Abstract: A variable vane system includes a unison ring driven by a harmonic drive. A multiple of pins extend from the unison ring. A multiple of variable vanes are driven by the unison ring, each of the multiple of variable vanes connected to the unison ring through a respective drive arm with a slot that receives one of the multiple of pins to accommodate axial motion a support that extends from an engine case to support the unison ring and a multiple of rollers to support the unison ring.

Abstract: A variable vane system for a gas turbine engine, comprising an actuator, a harmonic drive comprising a strain wave gearing mechanism comprising a fixed circular spline, a flex spline attached to an output shaft, and a wave generator attached to an input shaft driven by the actuator, the flex spline driven by the wave generator with respect to the circular spline, a drive gear driven by the output shaft along a first axis, and an actuator gear mounted to one of a multiple of variable vanes along a second axis transverse to the first axis, the actuator gear driven by the drive gear.

Abstract: In a compressor for a supercharger of an internal combustion engine comprising a shroud, an impeller, a vaneless diffuser, and a scroll, a hub-side wall of the vaneless diffuser is formed to be inclined to the opposite side to a shroud-side wall with respect to a direction perpendicular to a rotational axis of the impeller in the longitudinal cross section including the rotational axis of the impeller. With such a configuration, the amount of deposit formed on the hub-side wall of the vaneless diffuser is reduced.

Abstract: A cylindrical case includes a case main body made of a composite material of reinforcing fibers impregnated with a thermosetting resin, and an outward flange on the case main body. The outward flange includes: a bonding layer; a foundation layer disposed on the bonding layer; one flange constituting layer having a leg layer which is laminated from one slope surface of the foundation layer to the bonding layer and a wall layer which rises from the one slope surface; and the other flange constituting layer having a leg layer which is laminated from the other slope surface of the foundation layer to the bonding layer and a wall layer which rises from the other slope surface. The foundation layer is formed by laminating roving layers, while the flange constituting layers are formed by laminating a plurality of biaxial fabric layers including a biaxial fabric of a non-crimp structure.

Abstract: A series fan structure includes a series fan assembly and an assembling member. The series fan assembly has a first fan and a second fan. The first and second fans are correspondingly serially connected with each other. The first fan has a first fan frame defining a first receiving space. The second fan has a second fan frame defining a second receiving space. The assembling member is disposed between the first and second fan frames. The assembling member is formed with multiple straight-through perforations in communication with the first and second receiving spaces. The series fan structure improves the vibration and noise problem of the conventional series fan structure and is able to increase airflow volume.

Abstract: A heat exchanger assembly includes an outer manifold defining an outer cavity. An inner cavity is defined by an inner shell supported within the outer manifold and at least partially surrounded by the outer cavity. The inner shell includes a plurality of impingement openings for directing airflow into the inner cavity. An inner manifold is supported within the inner cavity. The inner manifold is exposed to impingement airflow through the plurality of impingement openings in the inner shell. The inner manifold includes a plurality of flow passages and at least one insulator pocket substantially aligned with the plurality of flow passages. A cooled cooling air system for a gas turbine engine and a gas turbine engine assembly are also disclosed.

Abstract: The technical field of the invention is steam turbines including a steam feed circuit based on a functional steam generator set that may be nuclear- or fossil-fuel powered, and in particular a steam feed circuit (1) of a turbine (2), comprising n main steam lines (3) and n? steam admission lines (4) to the turbine, the number n? of steam admission lines (4) to the turbine being strictly greater than the number n of main steam lines (3), characterized in that there are n direct steam admission lines (5) to the turbine linking the as main steam lines (3) directly to the steam admission lines (4) to the turbine.

Abstract: The present invention provides a thread groove pump mechanism which suppresses a backflow of the gas in the thread groove pump mechanism and reduces the pressure difference in the pump radial direction near the outlet of the thread groove pump mechanism to thereby improve the exhaust performance and the compression performance. The present invention also provides a vacuum pump including the thread groove pump mechanism, and a rotor, an outer circumference side stator, and an inner circumference side stator used in the thread groove pump mechanism. A thread groove pump mechanism includes an exhaust-performance improving means in an outer-circumference-side thread groove portion engraved on an opposite surface of an outer circumference side stator opposed to a rotor cylinder portion and an inner-circumference-side thread groove portion engraved on an opposite surface of an inner circumference side stator opposed to the rotor cylinder portion.

Abstract: A fan for a gas turbine engine is disclosed. The fan includes a fan disk and a plurality of fan blades coupled to the fan disk. The fan disk is adapted for rotation about a central axis. The fan blades are coupled to the fan disk for rotation therewith about the central axis.

Abstract: A rotor of an exhaust-gas turbocharger includes a rotor hub and rotor blades disposed on the rotor hub. The rotor blades have a blade thickness distribution selected in such a way that the rotor blades have along their extent from a fluid inlet or leading edge to a fluid outlet or trailing edge at least one transition between a stiffness or rigidity-oriented blade thickness distribution and an inertia and stress-oriented blade thickness distribution over the height of the blade.

