Inventor
HASEL KARL L
US24 patents
⚠️ This page may combine multiple inventors who share the name “HASEL KARL L”. Patents are grouped by organization below to help distinguish them — per-person disambiguation is on the roadmap.
UNITED TECHNOLOGIES CORP
11 patentsUS9816443B2Nov 14, 2017
Method for setting a gear ratio of a fan drive gear system of a gas turbine engine
UNITED TECHNOLOGIES CORP53 citations98
US8678743B1Mar 25, 2014
Method for setting a gear ratio of a fan drive gear system of a gas turbine engine
UNITED TECHNOLOGIES CORP50 citations98
US9194329B2Nov 24, 2015
Gas turbine engine shaft bearing configuration
UNITED TECHNOLOGIES CORP17 citations92
US8863491B2Oct 21, 2014
Gas turbine engine shaft bearing configuration
UNITED TECHNOLOGIES CORP17 citations92
US8807916B2Aug 19, 2014
Method for setting a gear ratio of a fan drive gear system of a gas turbine engine
UNITED TECHNOLOGIES CORP18 citations92
US10830152B2Nov 10, 2020
Gas turbine engine compressor arrangement
UNITED TECHNOLOGIES CORP6 citations84
US10215094B2Feb 26, 2019
Gas turbine engine shaft bearing configuration
UNITED TECHNOLOGIES CORP4 citations84
US10119466B2Nov 6, 2018
Geared turbofan engine with high compressor exit temperature
UNITED TECHNOLOGIES CORP8 citations84
US8814494B1Aug 26, 2014
Method for setting a gear ratio of a fan drive gear system of a gas turbine engine
UNITED TECHNOLOGIES CORP12 citations84
US8753065B2Jun 17, 2014
Method for setting a gear ratio of a fan drive gear system of a gas turbine engine
UNITED TECHNOLOGIES CORP12 citations84
US10036316B2Jul 31, 2018
Geared turbofan engine with high compressor exit temperature
UNITED TECHNOLOGIES CORP3 citations73
RAYTHEON TECH CORP
7 patentsUS11149689B2Oct 19, 2021
Gas turbine engine shaft bearing configuration
RAYTHEON TECH CORP2 citations73
US10823051B2Nov 3, 2020
Geared turbofan engine with high compressor exit temperature
RAYTHEON TECH CORP1 citations73
US11846238B2Dec 19, 2023
Gas turbine engine compressor arrangement
RAYTHEON TECH CORP0 citations63
US11566586B2Jan 31, 2023
Gas turbine engine shaft bearing configuration
RAYTHEON TECH CORP0 citations62
US11560851B2Jan 24, 2023
Geared turbofan engine with high compressor exit temperature
RAYTHEON TECH CORP0 citations62
US12392280B2Aug 19, 2025
Gas turbine engine with high low spool power extraction ratio
RAYTHEON TECH CORP0 citations51
US12123356B2Oct 22, 2024
Gas turbine engine with higher low spool torque-to-thrust ratio
RAYTHEON TECH CORP0 citations51