Patents by Inventor Clinton A. Mayer
Clinton A. Mayer 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: 11454126Abstract: Turbine components, such as blades, having a shank portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, Table 2, or Table 1 and Table 2. X and Y are distances in inches which, when connected by smooth continuing arcs, define shank portion profile section edges at each Z distance in inches. The shank portion profile section edges at the Z distances are joined smoothly with one another to form a complete shank shape.Type: GrantFiled: August 24, 2021Date of Patent: September 27, 2022Assignee: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.Inventors: Andres Jaramillo, Clinton Mayer, Jinwoo Song
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Patent number: 9938857Abstract: An insert for a component of a gas turbine is provided. The insert includes an insert portion and a retaining element such that the insert portion is retained by the retaining element so that movement of the insert portion relative to the retaining element is prevented. Additionally, a gas turbine component including the insert is provided as well as a method for inserting the insert into a gas turbine component.Type: GrantFiled: August 15, 2014Date of Patent: April 10, 2018Assignee: SIEMENS ENERGY, INC.Inventor: Clinton A. Mayer
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Patent number: 9829199Abstract: A flange (28A-C, 28E, 30A-E) with a primary contact surface (29B-C, 31B-D) that is curved (C) in a section plane (P) normal to a direction of the flange around a perimeter (60) of a component. The curve may have a maximum departure (D), from a straight line drawn between the ends (34, 35) of the curve, of at least 5% of a length of the straight line. The curve may be a circular arc with a span angle (A) of at least 40 degrees. The primary contact surface (29C, 31C) may be defined by an annular portion of a torus. Alternately, the primary contact surface (31D) may follow a non-circular perimeter path. A toric or other non-planar flange interface (32A-B) may be formed by mating contact surfaces on first (22, 36) and second (24, 38) components.Type: GrantFiled: October 30, 2014Date of Patent: November 28, 2017Assignee: SIEMENS ENERGY, INC.Inventor: Clinton A. Mayer
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Patent number: 9714611Abstract: A heat shield manifold system for an inner casing between a compressor and turbine assembly is disclosed. The heat shield manifold system protects the outer case from high temperature compressor discharge air, thereby enabling the outer case extending between a compressor and a turbine assembly to be formed from less expensive materials than otherwise would be required. In addition, the heat shield manifold system may be configured such that compressor bleed air is passed from the compressor into the heat shield manifold system without passing through a conventional flange to flange joint that is susceptible to leakage.Type: GrantFiled: February 15, 2013Date of Patent: July 25, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Clinton A. Mayer, Jesse Eng, Cheryl A. Schopf
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Patent number: 9702258Abstract: A gas turbine engine which has at least a combustor section and a turbine cylinder section, wherein the combustor section includes a transition piece coupled to a vane carrier assembly, wherein the vane carrier assembly includes a plurality of holes that correspond with one or more holes of the transition piece, and wherein at least one of the pluralities of holes is adapted to receive a pin-type member therein for shifting the transition piece toward an upstream or downstream end. A system and method for shifting a transition piece in a gas turbine engine includes at least moving a pin-type member from a first position to a second position, where the movement shifts the transition piece in a direction towards an upstream end or a downstream end.Type: GrantFiled: July 1, 2014Date of Patent: July 11, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Clinton A. Mayer, William M. Kieffer, Paul G. Hicks
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Patent number: 9593853Abstract: A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.Type: GrantFiled: February 20, 2014Date of Patent: March 14, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Matthew D. Montgomery, Richard C. Charron, Gary D. Snyder, William W. Pankey, Clinton A. Mayer, Benjamin G. Hettinger
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Patent number: 9404421Abstract: A structural support system is provided in a can annular gas turbine engine having an arrangement including a plurality of integrated exit pieces (IEPs) forming an annular chamber for delivering gases from a plurality of combustors to a first row of turbine blades. A bracket structure is connected between an IEP and an inner support structure on the engine. The bracket structure includes an axial bracket member attached to an IEP and extending axially in a forward direction. A transverse bracket member has an end attached to the inner support structure and extends circumferentially to a connection with a forward end of the axial bracket member. The transverse bracket member provides a fixed radial position for the forward end of the axial bracket member and is flexible in the axial direction to permit axial movement of the axial bracket member.Type: GrantFiled: January 23, 2014Date of Patent: August 2, 2016Assignee: SIEMENS ENERGY, INC.Inventors: Richard C. Charron, William W. Pankey, Clinton A. Mayer, Benjamin G Hettinger
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Publication number: 20160123231Abstract: A flange (28A-C, 28E, 30A-E) with a primary contact surface (29B-C, 31B-D) that is curved (C) in a section plane (P) normal to a direction of the flange around a perimeter (60) of a component. The curve may have a maximum departure (D), from a straight line drawn between the ends (34, 35) of the curve, of at least 5% of a length of the straight line. The curve may be a circular arc with a span angle (A) of at least 40 degrees. The primary contact surface (29C, 31C) may be defined by an annular portion of a torus. Alternately, the primary contact surface (31D) may follow a non-circular perimeter path. A toric or other non-planar flange interface (32A-B) may be formed by mating contact surfaces on first (22, 36) and second (24, 38) components.Type: ApplicationFiled: October 30, 2014Publication date: May 5, 2016Inventor: Clinton A. Mayer
