Turbine shaft power take-off

• US 10,458,340 B2
• Filed: 01/17/2017
• Issued: 10/29/2019
• Est. Priority Date: 07/19/2016
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Original Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Inventors: Lefebvre, Guy
• Primary Examiner(s): Dallo, Joseph J
• Application Number:
  US15/407,414
• Publication Number:
  US 20180023482A1
• Time in Patent Office: 1,015 Days
• CPC Class Codes: B64D 27/10 of gas-turbine type jet aircraft B64D27/16
• CPC Class Codes: B64D 35/04 characterised by the transmission driving a plurality of propellers or rotors
• CPC Class Codes: F01D 15/12 Combinations with mechanical gearing driven by multiple engines F01D13/00
• CPC Class Codes: F01D 25/18 Lubricating arrangements of machines or engines in general F01M
• CPC Class Codes: F01D 5/026 Shaft to shaft connections
• CPC Class Codes: F02C 3/08 the compressor comprising at least one radial stage F02C3/10 takes precedence
• CPC Class Codes: F02C 3/10 with another turbine driving an output shaft but not driving the compressor
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• CPC Class Codes: F02C 3/113 with variable power transmission between rotors
• CPC Class Codes: F02C 3/145 the combustion chamber being in the reverse flow-type
• CPC Class Codes: F02C 6/206 the vehicles being airscrew driven
• CPC Class Codes: F02C 7/06 Arrangements of bearings bearings F16C; Lubricating of turbo machines F01D25/18; of machines or engines in general F01M
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2220/324 to drive unshrouded, low solidity propeller
• CPC Class Codes: F05D 2220/329 in helicopters
• CPC Class Codes: F05D 2230/70 Disassembly methods
• CPC Class Codes: F05D 2230/72 : Maintenance
• CPC Class Codes: F05D 2240/61 : Hollow
• CPC Class Codes: F05D 2250/36 : in inner-outer relationship, e.g. shaft-bearing arrangements
• CPC Class Codes: F05D 2260/31 : Retaining bolts or nuts
• CPC Class Codes: F05D 2260/36 : by a form fit connection, e.g. by interlocking
• CPC Class Codes: F05D 2260/40 : Transmission of power
• CPC Class Codes: F05D 2260/4031 : as in toothed gearing
• CPC Class Codes: F05D 2260/40311 : of the epicyclical, planetary or differential type
• CPC Class Codes: F05D 2260/98 : Lubrication
• CPC Class Codes: F16H 57/0495 : with fixed gear ratio
• CPC Class Codes: Y02T 50/40 : Weight reduction
• CPC Class Codes: Y02T 50/60 : Efficient propulsion technologies, e.g. for aircraft

Abstract

A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable of one another about an engine axis. The LP spool comprises an LP turbine, an LP compressor and an LP shaft. The HP pressure spool comprises an HP turbine, an HP compressor and an HP shaft. The LP turbine is in fluid flow communication with the HP turbine and disposed downstream therefrom. The HP compressor is in fluid flow communication with the LP compressor and disposed downstream therefrom. The LP shaft has an upstream shaft portion extending upstream of the LP turbine to a location upstream of the LP compressor to provide a first power take-off at an upstream end of the engine and a downstream shaft portion extending downstream of the LP turbine to provide a second power take-off at a downstream end of the engine, thereby allowing mounting of a reduction gear box at either end of the engine.

Claims

1. A multi-spool gas turbine engine comprising:

a low pressure (LP) spool and a high pressure (HP) spool independently rotatable of one another about an engine axis, the LP spool comprising an LP turbine, an LP compressor and an LP shaft, the HP pressure spool comprising an HP turbine, an HP compressor and an HP shaft;

the LP turbine being in fluid flow communication with the HP turbine and disposed downstream therefrom, the HP compressor being in fluid flow communication with the LP compressor and disposed downstream therefrom, the LP shaft having an upstream shaft portion extending upstream of the LP turbine to a location upstream of the LP compressor to provide a first power take-off at an upstream end of the engine and a downstream shaft portion extending downstream of the LP turbine to provide a second power take-off at a downstream end of the engine.

