-
公开(公告)号：US07484928B2
公开(公告)日：2009-02-03
申请号：US11723739
申请日：2007-03-21
Applicant: Brian Peter Arness , Graham David Sherlock , Joseph Leonard Moroso , Stewart William Beitz , Graydon Wayne Peters
Inventor： Brian Peter Arness , Graham David Sherlock , Joseph Leonard Moroso , Stewart William Beitz , Graydon Wayne Peters
IPC: F01D9/02
CPC classification number: B23P6/005 , B23K9/0026 , B23K2101/001 , F01D5/005 , F05D2230/232 , F05D2260/202 , Y02T50/673 , Y02T50/676 , Y10T29/49318 , Y10T29/4973
Abstract: A trailing edge coupon for the trailing edge of a airfoil of a turbine nozzle segment is welded to an airfoil section of the nozzle segment having a damaged trailing edge portion removed. The coupon includes film cooling holes spaced one from the other along a pressure side wall portion of the coupon and a plurality of radially spaced openings along the trailing edge. By welding the pressure and suction side edges of the coupon to the pressure and side edges of the remaining portion of the airfoil, the operating life of the nozzle is extended.
Abstract translation: 用于涡轮喷嘴段的翼型的后缘的后缘试样焊接到具有损坏的后缘部分的去除的喷嘴段的翼型部分。 优惠券包括沿着优惠券的压力侧壁部分彼此间隔开的薄膜冷却孔和沿着后缘的多个径向隔开的开口。 通过将试样的压力和吸力侧边缘焊接到机翼的剩余部分的压力和侧边缘，喷嘴的使用寿命延长。
-
公开(公告)号：US20080166229A1
公开(公告)日：2008-07-10
申请号：US11621152
申请日：2007-01-09
Applicant: Graham David Sherlock , Christopher Edward Thompson
Inventor： Graham David Sherlock , Christopher Edward Thompson
CPC classification number: G01B5/25 , F01D9/044 , F01D25/285 , F05D2230/64
Abstract: A method for fabricating a nozzle segment for use within a turbine nozzle assembly. The method comprises providing a nozzle segment including an outer band, an inner band, and at least one vane extending there between, wherein at least one of the inner band and the outer band is formed with a transition piece groove defined therein, positioning an inspection tool in contact with the nozzle assembly such that the inspection tool is aligned relative to the nozzle segment using at least one datum, and verifying an alignment of each transition piece groove using the inspection tool.
Abstract translation: 一种用于制造在涡轮喷嘴组件内使用的喷嘴段的方法。 该方法包括提供包括外带，内带和在其间延伸的至少一个叶片的喷嘴段，其中内带和外带中的至少一个形成有限定在其中的过渡件槽，定位检查 与喷嘴组件接触的工具，使得检查工具使用至少一个基准相对于喷嘴段对准，并使用检查工具验证每个过渡件槽的对准。
-
公开(公告)号：US08671585B2
公开(公告)日：2014-03-18
申请号：US13270521
申请日：2011-10-11
Applicant: Graham David Sherlock , Christopher Edward Thompson
Inventor： Graham David Sherlock , Christopher Edward Thompson
CPC classification number: G01B5/25 , F01D9/044 , F01D25/285 , F05D2230/64
Abstract: A method for fabricating a nozzle segment for use within a turbine nozzle assembly. The method comprises providing a nozzle segment including an outer band, an inner band, and at least one vane extending there between, wherein at least one of the inner band and the outer band is formed with a transition piece groove defined therein, positioning an inspection tool in contact with the nozzle assembly such that the inspection tool is aligned relative to the nozzle segment using at least one datum, and verifying an alignment of each transition piece groove using the inspection tool.
Abstract translation: 一种用于制造在涡轮喷嘴组件内使用的喷嘴段的方法。 该方法包括提供包括外带，内带和在其间延伸的至少一个叶片的喷嘴段，其中内带和外带中的至少一个形成有限定在其中的过渡件槽，定位检查 与喷嘴组件接触的工具，使得检查工具使用至少一个基准相对于喷嘴段对准，并使用检查工具验证每个过渡件槽的对准。
-
Patent Agency Ranking
公开(公告)号：US07862264B2
公开(公告)日：2011-01-04
申请号：US11679505
申请日：2007-02-27
Applicant: Graham David Sherlock , Lynn Charles Gagne , Larry Paul Wencil
Inventor： Graham David Sherlock , Lynn Charles Gagne , Larry Paul Wencil
CPC classification number: B23B47/28 , B21J15/10 , B23B2215/81 , B23B2247/12 , Y10T408/03 , Y10T408/563 , Y10T408/567
Abstract: A method for forming an opening in two different turbine components is provided. The method includes coupling a clamp to a base and coupling the clamp to a clamp bar, wherein the clamp bar is moveable with respect to the base. A first bushing plate is selected based on a first turbine component being drilled and is removably coupled to the base. A bushing is removably coupled to at least one aperture extending through the first bushing plate. An opening is formed in the first turbine component. A second bushing plate is selected based on a second turbine component being drilled. The second turbine component is different from the first turbine component. The second bushing plate is removably coupled to the base. An opening is formed in the second turbine component.
