, and each impeller blade of the plurality of impeller blades has a plurality of mean camber lines that each extend from the leading edge to the trailing edge at a respective spanwise location. The leading edge includes a partially swept leading edge surface defined between 70% span to 100% span that extends in the streamwise direction between 3% to 15% of a mean camber line at 100% span.

An impeller for use in a fan system includes a hub extending along an axis of rotation and having a hub outer surface. There also are a plurality of blades extending radially outwardly of the hub outer surface. The blades have a unique cross-section at several different locations that result in relatively thin blades. A fan system and method are also disclosed.

A fixture for locating a straight edge of a curved surface of a part and holding the part in a fixed position during performance of a machining operation on the straight edge is described. The fixture includes: one or more supports for seating a convex curved surface of the part, one or more detachable end stops arranged to extend in a plane orthogonal to that in which the supports sit and against which, in use, the straight edge can be aligned, and a clamp arranged, in use, to push the convex curved surface against the supports such that the straight edge contacts the supports without obstruction of the straight edge.

A blade structure with multiple blade angles and a heat dissipation device include: the blade structure consisting of a plurality of blades with different blade angles. The blade angles of the blades decrease from an inner side to an outer side along a longitudinal direction of the blade structure. The blades have top portions on the same surface and are integrally formed in one piece. A joint between the blades has a transition part. The blade structures are evenly mounted on the hub and are connected to an outer frame. The hub and the blade structures are integrally formed in one piece, or the hub, the blade structures, and the outer frame are integrally formed in one piece. The blade structures can guide air flow to reduce air shedding, suppress backflows, reduce vortex turbulence, increase air volume, improve heat dissipation efficiency, and reduce vortex noise and vibration.