Abstract: A gas turbine engine including an outer case and an exhaust gas passage defined within the outer case for conducting an exhaust gas flow from a turbine section of the gas turbine engine. A cooling channel is associated with an outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct structure is provided and includes an inlet end in fluid communication with the channel outlet and includes an outlet end in fluid communication with an area of reduced pressure relative to the air duct structure inlet end. An exit cavity is located at the air duct structure outlet end, wherein the exit cavity effects a reduced pressure at the outlet end to draw air from the cooling channel into the air duct.

Abstract: A turbine assembly is provided having a hollow aerofoil having a cavity with an impingement tube insertable inside the cavity and used for impingement cooling of an inner surface of the cavity, and a platform arranged at a radial end of the hollow aerofoil, and a cooling chamber used for cooling of the platform which is arranged relative to the hollow aerofoil on an opposed side of the platform. The cooling chamber is limited at a first radial end from the platform and at an opposed radial second end from a cover plate. The impingement tube is formed from a leading piece and a trailing piece. The leading piece extends in span wise direction at least completely through the cooling chamber from the platform to the cover plate and the trailing piece terminates in span wise direction at the platform.

Abstract: A fan assembly for creating an air current includes an air outlet mounted on a stand. The stand includes a base and a body tiltable relative to the base. Each of the base and the body has an outer surface shaped so that adjoining portions of the outer surfaces are substantially flush when the body is in the untilted position.

Abstract: A fuel system incorporating a boost pump unit, a boost pump unit and method of pumping fuel are provided. The fuel system and boost pump unit are preferably self-priming and do not utilize an airframe mounted pump for supplying fuel for an aircraft combustor. The boost pump unit includes a liquid ring pump and an air/fuel separator. The air/fuel separator has an inlet and first and second outlet ports. The inlet is operably fluidly coupled to an outlet of the liquid ring pump. The air/fuel separator has an arcuate flow path. The first outlet port is in fluid communication with a radially outer portion of the arcuate flow path and the second outlet port is in fluid communication with a radially inner portion of the arcuate flow path. A return line connected to the first outlet port is configured to return fuel to the liquid ring pump.

Abstract: A turbine inlet housing has a main housing body extending about a central axis. An inlet duct delivers air into a cavity within the main housing body. Bolt hole bosses are formed on a downstream face of the inlet housing to receive bolts to secure an outlet housing to the inlet housing. A plurality of the bosses have a ramped surface which extends radially outwardly for a greater extent than a second plurality of bosses. The plurality of ramped bosses extend between the downstream face and the duct. The ramped bosses have a forward boss portion, and a ramped surface at an angle of between 50 and 54 degrees extending from an upstream end of the forward boss portion. A curved surface curves from an upstream end of the ramped surface to merge into the duct. A turbine stage and air cycle machine are also disclosed and claimed.

Abstract: Provided is a radial vane with which manufacturing is possible with superior economy, without incurring a cut loss associated with vane separation in a weld part of a thread bundle. With a longitudinal intermediate part of a contiguous bundle of threads being a fold-over part, both end parts of the fold-over part of the thread bundle are opened into radial shapes and superpositioned, leaving a space in the center part of the fold-over part, a ring-shaped fold-over part (12) is formed within the circumference of the space in the center part thereof. The outer part of the ring-shaped fold-over part (12) is welded in a ring shape, forming a ring-shaped core part (13). A through hole (11) is formed in the inner side of the fold-over part (12), and radial vane parts (14) are formed in which a plurality of thread materials (21) extend outward from the core part (13) toward the outer circumference side from all regions of the circumference direction.

Abstract: An insert for a component of a gas turbine is provided. The insert includes an insert portion and a retaining element such that the insert portion is retained by the retaining element so that movement of the insert portion relative to the retaining element is prevented. Additionally, a gas turbine component including the insert is provided as well as a method for inserting the insert into a gas turbine component.

Abstract: Disclosed are a system, a method and an apparatus of diffuser nozzle augmented wind turbine. In one embodiment, a method includes attaching a nozzle with a streamlined opening to a diffuser to direct an air flow into a wind turbine. In addition, the method includes increasing a wind speed approaching a set of turbine blades within a shrouded wind turbine configuration. The method also includes recirculating the air within the shroud configuration to increase an output power generated through the wind turbine. The system is composed of diffuser and nozzle integrated and non-integrated with and without a flange. In one embodiment, a method includes increasing a pressure differential of a wind turbine.

Abstract: A turbomachine fitted with a device for gathering the information recorded during operation of the former by a strain gauge positioned on a fan blade borne by a fan disc of the turbomachine, the device including a hollow cylindrical pipe positioned inside one of the rotating shafts of the turbomachine in order to guide at least one wire for transmitting this information, wherein the device further includes a part for attaching the pipe to the rotating shaft.

Abstract: Various methods and systems are provided for a system for a rotary machine, such as a compressor or turbocharger. In one example, the rotary machine includes a volute assembly and a bearing housing. The volute assembly has a first connector that is configured to interlock with a second connector of the bearing housing. The first and second connectors are configured to engage to a greater extent through relative rotation between the volute assembly and the bearing housing.

