Inventor · disambiguated record
Scott D. Lewis
Also filed as: LEWIS SCOTT D
40 granted patents·8 pending applications·124 citations·filing 2012–2020
97Inventor score
Files withUNITED TECHNOLOGIES CORP39RAYTHEON TECH CORP4ZELESKY MARK F2BEATTIE JEFFREY S1LEWIS SCOTT D1
Top patents by PatentIndex Score
48 records- 0198US11168570B1Cooling arrangement for gas turbine engine componentsRAYTHEON TECH CORP·Filed 2020·Granted Nov 9, 2021·7 cites·20 claims
- 0295US9284845B2Turbine airfoil tip shelf and squealer pocket coolingUNITED TECHNOLOGIES CORP·Filed 2014·Granted Mar 15, 2016·19 cites·13 claims
- 0393US10677066B2Turbine blade with airfoil tip vortex controlUNITED TECHNOLOGIES CORP·Filed 2016·Granted Jun 9, 2020·8 cites·20 claims
- 0493US8584470B2Tri-lobed cooling hole and method of manufactureZELESKY MARK F·Filed 2012·Granted Nov 19, 2013·15 cites·23 claims
- 0591US10077667B2Turbine airfoil film cooling holesUNITED TECHNOLOGIES CORP·Filed 2015·Granted Sep 18, 2018·6 cites·19 claims
- 0690US10156144B2Turbine airfoil and method of coolingUNITED TECHNOLOGIES CORP·Filed 2015·Granted Dec 18, 2018·6 cites·19 claims
- 0790US9822658B2Grooved seal arrangement for turbine engineUNITED TECHNOLOGIES CORP·Filed 2015·Granted Nov 21, 2017·5 cites·16 claims
- 0889US11029027B2Dilution/effusion hole pattern for thick combustor panelsUNITED TECHNOLOGIES CORP·Filed 2018·Granted Jun 8, 2021·5 cites·17 claims
- 0988US10801325B2Turbine blade with tip vortex control and tip shelfUNITED TECHNOLOGIES CORP·Filed 2017·Granted Oct 13, 2020·5 cites·19 claims
- 1088US10208603B2Staggered crossovers for airfoilsUNITED TECHNOLOGIES CORP·Filed 2015·Granted Feb 19, 2019·5 cites·23 claims
- 1188US10145246B2Staggered crossovers for airfoilsUNITED TECHNOLOGIES CORP·Filed 2015·Granted Dec 4, 2018·6 cites·21 claims
- 1287US10773344B2Systems and methods for manufacturing film cooling hole diffuser portionUNITED TECHNOLOGIES CORP·Filed 2017·Granted Sep 15, 2020·4 cites·4 claims
- 1387US10502066B2Turbine engine component including an axially aligned skin core passage interrupted by a pedestalUNITED TECHNOLOGIES CORP·Filed 2015·Granted Dec 10, 2019·4 cites·15 claims
- 1484US10041356B2Showerhead hole scheme apparatus and systemUNITED TECHNOLOGIES CORP·Filed 2015·Granted Aug 7, 2018·4 cites·15 claims
- 1582US10422230B2Cooling hole with curved metering sectionUNITED TECHNOLOGIES CORP·Filed 2016·Granted Sep 24, 2019·3 cites·18 claims
- 1680US9982542B2Airfoil platform impingement cooling holesUNITED TECHNOLOGIES CORP·Filed 2015·Granted May 29, 2018·3 cites·18 claims
- 1776US11352902B2Cooling arrangement including alternating pedestals for gas turbine engine componentsRAYTHEON TECH CORP·Filed 2020·Granted Jun 7, 2022·1 cites·20 claims
- 1875US10392943B2Film cooling hole including offset diffuser portionUNITED TECHNOLOGIES CORP·Filed 2016·Granted Aug 27, 2019·2 cites·18 claims
- 1972US10100645B2Trailing edge cooling configuration for a gas turbine engine airfoilLEWIS SCOTT D·Filed 2012·Granted Oct 16, 2018·6 cites·3 claims
- 2070US10815788B2Turbine blade with slot film coolingUNITED TECHNOLOGIES CORP·Filed 2017·Granted Oct 27, 2020·1 cites·16 claims
- 2167US11407065B2Systems and methods for manufacturing film cooling hole diffuser portionRAYTHEON TECH CORP·Filed 2020·Granted Aug 9, 2022·0 cites·19 claims
- 2263US11143039B2Turbine engine component including an axially aligned skin core passage interrupted by a pedestalRAYTHEON TECH CORP·Filed 2019·Granted Oct 12, 2021·0 cites·9 claims
- 2362US10815803B2BOAS thermal protectionUNITED TECHNOLOGIES CORP·Filed 2019·Granted Oct 27, 2020·0 cites·20 claims
- 2462US10323524B2Axial skin core cooling passage for a turbine engine componentUNITED TECHNOLOGIES CORP·Filed 2015·Granted Jun 18, 2019·1 cites·29 claims
