Aircraft engine with fan or propeller drive - has two independently rotating coaxial shafts with fuel combustion in compressed air fuel-enriching machine with bucket wheel

The aircraft engine has at least two coaxial shafts (1,2) driving independently of each other, each carrying a compressor (3,4) and turbine (5,6). The isochoric combustion chamber is located between the compressor and turbine of one shaft and is a compressed air fuel-enriching machine (pressure-wave...

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Bibliographische Detailangaben
1. Verfasser:	ALTHAUS, ROLF., FLAWIL
Format:	Patent
Sprache:	eng ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPING OF FLUID BY DIRECT CONTACT OF ANOTHER FLUID OR BYUSING INERTIA OF FLUID TO BE PUMPED PUMPS FOR LIQUIDS OR ELASTIC FLUIDS SIPHONS WEAPONS
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Beschreibung
Zusammenfassung:	The aircraft engine has at least two coaxial shafts (1,2) driving independently of each other, each carrying a compressor (3,4) and turbine (5,6). The isochoric combustion chamber is located between the compressor and turbine of one shaft and is a compressed air fuel-enriching machine (pressure-wave machine) with a bucket wheel and epicyclic gearbox. However the bucket wheel may rotate freely at a low speed. The wheel rotates between inlet and outlet openings and has a number of buckets in which a recurrent ignition and combustion process takes place. After this stage (9), there is an additional HP turbine (10) which precedes the IP turbine. ADVANTAGE- Increased efficiency and output.