Patents by Inventor Jonathan Jeffery Eastwood
Jonathan Jeffery Eastwood 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: 20190292915Abstract: A strut for a gas turbine engine includes an airfoil section extending in a spanwise direction between a first platform and a second platform, extending in a chordwise direction between a leading edge and trailing edge to define a chord length, and extending in a thickness direction between a first side and a second side to define a chord width. Exterior surfaces of the airfoil section define a leading portion between the leading edge and a widest location of the airfoil section relative to the thickness direction, and a trailing portion between the widest location and the trailing edge. The exterior surfaces establish a respective exterior contour for each span position between a 0% span position and a 100% span position. The exterior surfaces define a plurality of dimples in the leading portion.Type: ApplicationFiled: March 22, 2018Publication date: September 26, 2019Inventors: Jonathan Jeffery Eastwood, Curtis L. Memory, Jin Hu, Thomas J. Praisner
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Patent number: 10344623Abstract: A pre-diffuser of an inner diffuser case of a gas turbine engine may comprise an annular outer wall and an annular inner wall radially inside of the annular outer wall to define a passage for primary airflow therebetween. The pre-diffuser may further comprise at least one strut extending radially between the annular inner wall and the annular outer wall and at least one aperture formed in the strut that extends radially through the strut, the annular inner wall, and the annular outer wall. The pre-diffuser may further comprise at least one hollow cavity formed in the strut, and the hollow cavity may be separate from the aperture.Type: GrantFiled: November 6, 2015Date of Patent: July 9, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jonathan Jeffery Eastwood, Dave J. Hyland, Timothy Dale
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Patent number: 10288289Abstract: An inner casing for a diffuser-combustor assembly of a gas turbine engine is disclosed. The inner casing may include an outer-ring, an inner-ring circumscribed by the outer-ring, and a strut having a body extending between the inner-ring and the outer-ring. In addition, the inner casing may include a reinforcing-pad.Type: GrantFiled: November 3, 2015Date of Patent: May 14, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jonathan Jeffery Eastwood, Dave J. Hyland, Timothy Dale
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Patent number: 10260750Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface defining a combustion chamber, a first panel mounted to the interior surface at a first position, the first panel having a first surface and a first rail extending from the first surface toward the combustor shell, the first rail configured at a first angle relative to the first surface, and a second panel mounted to the interior surface at a second position axially adjacent to the first panel, the second panel having a second surface and a second rail extending from the second surface toward the combustor shell, the second rail configured at a second angle relative to the second surface. The first and second rails are proximal to each other and define a circumferential gap there between and at least one of the first or second angles is an acute angle.Type: GrantFiled: December 29, 2015Date of Patent: April 16, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John S. Tu, James B. Hoke, Jonathan Jeffery Eastwood, Kevin Joseph Low, Sean D. Bradshaw
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Publication number: 20190078457Abstract: A gas turbine engine sealing system includes a case including forward and aft hooks. The aft hook arranged radially outward of the forward hook. A blade outer air seal has a J-hook that receives the aft hook and includes an end received by the forward hook.Type: ApplicationFiled: September 11, 2017Publication date: March 14, 2019Inventors: Jonathan Jeffery Eastwood, Joseph F. Englehart, Christopher Carter Venable, Michael G. McCaffrey
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Publication number: 20190078459Abstract: A method of controlling a power turbine running clearance between blade tips and a case structure. The method includes the step of adjusting an active clearance control system fluid flow based upon a power turbine speed to obtain a desired running clearance in a power turbine.Type: ApplicationFiled: September 11, 2017Publication date: March 14, 2019Inventors: Jonathan Jeffery Eastwood, Joseph F. Englehart, Graham Ryan Philbrick
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Publication number: 20190078458Abstract: An active clearance control manifold assembly includes multiple arcuate manifold segments each having multiple circumferential channels axially spaced apart from one another. The circumferential channels include cooling holes facing radially inward. A tube at least partially circumscribes and fluidly interconnects the manifold segments.Type: ApplicationFiled: September 11, 2017Publication date: March 14, 2019Inventors: Jonathan Jeffery Eastwood, Joseph F. Englehart, Graham Ryan Philbrick, ChaiDee Woods Brown
