Bearing, Seal, Or Liner Between Runner Portion And Static Part Patents (Class 415/170.1)
  • Publication number: 20130280047
    Abstract: A stator seal for a turbine assembly includes a seal base securable to a turbine stator and including an annular inner surface, and an abradable coating disposed on the annular inner surface. The abradable coating and the annular inner surface have a predefined cross-sectional profile including a transient operation section that facilitates axial expansion and a steady state operation section that facilitates a tighter clearance.
    Type: Application
    Filed: April 18, 2012
    Publication date: October 24, 2013
    Inventors: Fred Thomas Willett, JR., Michael Earl Montgomery, Peter John Eisenzopf, Richard James Miller
  • Publication number: 20130272853
    Abstract: A compressor is provided with a substantially tubular compressor casing, a substantially circular lid that is provided inside an inner periphery of the compressor casing so as to close off an end surface of the compressor casing, a space that is enclosed by the lid and an inner circumferential surface of the compressor casing so as to accommodate a blade, and seal member that is provided in a circumferential direction on the space side of an outer circumferential surface of the lid, wherein a slit part is provided on the lid, radially inside the outer circumferential surface, where the seal member is provided, so as to extend in the axial direction from the space side of the lid.
    Type: Application
    Filed: July 21, 2011
    Publication date: October 17, 2013
    Inventors: Hitoshi Shinohara, Mitsuhiko Ota
  • Publication number: 20130272854
    Abstract: A bearing arrangement for a turbocharger, including a bearing housing-which extends in an axial direction, an anti-friction bearing, situated within the bearing housing, having an outer bearing ring and a number of rolling bodies and an axially extending shaft which is rotatably mounted within the bearing housing. It is provided that the shaft includes a rolling body raceway for guiding the rolling bodies. Moreover, the invention relates to a turbocharger having such a bearing arrangement. A bearing arrangement of this type allows the secure mounting of a shaft in a turbocharger with simple assembly and low costs.
    Type: Application
    Filed: November 14, 2011
    Publication date: October 17, 2013
    Applicant: Schaeffler Technologies AG & Co. KG
    Inventors: Heiko Schmidt, Peter Solfrank, Christopher Mitchell, Andre Kuckuk, Thomas Motz
  • Publication number: 20130266425
    Abstract: An exhaust gas turbocharger (1) with a compressor (2) which has a compressor wheel (3) arranged in a compressor housing (4); with a turbine (5) which has a turbine wheel (6) arranged in a turbine housing (7); and with a bearing housing (8) which is arranged between the compressor housing (4) and turbine housing (7); and which has a bearing (9) for a rotor shaft (10) which bears the turbine wheel (6) and the compressor wheel (3), wherein the bearing (9) has at least one ceramic insert (11, 12) which is on the bearing housing side and is under compressive prestress, and at least one ceramic insert (11, 12) which is on the motor shaft side and is under tensile prestress.
    Type: Application
    Filed: November 23, 2011
    Publication date: October 10, 2013
    Applicant: BorgWarner Inc.
    Inventor: Jaroslaw Kierat
  • Patent number: 8552613
    Abstract: A stator arrangement of an electric machine, particularly a generator in a wind turbine is provided. The stator arrangement is radially surrounded by a rotatably mounted rotor arrangement. During normal operation the stator arrangement is non-rotatably connected to a stationary part of the generator. The stator arrangement may be released from the non-rotatable connection to the stationary part of the generator so as to be revolved relative to the stationary part of the generator. A method for positioning such a stator arrangement is also provided.
    Type: Grant
    Filed: September 24, 2009
    Date of Patent: October 8, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventor: Henrik Stiesdal
  • Publication number: 20130259661
    Abstract: Bolt holes 16 are formed in a joint part 14 of a turbine housing 12, with flanged bolts 40 screwed in the bolt holes 16. A flange part 32 of a bearing housing 30 is sandwiched between bearing surfaces 44a of the flanged bolts 40 and an inner end face 14b of the joint part 14. A sealing ring 48 is interposed in an annular space s. Before the flanged bolts 40 are fastened, there is formed a height difference G equivalent to a compression allowance h for the sealing ring 48, between an outer end face 60a of the joint part 14 and a bolt receiving surface 32a of the flange part 32. The flanged bolts 40 are screwed into the bolt holes 16 until the bearing surfaces 44a make tight contact with the outer end face 60a so as to resiliently deform the sealing ring 48.
