A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a first nacelle which at least partially surrounds a second nacelle and the fan rotor, the fan section configured to communicate airflow into the first nacelle and the second nacelle, a first turbine, and a second turbine followed by the first turbine. The first turbine is configured to drive the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.
Gas turbine engine with low stage count low pressure turbine
2019-10-22
Patent
Electronic Resource
English
IPC: | F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke |
GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW STAGE PRESSURE TURBINE
European Patent Office | 2020
|GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE
European Patent Office | 2020
|Gas turbine engine with low stage count low pressure turbine and engine mounting arrangement
European Patent Office | 2022
|Turbine Engine Reliability - Stage II
SAE Technical Papers | 1963
|Turbine engine reliability -- Stage II
Engineering Index Backfile | 1963
|