Patents by Inventor Richard N. Allen
Richard N. Allen 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: 11111801Abstract: A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.Type: GrantFiled: May 21, 2014Date of Patent: September 7, 2021Assignee: Raytheon Technologies CorporationInventors: John T. Ols, Richard N. Allen, Steven D. Porter, Paul K. Sanchez, Sandra S. Pinero
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Patent number: 10641114Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.Type: GrantFiled: May 20, 2014Date of Patent: May 5, 2020Assignee: United Technologies CorporationInventors: John T. Ols, Richard N. Allen, Steven D. Porter
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Patent number: 10428666Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.Type: GrantFiled: December 12, 2016Date of Patent: October 1, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John David Forbes, Gregory Anselmi, Christina E. Botnick, Eleanor D. Kaufman, Jeffrey Leon, Jeffrey R. Levine, Gerald M. Mace, Daniel C. Nadeau, Tania Bhatia Kashyap, Richard N. Allen
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Patent number: 10329933Abstract: An engine component for isolating a first pressure and/or first flow and a second pressure and/or second flow is provided. The engine component may comprise a body portion, a first seal element and a second seal element. The body portion may include a first standoff and a second standoff. The first seal element housed within the body portion. The second seal element may also be housed within the body portion. The second seal element may be coupled to the first seal element.Type: GrantFiled: March 17, 2015Date of Patent: June 25, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Richard N. Allen, Brandon W. Spangler
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Patent number: 10132168Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.Type: GrantFiled: March 14, 2016Date of Patent: November 20, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jeffrey Leon, Daniel C. Nadeau, Jeffrey R. Levine, Eleanor D. Kaufman, Richard N. Allen, Evan P. Molony, Gregory Anselmi
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Patent number: 10107118Abstract: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.Type: GrantFiled: June 27, 2014Date of Patent: October 23, 2018Assignee: United Technologies CorporationInventors: John T Ols, Richard N Allen, Paul K Sanchez, Steven D Porter, Jonathan Lemoine
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Publication number: 20180163551Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.Type: ApplicationFiled: December 12, 2016Publication date: June 14, 2018Inventors: John David Forbes, Gregory Anselmi, Christina E. Botnick, Eleanor D. Kaufman, Jeffrey Leon, Jeffrey R. Levine, Gerald M. Mace, Daniel C. Nadeau, Tania Bhatia Kashyap, Richard N. Allen
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Patent number: 9982548Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.Type: GrantFiled: June 25, 2014Date of Patent: May 29, 2018Assignee: United Technologies CorporationInventors: John T. Ols, Karl A. Mentz, Richard N. Allen, Steven D. Porter, Renee J. Jurek, Paul K. Sanchez, Sandra S. Pinero
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Publication number: 20170260864Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.Type: ApplicationFiled: March 14, 2016Publication date: September 14, 2017Applicant: United Technologies CorporationInventors: Jeffrey Leon, Daniel C. Nadeau, Jeffrey R. Levine, Eleanor D. Kaufman, Richard N. Allen, Evan P. Molony, Gregory Anselmi
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Publication number: 20160194969Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, a radially outer platform and a radially inner platform. A rib is on one of the radially inner and radially outer platforms, and is adjacent the trailing edge of the airfoil. A mid-turbine frame is also disclosed.Type: ApplicationFiled: September 22, 2014Publication date: July 7, 2016Inventors: John T. OLS, Richard N. ALLEN, Steven D. PORTER, Paul K. SANCHEZ
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Publication number: 20160153296Abstract: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.Type: ApplicationFiled: June 27, 2014Publication date: June 2, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: John T. Ols, Richard N Allen, Paul K. Sanchez, Steven D. Porter, Jonathan Lemoine
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Publication number: 20160123166Abstract: An airfoil extends between radially inner and radially outer platforms. The airfoil extends between a leading edge and a trailing edge, and merges into facing surfaces of the radially inner and outer platforms. A variable fillet merges a facing surface of one of the radially inner and outer platforms into a wall of the airfoil. The variable fillet has a length extending away from a surface of the airfoil and a height extending away from the facing surface of at least one of the radially inner and outer platforms outwardly on to the airfoil. The variable fillet has a greater length at one of the leading edge and the trailing edge. A spaced portion has a shorter length at locations spaced from at least one of the leading and trailing edges. A mid-turbine frame and a gas turbine engine are also disclosed.Type: ApplicationFiled: June 25, 2014Publication date: May 5, 2016Inventors: John T. Ols, Karl A. Mentz, Richard N. Allen, Steven D. Porter, Renee J. Jurek, Paul K. Sanchez, Sandra S. Pinero
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Publication number: 20160069200Abstract: A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.Type: ApplicationFiled: May 21, 2014Publication date: March 10, 2016Applicant: United Technologies CorporationInventors: John T. Ols, Richard N. Allen, Steven D. Porter, Paul K. Sanchez, Sandra S. Pinero
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Publication number: 20160061046Abstract: A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.Type: ApplicationFiled: May 20, 2014Publication date: March 3, 2016Inventors: John T. Ols, Richard N. Allen, Steven D. Porter
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Publication number: 20150354385Abstract: An engine component for isolating a first pressure and/or first flow and a second pressure and/or second flow is provided. The engine component may comprise a body portion, a first seal element and a second seal element. The body portion may include a first standoff and a second standoff. The first seal element housed within the body portion. The second seal element may also be housed within the body portion. The second seal element may be coupled to the first seal element.Type: ApplicationFiled: March 17, 2015Publication date: December 10, 2015Applicant: United Technologies CorporationInventors: Richard N. Allen, Brandon W. Spangler