Patents by Inventor Mark Broomer
Mark Broomer 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: 11473437Abstract: In one aspect, a sealing assembly for a turbine of a gas turbine engine includes a first turbine component having a first surface and a second surface positioned aft of the first surface. The first turbine component, in turn, defines a slot positioned between the first surface and the second surface. Furthermore, the sealing assembly includes a second turbine component positioned aft of the first turbine component such that the first component and the second component define a gap therebetween. Additionally, the sealing assembly includes a seal configured to seal the gap defined between the first turbine component and the second turbine component. The seal includes a first portion positioned within the slot such that the first portion exerts a sealing force on the second surface of the first component. Moreover, the seal further includes a second portion that exerts a sealing force on the second component.Type: GrantFiled: September 20, 2019Date of Patent: October 18, 2022Assignee: General Electric CompanyInventors: Mark Broomer, Tyler Frederick Hooper, Jason Michael Ulberg
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Publication number: 20210079799Abstract: An apparatus for a nozzle assembly for a turbine engine and a method of forming the nozzle assembly are described herein. The nozzle assembly can include a set of nozzles including an inner band and an outer band, with one or more airfoils extending between the inner and outer bands. The nozzles can be coupled to adjacent nozzles at the inner and outer bands to form the nozzle assembly. A throat can be defined at the minimum cross-sectional area between adjacent airfoils in the nozzle assembly. A formed portion can be formed on either of or both of the inner or outer band at the throat.Type: ApplicationFiled: September 12, 2019Publication date: March 18, 2021Inventors: Paul Hadley Vitt, Wilson Frost, Mark Broomer
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Patent number: 10731493Abstract: A seal for sealing a radially outer component of a gas turbine engine stator to a radially inner component thereof includes an axially resilient seal carrier adapted for mounting the seal carrier and including at a radially inner portion thereof, a pair of radially spaced, axially extending, radially resilient jaws adapted to clamp a sealing element such as a rope seal there between in sealing engagement with a radially inner component of the engine stator.Type: GrantFiled: April 10, 2014Date of Patent: August 4, 2020Assignee: Ratheyon Technologies CorporationInventors: Timothy M. Davis, Mark J. Rogers, Mark Broomer, Craig R. McGarrah, Carson A. Roy Thill
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Publication number: 20200141256Abstract: In one aspect, a sealing assembly for a turbine of a gas turbine engine includes a first turbine component having a first surface and a second surface positioned aft of the first surface. The first turbine component, in turn, defines a slot positioned between the first surface and the second surface. Furthermore, the sealing assembly includes a second turbine component positioned aft of the first turbine component such that the first component and the second component define a gap therebetween. Additionally, the sealing assembly includes a seal configured to seal the gap defined between the first turbine component and the second turbine component. The seal includes a first portion positioned within the slot such that the first portion exerts a sealing force on the second surface of the first component. Moreover, the seal further includes a second portion that exerts a sealing force on the second component.Type: ApplicationFiled: September 20, 2019Publication date: May 7, 2020Inventors: Mark Broomer, Tyler Frederick Hooper
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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: 10392950Abstract: A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.Type: GrantFiled: May 7, 2015Date of Patent: August 27, 2019Assignee: General Electric CompanyInventors: Victor Hugo Silva Correia, Brian Kenneth Corsetti, Mark Broomer
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Patent number: 10280778Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a seal assembly. The first component includes a groove and a groove surface. The second component includes a tongue that extends into the groove to a tongue surface. The seal assembly at least partially seals a gap between the groove surface and the tongue surface. The seal assembly includes a rope seal and a clip that attaches the rope seal to the tongue. The rope seal is arranged within the groove between the groove surface and the tongue surface.Type: GrantFiled: February 24, 2014Date of Patent: May 7, 2019Assignee: United Technologies CorporationInventors: Mark J. Rogers, Timothy M. Davis, Mark Broomer, Kevin W. White, Craig McGarrah, Carson A. Roy Thill
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Publication number: 20190024513Abstract: An airfoil for a turbine engine can include a body having an outer wall defining a pressure side and a suction side, and the body can extend axially between a truncated nose and a trailing edge. A shield can be positioned upstream of the nose to define a leading edge for the airfoil.Type: ApplicationFiled: July 19, 2017Publication date: January 24, 2019Inventors: Robert Francis Manning, Mark Broomer, Brian Kenneth Corsetti
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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: 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: 20170089211Abstract: Snap in annular spring seal including continuous or split full 360 degree ring having radially outer second seal end spaced outwardly of a radially inner first end of the ring and axial biasing means urging first and second seal ends apart. Biasing means may include an axially aftwardly opening conical section connecting first and second seal ends and second seal end having outer aftwardly opening V-shaped cross-sectional bend or circular cross-sectional bend. Spring seal may extend radially and circumferentially between and in sealing engagement with first and second annular turbine components. First end may be spring-loaded and removably secured in U-shaped or V-shaped slot of turbine component. Slot may include symmetrical inner U-shaped bent first seal end including annular substantially parallel or non-parallel forward and aft legs connected by semi-circular cross-sectional bend. Seal may include bowed section connecting circular seal ends.Type: ApplicationFiled: September 24, 2015Publication date: March 30, 2017Inventors: Mark Broomer, Edip Sevincer, Anthony Christopher Marin
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Publication number: 20170058684Abstract: A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.Type: ApplicationFiled: May 7, 2015Publication date: March 2, 2017Inventors: Victor Hugo Silva CORREIA, Brian Kenneth CORSETTI, Mark BROOMER
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Publication number: 20160061047Abstract: A seal for sealing a radially outer component of a gas turbine engine stator to a radially inner component thereof includes an axially resilient seal carrier adapted for mounting the seal carrier and including at a radially inner portion thereof, a pair of radially spaced, axially extending, radially resilient jaws adapted to clamp a sealing element such as a rope seal there between in sealing engagement with a radially inner component of the engine stator.Type: ApplicationFiled: April 10, 2014Publication date: March 3, 2016Inventors: Timothy M. Davis, Mark J. Rogers, Mark Broomer, Craig R. McGarrah, Carson A. Roy Thill
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Publication number: 20160017738Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a seal assembly. The first component includes a groove and a groove surface. The second component includes a tongue that extends into the groove to a tongue surface. The seal assembly at least partially seals a gap between the groove surface and the tongue surface. The seal assembly includes a rope seal and a clip that attaches the rope seal to the tongue. The rope seal is arranged within the groove between the groove surface and the tongue surface.Type: ApplicationFiled: February 24, 2014Publication date: January 21, 2016Inventors: Mark J. Rogers, Timothy M. Davis, Mark Broomer, Kevin W. White, Craig McGarrah, Carson A. Roy Thill
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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: 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: 8296945Abstract: A method for repairing a turbine nozzle segment includes providing a turbine nozzle segment having an enclosure with an integral discourager, removing the enclosure and/or the discourager from the turbine nozzle segment and attaching a new enclosure ad/or discourager to the turbine nozzle segment.Type: GrantFiled: December 29, 2007Date of Patent: October 30, 2012Assignee: General Electric CompanyInventors: Mark Broomer, Victor Hugo Silva Correia