Abstract: A gas turbine engine includes a bleed structure which includes a forward wall and a rear structural wall to define a deposit space downstream of the bleed structure for a hail event of a predetermined duration.

Abstract: A system includes a linear-displacement fluidic actuator coaxial with the propeller, and a transmission device connecting the actuator to the blades that are to be controlled. The transmission device includes at least two radial arms arranged symmetrically with respect to the actuator and connected, on the inside, to a translationally mobile part of the actuator and, on the outside, to a translationally movable rotary transmission ring which is connected to the pivot pins of the blades by intermediate connecting mechanisms that convert the translational movement of the rotary ring brought about by the actuator into a rotation of the blades of the propeller.

Abstract: A propeller device for a marine vehicle with a main shaft; a front propeller is provided on the main shaft, the front propeller having a hub and a plurality of blades extending radially outwardly from the hub; a rear propeller being co-axially to and spaced from the front propeller, the rear propeller having a hub and a plurality of blades extending radially outwardly from the hub. A second shaft being communicated with the hub of the front propeller; and at least one support for supporting the rear propeller on the second shaft, the support prevents the second shaft to rotate in the direction of rotation of the main shaft, and being free to rotate thereof in the counter direction of rotation of the main shaft.

Abstract: A turbine assembly having a hollow aerofoil and impingement device, the aerofoil having a first side wall from leading to trailing edge and a cavity arranged a distance to an inner surface of the cavity for impingement cooling and a flow channel for cooling medium from the leading to trailing edge, the impingement device has first and second pieces arranged side by side, the second piece downstream of the first forming a first flow passage providing passage from one side of the aerofoil towards an opposite side. A blocking element is arranged in the flow channel between the second piece and first side wall at a suction side for blocking flow of cooling medium from leading to trailing edge denying access to a section of the flow channel downstream of the blocking element while directing cooling medium in the first flow passage away from the suction side towards pressure side.

Abstract: A banded turbine configuration has an integral outer band support structure capable of providing two point simple support for a multiplicity of blades. A large scale vertical array has a set of twelve 23 m-diameter banded turbines with up to nine blades and resting on an Open Web Steel Joist (OWSJ) platform. The banded turbine configuration is supported off of a main shaft hub assembly, which is supported by forward and aft pillow block bearing assemblies. The banded turbine allows for a protective screen for bird- and bat-kill prevention. Each banded turbine employs DC alternators to provide a switchable output which is subsequently fed to a dedicated set of high efficiency grid-compatible solid state invertors or, alternatively, to energy storage.

Abstract: The invention generally relates to a blade for a wind turbine, and to a blade for a wind turbine comprising a lightning measurement system. In particular, a lightning measurement system is provided, comprising a lightning current sensor located in the blade for more accurate lightning measurements. A method of measuring a lightning strike is also provided.

Abstract: A product usable with a turbocharger may include a compressor wheel having an inducer section and an exducer section. Air may be collected by the inducer section and expelled by the exducer section. A cover may define a diffuser and a collection volute. The diffuser may lead away from the exducer section to the collection volute. The cover may define a collection cavity opening to the collection volute through a port and extending in an axial direction. The cover may define an inlet passage around the inducer section and the cover may include a dividing wall separating the inlet passage from the collection cavity.

Abstract: A vibration sensor (5) mountable to a wind turbine generator for detecting excessive vibration of the wind turbine generator, the sensor comprising a pendulum having a pendulum bob (25) of pre-determined mass coupled to a detection switch (10), the detection switch arranged to detect oscillation of the pendulum exceeding a predetermined oscillation threshold; said pendulum bob selectively adjustable along said pendulum so as to vary the oscillation threshold of said sensor; wherein the sensor is arranged to exceed the oscillation threshold on receiving a forced vibration corresponding to a vibration threshold of the wind turbine generator.

Abstract: A turbine is provided comprising a plurality of stages, each stage comprising a rotatable disk and blades carried thereby, at least one pair of adjacent rotatable disks defining an annular gap therebetween and having respective opposing sealing band receiving slots aligned with the annular gap A sealing band is located in the opposing receiving slots to seal the annular gap Disk engagement structure is defined in the pair of adjacent rotatable disks. A clip member is coupled to the sealing band and engaged with the pair of adjacent rotatable disks through the disk engagement structure The clip member may have an aperture extending only partially through the clip member for alignment with a hole in the sealing band for engagement with a tool To improve weld geometry, the clip member may have angled surfaces and notched areas, and the sealing band may have chamfered edges.

Abstract: A multi or single-stage turbocompressor with at least one compressor wheel fastened to a shaft. The shaft is mounted in a turbocompressor housing which, behind the hub disc of the compressor wheel, includes an interior housing region as well as in front of the hub disc of the compressor wheel a front interior housing region. The driven compressor wheel delivers a fluid from an inlet channel to an outlet channel. The front interior housing region includes a wheel lateral space from which an extraction channel for the extraction of fluid is provided.