Patents Issued in March 6, 2014
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Publication number: 20140064930Abstract: A turbine engine case defines a centerline and a gaspath within the engine case. A fan is coupled to a fan shaft. A transmission couples the shaft to the fan shaft to drive the fan and comprises a gear system. A gutter system is positioned to capture lubricating fluid slung from the gear system. The gutter system includes a gutter extending partially circumferentially about the centerline having a first circumferential end edge. An inlet channel has an inlet at the gutter first circumferential end edge and locally radially outboard of the gutter. At least one vane is spaced apart from the gutter first circumferential end edge.Type: ApplicationFiled: September 4, 2012Publication date: March 6, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Fred NguyenLoc, San Quach
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Publication number: 20140064931Abstract: In a water pump, a reinforcement rib is integrally installed on either an outer surface or an inner surface of a flange wall of a pulley and radially extended toward an outer direction from a center side at which one end section of a drive shaft is coupled.Type: ApplicationFiled: August 21, 2013Publication date: March 6, 2014Applicant: HITACHI AUTOMOTIVE SYSTEMS, LTD.Inventor: Yusuke FURUSAWA
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Publication number: 20140064932Abstract: A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A viscous damper is provided between the torque frame and the flex support at the location.Type: ApplicationFiled: September 25, 2013Publication date: March 6, 2014Applicant: United Technologies CorporationInventors: James B. Coffin, John R. Otto
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Publication number: 20140064933Abstract: Embodiments of a diffuser assembly incorporate a diffuser vane with a trailing edge that changes position to improve flow performance of a compressor device. In one embodiment, the trailing edge rotates about the leading edge. This configuration maintains the position of the leading edge on the diffuser vanes relative to the orientation of the working fluid.Type: ApplicationFiled: August 31, 2012Publication date: March 6, 2014Applicant: Dresser, Inc.Inventor: Dale Eugene Husted
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Publication number: 20140064934Abstract: Embodiments of a diffuser vane comprise a vane body with a leading edge and a trialing edge that can rotate about the leading edge to improve performance of a compressor device. This configuration maintains the position of the leading edge on the diffuser vane relative to the orientation of the working fluid. In one embodiment, the diffuser vane incorporates a support element that couples with the vane body. The support element counteracts stimulating frequencies to reduce vibration of the vane body. The diffuser vane can also comprise an armature, which couples with a force coupler to facilitate rotation of the trailing edge when in position in a compressor device.Type: ApplicationFiled: August 31, 2012Publication date: March 6, 2014Applicant: General Electric CompanyInventor: Dale Eugene Husted
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Publication number: 20140064935Abstract: A seal for sealing a gap between adjacent first and second components, includes a first portion for attaching to the first component and a second portion extending at an angle from the first portion, the second portion having a top extending therealong that is flat in an uninstalled position, a thickened portion beneath the top and a hinge wherein the thickened portion is disposed between the hinge and an end of the top.Type: ApplicationFiled: September 6, 2012Publication date: March 6, 2014Inventor: Andrew G. Alarcon
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Publication number: 20140064936Abstract: A seal for sealing a space between a housing and a rotatable shaft disposed within the housing includes an annular, elastomeric seal body disposeable about the shaft. The body has a central axis, an outer portion disposeable within a housing recess, and an inner portion with a lip engageable with the shaft. At least a portion of the seal body is configured to bendingly deflect when fluid pressure exerted on the body exceeds a predetermined value such that at least a section of the body inner portion displaces radially outwardly to permit fluid flow between the shaft and the seal body. A rigid support member is disposed within the body outer portion so as to be located at least partially within the housing recess and is configured to reduce bending deflection of the body inner portion so as to prevent disengagement of the body from the recess.Type: ApplicationFiled: January 27, 2012Publication date: March 6, 2014Applicant: AKTIEBOLAGET SKFInventor: Scott Michael Barth
