Patents by Inventor Russell E. Keene
Russell E. Keene 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: 10451204Abstract: A turbine shroud for incorporation in a turbine of a gas turbine engine has a plurality of butted shroud segments circumferentially arrayed to form a ring. Each of the shroud segments has an arcuate main shroud body portion, a radially inward extending annular flange attached to a first end of the main body portion, and a radially outward extending flange with a plurality of mounting apertures attached to a second end of the main shroud body portion. A first mounting aperture is sized smaller than an adjacent second mounting aperture in the radially outward extending flange.Type: GrantFiled: March 11, 2014Date of Patent: October 22, 2019Assignee: United Technologies CorporationInventors: Mark Broomer, Russell E. Keene, Timothy M. Davis, Mark J. Rogers
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Patent number: 10196917Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.Type: GrantFiled: July 1, 2015Date of Patent: February 5, 2019Assignee: United Technologies CorporationInventors: Paul M. Lutjen, Shawn J. Gregg, Thurman Carlo Dabbs, Ken F. Blaney, Russell E. Keene, Bruce E. Chick
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Patent number: 10145308Abstract: A seal assembly for a gas turbine engine includes an engine static structure. First and second members fluidly separate cavities from one another. A seal assembly is captured by the engine structure. The seal assembly includes a carrier and a seal that engages the first member. The second member is captured by the carrier.Type: GrantFiled: February 2, 2015Date of Patent: December 4, 2018Assignee: United Technologies CorporationInventors: Carson A. Roy Thill, Mark Broomer, Timothy M. Davis, Craig R. McGarrah, Mark J. Rogers, Russell E. Keene, Anthony B. Swift
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Patent number: 10077680Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.Type: GrantFiled: October 2, 2014Date of Patent: September 18, 2018Assignee: United Technologies CorporationInventors: Anne-Marie B. Thibodeau, Bruce E. Chick, Thurman Carlo Dabbs, James N. Knapp, Dmitriy A. Romanov, Russell E. Keene, Jeffrey Vincent Anastas
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Patent number: 9951634Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body having circumferential sides between a forward face and an aft face, each of the circumferential sides defining a mate face, an attachment member extending from the body, and a transition member adjacent to the body and the attachment member. The transition member and the body define a slot configured to receive a seal member. The transition member is sloped inwardly from one of the circumferential sides. A method of fabricating a gas turbine engine component is also disclosed.Type: GrantFiled: June 11, 2015Date of Patent: April 24, 2018Assignee: United Technologies CorporationInventors: Carson A. Roy Thill, Russell E. Keene, Paul M. Lutjen
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Patent number: 9879558Abstract: An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture.Type: GrantFiled: February 5, 2014Date of Patent: January 30, 2018Assignee: United Technologies CorporationInventors: Mark J Rogers, Mark Broomer, Craig R. McGarrah, Timothy M Davis, Anthony B Swift, Russell E Keene, Carson A. Roy Thill, Timothy A. Dunbar
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Patent number: 9670791Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a flexible seal that is attached to the first component. The flexible seal at least partially seals a gap between the first component and the second component. The flexible seal includes a mount and a finger seal that sealingly engages the second component. The mount includes a boss that sealingly engages the first component.Type: GrantFiled: March 4, 2014Date of Patent: June 6, 2017Assignee: United Technologies CorporationInventors: Mark Broomer, Carson A. Roy Thill, Timothy M. Davis, Anthony P. Cherolis, Robert L. Hazzard, Craig R. McGarrah, Conway Choung, Russell E. Keene
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Publication number: 20160362992Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body having circumferential sides between a forward face and an aft face, each of the circumferential sides defining a mate face, an attachment member extending from the body, and a transition member adjacent to the body and the attachment member. The transition member and the body define a slot configured to receive a seal member. The transition member is sloped inwardly from one of the circumferential sides. A method of fabricating a gas turbine engine component is also disclosed.Type: ApplicationFiled: June 11, 2015Publication date: December 15, 2016Inventors: Carson A. Roy Thill, Russell E. Keene, Paul M. Lutjen
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Publication number: 20160010482Abstract: An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture.Type: ApplicationFiled: February 5, 2014Publication date: January 14, 2016Inventors: Mark J Rogers, Mark Broomer, Craig R McGarrah, Timothy M Davis, Anthony B Swift, Russell E Keene, Carson A. Roy Thill, Timothy A. Dunbar
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Publication number: 20160003081Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a flexible seal that is attached to the first component. The flexible seal at least partially seals a gap between the first component and the second component. The flexible seal includes a mount and a finger seal that sealingly engages the second component. The mount includes a boss that sealingly engages the first component.Type: ApplicationFiled: March 4, 2014Publication date: January 7, 2016Inventors: Mark Broomer, Carson A. Roy Thill, Timothy M. Davis, Anthony P. Cherolis, Robert L. Hazzard, Craig R. McGarrah, Conway Choung, Russell E. Keene
