Inventor · disambiguated record
Karl L. Hasel
Also filed as: HASEL KARL L
23 granted patents·32 pending applications·269 citations·filing 2012–2024
96Inventor score
Top patents by PatentIndex Score
55 records- 0199US9816443B2Method for setting a gear ratio of a fan drive gear system of a gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2016·Granted Nov 14, 2017·53 cites·22 claims
- 0298US8678743B1Method for setting a gear ratio of a fan drive gear system of a gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2013·Granted Mar 25, 2014·50 cites·20 claims
- 0397US8807916B2Method for setting a gear ratio of a fan drive gear system of a gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2014·Granted Aug 19, 2014·18 cites·30 claims
- 0496US8337149B1Gas turbine engine compressor arrangementHASEL KARL L·Filed 2012·Granted Dec 25, 2012·24 cites·20 claims
- 0595US12085025B2Gas turbine engine compressor arrangementRTX CORP·Filed 2023·Granted Sep 10, 2024·1 cites·30 claims
- 0695US10830152B2Gas turbine engine compressor arrangementUNITED TECHNOLOGIES CORP·Filed 2016·Granted Nov 10, 2020·6 cites·27 claims
- 0795US10119466B2Geared turbofan engine with high compressor exit temperatureUNITED TECHNOLOGIES CORP·Filed 2015·Granted Nov 6, 2018·8 cites·16 claims
- 0895US9194329B2Gas turbine engine shaft bearing configurationUNITED TECHNOLOGIES CORP·Filed 2014·Granted Nov 24, 2015·17 cites·4 claims
- 0995US8863491B2Gas turbine engine shaft bearing configurationUNITED TECHNOLOGIES CORP·Filed 2013·Granted Oct 21, 2014·17 cites·25 claims
- 1095US8277174B2Gas turbine engine compressor arrangementHASEL KARL L·Filed 2012·Granted Oct 2, 2012·24 cites·19 claims
- 1194US8449247B1Gas turbine engine compressor arrangementHASEL KARL L·Filed 2012·Granted May 28, 2013·17 cites·20 claims
- 1292US8814494B1Method for setting a gear ratio of a fan drive gear system of a gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2014·Granted Aug 26, 2014·12 cites·30 claims
- 1392US8753065B2Method for setting a gear ratio of a fan drive gear system of a gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2013·Granted Jun 17, 2014·12 cites·19 claims
- 1489US10215094B2Gas turbine engine shaft bearing configurationUNITED TECHNOLOGIES CORP·Filed 2015·Granted Feb 26, 2019·4 cites·3 claims
- 1586US11149689B2Gas turbine engine shaft bearing configurationRAYTHEON TECH CORP·Filed 2018·Granted Oct 19, 2021·2 cites·18 claims
- 1685US10036316B2Geared turbofan engine with high compressor exit temperatureUNITED TECHNOLOGIES CORP·Filed 2015·Granted Jul 31, 2018·3 cites·15 claims
- 1780US12331691B2Gas turbine engine compressor arrangementRTX CORP·Filed 2024·Granted Jun 17, 2025·0 cites·20 claims
- 1878US10823051B2Geared turbofan engine with high compressor exit temperatureRAYTHEON TECH CORP·Filed 2018·Granted Nov 3, 2020·1 cites·16 claims
- 1969US11566586B2Gas turbine engine shaft bearing configurationRAYTHEON TECH CORP·Filed 2021·Granted Jan 31, 2023·0 cites·28 claims
- 2069US2021215101A1Method for setting a gear ratio of a fan drive gear system of a gas turbine engineRAYTHEON TECH CORP·Filed 2021·Application pending·0 cites
- 2168US11846238B2Gas turbine engine compressor arrangementRAYTHEON TECH CORP·Filed 2020·Granted Dec 19, 2023·0 cites·30 claims
- 2267US11560851B2Geared turbofan engine with high compressor exit temperatureRAYTHEON TECH CORP·Filed 2020·Granted Jan 24, 2023·0 cites·15 claims
- 2362US2018156135A1Method for setting a gear ratio of a fan drive gear system of a gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2018·Application pending·0 cites
- 2462US2020095929A1High thrust geared gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2019·Application pending·0 cites
- 2559US2017122219A1Gas turbine engine compressor arrangementUNITED TECHNOLOGIES CORP·Filed 2017·Application pending·0 cites