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Publication number: 20140064937Abstract: A fan assembly is provided. The fan assembly includes a rotor having a hub and a plurality of rotor blades extending radially outward from the hub. Each rotor blade includes a blade tip at a radially distal end of each blade. The rotor blade tips define a rotor diameter. The fan assembly also includes a first cylindrical casing substantially axially aligned with the blade tips, the first casing including a first inner diameter that is greater than the rotor diameter. The fan assembly further includes a brush seal assembly coupled to the blade tip of a least one of the plurality of rotor blades, the brush seal assembly configured to contact the casing segment during a first operational mode of the fan assembly, the brush seal assembly configured to avoid contact with the casing segment during a second operational mode of the fan assembly.Type: ApplicationFiled: September 25, 2012Publication date: March 6, 2014Applicant: GENERAL ELECTRIC COMPANYInventor: GENERAL ELECTRIC COMPANY
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Publication number: 20140064938Abstract: A case apparatus for a gas turbine engine includes an annular case having an interior surface with annular recess formed therein; and an annular bumper disposed in the recess, the bumper comprising a frangible material and having a low-friction contact surface, wherein the bumper is configured to permit elastic radial deflection in response to applied forces below a predetermined threshold.Type: ApplicationFiled: September 6, 2012Publication date: March 6, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Michael Edward Eriksen, Gerald Alexander Pauley, Daniel Thomas Scorse
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Publication number: 20140064939Abstract: A metal sealing material used in a sealing device which can reduce a gap between a stator and a rotor of a turbine. The metal sealing material used in a sealing device for a stator and a rotor of a turbine includes a surface layer and a lower layer composed of a porous metal layer, wherein the porosity of the surface layer is smaller than the porosity of the lower layer; the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75% or less; and the porous metal layer has a thickness of 0.3 to 3.0 mm and may include, as a main component, an MCrAlY alloy where M is either one of Ni and Co or both thereof, and h-BN as a solid lubricant.Type: ApplicationFiled: August 28, 2013Publication date: March 6, 2014Applicant: HITACHI, LTD.Inventors: Yoshitaka KOJIMA, Hideyuki ARIKAWA, Akira MEBATA, Hiroyuki DOI, Hajime TORIYA, Kenjiro NARITA
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Publication number: 20140064940Abstract: A casing of a turbocharger has a main body and a heat dissipating layer disposed on an outer surface of the main body. When heat inside the main body is conducted to the outer surface of the main body, the heat dissipating layer dissipates the heat quickly. Since the heat does not accumulate in the main body, temperature of the main body is low and the casing does not oxidize under high temperature. Therefore, the casing of the turbocharger has low manufacturing cost and is economical.Type: ApplicationFiled: April 26, 2013Publication date: March 6, 2014Applicant: Tan Xin Technology Development Inc.Inventors: Chun-An LAI, Ching-Chung KO
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Publication number: 20140064941Abstract: A fan module (1) includes a support structure (2), a motor (6), and an impeller (12). The support structure (2) includes an outer frame (3), an inner seat (5), and spokes (4) connecting the outer frame (3) to the inner seat (5). The motor (6) includes a stator (7) fixed to the inner seat (5), a rotor (8) rotatably mounted to the stator (7), a heat sink (11) at one end of the stator (7), and a control circuit (9) in thermal contact with the heat sink (11). The impeller (12) includes a hub (13) having a front wall (13a), a side wall (13b) spaced from the front wall (13a), and inner vanes (17) extending from the side wall (13b) and connected to the front wall (13a). Top ends of two adjacent inner vanes (17) are spaced from each other with an intake opening (17c) defined therebetween.Type: ApplicationFiled: September 4, 2013Publication date: March 6, 2014Applicant: Johnson Electric S.A.Inventors: Davide Parodi, Piergiorgio Innocenti
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Publication number: 20140064942Abstract: A cooling arrangement in a platform in a rotor blade or a sidewall in a stator blade in a turbine of a combustion turbine engine is described. The cooling arrangement may include: a cooling chamber configured to pass coolant from an inlet to an outlet; and a rib positioned within the cooling chamber. The rib may partially divide the cooling chamber so to form a switchback. The rib may be canted with respect to the cooling chamber such that the switchback has an ever narrowing channel.Type: ApplicationFiled: August 31, 2012Publication date: March 6, 2014Inventors: Christopher Donald Porter, Gary Michael Itzel