    Type: Application
    Filed: December 8, 2011
    Publication date: October 3, 2013
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Shingo Shudo, Daigo Watanabe, Takumi Tokiyoshi, Motoki Ebisu
  • Publication number: 20130259700
    Abstract: A turbine bucket includes an airfoil portion; a platform at radially inner end of the airfoil portion; a shank portion extending radially-inwardly of the platform; and a mounting portion extending radially-inwardly of the shank portion. The shank portion and the mounting portion have at least one axially-extending seal-engaging surface formed as part of a separable, non-integral isolation element that isolates the bucket from forces caused by a near-flow-path seal engaging the at least one axially-extending seal-engaging surface.
    Type: Application
    Filed: March 29, 2012
    Publication date: October 3, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Matthew Robert PIERSALL, Brian Denver POTTER
  • Publication number: 20130259659
    Abstract: A seal for a gas turbine engine and a gas turbine engine employing such a seal are disclosed. More specifically, the engine includes a knife edge seal which is better able to withstand the extremely high temperatures and mechanical loads to which gas turbine engine components are increasingly subjected. By moving the knife edge seal to the aft hub and cantilevering its angle off of vertical, thermal and mechanical loads are balanced and thus thermal mechanical fatigue life is improved while low cycle fatigue is maintained.
    Type: Application
    Filed: March 27, 2012
    Publication date: October 3, 2013
    Applicant: Pratt & Whitney
    Inventors: David A. Knaul, Fadi S. Maalouf, Nicholas Aiello, Orenthral T. Morgan, Raji Mali
  • Publication number: 20130259660
    Abstract: A gas turbine engine has a turbine section and an air moving section upstream of the turbine section. A seal is between a static surface and a rotating surface in at least one of the turbine section and air moving section. The seal includes a seal shoe which is biased at least in part by a spring force, with the spring force created by cuts formed to provide a gap to allow arms associated with the seal to provide the spring force. The movement of the shoe is along a direction having at least a component parallel to an axis of rotation of the gas turbine engine. In addition, an axially moving non-contact seal is claimed.
    Type: Application
    Filed: April 2, 2012
    Publication date: October 3, 2013
    Inventor: Timothy Dale
  • Publication number: 20130243581
    Abstract: A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings. The bearing housing forms a shroud for the internal side of the compressor wheel.
    Type: Application
    Filed: April 24, 2013
    Publication date: September 19, 2013
    Applicant: HONEYWELL INTERNATIONAL INC
    Inventor: Jeffrey Allen Lotterman
  • Patent number: 8534076
    Abstract: A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.
    Type: Grant
    Filed: June 9, 2009
    Date of Patent: September 17, 2013
    Assignee: Honeywell Internationl Inc.
    Inventors: Gregory O. Woodcock, Bradley Reed Tucker, Jason Smoke, Stony Kujala, Terrel Kuhn
  • Patent number: 8535009
    Abstract: A two-row tapered roller bearing includes an outer ring (1) having an outer diameter of at least one meter, a first inner ring (2) and a second inner ring (3) that is disposed axially adjacent the first inner ring (2). A first set of conically-formed roller bodies (4) roll between the outer ring (1) and the first inner ring (2) and a second set of conically-formed roller bodies (5) are disposed axially adjacent the first roller bodies (4) and roll between the outer ring (1) and the second inner ring (3). A first sealing ring (11) is disposed axially adjacent the outer ring (1), is connected with the outer ring (1) and slips on a slip surface (16) of the first inner ring (2) in a contacting manner.
    Type: Grant
    Filed: March 25, 2010
    Date of Patent: September 17, 2013
    Assignee: Aktiebolaget SKF
    Inventor: Matthias Hofmann
  • Publication number: 20130236289
    Abstract: A system includes a multi-stage turbine. The multi-stage turbine has an interstage seal extending axially between a first turbine stage and a second turbine stage. The interstage seal has an upper body that extends from an upstream seating arm to a downstream seating arm. The upstream and downstream seating arms are designed to constrain movement of the interstage seal along a radial direction of the multi-stage turbine. The interstage seal also has a lower body that extends from a seating end to a hook end. The seating end is designed to constrain movement of the interstage seal along the radial direction. The hook end has a protrusion that extends crosswise relative to a base of the lower body. The hook end is designed to constrain movement of the interstage seal along the radial direction and an axial direction of the multi-stage turbine.
