Turbine engine comprising means for heating the air entering the free turbine

Abstract

The invention relates to a turbine engine ( 10 ), particularly for a helicopter, comprising a gas generator ( 12 ) and a free turbine ( 14 ) rotated by a gas flow (F) generated by the gas generator. The invention is characterized in that the turbine engine also comprises heating means ( 26 ) placed between the gas generator and the free turbine ( 14 ), the said heating means ( 26 ) being capable of increasing the temperature of the gas flow (f) generated by the gas generator ( 12 ) and driving the free turbine.

1 . Turbine engine, particularly for a helicopter, comprising a gas generator and a free turbine rotated by a gas flow generated by the gas generator, the turbine engine also comprising a stream connecting an outlet of the gas generator to an inlet of the free turbine, through which the gas flow generated by the gas generator travels, wherein the turbine engine also comprises heating means placed between the gas generator and the free turbine, the said heating means being capable of increasing the temperature of the gas flow driving the free turbine which flows in the said stream, the said heating means comprising a combustion chamber connected to the stream via an upstream passageway so as to be able to be supplied by a fraction of the gas flow generated by the gas generator, the combustion chamber also being connected to the stream via a downstream passageway so as to be able to inject a current of hot gas into the stream. 
   
   
       2 . Turbine engine according to  claim 1 , wherein the said temperature increase is between 50 and 200° K. 
   
   
       3 . Turbine engine according to  claim 1 , wherein the combustion chamber encircles the stream.