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Publication number: 20160047276Abstract: An insert for a component of a gas turbine is provided. The insert includes an insert portion and a retaining element such that the insert portion is retained by the retaining element so that movement of the insert portion relative to the retaining element is prevented. Additionally, a gas turbine component including the insert is provided as well as a method for inserting the insert into a gas turbine component.Type: ApplicationFiled: August 15, 2014Publication date: February 18, 2016Inventor: Clinton A. Mayer
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Publication number: 20160003069Abstract: A gas turbine engine including an adjustable transition assembly is disclosed. The gas turbine engine includes at least a combustor section and a turbine cylinder section, wherein the combustor section includes a transition piece coupled to a vane carrier assembly. The vane carrier assembly includes a plurality of holes that correspond with one or more holes of the transition piece, wherein at least one of the plurality of holes is adapted to receive a transition adjustable means therein for shifting the transition piece toward an upstream or downstream end. Also provided is a method for shifting a transition piece in a gas turbine engine, the method including at least the step of moving a transition adjustable means from a first position to a second position, where the movement shifts the transition piece in a direction towards an upstream end or a downstream end.Type: ApplicationFiled: July 1, 2014Publication date: January 7, 2016Inventors: Clinton A. Mayer, William M. Kieffer, Paul G. Hicks
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Publication number: 20150233582Abstract: A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.Type: ApplicationFiled: February 20, 2014Publication date: August 20, 2015Applicant: SIEMENS ENERGY, INC.Inventors: Matthew D. Montgomery, Richard C. Charron, Gary D. Snyder, William W. Pankey, Clinton A. Mayer, Benjamin G. Hettinger
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Publication number: 20150204243Abstract: A structural support system is provided in a can annular gas turbine engine having an arrangement including a plurality of integrated exit pieces (IEPs) forming an annular chamber for delivering gases from a plurality of combustors to a first row of turbine blades. A bracket structure is connected between an IEP and an inner support structure on the engine. The bracket structure includes an axial bracket member attached to an IEP and extending axially in a forward direction. A transverse bracket member has an end attached to the inner support structure and extends circumferentially to a connection with a forward end of the axial bracket member. The transverse bracket member provides a fixed radial position for the forward end of the axial bracket member and is flexible in the axial direction to permit axial movement of the axial bracket member.Type: ApplicationFiled: January 23, 2014Publication date: July 23, 2015Inventors: Richard C. Charron, William W. Pankey, Clinton A. Mayer, Benjamin G. Hettinger
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Publication number: 20140230441Abstract: A heat shield manifold system for an inner casing between a compressor and turbine assembly is disclosed. The heat shield manifold system protects the outer case from high temperature compressor discharge air, thereby enabling the outer case extending between a compressor and a turbine assembly to be formed from less expensive materials than otherwise would be required. In addition, the heat shield manifold system may be configured such that compressor bleed air is passed from the compressor into the heat shield manifold system without passing through a conventional flange to flange joint that is susceptible to leakage.Type: ApplicationFiled: February 15, 2013Publication date: August 21, 2014Inventors: Clinton A. Mayer, Jesse Eng, Cheryl A. Schopf
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Patent number: 8790082Abstract: A gas turbine blade (10) including a hollow mid-span snubber (16). The snubber is affixed to the airfoil portion (14) of the blade by a fastener (20) passing through an opening (24) cast into the surface (22) of the blade. The opening is defined during an investment casting process by a ceramic pedestal (38) which is positioned between a ceramic core (32) and a surrounding ceramic casting shell (48). The pedestal provides mechanical support for the ceramic core during both wax and molten metal injection steps of the investment casting process.Type: GrantFiled: August 2, 2010Date of Patent: July 29, 2014Assignee: Siemens Energy, Inc.Inventors: Gary B. Merrill, Clinton Mayer
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Patent number: 8684692Abstract: A turbine blade assembly in a turbine engine. The turbine blade assembly includes a turbine blade and a first snubber structure. The turbine blade includes an internal cooling passage containing cooling air. The first snubber structure extends outwardly from a sidewall of the turbine blade and includes a hollow interior portion that receives cooling air from the internal cooling passage of the turbine blade.Type: GrantFiled: February 9, 2011Date of Patent: April 1, 2014Assignee: Siemens Energy, Inc.Inventors: Clinton A. Mayer, Christian X. Campbell, Andrew Whalley, John J. Marra
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Publication number: 20120027616Abstract: A gas turbine blade (10) including a hollow mid-span snubber (16). The snubber is affixed to the airfoil portion (14) of the blade by a fastener (20) passing through an opening (24) cast into the surface (22) of the blade. The opening is defined during an investment casting process by a ceramic pedestal (38) which is positioned between a ceramic core (32) and a surrounding ceramic casting shell (48). The pedestal provides mechanical support for the ceramic core during both wax and molten metal injection steps of the investment casting process.Type: ApplicationFiled: August 2, 2010Publication date: February 2, 2012Inventors: Gary B. Merrill, Clinton Mayer
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Publication number: 20110194943Abstract: A turbine blade assembly in a turbine engine. The turbine blade assembly includes a turbine blade and a first snubber structure. The turbine blade includes an internal cooling passage containing cooling air. The first snubber structure extends outwardly from a sidewall of the turbine blade and includes a hollow interior portion that receives cooling air from the internal cooling passage of the turbine blade.Type: ApplicationFiled: February 9, 2011Publication date: August 11, 2011Inventors: Clinton A. Mayer, Christian X. Campbell, Andrew Whalley, John J. Marra