Plural, Radially Spaced Vane Sets Patents (Class 415/208.4)
  • Patent number: 9587646
    Abstract: 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: Grant
    Filed: August 23, 2013
    Date of Patent: March 7, 2017
    Assignee: Ingersoll-Rand Company
    Inventors: Chester V. Swiatek, Mikhail Grigoriev, James Hitt, Noel Blair
  • Patent number: 9222485
    Abstract: A system, in certain embodiments, includes a centrifugal compressor diffuser vane including a leading edge, a trailing edge, and a constant thickness section extending between the leading edge and the trailing edge. A radius of curvature of the leading edge and a radius of curvature of the trailing edge vary along a span of the vane. A ratio of a length of the constant thickness section to a chord length of the vane is at least approximately 50%, and the ratio is substantially constant along the span of the vane.
    Type: Grant
    Filed: July 19, 2010
    Date of Patent: December 29, 2015
    Inventors: Paul C. Brown, Mikhail Grigoriev, Chester V. Swiatek
  • Publication number: 20140064953
    Abstract: 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: Application
    Filed: August 23, 2013
    Publication date: March 6, 2014
    Applicant: Cameron International Corporation
    Inventors: Chester V. Swiatek, Mikhail Grigoriev, James Hitt, Noel Blair
  • Patent number: 8602728
    Abstract: 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: Grant
    Filed: February 5, 2010
    Date of Patent: December 10, 2013
    Assignee: Cameron International Corporation
    Inventors: Chester V. Swiatek, Mikhail Grigoriev, James Hitt, Noel Blair, Jr.
  • Patent number: 8540484
    Abstract: A wedge-type diffuser includes a diffuser floor and a plurality of wedge-shaped vanes. The wedge-shaped vanes extend from the diffuser floor and have a top surface, a leading edge and a trailing edge. Each of the wedge-shaped vanes has a slot extending from the trailing edge toward the leading edge.
    Type: Grant
    Filed: July 23, 2010
    Date of Patent: September 24, 2013
    Assignee: United Technologies Corporation
    Inventors: Timothy M. Hollman, Kevin K. Taft, Gordon F. Jewess
  • Patent number: 8540483
    Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.
    Type: Grant
    Filed: March 9, 2012
    Date of Patent: September 24, 2013
    Assignee: United Technologies Corporation
    Inventors: Matthew E. Bintz, Peter T. Schutte, Anthony R. Bifulco, Eric W. Malmborg
  • Publication number: 20130045085
    Abstract: A motor suspension for fans has an air grille with radially extending braces and grille rings that are positioned coaxially to each other and are connected to each other by the radially extending braces. For adapting the motor suspension to a vibration behavior of a fan, at least one of a feature selected from a number of the braces and a diameter of the braces is varied to effect a reduction of acoustic noises and/or natural resonances of the motor suspension. The number of the braces that are preferably made of metal is preferably unequal to the number of vanes of the fan.
    Type: Application
    Filed: August 10, 2012
    Publication date: February 21, 2013
    Applicant: ZIEHL-ABEGG AG
    Inventors: Christian Frank, Patrick Neumaier, Christian Schönbein
  • Patent number: 8328535
    Abstract: A restraint system (300, 300?, 500) for a vaned diffuser (225) of a turbocharger (100) or other fluid boosting device is provided that can reduce or eliminate losses. The system (300, 300?, 500) uses a structure to provide both a pressure load on the vaned diffuser (225) and a seal for the vaned diffuser (225). The structure can be a fluoroelastomer O-ring (350, 350?, 550). The O-ring (350, 350?, 550) can be positioned at least partially in a channel (325, 325?, 525) formed in at least one of the diffuser ring (206, 206?), the compressor housing (103) and the center housing (102).
    Type: Grant
    Filed: February 6, 2008
    Date of Patent: December 11, 2012
    Assignee: BorgWarner Inc.