- 2562US10053992B2Gas turbine engine airfoil squealer pocket cooling hole configurationUNITED TECHNOLOGIES CORP·Filed 2015·Granted Aug 21, 2018·1 cites·14 claims
- 2662US9243500B2Turbine blade platform with U-channel cooling holesZELESKY MARK F·Filed 2012·Granted Jan 26, 2016·2 cites·15 claims
- 2760US10227875B2Gas turbine engine component with combined mate face and platform coolingUNITED TECHNOLOGIES CORP·Filed 2014·Granted Mar 12, 2019·2 cites·14 claims
- 2860US10180067B2Mate face cooling holes for gas turbine engine componentBEATTIE JEFFREY S·Filed 2012·Granted Jan 15, 2019·2 cites·19 claims
- 2958US10408071B2BOAS thermal protectionUNITED TECHNOLOGIES CORP·Filed 2014·Granted Sep 10, 2019·1 cites·20 claims
- 3058US10001023B2Grooved seal arrangement for turbine engineUNITED TECHNOLOGIES CORP·Filed 2017·Granted Jun 19, 2018·0 cites·25 claims
- 3151US11306919B2Combustor panel cooling hole arrangementUNITED TECHNOLOGIES CORP·Filed 2018·Granted Apr 19, 2022·0 cites·15 claims
- 3249US10400607B2Large-footprint turbine cooling holeUNITED TECHNOLOGIES CORP·Filed 2015·Granted Sep 3, 2019·0 cites·26 claims
- 3348US10533428B2Oblong purge holesUNITED TECHNOLOGIES CORP·Filed 2017·Granted Jan 14, 2020·0 cites·18 claims
- 3446US10577936B2Mateface surfaces having a geometry on turbomachinery hardwareUNITED TECHNOLOGIES CORP·Filed 2014·Granted Mar 3, 2020·0 cites·10 claims
- 3545US11286809B2Airfoil platform cooling channelsUNITED TECHNOLOGIES CORP·Filed 2017·Granted Mar 29, 2022·0 cites·18 claims
- 3645US11286787B2Gas turbine engine airfoil with showerhead cooling holes near leading edgeUNITED TECHNOLOGIES CORP·Filed 2016·Granted Mar 29, 2022·0 cites·3 claims
- 3744US11156117B2Seal arc segment with sloped circumferential sidesUNITED TECHNOLOGIES CORP·Filed 2016·Granted Oct 26, 2021·0 cites·20 claims
- 3844US10513931B2Cooling systems and internally-cooled engine parts having an impingement cavity with an undulating internal surfaceUNITED TECHNOLOGIES CORP·Filed 2015·Granted Dec 24, 2019·0 cites·17 claims
- 3944US2018306038A1Airfoil impingement cavityUNITED TECHNOLOGIES CORP·Filed 2018·Application pending·0 cites
- 4044US2017022839A1Gas turbine engine component mateface surfacesUNITED TECHNOLOGIES CORP·Filed 2014·Application pending·0 cites
- 4142US10364680B2Gas turbine engine component having platform trenchTELLER BRET M·Filed 2012·Granted Jul 30, 2019·0 cites·19 claims
- 4242US2018135520A1Large area ratio cooling holesUNITED TECHNOLOGIES CORP·Filed 2017·Application pending·0 cites
- 4340US10801331B2Gas turbine engine rotor including squealer tip pocketUNITED TECHNOLOGIES CORP·Filed 2016·Granted Oct 13, 2020·0 cites·15 claims
- 4439US2017145834A1Airfoil platform cooling core circuits with one-wall heat transfer pedestals for a gas turbine engine component and systems for cooling an airfoil platformUNITED TECHNOLOGIES CORP·Filed 2015·Application pending·0 cites
- 4538US2016333701A1Airfoil impingement cavityUNITED TECHNOLOGIES CORP·Filed 2015·Application pending·0 cites
- 4637US2017145827A1Turbine blade with airfoil tip vortex controlUNITED TECHNOLOGIES CORP·Filed 2016·Application pending·0 cites
- 4737US2017101870A1Cooling holes of turbineUNITED TECHNOLOGIES CORP·Filed 2015·Application pending·0 cites
- 4834US2016177733A1Method of forming cooling holesUNITED TECHNOLOGIES CORP·Filed 2015·Application pending·0 cites
Join the waitlist — get patent alerts
Get an alert when Scott D. Lewis files or is granted a new patent.
We store only your email — no account needed. See our privacy policy.
Identity basis: PatentsView inventor disambiguation (2025Q4-odp release). How scoring works →