A gas turbine engine includes a supply air conduit fluidly connected to an inlet of a combustion chamber to convey supply air to the combustion chamber, an exhaust conduit fluidly connected to an exit of the combustion chamber to convey exhaust gases away from the combustion chamber, and a recuperator defining a first flow path and a second flow path therethrough, the second flow path being in heat transfer communication with the first flow path, the first flow path defining part of the supply air conduit, the second flow path defining part of the exhaust conduit. Methods of operating the engine are also provided.
Gas turbine auxiliary power unit
18.05.2021
Patent
Elektronische Ressource
Englisch
Diesel and turbine combined in marine auxiliary power unit
Tema Archiv | 1989
|Gas turbine auxiliary power unit noise and its attenuation
Engineering Index Backfile | 1967
|Gas-turbine-driven auxiliary electric power unit for aircraft
Engineering Index Backfile | 1956