Patents by Inventor David Scott Stapleton
David Scott Stapleton 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: 11187094Abstract: An assembly for a turbine engine comprising a plurality of circumferentially arranged segments having first and second confronting end faces. The first and second confronting end faces include a multi-channel spline seal assembly. The multi-channel spline seal assembly includes at least a first and second channel wherein confronting first or second channels can receive at least one spline seal.Type: GrantFiled: August 26, 2019Date of Patent: November 30, 2021Assignee: General Electric CompanyInventors: Kevin Robert Feldmann, Robert Proctor, David Scott Stapleton, Robert Charles Groves, II
-
Publication number: 20210062666Abstract: An assembly for a turbine engine comprising a plurality of circumferentially arranged segments having first and second confronting end faces. The first and second confronting end faces include a multi-channel spline seal assembly. The multi-channel spline seal assembly includes at least a first and second channel wherein confronting first or second channels can receive at least one spline seal.Type: ApplicationFiled: August 26, 2019Publication date: March 4, 2021Inventors: Kevin Robert Feldmann, Robert Proctor, David Scott Stapleton, Robert Charles Groves, II
-
Patent number: 10794204Abstract: In one aspect, the present disclosure is directed to a gas turbine sealing assembly that includes a first static gas turbine wall and a second static gas turbine wall. A seal is disposed between the first static gas turbine wall and the second static gas turbine wall. The seal includes a shield wall constructed from a first material that includes a first shield wall portion and a second shield wall portion. A spring constructed from a second material includes a first spring portion and a second spring portion. The first shield wall portion is adjacent to the first spring portion, and the second shield wall portion is adjacent to the second spring portion.Type: GrantFiled: September 28, 2015Date of Patent: October 6, 2020Assignee: General Electric CompanyInventors: Dylan James Fitzpatrick, David Scott Stapleton, Jonathan David Baldiga, Christopher Paul Tura
-
Patent number: 10689998Abstract: Shrouds and methods for forming turbine components are provided. A shroud includes a shroud body which includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a forward flange extending from the outer surface of the shroud body, and a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange. The shroud further includes a cooling passage defined in the shroud, the cooling passage extending generally circumferentially through the shroud.Type: GrantFiled: October 14, 2015Date of Patent: June 23, 2020Assignee: General Electric CompanyInventors: David Scott Stapleton, Robert Charles Groves, II
-
Patent number: 10655495Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.Type: GrantFiled: February 24, 2017Date of Patent: May 19, 2020Assignee: General Electric CompanyInventors: Robert Charles Groves, II, David Scott Stapleton
-
Patent number: 10648362Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.Type: GrantFiled: February 24, 2017Date of Patent: May 12, 2020Assignee: General Electric CompanyInventors: Robert Charles Groves, II, David Scott Stapleton
-
Patent number: 10472989Abstract: According to some embodiments, a ceramic matrix composite (CMC) hanger sleeve is provided for retaining a ceramic matrix composite shroud panel. The sleeve may be connected to an upper hanger by a retainer or a casing. The hanger sleeve includes a radially inward opening with a flowpath panel disposed therein. When the CMC flowpath panel is worn due to time, rubs or both, the panel may be replaced without need to replace the entire assembly.Type: GrantFiled: December 18, 2014Date of Patent: November 12, 2019Assignee: General Electric CompanyInventor: David Scott Stapleton
-
Patent number: 10465558Abstract: A shroud hanger assembly or shroud assembly is provided for components which may be formed of materials having differing coefficient thermal expansion. The assembly includes a multi-piece hanger including a shroud positioned in a cavity between a first hanger portion and a second hanger portion. A shroud may be formed of a low coefficient of thermal expansion material which may have a differing coefficient thermal expansion than the material defining the shroud hanger. The shroud is deflected by an axial force acting between the hanger and the shroud which also forms a seal. The seal compensates for differing rates of thermal growth between the shroud and the hanger throughout the engine operating envelope.Type: GrantFiled: April 28, 2015Date of Patent: November 5, 2019Assignee: General Electric CompanyInventors: Jason David Shapiro, Michael John Franks, David Scott Stapleton
-
Patent number: 10301960Abstract: Shroud assemblies for gas turbine engines are provided. A shroud assembly includes a hanger having a forward hanger arm, a rear hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm. The shroud assembly further includes a shroud having a forward surface, a rear surface, and an inner surface and outer surface extending between the forward surface and the rear surface, the outer surface radially spaced from the inner surface, the shroud connected to the hanger. The shroud assembly further includes a support member positioned axially forward of the forward hanger arm, the support member having a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud.Type: GrantFiled: July 13, 2015Date of Patent: May 28, 2019Assignee: General Electric CompanyInventors: David Scott Stapleton, Bryce Loring Heitman, Laura Isabelle Armanios
