Abstract: A gas turbine engine includes a compressor section and a nosecone assembly. The compressor section includes an inlet guide vane assembly including an inner shroud, an outer shroud, and an inlet guide vane extending from the inner shroud to the outer shroud. The nosecone assembly is attached to the inner shroud.

Abstract: One aspect of the present invention provides a propeller for an aircraft. The propeller comprises a propeller hub, a spinner for streamlining the propeller and a plurality of composite propeller blades mounted to the propeller hub. The propeller blades are arranged to rotate together in the same rotational direction in at least two parallel planes substantially perpendicular to an axis of rotation of the propeller. The propeller has a reduced sized spinner with an improved aerodynamic profile that can be better matched to an engine nacelle and also has reduced drag.

Abstract: In a turbine vane and a gas turbine, an outer shroud is fixed to one end of a vane body formed in a hollow shape, an inner shroud is fixed to the other end thereof, and a partition plate is fixed to the inner portions of the vane body, the outer shroud, and the inner shroud, so that a cavity is formed so as to be continuous between the partition plate and the group of the vane body, the outer shroud, and the inner shroud. Then, the vane body, the outer shroud, and the inner shroud are provided with a plurality of cooling holes, and the partition plate is provided with a plurality of penetration holes. Accordingly, since the vane structure or the end wall structure is evenly cooled, a deformation or damage may be suppressed.

Abstract: A wind turbine control method is described comprising the detection of the presence of an anomaly in the aerodynamic profile of the blades and operation of the wind turbine in accordance not only with the determination of said anomaly, but also taking into account the characteristics thereof.

Abstract: A pump assembly having improved cooling for use in a selective catalytic reduction system is disclosed. The pump assembly comprises a pump housing having a body portion and a nozzle portion extending from the body portion, a jacket including a cavity for receiving the pump housing, first and second ports for cooling fluid, and a flow guide disposed between the jacket and the pump housing. The cavity includes a first compartment for cooling fluid defined in part by the flow guide and in part by the pump housing and being in fluid communication with the first port; and a second compartment for cooling fluid defined in part by the flow guide and in part by the jacket. The first compartment is in fluid communication with the second port by way of the second compartment.

Abstract: A device for attaching blades to a rotor disk of a turbine engine is provided. The device includes: a rotor disk provided at its outer periphery with a plurality of slots, each slot being formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk.

Abstract: The invention relates to a patient ventilation or breathing device and components therefore for use in all forms of respiratory apparatus ventilation systems including invasive and non-invasive ventilation, positive airway pressure therapy, Continuous Positive Airway Pressure (CPAP), and particularly Bi-Level therapy and treatment for sleep disordered breathing (SDB) conditions such as Obstructive Sleep Apnea (OSA), and for various other respiratory disorders and diseases. The invention particularly relates to a blower, to a blade, to a gasket, to a cable, to an impeller, to a gas inlet and inlet member, to an improved air path or fluid flow path and components thereof, and/or to a modular ventilation or breathing device as referred to above and particularly incorporating one or more of the other aspects of the invention.

Abstract: A dual-flow turbine engine including: a fan rotatably mounted on a fan shaft and a stationary structural element, the fan shaft and the structural element being connected to one another at an upstream bearing and at a downstream bearing via an upstream bearing bracket and a downstream bearing bracket, respectively; and a decoupling device surrounding the fan shaft, and including a set of attachment screws joining the downstream bearing bracket to the structural element and a set of fusible screws joining the upstream bearing bracket to the downstream bearing bracket. At least some of the fusible screws are arranged between at least some of the attachment screws over a single circumference surrounding the fan shaft.

Abstract: An oil supply system for a propeller turbine engine includes a first oil circuit for supplying the turbomachine and a second oil circuit for supplying the propeller gearbox and the high-pressure pump associated with a propeller adjusting device. The two oil circuits are integrated into a common oil tank and connected to one another by means of an oil supply line in the flow direction downstream of the first and the second oil conveying pumps in such a way that a limited oil volumetric flow can flow from the first oil circuit into the second oil circuit, and only in this direction, if the pressure difference between the first and the second oil circuits falls below a certain level in the event of a pressure reduction in the second oil circuit.

Abstract: Apparatus, systems and methods of 70 (seventy) CFM (cubic feet per minute) ventilation fans for bathrooms with recessed can with light and having the motor partially inside and beneath the blower wheel. A housing for the bath fan can be attached to joists in the ceiling by a long telescoping mounting brackets. The motor and blower wheel can be attached to a mounting plate inside of the housing, which can be removed as a single unit to allow the motor to be easily replaced or repaired, and also to allow for the inside of the housing to be inspected during and after installation of the exhaust fan. A ring about the light can have vents that receive incoming air into the fan, which is exhausted therefrom by the blower. Seals such as elastomeric rings can seal the bottom of the can to the light, and the top end of the can to the decorative ring shaped pan. A vertical panel can separate a first compartment having the motor and blower from a second adjacent compartment having the light.