    Inventors: Paul Anschel, Michael Bucking, Robert Lancaster
  • Patent number: 8313290
    Abstract: In a high pressure centrifugal compressor, the occurrence of rotating stall noticeable in a comparatively-low specific speed wheel stage is prevented, thereby high efficient fluid performance is obtained and reliability is improved. The centrifugal compressor has a first vaneless diffuser with a constant flow channel height on the downstream side of an impeller, and a second vaneless diffuser in which the flow channel height decreases in a flow direction from an inlet to an outlet on the downstream side of the first vaneless diffuser. These diffusers are combined with an impeller using thick blades.
    Type: Grant
    Filed: June 22, 2009
    Date of Patent: November 20, 2012
    Assignee: Hitachi Plant Technologies, Ltd.
    Inventors: Masanori Tanaka, Hideo Nishida, Hiromi Kobayashi, Tetsuya Kuwano, Toshio Itou
  • Patent number: 8177503
    Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.
    Type: Grant
    Filed: April 17, 2009
    Date of Patent: May 15, 2012
    Assignee: United Technologies Corporation
    Inventors: Matthew E. Bintz, Peter T. Schutte, Anthony R. Bifulco, Eric W. Malmborg
  • Patent number: 8162604
    Abstract: The guide device for the diffusor at the compressor impeller outlet of a radial compressor has guide blades with stepped inlet edges. The step is implemented by setting back the hub-side inlet edge. This meridional stepping divides the guide blades into two component blades, of which the first component blade is made longer than the second component blade. The set-back of the inlet edge of the hub-side component blade and the associated superposition of the noise fields which are produced on the front and rear inlet edge of the diffusor leads to improvement of the acoustic properties of the compressor.
    Type: Grant
    Filed: May 23, 2007
    Date of Patent: April 24, 2012
    Assignee: ABB Turbo Systems AG
    Inventors: Janpeter Kühnel, Heinz-J{dot over (u)}rgen Feld, Christine Lindblom
  • Patent number: 8127551
    Abstract: A turbomachine including an annular combustion chamber, a centrifugal compressor, an annular diffuser enabling the flow of gas leaving the compressor to be diffused and directing this flow of gas towards the combustion chamber, and an outer casing surrounding the outside of the combustion chamber is disclosed. The diffuser includes an upstream portion oriented radially and presenting diffusion passages connected to the outlet from the compressor, an intermediate portion that is elbow-shaped, and a downstream portion having a series of circularly spaced-apart flow-straightening vanes. The flow stream in the downstream portion is delimited externally by the outer casing. The outer casing presents a shoulder against which the outer downstream edge of the intermediate portion comes into abutment.
    Type: Grant
    Filed: July 16, 2008
    Date of Patent: March 6, 2012
    Assignee: SNECMA
    Inventors: Patrice Commaret, Didier Hernandez
  • Patent number: 8047777
    Abstract: A turbomachine comprising an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage and an annular diffuser (20) comprising: a radially-oriented upstream portion (21)with diffusion passages (22) connected to the outlet of the compressor and an elbow-shaped intermediate portion (24)and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (0) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.
    Type: Grant
    Filed: August 12, 2008
    Date of Patent: November 1, 2011
    Assignee: SNECMA
    Inventors: Patrice Andre Commaret, Michel Andre Albert Desaulty, Romain Nicolas Lunel, Pascale Rollet
  • Patent number: 7797922
    Abstract: A casing for an aircraft turbine bypass engine comprises a splitter having slots to receive and be welded to a plurality of struts extending between an outer ring and an inner hub of the casing.
    Type: Grant
    Filed: June 4, 2007
    Date of Patent: September 21, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Andreas Eleftheriou, David Denis, Denis Leclair, Yves Roussel
  • Patent number: 7739866
    Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.
    Type: Grant
    Filed: July 20, 2007
    Date of Patent: June 22, 2010
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Andreas Eleftheriou, Kevin Walter Lobo, Maurice Weinberg, Quantai Liu
  • Patent number: 7726937
    Abstract: A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The airfoils have dihedral and sweep.
    Type: Grant
    Filed: September 12, 2006
    Date of Patent: June 1, 2010
    Assignee: United Technologies Corporation
    Inventors: P. William Baumann, Om Parkash Sharma, Charles R. LeJambre, Sanjay S. Hingorani
  • Patent number: 7654793
    Abstract: A support system for a motor within a fan shroud. Struts extending from the shroud to the motor support the motor. The struts are arranged in groups, which are spaced from adjacent groups, and each group contains a non-radial strut.