    Type: Application
    Filed: March 12, 2012
    Publication date: September 12, 2013
    Applicant: General Electric Company
    Inventors: Gary Charles Liotta, Brian Denver Potter
  • Publication number: 20130236297
    Abstract: Pump, in particular a canned motor pump, to deliver liquids in water carrying domestic appliances and such like, which comprises a stator, a rotor and a drive shaft non-rotatably coupled to an impeller disposed in a pump compartment which is rotatably arranged inside a motor casing via bearing means wherein seal means are fitted on a first face end of the motor casing to seal said casing off against the pump compartment, wherein the bearing and seal means arranged on the first face end of the motor casing are in the form of a seal-bearing combination which comprises an axial bushing section for sliding arrangement on the drive shaft, a radial closing section to cover up the motor casing and at least one flexible seal element formed to said axial bushing section and/or said radial closing section.
    Type: Application
    Filed: March 6, 2013
    Publication date: September 12, 2013
    Applicant: HANNING ELEKTRO-WERKE GMBH & CO. KG
    Inventor: Norbert Krogmeier
  • Publication number: 20130230388
    Abstract: A compressor having a stator vane assembly having an inner ring and a seal carrier secured thereto, the seal carrier having two opposite seal carrier end faces and the inner ring having two inner ring end faces which face said seal carrier end faces and are received between said seal carrier end faces with an axial gap therebetween, at least one clamping element bearing axially with a first clamping element end face against the inner ring and with a second clamping element end face against the seal carrier and being axially resiliently clamped between the inner ring and the seal carrier. A compressor with a clamping element for radial clamping is also provided.
    Type: Application
    Filed: March 4, 2013
    Publication date: September 5, 2013
    Applicant: MTU Aero Engines GmbH
    Inventors: Juergen Kraus, Felix Kern
  • Publication number: 20130230386
    Abstract: A diffuser seal for an aft end of a high pressure compressor of a gas turbine engine is disclosed. The diffuser seal includes a flow guide carrier coupled to the diffuser case. The flow guide carrier is also coupled to a static seal. The static seal engages a rotary seal and permits air flow through the static and rotary seals in the aft direction. The flow guide carrier is also coupled to a fairing and a fairing/hub support. The flow guide carrier supports the fairing in a spaced-apart position with respect to the rear hub so that air flowing through the static and rotary seals passes between a forward surface of the fairing and the rear hub. The fairing/hub support extends forward from the flow guide support and engages an aft surface of the fairing thereby limiting movement of the rear hub and fairing in the aft direction. This design helps to prevent parts or debris from piercing the rear hub and entering the high pressure turbine in the even of a fan blade-out or fan blade-off event.
    Type: Application
    Filed: March 1, 2012
    Publication date: September 5, 2013
    Applicant: Pratt & Whitney
    Inventors: Paul W. Baumann, Charles H. Warner, Brian Ellis Clouse
  • Publication number: 20130230387
    Abstract: The propeller blade seal positioning gauge provides for precisely marking the position(s) of the circumferential seal(s) about the blade shank of a controllable pitch propeller prior to propeller reassembly. The gauge includes an elongate arm having a stop extending from one end normal thereto. The distal portion of the arm is inwardly offset toward the spanwise axis of the blade to place the distal portion of the arm adjacent the blade shank. One or more marker notches are formed in either or both edges of the arm, their locations being precisely determined according to the specific propeller type. The stop is placed upon the butt of the blade and the tip of an appropriate marker is placed in the appropriate notch of the gauge. The device is then rotated about the blade shank to mark a circumferential ring about the shank to indicate the precise position of the seal.
    Type: Application
    Filed: January 21, 2013
    Publication date: September 5, 2013
    Inventor: MARICELA CARLOTA SILVA
  • Publication number: 20130223997
    Abstract: A bearing assembly that includes a first bearing, a second bearing, a spring and a sleeve. The spring applies a preload to each of the bearings, and the sleeve surrounds the spring and the bearings. The sleeve includes an end portion that extends axially beyond the first bearing. The end portion includes a step down in the outer diameter that defines a seat for an o-ring.
