Patents by Inventor Vaclav Kares

Vaclav Kares 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: 10233756
    Abstract: A two-sided turbocharger compressor wheel and a housing forming a diffuser for the compressor. A first side and a second side of the compressor wheel are characterized by different values of a trim and of an annulus area. A first side of the diffuser surrounds the first side of the compressor wheel, and a second side of the diffuser surrounds the second side of the compressor wheel. The first and second sides of the diffuser are characterized by different annulus area ratios. The blades of the first and second sides of the compressor wheel are angularly offset from one another. The compressor wheel is configured for greater flow through the side of the compressor wheel that faces away from a related turbine wheel.
    Type: Grant
    Filed: August 27, 2013
    Date of Patent: March 19, 2019
    Assignee: GARRETT TRANSPORTATION I INC.
    Inventors: Hua Chen, Annie Li, Michael Zhao, Wei Dai, Jose Luis Lazaro Bercianos, Vit Houst, Daniel Turecek, Vaclav Kares, Milan Nejedly, Michal Mokos
  • Patent number: 10190596
    Abstract: A multi-stage compressor for a turbocharger includes a compressor housing that defines an aperture for receiving a compressor wheel for successively compressing air in first and second stages. First- and second-stage inlets are fluidly connected to the aperture in opposite axial directions, and first- and second-stage volutes extend at least partially annularly therearound so that each volute is configured to receive gas flowing generally radially outward from the compressor wheel. First and second passages fluidly connect the first-stage volute to the second-stage inlet. The passages approach the second-stage inlet from opposite radially inward directions, and are asymmetric with respect to any pair of orthogonal axes having an origin lying on the turbocharger rotary axis as viewed on a transverse cross-section that is normal to the turbocharger axis.
    Type: Grant
    Filed: November 3, 2016
    Date of Patent: January 29, 2019
    Assignee: Garrett Transportation I Inc.
    Inventors: Vaclav Kares, Vit Houst, Ondrej Lednicky, Milan Nejedly, Michal Mokos, Zbynek Oslejsek, Daniel Turecek
  • Patent number: 10006290
    Abstract: A two-sided turbocharger compressor wheel and a housing forming a diffuser for the compressor. A first side and a second side of the compressor wheel are characterized by different values of a trim and of an annulus area. A first side of the diffuser surrounds the first side of the compressor wheel, and a second side of the diffuser surrounds the second side of the compressor wheel. The first and second sides of the diffuser are characterized by different annulus area ratios. The blades of the first and second sides of the compressor wheel are angularly offset from one another. The compressor wheel is configured for greater flow through the side of the compressor wheel that faces away from a related turbine wheel.
    Type: Grant
    Filed: August 27, 2013
    Date of Patent: June 26, 2018
    Assignee: Honeywell International Inc.
    Inventors: Vit Houst, Daniel Turecek, Vaclav Kares, Milan Nejedly, Michal Mokos, Hua Chen, Annie Li, Michael Zhao, Wei Dai, Jose Luis Lazaro Bercianos
  • Publication number: 20180119708
    Abstract: A multi-stage compressor for a turbocharger includes a compressor housing that defines an aperture for receiving a compressor wheel for successively compressing air in first and second stages. First- and second-stage inlets are fluidly connected to the aperture in opposite axial directions, and first- and second-stage volutes extend at least partially annularly therearound so that each volute is configured to receive gas flowing generally radially outward from the compressor wheel. First and second passages fluidly connect the first-stage volute to the second-stage inlet. The passages approach the second-stage inlet from opposite radially inward directions, and are asymmetric with respect to any pair of orthogonal axes having an origin lying on the turbocharger rotary axis as viewed on a transverse cross-section that is normal to the turbocharger axis.
    Type: Application
    Filed: November 3, 2016
    Publication date: May 3, 2018
    Applicant: Honeywell International Inc.
    Inventors: Vaclav Kares, Vit Houst, Ondrej Lednicky, Milan Nejedly, Michal Mokos, Zbynek Oslejsek, Daniel Turecek
  • Patent number: 9869237
    Abstract: A turbocharger includes a two-stage serial compressor having first and second impellers, with a crossover duct for leading air from the first impeller into the second impeller for further compression. The compressor housing also defines a bypass duct from the crossover duct to the air discharge duct from the compressor, and a bypass valve disposed in the bypass duct. Under certain operating conditions (such as high-flow, low-pressure-ratio conditions) the bypass valve can be opened to bypass the second impeller, such that the compressor behaves like a single-stage compressor. At other operating conditions, the bypass valve is closed so that the compressor provides two-stage compression for higher pressure ratios.
    Type: Grant
    Filed: August 19, 2015
    Date of Patent: January 16, 2018
    Assignee: Honeywell International Inc.
