Abstract: A gas turbine engine strut has a forebody positioned upstream of a point of maximum thickness and an aft body positioned downstream of the point of maximum thickness. The aft body has a discontinuity in a curvature distribution which provides for a “subsonic shock.” The discontinuity in curvature distribution can include in inflection point that marks a transition from a curvature associated with an upstream portion of the aft body to a second curvature associated with a downstream portion of the aft body. In some forms, the aft body can additionally include boundary layer aspiration. The gas turbine engine strut can be symmetrical about a centerline.

Abstract: Shroud assemblies for gas turbine engines are provided. A shroud assembly includes a hanger having a forward hanger arm, a rear hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm. The shroud assembly further includes a shroud having a forward surface, a rear surface, and an inner surface and outer surface extending between the forward surface and the rear surface, the outer surface radially spaced from the inner surface, the shroud connected to the hanger. The shroud assembly further includes a support member positioned axially forward of the forward hanger arm, the support member having a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud.

Abstract: A variable pitch fan for a propulsion device is provided. The variable pitch fan includes a plurality of fan blades coupled to a disk and a rotatable front hub covering the disk. Each fan blade is rotatable about a pitch axis to vary a pitch of the fan blade. The pitch is variable within a pitch range that is at least about 80° to about 130°. Each fan blade extends radially outward from the disk along a span from a root to a tip. A portion of the span adjacent the root defines a root span region, a portion of the span adjacent the tip defines a tip span region. A solidity of the variable pitch fan is at least 1.0 in the root span region.

Abstract: A shroud assembly for a turbine section of a turbine engine includes a shroud plate in thermal communication with a hot combustion gas flow and a baffle overlying the shroud plate to define a region. One or more shaped cooling features are located along the region such that a cooling fluid flow passing through the region encounters the shaped cooling features to increase the turbulence of the cooling fluid flow.

Abstract: A compressor shroud for an aircraft turbine engine, the shroud being arranged between two bladed rotary wheels and radially in line with a deflector, the shroud including a sealing device including one or more sealing elements, including a downstream end sealing element on which, projecting downstream, an air entraining and diverting structure is provided, designed to axially divert the discharge air issuing from the end sealing element.

Abstract: A method includes generating an exhaust gas from combustion gases with a turbine; recirculating the exhaust gas along an exhaust recirculation flow path; reducing moisture within the exhaust gas along the exhaust recirculation path with an exhaust gas processing system; providing the exhaust gas to a first exhaust gas inlet of an exhaust gas compressor for compression; and providing the exhaust gas from the exhaust recirculation path to a second exhaust gas inlet separate from the first exhaust gas inlet for cooling, preheating, sealing, or any combination thereof.

Abstract: A method for operating an engine system in an internal combustion engine comprising during a first operating condition, circulating coolant through a coolant jacket in a turbine housing at least partially enclosing a turbine rotor and during a second operating condition, replacing coolant in the coolant jacket with air from a venting reservoir.

Abstract: A demand-based load balancing function may be provided by one or more drive controllers that takes advantage of the affinity laws to linearize the control of the variable of interest (e.g., flow, pressure, etc.). Each drive controller may be set up by the user simply inputting a few values into the drive controller. Based on the inputs, the drive controllers may interpolate control points using an assumed linear relationship between the variable to be controlled (e.g., pressure) and the current driven to the pump. Feedback data from the system may be used to continually update the drive controllers so as to potentially allow them to better balance power usage to each pump.

Abstract: Disclosed herein is a method comprising heating a strontium-containing compound using radiation in a first reactor; decomposing the strontium-containing compound into an oxide and carbon dioxide as a result of heat generated by the exposure to the radiation; reacting the oxide and the carbon dioxide in a second reactor; where the oxide and carbon dioxide react to produce heat; heating a working fluid using the heat produced in the second reactor; and driving a turbine with the heated working fluid to generate energy. Disclosed herein too is a composition comprising strontium carbonate; and strontium zirconate; where the mass ratio of strontium carbonate to strontium zirconate 2:8 to 8:2.