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Publication number: 20150369409Abstract: A turbine shroud for incorporation in a turbine of a gas turbine engine has a plurality of butted shroud segments circumferentially arrayed to form a ring. Each of the shroud segments has an arcuate main shroud body portion, a radially inward extending annular flange attached to a first end of the main body portion, and a radially outward extending flange with a plurality of mounting apertures attached to a second end of the main shroud body portion. A first mounting aperture is sized smaller than an adjacent second mounting aperture in the radially outward extending flange.Type: ApplicationFiled: March 11, 2014Publication date: December 24, 2015Inventors: Mark BROOMER, Russell E. KEENE, Timothy M. DAVIS, Mark J. ROGERS
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Publication number: 20150300195Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.Type: ApplicationFiled: July 1, 2015Publication date: October 22, 2015Applicant: United Technologies CorporationInventors: Paul M. Lutjen, Shawn J. Gregg, Thurman Carlo Dabbs, Ken F. Blaney, Russell E. Keene, Bruce E. Chick
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Publication number: 20150226132Abstract: A seal assembly for a gas turbine engine includes an engine static structure. First and second members fluidly separate cavities from one another. A seal assembly is captured by the engine structure. The seal assembly includes a carrier and a seal that engages the first member. The second member is captured by the carrier.Type: ApplicationFiled: February 2, 2015Publication date: August 13, 2015Inventors: Carson A. Roy Thill, Mark Broomer, Timothy M. Davis, Craig R. McGarrah, Mark J. Rogers, Russell E. Keene, Anthony B. Swift
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Patent number: 9103225Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.Type: GrantFiled: June 4, 2012Date of Patent: August 11, 2015Assignee: United Technologies CorporationInventors: Paul M. Lutjen, Shawn J. Gregg, Thurman Carlo Dabbs, Ken F. Blaney, Russell E. Keene, Bruce E. Chick
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Publication number: 20150016954Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.Type: ApplicationFiled: October 2, 2014Publication date: January 15, 2015Inventors: Anne-Marie B. Thibodeau, Bruce E. Chick, Thurman Carlo Dabbs, James N. Knapp, Dmitriy A. Romanov, Russell E. Keene, Jeffrey Vincent Anastas
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Patent number: 8876458Abstract: An example blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially from the support member toward the blade outer air seal. The support tab is configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the support member.Type: GrantFiled: January 25, 2011Date of Patent: November 4, 2014Assignee: United Technologies CorporationInventors: Anne-Marie B. Thibodeau, Bruce E. Chick, Thurman Carlo Dabbs, James N. Knapp, Dmitriy A. Romanov, Russell E. Keene, Jeffrey Vincent Anastas
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Publication number: 20140127006Abstract: A blade outer air seal for a gas turbine engine includes a first side surface, a second side surface, and a wall. The wall extends between the first side surface and the second side surface and has one or more holes formed therein. The holes are spaced from the first side surface and/or the second side surface and have areas between about 0.005% and 0.450% of a surface area of the blade outer air seal.Type: ApplicationFiled: November 5, 2012Publication date: May 8, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Dmitriy A. Romanov, Brian Duguay, Russell E. Keene
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Publication number: 20140064969Abstract: An example blade outer air seal assembly for a gas turbine engine includes a main body portion extending along an axis. The main body portion has a radially inward facing surface and at least one radially outward facing surface. A passage is provided in the main body portion between the at least one radially inward facing surface and the at least one radially outward facing surface. The passage has a first portion and a second portion transverse to the first portion, and at least one rib disposed along the axis radially outward of the second portion.Type: ApplicationFiled: August 29, 2012Publication date: March 6, 2014Inventors: Dmitriy A. Romanov, Brian R. Pelletier, Russell E. Keene
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Publication number: 20130323033Abstract: A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.Type: ApplicationFiled: June 4, 2012Publication date: December 5, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Paul M. Lutjen, Shawn J. Gregg, Thurman Carlo Dabbs, Ken F. Blaney, Russell E. Keene, Bruce E. Chick
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Publication number: 20120189426Abstract: An example blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially from the support member toward the blade outer air seal. The support tab is configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the support member. An example blade outer air seal assembly includes a blade outer air seal assembly having an inwardly facing surface. A blade path portion of the inwardly facing surface is axially aligned with a tip of a rotating blade.Type: ApplicationFiled: January 25, 2011Publication date: July 26, 2012Inventors: Anne-Marie B. Thibodeau, Bruce E. Chick, Thurman Carlo Dabbs, James N. Knapp, Dmitriy A. Romanov, Russell E. Keene, Jeffrey Vincent Anastas