    Type: Grant
    Filed: May 13, 2005
    Date of Patent: February 2, 2010
    Assignee: Valeo Electrical Systems, Inc.
    Inventor: John R. Savage
  • Patent number: 7442006
    Abstract: An integrated assembly is provided for a centrifugal compressor, which integrates selected static portions of the centrifugal compressor into a monolithic structure to allow a small deflection of the inner flow path at assembly. The integrated assembly may include a machined compressor shroud casting having integral diffuser vanes, an aft sheet metal inner flow ring having a radially extending rim with slots in the inner flow ring for receiving diffuser vanes and slots in the rim for receiving deswirler vanes, an outer deswirler band surrounding the inner flow ring and having slots opposing those in the rim, and a plurality of deswirler vanes for fabrication between the inner flow ring and the deswirler band within the respective slots.
    Type: Grant
    Filed: August 15, 2005
    Date of Patent: October 28, 2008
    Assignee: Honeywell International Inc.
    Inventors: Ly D. Nguyen, Gary A. Shoff
  • Patent number: 7314113
    Abstract: Systems and methods for absorbing acoustic noise generated by computer cabinet cooling fans are described herein. In one embodiment, an acoustic absorber for use with a fan carried by a computer cabinet in a room includes a first acoustic panel spaced apart from a second acoustic panel. The first acoustic panel is configured to be positioned proximate to an outlet of the fan and at least approximately parallel to a flow of cooling air discharging from the outlet. The second acoustic panel is also configured to be positioned proximate to the outlet of the fan and at least approximately parallel to the flow of cooling air discharging from the outlet. The first and second acoustic panels together form an opening configured to direct the flow of cooling air away from the fan outlet and into the surrounding room. In a further embodiment, the opening formed by the first and second acoustic panels can be configured to extend at least approximately 360 degrees around the fan.
    Type: Grant
    Filed: September 14, 2004
    Date of Patent: January 1, 2008
    Assignee: Cray Inc.
    Inventor: Wade J. Doll
  • Patent number: 6634856
    Abstract: Integrally formed stamping sheet-metal blades having 3D structure for impeller or diffuser of a centrifugal pump or blower includes at least two integral forming blade or vane members. Each blade or vane member has a plurality of relatively short 3D blades or vanes extending radially outward and an engaging edge of selected shape. Two or more blade or vane members may be positioned and stacked together through mating the engaging edge and be spot welded to form a complete impeller or diffuser assembly. The blade or vane may be joined to form a completed smooth blade or vane, or may be spaced from each other to form a multi-row blade or vane assembly. The impeller and vane assembly may be made with less number of stamping molds and jigs. Production is less expensive. Positioning and assembly of the blade and vane is easier at a lower cost.
    Type: Grant
    Filed: April 26, 2002
    Date of Patent: October 21, 2003
    Assignee: Industrial Technology Research Insitute
    Inventors: Huan-Jan Chien, Yee-Ren Chen, Jing-Fuh Chen, Rong-Jau Liaw
  • Patent number: 6607353
    Abstract: The centrifugal compressor of the present invention is equipped with a plurality of vane groups (A, B) comprised of a plurality of vanes (16A, 16B) disposed in the peripheral direction of an impeller (12) so as to be concentric about the center of an axis of rotation (15) of the impeller, and the individual vanes (16A) belonging to vane group (A) nearest to the impeller are able to rotate. Since diffuser efficiency decreases if the intake flow volume of the impeller changes and the flow of gas is unable to easily continue from the vanes (16A) to vanes (16B), the vanes (16A) are rotated to change the inclination of the direction of a wing center line on their front edges so as to coincide with the direction of the flow of gas discharged from the impeller. As a result, diffuser efficiency is maintained at a high level even if the intake flow volume of the impeller is changed.