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Publication number: 20190078514Abstract: A turbine section for a gas turbine engine includes blade outer air seals and stator vanes that provide a core flow path. A turbine case supports blade outer air seals and stator vanes. An annular cavity is provided between an interior surface of the turbine case and the blade outer air seals and the stator vanes. A hole extends through the turbine case from an exterior surface to the interior surface. The annular cavity extends axially to an exit. A manifold circumscribes the exterior surface of the turbine case and provides an annular space therebetween. The annular space is in fluid communication with the exit of the annular cavity via the hole.Type: ApplicationFiled: September 11, 2017Publication date: March 14, 2019Inventors: Jonathan Jeffery Eastwood, Joseph F. Englehart, Graham Ryan Philbrick, Henry K. Webster, Richard Seleski, ChaiDee Woods Brown, Michael G. McCaffrey
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Patent number: 10215411Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.Type: GrantFiled: March 7, 2016Date of Patent: February 26, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John S. Tu, James B. Hoke, David Kwoka, Jonathan Jeffery Eastwood
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Patent number: 10161414Abstract: A pre-diffuser and exit guide vane (EGV) system for a gas turbine engine includes an annular EGV assembly containing a number of guide vanes and having an annular opening bounded by a radially inner annular sealing surface at a first radius and a radially outer annular sealing surface at a second radius. First and second seals substantially matching the first and second radii respectively join the EGV assembly to an annular pre-diffuser having an annular opening bounded by radially inner and outer annular sealing surfaces at substantially the first and second radii. The seals seal the inner sealing surface of the EGV assembly to the inner sealing surface of the pre-diffuser and the second seal seals the outer sealing surface of the EGV assembly to the outer sealing surface of the pre-diffuser, such that the EGV assembly annular opening is in fluid communication with the annular opening of the pre-diffuser.Type: GrantFiled: November 9, 2015Date of Patent: December 25, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jonathan Jeffery Eastwood, Dave J. Hyland, Timothy Dale, Matthew R. Willett
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Publication number: 20180283690Abstract: A combustor panel may include a combustion facing surface, a cooling surface opposite the combustion facing surface, a first heat transfer pin extending from the cooling surface having a first geometric specification, and a second heat transfer pin extending from the cooling surface having a second geometric specification. The first geometric specification may be different than the second geometric specification. The first geometric specification may be a first height of the first pin and the second geometric specification may be a second height of the second pin.Type: ApplicationFiled: March 29, 2017Publication date: October 4, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: JONATHAN LEMOINE, KEVIN ZACCHERA, JONATHAN JEFFERY EASTWOOD
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Patent number: 10087767Abstract: A pre-diffuser may include a plurality of struts, and each strut may have a leading edge. An upper contour of the leading edge may have a forward end and an aft end, and may include a first radius and a second radius. The first and second radii may be associated with the forward end and the aft end, respectively. The first radius may also be located farther forward than the second radius, and may be larger than the second radius.Type: GrantFiled: November 3, 2015Date of Patent: October 2, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jonathan Jeffery Eastwood, Dave J. Hyland, Timothy Dale
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Patent number: 10041364Abstract: An inner diffuser case for a gas turbine engine may include a pre-diffuser including a plurality of struts. At least one of the struts may include an aperture therethrough. A cone may have a downstream end coupled to the pre-diffuser downstream of, and proximate to, the aperture. A skirt may have a forward end coupled to the pre-diffuser downstream of, and proximate to, the aperture. The forward end of the skirt may be axially aligned with the downstream end of the cone.Type: GrantFiled: November 3, 2015Date of Patent: August 7, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jonathan Jeffery Eastwood, Dave J. Hyland, Timothy Dale
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Publication number: 20180128485Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a stud free zone downstream of a combustor swirler. A combustor for a gas turbine engine, the combustor including a liner panel mounted to the support shell via a multiple of studs, the liner panel including a stud free zone downstream of each respective combustor swirler, the stud free zone including a multiple of film cooling holes. A method of directing airflow through a wall assembly within a combustor of a gas turbine engine including providing a stud free zone in a forward liner panel downstream of a combustor swirler, the stud free zone including a multiple of film cooling holes.Type: ApplicationFiled: November 4, 2016Publication date: May 10, 2018Applicant: United Technologies CorporationInventors: Jonathan Jeffery Eastwood, Monica Pacheco-Tougas, Kevin Zacchera
