Patents by Inventor Allister W. James
Allister W. James 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: 9726028Abstract: A vane assembly (10) having: an airfoil (12) and a shroud (14) held together without metallurgical bonding there between; a channel (22) disposed circumferentially about the airfoil (12), between the airfoil (12) and the shroud (14); and a seal (20) disposed in the channel (22), wherein during operation of a turbine engine having the vane assembly (10) the seal (20) has a sufficient ductility such that a force generated on the seal (20) resulting from relative movement of the airfoil (12) and the shroud (14) is sufficient to plastically deform the seal (20).Type: GrantFiled: June 29, 2011Date of Patent: August 8, 2017Assignee: SIEMENS ENERGY, INC.Inventors: John J. Marra, Brian J. Wessell, Allister W. James, Jan H. Marsh, Paul J. Gear
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Patent number: 9700941Abstract: A removed damaged portion of a fully consolidated turbine engine component is replaced with a powder coupon that includes powder particles that are at most partially sintered or are bonded together with a binder. A bonding agent is applied to the component and/or the powder coupon. The powder coupon is then positioned over the component and heat is applied to fully sinter the powder particles, thus causing the powder coupon to shrink onto the component. The heat also activates the bonding agent to bond the shrunken powder coupon to the component, but the heat does not sinter the material forming the fully consolidated component.Type: GrantFiled: October 3, 2012Date of Patent: July 11, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Allister W. James, Zafir A. M. Abdo, Ahmed Kamel
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Patent number: 9422828Abstract: A structural layer (30) may be bi-cast onto ligaments (62) extending from a porous cooling construction (20). The material of the structural layer may be optimized for high-temperature strength, while the material of the porous construction may be optimized for high thermal conductivity. A fugitive material (56) such as wax may be formed on the ligaments of the porous construction. A second fugitive material (58) such as ceramic may fill the remaining part of the porous construction. An investment casting shell (60) may be disposed around the porous construction and the fugitive materials. The first fugitive material may then be replaced with the material of the structural layer (30), and the second fugitive material may be removed to provide coolant paths (26). A second structural layer (52) may be bi-cast onto further ligaments (62) on a second side of the porous construction.Type: GrantFiled: August 4, 2014Date of Patent: August 23, 2016Inventors: Jay A. Morrison, Raymond G. Snider, Allister W. James
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Patent number: 9156086Abstract: Multi-component vane segment and method for forming the same. Assembly includes: positioning a pre-formed airfoil component (12) and a preformed shroud heat resistant material (18) in a mold, wherein the airfoil component (12) and the shroud heat resistant material (18) each comprises an interlocking feature (24); preheating the mold; introducing molten structural material (46) into the mold; and solidifying the molten structural material such that it interlocks the pre-formed airfoil component (12) with respect to the preformed shroud heat resistant material (18) and is effective to provide structural support for the shroud heat resistant material (18). Surfaces between the airfoil component (12) and the structural material (46), between the airfoil component (12) and the shroud heat resistant material (18), and between the shroud heat resistant material (18) and the structural material (46) are free of metallurgical bonds.Type: GrantFiled: June 7, 2010Date of Patent: October 13, 2015Assignee: Siemens Energy, Inc.Inventor: Allister W. James
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Patent number: 8940114Abstract: Fabricating a core of a component (34A, 34B, 34C) from a stack (25, 36) of sheets (20) of material with cutouts (22A) in the sheets aligned to form passages (38) in the core. A casing preform (28) is then fitted over the core. The preform is processed to form a casing (29) that brackets at least parts of opposed ends of the stack. Shrinkage of the casing during processing compresses (46) the sheets together. The preform may slide (52) over the core, and may be segmented (28A, 28B, 28C) to fit over the core. A hoop (66) may be fitted and compressed around the segmented casing (29A, 29B, 29C).Type: GrantFiled: April 27, 2011Date of Patent: January 27, 2015Assignees: Siemens Energy, Inc., Mikro Systems, Inc.Inventors: Allister W. James, Gary B. Merrill, Iain A. Fraser