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Publication number: 20140064943Abstract: A casing apparatus for an air pump has a body and a cap. The body has a housing and a combined portion. The housing is composed of a first semi-housing and a second semi-housing. The combined portion is axially formed on and is protruded from a front end of the housing. The cap is rotatably connected with the body and has an inwall a rotating connecter. The rotating connecter protrudes from the inwall and rotatably engages with the combined portion of the body. The cap is mounted on the front end of the housing and combines the first semi-housing with the second semi-housing without any separate securing device such as screws. To form screw holes in the housing is unnecessary. Therefore, the casing apparatus is easy to install and has a low cost.Type: ApplicationFiled: August 30, 2012Publication date: March 6, 2014Inventor: Wei-Chi WANG
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Publication number: 20140064944Abstract: A preload disk spring assembly structure for applying a preload to a bearing includes a first and a second main body correspondingly connected to each other face to face. The first main body is provided with at least one first retainer, at least one first notch, and at least one first protruded portion. Similarly, the second main body is provided with at least one second retainer, at least one second notch, and at least one second protruded portion. When the first and the second main body are aligned with each other such that the first retainer is tightly engaged with the second notch, the first notch is tightly engaged with the second retainer and the first protruded portion correspondingly contacts with the second protruded portion, the first and the second main body are brought to assemble together and form an integral body.Type: ApplicationFiled: September 6, 2012Publication date: March 6, 2014Inventors: Yingliang Li, Qi Ai
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Publication number: 20140064945Abstract: The present application thus provides a stator vane assembly for a turbine engine. The stator vane assembly may include a casing slot and a number of ring segments positioned within the casing slot. Each of the ring segments may include a first end and a second end. The first end and the second end may have a stepped configuration.Type: ApplicationFiled: September 4, 2012Publication date: March 6, 2014Applicant: GENERAL ELECTRIC COMPANYInventor: Michael T. Hudson
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Publication number: 20140064946Abstract: A gas turbine engine compressor spacer (230) includes a body (229) with a hollow cylinder shape. The body (229) includes an outer surface (232) with an axially forward end. The body (229) also includes a forward face (233) extending radially inward from the axially forward end. A forward lip (237) extends axially from the body (229). The forward lip (237) includes a forward lip surface (239) located radially inward from the forward face (233). The forward lip surface (239) is the radially outer circumferential surface of the forward lip (237). The spacer (230) also includes a forward undercut (235). The forward undercut (235) is located between the forward face (233) and the forward lip surface (239).Type: ApplicationFiled: September 6, 2012Publication date: March 6, 2014Applicant: SOLAR TURBINES INCORPORATEDInventors: Engward William Nielsen, Kenneth Blair Hurst, Victor Manuel Siordia, II
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ROTOR MACHINE INTENDED TO FUNCTION AS A PUMP OR AN AGITATOR AND AN IMPELLER FOR SUCH A ROTOR MACHINE
Publication number: 20140064947Abstract: The invention concerns a rotor machine and an impeller, of which the rotor machine is intended to function as a liquid pump or as an agitator in a fluid such as a liquid or a colloid, whereby the rotor machine has a pump casing (1) with an impeller (2) mounted in bearings in a manner that allows rotation around an axis (X), and in which the rotor machine has three principal flow pathways, comprising: —an axial inlet opening (4) with a defined area of opening (Ain) —a radially oriented outlet opening (5) with a defined area of opening (Aut), and —a series of radially extending blades (3) that, distributed around the circumference of the impeller, form between them a number of flow channels (22:1-22:n).Type: ApplicationFiled: May 8, 2012Publication date: March 6, 2014Applicant: Luossavaara-Kiirunavaara ABInventors: Ola Eriksson, Daniel Marjavaara -
Publication number: 20140064948Abstract: Embodiments of a system and method manipulate the position of inlet guide vanes and the drive speed for optimizing performance of a compressor device (e.g., a centrifugal compressor). In one embodiment, the systems and methods can correlate setpoints (e.g., inlet volume flow and discharge pressure) desired for installation and/or implementation of the compressor device with reference data collected as part of in-situ performance testing. This reference data identifies, in one embodiment, a position for the inlet guide vanes and a drive speed for a number of different setpoints at a set of reference conditions (e.g., ambient temperature and ambient pressure).Type: ApplicationFiled: August 31, 2012Publication date: March 6, 2014Applicant: Dresser, Inc.Inventors: Dale Eugene Husted, Timothy Daniel Hilgart