-
Publication number: 20180355754Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.Type: ApplicationFiled: February 24, 2017Publication date: December 13, 2018Inventors: Robert Charles Groves, II, David Scott Stapleton
-
Publication number: 20180355755Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.Type: ApplicationFiled: February 24, 2017Publication date: December 13, 2018Inventors: Robert Charles Groves, II, David Scott Stapleton
-
Publication number: 20180355741Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.Type: ApplicationFiled: February 24, 2017Publication date: December 13, 2018Inventors: Robert Charles Groves, II, David Scott Stapleton
-
Publication number: 20180355753Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.Type: ApplicationFiled: February 24, 2017Publication date: December 13, 2018Inventors: Robert Charles Groves, II, David Scott Stapleton
-
Publication number: 20180340437Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.Type: ApplicationFiled: February 24, 2017Publication date: November 29, 2018Inventors: Robert Charles Groves, II, David Scott Stapleton
-
Patent number: 9863265Abstract: Shroud assemblies and shrouds for gas turbine engines are provided. A shroud includes a shroud body which includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a forward flange extending from the outer surface of the shroud body, and a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange. The shroud further includes a rib disposed between and in contact with the forward flange and the rear flange.Type: GrantFiled: April 15, 2015Date of Patent: January 9, 2018Assignee: General Electric CompanyInventor: David Scott Stapleton
-
Patent number: 9810086Abstract: A shroud apparatus for a gas turbine engine includes: an annular shroud segment having an arcuate bottom wall defining an arcuate inner flowpath surface, spaced-apart forward and aft walls extending radially outward from the bottom wall, and spaced-apart side walls extending radially outward from the bottom wall and between the forward and aft walls, each side wall defining an end face which includes: an axial slot extending in a generally axial direction along the end face; a first radial slot extending in a generally radial direction along the end face, and intersecting the axial slot; an axial spline seal received in the axial slot; and a first radial spline seal having an L-shape with radial and axial legs, the radial leg being substantially longer than the axial leg, wherein the radial leg is received in the first radial slot, and the axial leg is received in the axial slot.Type: GrantFiled: April 11, 2012Date of Patent: November 7, 2017Assignee: General Electric CompanyInventors: Victor Hugo Silva Correia, Christopher Michael Ceglio, David Scott Stapleton
-
Publication number: 20170159487Abstract: The present disclosure is directed to a composite component for a gas turbine engine. The composite component includes a composite wall having a flow side surface and non-flow side surface. The non-flow side surface includes at least one composite cooling projection positioned on and extending outwardly from the non-flow side surface.Type: ApplicationFiled: December 2, 2015Publication date: June 8, 2017Inventors: David Scott Stapleton, Jonathan David Baldiga, Gregory Scot Corman
-
Publication number: 20170114670Abstract: A shroud hanger assembly or shroud assembly is provided for components which may be formed of materials having differing coefficient thermal expansion. The assembly includes a multi-piece hanger including a shroud positioned in a cavity between a first hanger portion and a second hanger portion. A shroud may be formed of a low coefficient of thermal expansion material which may have a differing coefficient thermal expansion than the material defining the shroud hanger. The shroud is deflected by an axial force acting between the hanger and the shroud which also forms a seal. The seal compensates for differing rates of thermal growth between the shroud and the hanger throughout the engine operating envelope.Type: ApplicationFiled: April 28, 2015Publication date: April 27, 2017Inventors: Jason David SHAPIRO, Michael John FRANKS, David Scott STAPLETON
-
Publication number: 20170107840Abstract: Shrouds and methods for forming turbine components are provided. A shroud includes a shroud body which includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a forward flange extending from the outer surface of the shroud body, and a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange. The shroud further includes a cooling passage defined in the shroud, the cooling passage extending generally circumferentially through the shroud.Type: ApplicationFiled: October 14, 2015Publication date: April 20, 2017Inventors: David Scott Stapleton, Robert Charles Groves, II
-
Publication number: 20170089212Abstract: In one aspect, the present disclosure is directed to a gas turbine sealing assembly that includes a first static gas turbine wall and a second static gas turbine wall. A seal is disposed between the first static gas turbine wall and the second static gas turbine wall. The seal includes a shield wall constructed from a first material that includes a first shield wall portion and a second shield wall portion. A spring constructed from a second material includes a first spring portion and a second spring portion. The first shield wall portion is adjacent to the first spring portion, and the second shield wall portion is adjacent to the second spring portion.Type: ApplicationFiled: September 28, 2015Publication date: March 30, 2017Inventors: Dylan James Fitzpatrick, David Scott Stapleton, Jonathan David Baldiga, Christopher Paul Tura