Patents by Inventor J. Page Strohl
J. Page Strohl 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: 9322089Abstract: A nickel-based alloy suitable for casting gas turbine components having a lower density and basic heat treating process while achieving improved strength is disclosed. Multiple embodiments of the alloy are disclosed capable of providing both directionally-solidified and equiaxed castings. Also disclosed is a method of making a cast and heat treated article utilizing the improved nickel-base alloy.Type: GrantFiled: July 25, 2006Date of Patent: April 26, 2016Assignee: Alstom Technology LtdInventors: Charles Biondo, J. Page Strohl, Jeffery W. Samuelson, Gerhard E. Fuchs, Stanley T. Wlodek, Ramona T. Wlodek
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Patent number: 8057188Abstract: A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.Type: GrantFiled: July 18, 2008Date of Patent: November 15, 2011Assignee: Alstom Technologies Ltd. LLCInventors: David Parker, J. Page Strohl, Richard Ramirez, Robert Moore
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Patent number: 7958735Abstract: A turbine static structure having reduced leakage air is disclosed. A static structure turbine support ring having few segments is disclosed in which the segments have improved thermal expansion capability with reduced air leakage. A plurality of radially extending slots are placed in the segments to reduce stiffness. In order to minimize air leakage through the support ring, generally circumferential slots are placed in the ring and connect with the generally radially extending slots. Positioned in each of the generally radially extending slots and generally circumferential slots, and in contact with each other, are two sheet metal plates. The plates are staked to the support ring structure so as to provide a seal member, yet compensate for thermal growth.Type: GrantFiled: December 21, 2006Date of Patent: June 14, 2011Assignee: Power Systems Manufacturing, LLCInventors: Charlie Ellis, J. Page Strohl, Matt Thomas
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Publication number: 20100080729Abstract: A nickel-based alloy suitable for casting gas turbine components having a lower density and basic heat treating process while achieving improved strength is disclosed. Multiple embodiments of the alloy are disclosed capable of providing both directionally-solidified and equiaxed castings. Also disclosed is a method of making a cast and heat treated article utilizing the improved nickel-base alloy.Type: ApplicationFiled: July 25, 2006Publication date: April 1, 2010Applicant: Power Systems Manufacturing, LLCInventors: Charles Biondo, J. Page Strohl, Jeffery W. Samuelson, Gerhard E. Fuchs, Stanley T. Wlodek, Ramona T. Wlodek
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Publication number: 20090290987Abstract: A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased thickness over a portion of the airfoil span in order to increase stiffness. Furthermore, the airfoil has been restacked so as to induce a compressive stress in the blade root/attachment area. The increased stiffness and restacked airfoil combine to improve high-cycle fatigue capability of the compressor component.Type: ApplicationFiled: July 18, 2008Publication date: November 26, 2009Applicant: ALSTOM TECHNOLOGIES, LTD., LLCInventors: DAVID PARKER, J. PAGE STROHL, RICHARD RAMIREZ, ROBERT MOORE
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Patent number: 7618234Abstract: Embodiments for a compressor stator vane assembly in a gas turbine engine are disclosed. In an embodiment of the present invention a stator vane assembly is provided having a plurality of vanes each with an attachment and channels machined into the forward and aft walls of the attachment. A forward hook ring segment is pressfit into the channel in the forward wall of the attachment and an aft hook ring is pressfit into the channel in the aft wall of the attachment. The hook ring segments join a plurality of vanes together so as to provide a uniform engagement of mounting slots in the compressor case. Such an arrangement increases the contact area between the hook rings and the compressor case such that damping of individual vane vibrations are improved and operating stresses are reduced.Type: GrantFiled: February 14, 2007Date of Patent: November 17, 2009Assignee: Power System Manufacturing, LLCInventors: James G. Brackett, Charles Ellis, Michael Davis McGhee, J. Page Strohl
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Publication number: 20090148298Abstract: An apparatus and method are disclosed for reducing the operating stresses in a disk of a gas turbine engine while providing a seal plate to minimize leakage of a cooling fluid from the blades positioned in the disk. The seal plate is fastened to a tang of one or more of the blades. The seal plate configuration can be utilized with a newly manufactured disk and blades or with a modification to an existing disk and blades. The disk, blade, and seal plate configuration reduce operating stresses in the disk that are caused by mechanical loading on the disk by one or more rotating blades.Type: ApplicationFiled: December 9, 2008Publication date: June 11, 2009Applicant: ALSTOM TECHNOLOGIES, LTD. LLCInventors: J. Page Strohl, Anthony Petett, Robert J. Kraft
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Publication number: 20080193290Abstract: Embodiments for a compressor stator vane assembly in a gas turbine engine are disclosed. In an embodiment of the present invention a stator vane assembly is provided having a plurality of vanes each with an attachment and channels machined into the forward and aft walls of the attachment. A forward hook ring segment is pressfit into the channel in the forward wall of the attachment and an aft hook ring is pressfit into the channel in the aft wall of the attachment. The hook ring segments join a plurality of vanes together so as to provide a uniform engagement of mounting slots in the compressor case. Such an arrangement increases the contact area between the hook rings and the compressor case such that damping of individual vane vibrations are improved and operating stresses are reduced.Type: ApplicationFiled: February 14, 2007Publication date: August 14, 2008Applicant: Power Systems Manufacturing, LLCInventors: James G. Brackett, Charles Ellis, Michael Davis McGhee, J. Page Strohl
