Patents by Inventor Michael S. Stevens
Michael S. Stevens 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: 11459905Abstract: A method of making a component includes creating a computer file defining the component in layers, the component including: a body including a sealing portion; and an abradable seal extending from the sealing portion; and building the component using an additive manufacturing process that builds the component on a layer-by-layer basis such that the abradable seal is integral to the body.Type: GrantFiled: October 28, 2019Date of Patent: October 4, 2022Assignee: Raytheon Technologies CorporationInventors: Michael S. Stevens, Jeffrey Vincent Anastas
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Patent number: 11021983Abstract: The present disclosure relates generally to a seal between two components. The seal includes a plurality of seal sections including convolutions therein that are inter-engaged with one another to form flexible and resilient seals.Type: GrantFiled: June 14, 2018Date of Patent: June 1, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Timothy M. Davis, Michael S. Stevens
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Patent number: 10865650Abstract: A stator vane support with anti-rotation features is provided. The stator vane support may comprise an inner diameter surface opposite an outer diameter surface. The stator vane support may comprise an anti-rotation lug defining a protrusion extending inward from the inner diameter surface. The stator vane support may have a first recess defining a first void on the inner diameter surface proximate a first surface of the anti-rotation lug. The stator vane support may have a second recess defining a second void on the inner diameter surface proximate a second surface of the anti-rotation lug. The anti-rotation lug may be configured to interface with a stator vane to at least partially limit circumferential movement, and each recess may be configured to allow the stator vane to thermally expand during gas turbine engine operation.Type: GrantFiled: September 12, 2017Date of Patent: December 15, 2020Assignee: Raytheon Technologies CorporationInventors: Michael S. Stevens, Tomasz Pelic
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Patent number: 10808558Abstract: A heat shield vane support may have a structure including at least one of a cylindrical and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face and may comprise a flange extending circumferentially about the aft face radially inward from the inboard diameter, a plurality of anti-rotation features distributed circumferentially about the inboard diameter extending radially inward from the inboard diameter and extending axially with respect to the cylindrical structure between a forward edge and an aft edge defining a length L, and a plurality of teeth distributed circumferentially about the forward face and extending axially from the forward face.Type: GrantFiled: May 17, 2018Date of Patent: October 20, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Michael S. Stevens, Christine F. McGinnis, Major D. Jones, Judith F. Brooks, Brian Duguay, Tomasz Pelic
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Patent number: 10662791Abstract: A support ring for a gas turbine engine includes a main body portion extending circumferentially about a center axis, a radially extending portion extending radially inward from the main body portion and having a plurality of openings, and a plurality of anti-rotation tabs extending radially inward from the main body portion and axially spaced from the radially extending portion.Type: GrantFiled: October 16, 2018Date of Patent: May 26, 2020Assignee: United Technologies CorporationInventors: Michael S. Stevens, David Richard Griffin
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Patent number: 10584613Abstract: A debris separator for a gas turbine engine component includes a first body section along an axis, the first body section comprising a first orifice, a neck section adjacent to the first body section along the axis, and a second body section along the axis adjacent to the neck region, the second body section forming an exit along the axis.Type: GrantFiled: July 18, 2018Date of Patent: March 10, 2020Assignee: United Technologies CorporationInventors: Michael S. Stevens, David Richard Griffin
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Publication number: 20200063594Abstract: A method of making a component includes creating a computer file defining the component in layers, the component including: a body including a sealing portion; and an abradable seal extending from the sealing portion; and building the component using an additive manufacturing process that builds the component on a layer-by-layer basis such that the abradable seal is integral to the body.Type: ApplicationFiled: October 28, 2019Publication date: February 27, 2020Inventors: Michael S. Stevens, Jeffrey Vincent Anastas
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Publication number: 20200025041Abstract: A debris separator for a gas turbine engine component includes a first body section along an axis, the first body section comprising a first orifice, a neck section adjacent to the first body section along the axis, and a second body section along the axis adjacent to the neck region, the second body section forming an exit along the axis.Type: ApplicationFiled: July 18, 2018Publication date: January 23, 2020Applicant: United Technologies CorporationInventors: Michael S. Stevens, David Richard Griffin
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Publication number: 20190353043Abstract: A heat shield vane support may have a structure including at least one of a cylindrical and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face and may comprise a flange extending circumferentially about the aft face radially inward from the inboard diameter, a plurality of anti-rotation features distributed circumferentially about the inboard diameter extending radially inward from the inboard diameter and extending axially with respect to the cylindrical structure between a forward edge and an aft edge defining a length L, and a plurality of teeth distributed circumferentially about the forward face and extending axially from the forward face.Type: ApplicationFiled: May 17, 2018Publication date: November 21, 2019Applicant: United Technologies CorporationInventors: Michael S. Stevens, Christine F. McGinnis, Major D. Jones, Judith F. Brooks, Brian Duguay, Tomasz Pelic
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Patent number: 10393024Abstract: A multi-air stream cooling system is provided. The multi-air stream cooling system may comprise an inner vane support, a flow guide, and a fastened inner duct. The inner vane support may partially define a first airflow path. The flow guide may couple to the inner vane support and may partially define a second airflow path. The fastened inner duct may couple to the flow guide and may partially define a third airflow path. The inner vane support may comprise a discharge slot to allow a first airflow into a blade rim cavity. The flow guide may comprise a tangential onboard injector (TOBI) to provide a second airflow through a cover plate. The flow guide may also comprise a bypass passage configured to enable a third airflow from the third airflow path.Type: GrantFiled: August 29, 2016Date of Patent: August 27, 2019Assignee: United Technologies CorporationInventors: Michael S. Stevens, Brian C. McLaughlin
