Patents by Inventor Günter Ambrosy

Günter Ambrosy 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: 10518359
    Abstract: The present relates to a method of welding in deep joints in narrow-gap geometry. The two metallic components are arranged next to each other such that there is nearly a zero gap between the two components. The step of joining two metallic components is performed in two stages, the first stage being a root weld and the second stage being a fill up weld. The root weld is completed at the joining of the two discs starting from a middle portion to a point up to which there is still a zero gap between the two discs. From the point there exists a non-zero gap between the two discs up to an outer portion. The filler gap is filled by fill up welding. During fill up welding, a filler wire is melted along with the two discs by using the first source of energy, and to fill the filler gap along with molten material of the two discs.
    Type: Grant
    Filed: October 19, 2015
    Date of Patent: December 31, 2019
    Assignee: General Electric Technology GMBH
    Inventors: Dirk Jaekel, Balint Horvath, Sorin Keller, Guenter Ambrosy
  • Patent number: 9677149
    Abstract: A method for post-weld heat treatment of a without a filler material welded high strength component made of a gamma prime (??) strengthened superalloy can include providing the welded component, heating the welded component by applying a rapid heating-up rate in the range of 20° C./min to 40° C./min during the entire temperature range from room temperature (RT) up to a temperature T1 of at least 1000° C., holding the welded component at T1 and then heating the component by applying a slow heating-up rate of about 5° C./min to a final temperature Tf, then holding the welded component at Tf for a time tf sufficient for at least partially dissolving the gamma prime phase in a weld of the welded component and also in a base material surrounding the weld, and cooling the component with a cooling rate that is greater than or equal to about 20° C./min.
    Type: Grant
    Filed: June 17, 2014
    Date of Patent: June 13, 2017
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Thomas Etter, Daniel Beckel, Thomas Opderbecke, Guenter Ambrosy
  • Patent number: 9631813
    Abstract: An insert element for closing an opening inside a wall of a hot gas path component of a gas turbine includes a plate like body with an opening sided surface. The surface provides at least one first area which projects beyond at least one second area of said surface which surrounds the at least one first area frame-like. The at least one first area is encompassed by a circumferential edge corresponding in form and size to the opening such that the circumferential edge and the opening contour limit a gap at least in some areas, while the at least one second area contacts directly or indirectly the wall of the hot gas path component at a rear side facing away from the hot gas path. The plate like body provides at least a first functional layer-system, providing at least one layer made of heat resistant material, defining the first area of the surface (S).
    Type: Grant
    Filed: November 22, 2013
    Date of Patent: April 25, 2017
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Felix Reinert, Guenter Ambrosy, Matthias Hoebel, Jeffrey De Jonge
  • Patent number: 9488053
    Abstract: A method is provided for repairing a single crystal turbine blade, which includes an airfoil with a tip having a tip cover plate, tip cooling air holes and a tip crown. The method includes removing the tip crown by manual grinding, thereby preserving the underlying tip cover plate; preparing the tip cooling air holes by manual grinding; closing said prepared tip cooling air holes by manual welding; and building-up a new tip crown by a LMF (Laser Metal Forming) process.
    Type: Grant
    Filed: January 7, 2015
    Date of Patent: November 8, 2016
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Tobias Schmitt, Hans Bissig, Stefan Schlegel, Guenter Ambrosy, Michael Seemann, Hermann Emminger
  • Publication number: 20160114433
    Abstract: The present relates to a method of welding in deep joints in narrow-gap geometry. The two metallic components are arranged next to each other such that there is nearly a zero gap between the two components. The step of joining two metallic components is performed in two stages, the first stage being a root weld and the second stage being a fill up weld. The root weld is completed at the joining of the two discs starting from a middle portion to a point up to which there is still a zero gap between the two discs. From the point there exists a non-zero gap between the two discs up to an outer portion. The filler gap is filled by fill up welding. During fill up welding, a filler wire is melted along with the two discs by using the first source of energy, and to fill the filler gap along with molten material of the two discs.
    Type: Application
    Filed: October 19, 2015
    Publication date: April 28, 2016
    Inventors: Dirk JAEKEL, Balint HORVATH, Sorin KELLER, Guenter AMBROSY
  • Publication number: 20150184514
    Abstract: A method is provided for repairing a single crystal turbine blade, which includes an airfoil with a tip having a tip cover plate, tip cooling air holes and a tip crown. The method includes removing the tip crown by manual grinding, thereby preserving the underlying tip cover plate; preparing the tip cooling air holes by manual grinding; closing said prepared tip cooling air holes by manual welding; and building-up a new tip crown by a LMF (Laser Metal Forming) process.
    Type: Application
    Filed: January 7, 2015
    Publication date: July 2, 2015
    Inventors: Tobias SCHMITT, Hans BISSIG, Stefan SCHLEGEL, Guenter AMBROSY, Michael SEEMANN, Hermann EMMINGER
  • Patent number: 8978249
    Abstract: A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10).
    Type: Grant
    Filed: October 29, 2010
    Date of Patent: March 17, 2015
    Assignee: Alstom Technology Ltd.
