Patents by Inventor Wolfgang Balzer
Wolfgang Balzer 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).
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Patent number: 11466573Abstract: A turbine vane for a gas turbine engine, including: a first airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from an inner platform in a radial direction to an outer platform, wherein a portion of the exterior airfoil surface of the first airfoil is formed in conformance with a set of Cartesian coordinates set forth in Table 1 as offset by corresponding values in Table 4, and wherein the values of Table 4 are offset from a point of origin that is a point where a radially outward surface of the inner platform meets a surface of a trailing edge of the inner platform and a surface of a mate face of the inner platform.Type: GrantFiled: March 15, 2021Date of Patent: October 11, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: Wolfgang Balzer
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Patent number: 11078793Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.Type: GrantFiled: September 18, 2019Date of Patent: August 3, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Wolfgang Balzer, Thomas J. Praisner, Atul Kohli, Mark F. Zelesky, Dominic J. Mongillo, Jr.
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Patent number: 10890072Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extend along an axial chord between a leading edge and a trailing edge. A first profiled region protrudes from the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall along the leading edge of the second side of the second airfoil adjacent the leading edge of the second airfoil. A third profiled region recessed into the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil.Type: GrantFiled: April 5, 2018Date of Patent: January 12, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: Wolfgang Balzer
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Publication number: 20200368129Abstract: The present invention relates to a composition for dyeing keratin fibers, for example human hair, with oxidative hair dyes. The composition contains as oxidative dyes a combination of a p-phenylenediamine derivative as the developer substance and 2,7-naphthalenediol as the coupler substance in a suitable base. An oxidizing agent such as hydrogen peroxide is used as an additional component for developing the dye. The invention relates to a use of the composition for gray coloration, with a long-lasting reduction of a yellow tinge in a hairstyle of gray, previously dark hair.Type: ApplicationFiled: December 21, 2017Publication date: November 26, 2020Inventors: Wolfgang BALZER, Gunther AUGENSTEIN, Christian ADER
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Publication number: 20200230753Abstract: A method of forming an airfoil includes casting the airfoil with an internal cooling circuit and an exterior surface with a positive feature. The exterior surface of the airfoil is scanned with a first probe. A size and a location of the positive feature are identified based on the scan of the exterior surface. A transformation matrix is created with a controller such that the transformation matrix includes toolpath transformation instructions. A transformed set of machine toolpath instructions is created by applying the transformation matrix using the controller to a first set of machine toolpath instructions to align the first set of machine toolpath instructions relative to the positive feature. A contour is then machined into the exterior surface of the airfoil based on the transformed set of machine toolpath instructions.Type: ApplicationFiled: January 18, 2019Publication date: July 23, 2020Inventors: James Tilsley Auxier, Alan C. Barron, Wolfgang Balzer
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Patent number: 10711618Abstract: In one embodiment, a component for a gas turbine engine is provided. The component including: an airfoil having a tip portion; a tip shelf located in the tip portion; a first plurality of cooling openings located in an edge of the tip shelf that extends along at least a portion of a pressure side of the airfoil; and a second plurality of cooling openings located in an edge of the tip portion proximate to the tip shelf that extends along at least a portion of a pressure side of the tip portion.Type: GrantFiled: May 25, 2017Date of Patent: July 14, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Dominic J. Mongillo, Wolfgang Balzer, Atul Kohli
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Publication number: 20200141244Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.Type: ApplicationFiled: September 18, 2019Publication date: May 7, 2020Inventors: Wolfgang Balzer, Thomas J. Praisner, Atul Kohli, Mark F. Zelesky, Dominic J. Mongillo, JR.
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Patent number: 10508549Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.Type: GrantFiled: June 2, 2015Date of Patent: December 17, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Wolfgang Balzer, Thomas J. Praisner, Atul Kohil, Mark F. Zelesky, Dominic J. Mongillo, Jr.