    Type: Application
    Filed: August 20, 2012
    Publication date: August 29, 2013
    Applicant: Dyson Technology Limited
    Inventors: Matthew John Childe, Geoffrey Michael Burlington, David Michael Jones
  • Publication number: 20130213057
    Abstract: Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal segment for a set of rotatable blades includes: a blade arrival end; and a blade departure end; each of the blade arrival end and the blade departure end being angularly offset with respect to a longitudinal axis about which the blades rotate.
    Type: Application
    Filed: February 13, 2008
    Publication date: August 22, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Paul M. Lutjen, Susan M. Tholen
  • Publication number: 20130195632
    Abstract: In order to provide a wind turbine generator with a shaft and a bearing system which bearing system, e.g., using less material or using material which is relatively cheaper or which is not needed to have the same strength in comparison with some other solutions, there is disclosed a wind turbine generator with a bearing system including a lockable connection comprising a bearing surface and a support surface which surfaces are engaged when the lockable connection is locked and where forces from the shaft are transferred via the bearing and into the support through the bearing surface and wherein a support angle of the support surface, relatively to a shaft plane formed by rotating the shaft around a first axis, which first axis is perpendicular to the centre axis and which first axis is comprised in a vertical plane, is ranging from and including 5 degrees to and including 70 degrees.
    Type: Application
    Filed: September 27, 2011
    Publication date: August 1, 2013
    Applicant: VESTAS WIND SYSTEMS A/S
    Inventor: Jens Demtroder
  • Publication number: 20130195631
    Abstract: A thrust-bearing (1) disposed to face a thrust collar provided on a rotary shaft, including: grooves (5) formed at a bearing-surface (4b); a first-groove-group (6A) constituted by a plurality of first-spiral-grooves (6) formed at an inner circumferential side of the bearing-surface (4b); a second-groove-group (7A) constituted by a plurality of second-spiral-grooves (7) formed at an outer circumferential side more than the first-groove-group (6A) and wound in the same direction as the first-spiral-groove (6); and an annular-land-section (8) formed at the side, to which a fluid is drawn, among the inner circumferential more than the first-groove-group (6A) and the outer circumferential more than the second-groove-group (7A), wherein some of the first-spiral-grooves (6) of the first-groove-group (6A) and some of the second-spiral-grooves (7) of the second-groove-group (7A) are in communication with each other via a partial-communication-section (11), at least one side of which is in partial communication with th
    Type: Application
    Filed: October 19, 2011
    Publication date: August 1, 2013
    Inventor: Naomichi Omori
  • Publication number: 20130192261
    Abstract: A gas turbine engine includes high and low pressure turbines. A mid turbine frame is arranged axially between the high and low pressure turbines. A bearing is operatively supported by a support structure. An inner case is secured to the support structure and includes a first conical member and a bearing support to which the bearing is mounted. The bearing support includes a second conical member that is secured to the first conical member at a joint. The first and second conical members are arranged radially inward of the joint.
    Type: Application
    Filed: January 31, 2012
    Publication date: August 1, 2013
    Inventors: Robert Russell Mayer, George J. Kramer, Paul W. Palmer
  • Patent number: 8496431
    Abstract: A turbine ring assembly for a gas turbine, the assembly having a complete ring forming a single piece of ceramic matrix composite material (CMC), a metal structure for supporting the CMC ring having metal annular supports between which the CMC ring is placed while allowing differential expansion at least in a radial direction between the CMC ring and the annular supports, an arrangement for centering the CMC ring, and at least one element for preventing turning of the CMC ring about its axis.
    Type: Grant
    Filed: March 14, 2008
    Date of Patent: July 30, 2013
    Assignee: Snecma Propulsion Solide
    Inventors: Georges Habarou, Julien Mateo, Eric Bouillon
  • Publication number: 20130189084
    Abstract: A propeller shaft of a marine vessel is supported by bearing means within a stern tube or frame. The stern tube or frame has an aft end provided with a sealing assembly for sealing the propeller shaft. The sealing assembly and the stern tube or frame have at least one leakage monitor line for monitoring the condition of the sealing assembly. The at least one leakage monitor line is provided with a circumferentially extending channel section.
    Type: Application
    Filed: September 29, 2010
    Publication date: July 25, 2013
    Inventor: Craig Hatfull
  • FAN
    Publication number: 20130189083
    Abstract: A fan includes an outer casing having an air inlet and an air outlet, and an impeller housing located within the casing. An impeller is provided within the impeller housing for generating an air flow along a path extending from the air inlet to the air outlet through the impeller housing. A motor for driving the impeller is located within a motor housing connected to the impeller housing. A foam annular seal is located between the impeller housing and a seat to inhibit the leakage of air between the impeller housing and the casing. A plurality of resilient supports is provided between the impeller housing and the seat to reduce the load on the annular seal.
