An inlet for a gas turbine engine having an inlet lip and an inlet barrel, the inlet lip having a highlight defining a boundary between inner and outer surfaces of the inlet lip. The inlet barrel has a forwardly extending flange that is joined to the inlet lip by overlapping surfaces. The flange interface surface has a conus angle that is divergent from the highlight axis.
A GAS TURBINE INLET
GASTURBINENEINLASS
ENTRÉE D'UNE TURBINE À GAZ
2021-07-21
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 |
INLET AIR COOLING - Applying Wet Compression for Turbine Inlet Cooling
Online Contents | 2007
INLET AIR COOLING - Sizing Up Value in Turbine Inlet Cooling
Online Contents | 2005