Patents by Inventor Thomas N. Slavens

Thomas N. Slavens 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).

ENHANCED COOLING FOR BLADE TIP

Publication number: 20160298463

Abstract: In a featured embodiment, a gas turbine engine component comprises an airfoil having a leading edge, a trailing edge, and pressure and suction side walls extending from the leading edge to the trailing edge. The airfoil extends from a base to a tip. A shelf is formed in the tip, and extends from the pressure side wall, around the leading edge, to the suction side wall.

Type: Application

Filed: November 5, 2014

Publication date: October 13, 2016

Applicant: United Technologies corporation

Inventors: James T. Auxier, Thomas N. Slavens, Brandon S. Donnell, Yafet Girma
A METHOD FOR PROVIDING COOLANT TO A MOVABLE AIRFOIL

Publication number: 20160298484

Abstract: A gas turbine engine with an adjustable vane includes a platform with a hole and an aperture. A vane is supported for rotation relative to the platform by a trunion that is received in the hole. The vane has an opening that is laterally spaced from the trunion and is in alignment with the aperture. The vane includes an airfoil with a cooling passage in fluid communication with the opening.

Type: Application

Filed: November 3, 2014

Publication date: October 13, 2016

Inventors: John D. Teixeira, Thomas N. Slavens, Raymond Surace
COOLING PASSAGES FOR A GAS TURBINE ENGINE COMPONENT

Publication number: 20160298462

Abstract: A gas turbine engine component includes a wall which includes a first surface and a second surface opposing the first surface. A plurality of cooling passages extends between the first surface and the second surface each including a metering portion and a diffusion portion. The diffusion portion includes a cast or as-consolidated surface.

Type: Application

Filed: April 9, 2015

Publication date: October 13, 2016

Inventors: Lane Thornton, Thomas N. Slavens
AIRFOIL CONTOUR FOR LOW-LOSS ON-BOARDING OF COOLING AIR THROUGH AN ARTICULATING SPINDLE

Publication number: 20160290158

Abstract: A turbine stator vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about an axis transverse to an engine longitudinal axis. The airfoil includes outer walls defining an inner chamber between a pressure side and a suction side of the airfoil. At least one spindle supports rotation of the airfoil and includes a feed opening for communicating cooling air into the inner chamber. An inlet defines a passage between the feed opening and the inner chamber and includes a protrusion of the outer wall on at least one of the pressure side and suction side of the airfoil.

Type: Application

Filed: November 3, 2014

Publication date: October 6, 2016

Applicant: United Technologies Corporation

Inventors: Thomas N. Slavens, Eric A. Grover, John D. Teixeira
GAS TURBINE ENGINE COMPONENT COOLING PASSAGE TURBULATOR

Publication number: 20160290139

Abstract: A gas turbine engine component includes opposing walls that provide an interior cooling passage. One of the walls has a turbulator with a hook that is enclosed within the walls.

Type: Application

Filed: November 5, 2014

Publication date: October 6, 2016

Inventors: Brooks E. Snyder, Thomas N. Slavens, Nicholas M. LoRicco, James T. Auxier
FLOWING MATEFACE SEAL

Publication number: 20160281521

Abstract: Aspects of the disclosure are directed to a first platform, a second platform, a seal arranged between the first platform and the second platform, a first slot in the first platform with unequal seal rates between inner and outer sealing surfaces, and a second slot in the second platform with unequal seal rates between the inner and outer sealing surfaces, wherein the seal is configured to be positioned in the inner or outer sealing surfaces based on a ratio of a first pressure associated with a first flow to a second pressure associated with a second flow.

Type: Application

Filed: March 23, 2015

Publication date: September 29, 2016

Inventors: Carey Clum, Thomas N. Slavens, Christopher Whitfield
Gas turbine engine turbine blade tip cooling

Patent number: 9453419

Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A camber line at the tip extends from the leading edge to the trailing edge. Pressure and suction side shelves are arranged in the exterior surface on opposing sides of the camber line respectively in the pressure and suction side walls. A plateau is proud of and separates the pressure and suction side shelves. The plateau is arranged along the camber line and extends to the leading edge.

Type: Grant

Filed: December 28, 2012

Date of Patent: September 27, 2016

Assignee: UNITED TECHNOLOGIES CORPORATION

Inventors: James T. Auxier, Jason L. O'Hearn, Thomas N. Slavens, Yafet Girma
GAS TURBINE ENGINE AIRFOIL WITH LEADING EDGE TRENCH AND IMPINGEMENT COOLING

Publication number: 20160273365

Abstract: A gas turbine engine airfoil includes an airfoil structure including an exterior surface that is provided by an exterior wall that has a leading edge. A radially extending interior wall within the airfoil structure separates first and second radial cooling passages. The first cooling passage is arranged near the leading edge. A radially extending trench is in the leading edge. An impingement hole is provided in the interior wall and is configured to direct a cooling fluid from the second cooling passage to the first cooling passage and onto the exterior wall at the leading edge.

Type: Application

Filed: November 5, 2014

Publication date: September 22, 2016

Inventors: Thomas N. Slavens, Brooks E. Snyder
GAS TURBINE ENGINE TURBINE BLADE TIP COOLING

Publication number: 20160265366

Abstract: A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by the overhang.

Type: Application

Filed: October 10, 2014

Publication date: September 15, 2016

Inventors: Brooks E. Snyder, Thomas N. Slavens
MULTIPLE PIECE ENGINE COMPONENT

Publication number: 20160265362

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.