    Type: Application
    Filed: January 17, 2013
    Publication date: July 25, 2013
    Applicant: DYSON TECHNOLOGY LIMITED
    Inventor: Dyson Technology Limited
  • Publication number: 20130183144
    Abstract: A bearing housing (1) of an exhaust-gas turbocharger, having a housing body (2) in which an axial bearing (3) is arranged, and a compressor-side housing cover (4) which can be fixed in a compressor-side housing opening (6) by means of a fastening device (5). The fastening device (5) is a non-positively locking fastening device.
    Type: Application
    Filed: August 18, 2011
    Publication date: July 18, 2013
    Applicant: BORGWARNER INC.
    Inventors: Niclas Schenkenberger, Johannes Hornbach
  • Publication number: 20130170960
    Abstract: According to one aspect of the invention, a turbine assembly includes a stator and a rotor adjacent to the stator. The turbine assembly also includes a passage formed in a member coupled to the rotor to form a fluid curtain between the rotor and stator, wherein the fluid curtain reduces a flow between the stator and rotor.
    Type: Application
    Filed: January 4, 2012
    Publication date: July 4, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Ramesh Kempanna Babu
  • Publication number: 20130170961
    Abstract: Systems and methods according to these exemplary embodiments provide sealing mechanisms for centrifugal compressors. A sealing mechanism includes first, second and third dry gas seals arranged in series. Each seal receives its own sealing gas and has its own venting mechanism. Sealing gas pressures remain low enough that a dedicated compressor for supplying the sealing gases is not needed. Additionally, the risk of process gas being released into the atmosphere in case of seal failure is limited.
    Type: Application
    Filed: November 15, 2010
    Publication date: July 4, 2013
    Inventors: Stefano Meucci, Paolo Susini
  • Publication number: 20130170964
    Abstract: The present application provides a stage of a turbine engine. The stage may include a bucket, a shroud facing the bucket, and a contoured honeycomb seal on the shroud. The contoured honeycomb seal may include a first step with a first shape and a second step with a contoured shape.
    Type: Application
    Filed: January 3, 2012
    Publication date: July 4, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Rohit Chouhan, Georgia L. Fleming, Sumeet Soni
  • Patent number: 8475895
    Abstract: Articles including a primary composite structure having a circumference, at least one mounting flange operably connected to the primary composite structure about the circumference, the mounting flange having at least one circumferentially oriented core fiber.
    Type: Grant
    Filed: November 21, 2006
    Date of Patent: July 2, 2013
    Assignee: General Electric Company
    Inventor: Ming Xie
  • Publication number: 20130156553
    Abstract: A seal for a turbo machine is provided. The seal includes a plurality of honeycomb cells, at least one circumferential groove within the plurality of honeycomb cells, and at least one swirl brake within the at least one groove.
    Type: Application
    Filed: December 20, 2012
    Publication date: June 20, 2013
    Applicant: NUOVO PIGNONE S.P.A.
    Inventor: Nuovo Pignone S.P.A.
  • Publication number: 20130156544
    Abstract: A compressor (22) has a housing assembly (50) with a suction port (24) and a discharge port (26). A shaft (70) is mounted for rotation about an axis (500) and an impeller (44) is mounted to the shaft to be driven in at least a first condition so as to draw fluid in through the suction port and discharge the fluid from the discharge port. A magnetic bearing system (66, 67, 68) supports the shaft. A controller (84) is coupled to a sensor (80, 82) and configured to detect at least one of surge and pre-surge rotating stall and, responsive to said detection, take action to prevent or counter surge.
    Type: Application
    Filed: June 6, 2012
    Publication date: June 20, 2013
    Applicant: CARRIER CORPORATION
    Inventor: Vishnu M. Sishtla
  • Publication number: 20130156552
    Abstract: An assembly for a turbocharger and methods for creating the same are disclosed. Such assembly for a turbocharger includes a bearing housing having first and second bore ends, a housing cavity, and a bearing assembly disposed within the housing cavity. The bearing assembly includes an annular rotating journal positioned at the first bore end and first and second angular contact bearings positioned at the second bore end, where the first and second angular contact bearings resist axial loads in opposite directions. The bearing housing and bearing assembly are configured to receive a shaft and together dampen axial and radial loads in all directions from the shaft.