    Inventors: Vit Houst, Daniel Turecek, Vaclav Kares, Milan Nejedly, Ondrej Lednicky, Michal Mokos, Zbynek Oslejsek
  • Patent number: 9856886
    Abstract: An assembly can include a first radial compressor wheel that has a rotational axis and that includes a hub surface that includes an annular ridge disposed at a radius measured from the rotational axis; a second radial compressor wheel that includes a hub surface; and an annular baffle disposed at least in part between the hub surfaces where the annular baffle includes an outer surface and an inner edge that defines an opening having a central axis where the outer surface includes a surface portion to one side of the inner edge that faces the hub surface of the first radial compressor wheel, where the surface portion includes an annular channel over a radial width measured from the central axis and where the radial width spans the radius of the annular ridge.
    Type: Grant
    Filed: January 8, 2015
    Date of Patent: January 2, 2018
    Assignee: Honeywell International Inc.
    Inventors: Vaclav Kares, Vit Houst, Ondrej Lednicky, Michal Mokos, Milan Nejedly, Zbynek Oseljsek, Daniel Turecek
  • Patent number: 9702299
    Abstract: An assembly for a turbocharger can include a pinched nozzle cartridge that includes a base component, an insert component and vanes disposed at least in part between the base component and the insert component, where the insert component includes a shroud surface and an upper pinch profile, where the base component includes an annular surface that defines a turbine wheel opening and a lower profile and where the upper pinch profile and the lower profile form a pinched nozzle. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.
    Type: Grant
    Filed: December 9, 2013
    Date of Patent: July 11, 2017
    Assignee: Honeywell International Inc.
    Inventor: Vaclav Kares
  • Patent number: 9631625
    Abstract: A statorless axial turbine for a turbocharger has a turbine housing assembly defining a meridionally divided scroll extending circumferentially and surrounding the turbine wheel, the meridionally divided scroll defining a first scroll extending substantially fully about the turbine wheel and a separate second scroll extending substantially fully about the turbine wheel. The turbine housing assembly defines a separate inlet for each of the first and second scrolls through which a separate exhaust gas stream is received, and separate first and second outlets for each of the first and second scrolls, respectively, through which the respective exhaust gas streams are fed into an inlet side of the turbine wheel generally in an axial direction of the turbine wheel.
    Type: Grant
    Filed: February 1, 2013
    Date of Patent: April 25, 2017
    Assignee: Honeywell International Inc.
    Inventors: Vit Houst, Vaclav Kares
  • Publication number: 20170051661
    Abstract: A turbocharger includes a two-stage serial compressor having first and second impellers, with a crossover duct for leading air from the first impeller into the second impeller for further compression. The compressor housing also defines a bypass duct from the crossover duct to the air discharge duct from the compressor, and a bypass valve disposed in the bypass duct. Under certain operating conditions (such as high-flow, low-pressure-ratio conditions) the bypass valve can be opened to bypass the second impeller, such that the compressor behaves like a single-stage compressor. At other operating conditions, the bypass valve is closed so that the compressor provides two-stage compression for higher pressure ratios.
    Type: Application
    Filed: August 19, 2015
    Publication date: February 23, 2017
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Vit Houst, Daniel Turecek, Vaclav Kares, Milan Nejedly, Ondrej Lednicky, Michal Mokos, Zbynek Oslejsek
  • Patent number: 9429162
    Abstract: A statorless or nozzleless axial turbine for a turbocharger has an axial turbine wheel that receives a swirling flow of exhaust gas substantially in an axial direction. The turbine includes a sector-divided turbine housing defining a plurality of separate exhaust gas inlets each for receiving a separate exhaust gas stream from an internal combustion engine, the sector-divided turbine housing further defining a plurality of separate angular sector passageways each of which occupies a fractional part of a circumference surrounding the turbine wheel, each angular sector passageway being supplied with exhaust gas by a respective one of the plurality of exhaust gas inlets. The turbine housing assembly defines a separate sector outlet for each angular sector passageway. The turbine housing assembly can include a separately formed heat shroud, and the sector outlets can be formed at least in part by the heat shroud.
    Type: Grant
    Filed: February 1, 2013
    Date of Patent: August 30, 2016
    Assignee: Honeywell International Inc.
    Inventors: Vit Houst, Vaclav Kares
  • Publication number: 20160201683
    Abstract: An assembly can include a first radial compressor wheel that has a rotational axis and that includes a hub surface that includes an annular ridge disposed at a radius measured from the rotational axis; a second radial compressor wheel that includes a hub surface; and an annular baffle disposed at least in part between the hub surfaces where the annular baffle includes an outer surface and an inner edge that defines an opening having a central axis where the outer surface includes a surface portion to one side of the inner edge that faces the hub surface of the first radial compressor wheel, where the surface portion includes an annular channel over a radial width measured from the central axis and where the radial width spans the radius of the annular ridge.
    Type: Application
    Filed: January 8, 2015
    Publication date: July 14, 2016
    Inventors: Vaclav Kares, Vit Houst, Ondrej Lednicky, Michal Mokos, Milan Nejedly, Zbynek Oseljsek, Daniel Turecek
  • Patent number: 9200518
    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 and a curved leading edge, 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.