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Publication number: 20140064949Abstract: A turbomachine casing assembly includes a first casing element locatable radially outward of one or more rotating aerofoil elements of a turbomachine and a second casing element located radially distal to the first casing element. A void is provided between a radially proximal face of the first casing element and a radially proximal face of the second casing element, at the first end of the first casing element. The first end of the first casing element is located against a corresponding first end of the second casing element by an energy absorbing element, with the first casing element; including a cantilever. Release of one of the rotating aerofoil elements results in the element, or part thereof, impacting the first casing element which results in the cantilever bending into the void provided between the first and second casing elements.Type: ApplicationFiled: January 15, 2013Publication date: March 6, 2014Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20140064950Abstract: A propulsion unit for an aircraft, comprising one turbine engine and a mounting device for a turbine engine designed to be added laterally on an aircraft structure and comprising a rigid mounting structure. The rigid mounting structure supports at least one arch which is concave towards the longitudinal axis of the propulsion unit and which has a distal end at an angular distance of between 45 and 120 degrees from a vertical plane passing through the axis, on the other side of the structure, and supporting a distal connecting element connecting the turbine engine to the arch.Type: ApplicationFiled: September 3, 2013Publication date: March 6, 2014Inventors: Wolfgang Brochard, Romain Terral
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Publication number: 20140064951Abstract: A vane assembly used for controlling a turning gas flow includes multiple vanes, each of which is bowed toward a pressure side of the vane at the root of the vane.Type: ApplicationFiled: September 5, 2012Publication date: March 6, 2014Inventors: Renee J. Jurek, Thomas J. Praisner, Martin Hoeger
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Publication number: 20140064952Abstract: The present invention relates to an assembly of an axial turbomachine, comprising at least one outlet guide vane of a compressor and a diffuser arranged downstream of the outlet guide vane in the flow direction. It is provided that the outlet guide vane is connected to the compressor and that the diffuser is connected to the combustion chamber, without there being a direct mechanical connection between the diffuser and the outlet guide vane. The invention furthermore relates to a method for manufacturing an assembly of this type.Type: ApplicationFiled: August 29, 2013Publication date: March 6, 2014Applicant: Rolls-Royce Deutschland Ltd & Co KGInventor: Carsten CLEMEN
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Publication number: 20140064953Abstract: A system, in certain embodiments, includes a centrifugal compressor diffuser including a flow path having a first surface and a second surface defining opposite axial sides of the flow path. The centrifugal compressor diffuser also includes multiple vanes extending from the first surface to the second surface of the flow path. A first profile of each vane varies along an axial direction. The centrifugal compressor diffuser further includes multiple vanelets extending from the first surface toward the second surface in the axial direction. A first axial extent of each vanelet is less than a second axial extent of the flow path. In addition, a second profile of each vanelet varies along the axial direction and/or the vanelets form a non-periodic pattern around a circumference of the flow path.Type: ApplicationFiled: August 23, 2013Publication date: March 6, 2014Applicant: Cameron International CorporationInventors: Chester V. Swiatek, Mikhail Grigoriev, James Hitt, Noel Blair
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Publication number: 20140064954Abstract: A turbomachine diaphragm includes a sealing section having a first end portion that extends to a second end portion through an intermediate portion. At least one rail member includes a first end section that extends from the first end portion of the sealing section to a second end section through an intermediate section having an inner surface section and an outer surface section. The second end section includes a machined surface having a repair coupon mounting element. A repair coupon is mounted at the repair coupon mounting element and operatively connected to the at least one rail member. A method of repairing a turbomachine diaphragm is also disclosed herein.Type: ApplicationFiled: August 30, 2012Publication date: March 6, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Anshuman Singh, Paul Lawrence Kalmar, Graham David Sherlock, Americo Zapata
