Fluid reaction surfaces (i.e., impellers) inventions 03/07

20070071601 - Cooled airfoil trailing edge tip exit: A gas turbine engine airfoil comprises first and second opposite sides joined together at spaced-apart leading and trailing edges and extending from a root to a tip. An internal cooling passage is provided for channelling coolant through the airfoil. The internal cooling passage has a discharge aperture at a juncture... Agent: Ogilvy Renault LLP (pwc)

20070071602 - Rotorcraft rotor with blades hinged in flap and in lag: The invention relates to a rotorcraft rotor comprising a hub and at least two blades hinged relative to the hub about respective pitch axes and about respective flap axes, and about respective lag axes; each blade is secured to a respective pitch lever; the rotor includes a respective pitch control... Agent: Young & Thompson

20070071603 - Fan and blower unit having the same: A fan has a plurality of blades extending in a radial direction with respect to a rotation axis and a ring portion disposed on radial outside edges of the blades. Further, the fan has a first connecting wall and a second connecting wall. The first connecting wall extending from the... Agent: Harness, Dickey & Pierce, P.L.C

20070071604 - Vertical axis windmill: The present invention relates to a vertical axis windmill and a wind power generation system, and especially to a vertical axis windmill in which a support frame is provided as wind power dam to form a plurality of shaft-installation sections, a plurality of vertically long blades each of which has... Agent: Ostrolenk Faber Gerb & Soffen

20070071605 - Integrated nozzle and bucket wheels for reaction steam turbine stationary components and related method: Integrated nozzle and bucket wheels for turbine stator and rotor components, respectively, include a three hundred sixty degree wheel formed from a single piece of stock material. The nozzle wheels include radially inner portions formed to include a plurality of nozzles, while the bucket wheels are each formed to include... Agent: Nixon & Vanderhye P.C.

20070071606 - Turbine blade: A turbine blade is provided, comprising a stator-side end located toward a stationary stator cylinder of the turbine, a rotor-side end located toward an axial rotor of the turbine, a leading edge located between the stator-side end and the rotor-side end, a trailing edge located between the stator-side end and... Agent: Siemens Corporation Intellectual Property Department

20070071608 - Gas turbine engine components and methods of fabricating same: A method for fabricating a component for a gas turbine engine includes providing a blisk forging fabricated from a first material, inertia welding a second material to the blisk forging to create a bi-alloy blisk forging, and machining the bi-alloy blisk forging to pre-determined dimensions.... Agent: John S. Beulick (12729) C/o Armstrong Teasdale LLP

20070071607 - High-temperature-resistant component: The invention a high temperature resistant component made of an alloy, in particular a nickel-based-super alloy in the following composition and expressed in weight percentage: 9-13% Cr, 3-5% W, 0.5-2.5% Mo, 3-5% Ti, 3-7% Ta, 1-5% Re, up to 2000 ppm of a solidification promoter, the remainder being nickel.... Agent: Siemens Corporation Intellectual Property Department

20070065282 - Performance propeller: The invention relates to a propeller and an apparatus to modify a propeller that provide new propeller performance characteristics. In a preferred embodiment, the propeller includes two blade sets wherein the blades in the sets of distinct geometries from the blades in the corresponding set(s). In another preferred embodiment, a... Agent: Alexander D. Raring John H. Thomas, P.C.

20070065283 - Gas turbine rotor blade, gas turbine using the rotor blade, and power plant using the gas turbine: A gas turbine rotor blade capable of effectively reducing creep damage by forming a cooling through hole to cool a target area in which significant creep damage of a shroud cover is predicted based on analysis of stress and temperature acting on the gas turbine rotor blade. A gas turbine... Agent: Mattingly, Stanger, Malur & Brundidge, P.C.

20070065284 - Method and a device for blocking the pitch of a foldable blade of a rotorcraft rotor: The invention relates to a rotor for a rotorcraft having foldable hinged blades, the rotor comprising a hub (10), each blade being connected to the hub via a sleeve, each sleeve being hinged about a pitch axis (15) relative to the hub, the rotor including a respective lag damper (14)... Agent: Young & Thompson

20070065286 - Seal arrangement: A seal arrangement 30 presents a barrier in the form of a combined seal and anti-fret liner 36 across a shroud ring cavity 32 in order to inhibit air leakage in the platform gap between platforms 33. It will be understood that these gaps are provided for thermal expansion and... Agent: Manelli Denison & Selter

20070065285 - Seal-less cmc vane to platform interfaces: A stator vane assembly for a gas turbine includes a ceramic matrix composite airfoil held between radially inner and outer metal platforms wherein an interface between the airfoil and at least one of the radially inner and outer platforms is shaped to create a circuitous leakage path for gas from... Agent: Nixon & Vanderhye P.C.

