Open rotor type turbomachine for aircraft, has free turbine placed between gas generator and power turbines, and power generator comprising rotor driven in rotation by free turbine, where gas generator comprises high pressure compressor

• Main Authors: BEUTIN BRUNO ALBERT, YVON DIDIER JEAN LOUIS, COLIN ANTOINE OLIVIER FRANCOIS, REAUX CLARISSE SAVINE MATHILDE
• Format: Patent
• Language: English; French
• Published: 30.07.2010
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS; INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04; JET-PROPULSION PLANTS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; WEAPONS

The turbomachine (1) has a receiver (30) driven by power turbines (34, 38) and located in downstream of a gas generator (14) e.g. twin-spool gas generator. A free turbine (62) is placed between the gas generator and the power turbines. An electrical power generator (60) e.g. axial or radial flow generator, has a rotor driven in rotation by the free turbine. The gas generator has a high pressure compressor (18) equipped with a radial shaft (72) for driving the rotor of the generator. La présente invention se rapporte à une turbomachine (1) pour aéronef comprenant un générateur de gaz (14), un récepteur (30) entraîné par turbine de puissance (34, 38), ainsi qu'un générateur électrique de puissance (60), et comprenant en outre une turbine libre (62) interposée entre le générateur de gaz (14) et la turbine de puissance, le rotor du générateur électrique de puissance (60) étant entraîné en rotation par la turbine libre (62).