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Publication number: 20140064955Abstract: A guide vane assembly for a gas turbine engine includes: a strut having: a root, a tip, a leading edge, a trailing edge wall, and opposed sidewalls extending between the leading edge and the trailing edge wall; and a pair of spaced-apart prongs extending axially aft from the trailing edge wall, each prong having an outer wall that is flush with a respective one of the sidewalls; and a flap positioned axially aft of the strut, the flap having a root, a tip, a leading edge, a trailing edge, and opposed sides extending between the leading and trailing edge, wherein a portion of the leading edge is disposed between the prongs, and wherein a disk-like flap button is disposed at the tip of the flap adjacent its leading edge, the flap button including a pair of spaced-apart notches formed therein.Type: ApplicationFiled: September 7, 2012Publication date: March 6, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Thurmond Douglas Senter, Mark Joseph Mielke, Alan Glen Turner, Thomas Becker
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Publication number: 20140064956Abstract: A guide vane assembly for a stator vane stage comprises at least two aerofoil members joined together using a vane assembly attachment web. The vane assembly attachment web may be provided at the inner and/or outer radius of the aerofoil members. The vane assembly attachment web allows the guide vane assembly to be attached to an inner and/or outer attachment ring, thereby forming a stator vane stage. Such an arrangement may allow composite fibre reinforced guide vane assemblies to be readily assembled together to form stator vane stages. Stator vane stages that comprise such composite fibre reinforced guide vane assemblies may be lighter than conventional metallic stator vane stages.Type: ApplicationFiled: August 15, 2013Publication date: March 6, 2014Applicant: ROLLS-ROYCE PLCInventor: Andrew James DRANE
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Publication number: 20140064957Abstract: The invention relates to a gas turbine fan casing (10) comprising an annular casing wall (12) centered on a longitudinal axis (X-X) of the casing and at least one fastening belt (100) mounted on the periphery of the casing wall to fasten equipment on the casing, each fastening belt comprising two distinct annular flanges (102, 104) each having an L-shaped straight section, said flanges being fastened to each other and maintained on the wall of the casing by tightening of the inverted cone type.Type: ApplicationFiled: August 28, 2013Publication date: March 6, 2014Applicant: SNECMAInventors: Julien SCHNEIDER, Thierry Godon
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Publication number: 20140064958Abstract: A fan assembly that includes a housing having an inner peripheral wall defining a flow through opening, a stator located within the through opening and comprising an annular array of stationary blades provided along the inner peripheral wall, a rotor comprising a hub having a front wall supporting an outer peripheral wall having a forward balancing ring and an aft balancing ring, and an annular array of non-stationary blades extending from the outer peripheral wall, and strengthening ribs.Type: ApplicationFiled: August 31, 2012Publication date: March 6, 2014Applicant: GE AVIATION SYSTEMS LLCInventors: Sukeyuki Kobayashi, Frank Leslie Sincox, III
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Publication number: 20140064959Abstract: A leading edge of a rotating blade of an impeller is formed in an arc recessed in a direction opposite to a rotating direction of the impeller. An angle where an extended line of the recessed arc of the leading edge meets another extended line of a curve of a side edge is set in an acute angle of 30 to 37 degrees in a front view so that a leading tip of the rotating blade may be projected in the rotating direction. An opening angle of a suction-side slant portion of a venturi casing is set in the range of 12 to 17 degrees and an opening angle of a discharge-side slant portion is set in the range of 30 to 35 degrees.Type: ApplicationFiled: September 5, 2013Publication date: March 6, 2014Applicant: SANYO DENKI CO., LTD.Inventor: Atsushi Yanagisawa
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Publication number: 20140064960Abstract: In accordance with one embodiment of the present application, an actuation system is configured for actuation of an airfoil member with a flap mechanism. The actuation system can include an upper drive tape and a lower drive tape, each partially wrapped around a first bearing and second bearing. An inboard frame can be actuated by at least one linear actuator. Similarly, an outboard frame can be actuated by at least one linear actuator. The inboard frame is coupled to the upper drive tape, while the outboard frame is coupled to the lower drive tape. An actuation of the inboard frame and outboard frame in a reciprocal manner acts move a flap input lever reciprocally upward and downward. A flap mechanism is configured to convert the movement of the flap input lever into rotational movements of the airfoil member.Type: ApplicationFiled: August 28, 2012Publication date: March 6, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Troy C. Schank, Peter H. Kintzinger, Jonathan A. Knoll, Christopher E. Foskey
