Inventor
Scott D. Lewis
Inventor
Vernon, CT, US
Overview
Patents· 32 as inventor
Public. Assignee & technology derived from the patent record. Each patent links to its LexDana page.
F01Dprimary
F01DNon-positive displacement machines or engines, e.g. steam turbines27%
F05DIndexing scheme for aspects relating to non-positive-displacement machines or engines, gas-turbines or jet-propulsion plants27%
Y02TClimate change mitigation technologies related to transportation24%
F02CGas-turbine plants7%
F23RGenerating combustion products of high pressure or high velocity, e.g. gas-turbine combustion chambers5%
F04DNon-positive-displacement pumps3%
F16JPistons2%
B22CFoundry moulding1%
B23HWorking of metal by the action of a high concentration of electric current on a workpiece using an electrode which takes the place of a tool1%
B23KSoldering or unsoldering1%
PatentTitleYear
10,815,788Turbine blade with slot film cooling202010,815,803BOAS thermal protection202010,801,331Gas turbine engine rotor including squealer tip pocket202010,801,325Turbine blade with tip vortex control and tip shelf202010,773,344Systems and methods for manufacturing film cooling hole diffuser portion202010,677,066Turbine blade with airfoil tip vortex control202010,577,936Mateface surfaces having a geometry on turbomachinery hardware202010,533,428Oblong purge holes202010,513,931Cooling systems and internally-cooled engine parts having an impingement cavity with an undulating internal surface201910,502,066Turbine engine component including an axially aligned skin core passage interrupted by a pedestal201910,422,230Cooling hole with curved metering section201910,408,071BOAS thermal protection201910,400,607Large-footprint turbine cooling hole201910,392,943Film cooling hole including offset diffuser portion201910,364,680Gas turbine engine component having platform trench201910,323,524Axial skin core cooling passage for a turbine engine component201910,273,811Axial skin core cooling passage for a turbine engine component201910,227,875Gas turbine engine component with combined mate face and platform cooling201910,208,603Staggered crossovers for airfoils201910,180,067Mate face cooling holes for gas turbine engine component201910,156,144Turbine airfoil and method of cooling201810,145,246Staggered crossovers for airfoils201810,100,645Trailing edge cooling configuration for a gas turbine engine airfoil201810,077,667Turbine airfoil film cooling holes201810,053,992Gas turbine engine airfoil squealer pocket cooling hole configuration201810,041,356Showerhead hole scheme apparatus and system201810,001,023Grooved seal arrangement for turbine engine20189,982,542Airfoil platform impingement cooling holes20189,822,658'Grooved seal arrangement for turbine engine'20179,284,845'Turbine airfoil tip shelf and squealer pocket cooling'20169,243,500'Turbine blade platform with U-channel cooling holes'20168,584,470'Tri-lobed cooling hole and method of manufacture'2013Career & activity timeline
Assembled from patent assignee/location history and declaration credentials.
2013–2020Patents assigned to UNITED TECHNOLOGIES CORP (31)· patent assignee history
2013–2019Patents assigned to LEWIS SCOTT D (5)· patent assignee history
2013–2019Patents assigned to ZELESKY MARK F (4)· patent assignee history
2013–2020Based in Vernon, CT, US· patent location history
2016–2019Patents assigned to TELLER BRET M (3)· patent assignee history
2020Patents assigned to RAYTHEON TECH CORP (5)· patent assignee history
2020Based in East Hartford, CT, US· patent location history
Inventor activity
Assignee and location history derived from the patent record.
Assignees
| Assignee | Patents | Span |
|---|---|---|
| UNITED TECHNOLOGIES CORP | 31 | 2013–2020 |
| LEWIS SCOTT Dself | 5 | 2013–2019 |
| RAYTHEON TECH CORP | 5 | 2020 |
| ZELESKY MARK F | 4 | 2013–2019 |
| TELLER BRET M | 3 | 2016–2019 |
Locations
| Location | Patents | Span |
|---|---|---|
| Vernon, CT, US | 31 | 2013–2020 |
| East Hartford, CT, US | 1 | 2020 |