A gas turbine engine includes a compressor section in series flow with a turbine section. The compressor section includes one or more compressors and the turbine section includes one or more turbines, the compressor section and turbine section together defining a core air flowpath. A sump is positioned inward of the core air flowpath for containing and collecting lubrication oil. Additionally, a heat exchanger is positioned in direct thermal communication with the sump for removing heat from lubrication oil contained therein to reduce a size and/or amount of heat exchangers located radially outward of the core air flowpath.
GAS TURBINE ENGINE SUMP HEAT EXCHANGER
ECHANGEUR DE CHALEUR DE CARTER DE MOTEUR DE TURBINE A GAZ
2017-04-30
Patent
Elektronische Ressource
Englisch
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F16N LUBRICATING , Schmierung |
SAE Technical Papers | 2011
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