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Patent number: 10480323Abstract: A turbine blade for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates.Type: GrantFiled: January 12, 2016Date of Patent: November 19, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Wolfgang Balzer
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Patent number: 10480333Abstract: A blade for a gas powered turbine includes a platform having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a suction side mateface and by a pressure side mateface. A blade extends outward from the platform. The blade has a foil shaped cross section and a suction side of the blade faces the suction side mateface and a pressure side of the blade faces the pressure side mateface. A radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position.Type: GrantFiled: May 30, 2017Date of Patent: November 19, 2019Assignee: United Technologies CorporationInventors: Evan P. Molony, Carey Clum, Wolfgang Balzer
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Publication number: 20190309628Abstract: An airfoil array includes an endwall. A first airfoil and a second airfoil each extend radially from the endwall and have a first side and an opposite second side that extend along an axial chord between a leading edge and a trailing edge. A first profiled region protrudes from the endwall along the first side of the first airfoil. A second profiled region protrudes from the endwall along the leading edge of the second side of the second airfoil adjacent the leading edge of the second airfoil. A third profiled region recessed into the endwall approximately equidistant from the first side of the first airfoil and the second side of the second airfoil.Type: ApplicationFiled: April 5, 2018Publication date: October 10, 2019Inventor: Wolfgang Balzer
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Patent number: 10280756Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from a radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of maximum thickness to axial chord length is between 0.40 (Tmax/bx) and 0.65 (Tmax/bx).Type: GrantFiled: October 2, 2017Date of Patent: May 7, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Timothy Charles Nash, Wolfgang Balzer
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Publication number: 20190101001Abstract: A component for a gas turbine engine includes a platform that has a radially inner side and a radially outer side. A root portion extends from the radially inner side of the platform. An airfoil extends from a radially outer side of the platform. The airfoil includes a pressure side that extends between a leading edge and a trailing edge. A suction side extends between the leading edge and the trailing edge. A ratio of maximum thickness to axial chord length is between 0.40 (Tmax/bx) and 0.65 (Tmax/bx).Type: ApplicationFiled: October 2, 2017Publication date: April 4, 2019Inventors: Timothy Charles Nash, Wolfgang Balzer
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Publication number: 20180347381Abstract: A blade for a gas powered turbine includes a platform having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a suction side mateface and by a pressure side mateface. A blade extends outward from the platform. The blade has a foil shaped cross section and a suction side of the blade faces the suction side mateface and a pressure side of the blade faces the pressure side mateface. A radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position.Type: ApplicationFiled: May 30, 2017Publication date: December 6, 2018Inventors: Evan P. Molony, Carey Clum, Wolfgang Balzer
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Publication number: 20180340426Abstract: In one embodiment, a component for a gas turbine engine is provided. The component including: an airfoil having a tip portion; a tip shelf located in the tip portion; a first plurality of cooling openings located in an edge of the tip shelf that extends along at least a portion of a pressure side of the airfoil; and a second plurality of cooling openings located in an edge of the tip portion proximate to the tip shelf that extends along at least a portion of a pressure side of the tip portion.Type: ApplicationFiled: May 25, 2017Publication date: November 29, 2018Inventors: Dominic J. Mongillo, Wolfgang Balzer, Atul Kohli
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Publication number: 20170198586Abstract: A turbine blade for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates.Type: ApplicationFiled: January 12, 2016Publication date: July 13, 2017Inventor: Wolfgang Balzer
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Publication number: 20150354365Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.Type: ApplicationFiled: June 2, 2015Publication date: December 10, 2015Inventors: Wolfgang Balzer, Thomas J. Praisner, Atul Kohli, Mark F. Zelesky, Dominic J. Mongillo, JR.
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Patent number: 5865856Abstract: The oxidation hair dye composition is based on a combination of coupler substance and developer substance, and includes, as developer substance, at least one 2,5-diaminobenzonitrile compound of the formula (I), ##STR1## in which R.sup.1 and R.sup.2, independently of each other, are selected from the group consisting of H, alkyl groups having 1 to 6 carbon atoms, hydroxyalkyl groups having 2 to 4 carbon atoms and dihydroxyalkyl groups having 3 to 4 carbon atoms, with the proviso that both of the R.sup.1 and R.sup.2 groups are not both hydrogen at the same time, or a physiologically compatible water-soluble salt thereof. The invention also includes new 2,5-diaminobenzonitrile compounds of formula I.Type: GrantFiled: March 17, 1997Date of Patent: February 2, 1999Assignee: Wella AktiengesellschaftInventors: Helmut Keller, Wolfgang Balzer
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Patent number: 5865853Abstract: The composition for dyeing keratin fibers is mixed with water prior to use and contains from 35 to 75 percent by weight of at least one powdery vegetable dye material; from 25 to 65 percent by weight of at least one oil; and from 0.001 to 15 percent by weight of a physiologically unobjectionable nitro dye compound, azo dye compound, quinone dye compound and/or a triphenylmethane dye compound. A method of dyeing hair using this composition is also described.Type: GrantFiled: May 1, 1997Date of Patent: February 2, 1999Assignee: Wella AktiengesellschaftInventors: Manfred Schmitt, Uwe Lenz, Wolfgang Balzer, Henk Niessink
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Patent number: 4997451Abstract: Compositions for oxidative dyeing of hair based on 4-aminophenol derivatives of the formula (I): ##STR1## or their physiologically compatible water soluble salts, wherein R is selected from the group consisting of alkyl groups with from one to four carbon atoms, monohydroxyalkyl groups with from two to four carbon atoms, aminoalkyl groups with from two to four carbon atoms, aminoalkyl groups having amino groups substituted with from one to two alkyl groups having from one to four carbon atoms and dihydroxyalkyl groups with from three to four carbon atoms. New developer substances include 4-amino-2-propoxymethyl phenol, 4-amino-2-isopropoxymethyl phenol and 4-amino-2-(2'-hydroxyethoxymethyl)-phenol. The developer substances of the formula I have physiologically improved properties with equally good dyeing properties as the p-aminophenol used up to now in the red region of the spectrum.Type: GrantFiled: March 22, 1990Date of Patent: March 5, 1991Assignee: Wella AktiengesellschaftInventors: Thomas Clausen, Wolfgang Balzer, Anke Flohr