Abstract: A ducted cowl support includes an annular structure configured to be mounted to an annular turbine engine frame and including one or more bypass ducts integrally formed therein.

Abstract: A disc for a fan rotor (with a pilot to connect to a rotating shaft, a hub and a plurality of blades) includes a flat circular portion connecting to the pilot at an inner edge and to the hub at an outer edge; a plurality of first circular cooling holes of a first diameter located around the inner edge of the disc; and a plurality of second circular cooling holes of a second diameter located around the outer edge of the disc, wherein the second diameter is larger than the first diameter.

Abstract: A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.

Abstract: A centrifugal pump (1) includes at least one pump stage (2) and a first housing part (3) having a suction connection (5). A second housing part (6) has a pressure connection (7). At least one intermediate housing part (10) at least in sections delimits a channel (11) leading to a pressure side of the at least one pump stage (2). The pump further includes a third housing part (20). The second housing part (6) and the at least one intermediate housing part (10) are arranged between the first and the third housing part (3, 20). The at least one intermediate housing part (10) and the second housing part (6) are configured to be arranged in at least two different positions with respect to the first and the third housing (3, 20).

Abstract: The present disclosure is directed to thermoplastic airflow modifying elements for a rotor blade for a wind turbine and methods of assembling same. The rotor blade may be constructed from at least one of a thermoset material or a thermoplastic material. Further, the rotor blade includes a blade shell defining an outer surface. Moreover, the rotor blade includes one or more layers of thermoplastic material infused to the outer surface of the blade shell so as to define one or more attachment locations. In addition, the rotor blade includes at least one airflow modifying element constructed, at least in part, from a thermoplastic material. Thus, the airflow modifying element(s) is welded to one of the attachment locations on the outer surface of the blade shell.

Abstract: A suction diffuser or arrangement is provided featuring a main suction diffuser body and a flow conditioning arrangement. The main suction diffuser body is configured with an inlet to receive an incoming fluid flow, an interior cavity to receive the incoming fluid from the inlet, and an outlet to receive the incoming fluid from the interior cavity and provide an outgoing fluid. The flow conditioning arrangement is configured in relation to the inlet and also comprises a flow conditioning portion having at least one inwardly contoured surface, configured to extend into the interior cavity, diffuse the incoming fluid passing from the inlet into the interior cavity, and provide a flow conditioning that produces a uniform flow of the outgoing fluid by directing the incoming fluid towards the outlet, based at least partly on a contoured design corresponding to the at least one inwardly contoured surface.

Abstract: A stator rim structure for a gas turbine engine comprises a stator having an end wall and a discourager defining a channel therebetween. The end wall is adjacent to a hot gas flow and the discourager is adjacent to a purge flow. A rotor has an angel wing extending into the channel. At least one supply passage is disposed within the stator and extends through the discourager and at least one aperture fluidly couples the supply passage with the channel. A flow of cooling air is fed from the supply passage into the aperture and into the channel to form a fluidic dam discouraging ingestion of the hot gas flow.

Abstract: Stator vane assembly includes plurality of vanes arranged in circumferential array, radially proximal mounting portion, radially distal mounting portion, and first latching mechanism. Each of plurality of vanes extends radially between radially proximal mounting portion and radially distal mounting portion, with each of plurality of vanes being pivotally mounted between radially proximal mounting portion and radially distal mounting portion. Plurality of vanes is movable between first arrangement allowing gas to flow across vanes, and second arrangement blocking gas flow across vanes. Pivot axis of each of plurality of vanes is offset from the line of aerodynamic center of pressure of vane towards trailing edge of vane, and first latching mechanism holds plurality of vanes in first arrangement. Upon receipt of signal, first latching mechanism releases plurality of vanes so that gas flow through vane assembly causes plurality of vanes to move from first arrangement to second arrangement.

Abstract: A gas turbine shroud ring segment assembly (36) with an outer structural block (32A) having cooling channels (72) between inlets (60) on a front face and outlets (74, 76) on a front hanger rail (48). The outlets may be positioned on a radially inner surface (77) of the front rail for impingement and forced convection cooling of backsides of radially inner front lips (44) of adjacent shroud ring segments (30A, 30B) mounted on front and rear rails (48, 50) of the block. The outlets may enter a pocket (86) on the inner surface configured to allow coolant flow in all positions of the ring segments (32A, 32B). The cooling channel may form a main channel (72A) and tributary channels (72B, 72C). These channels may be drilled upward from the rail to the inlet. The tributaries may have offset intersections (72E, 72D) with the main channel.

Abstract: A seal for sealing a gap between a vane and a liner of an outlet guide vane is provided. The seal includes: a joint section for joining with the liner; a flexible fillet section elongated from the joint section and tapering toward a tip so as to form a round corner between the vane and the liner when the tip is placed in contact with the vane; and a flexible rib section projecting from an inner surface and so dimensioned as to get in contact with an upper surface of an external structure for securing the vane to keep gas tightness.