Patents by Inventor Robert J. Albers

Robert J. Albers has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 7717667
    Abstract: A method for operating a gas turbine engine is provided. The gas turbine engine includes a fan, a high pressure turbine coupled downstream from the fan, and a low pressure turbine downstream from the high pressure turbine. The method includes channeling a portion of air discharged from the fan through a clearance control system including an inlet assembly that includes a plurality of louvers, and directing air from the inlet assembly into a first pipe and second pipe coupled to the inlet assembly such that pressure losses associated with the airflow are facilitated to be reduced.
    Type: Grant
    Filed: September 29, 2006
    Date of Patent: May 18, 2010
    Assignee: General Electric Company
    Inventors: Ryan Michael Urbassik, Scott Anthony Estridge, Rafael Ruiz, Robert Proctor, Robert J. Albers, Kevin Stephen Hansell
  • Patent number: 7487280
    Abstract: Information is obtained from a module received in a slot in a chassis. The information includes a number of ports in one or more module connectors which route at least one communication channel associated with a communication interfaces on the module. A determination is made as to the number of ports the slot has a capability to route the at least one communication channel to one or more backplanes in the chassis and to another module received in another slot in the chassis. A given number of ports in the one or more module connectors are enabled to forward data from the communication interface on the module and through the at least one communication channel to the other module based on the determination.
    Type: Grant
    Filed: May 12, 2006
    Date of Patent: February 3, 2009
    Assignee: Intel Corporation
    Inventors: Edoardo Campini, Douglas P. Bogia, Robert J. Albers
  • Patent number: 7458815
    Abstract: A chassis includes a plurality of slots to receive modules. The chassis further includes a first backplane to couple to modules that are received in the plurality of slots. The modules are to couple to the first backplane via a first communication interface on each module. The chassis also includes a second backplane to couple to at least a subset of the modules via a second communication interface on each of the subset of modules. One of the backplanes may be located in an upper or lower air plenum and used to interconnect modules slid along the slots from opposite directions. Some of the module connectors may be retractable to enable the modules to move into the chassis. The interface may be electrical, optical inductive or capacitive.
    Type: Grant
    Filed: March 30, 2006
    Date of Patent: December 2, 2008
    Assignee: Intel Corporation
    Inventors: Hassan Fallah-Adl, Edoardo Campini, Robert J. Albers
  • Publication number: 20080080967
    Abstract: A method for operating a gas turbine engine is provided. The gas turbine engine includes a fan, a high pressure turbine coupled downstream from the fan, and a low pressure turbine downstream from the high pressure turbine. The method includes channeling a portion of air discharged from the fan through a clearance control system including an inlet assembly that includes a plurality of louvers, and directing air from the inlet assembly into a first pipe and second pipe coupled to the inlet assembly such that pressure losses associated with the airflow are facilitated to be reduced.
    Type: Application
    Filed: September 29, 2006
    Publication date: April 3, 2008
    Inventors: Ryan Michael Urbassik, Scott Anthony Estridge, Rafael Ruiz, Robert Proctor, Robert J. Albers, Kevin Stephen Hansell
  • Patent number: 7272274
    Abstract: A chassis includes a plurality of slots to receive modules. The chassis includes an electrical backplane to couple to a module received in a first slot of the plurality of slots. The module to couple via a first communication interface on the module. An optical backplane is also included in the chassis. The optical backplane is to couple to the modules via a second communication interface on the module. The optical backplane is to couple to the second interface on the module via at least one interconnect through an opening in the electrical backplane. The interconnect configured to couple a fabric interface associated with the second communication interface to a communication channel routed over the optical backplane.
    Type: Grant
    Filed: March 30, 2006
    Date of Patent: September 18, 2007
    Assignee: Intel Corporation
    Inventors: Robert J. Albers, Edoardo Campini, Hassan Fallah-Adl
  • Patent number: 7165937
    Abstract: A method enables a gas turbine engine to be assembled. The method comprises coupling a rotor assembly including a plurality of circumferentially-spaced rotor blades downstream from, and in flow communication with, a compressor, coupling a casing assembly circumferentially around the rotor assembly such that a clearance is defined between an inner shroud surface of the casing assembly and the rotor blade tips, and coupling a clearance control system to the casing assembly to facilitate maintaining the clearance between the casing assembly and the rotor blade tips, wherein at least a portion of an external surface of the clearance control system is formed with a textured pattern that facilitates increasing the clearance control closure capability during engine operation.
    Type: Grant
    Filed: December 6, 2004
    Date of Patent: January 23, 2007
    Assignee: General Electric Company
    Inventors: Zhifeng Dong, Michael J. Epstein, Glen William Royal, Robert J. Albers
  • Publication number: 20040219011
    Abstract: A system and method for achieving clearance control for a high-pressure turbine by means of casing mechanical deflection. An active clearance control system is provided to act on a blade that rotates near a shroud. The shroud is attached to a case at a shroud supporting location, or shroud hanger. A clearance is required between a tip of the blade and the shroud. The blade tip and shroud are surrounded with an elastic case. This case can deflect radially in response not only to thermal expansion, but also to a difference in pressures acting on the inner and outer diameters of the case.
