Patents by Inventor Michael J. Bruskotter
Michael J. Bruskotter 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: 10961862Abstract: A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss.Type: GrantFiled: June 7, 2019Date of Patent: March 30, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Paul M. Lutjen, Michael J. Bruskotter, Brian C. McLaughlin, Terence P. Tyler
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Publication number: 20200386112Abstract: A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss.Type: ApplicationFiled: June 7, 2019Publication date: December 10, 2020Inventors: Paul M. Lutjen, Michael J. Bruskotter, Brian C. McLaughlin, Terence P. Tyler
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Patent number: 10760443Abstract: An air scal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.Type: GrantFiled: April 9, 2018Date of Patent: September 1, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Christopher W. Strock, Paul M. Lutjen, Michael J. Bruskotter
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Patent number: 10612407Abstract: A blade outer air seal (BOAS) segment according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face, wherein a radial position of the radially inner face varies at a given axial position.Type: GrantFiled: February 4, 2014Date of Patent: April 7, 2020Assignee: United Technologies CorporationInventors: Paul M. Lutjen, Michael J. Bruskotter
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Patent number: 10443435Abstract: A component for a turbomachine includes an annular body defining an inner diameter portion and an outer diameter portion, and a crack guiding slot defined in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter portion or extending from the outer diameter portion radially inward toward the inner diameter portion. The outer diameter portion can be mountable to a stationary structure of a turbomachine. The inner diameter portion can be mountable to a turbine vane.Type: GrantFiled: December 15, 2015Date of Patent: October 15, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Richard K. Hayford, Michael J. Bruskotter, Ross A. Vandenbosch
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Publication number: 20180298776Abstract: An air scal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.Type: ApplicationFiled: April 9, 2018Publication date: October 18, 2018Inventors: Christopher W. Strock, Paul M. Lutjen, Michael J. Bruskotter
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Patent number: 9938849Abstract: An air seal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.Type: GrantFiled: September 17, 2014Date of Patent: April 10, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Christopher W. Strock, Paul M. Lutjen, Michael J. Bruskotter
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Patent number: 9708922Abstract: A seal assembly includes a first component, a second component, a first seal, a first shelf, a second shelf, and a second seal. The second component is adjacent to the first component and forms a cavity between the first and second components. The first seal spans the cavity. The first shelf extends axially from the first component and is located between the first seal and a hot gas path. The second shelf extends axially from the second component and is located between the first shelf and the hot gas path; the second shelf together with the first shelf forms a flow channel. The second seal conforms to the first shelf, sealing the flow channel.Type: GrantFiled: May 23, 2016Date of Patent: July 18, 2017Assignee: United Technologies CorporationInventors: Timothy M. Davis, Mark J. Rogers, Paul M. Lutjen, Terence P. Tyler, Jr., Michael J. Bruskotter
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Patent number: 9657584Abstract: An air seal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.Type: GrantFiled: September 17, 2014Date of Patent: May 23, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Christopher W. Strock, Paul M. Lutjen, Michael J. Bruskotter
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Publication number: 20160251976Abstract: An air seal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.Type: ApplicationFiled: September 17, 2014Publication date: September 1, 2016Inventors: Christopher W. Strock, Paul M. Lutjen, Michael J. Bruskotter
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Publication number: 20160169039Abstract: A component for a turbomachine includes an annular body defining an inner diameter portion and an outer diameter portion, and a crack guiding slot defined in a surface of the annular body extending from the inner diameter portion radially outward toward the outer diameter portion or extending from the outer diameter portion radially inward toward the inner diameter portion. The outer diameter portion can be mountable to a stationary structure of a turbomachine. The inner diameter portion can be mountable to a turbine vane.Type: ApplicationFiled: December 15, 2015Publication date: June 16, 2016Inventors: Richard K. Hayford, Michael J. Bruskotter, Ross A. Vandenbosch
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Publication number: 20160003082Abstract: A blade outer air seal (BOAS) segment according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face, wherein a radial position of the radially inner face varies at a given axial position.Type: ApplicationFiled: February 4, 2014Publication date: January 7, 2016Inventors: Paul M. Lutjen, Michael J. Bruskotter
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Patent number: 8439629Abstract: A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating forward and aft cavity portions.Type: GrantFiled: March 1, 2007Date of Patent: May 14, 2013Assignee: United Technologies CorporationInventors: Edward F. Pietraszkiewicz, John C. Calderbank, Joseph A. Peto, Lisa P. O'Neill, Michael J. Bruskotter
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Patent number: 8123466Abstract: A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating circumferentially and fore-aft offset cavity portions.Type: GrantFiled: March 1, 2007Date of Patent: February 28, 2012Assignee: United Technologies CorporationInventors: Edward F. Pietraszkiewicz, John C. Calderbank, Joseph A. Peto, Lisa P. O'Neill, Michael J. Bruskotter
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Patent number: 7770375Abstract: A material having a plurality of impurity collection spaces has an outer face facing into a cooling air flow stream for a gas turbine engine component. Impurities such as sand or dirt will collect in the plurality of spaces. In a disclosed embodiment, a honeycombed material is utilized. The material may have a surface that will sit with at least a component parallel to an axial centerline of a gas turbine engine that is to receive the collection material. The material surface may also have a component which is generally perpendicular to the axial centerline. The material may be placed in a gas turbine engine upstream of the turbine section, and downstream of the combustion section. Moreover, the collection material may be placed such that there is cleaner air flow radially inwardly of the collection material, and heavier dirt-laden air passing along the collection material such that impurities can be collected.Type: GrantFiled: February 9, 2006Date of Patent: August 10, 2010Assignee: United Technologies CorporationInventors: Ioannis Alvanos, Bernard A. Andrews, Robert A. Charbonneau, Susan M. Tholen, Thurman Carlo Dabbs, Michael J. Bruskotter
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Publication number: 20090067994Abstract: A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating forward and aft cavity portions.Type: ApplicationFiled: March 1, 2007Publication date: March 12, 2009Inventors: Edward F. Pietraszkiewicz, John C. Calderbank, Joseph A. Peto, Lisa P. O'Neill, Michael J. Bruskotter
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Publication number: 20080211192Abstract: A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating circumferentially and fore-aft offset cavity portions.Type: ApplicationFiled: March 1, 2007Publication date: September 4, 2008Inventors: Edward F. Pietraszkiewicz, John C. Calderbank, Joseph A. Peto, Lisa P. O'Neill, Michael J. Bruskotter