Patents by Inventor Edwin Otero
Edwin Otero 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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Publication number: 20190136699Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.Type: ApplicationFiled: November 7, 2017Publication date: May 9, 2019Applicant: United Technologies CorporationInventors: Brandon W. Spangler, Edwin Otero, David R. Pack
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Publication number: 20190136716Abstract: A component for a gas turbine engine is disclosed. The component includes a platform and a rail having an outer radial surface and an inner radial surface, with the inner radial surface connected to the platform. The rail includes a plurality of apertures spaced circumferentially between the outer radial surface and the inner radial surface, the apertures disposed to form a truss-like structure.Type: ApplicationFiled: November 8, 2017Publication date: May 9, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: BRANDON W. SPANGLER, JOSE R. PAULINO, CRAIG R. McGARRAH, EDWARD R. BAREISS, EDWIN OTERO
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Publication number: 20190010810Abstract: An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour.Type: ApplicationFiled: September 10, 2018Publication date: January 10, 2019Inventors: Daniel A. Snyder, Jaimie Schweitzer, Jonathan Perry Sandoval, Edwin Otero, Kyle C. Lana, Scott D. Virkler
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Patent number: 10113434Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.Type: GrantFiled: January 31, 2012Date of Patent: October 30, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Daniel A. Snyder, Kyle Charles Lana, Jonathan Perry Sandoval, Scott Daniel Virkler, Jaimie Taraskevich, Edwin Otero
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Patent number: 10107107Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an body portion that extends between a leading edge and a trailing edge. At least one of the leading edge and the trailing edge includes at least one discharge slot having a first portion that includes an oval geometry.Type: GrantFiled: August 30, 2012Date of Patent: October 23, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Mark A. Boeke, Edwin Otero, Jeffrey J. DeGray, Tracy A. Propheter-Hinckley, Guillermo J. Fernandez, Sarah Riley
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Patent number: 9963991Abstract: A brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin.Type: GrantFiled: September 14, 2015Date of Patent: May 8, 2018Assignee: United Technologies CorporationInventors: Ross Wilson, Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John W. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Edwin Otero, Alan W. Stoner
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Publication number: 20180099362Abstract: A method of manufacturing an airfoil. The method includes fixing the airfoil in a workpiece space, detecting a position of the airfoil in the workpiece space using a force-sensing element, and removing material from the airfoil to reduce a dimension of the airfoil. In various embodiments, detecting the position of the airfoil includes moving the force-sensing element across a surface of the airfoil. For example, the surface of the airfoil may be a first surface, wherein removing material from the airfoil to reduce the dimension of the airfoil comprises removing material from a second surface of the airfoil opposite the first surface. Removing material from the second surface of the airfoil may be performed without moving the force-sensing element across the second surface of the airfoil.Type: ApplicationFiled: October 10, 2016Publication date: April 12, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Eric A. Hudson, Alan C. Barron, Edwin Otero
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Patent number: 9863257Abstract: A damper-seal assembly for a gas turbine engine includes an additively manufactured seal and an additively manufactured damper inseparably assembled with the additively manufactured seal.Type: GrantFiled: February 4, 2015Date of Patent: January 9, 2018Assignee: United Technologies CorporationInventors: Daniel A Snyder, Edwin Otero, Lexia Kironn, Wendell V Twelves, Jr., Evan Butcher
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Patent number: 9726023Abstract: In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.Type: GrantFiled: January 26, 2015Date of Patent: August 8, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, Edwin Otero, Daniel A. Snyder, Jaimie Taraskevich, Di Wu
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Publication number: 20160222798Abstract: A damper-seal assembly for a gas turbine engine includes an additively manufactured seal and an additively manufactured damper inseparably assembled with the additively manufactured seal.Type: ApplicationFiled: February 4, 2015Publication date: August 4, 2016Inventors: Daniel A. Snyder, Edwin Otero, Lexia Kironn, Wendell V. Twelves, JR., Evan Butcher
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Publication number: 20160222796Abstract: A blade includes a platform and a monolithic airfoil extending from the platform to a tip. The airfoil includes a first wall extending from a leading edge to a trailing edge, a second wall extending from the leading edge to the trailing edge and joined to the first wall at the leading edge, and at least one rib extending from the first wall to the second wall. The at least one rib and the first and second walls define a cavity. The blade also includes a baffle positioned within the cavity. The baffle has walls that are separate and distinct from and not attached to the at least one rib and the first and second walls of the airfoil. A method for forming a blade includes forming a platform and forming an airfoil and a baffle within the airfoil on a layer-by-layer basis using additive manufacturing.Type: ApplicationFiled: September 16, 2014Publication date: August 4, 2016Applicant: United Technologies CorporationInventors: Brandon W. Spangler, Edwin Otero
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Publication number: 20160215628Abstract: In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.Type: ApplicationFiled: January 26, 2015Publication date: July 28, 2016Applicant: United Technologies CorporationInventors: Brandon W. Spangler, Edwin Otero, Daniel A. Snyder, Jaimie Taraskevich, Di Wu
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Publication number: 20160208621Abstract: A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.Type: ApplicationFiled: August 27, 2014Publication date: July 21, 2016Inventors: Brandon W. Spangler, Edwin Otero
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Publication number: 20160201477Abstract: A gas turbine engine component includes spaced apart walls that provide a cooling passage that extends in a first direction. A cross-over rib joins the walls and extends along the first direction. The cross-over rib has holes that extend in a second direction transverse to the first direction. A row of at least one pedestal joins the walls and extends along the first direction. The row and the cross-over rib overlap one another in the second direction.Type: ApplicationFiled: August 13, 2014Publication date: July 14, 2016Inventors: Edwin Otero, Kyle C. Lana
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Publication number: 20160130963Abstract: The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least two beams. An anti-vibration beam spacer is disposed in contact with two adjacent beams and operative to mitigate an externally induced vibratory response of the beams.Type: ApplicationFiled: August 19, 2015Publication date: May 12, 2016Inventors: Ross Wilson, Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, Edwin Otero, John E. Paul
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Publication number: 20160115804Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.Type: ApplicationFiled: October 23, 2015Publication date: April 28, 2016Inventors: Ross Wilson, Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Alan W. Stoner, Edwin Otero
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Publication number: 20160115825Abstract: A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.Type: ApplicationFiled: October 23, 2015Publication date: April 28, 2016Inventors: Ross Wilson, Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Alan W. Stoner, Edwin Otero
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Publication number: 20160109025Abstract: A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.Type: ApplicationFiled: September 14, 2015Publication date: April 21, 2016Applicant: United Technologies CorporationInventors: Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Ross Wilson, Edwin Otero, Alan W. Stoner
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Publication number: 20160102570Abstract: Non-contacting dynamic seals having wave springs are disclosed herein. A non-contacting dynamic seal may have a shoe coupled to an outer ring by an inner beam and an outer beam. A wave spring may be located between the inner beam and the outer beam, between the shoe and the inner beam, or between the outer beam and the outer ring. The wave spring may damp vibrations in the inner beam and the outer beam.Type: ApplicationFiled: September 14, 2015Publication date: April 14, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Ross Wilson, John R. Farris, Michael G. McCaffrey, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Edwin Otero, Alan W. Stoner
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Publication number: 20160097294Abstract: A brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin.Type: ApplicationFiled: September 14, 2015Publication date: April 7, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Ross Wilson, Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John W. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Edwin Otero, Alan W. Stoner