    Type: Grant
    Filed: October 24, 2013
    Date of Patent: December 1, 2015
    Assignee: Honeywell International Inc.
    Inventor: Vaclav Kares
  • Publication number: 20150159660
    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.
    Type: Application
    Filed: December 6, 2013
    Publication date: June 11, 2015
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Vaclav Kares, Jeffrey Allen Lotterman, Josef Ferda
  • Publication number: 20150113982
    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 and a curved leading edge, 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.
    Type: Application
    Filed: October 24, 2013
    Publication date: April 30, 2015
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventor: Vaclav Kares
  • Publication number: 20150064002
    Abstract: A two-sided turbocharger compressor wheel and a housing forming a diffuser for the compressor. A first side and a second side of the compressor wheel are characterized by different values of a trim and of an annulus area. A first side of the diffuser surrounds the first side of the compressor wheel, and a second side of the diffuser surrounds the second side of the compressor wheel. The first and second sides of the diffuser are characterized by different annulus area ratios. The blades of the first and second sides of the compressor wheel are angularly offset from one another. The compressor wheel is configured for greater flow through the side of the compressor wheel that faces away from a related turbine wheel.
    Type: Application
    Filed: August 27, 2013
    Publication date: March 5, 2015
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Hua Chen, Annie Li, Michael Zhao, Wei Dai, Jose Luis Lazaro Bercianos, Vit Houst, Daniel Turecek, Vaclav Kares, Milan Nejedly, Michal Mokos
  • Publication number: 20150063980
    Abstract: A two-sided turbocharger compressor wheel and a housing forming a diffuser for the compressor. A first side and a second side of the compressor wheel are characterized by different values of a trim and of an annulus area. A first side of the diffuser surrounds the first side of the compressor wheel, and a second side of the diffuser surrounds the second side of the compressor wheel. The first and second sides of the diffuser are characterized by different annulus area ratios. The blades of the first and second sides of the compressor wheel are angularly offset from one another. The compressor wheel is configured for greater flow through the side of the compressor wheel that faces away from a related turbine wheel.
    Type: Application
    Filed: August 27, 2013
    Publication date: March 5, 2015
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Vit Houst, Daniel Turecek, Vaclav Kares, Milan Nejedly, Michal Mokos, Hua Chen, Annie Li, Michael Zhao, Wei Dai, Jose Luis Lazaro Bercianos
  • Publication number: 20140219790
    Abstract: A statorless or nozzleless axial turbine for a turbocharger has an axial turbine wheel that receives a swirling flow of exhaust gas substantially in an axial direction. The turbine includes a sector-divided turbine housing defining a plurality of separate exhaust gas inlets each for receiving a separate exhaust gas stream from an internal combustion engine, the sector-divided turbine housing further defining a plurality of separate angular sector passageways each of which occupies a fractional part of a circumference surrounding the turbine wheel, each angular sector passageway being supplied with exhaust gas by a respective one of the plurality of exhaust gas inlets. The turbine housing assembly defines a separate sector outlet for each angular sector passageway. The turbine housing assembly can include a separately formed heat shroud, and the sector outlets can be formed at least in part by the heat shroud.
    Type: Application
    Filed: February 1, 2013
    Publication date: August 7, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Vit Houst, Vaclav Kares
  • Publication number: 20140219836
    Abstract: A statorless axial turbine for a turbocharger has a turbine housing assembly defining a meridionally divided scroll extending circumferentially and surrounding the turbine wheel, the meridionally divided scroll defining a first scroll extending substantially fully about the turbine wheel and a separate second scroll extending substantially fully about the turbine wheel. The turbine housing assembly defines a separate inlet for each of the first and second scrolls through which a separate exhaust gas stream is received, and separate first and second outlets for each of the first and second scrolls, respectively, through which the respective exhaust gas streams are fed into an inlet side of the turbine wheel generally in an axial direction of the turbine wheel.
    Type: Application
    Filed: February 1, 2013
    Publication date: August 7, 2014
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Vit Houst, Vaclav Kares
  • Patent number: 8769950
    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.
    Type: Grant
    Filed: June 3, 2013
    Date of Patent: July 8, 2014
    Assignee: Honeywell International Inc.
    Inventors: Jeffrey A. Lotterman, Vaclav Kares
  • Publication number: 20140178217
    Abstract: An assembly for a turbocharger can include a pinched nozzle cartridge that includes a base component, an insert component and vanes disposed at least in part between the base component and the insert component, where the insert component includes a shroud surface and an upper pinch profile, where the base component includes an annular surface that defines a turbine wheel opening and a lower profile and where the upper pinch profile and the lower profile form a pinched nozzle. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.
    Type: Application
    Filed: December 9, 2013
    Publication date: June 26, 2014
    Applicant: Honeywell International Inc.
    Inventor: Vaclav Kares