Patents by Inventor Jason Douglas Herzlinger
Jason Douglas Herzlinger 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: 10247007Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: May 2, 2017Date of Patent: April 2, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Neil Ristau, Mehmet Suleyman Ciray, Jason Douglas Herzlinger
-
Publication number: 20180320527Abstract: A turbine rotor blade is provided including an airfoil having an airfoil shape. The airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: ApplicationFiled: May 2, 2017Publication date: November 8, 2018Inventors: Neil Ristau, Mehmet Suleyman Ciray, Jason Douglas Herzlinger
-
Patent number: 9797258Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular profile for a turn of a cooling passage in an airfoil. By blending aspects of baseline and bulb contours into a blended turn with a non-uniform profile, mechanical and/or thermal stress can be reduced in the turn and in an airfoil including the turn, particularly on an outflow side of the turn. Stresses on the airfoil can be reduced using a turn profile that is a blend of a baseline profile and a bulb profile and that can be described by the airfoil core profile.Type: GrantFiled: October 23, 2013Date of Patent: October 24, 2017Assignee: GENERAL ELECTRIC COMPANYInventors: Jason Douglas Herzlinger, Harish Bommanakatte, Anthony Louis Giglio
-
Patent number: 9765630Abstract: A rotor blade including an airfoil portion and a root portion, and an internal cooling circuit having flow passages in the root portion and the airfoil portion, wherein the internal cooling circuit includes: a first flow passage; and a non-integral plug. The plug may include a plug channel configured to correspond to a desired level of coolant flow through the first cooling passage. The plug may be connected to the rotor blade in a fixed blocking position relative to the first flow passage.Type: GrantFiled: January 9, 2013Date of Patent: September 19, 2017Assignee: General Electric CompanyInventors: Jason Douglas Herzlinger, Bradley Taylor Boyer, Harish Bommanakatte, Anthony Louis Giglio
-
Patent number: 9670784Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: a base including: a casing having at least one exhaust aperture on an outer surface of the casing; and a core within the casing, the core having: a serpentine cooling passage; and at least one outlet passage fluidly connected with the serpentine cooling passage and the exhaust aperture, wherein the at least one outlet passage permits flow of a coolant from the serpentine cooling passage to the at least one exhaust aperture on the outer surface of the casing; and an airfoil connected with the base at a first end of the airfoil, the airfoil including: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side.Type: GrantFiled: October 23, 2013Date of Patent: June 6, 2017Assignee: General Electric CompanyInventors: Jason Douglas Herzlinger, Harish Bommanakatte, Anthony Louis Giglio, Jacob Charles Perry, II
-
Patent number: 9551226Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using an airfoil profile and/or an endwall contour including at least one of a pressure side bump, a pressure side leading edge bump, or a suction side trough. In particular, by including two endwall bumps on the pressure side and a trough on the suction side combined with a particular airfoil profile, performance can be further improved.Type: GrantFiled: October 23, 2013Date of Patent: January 24, 2017Assignee: General Electric CompanyInventors: Paul Kendall Smith, Harish Bommanakatte, Anthony Louis Giglio, Jason Douglas Herzlinger, Jacob Charles Perry, II, Alexander Stein
-
Patent number: 9528379Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: a base; and an airfoil connected with the base at a first end of the airfoil, the airfoil including: a casing having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, the casing including an aperture on the leading edge; and a core within the casing, the core having a serpentine shape for supporting the casing and a leading edge passage fluidly connected with the aperture on the leading edge of the casing.Type: GrantFiled: October 23, 2013Date of Patent: December 27, 2016Assignee: General Electric CompanyInventors: Jason Douglas Herzlinger, Harish Bommanakatte, Anthony Louis Giglio, Jacob Charles Perry, II
-
Patent number: 9376922Abstract: An interior cooling configuration formed within an airfoil of a blade of a combustion turbine engine is provided. The interior cooling configuration may include a first flow passage and a second flow passage that have a side-by-side configuration for a segment, and multiple lateral crossover passages extending between and fluidly connecting the first flow passage to the second flow passage. The crossover passages may be staggered.Type: GrantFiled: January 9, 2013Date of Patent: June 28, 2016Assignee: General Electric CompanyInventors: Harish Bommanakatte, Jalindar Appa Walunj, Anthony Louis Giglio, Jason Douglas Herzlinger
-
Publication number: 20150204237Abstract: A turbine blade comprises a cooling passage defined between a pressure side wall and a suction side wall. A pin is disposed within the cooling passage and includes a first end that is connected to the pressure side wall and a second end that is connected to the suction side wall. A radially oriented fillet having a maximum radius of curvature value is disposed along a periphery of at least one of the first end or the second end within a region of peak steady state stress. An axially oriented fillet having a maximum radius of curvature value is disposed along a periphery of at least one of the first end or second end within a region of peak vibratory stress. The maximum radius of curvature value of the axially oriented fillet is greater than the maximum radius of curvature value of the radially oriented fillet.Type: ApplicationFiled: January 17, 2014Publication date: July 23, 2015Applicant: General Electric CompanyInventors: William Scott Zemitis, Ariel Caesar Prepena Jacala, Jason Douglas Herzlinger
