Turboshaft engine with parallel shafts

• US 9,297,305 B2
• Filed: 09/29/2010
• Issued: 03/29/2016
• Est. Priority Date: 09/17/2009
• Status: Active Grant

• Current Assignee: Safran Helicopter Engines
• Original Assignee: Turbomeca
• Inventors: Drachsler, Antoine, Perbos, Alain Michel, Silet, Joel
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): Ibroni, Stefan
• Application Number:
  US13/395,212
• Publication Number:
  US 20120167591A1
• Time in Patent Office: 2,008 Days
• Field of Search: 60/391.62
• US Class Current: 1/1
• CPC Class Codes: F02C 3/05 the compressor and the turbine being of the radial flow type
• CPC Class Codes: F02C 3/103 the compressor being of the centrifugal type
• CPC Class Codes: F02C 3/14 characterised by the arrangement of the combustion chamber in the plant combustion chambers per se F23R; F02C3/205 takes precedence
• CPC Class Codes: F02C 3/145 the combustion chamber being in the reverse flow-type
• CPC Class Codes: F05D 2250/231 cylindrical
• CPC Class Codes: F05D 2250/232 conical
• CPC Class Codes: F05D 2250/311 the axes being in line
• CPC Class Codes: F05D 2250/312 the axes being parallel to each other
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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.

Claims

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.

2. The turboshaft engine as claimed in claim 1, wherein a casing of the reduction gearbox/accessories gearbox and a casing of the gas generator are combined into a single casing.

3. The turboshaft engine as claimed in claim 1, wherein the combustion chamber comprises an injector incorporating Lean Premixed Prevaporized (LPP) technology.

4. The turboshaft engine as claimed in claim 1, wherein an outlet of the combustion chamber is oriented towards the compressor.

5. The turboshaft engine as claimed in claim 1, wherein the gases arising from combustion are collected in an annular collector positioned downstream of the generator turbine for transfer into an annular distribution chamber positioned upstream of the free turbine.

6. The turboshaft engine as claimed in claim 1, wherein the gas generator is a multi-spool generator comprising a high pressure compressor and a low pressure compressor together with a high pressure turbine and a low pressure turbine, the turbines driving the compressors by respectively a high pressure drive shaft and a low pressure drive shaft, the power shaft driven by the free turbine not being in an extension of the high pressure drive shaft of the generator and the combustion chamber being in the extension of the high pressure drive shaft.

7. The turboshaft engine as claimed in claim 6, wherein the low pressure drive shaft is hollow and the power shaft passes through the low pressure drive shaft.

8. The turboshaft engine as claimed in claim 7, wherein the power shaft and the low pressure drive shaft are concentric.

9. The turboshaft engine as claimed in claim 1, on which a high speed alternator is mounted.

10. The turboshaft engine as claimed in claim 1, further comprising a hot gas/compressed air heat exchanger, between the gases leaving the free turbine and the air leaving the compressor.

11. An aircraft propelled by a turboshaft engine as claimed in claim 1.

12. The turboshaft engine as claimed in claim 1, wherein the combustion chamber comprises only a single injector.

13. The turboshaft engine as claimed in claim 1, wherein the drive shaft does not pass through the combustion chamber.