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Publication number: 20140064961Abstract: A pitch drive system for a wind turbine includes a pitch drive motor, a first position detector, a driver, a second position detector, and a controller. When the blades rotate to a mechanical zero position, a position value detected by the first position detector is a first zero point position value. The driver is operable to store the first zero point position value. When the blades rotate to the mechanical zero position, a position value detected by the second position detector is a second zero point position value. The controller is operable to store the second zero point position value. When a corresponding back up command is received, the first zero point position value stored in the driver is backed up into the controller, and the second zero point position value stored in the controller is backed up into the driver respectively.Type: ApplicationFiled: March 15, 2013Publication date: March 6, 2014Applicant: DELTA ELECTRONICS, INC.Inventors: Yu-Ding HE, Jian WANG, Hong-Yan LIU, Zhi-Guang GAO
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Publication number: 20140064962Abstract: A rotor blade assembly includes a rotor blade and a movable trim tab located along a span of the rotor blade. A linear positioner is located inside the rotor blade and operably connected to the trim tab to move the trim tab thereby reducing rotor blade vibration. A method for reducing vibration of a rotor assembly includes energizing a linear positioner located inside a rotor blade of the rotor assembly and moving an output piston of the linear positioner. A trim tab located at the rotor blade is moved to a selected trim tab angle relative to the rotor blade by the output piston, and the linear positioner is deenergized thereby locking the trim tab at the selected trim tab angle.Type: ApplicationFiled: July 23, 2013Publication date: March 6, 2014Applicant: Claverham LTD.Inventors: Paul R. Brewer, Suat Bekircan
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Publication number: 20140064963Abstract: A wind turbine system includes blades which rotate by receiving wind, a nacelle which supports the blades and rotates with the blades, a main shaft for transmitting torque which is connected to the hub and is rotated by the rotation of the hub, and a generator which generates electricity using rotating energy of the main shaft, wherein the main shaft is connected to the hub inside the hub in the axial direction of the main shaft.Type: ApplicationFiled: August 8, 2013Publication date: March 6, 2014Applicant: Hitachi, Ltd.Inventor: Ikuo TOBINAGA
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Publication number: 20140064964Abstract: Tip rub in gas turbine engines is a well-known phenomenon, and may lead to increased tip clearances, with consequent detrimental effects on the engine's performance and blade flutter margins. Heavy or repeated rubbing may cause blade tip over temperature leading to cracking and fatigue failure. The invention provides a tip for a gas turbine engine rotor blade, which under contact with the casing surface interacts with the casing surface so as to reduce the contact force and thereby reduce the energy transferred to the blade. The tip may be designed to ablate under contact with the casing surface, or to cut or abrade the casing surface, or to crush or compress of deflect under contact with the casing surface. In a preferred embodiment, the tip comprises fibre-reinforced metallic foam material.Type: ApplicationFiled: August 8, 2013Publication date: March 6, 2014Inventors: Ian Colin Deuchar CARE, Giuseppe ZUMPANO, Nicholas Michael MERRIMAN
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Publication number: 20140064965Abstract: In accordance with one embodiment of the present application, an actuation system is configured for actuation of an airfoil member with a flap mechanism. The actuation system can include an upper drive tape and a lower drive tape, each partially wrapped around a first bearing and second bearing. An inboard frame can be actuated by at least one linear actuator. Similarly, an outboard frame can be actuated by at least one linear actuator. The inboard frame is coupled to the upper drive tape, while the outboard frame is coupled to the lower drive tape. An actuation of the inboard frame and outboard frame in a reciprocal manner acts move a flap input lever reciprocally upward and downward. A flap mechanism is configured to convert the movement of the flap input lever into rotational movements of the airfoil member.Type: ApplicationFiled: August 28, 2012Publication date: March 6, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Troy C. Schank, Peter H. Kintzinger, Jonathan A. Knoll, Christopher E. Foskey
