Turboshaft engine with parallel shafts
First Claim
1. A turboshaft engine with a free turbine for an aircraft, comprising:
- a gas generator comprising at least one compressor supplied with air;
a combustion chamber receiving compressed air leaving the compressor;
at least one generator turbine connected mechanically to the compressor by a drive shaft and driven by gases arising from fuel combustion carried out in the combustion chamber;
a free turbine supplied with the gases arising from the combustion after passage thereof through the generator turbine, and which drives a power shaft not in an extension of the drive shaft of the gas generator, and supplying the turboshaft engine power via a reduction gearbox, wherein the generator turbine is of axial type and the combustion chamber is a substantially cylindrical or frustoconical chamber, in an extension of the axis of the generator turbine, and comprising a single injector;
wherein the power shaft is oriented parallel to the drive shaft; and
wherein the reduction gearbox is associated with an accessories gearbox, the two gearboxes being positioned in the longitudinal direction on a level with an air inlet of the compressor.
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Accused Products
Abstract
A free-turbine turboshaft engine including a gas generator including at least one compressor supplied with air, a combustion chamber receiving the compressed air at the output of the compressor, and at least one generator turbine mechanically connected to the compressor by a drive shaft and driven by gases from combustion of fuel carried out in the combustion chamber, and including a free turbine supplied by the gases from the combustion after passing through the generator turbine and which drives a power shaft positioned non-coaxially relative to the drive shaft of the gas generator and supplying the power of the turboshaft engine via a reduction gear. The combustion chamber is a substantially cylindrical or frusto-conical chamber, coaxial with the axis of the generator turbine, and includes a single injector.
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Citations
13 Claims
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1. A turboshaft engine with a free turbine for an aircraft, comprising:
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a gas generator comprising at least one compressor supplied with air; a combustion chamber receiving compressed air leaving the compressor; at least one generator turbine connected mechanically to the compressor by a drive shaft and driven by gases arising from fuel combustion carried out in the combustion chamber; a free turbine supplied with the gases arising from the combustion after passage thereof through the generator turbine, and which drives a power shaft not in an extension of the drive shaft of the gas generator, and supplying the turboshaft engine power via a reduction gearbox, wherein the generator turbine is of axial type and the combustion chamber is a substantially cylindrical or frustoconical chamber, in an extension of the axis of the generator turbine, and comprising a single injector;
wherein the power shaft is oriented parallel to the drive shaft; and
wherein the reduction gearbox is associated with an accessories gearbox, the two gearboxes being positioned in the longitudinal direction on a level with an air inlet of the compressor. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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Specification