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Patent number: 8914976Abstract: Bi-casting a platform (50) onto an end portion (42) of a turbine airfoil (31) after forming a coating of a fugitive material (56) on the end portion. After bi-casting the platform, the coating is dissolved and removed to relieve differential thermal shrinkage stress between the airfoil and platform. The thickness of the coating is varied around the end portion in proportion to varying amounts of local differential process shrinkage. The coating may be sprayed (76A, 76B) onto the end portion in opposite directions parallel to a chord line (41) of the airfoil or parallel to a mid-platform length (80) of the platform to form respective layers tapering in thickness from the leading (32) and trailing (34) edges along the suction side (36) of the airfoil.Type: GrantFiled: August 2, 2011Date of Patent: December 23, 2014Assignee: Siemens Energy, Inc.Inventors: Christian X. Campbell, Anand A. Kulkarni, Allister W. James, Brian J. Wessell, Paul J. Gear
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Publication number: 20140342175Abstract: A structural layer (30) may be bi-cast onto ligaments (62) extending from a porous cooling construction (20). The material of the structural layer may be optimized for high-temperature strength, while the material of the porous construction may be optimized for high thermal conductivity. A fugitive material (56) such as wax may be formed on the ligaments of the porous construction. A second fugitive material (58) such as ceramic may fill the remaining part of the porous construction. An investment casting shell (60) may be disposed around the porous construction and the fugitive materials. The first fugitive material may then be replaced with the material of the structural layer (30), and the second fugitive material may be removed to provide coolant paths (26). A second structural layer (52) may be bi-cast onto further ligaments (62) on a second side of the porous construction.Type: ApplicationFiled: August 4, 2014Publication date: November 20, 2014Inventors: Jay A. Morrison, Raymond G. Snider, Allister W. James
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Publication number: 20140294652Abstract: A method of making a combustion turbine component includes assembling a plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly and sintering the metallic greenbody assembly to thereby form the combustion turbine component. Each of the plurality of metallic combustion turbine subcomponent greenbodies may be formed by direct metal fabrication (DMF). In addition, each of plurality of metallic combustion turbine subcomponent greenbodies may include an activatable binder and the activatable binder may be activated prior to sintering.Type: ApplicationFiled: December 30, 2013Publication date: October 2, 2014Inventors: Jay A. Morrison, Jay E. Lane, Allister W. James, Michael Appleby, Iain Fraser, John Paulus
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Patent number: 8846206Abstract: An intermediate component includes a first wall member, a leachable material layer, and a precursor wall member. The first wall member has an outer surface and first connecting structure. The leachable material layer is provided on the first wall member outer surface. The precursor wall member is formed adjacent to the leachable material layer from a metal powder mixed with a binder material, and includes second connecting structure.Type: GrantFiled: July 31, 2008Date of Patent: September 30, 2014Assignee: Siemens Energy, Inc.Inventors: Allister W. James, Douglas J. Arrell
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Structure and method for forming detailed channels for thin walled components using thermal spraying
Patent number: 8815371Abstract: A coated substrate with a subsurface cooling channel having no corner disposed proximate a seam between the substrate and the coating. A method for forming such a structure, including forming a groove in a surface of a substrate, forming a preform having a cooperating portion and a protruding portion, inserting the cooperating portion of the preform into the groove, leaving the protruding portion of the preform protruding beyond the surface of the substrate, applying a layer of a coating material to the surface of the substrate and the protruding portion of the perform, and removing the preform, thereby creating a cooling channel.Type: GrantFiled: April 8, 2009Date of Patent: August 26, 2014Assignee: Siemens Energy, Inc.Inventors: Douglas J. Arrell, Allister W. James, Anand A. Kulkarni -