    Type: Grant
    Filed: July 26, 2001
    Date of Patent: August 19, 2003
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventor: Joo Masutani
  • Publication number: 20030021677
    Abstract: The centrifugal compressor of the present invention is equipped with a plurality of vane groups (A, B) comprised of a plurality of vanes (16A, 16B) disposed in the peripheral direction of an impeller (12) so as to be concentric about the center of an axis of rotation (15) of the impeller, and the individual vanes (16A) belonging to vane group (A) nearest to the impeller are able to rotate. Since diffuser efficiency decreases if the intake flow volume of the impeller changes and the flow of gas is unable to easily continue from the vanes (16A) to vanes (16B), the vanes (16A) are rotated to change the inclination of the direction of a wing center line on their front edges so as to coincide with the direction of the flow of gas discharged from the impeller. As a result, diffuser efficiency is maintained at a high level even if the intake flow volume of the impeller is changed.
    Type: Application
    Filed: July 26, 2001
    Publication date: January 30, 2003
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Joo Masutani
  • Publication number: 20020146320
    Abstract: A diffuser for a centrifugal compressor in which the diffuser has a plurality of passageways that each include a diffuser inlet region, a diffuser throat region, and a diffusion region. Within the diffuser inlet region are positioned pairs of opposed ridges that disrupt the boundary layer growth and minimize aerodynamic blockage at the throat region. The diffusion region includes a first diffusion region downstream of the throat region and that has a first area expansion ratio, and the second diffusion region that includes flow dividers to allow a total area expansion rate within the second diffusion region that is about twice that of the area expansion rate in the first diffusion region.
    Type: Application
    Filed: April 4, 2001
    Publication date: October 10, 2002
    Inventors: Zaher Milad Moussa, Gilbert John Laidlaw, David John Tapparo
  • Patent number: 6425737
    Abstract: A turbine comprises a housing having an inlet and an outlet, a stator mounted in the housing and including an arcuate stator blade projecting radially inward, and a turbine rotor having a central annular jet path accommodating therein said arcuate stator blade in communication with the inlet and the outlet. The turbine rotor comprises a pair of annular flywheel discs formed with pluralities of rotor blades facing each other in an axial direction. The arcuate stator blade has at least one deflection guide to direct the jet stream of working fluid toward the rotor blades in the central annular jet path.
    Type: Grant
    Filed: August 7, 2000
    Date of Patent: July 30, 2002
    Inventor: Takefumi Hatanaka
  • Patent number: 6203275
    Abstract: In a multi-stage centrifugal compressor, having a plurality of impellers mounted on a rotation shaft, or a single-stage centrifugal compressor, a vaned diffuser, having a plurality of vanes, is mounted at a downstream side of the impeller, and a vaneless diffuser portion is formed downstream of this vaned diffuser. A meridian plane cross-sectional shape of each of two wall surfaces forming the vaneless diffuser portion provided downstream of the vaned diffuser is such that its channel height is decreased progressively in a downstream direction. Instead of this vaneless diffuser, there can be provided a second vaned diffuser having a small number of vanes. In this case, also, two wall surfaces, forming the second vaned diffuser, are contracted progressively in the downstream direction.
    Type: Grant
    Filed: August 31, 1998
    Date of Patent: March 20, 2001
    Assignee: Hitachi, LTD
    Inventors: Hiromi Kobayashi, Hideo Nishida, Kazuki Takahashi, Takashi Eino
  • Patent number: 6200094
    Abstract: A wave augmented diffuser for a centrifugal compressor surrounds the outlet of an impeller that rotates on a drive shaft having an axis of rotation. The impeller brings flow in in an axial direction and imparts kinetic energy to the flow discharging it in radial and tangential directions. The flow is discharged into a plurality of circumferentially disposed wave chambers. The wave chambers are periodically opened and closed by a rotary valve such that the flow through the diffuser is unsteady. The valve includes a plurality of valve openings that are periodically brought into and out of fluid communication with the wave chambers. When the wave chambers are closed, a reflected compression wave moves upstream towards the diffuser bringing the flow into the wave chamber to rest. This action recovers the kinetic energy from the flow and limits any boundary layer growth. The flow is then discharged in an axial direction through an opening in the valve plate when the valve plate is rotated to an open position.
    Type: Grant
    Filed: June 18, 1999
    Date of Patent: March 13, 2001
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Gary J. Skoch, Daniel E. Paxson