Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Office National D'etudes Et De Recherches Aerospatiales

Office National D'etudes Et De Recherches Aerospatiales (par Abreviation

Serge Boudigues

Alain Ponthieux

Georges Frattacci

The turbocompressor for supercharging an internal combustion engine comprises a compressor whose output is connected to the intake manifold of the engine driven by a turbine which is driven by the exhaust gases of the engine. A take-off duct brings a fraction of the airflow supplied by the compressor to the exhaust gases upstream of the turbine. The turbine comprises distributor vanes with variable setting, typically in a range of about 40.degree.. With this arrangement, the low speed running torque and the efficiency are improved, more especially in the case of traction engines.

Internal combustion engine supercharged by turbocompressor

The blade comprises a metal web (1) surrounded by a refractory ceramic casing (2). The central web (1) is provided with at least one ventilation passage (4) in which flows a small amount of ventilation air. The zones where there is contact between the ceramic casing (2) and the central metal web (1) are provided with cooling cavities (5) in which cooling air flows at a high rate so as to establish a forced cooling condition.

Ceramic blades for turbomachines

A turbojet having a multistage axial compressor with contrarotating blade wheels fitted on inner and outer contrarotating rotors driven in opposite directions by respective turbine wheels. Each blade wheel (105) of the outer compressor rotor is associated with a rotating shell (86, 81, 82) having relatively few thick spokes for transmitting the drive from the turbine wheel, thereby leaving the blades to transmit aerodynamically induced forces only.

Turbojet with contrarotating wheels

A multiple-flow turbojet with adjustable bypass ratio comprising a low pressure spool and a high pressure spool casing. Aerodynamic surfaces mechanically integral with the high pressure spool are disposed in a cold secondary flow whose characteristics vary as a function of the setting of a guide means and cause a variation in the bypass ratio.

Multiple flow turbojet with adjustable bypass ratio

A dual-flow or multiflow gas turbine power plant comprising a jet pipe, at east two separate flow-ducts each opening into the jet pipe, namely a first flow-duct through which passes, in operation, a first gas flow and which contains a gas generator of the gas turbine type and an expansion-turbine located downstream of the gas generator, and a second flow-duct through which passes, in operation, a second gas flow and a mixer device in which the first gas flow leaving the expansion turbine, and the second gas flow, are arranged to be mixed prior to entering the jet pipe, the plant further comprising a recompressor located downstream of the mixer device, in which the mixture of the two gas flows is arranged to be recompressed before entering the jet pipe.

Multiflow gas turbine power plant

A dual-flow or multiflow gas turbine power plant comprising a jet pipe, at east two separate flow-ducts each opening into the jet pipe, namely a first flow-ducts through which passes, in operation, a first gas flow and which contains a gas generator of the gas turbine type and an expansion-turbine located downstream of the gas generator, and a second flow-ducts through which passes, in operation, a second gas flow and a mixer device in which the first gas flow leaving the expansion turbine, and the second gas flow, are arranged to be mixed prior to entering the jet pipe, the plant further comprising a recompressor located downstream of the mixer device, in which the mixture of the two gas flows is arranged to be recompressed before entering the jet pipe.

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Sceaux, France

Serge Boudigues