Patent number: 8793871Abstract: A structural layer (30) may be bi-cast onto ligaments (62) extending from a porous cooling construction (20). The material of the structural layer may be optimized for high-temperature strength, while the material of the porous construction may be optimized for high thermal conductivity. A fugitive material (56) such as wax may be formed on the ligaments of the porous construction. A second fugitive material (58) such as ceramic may fill the remaining part of the porous construction. An investment casting shell (60) may be disposed around the porous construction and the fugitive materials. The first fugitive material may then be replaced with the material of the structural layer (30), and the second fugitive material may be removed to provide coolant paths (26). A second structural layer (52) may be bi-cast onto further ligaments (62) on a second side of the porous construction.Type: GrantFiled: March 17, 2011Date of Patent: August 5, 2014Assignee: Siemens Energy, Inc.Inventors: Jay A. Morrison, Raymond G. Snider, Allister W. James
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Patent number: 8770930Abstract: A modular airfoil assembly (200) and related method for interlocking components of an airfoil structure (210) including a platform (220), an airfoil (210) having a shoulder (230) and a stem (232) extending outward from the shoulder. A ring element (100) positioned against the stem (232) secures the shoulder (230) against the platform (210). First and second members (100a, 100b) of the ring element (100) are bonded together with a portion (128j) of a surface (112a) of the second member (100b) extending within and bonded to a portion (128i) of a surface (112b) of the first member (100a).Type: GrantFiled: February 9, 2011Date of Patent: July 8, 2014Assignees: Siemens Energy, Inc., Mikro Systems, Inc.Inventors: Gary B. Merrill, Allister W. James, Iain A. Fraser
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Patent number: 8714920Abstract: A turbine airfoil (31) with an end portion (42) that tapers (44) toward the end (43) of the airfoil. A ridge (46) extends around the end portion. It has proximal (66) and distal (67) sides. A shroud platform (50) is bi-cast onto the end portion around the ridge without bonding. Cooling shrinks the platform into compression (62) on the end portion (42) of the airfoil. Gaps between the airfoil and platform are formed using a fugitive material (56) in the bi-casting stage. These gaps are designed in combination with the taper angle (44) to accommodate differential thermal expansion while maintaining a gas seal along the contact surfaces. The taper angle (44) may vary from lesser on the pressure side (36) to greater on the suction side (38) of the airfoil. A collar portion (52) of the platform provides sufficient contact area for connection stability.Type: GrantFiled: April 1, 2010Date of Patent: May 6, 2014Assignee: Siemens Energy, Inc.Inventors: Christian X. Campbell, Jay A. Morrison, Allister W. James, Raymond G. Snider, Daniel M. Eshak, John J. Marra, Brian J. Wessell
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Publication number: 20140093415Abstract: A removed damaged portion of a fully consolidated turbine engine component is replaced with a powder coupon that includes powder particles that are at most partially sintered or are bonded together with a binder. A bonding agent is applied to the component and/or the powder coupon. The powder coupon is then positioned over the component and heat is applied to fully sinter the powder particles, thus causing the powder coupon to shrink onto the component. The heat also activates the bonding agent to bond the shrunken powder coupon to the component, but the heat does not sinter the material forming the fully consolidated component.Type: ApplicationFiled: October 3, 2012Publication date: April 3, 2014Applicant: SIEMENS ENERGY, INC.Inventors: Allister W. James, Zafir A. M. Abdo, Ahmed Kamel
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Patent number: 8618440Abstract: A method for welding to a superalloy material without causing cracking of the material. The method includes the steps of depositing a weld strip (18) of a weldable material onto a superalloy substrate material (12) using a spray deposition process (20) and then forming a weldment (26) to the weld strip. None or a controlled amount of the substrate material (12) is melted during the weld in order to maintain the concentration of strengthening elements in the local melt within a zone of weldability. The spray deposition process may be a thermal process such as HVOF or a cold spray process. A groove (16) may be formed in a surface (10) of the superalloy substrate material to receive the weld strip. A diffusion heat treatment step may be used to improve adhesion between the weld strip and the superalloy material.Type: GrantFiled: January 4, 2007Date of Patent: December 31, 2013Assignee: Siemens Energy, Inc.Inventors: David B. Allen, Allister W. James, David W. Hunt