Abstract: A steam turbine arrangement is provided and includes a first steam turbine with a first steam outlet, wherein the first steam turbine exhibiting a first sealing leakage, a second steam turbine exhibiting a second sealing leakage, and a third steam turbine with a cooling steam inlet, a functional device and a cooling arrangement. The cooling arrangement is coupled to the cooling steam inlet. The cooling arrangement is adapted for guiding a cooling steam to the functional device for cooling purposes. A steam pipe is coupled to the first steam turbine and to the second steam turbine such that a first steam being provided by the first sealing leakage and a second steam being provided by the second sealing leakage is gathered to a cooling steam in the steam pipe. The steam pipe is coupled to the cooling steam inlet such that the cooling steam is injectable to the cooling arrangement.

Abstract: The present invention describes a floating yawing spar buoy current/tidal turbine. The spar includes a spreader above the rotor(s) with the spreader tips connected to fore and aft cable yokes that transition to opposing mooring lines connected to anchors on the seabed. The spreader comprises a yaw motor, which drives gears that engage with a ring gear fixed to the outer perimeter of the spar. Flow direction sensors activate the yaw motor for automatic yaw adjustments of the spar turbine. As tidal direction changes, the entire spar and turbine are yawed to maintain the rotor plane facing the tidal flow. The bottom end of the spar extends to approximately the bottom sweep of the rotor plane and contains a winched vertical mooring line, extending to the seabed and attached to a gravity or suction pile anchor. The turbine drive train can be accessed for servicing from the surface via hatches and ladders within the spar to enter the drive train and generating system vessel.

Abstract: A method of making a wind turbine component of composite construction with enhanced radar absorbing properties is described. The method comprises making the component and then modifying the component by applying circuit analog elements to a surface of the component.

Abstract: Segmented wind turbine blades with truss connection regions, and associated systems and methods are disclosed. A wind turbine system in accordance with a particular embodiment includes a wind turbine with a first segment having a first position along the longitudinal axis and having a first internal load-bearing structure for which non-truss structure elements carry at least 90% of the shear loads in the first segment. The blade further includes a second segment having a second position along the longitudinal axis and having a second internal load-bearing structure for which non-truss structure elements carry at least 90% of the shear loads in the first segment. A connection region between the first and second segments includes an internal load-bearing truss structure connected between the first internal load-bearing structure and the second internal load-bearing structure.

Abstract: The invention relates to a turbine wheel (1) composed of a turbine wheel blank (2), having a turbine wheel back (3) and having a weld peg (Z) which is arranged on the turbine wheel back (3) via a transition region (5) provided with an undercut (4), wherein the undercut (4) is already provided in the turbine wheel blank (2).

Abstract: A floating brush seal in a rim cavity of a turbine in a gas turbine engine, where the floating brush seal includes a seal holder in which the floating brush seal floats, and a expandable seal that fits within two radial extending seal slots that maintains a seal with radial displacement of the floating brush seal and the seal holder.

Abstract: A turbine assembly and turbocharger containing the same are disclosed. Such an assembly can include a turbine housing for a turbocharger having an inlet portion, a central portion, and a hollow cylindrical portion defining a hollow passageway and an outlet. The inlet portion, central portion, and hollow cylindrical portion are in fluid connection with one another which allows a fluid to enter and pass through the inlet portion to the central portion, pass through the central portion to the hollow passageway, and pass through the hollow passageway to exit the turbine housing through the outlet. The assembly also includes a containment assembly at least partially disposed in the hollow passageway of the hollow cylindrical portion.

Abstract: A wind turbine blade with a blade attachment is provided. A tip end of the wind turbine blade is connected with the blade attachment by a glue-interface. The glue-interface is arranged between the tip end of the blade and the blade attachment. The glue-interface is arranged in a circumferential manner in view to the tip end of the blade and in view to the blade attachment. The blade attachment includes a core with a surface, while the core is surrounded by this surface. The blade attachment, which comprises the core and the surface, is completely made of one foam, showing at least two different densities. That part of the surface of the core, which is arranged adjacent to the glue-interface, is made of foam with a first density, while the chosen first density prevents the infusion of water from the glue-interface into the core.

Abstract: Rotor blade assemblies and methods for constructing rotor blade assemblies are provided. A rotor blade assembly may include a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge and a trailing edge each extending between a tip and a root, the rotor blade defining a span and a chord. The rotor blade assembly further includes an extension plate mounted to one of the pressure side or the suction side, the extension plate extending in the chord-wise direction between a first end and a second end, the second end extending beyond the trailing edge. The rotor blade assembly further includes a filler substrate provided on an inner surface of the extension plate and the trailing edge, the filler substrate tapering from the trailing edge towards the second end.

Abstract: The invention refers to a stationary gas turbine arrangement with at least one turbine stage that includes at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. Further a method for performing maintenance work on a stationary gas turbine is described. The invention is characterized in that the stationary component provides for each vane a radially orientated through-hole designed and arranged for a radial insertion and removal of the vane, and each of said vanes comprises an airfoil having at its one end directed radially outwards a contour being adapted to close the through-hole airtight by a detachable fixation means.