    Type: Application
    Filed: December 14, 2011
    Publication date: June 20, 2013
    Applicant: Precision Turbo & Engine Rebuilders, Inc.
    Inventor: Daniel J. Barlog
  • Publication number: 20130149116
    Abstract: A bearing housing (1) of an exhaust-gas turbocharger (24), having a mounting bore (2), a bearing device (3) which has two bearing bushes (4, 5) arranged in the mounting bore (2), between which bearing bushes is arranged a spacer (6), and a rotational speed sensor (7) which is fixed in a bearing housing recess (9) and which engages into a sensor recess (8) of the spacer (6). A resilient sleeve (10) is arranged in the bearing housing recess (9) around the rotational speed sensor (7) and engages with one end (11) into the sensor recess (8).
    Type: Application
    Filed: August 4, 2011
    Publication date: June 13, 2013
    Applicant: BorgWarner Inc.
    Inventor: Johannes Hornbach
  • Publication number: 20130129471
    Abstract: A compressor is disclosed having a shaft seal assembly and system that allows a high-pressure compressor to settle-out at a lower pressure level during shutdown. The seal assembly may be disposed about a portion of the shaft and define a blow-down seal chamber, the seal assembly including one or more gas seals in fluid communication with the blow-down seal chamber. A blow-down line is communicably coupled to the blow-down seal chamber to reference the blow-down seal chamber to a low pressure reference, such as a separate centrifugal compressor, or the like. Referencing the blow-down seal chamber to the low pressure reference reduces the required sealing pressure of the one or more gas seals. A valve may be disposed in the blow-down line and configured to regulate a flow of process gas leakage through the blow-down line.
    Type: Application
    Filed: June 28, 2011
    Publication date: May 23, 2013
    Applicant: Dresser-Rand Company
    Inventors: Manoj K. Gupta, Jose L. Gilarranz, Steven Nove, Kenneth Devito
  • Publication number: 20130129488
    Abstract: A high-speed blower designed to move and circulate dry process gas includes an axial or mixed-flow compressor driven by a brushless permanent magnet synchronous motor utilizing a remotely mounted variable frequency drive. The blower uses foil gas bearings which enable high-speed, low-power loss, and oil-free operation. The blower comprises an outer blower housing and an inner blower housing defining an annular cavity therebetween. A cooling flow of process gas may be leaked through the inner blower housing to cool the internal operational components of the blower, including the motor and the bearings, and to capture heat therefrom, which can be added to the process gas flow moving through the blower. Diffuser vanes and flow-straightening vanes are provided on the outer surface of the inner blower housing to improve the fluid dynamics of the process gas flow through the blower and heat transfer from the inner blower housing.
    Type: Application
    Filed: November 16, 2012
    Publication date: May 23, 2013
    Inventors: Giridhari L. Agrawal, Charles W. Buckley, Alexander R. Nelson
  • Patent number: 8439634
    Abstract: A BOAS with a blade tip shroud having rows of sinusoidal shaped grooves on a bottom side, each groove having a row of thin slots extending along the aft side of the groove and opening into the groove, and each thin slot connected to a plurality of metering holes that open into a cooling air supply cavity formed on the top surface of the tip shroud.
    Type: Grant
    Filed: January 21, 2011
    Date of Patent: May 14, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Publication number: 20130115058
    Abstract: There is provided a stator seal structure in a uniaxial eccentric screw pump by which the abrasion resistance of sealing mechanisms is improved and the pumped fluid can be prevented from stagnating in the sealing mechanisms. The stator seal structure is provided with a pair of sealing mechanisms for sealing between a housing and an intake side end portion, and between the housing and a discharge side end portion of the stator. The pair of sealing mechanisms is provided with ring-shaped secured rings respectively secured to the housing. The secured rings are respectively attached with elastic bodies for ensuring contact pressures between the sliding seal surface of the stator and the sliding seal surface of the secured rings with the elastic forces of the elastic bodies and for sealing between the secured rings and the housing.
    Type: Application
    Filed: August 11, 2011
    Publication date: May 9, 2013
    Applicant: FURUKAWA INDUSTRIAL MACHINERY SYSTEMS CO., LTD.
