Twin spool turbine engine with power take-off means on the low-pressure and high-pressure rotors, and power take-off module for the turbine engine

• US 7,552,591 B2
• Filed: 02/09/2006
• Issued: 06/30/2009
• Est. Priority Date: 02/11/2005
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Beutin, Bruno Albert, Bart, Jacques Rene, Morel, Patrick Charles Georges
• Primary Examiner(s): Casaregola; Louis J
• Application Number:
  US11/276,012
• Publication Number:
  US 20060277920A1
• Time in Patent Office: 1,237 Days
• Field of Search: 607/88, 607/92, 607/93, 608/02
• US Class Current: 60/792
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F05D 2230/61 using limited numbers of standard modules which can be adapted by machining
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The invention relates to a twin spool turbine engine comprising a high-pressure rotor and a low-pressure rotor, at least one accessory gearbox, a drive means, driving coaxial transmission shafts that transmit movement to the accessory gearbox, characterized in that the drive means comprises a high-pressure drive pinion secured to the high-pressure rotor near its upstream end, a low-pressure drive pinion secured to the low-pressure rotor upstream of the high-pressure rotor, and a power take-off module in direct mesh with the drive pinions, driving the transmission shafts.

By virtue of the invention, the transmission shafts run coaxial with one another and therefore pass through a single arm. The use of a power take-off module simplifies the mechanism. The turbine engine is simpler to assemble.

Claims

1. A twin spool turbine engine comprising:

a high-pressure rotor,

a low-pressure rotor,

at least one accessory gearbox,

drive means for driving coaxial transmission shafts that transmit movement to the accessory gearbox, wherein the drive means comprises a high-pressure drive pinion secured to the high-pressure rotor near its upstream end, a low-pressure drive pinion secured to the low-pressure rotor upstream of the high-pressure rotor, and

a power take-off module in direct mesh with the drive pinions, driving the transmission shafts, wherein said power take-off module comprises a cylindrical portion secured to said coaxial transmission shafts and a frustroconical portion extending internally from said cylindrical portion, said power take-off module further comprising a high pressure take-off pinion secured to said frustroconical portion and in direct mesh with said high-pressure drive pinion, and a low pressure take-off pinion secured to said frustroconical portion and in direct mesh with said low-pressure drive pinion.

2. A turbine engine according to claim 1, wherein the transmission shafts are fitted into the power take-off module.

3. A turbine engine according to claim 1, wherein said low-pressure power take-off pinion is coaxial with the high-pressure power take-off pinion.

4. A turbine engine according to claim 1, wherein the turbine engine includes a fixed structure and the power take-off pinions are secured to end pieces, the power take-off module and said end pieces are contained in a box secured to the fixed structure of the turbine engine.

5. A turbine engine according to claim 4, wherein the transmission shafts are in mesh with the end pieces via splines.

6. A turbine engine according to claim 1, wherein the diameter of the high-pressure drive pinion is smaller than the diameter of the low-pressure drive pinion.

7. A turbine engine according to claim 1, wherein the high-pressure drive pinion is situated upstream of the upstream bearing of the high-pressure rotor and the low-pressure drive pinion is situated downstream of the downstream bearing of the low-pressure compressor shaft of the low-pressure rotor.

8. A turbine engine according to claim 1 which is a jet engine, in which the transmission shafts run along one structural arm of the intermediate casing.

9. A turbine engine according to claim 1, further comprising a box having a frustroconical shape and containing said frustroconical portion of said power take-off module, said box being secured to a fixed structure for said turbine engine.

10. A turbine engine according to claim 1, wherein said coaxial transmission shafts are not at right angles with respect to an axis of said turbine engine, said high-pressure and low-pressure rotors being configured to rotate around said axis.

11. A twin spool turbine engine comprising:

a high-pressure rotor,

a low-pressure rotor,

at least one accessory gearbox,

a drive means for driving coaxial transmission shafts that transmit movement to the accessory gearbox, wherein the drive means comprises a high-pressure drive pinion secured to the high-pressure rotor near its upstream end, a low-pressure drive pinion secured to the low-pressure rotor upstream of the high-pressure rotor, and

a power take-off module in direct mesh with the drive pinions, driving the transmission shafts, wherein said power take-off module is a preassembled module mounted on said turbine engine as a unit comprising a high pressure take-off pinion configured to be in direct mesh with said high-pressure drive pinion, and a low pressure take-off pinion configured to be in direct mesh with said low-pressure drive pinion.