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Publication number: 20190178097Abstract: A support ring for a gas turbine engine includes a main body portion extending circumferentially about a center axis, a radially extending portion extending radially inward from the main body portion and having a plurality of openings, and a plurality of anti-rotation tabs extending radially inward from the main body portion and axially spaced from the radially extending portion.Type: ApplicationFiled: October 16, 2018Publication date: June 13, 2019Inventors: Michael S. Stevens, David Richard Griffin
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Publication number: 20190078451Abstract: A stator vane support with anti-rotation features is provided. The stator vane support may comprise an inner diameter surface opposite an outer diameter surface. The stator vane support may comprise an anti-rotation lug defining a protrusion extending inward from the inner diameter surface. The stator vane support may have a first recess defining a first void on the inner diameter surface proximate a first surface of the anti-rotation lug. The stator vane support may have a second recess defining a second void on the inner diameter surface proximate a second surface of the anti-rotation lug. The anti-rotation lug may be configured to interface with a stator vane to at least partially limit circumferential movement, and each recess may be configured to allow the stator vane to thermally expand during gas turbine engine operation.Type: ApplicationFiled: September 12, 2017Publication date: March 14, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Michael S. Stevens, Tomasz Pelic
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Patent number: 10132193Abstract: A duct assembly according to an exemplary aspect of the present disclosure includes, among other things, a casing body that extends between a flange and a wall, a first discrete cooling passage formed in the casing body and a second discrete cooling passage circumferentially spaced from the first discrete cooling passage. At least one of the first discrete cooling passage and the second discrete cooling passage includes an axial portion and a tangential portion configured to turn a cooling fluid communicated in each of the first and second discrete cooling passages.Type: GrantFiled: August 13, 2014Date of Patent: November 20, 2018Assignee: United Technologies CorporationInventors: Ken F. Blaney, Michael S. Stevens
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Patent number: 10113437Abstract: The present disclosure relates generally to a seal between two components. The seal includes a plurality of seal sections including convolutions therein that are inter-engaged with one another to form flexible and resilient seals.Type: GrantFiled: August 19, 2015Date of Patent: October 30, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Timothy M Davis, Michael S Stevens
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Publication number: 20180291759Abstract: The present disclosure relates generally to a seal between two components. The seal includes a plurality of seal sections including convolutions therein that are inter-engaged with one another to form flexible and resilient seals.Type: ApplicationFiled: June 14, 2018Publication date: October 11, 2018Inventors: Timothy M. Davis, Michael S. Stevens
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Patent number: 10088049Abstract: A seal assembly that may be for turbine engine includes first and second rings with a convoluted seal resiliently compressed there-between. The seal may define a gap for receipt of a thermally resistant shield that may also reduce wear of the seal. The seal may include a hole for the flow of cooling air and the shield may be porous so as not to obstruct the cooling air flow for cooling of the seal.Type: GrantFiled: May 5, 2015Date of Patent: October 2, 2018Assignee: United Technologies CorporationInventors: Timothy M. Davis, Michael S. Stevens
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Patent number: 9970311Abstract: A method of assembling a gas turbine engine is provided that includes locating a consumable assembly tool within the engine. The consumable assembly tool is attached to another component of the gas turbine engine. The engine is run to vaporize the consumable assembly tool.Type: GrantFiled: March 5, 2014Date of Patent: May 15, 2018Assignee: United Technologies CorporationInventors: Michael S. Stevens, Jeremy Drake, Brian Duguay, Timothy M. Davis, Ryan M. Kohn, Dairus D. McDowell, Brian McLaughlin
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Publication number: 20180058329Abstract: A multi-air stream cooling system is provided. The multi-air stream cooling system may comprise an inner vane support, a flow guide, and a fastened inner duct. The inner vane support may partially define a first airflow path. The flow guide may couple to the inner vane support and may partially define a second airflow path. The fastened inner duct may couple to the flow guide and may partially define a third airflow path. The inner vane support may comprise a discharge slot to allow a first airflow into a blade rim cavity. The flow guide may comprise a tangential onboard injector (TOBI) to provide a second airflow through a cover plate. The flow guide may also comprise a bypass passage configured to enable a third airflow from the third airflow path.Type: ApplicationFiled: August 29, 2016Publication date: March 1, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Michael S. Stevens, Brian C. McLaughlin
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Patent number: 9874111Abstract: A gas turbine engine includes a tangential on-board injector (TOBI) fluidly connected to a compressor section. A diffuser case structurally supports a combustor section and the tangential on-board injector via at least one low thermal mass joint.Type: GrantFiled: September 5, 2014Date of Patent: January 23, 2018Assignee: United Technologies CorporationInventors: Michael S. Stevens, Ken F. Blaney
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Publication number: 20170292393Abstract: A TOBI for a gas turbine engine having a TOBI body, a first TOBI airfoil having a radially extending portion extending from a leading edge and an axially extending portion extending toward a trailing edge, and a second TOBI airfoil circumferentially adjacent to the first TOBI airfoil, the second TOBI airfoil having a radially extending portion extending from a leading edge and an axially extending portion extending toward a trailing edge. An entrance is defined between the leading edges of the adjacent TOBI airfoils and an exit is defined between the trailing edges of the TOBI airfoils, wherein airflow entering the entrance enters in a radial direction relative to the TOBI body and airflow exiting the exit exits in a circumferential direction relative to the TOBI body.Type: ApplicationFiled: April 8, 2016Publication date: October 12, 2017Inventors: Jeffrey Vincent Anastas, Michael S. Stevens