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Publication number: 20080148737Abstract: A turbine static structure having reduced leakage air is disclosed. A static structure turbine support ring having few segments is disclosed in which the segments have improved thermal expansion capability with reduced air leakage. A plurality of radially extending slots are placed in the segments to reduce stiffness. In order to minimize air leakage through the support ring, generally circumferential slots are placed in the ring and connect with the generally radially extending slots. Positioned in each of the generally radially extending slots and generally circumferential slots, and in contact with each other, are two sheet metal plates. The plates are staked to the support ring structure so as to provide a seal member, yet compensate for thermal growth.Type: ApplicationFiled: December 21, 2006Publication date: June 26, 2008Applicant: Power Systems Manufacturing, LLCInventors: Charlie Ellis, J. Page Strohl, Matt Thomas
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Patent number: 7293957Abstract: A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing its resistance to thermal deflection. This is accomplished by placing an opening along the innermost vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.Type: GrantFiled: March 28, 2007Date of Patent: November 13, 2007Assignee: Power Systems Mfg., LLCInventors: Charlie Ellis, David Parker, J. Page Strohl, David Medrano
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Patent number: 7229245Abstract: A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing their resistance to thermal deflection. This is accomplished by placing an opening along the vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.Type: GrantFiled: July 14, 2004Date of Patent: June 12, 2007Assignee: Power Systems Mfg., LLCInventors: Charles A. Ellis, David Parker, J. Page Strohl, David Medrano
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Patent number: 7101150Abstract: A vane assembly for a gas turbine is described wherein the vane assembly comprises a first vane and a second vane connected together by a plurality of flanges, at least one fastener, and at least one spring plate. The fastener and hole diameters in the respective flanges are sized such that the first vane and second vane are essentially pinned together along their inner flanges and allowed to adjust due to thermal growth along their outer flanges, while maintaining a constant seal along both inner and outer platform edges. The thermal growth along the outer flanges is made possible by oversized flange holes relative to the diameter of the fastener.Type: GrantFiled: May 11, 2004Date of Patent: September 5, 2006Assignee: Power Systems MFG, LLCInventors: Gary Bash, J. Page Strohl
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Publication number: 20060013685Abstract: A vane assembly for a gas turbine engine is disclosed having lower thermally induced stresses resulting in improved component durability. The stresses in the vane assembly airfoils are lowered by increasing the flexibility of the vane platform and reducing their resistance to thermal deflection. This is accomplished by placing an opening along the vane assembly rail that reduces the effective stiffness of the platform, thereby lowering the operating stresses in the airfoils of the vane assembly. A removable seal is then placed in the opening in order to prevent undesired leakages, while maintaining the benefit of the increased platform flexibility.Type: ApplicationFiled: July 14, 2004Publication date: January 19, 2006Inventors: Charles Ellis, David Parker, J. Page Strohl, David Medrano
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Patent number: 6932577Abstract: A turbine blade including an airfoil having a profile in accordance with Table 1 is disclosed. The turbine blade has a plurality of cooling passages extending radially outward through the airfoil. The aerodynamic profile of the airfoil has been reconfigured to reduce airfoil stress for a given operating temperature, thereby resulting in increased creep rupture life of the airfoil.Type: GrantFiled: November 21, 2003Date of Patent: August 23, 2005Assignee: Power Systems Mfg., LLCInventors: J. Page Strohl, David G. Parker, Michael Barrett
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Patent number: 6769878Abstract: A turbine blade including an airfoil having a profile in accordance with Table 1 is disclosed. The turbine blade has a plurality of cooling passages extending radially outward through the airfoil. The aerodynamic profile of the airfoil has been reconfigured to further reduce overall heat load to the airfoil while paying particular attention to the leading edge region. Specifically, the airfoil leading edge, which is the life-limiting location of the turbine blade has been reconfigured to lower heat load and allow for increased cooling, thereby increasing turbine blade life.Type: GrantFiled: May 9, 2003Date of Patent: August 3, 2004Assignee: Power Systems Mfg. LLCInventors: David G. Parker, Jeffrey S. Taylor, Christopher Johnston, J. Page Strohl
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Patent number: 6761536Abstract: A gas turbine blade having an airfoil to platform interface configured to minimize thermal and vibratory stresses is disclosed. This configuration minimizes exposure to the conditions that are known to cause high cycle fatigue and low cycle fatigue cracks. The turbine blade incorporates a channel in the platform trailing edge that extends from the platform concave face to the platform convex face and has a portion having a constant radius. The channel extends a sufficient distance into a stress field created by the aerodynamic loading of the turbine blade airfoil in order to redirect the mechanical stresses away from the blade trailing edge while allowing the platform trailing edge region to be more responsive to thermal fluctuations.Type: GrantFiled: January 31, 2003Date of Patent: July 13, 2004Assignee: Power Systems Mfg, LLCInventors: Gary Bash, J. Page Strohl