- 2659US2017122220A1Gas turbine engine compressor arrangementUNITED TECHNOLOGIES CORP·Filed 2017·Application pending·0 cites
- 2759US2018066590A1Method for setting a gear ratio of a fan drive gear system of a gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2017·Application pending·0 cites
- 2858US2015308335A1Method for setting a gear ratio of a fan drive gear system of a gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2015·Application pending·0 cites
- 2957US2016281610A1Method for setting a gear ratio of a fan drive gear system of a gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2016·Application pending·0 cites
- 3056US2015233301A1Method for setting a gear ratio of a fan drive gear system of a gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2015·Application pending·0 cites
- 3156US2018073439A9A fan drive gear system for driving a fan in a gas turbine engine having a high bypass ratioUNITED TECHNOLOGIES CORP·Filed 2015·Application pending·0 cites
- 3256US2015285155A1Method for setting a gear ratio of a fan drive gear system of a gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2015·Application pending·0 cites
- 3354US2014157754A1Gas turbine engine compressor arrangementUNITED TECHNOLOGIES CORP·Filed 2014·Application pending·0 cites
- 3451US2016363047A1High thrust geared gas turbine engineUNITED TECHNOLOGIES CORP·Filed 2014·Application pending·0 cites
- 3549US2014165534A1Gas turbine engine compressor arrangementUNITED TECHNOLOGIES CORP·Filed 2014·Application pending·0 cites
- 3649US2014157752A1Gas turbine engine compressor arrangementUNITED TECHNOLOGIES CORP·Filed 2014·Application pending·0 cites
- 3748US2015267610A1Turbine enigne including balanced low pressure stage countUNITED TECHNOLOGIES CORP·Filed 2014·Application pending·0 cites
- 3847US2015027101A1Geared gas turbine engine architecture for enhanced efficiencyUNITED TECHNOLOGIES CORP·Filed 2013·Application pending·0 cites
- 3947US2015315974A1Two spool gas generator with improved pressure splitUNITED TECHNOLOGIES CORP·Filed 2013·Application pending·0 cites
- 4046US2014157757A1Gas turbine engine compressor arrangementUNITED TECHNOLOGIES CORP·Filed 2014·Application pending·0 cites
- 4146US2014157753A1Gas turbine engine compressor arrangementUNITED TECHNOLOGIES CORP·Filed 2014·Application pending·0 cites
- 4246US2014090388A1Off-take power ratioUNITED TECHNOLOGIES CORP·Filed 2012·Application pending·0 cites
- 4345US2018230912A1Gas turbine engine compressor arrangementUNITED TECHNOLOGIES CORP·Filed 2018·Application pending·0 cites
- 4445US2015013301A1Turbine engine including balanced low pressure stage countUNITED TECHNOLOGIES CORP·Filed 2013·Application pending·0 cites
- 4544US12392280B2Gas turbine engine with high low spool power extraction ratioRAYTHEON TECH CORP·Filed 2021·Granted Aug 19, 2025·0 cites·2 claims
- 4644US12123356B2Gas turbine engine with higher low spool torque-to-thrust ratioRAYTHEON TECH CORP·Filed 2021·Granted Oct 22, 2024·0 cites·10 claims
- 4744US2014260326A1Geared turbofan engine with high compressor exit temperatureUNITED TECHNOLOGIES CORP·Filed 2013·Application pending·0 cites
- 4844US2014290211A1Turbine engine including balanced low pressure stage countUNITED TECHNOLOGIES CORP·Filed 2013·Application pending·0 cites
- 4943US2014157756A1Gas turbine engine compressor arrangementUNITED TECHNOLOGIES CORP·Filed 2014·Application pending·0 cites
- 5043US2014157755A1Gas turbine engine compressor arrangementUNITED TECHNOLOGIES CORP·Filed 2014·Application pending·0 cites
Showing the top 50 of 55 patent records by PatentIndex Score.
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Identity basis: PatentsView inventor disambiguation (2025Q4-odp release). How scoring works →