Abstract translation: 提供了一种用于在两个不同涡轮机部件中形成开口的方法。 该方法包括将夹具连接到基座并将夹具连接到夹紧杆，其中夹紧杆可相对于基座移动。 基于正在钻孔的第一涡轮机部件选择第一衬套板，并且可拆卸地联接到基座。 衬套可移除地联接到延伸穿过第一衬套板的至少一个孔。 在第一涡轮机部件中形成开口。 基于正在钻的第二涡轮机部件来选择第二衬套板。 第二涡轮机部件与第一涡轮部件不同。 第二衬套板可移除地联接到基座。 在第二涡轮机部件中形成开口。
-
公开(公告)号：US20080206063A1
公开(公告)日：2008-08-28
申请号：US11679468
申请日：2007-02-27
Applicant: Lynn Charles Gagne , Graham David Sherlock , Kelvin Aaron , Thomas Robbins Tipton
Inventor： Lynn Charles Gagne , Graham David Sherlock , Kelvin Aaron , Thomas Robbins Tipton
IPC: B64C11/16
CPC classification number: F01D9/042 , F05D2250/191
Abstract: A method for assembling a stator assembly for a turbine engine is provided. The method includes providing a blade with a base including an end wall having at least one hole defined therein and providing a shim having at least one aperture extending therethrough. The shim aperture is aligned with the end wall hole, and the shim is secured to the blade base end wall using a fastener. The fastener is inserted through the shim aperture in an interference fit within the end wall hole. The blade and the shim are coupled to a turbine casing.
Abstract translation: 提供一种用于组装用于涡轮发动机的定子组件的方法。 该方法包括提供具有底座的刀片，底座包括具有限定在其中的至少一个孔的端壁，并提供具有延伸穿过其中的至少一个孔的垫片。 垫片孔与端壁孔对齐，并且垫片使用紧固件固定到刀片底端壁上。 紧固件通过垫片孔以过盈配合插入端壁孔内。 叶片和垫片联接到涡轮机壳体。
-
公开(公告)号：US07578164B2
公开(公告)日：2009-08-25
申请号：US11232625
申请日：2005-09-22
Applicant: Graham David Sherlock , Paul Lawrence Kalmar , Benjamin Erick Baker
Inventor： Graham David Sherlock , Paul Lawrence Kalmar , Benjamin Erick Baker
IPC: G01B3/30
CPC classification number: G01B5/0004 , F01D5/141 , F01D9/041 , F01D21/003 , F05D2230/14
Abstract: A method for inspecting a turbine nozzle segment includes positioning the turbine nozzle segment on a base of a tool, with the outer forward face and the inner forward face of the turbine nozzle segment contacting a surface of the base. The outer wall is positioned between a first pedestal outer stand and a second pedestal outer stand of the tool, and the inner wall is positioned between a first pedestal inner stand and a second pedestal inner stand of the tool. At least one of a position, a depth and a width of a seal slot formed in a side edge of the outer wall and/or the inner wall is measured. At least one axial dimension of the turbine nozzle segment and at least one radial dimension of the turbine nozzle segment are measured.
Abstract translation: 用于检查涡轮喷嘴段的方法包括将涡轮喷嘴段定位在工具的基部上，涡轮喷嘴段的外前面和内前面接触基座的表面。 外壁位于工具的第一基座外支架和第二基座外支架之间，并且内壁位于工具的第一基座内支架和第二基座内支架之间。 测量形成在外壁和/或内壁的侧边缘中的密封槽的位置，深度和宽度中的至少一个。 测量涡轮喷嘴段的至少一个轴向尺寸和涡轮喷嘴段的至少一个径向尺寸。
-
公开(公告)号：US20080206005A1
公开(公告)日：2008-08-28
申请号：US11679505
申请日：2007-02-27
Applicant: Graham David Sherlock , Lynn Charles Gagne , Larry Paul Wencil
Inventor： Graham David Sherlock , Lynn Charles Gagne , Larry Paul Wencil
IPC: B23B43/00
CPC classification number: B23B47/28 , B21J15/10 , B23B2215/81 , B23B2247/12 , Y10T408/03 , Y10T408/563 , Y10T408/567
Abstract: A method for forming an opening in two different turbine components is provided. The method includes coupling a clamp to a base and coupling the clamp to a clamp bar, wherein the clamp bar is moveable with respect to the base. A first bushing plate is selected based on a first turbine component being drilled and is removably coupled to the base. A bushing is removably coupled to at least one aperture extending through the first bushing plate. An opening is formed in the first turbine component. A second bushing plate is selected based on a second turbine component being drilled. The second turbine component is different from the first turbine component. The second bushing plate is removably coupled to the base. An opening is formed in the second turbine component.
Abstract translation: 提供了一种用于在两个不同涡轮机部件中形成开口的方法。 该方法包括将夹具连接到基座并将夹具连接到夹紧杆，其中夹紧杆可相对于基座移动。 基于正在钻孔的第一涡轮机部件选择第一衬套板，并且可拆卸地联接到基座。 衬套可移除地联接到延伸穿过第一衬套板的至少一个孔。 在第一涡轮机部件中形成开口。 基于正在钻的第二涡轮机部件来选择第二衬套板。 第二涡轮机部件与第一涡轮部件不同。 第二衬套板可移除地联接到基座。 在第二涡轮机部件中形成开口。
-
公开(公告)号：US07231724B2
公开(公告)日：2007-06-19
申请号：US11260151
申请日：2005-10-28
Applicant: Graham David Sherlock , Paul Lawrence Kalmar , Christopher Edward Thompson
IPC: G01B5/14
Abstract: A tool for measuring seal slot position includes a tool shaft having a longitudinal axis, a pin eccentrically disposed at one end of the tool shaft relative to the longitudinal axis, and a disk member disposed at an opposite end of the tool shaft that facilitates rotation of the tool shaft and pin in the seal slot. The tool provides for increased accuracy in measuring seal slot position such as turbine nozzle seal slot position.
-
-
-
-
-
-
-
Search Results
18
records
(took 0.013 seconds)