Abstract: Compositions, devices, systems, and methods directed to concentrating solar power are disclosed. In certain aspects, the disclosure is directed to a heat storage material comprising a transformative alloy composition (internal core component) Al—B—Si—Fe/Al2O3—B2O3—SiO2—Fe3O4 embedded in a SiC outer coating.

Abstract: A supercharging system includes a waste gate valve and an ECU. The ECU is configured to: calculate a first parameter and a second parameter, each of which has a positive correlation with an intake air amount; obtain a first difference by subtracting a first boost pressure from a second boost pressure; obtain a second difference by subtracting the first parameter from the second parameter; obtain a quotient by dividing the first difference by the second difference; and determine that a malfunction occurs in the waste gate valve when the quotient is larger than a threshold value.

Abstract: An apparatus for the actuation of a throttle valve, in particular a throttle valve arranged in an intake system of an internal combustion engine, uses a servomotor, in which apparatus at least one device for thermal decoupling is arranged between the throttle valve and servomotor. A shaft of the servomotor is coupled to a shaft of the throttle valve via a torque-transmitting coupling element with a definedly low heat transfer capability.

Abstract: A platform for a bladed wheel having a small hub-tip ratio, suitable for being fabricated out of composite material from a three-dimensionally woven fiber preform, the platform including a bottom wall, a top wall defining an air flow passage, and two side walls extending transversely between the bottom wall and the top wall, wherein the side walls extend longitudinally beyond the upstream end of the bottom wall. The platform further includes a fastener tab that is folded from the upstream end of the bottom wall.

Abstract: In one embodiment, an exhaust chamber cooling apparatus measures output of a generator driven by a steam turbine, a temperature in an exhaust chamber of the turbine, and a pressure in a condenser that changes steam from the turbine back to water. The apparatus further outputs a first signal when it is detected that a measurement value of the output is larger than a first setting value and a measurement value of the temperature is larger than a second setting value, and a second signal when it is detected that the measurement value of the output is smaller than the first setting value and a measurement value of the pressure or a calculation value obtained from the measurement value of the pressure is larger than a third setting value. The apparatus further controls supply of a cooling fluid into the chamber, based on the first or second signal.

Abstract: A heat dissipating module including a casing, a fan, a plurality of blades and at least one locking element is provided. The casing has a first positioning side and a second positioning side opposite each other, and the casing includes a sliding recess located on the first positioning side. The fan is disposed in the casing. The blades respectively slide into the sliding recess and are positioned on the first positioning side and the second positioning side. The locking element passes through the sliding recess to limit the blades from moving out of the sliding recess.

Abstract: A turbine blade, including: an airfoil and a platform, which has an upper face on which the airfoil is arranged; and at least one lateral face, the lateral face including a slot for insertion of a sealing strip. The transition between the upper face of the platform and the at least one lateral face includes a stepped portion and a beveled portion is provided.

Abstract: Cooling systems for high pressure compressor systems are provided. The cooling systems may comprise tangential on board injectors (“TOBIs”). The TOBIs may comprise one or more fluid channels configured to conduct cooling fluid flow to components of the compressor, including, for example, disk-hub portions of the compressor. In this regard, the TOBI may be configured to exhaust cooling air in a manner such that the exhausted air has a similar linear velocity of the disk-hub portion. The cooling air may also be exhausted in a manner that is substantially parallel to the disk-hub portion.

Abstract: A turbine blade assembly for a gas turbine engine is provided. The turbine rotor blade assembly includes a turbine rotor blade and an attachment pin, and the turbine rotor blade and attachment pin have features for providing a surface interface between the blade and pin. In particular, the attachment pin has a triangular cross-sectional shape, and the blade defines a pin hole for receipt of the attachment pin. An attachment pin for attaching a turbine rotor blade to a turbine rotor disk of a gas turbine engine also is provided. The attachment pin includes a body defining at least one planar surface, and the planar surface provides a surface contact interface between the attachment pin and the turbine rotor blade.

Abstract: A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.

Abstract: An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface. The recess provides a radially outwardly extending flange and a bumper extending radially inward from and proud of the inner diameter surface. A method of working on a gas turbine engine section includes inserting a tool into a cavity beneath a seal assembly, and engaging a flange of a minidisk with the tool to manipulate first and second rotors with respect to one another.