    Inventors: Simone Hövel, Günter Ambrosy, Matthias Höbel
  • Publication number: 20140366995
    Abstract: The invention relates to a method of post-weld heat treatment of a without a filler material electron beam or laser welded high strength component made of a gamma prime (??) strengthened superalloy based on Ni or Co or Fe or combinations thereof. The method consists of the following steps a) providing the welded component, then b) heating the welded component by applying a rapid heating-up rate in the range of about 20 to 40° C./min during the entire temperature range from RT up to a temperature T1 of at least 1000° C., then c) holding the welded component at T1 and then heating the component by applying a slow heating-up rate of about 5° C./min to a final temperature Tf, then d) holding the welded component at Tf for a time tf, wherein isothermal dwell time tf is sufficient for at least partially dissolving the gamma prime phase in the weld and also in the base material surrounding the weld; then e) cooling the component with a cooling rate of about 20° C.
    Type: Application
    Filed: June 17, 2014
    Publication date: December 18, 2014
    Inventors: Thomas Etter, Daniel Beckel, Thomas Opderbecke, Guenter Ambrosy
  • Patent number: 8740572
    Abstract: A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there.
    Type: Grant
    Filed: November 1, 2010
    Date of Patent: June 3, 2014
    Assignee: Alstom Technology Ltd.
    Inventors: Matthias Hoebel, Günter Ambrosy, Felix Reinert, Stephane Barril
  • Publication number: 20140147251
    Abstract: The invention refers an insert element for closing an opening inside a wall of a hot gas path component of a gas turbine. The insert includes a plate like body with an opening sided surface. The surface provides at least one first area which projects beyond at least one second area of said surface which surrounds the at least one first area frame-like. The at least one first area is encompassed by a circumferential edge corresponding in form and size to the opening such that the circumferential edge and the opening contour limit a gap at least in some areas, while the at least one second area contacts directly or indirectly the wall of the hot gas path component at a rear side facing away from the hot gas path. The plate like body provides at least a first functional layer-system, providing at least one layer made of heat resistant material, defining the first area of the surface (S).
    Type: Application
    Filed: November 22, 2013
    Publication date: May 29, 2014
    Applicant: ALSTOM Technology Ltd
    Inventors: Felix REINERT, Guenter Ambrosy, Matthias Hoebel, Jeffrey De Jonge
  • Patent number: 8517673
    Abstract: A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).
    Type: Grant
    Filed: March 26, 2010
    Date of Patent: August 27, 2013
    Assignee: ALSTOM Technology Ltd.
    Inventors: Günter Ambrosy, Matthias Höbel, Ernst Vogt, Josef Hafner
  • Patent number: 8156649
    Abstract: A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair.
    Type: Grant
    Filed: April 8, 2009
    Date of Patent: April 17, 2012
    Assignee: Alstom Technology Ltd
    Inventors: Simone Hövel, Alexander Stankowski, Günter Ambrosy, Matthias Hoebel, Alexander Schnell, Hans Bissig, Rainer Kurtz
  • Publication number: 20110103968
    Abstract: A wear- and oxidation-resistant turbine blade and a method for producing the blade are provided. At least portions of the surface of the main blade section are provided with at least one first protective coating comprised of oxidation-resistant material, the first, oxidation-resistant coating is a metallic coating, which is optionally covered by a ceramic thermal barrier coating. The metallic first protective coating is arranged at least at the inner and outer crown edge of the blade tip, but not at the radially outer blade tip. The radially outer blade tip of the turbine blade is comprised of a second, single- or multi-layer wear- and oxidation-resistant protective coating, which is built up by laser metal forming and is comprised of abrasive and binder materials. The second protective coating on the blade tip overlaps along the outer and/or inner crown edge at least partially with the first, metallic protective coating arranged there.
    Type: Application
    Filed: November 1, 2010
    Publication date: May 5, 2011
    Applicant: ALSTOM TECHNOLOGY LTD
    Inventors: Matthias HOEBEL, Günter AMBROSY, Felix REINERT, Stephane BARRIL
  • Publication number: 20110099809
    Abstract: A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10).
    Type: Application
    Filed: October 29, 2010
    Publication date: May 5, 2011
    Inventors: Simone Hövel, Günter Ambrosy, Matthias Höbel
  • Publication number: 20110099810
    Abstract: A method for repairing an ex-service gas turbine component (10) includes the steps of: removing a damaged section (13) from the gas turbine component (10), manufacturing a 3-D article, which fits in the gas turbine component (10) to replace the removed damaged section (13), and joining the gas turbine component (10) and the 3-D article inserted therein. Reduced cost, improved flexibility and productivity, and simplified handling are achieved by removing the damaged section (13) in the form of a cut-out section along a split line (14) as one single cut-out piece (15), measuring the cut-out piece (15) to obtain the actual non-parametric geometry data set of the cut-out piece (15), and manufacturing the 3-D article based on the geometry data set of the cut-out piece (15).
    Type: Application
    Filed: October 29, 2010
    Publication date: May 5, 2011
    Inventors: Alexander STANKOWSKI, Simone HÖVEL, Lukas RICKENBACHER, Matthias HÖBEL, Günter AMBROSY
  • Publication number: 20100247309
    Abstract: A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).
    Type: Application
    Filed: March 26, 2010
    Publication date: September 30, 2010
    Inventors: Günter Ambrosy, Matthias Höbel, Ernst Vogt, Josef Hafner