    Type: Application
    Filed: May 2, 2003
    Publication date: November 4, 2004
    Applicant: General Electric Company
    Inventors: Robert J. Albers, Rafael Ruiz, Marcia Boyle
  • Patent number: 6758477
    Abstract: A gas turbine engine aspirating face seal includes rotatable and non-rotatable engine members and a leakage path therebetween. Annular generally planar rotatable and non-rotatable gas bearing face surfaces are operably associated with the rotatable and non-rotatable engine members respectively and are circumscribed about and generally perpendicular to a centerline axis. A substantially fully annular pull off biasing element is operably disposed for urging the non-rotatable gas bearing face surface axially away from the rotatable gas bearing face surface and circumscribed about the centerline axis. The pull off biasing element may be at least one wave spring or one bellville washer. The non-rotatable gas bearing face surface may be on a face seal ring mounted on a translatable cylindrical piston which is axially movable and supported by the non-rotatable engine member.
    Type: Grant
    Filed: March 26, 2002
    Date of Patent: July 6, 2004
    Assignee: General Electric Company
    Inventors: John C. Brauer, Robert J. Albers
  • Patent number: 6676369
    Abstract: A gas turbine engine aspirating face seal includes a rotatable engine member and a non-rotatable engine member and a leakage path therebetween. Annular generally planar rotatable and non-rotatable gas bearing face surfaces circumscribed about a centerline are operably associated the rotatable and non-rotatable engine members respectively. Radially inner and outer tooth rings axially extend away from a first one of the rotatable and non-rotatable gas bearing face surfaces across the leakage path and towards a second one of the gas bearing face surfaces. A pull off biasing means is used for urging the inner and outer tooth rings axially away from the second one of the gas bearing face surfaces. The rotatable engine member may be a side plate mounted on a rotor disk and the non-rotatable engine member is mounted on a translatable piston axially movably supported on a stationary face seal support structure.
    Type: Grant
    Filed: March 26, 2002
    Date of Patent: January 13, 2004
    Assignee: General Electric Company
    Inventors: John C. Brauer, Christopher C. Glynn, Robert J. Albers
  • Patent number: 6644668
    Abstract: A support arrangement for a brush seal positioned between a stationary and a rotatable component of a turbomachine. The brush seal has a downstream backing plate that includes an axially-extending lip adjacent its radially outermost end to minimize axial deflection of the seal as a result of a gas pressure differential acting across the seal.
    Type: Grant
    Filed: June 13, 2002
    Date of Patent: November 11, 2003
    Assignee: General Electric Company
    Inventors: Robert J. Albers, Randall C. Bauer, John C. Brauer, Scott Joseph Schmid, Kenneth M. Lewis
  • Publication number: 20030184022
    Abstract: A gas turbine engine aspirating face seal includes rotatable and non-rotatable engine members and a leakage path therebetween. Annular generally planar rotatable and non-rotatable gas bearing face surfaces are operably associated with the rotatable and non-rotatable engine members respectively and are circumscribed about and generally perpendicular to a centerline axis. A substantially fully annular pull off biasing means s operably disposed for urging the non-rotatable gas bearing face surface axially away from the rotatable gas bearing face surface and circumscribed about the centerline axis. The pull off biasing means may be at least one wave spring or one bellville washer. The non-rotatable gas bearing face surface may be on a face seal ring mounted on a translatable cylindrical piston which is axially movable and supported by the non-rotatable engine member.
    Type: Application
    Filed: March 26, 2002
    Publication date: October 2, 2003
    Inventors: John C. Brauer, Robert J. Albers
  • Publication number: 20030185669
    Abstract: A gas turbine engine aspirating face seal includes a rotatable engine member and a non-rotatable engine member and a leakage path therebetween. Annular generally planar rotatable and non-rotatable gas bearing face surfaces circumscribed about a centerline are operably associated the rotatable and non-rotatable engine members respectively. Radially inner and outer tooth rings axially extend away from a first one of the rotatable and non-rotatable gas bearing face surfaces across the leakage path and towards a second one of the gas bearing face surfaces. A pull off biasing means is used for urging the inner and outer tooth rings axially away from the second one of the gas bearing face surfaces. The rotatable engine member may be a side plate mounted on a rotor disk and the non-rotatable engine member is mounted on a translatable piston axially movably supported on a stationary face seal support structure.
    Type: Application
    Filed: March 26, 2002
    Publication date: October 2, 2003
    Inventors: John C. Brauer, Christopher C. Glynn, Robert J. Albers
  • Patent number: 6095750
    Abstract: A turbine nozzle assembly includes a plurality of nozzle segments and a nozzle support for supporting the nozzle segments. Each nozzle segment includes an outer band, an inner band and at least two vanes disposed between the outer and inner bands. A retention flange extends radially inwardly from the inner band and has a first hole formed therein. The nozzle support includes a recess formed therein and a mounting flange extending therefrom. The mounting flange is disposed in contact with the retention flange and has a second hole formed therein. A pin is disposed in the first and second holes to position the flanges with respect to one another. A pin retainer is disposed in the recess and has a holding flange for retaining the pin in place. The nozzle support includes a substantially conical portion and an air seal integrally formed thereto.
