| 摘要 |
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.
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