20070065287 - Turbine engine disk spacers: A gas turbine engine rotor stack may be engineered or reengineered to include one or more longitudinally outwardly concave spacers. The spacers may provide a longitudinal compression force that increases with rotational speed.... Agent: Bachman & Lapointe, P.C. (p&w)

20070065288 - Wind turbine blade and method of manufacturing thereof: Method of manufacturing a blade root of a wind turbine blade and wind turbine blade having an aerodynamically designed blade portion and a blade root adapted for releasable attachment to a hub of a wind turbine, said blade root being of laminated construction and comprising a plurality of fully bonded... Agent: Sughrue Mion, PLLC

20070065289 - Helicopter speed display for displaying maximum airspeed: A helicopter speed display for displaying the maximum speed of a helicopter under current conditions is disclosed. The display includes a first scale indicative of the actual airspeed of a helicopter and a second scale juxtapositioned on the first scale for displaying a maximum airspeed under current conditions of altitude,... Agent: Lowe Hauptman Berner, LLP

20070065290 - Wind turbine rotor assembly and blade having acoustic flap: A wind turbine includes a rotor assembly having at least one blade with a blade body defining a leading edge and a trailing edge and adapted for movement in response to a wind flow over the body to produce electricity. A rigid acoustic flap extends outward from the trailing edge,... Agent: Patrick W. Rasche (22402)

20070065291 - Hybrid blisk: A rotor assembly or “blisk” for a gas turbine engine includes a metallic hub having an annular flowpath surface, and at least one blade extending outwardly from the flowpath surface. The blade includes a metallic body having a first density. The metallic body defines a shank portion and an airfoil... Agent: Adams Evans P.A.

20070065292 - Methods and apparatus for gas turbine engines: A method for assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation, the gas turbine engine including a fan assembly. The method includes coupling a plurality of fan blades to a fan rotor, and applying a polyurethane material to at least a portion... Agent: John S. Beulick (12729) C/o Armstrong Teasdale LLP

20070059171 - Method of forming a cast component: A method of forming a turbine nozzle guide vane 2 for a gas turbine engine, the guide vane 2 comprising an internal cavity 14 and having internal features 16, comprises investment casting metal around a core member 30 that defines the internal cavity 14 and internal features 16 of the... Agent: Oliff & Berridge, PLC

20070059172 - Method and apparatus for reducing turbine blade temperatures: An airfoil for a gas turbine engine includes a first sidewall and a second sidewall coupled together at a leading edge and atrailing edge, such that a cavity is defined therebetween. A plurality of rib walls extends at least partially between the first and second sidewalls, wherein the plurity of... Agent: John S. Beulick Armstrong Teasdale LLP

20070059173 - Turbine airfoil curved squealer tip with tip shelf: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls... Agent: Adams Evans P.A.

20070059174 - Windmill with rotating panes: A windmill comprises means for orienting panes so that each panes shows optimal surface area windside. A plurality of supporting frames to hold the panes around a central axis, drive means for communicating between each panes' rotational axis and the central axis, an orientation means to reorient the panes according... Agent: Inventarium

20070059175 - Rotocraft rotor with hinged blades and lockable retractable flapping abutments: A rotorcraft rotor with hinged blades, includes: a hub; a plurality of blades hinged to flap relative to the hub; bottom abutments of the hub, and bottom abutments of the blades suitable for co-operating with the bottom abutments of the hub; and top abutments of the hub, and top abutments... Agent: Young & Thompson

20070059176 - Fluid moving device with low-drag impellers: A cooling system for cooling a device in a computer system includes a plurality of cooling fans positioned in series. Each cooling fan includes a hub and at least one fan blade connected to the hub. The fan blade rotates relative to the hub about a substantially radially extending axis... Agent: Carey, Rodriguez, Greenberg & Paul, LLP Steven M. Greenberg

20070059177 - Axial compressor blading: An axial compressor has at least one circumferential row of aerofoil members (30a, 30b, 30c) in which at least one of the two end walls (37) between adjacent blades is given a non-axisymmetric profile, defined by circumferentially-extending sinusoids at a number of axial positions (AA, BB, CC). Corresponding points on... Agent: Oliff & Berridge, PLC

20070059178 - Counterflow film cooled wall: A turbine wall includes opposite back and front sides. Film cooling holes are inclined longitudinally through the wall. Adjacent holes are spaced laterally apart and are inclined oppositely for channeling cooling air therethrough in counterflow.... Agent: Francis L. Conte, Esq.

20070059179 - Impeller for a centrifugal compressor: An impeller rotatable in a direction of rotation in a centrifugal compressor including an intake ring. The impeller includes a back plate having a shaft portion and a plurality of blades. Each blade extends from the back plate and includes an inducer portion adapted to draw fluid into the impeller... Agent: Michael Best & Friedrich, LLP

20070059180 - Fabric fan blade and fan body trim: The conventional fan blade is replaced by a frame over which any of a wide range of decorative fabrics or other similar materials is drawn and secured by a clamping method to form a lightweight fan blade of any surface design desired by the user. The decorative fabric replaces the... Agent: Hiscock & Barclay, LLP

20070059181 - Apparatus and method for securing a rotor blade in a rotor of a turbine-type machine: A rotor of a turbine-type machine, in particular a gas turbine rotor, is disclosed. The rotor has a rotor base body, where the rotor base body has a groove extending in the circumferential direction of the rotor base body, and has multiple rotor blades, or rotor blade segments, or an... Agent: Crowell & Moring LLP Intellectual Property Group

20070059182 - Turbine airfoil with curved squealer tip: An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls... Agent: Adams Evans P.A.