    Type: Grant
    Filed: December 21, 1998
    Date of Patent: August 1, 2000
    Assignee: General Electric Company
    Inventors: Steven A. Ross, Robert J. Albers, Edward P. Brill, Andrew D. Kemp, Larry W. Plemmons
  • Patent number: 5984630
    Abstract: A blocker and swirl inducer hole configuration for use in connection with a high pressure turbine is described. In one embodiment, the blocker holes are oriented to a 45-degree tangential angle with respect to the direction of rotation of the seal, which results in pre-swirling the air before being injected into the swirl cavity. In addition, the number of blocker holes is reduced by as much as 50% of the number of blocker holes used in the known CFM56 turbine. Further, rather than injecting the air into the first swirl cavity as is known, the air is injected into a second swirl cavity. The combined effect of orienting the holes to the 45-degree tangential angle with respect to the direction of rotation of the seal, locating the holes to open into the second swirl cavity, and reducing the flow area by about 50%, results in an increase in blocker hole pressure ratio. Increasing the blocker hole pressure ratio results in a higher hole exit velocity which maximizes the cavity inlet swirl.
    Type: Grant
    Filed: December 24, 1997
    Date of Patent: November 16, 1999
    Assignee: General Electric Company
    Inventors: David A. Di Salle, Robert Proctor, Edward P. Brill, Steven A. Ross, Robert J. Albers, John C. Brauer, Gulcharan S. Brainch, Dean T. Lenahan
  • Patent number: 5970716
    Abstract: A double annular combustor having concentrically disposed inner and outer annular combustors including an inner dome having an inner portion and an outer portion, an outer dome having an inner portion and an outer portion, wherein the outer dome inner portion is connected to the inner dome outer portion, and a substantially annular centerbody disposed between the inner dome and the outer dome. The centerbody includes a plurality of structurally independent arcuate segments, wherein each centerbody segment is retained in position via an interference fit between a first flange of such centerbody extending downstream and a hook in the inner dome outer portion and/or via a clamping fit of a second flange of the centerbody extending upstream to a flange of the inner dome outer portion.
    Type: Grant
    Filed: October 2, 1997
    Date of Patent: October 26, 1999
    Assignee: General Electric Company
    Inventors: James M. Forrester, Gregory A. Cimmarusti, David B. Legger, James N. Cooper, Robert J. Albers
  • Patent number: 5735671
    Abstract: A turbine rotor includes a rotor disk having a plurality of dovetail slots defining therebetween respective disk posts. Each post has a top land and a plurality of tangs spaced radially therebelow inside adjacent ones of the slots. A plurality of turbine blades each having a dovetail are mounted in respective ones of the dovetail slots for radially retaining the blades. A platform is joined integrally with the dovetail and extends circumferentially to adjoin adjacent ones of the platforms to define a radially inner flowpath. An airfoil extends integrally from the platform for extracting energy from combustion gases flowable thereover. A thermal barrier coating is fixedly bonded to each of the disk post top lands for providing thermal insulation between the platforms and the disk posts for reducing disk post temperature.
    Type: Grant
    Filed: November 29, 1996
    Date of Patent: April 7, 1998
    Assignee: General Electric Company
    Inventors: John C. Brauer, David A. Di Salle, Edward P. Brill, Robert J. Albers, Dean T. Lenahan
  • Patent number: 5205115
    Abstract: A thermal control apparatus is provided for gas turbine engine cases and particularly for thermal control of clearances between turbine rotors and surrounding shrouds. Thermal control of an annular case section or ring is provided by counterflowing two heat transfer fluid flowpaths in heat transfer communication with the section of engine casing. The flowpaths may be in parallel or series such that there is substantially no circumferential gradient in the mass flowrate weighted average temperature of the heat transfer fluid supplied by the two counterflowing fluid flowpaths. One embodiment provides forward and aft rings cooled by three spray tubes in each of two 180.degree. sectors whereby the forward and aft spray tubes flow thermal control air flowing in one circumferential direction and the middle spray tubes flows thermal control air in an opposite circumferential direction.
    Type: Grant
    Filed: November 4, 1991
    Date of Patent: April 27, 1993
    Assignee: General Electric Company
    Inventors: Larry W. Plemmons, Robert Proctor, Robert J. Albers, Donald L. Gardner
  • Patent number: 5169287
    Abstract: To cool the shroud in the high pressure turbine section of a gas turbine engine, high pressure cooling air is directed in metered flow to baffle plenums and thence through baffle perforations to impingement cool the shroud rails and back surface. Impingement cooling air then flows through elongated, convection cooling passages in the shroud and exits to flow along the shroud front surface with the main gas stream to provide film cooling. The baffle perforations and the convection cooling passages are interactively located to achieve maximum cooling benefit and highly efficient cooling air utilization.
    Type: Grant
    Filed: May 20, 1991
    Date of Patent: December 8, 1992
    Assignee: General Electric Company
    Inventors: Robert Proctor, Larry W. Plemmons, Gulcharan S. Brainch, John R. Hess, Robert J. Albers