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Publication number: 20140064966Abstract: A blade tracking system including a detector having one or more sensors to detect radiation from at least one field of view of the detector, the one or more sensors generating signals based on changes in incident radiation to the one or more sensors as a rotor blade passes the field of view, and a processor to determine a pass time for the rotor blade to pass through the at least one field of view based on the generated signals.Type: ApplicationFiled: August 21, 2012Publication date: March 6, 2014Inventors: William Simpkins, John Wilson, David Dorris
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Publication number: 20140064967Abstract: An aerofoil typically for a blade or vane for a gas turbine engine comprises a pressure wall, a suction wall and a web that extends therebetween. One of the walls comprises an inner leaf and an outer leaf which defines a cavity, the other wall defines a first outlet, the aerofoil defines at least one first passage extending from the cavity through the web and to the outlet. Coolant in the cavity on one side wall of the aerofoil is thereby routed across the web to be used to cool the other wall by convention and formation of a coolant film.Type: ApplicationFiled: November 20, 2012Publication date: March 6, 2014Applicant: ROLLS-ROYCE PLCInventor: ROLLS-ROYCE PLC
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Publication number: 20140064968Abstract: Enriching and balancing the acoustic spectrum radiated by a propeller by introducing a differential pitch angle on certain blades of the propeller. Modifying the acoustic spectrum makes it possible to render the propeller noise more pleasant to the human ear.Type: ApplicationFiled: May 14, 2013Publication date: March 6, 2014Applicant: Airbus Operations (SAS)Inventors: Camil Negulescu, Magdi Omais
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Publication number: 20140064969Abstract: An example blade outer air seal assembly for a gas turbine engine includes a main body portion extending along an axis. The main body portion has a radially inward facing surface and at least one radially outward facing surface. A passage is provided in the main body portion between the at least one radially inward facing surface and the at least one radially outward facing surface. The passage has a first portion and a second portion transverse to the first portion, and at least one rib disposed along the axis radially outward of the second portion.Type: ApplicationFiled: August 29, 2012Publication date: March 6, 2014Inventors: Dmitriy A. Romanov, Brian R. Pelletier, Russell E. Keene
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Publication number: 20140064970Abstract: An impeller of a centrifugal pump is provided. The impeller includes at least two blades (4) for conveying media containing solids. An impeller blade leading angle (?1) is smaller than 0°. The blade angle (?) increases in a first section (9) until a value of 0° is reached. In a second section (10), another increase occurs until a maximum value is reached. In a third section (11), the blade angle (?) decreases again.Type: ApplicationFiled: April 18, 2012Publication date: March 6, 2014Applicant: KSB AktiengesellschaftInventor: Peer Springer
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Publication number: 20140064971Abstract: In one aspect, a stiffener plate for coupling a rotor blade to a hub of a wind turbine is disclosed. The stiffener plate may generally include a mounting flange configured to be coupled to at least one of the rotor blade or the hub. The mounting flange may define an inner perimeter and a center point. In addition, the stiffener plate may include a web extending from the inner perimeter towards the center point. The web may define a cross-sectional width that varies between the inner perimeter and the center point.Type: ApplicationFiled: August 29, 2012Publication date: March 6, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Mohan Muthu Kumar Sivanantham, Suresh S. Tirumalai, Gitesh Verma, Giridhar Ron
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Publication number: 20140064972Abstract: A combination of a motor and a wind wheel. The motor includes a shaft (11) including a plurality of mounting holes (21). The wind wheel (2) is arranged on the motor (1). A plurality of wind blades (22) is arranged on the mounting plate (21). A first through hole (210) is disposed on a middle part of the mounting plate (21). A boss (23) is disposed on the mounting plate (21) outside the first through hole (210). A second through hole (230) is arranged on the boss (23). A plurality of mounting holes (110) is arranged on the shaft (11). The shaft (11) passes through the first through hole (210). A screw (3) passes through the second through hole (230) and is inserted into the mounting hole (110) for fastening the wind wheel (2) on the shaft (11).Type: ApplicationFiled: March 16, 2013Publication date: March 6, 2014Applicant: Zhongshan Broad-Ocean Motor Manufacturing Co., LtdInventor: Zhongshan Broad-Ocean Motor Manufacturing Co., Ltd.