    Inventors: Kazutomo Hayashimoto, Jun Taneichi
  • Publication number: 20130115057
    Abstract: A bearing assembly for a gas turbine engine includes a bearing, an outer assembly disposed about an axis and having an angled perimeter, and an inner assembly supporting the bearing and having a surface angled to slide against and attach to the angled perimeter as the bearing is aligned with the axis.
    Type: Application
    Filed: November 7, 2011
    Publication date: May 9, 2013
    Inventors: Gabriel L. Suciu, Christopher M. Dye, Steven J. Bauer
  • Patent number: 8430628
    Abstract: A pressure balance seal includes a sealing surface facing an inward radial direction, and a stator interface comprising at least one surface interfacing with a stator. The pressure balance seal further includes a friction reducing feature. The friction reducing feature includes a cavity on the sealing surface. The cavity is configured to receive a fluid such that a normal force acting on the pressure balance seal is counterbalanced by a force generated by a pressure of the fluid.
    Type: Grant
    Filed: December 4, 2009
    Date of Patent: April 30, 2013
    Assignee: General Electric Company
    Inventors: Norman Arnold Turnquist, Keith Michael Parker, Xiaoqing Zheng, Rodrigo Rodriguez Erdmenger, Robbert Christiaan Pannekeet, Alexander Kimberley Simpson, Biao Fang
  • Publication number: 20130102834
    Abstract: Provided is a slide device which can reduce a frictional force more than a conventional slide device when used in an aqueous liquid containing a blood component. In a slide device which includes: a fixed-side slide member having a slide surface; and a rotary-side slide member having a slide surface, the slide device being used in an aqueous liquid containing a blood component in a state where the slide surface of the fixed-side slide member and the slide surface of the rotary-side slide member face each other in an opposed manner, at least one of the fixed-side slide member and the rotary-side slide member is formed of a member which is made of a material which contains silicon and has hydrate of silicon oxide on the slide surface thereof.
    Type: Application
    Filed: April 18, 2012
    Publication date: April 25, 2013
    Applicants: TOHOKU UNIVERSITY, SUN MEDICAL TECHNOLOGY RESEARCH CORPORATION
    Inventors: Keiichiro KANESHIMA, Takayuki MIYAKOSHI, Tomoya KITANO, Hideki KANEBAKO, Shinji KOBAYASHI, Koshi ADACHI, Koki KANDA, Daisuke SUZUKI
  • Publication number: 20130094943
    Abstract: An unducted fan of variable-pitch blades including roots engaged from outside in respective radial housings of an annular rotor element and guided to turn about their respective axes by pairs of rolling bearings, one of which is carried by an annular segment of a cylindrical skirt mounted in a groove of the annular body and by a locknut screwed onto the cylindrical skit. The bearing is covered externally by a ring including outer dog-clutch teeth co-operating with inner dog-clutch teeth of the housing to hold the ring axially in the housing. A blocking mechanism is engaged between the teeth of the housing and the teeth of the ring preventing the ring from turning and preventing the ring from being withdrawn axially from the housing.
    Type: Application
    Filed: April 1, 2011
    Publication date: April 18, 2013
    Applicant: SNECMA
    Inventors: Michel Andre Bouru, Adrien Jacques Philippe Fabre, Laurent Jablonski, Jean-Noel Mahieu
  • Patent number: 8419355
    Abstract: A fluid flow machine has a flow path provided by a casing (1) and a rotating shaft (2), in which rows of rotor blades (3) and stator blades (4) are arranged, and includes at least one annular groove-type recess (5) being disposed in a blade (3, 4) tip area in an annulus duct wall of the casing (1) and/or the shaft (2). An upstream end point (E) of the recess (5) in a flow direction is set at a distance (e)>0 forward of a forward blade tip point (A), and a downstream end point (F) of the recess (5) is set at a distance (f) rearward of point (A), where: 0.5 L>(f)>0, and L is a distance between point (A) and a rearward blade tip point (B).
    Type: Grant
    Filed: August 11, 2008
    Date of Patent: April 16, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Volker Guemmer, Marius Swoboda
  • Patent number: 8419347
    Abstract: A fluid pump comprising a pump body, a low pressure impeller, a high pressure impeller, impeller seal means separating the inlet side of the low pressure impeller from its pressure side, a pump priming system, and a pump priming conduit provided through the low pressure impeller radially inboard of the impeller seal means. The high pressure impeller is preferably provided within a cavity, defined by an impeller recess and a cover plate. A wear ring is preferably provided between the low pressure impeller and the inboard end of the cover plate. The pump priming conduit preferably comprises: first and second axial bores through the pump body; a radial bore and two axial holes through the cover plate; an axial hole through the rear wear ring; a cavity between the wear ring and the low pressure impeller; and axial holes through the low pressure impeller, connecting the cavity to the suction side of the low pressure impeller.