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Patent number: 8500411Abstract: A turbine airfoil usable in a turbine engine and including a depth indicator for determining outer wall blade thickness. The airfoil may include an outer wall having a plurality of grooves in the outer surface of the outer wall. The grooves may have a depth that represents a desired outer surface and wall thickness of the outer wall. The material forming an outer surface of the outer wall may be removed to be flush with an innermost point in each groove, thereby reducing the wall thickness and increasing efficiency. The plurality of grooves may be positioned in a radially outer region of the airfoil proximate to the tip.Type: GrantFiled: June 7, 2010Date of Patent: August 6, 2013Assignee: Siemens Energy, Inc.Inventors: John J. Marra, Allister W. James, Gary B. Merrill
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Patent number: 8439647Abstract: A turbine airfoil (20) fabricated as an assembly of U-channels (22A-E), each U-channel having a closed side formed by a cross wall (25), an open side (26) opposite the cross wall, and two side walls (27) extending from the cross wall to the open side. The U-channels are attached to each other in a parallel, closed-side to open-side sequence, forming a series of cooling channels (23) oriented span-wise (S) in the airfoil. A first of the U-channels (22A) has a curved cross wall forming the leading edge (24) of the airfoil. A last of the U-channels (22E) may have side walls (27) that converge to form a trailing edge (28) of the airfoil. Alternately, a solid trailing edge (22E?) may be attached to a last of the U-channels. Each U-channel may be bonded to an adjacent U-channel using half-lap joints (30).Type: GrantFiled: September 8, 2009Date of Patent: May 14, 2013Assignee: Siemens Energy, Inc.Inventor: Allister W. James
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Publication number: 20130004294Abstract: A vane assembly (10) having: an airfoil (12) and a shroud (14) held together without metallurgical bonding there between; a channel (22) disposed circumferentially about the airfoil (12), between the airfoil (12) and the shroud (14); and a seal (20) disposed in the channel (22), wherein during operation of a turbine engine having the vane assembly (10) the seal (20) has a sufficient ductility such that a force generated on the seal (20) resulting from relative movement of the airfoil (12) and the shroud (14) is sufficient to plastically deform the seal (20).Type: ApplicationFiled: June 29, 2011Publication date: January 3, 2013Inventors: John J. Marra, Brian J. Wessell, Allister W. James, Jan H. Marsh, Paul J. Gear
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Publication number: 20120276361Abstract: Fabricating a core of a component (34A, 34B, 34C) from a stack (25, 36) of sheets (20) of material with cutouts (22A) in the sheets aligned to form passages (38) in the core. A casing preform (28) is then fitted over the core. The preform is processed to form a casing (29) that brackets at least parts of opposed ends of the stack. Shrinkage of the casing during processing compresses (46) the sheets together. The preform may slide (52) over the core, and may be segmented (28A, 28B, 28C) to fit over the core. A hoop (66) may be fitted and compressed around the segmented casing (29A, 29B, 29C).Type: ApplicationFiled: April 27, 2011Publication date: November 1, 2012Inventors: Allister W. James, Gary B. Merrill, Iain A. Fraser
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Publication number: 20120237786Abstract: A structural layer (30) may be bi-cast onto ligaments (62) extending from a porous cooling construction (20). The material of the structural layer may be optimized for high-temperature strength, while the material of the porous construction may be optimized for high thermal conductivity. A fugitive material (56) such as wax may be formed on the ligaments of the porous construction. A second fugitive material (58) such as ceramic may fill the remaining part of the porous construction. An investment casting shell (60) may be disposed around the porous construction and the fugitive materials. The first fugitive material may then be replaced with the material of the structural layer (30), and the second fugitive material may be removed to provide coolant paths (26). A second structural layer (52) may be bi-cast onto further ligaments (62) on a second side of the porous construction.Type: ApplicationFiled: March 17, 2011Publication date: September 20, 2012Inventors: Jay A. Morrison, Raymond G. Snider, Allister W. James