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Publication number: 20140064973Abstract: Disclosed are mechanisms for an impeller (10, 20, 40) and method of reducing noise levels while driving fluids with impellers. Exemplary implementations include a hub (21, 41) and multiple blades (22) separably attached to or inseparably formed on the hub. The hub may be used to effectively reduce noise levels during operations of the impeller by having a first cylindrical feature (261), a first number of first ribs (27, 47, 706), and a second number of second ribs (281, 48, 708), while maintaining substantially similar mechanical properties or operational characteristics. The hub may further optionally include a second substantially cylindrical feature (704) that is separably attached to or is inseparably formed on the hub to further enhance one or more properties or characteristics of the hub while serving to reduce the noise level of the impeller.Type: ApplicationFiled: July 23, 2013Publication date: March 6, 2014Applicant: Johnson Electric S.A.Inventors: Guodong REN, Anbang CHEN, Di WANG, Rui Feng QIN
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Publication number: 20140064974Abstract: A fixture having a foot damp for damping a foot of an aerofoil and a tip damp for clamping a tip of the aerofoil is provided with an array of supports between the foot clamp and the tip clamp. Each support within the array is independently addressable to one of the aerofoil flanks when the aerofoil is secured to the fixture. The support is driven by pneumatics till it contacts the aerofoil when it is locked by an alternative mechanism.Type: ApplicationFiled: August 22, 2013Publication date: March 6, 2014Inventors: Christopher Alan SIMMONS, Mark David HANCOCK, Andrew MANTLE
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Publication number: 20140064975Abstract: The present invention is related to an impeller and a rotary machine including an inner diameter portion, a disk portion, a blade portion, and a cover portion. The disk portion includes a main body portion provided the blade portion, and a fixing portion disposed at an inner side in a radial direction of the rotor than the main body portion and fitted at the outside of an outer peripheral surface of the inner diameter portion. The fixing portion is formed so as to protrude toward the other side in the axial direction from the main body portion.Type: ApplicationFiled: December 25, 2012Publication date: March 6, 2014Applicants: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATION, MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Nobuyori Yagi, Katsuya Yamashita, Akihiro Nakaniwa, Atsushi Higashio
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Publication number: 20140064976Abstract: A rotor for a gas turbine engine includes an annular structure having a blade slot. A hub engagement feature is provided on the annular structure. The hub engagement feature includes first and second surfaces transverse to one another and joined by a fillet that is recessed with respect to the first and second surfaces. A method of manufacturing a rotor includes the steps of machining an annular hub engagement feature into a rotor. The hub engagement feature includes first and second surfaces transverse to one another and is joined by a fillet that is recessed with respect to the first and second surfaces. The method includes the step of peening the fillet, and grinding the first and second surfaces.Type: ApplicationFiled: August 14, 2012Publication date: March 6, 2014Inventors: Kevin L. Corcoran, Jody M. Grosso
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Publication number: 20140064977Abstract: A pinned root fixing arrangement of axial flow steam turbine rotor discs made of a low alloy that is less susceptible to stress corrosion cracking (SCC). Such an arrangement has a first ratio, which is defined as ratio of the axial breadth of the disc fingers and the sum of the axial breath and the axial breadth G of the gap between adjacent disc fingers, in the range of about 0.4 to about 0.6 and further has a second ratio, which is defined as the ratio of the length of the disc fingers and the blade fingers to the diameter, between 4 and 6.Type: ApplicationFiled: July 25, 2013Publication date: March 6, 2014Applicant: ALSTOM Technology LtdInventors: Arnaud Buguin, Michel Floch, Julien Lemaire
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Publication number: 20140064978Abstract: Multi-axis balancing propellers and methods of balancing multi-axis balancing propellers along multiple axes are disclosed herein. In some embodiments, a propeller comprises a first blade extending from a hub in a first direction along a first axis, a second blade extending from the hub in a second direction along the first axis, a first balancing ear extending from the hub in a third direction along a second axis, and a second balancing ear extending from the hub in a fourth direction along the second axis.Type: ApplicationFiled: October 4, 2012Publication date: March 6, 2014Applicant: Horizon Hobby, Inc.Inventor: Mario Enrique Somenzini
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Publication number: 20140064979Abstract: A multicant winglet has a first blade section having a leading and a trailing edge, a first lowermost edge and a first uppermost edge, and a first central plane defined by the edges, and a second blade section having a leading and a trailing edge, a second lowermost edge and a second uppermost edge, and a second central plane defined by the edges. The first central plane is canted from vertical by a first cant angle, and the second central plane is canted from vertical by a second cant angle, the first cant angle unequal to the second cant angle.Type: ApplicationFiled: September 5, 2013Publication date: March 6, 2014Inventors: James David Colling, John Stephenson Neel, York Nelson Zentner