Type: Application

Filed: October 17, 2014

Publication date: September 15, 2016

Applicant: UnitedTechnologies Corporation

Inventors: Thomas N. Slavens, Mark F. Zelesky
FLUIDIC MACHINING METHOD AND SYSTEM

Publication number: 20160258299

Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.

Type: Application

Filed: November 14, 2014

Publication date: September 8, 2016

Inventors: Sasha M. Moore, Thomas N. Slavens, Nicholas M. Loricco, Timothy J. Jennings
INCIDENT TOLERANT TURBINE VANE GAP FLOW DISCOURAGEMENT

Publication number: 20160251980

Abstract: A turbine vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about a first axis transverse to an engine longitudinal axis. The airfoil includes an endwall and at least one protrusion disposed on the endwall configured for obstructing flow through a gap between the endwall and a static structure of the gas turbine engine.

Type: Application

Filed: October 17, 2014

Publication date: September 1, 2016

Inventors: Thomas N. Slavens, Steven Bruce Gautschi
INCIDENT TOLERANT TURBINE VANE COOLING

Publication number: 20160251974

Abstract: A disclosed turbine vane assembly for a gas turbine engine includes an airfoil including a pressure side and a suction side that extends from a leading edge toward a trailing edge. The airfoil is rotatable about an axis transverse to an engine longitudinal axis and includes a forward chamber within the airfoil and in communication with a cooling air source, a forward impingement baffle defining a pre-impingement cavity within the forward chamber. The pre-impingement cavity is split into a leading edge cavity, pressure side cavity and a suction side cavity defined between an inner surface of the forward chamber and an outer surface of the forward impingement baffle.

Type: Application

Filed: October 17, 2014

Publication date: September 1, 2016

Inventors: Thomas N. Slavens, Matthew A. Devore
ANTI-DEFLECTION FEATURE FOR ADDITIVELY MANUFACTURED THIN METAL PARTS AND METHOD OF ADDITIVELY MANUFACTURING THIN METAL PARTS

Publication number: 20160237848

Abstract: A conduction riser additively manufactured onto thin metal parts, the conduction riser extending in a build direction of the thin metal part and traversing the thin metal part as the conduction riser extends in the build direction. The conduction riser transferring heat from the upper layers of additively manufactured part during manufacturing, preventing thermal deflection of the part.

Type: Application

Filed: February 12, 2015

Publication date: August 18, 2016

Inventors: Thomas N. Slavens, Brooks E. Snyder
PEDESTALS WITH HEAT TRANSFER AUGMENTER

Publication number: 20160230664

Abstract: A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.

Type: Application

Filed: October 16, 2014

Publication date: August 11, 2016

Inventors: San Quach, Thomas N. Slavens
COOLING CONFIGURATION FOR ENGINE COMPONENT

Publication number: 20160222793

Abstract: This disclosure relates to a gas turbine engine. The engine includes a component having a first wall and a second wall spaced-apart from the first wall. The component further includes a cooling passageway provided in part by a helical wall between the first wall and the second wall.

Type: Application

Filed: September 9, 2014

Publication date: August 4, 2016

Inventors: Brooks E. Snyder, Thomas N. Slavens
INCIDENCE TOLERANT ENGINE COMPONENT

Publication number: 20160222794

Abstract: This disclosure relates to a gas turbine engine including a component having a leading edge, a pressure side and a suction side opposite the pressure side. The component includes a first group of showerhead holes in the leading edge and a second group of showerhead holes in one of the pressure side and the suction side. The component further includes a first core passageway and a second core passageway separate from the first core passageway. The first core passageway and the second core passageway are in communication with a respective one of the first group of showerhead holes and the second group of showerhead holes.

Type: Application

Filed: September 9, 2014

Publication date: August 4, 2016

Inventors: Thomas N. Slavens, Mark F. Zelesky, Atul Kohli, Sean D. Bradshaw, Steven Bruce Gautschi
Turbine Airfoil Cooling Core Exit

Publication number: 20160222795

Abstract: A gas turbine engine component has an airfoil extending from a platform to a tip at an end of the airfoil spaced from the platform. The airfoil has a suction wall and a pressure wall, with at least one channel extending toward the tip from the platform. A plenum communicates with the at least one channel. The plenum flows from the suction wall toward the pressure wall at the tip to communicate with cooling holes near the pressure wall. The plenum has a reduced cross-sectional area between the suction wall and the pressure wall, and an increase in cross-sectional area downstream of the reduced cross-sectional area. A mold core is also disclosed.

Type: Application

Filed: September 24, 2014

Publication date: August 4, 2016

Inventors: San Quach, Thomas N. Slavens
ROTATING TURBINE VANE BEARING COOLING

Publication number: 20160222825

Abstract: A pivoting turbine vane has an airfoil, an inner bearing race and an outer bearing race, with the inner and outer bearing races on a pivot axis of the pivoting turbine vane. There are cooling air passages through at least one of the inner and outer bearing races to provide cooling air from a remote facing face of at least one of the inner and outer bearing races to an airfoil facing face of at least one of the inner and outer bearing races. A turbine section is also disclosed.

Type: Application

Filed: September 22, 2014

Publication date: August 4, 2016

Inventors: Thomas N. Slavens, Steven Bruce Gautschi
SEAL FOR GAS TURBINE ENGINE

Publication number: 20160215644

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal between the mate face of the first engine component and the mate face of the second engine component. The seal establishes three points of contact with each mate face in at least one condition.

Type: Application

Filed: August 29, 2014

Publication date: July 28, 2016

Inventors: Brooks E. Snyder, Thomas N. Slavens, Mosheshe Camara-Khary Blake

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