2. The multi spool gas turbine engine defined in claim 1, further comprising an accessory gearbox (AGB) disposed at the upstream end of the engine upstream of the LP compressor, the AGB being drivingly connected to the HP spool.

3. The multi spool gas turbine engine defined in claim 2, further comprising a reduction gear box (RGB) disposed at the upstream or downstream end of the engine for connection to a selected one of the first and second power take-offs of the LP shaft.

4. The multi-spool gas turbine engine defined in claim 3, wherein the AGB and the RGB are both disposed at the upstream end of the engine upstream of the LP compressor.

5. The multi-spool gas turbine engine defined in claim 4, wherein the HP shaft extends axially through the LP compressor and is drivingly connected to the AGB upstream of the LP compressor, and wherein the upstream shaft portion of the LP shaft also extends axially through the LP compressor and is drivingly connected to the RGB upstream of the LP compressor, the HP shaft and the upstream shaft portion of the LP shaft being concentric.

6. The multi-spool gas turbine engine defined in claim 5, wherein the AGB and the RGB have respective input axis coaxial to the engine axis.

7. The multi-spool engine defined in claim 4, wherein the RGB and the AGB share a common casing.

8. The multi-spool gas turbine engine defined in claim 3, wherein the RGB is disposed at the downstream end of the engine downstream of the LP turbine.

9. The multi-spool gas turbine engine defined in claim 8, wherein the RGB is drivingly connected to a propeller shaft.

10. The multi-spool engine defined in claim 1, wherein the LP shaft extends from the upstream end to the downstream end of the engine along the engine axis, and wherein the upstream shaft portion of the LP shaft is drivingly coupled to the LP compressor via a gear train.

11. The multi-spool engine defined in claim 10, wherein the upstream shaft portion is also drivingly connected to a reduction gear box (RGB) disposed downstream of the LP compressor.

12. The multi-spool engine defined in claim 3, wherein a second RGB is drivingly connected to the other one of the first and second drive outputs of the LP shaft.

13. A multi-spool gas turbine engine comprising:

a low pressure (LP) spool;

a high pressure (HP) spool;

the LP and HP spools independently rotatable of one another about an engine axis;

the LP spool comprising an LP turbine drivingly connected to an LP compressor by an LP shaft, the LP turbine disposed downstream of the LP compressor relative to a flow of gases through the engine, the LP shaft having an upstream and a downstream shaft portion extending in opposite directions from the LP turbine to an upstream end and a downstream end of the engine, respectively, the upstream shaft portion of the LP shaft extending axially through the LP compressor to a location upstream of the LP compressor at the upstream end of the engine;

the HP pressure spool comprising an HP turbine drivingly connected to an HP compressor by an HP shaft;

an accessory gear box (AGB) disposed at the upstream end of the engine upstream of the LP compressor and drivingly connected to the HP spool; and

a reduction gearbox (RGB) disposed at the upstream or the downstream end of the engine and drivingly connected to a corresponding output end of the upstream or downstream shaft portion of the LP shaft.

14. The multi-spool gas turbine engine defined in claim 13, further comprising an air inlet upstream of the LP compressor, and wherein the AGB and the RGB are both disposed at the upstream end of the engine upstream of the air inlet.

15. The multi-spool gas turbine engine defined in claim 14, wherein the upstream shaft portion of the LP shaft is drivingly connected to both the LP compressor and the RGB.

16. The multi-spool gas turbine engine defined in claim 14, wherein the HP shaft extends centrally through the LP compressor to a location upstream of the LP compressor for connection to the AGB.

17. The multi-spool gas turbine engine defined in claim 16, wherein the upstream shaft portion of the LP shaft projects coaxially out of the HP shaft to a location upstream of an upstream end of the HP shaft.

18. The multi-spool gas turbine engine defined in claim 17, wherein the upstream portion of the LP shaft is drivingly connected to the LP compressor via a gear train disposed upstream of the LP compressor.

19. The multi-spool gas turbine engine defined in claim 18, wherein the gear train, the AGB and the RGB are housed in a common casing.

20. The multi-spool gas turbine engine defined in claim 13, wherein the AGB and the RGB have respective input axis coaxial to the engine axis.