Inventor · disambiguated record
Assaf Farah
Also filed as: FARAH ASSAF
9 granted patents·7 pending applications·45 citations·filing 2005–2024
84Inventor score
Top patents by PatentIndex Score
16 records- 0187US7520715B2Turbine shroud segment transpiration cooling with individual cast inlet and outlet cavitiesPRATT & WHITNEY CANADA·Filed 2005·Granted Apr 21, 2009·26 cites·12 claims
- 0286US12078354B1Fuel containment structure for engine fuel delivery systemPRATT & WHITNEY CANADA·Filed 2023·Granted Sep 3, 2024·2 cites·20 claims
- 0376US10801441B2Flow mixer stiffener ring segmented springsPRATT & WHITNEY CANADA·Filed 2018·Granted Oct 13, 2020·2 cites·20 claims
- 0471US9291070B2Gas turbine rotor containmentFIELDING BRUCE·Filed 2011·Granted Mar 22, 2016·6 cites·7 claims
- 0566US10227895B2Gas turbine case and reinforcement strut for samePRATT & WHITNEY CANADA·Filed 2013·Granted Mar 12, 2019·3 cites·15 claims
- 0664US11268696B2Slot cooled combustorUNITED TECHNOLOGIES CORP·Filed 2018·Granted Mar 8, 2022·1 cites·18 claims
- 0763US12292007B2Hydrogen leak detection system for an aircraft propulsion systemPRATT & WHITNEY CANADA·Filed 2023·Granted May 6, 2025·0 cites·18 claims
- 0858US2025083831A1Vented hydrogen fuel reservoir for aircraft enginePRATT & WHITNEY CANADA·Filed 2023·Application pending·0 cites
- 0955US2019153897A1Gas turbine case and reinforcement strut for samePRATT & WHITNEY CANADA·Filed 2019·Application pending·0 cites
- 1047US2025369614A1Augmented thermal fencing of a fuel nozzle heat shieldPRATT & WHITNEY CANADA·Filed 2024·Application pending·0 cites
- 1146US8182199B2Turbine shroud cooling systemFARAH ASSAF·Filed 2007·Granted May 22, 2012·5 cites·15 claims
- 1246US2025084792A1Fuel containment structure for engine fuel delivery systemPRATT & WHITNEY CANADA·Filed 2023·Application pending·0 cites
- 1344US11286882B2Exhaust casing for a gas turbine enginePRATT & WHITNEY CANADA·Filed 2018·Granted Mar 29, 2022·0 cites·9 claims
- 1443US2024093869A1Fuel nozzlePRATT & WHITNEY CANADA·Filed 2022·Application pending·0 cites
- 1541US2008232963A1Turbine shroud segment transpiration cooling with individual cast inlet and outlet cavitiesPRATT & WHITNEY CANADA·Filed 2008·Application pending·0 cites
- 1636US2007020088A1Turbine shroud segment impingement cooling on vane outer shroudPRATT & WHITNEY CANADA·Filed 2005·Application pending·0 cites
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Identity basis: PatentsView inventor disambiguation (2025Q4-odp release). How scoring works →