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Publication number: 20180112877Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a radiused edge blended into a hot side of the linear panel. A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a radiused edge blended into a hot side of the linear panel, the hot side including a thermal barrier coating. A method of manufacturing including casting a radiused edge blended into a hot side of a linear panel; and applying a thermal barrier coating to the hot side of the liner panel.Type: ApplicationFiled: October 26, 2016Publication date: April 26, 2018Applicant: United Technologies CorporationInventors: Jonathan Jeffery Eastwood, Kevin Zacchera, Brian T. Hazel, William F. Werkheiser
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Publication number: 20180112597Abstract: A combustor seal for use in a combustor of a gas turbine engine including a seal with a multiple of slots that correspond with a multiple of 1st HPT vanes. A method of cooling within a gas turbine engine including communicating cooling air through combustor seal toward each of a multiple of 1st HPT vanes.Type: ApplicationFiled: October 26, 2016Publication date: April 26, 2018Applicant: United Technologies CorporationInventors: Jonathan Jeffery Eastwood, Dennis M. Moura
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Publication number: 20180112876Abstract: A liner panel for use in a combustor of a gas turbine engine, the liner panel includes a radiused gate blended into a hot side of the liner panel. A combustor for a gas turbine engine including a liner panel mounted to a support shell via a multiple of studs, the liner panel including a radiused gate blended into a hot side of the liner panel, the hot side including a thermal barrier coating. A method of manufacturing including casting a radiused gate tangentially cast into a hot side of a liner panel; and applying a thermal barrier coating to the hot side of the liner panel over the remnants of the radiused gate.Type: ApplicationFiled: October 26, 2016Publication date: April 26, 2018Applicant: United Technologies CorporationInventors: Jonathan Jeffery Eastwood, Kevin Zacchera, Brian T. Hazel, William F. Werkheiser
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COMBUSTOR LINER PANEL WITH A MULTIPLE OF HEAT TRANSFER AUGMENTORS FOR A GAS TURBINE ENGINE COMBUSTOR
Publication number: 20180112878Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer augmentors located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer augmentors located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer augmentors define a height that extends about half the distance between a cold surface of the liner panel and the support shell.Type: ApplicationFiled: October 26, 2016Publication date: April 26, 2018Applicant: United Technologies CorporationInventors: Monica Pacheco-Tougas, Kevin Zacchera, Jonathan Jeffery Eastwood -
Publication number: 20180094545Abstract: A flange heat shield is provided. The flange heat shield may comprise an annular body having a forward end opposite an aft end. The forward end of the flange heat shield may comprise a radial snap configured to interface with an inner surface of an engine case. The inner surface of the engine case may comprise an airflow ramp forward of the radial snap. The aft end of the flange heat shield may comprise a plurality of notches defining voids on the aft end. The aft end of the flange heat shield may also comprise mounting tabs configured to couple the flange heat shield to the engine case.Type: ApplicationFiled: October 4, 2016Publication date: April 5, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Timothy Dale, Jonathan Jeffery Eastwood
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Publication number: 20170254538Abstract: A combustor of a gas turbine engine including a combustor shell having an interior surface, a first panel mounted to the interior surface at a first position and a second panel mounted to the interior surface at a second position. The first panel has a first end, a first combustion chamber surface parallel with the interior surface, a first rail extending from the first combustion chamber surface toward the interior surface of the combustor shell, and a first extension extending axially from the first rail to the end of the first panel. The second panel has a second end, a second combustion chamber surface, and a second rail extending from the second combustion chamber surface toward the interior surface of the combustor shell. The first end and the second end are proximal to each other and define a circumferentially extending gap there between.Type: ApplicationFiled: March 7, 2016Publication date: September 7, 2017Inventors: John S. Tu, James B. Hoke, David Kwoka, Jonathan Jeffery Eastwood