20070053777 - Shock absorbing device for watercraft propeller: A shock absorbing device for a watercraft propeller is provided that can include an outer tube unitarily formed with blades of a propeller. An inner tube can be coupled with a propeller shaft. An intermediate tube can be positioned between the outer tube and the inner tube. A first damping... Agent: Knobbe Martens Olson & Bear LLP

20070053778 - Shroud honeycomb cutter: A turbine blade for use in a gas turbine engine is provided. The turbine blade includes an airfoil portion having a tip end, a shroud attached to the tip end, which shroud has an outer surface, and a knife edge attached to an outer surface of the shroud. The knife... Agent: Bachman & Lapointe, P.c. (p&w)

20070053779 - Blade of a turbomachine with block-wise defined profile skeleton line: t

20070048132 - Helicopter blade emergency detachment system: A method and system for a helicopter blade emergency detachment system that has an activator in the cockpit to initiate the system, an ignition train to provide the detonation signal, a transfer system at the base of the main rotor shaft to move the signal from the stationary helicopter to... Agent: William Spencer Boice

20070048136 - Air deflector for a cooling circuit for a gas turbine blade: A gas turbine blade comprising an internal cooling circuit consisting of at least one cavity extending radially between the base and tip of the blade, at least one air inlet aperture at one radial end of the cavity and at least one air outlet orifice opening into the cavity and... Agent: Oblon, Spivak, Mcclelland, Maier & Neustadt, P.C.

20070048134 - Manufacturable and inspectable microcircuit cooling for blades: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a plurality of microcircuits having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The... Agent: Bachman & Lapointe, P.C. (p&w)

20070048133 - Pattern cooled turbine airfoil: A hollow turbine airfoil includes pressure and suction sidewalls extending in span between a root and tip and extending in chord between opposite leading and trailing edges. The pressure sidewall includes a first pattern of first holes distributed in span and chord over a majority thereof, and a second pattern... Agent: Francis L. Conte, Esq.

20070048135 - Turbine vane construction: A method for forming a component for use in a gas turbine engine, such as a turbine vane construction is provided. The method broadly comprises the steps of: forming a first aerodynamic structure having a first platform with a leading edge and a trailing edge, and an edge with an... Agent: Bachman & Lapointe, P.C. (p&w)

20070048137 - Wind turbine and energy distribution system: A new design of vertical axis wind turbine is disclosed based on a dome structure using dome struts as blades that work in concert to produce rotational motion. The stability and low cost of the new design allows the turbine to function in low wind speed regimes as well as... Agent: Paul Hartman

20070048138 - Fan shroud structure reinforcement to reduce or eliminate warping and distortion: A fan shroud structure 10 is constructed and arranged to carry a fan and motor. The fan shroud structure includes a base 12 and an annular rim 24 extending from the base. The rim defines a generally central opening 26 sized to accommodate blades of a fan. Motor mounting structure... Agent: Siemens Corporation Intellectual Property Department

20070048139 - Cylindrical rotor with internal blades: A cylindrical rotor with internal blades, configured by a ring of variable diameter and length according to necessity, as well as the blade quantity, pitch, surface and angle in its interior, being the assembly made of different materials.... Agent: Alan M. Weisberg, Esq. Christopher & Weisberg, P.A.

20070048140 - Methods and apparatus for assembling gas turbine engines: A method for assembling a gas turbine engine compressor having a plurality of stages and a plurality of blades coupled to each respective stage includes depositing a silicone oxime sealant onto at least a portion of a compressor blade, and coupling the compressor blade to a compressor disk such that... Agent: John S. Beulick (12729) C/o Armstrong Teasdale LLP

20070048142 - Assembly and method for the mounting of the foot of a blade of a turbine, blower, compressor, and turbine comprising such an assembly: m

20070048141 - Device for blocking a ring for axially retaining a blade, associated rotor disk and retaining ring, and rotor and aircraft engine comprising them: The position of said at least one cleat (302, 304, 306) on said retaining ring (20) is such that, when said retaining ring (20) is in place in a groove (22) situated in the rotor disk (10), said at least one cleat (302, 304, 306) is in abutment against said... Agent: Oblon, Spivak, Mcclelland, Maier & Neustadt, P.C.

20070048143 - Stator vane profile optimization: An airfoil for a stator vane having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I is provided. The profile is carried only to three decimal places wherein Z is a distance from a platform on which the airfoil... Agent: John S. Beulick (17851)

20070048144 - Refractory component with ceramic matrix composite skeleton: Aspects of the invention relate to a construction system and method for components in high temperature environments, such as the hot gas path components of a turbine engine. Such a component can include a skeleton and a coating. The skeleton can be formed by a plurality of interconnected frame members,... Agent: Siemens Corporation Intellectual Property Department