    Type: Grant
    Filed: March 10, 2008
    Date of Patent: April 16, 2013
    Assignee: Godiva Limited
    Inventor: Colin Thomas Pomfret
  • Publication number: 20130078080
    Abstract: A mid-turbine frame is disposed between high and low pressure turbine assemblies. A secondary air system is defined in the mid-turbine frame (MTF) to provide cooling to the turbine section of the engine. The secondary air system may be used to cool and pressurize seals to assist with oil retention in bearing cavities. The temperature gain of the secondary air may be reduced by flowing the secondary air through one or more external lines and then generally radially inwardly through air passages defined in the MTF.
    Type: Application
    Filed: September 13, 2012
    Publication date: March 28, 2013
    Inventors: Eric Durocher, Pierre-Yves Legare, Alessandro Ciampa
  • Patent number: 8398363
    Abstract: A device for sealing a bearing housing, which holds lubricating oil, from which a rotor supported inside the housing of an exhaust gas turbocharger is guided into a compressor housing, loadable by a mass flow of a charger. The device includes a fixed partition with a wall extension, a sealing disk fastened on a shaft of the rotor, a separating gap arranged between the sealing disk and the wall extension, and a drip device connected to an oil-collecting channel and directs lubricating oil collected in the oil-collecting channel into an oil drain by gravity. The drip device includes a drain-off surface for lubricating oil, which has a large axial distance from a rotating sealing disk which delimits the separating gap. Lubricating oil which can penetrate into the separating gap is guided into an oil drain of the bearing housing without interacting with the sealing disk.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: March 19, 2013
    Assignee: ABB Turbo Systems AG
    Inventors: Gerd Mundinger, Joel Schlienger, Matthias Kies, Patrick Aberle
  • Publication number: 20130051990
    Abstract: A method of repairing a circumferential flanged ring of a gas turbine engine with a bushing includes the steps of removing a damaged portion from a flange of a circumferential flanged ring that has an original profile to define a new profile and removing a portion of a bushing to define a bushing profile that matches the new profile of the flange. The method further includes the step of attaching the bushing to the flange of the circumferential flanged ring.
    Type: Application
    Filed: August 29, 2011
    Publication date: February 28, 2013
    Inventors: Leonard Paul Palmisano, William Bogue, Ron I. Prihar
  • Publication number: 20130051991
    Abstract: A seal for a gas turbine engine is shown. The engine may have a first vane for imparting a first twist to air passing thereby and/or a second vane for imparting a second, different twist to air passing thereby, each of the first and second vanes having a mounting area for mounting the seal thereto. The seal includes a top, a bottom, a left side, a right side a back, and a front. The back is parallel to the front and the left side is parallel to the right side such that a non-square shape is formed by the intersection of the back, the left side, the front and the right side so that the seal may mate with the mounting area of the first vane and, if the seal is inverted, may mate with the mounting area of the second vane.
    Type: Application
    Filed: August 30, 2011
    Publication date: February 28, 2013
    Inventors: Bradley T. Duelm, Randall J. Brown, Nathan A. Shirk, Lewis M. Holby
  • Publication number: 20130042628
    Abstract: A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal compartment structure.
    Type: Application
    Filed: August 17, 2011
    Publication date: February 21, 2013
    Inventor: Russell B. Witlicki
  • Patent number: 8371799
    Abstract: An apparatus and method for maintaining separation of two journal foil bearing assemblies, where each journal foil bearing assembly comprises one or more foils with lugs formed thereon for insertion into axial grooves of a bore, the means comprising a pin for insertion into each groove so that an edge of the lug that is inserted into the groove abuts the pin and is prevented from axially drifting along the bore. The pin provides a broad area along the lug edge so that the lug edge does not cut into the pin.
    Type: Grant
    Filed: January 13, 2010
    Date of Patent: February 12, 2013
    Assignee: Honeywell International Inc.
    Inventors: Adonis Kosta Spathias, Keith Alan Hurley, Hokuto Olson