-
Publication number: 20150110641Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets.Type: ApplicationFiled: October 23, 2013Publication date: April 23, 2015Applicant: General Electric CompanyInventors: Jason Douglas Herzlinger, Harish Bommanakatte, Anthony Louis Giglio, Jacob Charles Perry, II
-
Publication number: 20150110640Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: a base; and an airfoil connected with the base at a first end of the airfoil, the airfoil including: a casing having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, the casing including an aperture on the leading edge; and a core within the casing, the core having a serpentine shape for supporting the casing and a leading edge passage fluidly connected with the aperture on the leading edge of the casing.Type: ApplicationFiled: October 23, 2013Publication date: April 23, 2015Applicant: General Electric CompanyInventors: Jason Douglas Herzlinger, Harish Bommanakatte, Anthony Louis Giglio, Jacob Charles Perry, II
-
Publication number: 20150107265Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using an airfoil profile and/or an endwall contour including at least one of a pressure side bump, a pressure side leading edge bump, or a suction side trough. In particular, by including two endwall bumps on the pressure side and a trough on the suction side combined with a particular airfoil profile, performance can be further improved.Type: ApplicationFiled: October 23, 2013Publication date: April 23, 2015Applicant: General Electric CompanyInventors: Paul Kendall Smith, Harish Bommanakatte, Anthony Louis Giglio, Jason Douglas Herzlinger, Jacob Charles Perry, Alexander Stein
-
Publication number: 20150110639Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular profile for a turn of a cooling passage in an airfoil. By blending aspects of baseline and bulb contours into a blended turn with a non-uniform profile, mechanical and/or thermal stress can be reduced in the turn and in an airfoil including the turn, particularly on an outflow side of the turn. Stresses on the airfoil can be reduced using a turn profile that is a blend of a baseline profile and a bulb profile and that can be described by the airfoil core profile.Type: ApplicationFiled: October 23, 2013Publication date: April 23, 2015Applicant: General Electric CompanyInventors: Jason Douglas Herzlinger, Harish Bommanakatte, Anthony Louis Giglio
-
Patent number: 8790086Abstract: A turbine has blade assemblies disposed about a rotor. Each of the blade assemblies have an airfoil and a bucket. Pockets are defined at trailing and leading sides of the bucket, with damper pin slots at an ends thereof. The damper pin slot at the trailing side has a depth sufficient for fully receiving a damper pin. The damper pin slot at the trailing side of a first adjacent blade assembly is positioned relative to the damper pin slot at the leading side of a second adjacent blade assembly to allow the damper pin to move. At each side of the pocket at the trailing side is a seal pin slot with seal pins therein. The seal pin slots extend beyond a line that is aligned with an inner edge of the damper pin slot at the trailing side, wherein the seal pins overlap the damper pin.Type: GrantFiled: November 11, 2010Date of Patent: July 29, 2014Assignee: General Electric CompanyInventors: Mark Steven Honkomp, Matthew Durham Collier, Jason Douglas Herzlinger
-
Publication number: 20140193273Abstract: An interior cooling configuration formed within an airfoil of a blade of a combustion turbine engine is provided. The interior cooling configuration may include a first flow passage and a second flow passage that have a side-by-side configuration for a segment, and multiple lateral crossover passages extending between and fluidly connecting the first flow passage to the second flow passage. The crossover passages may be staggered.Type: ApplicationFiled: January 9, 2013Publication date: July 10, 2014Applicant: General Electric CompanyInventors: Harrish Bommanakatte, Jalindar Appa Walunj, Anthony Louis Giglio, Jason Douglas Herzlinger
-
Patent number: 8714930Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: September 12, 2011Date of Patent: May 6, 2014Assignee: General Electric CompanyInventors: Jason Douglas Herzlinger, Craig Allen Bielek, Jonathan Glenn Reed, Holly Renae Davis, Luis Manuel Herrera, Ariel Caesar Prepena Jacala, William Scott Zemitis
-
Publication number: 20130064671Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: ApplicationFiled: September 12, 2011Publication date: March 14, 2013Inventors: Jason Douglas Herzlinger, Craig Allen Bielek, Jonathan Glenn Reed, Holly Renae Davis, Luis Manuel Herrera, Ariel Caesar Prepena Jacala, William Scott Zemitis
-
Publication number: 20120121423Abstract: A turbine has blade assemblies disposed about a rotor. Each of the blade assemblies have an airfoil and a bucket. Pockets are defined at trailing and leading sides of the bucket, with damper pin slots at an ends thereof. The damper pin slot at the trailing side has a depth sufficient for fully receiving a damper pin. The damper pin slot at the trailing side of a first adjacent blade assembly is positioned relative to the damper pin slot at the leading side of a second adjacent blade assembly to allow the damper pin to move. At each side of the pocket at the trailing side is a seal pin slot with seal pins therein. The seal pin slots extend beyond a line that is aligned with an inner edge of the damper pin slot at the trailing side, wherein the seal pins overlap the damper pin.Type: ApplicationFiled: November 11, 2010Publication date: May 17, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Mark Steven Honkomp, Matthew Durham Collier, Jason Douglas Herzlinger