| 摘要 |
#CMT# #/CMT# The engine (10) has a core engine (11) with a compressor, a combustion chamber and a turbine, where the core engine is surrounded in sections over a core engine housing by a bypass channel (16) that is limited radially outside by a channel housing. A thermoelectric generator generates electrical energy from a temperature difference between hot current through the core engine and cold current through the channel. Thermocouple sections (26) are assigned to the hot core engine housing and thermocouple sections (27) are assigned to cold bypass channel housing. #CMT#USE : #/CMT# Gas-turbine engine such as civilian aircraft engine or military aircraft engine. #CMT#ADVANTAGE : #/CMT# The thermoelectric generator generates the electrical energy from the temperature difference between the hot current through the core engine and cold current through the bypass channel, without the removal of mechanical shaft power from the core engine to operate ancillary units of the aircraft engine, so that overall efficiency of the engine is improved and the fuel is saved, thus reducing emission of the aircraft engine. The thermoelectric generator is integrated into the engine at simple constructional measures and ensures a small weight of the aircraft engine. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a schematic sectional view of a gas-turbine engine. 10 : Gas-turbine engine 11 : Core engine 16 : Bypass channel 24, 25 : Thermocouples 26, 27 : Thermocouple sections. |
