Gas turbine engine shaft architecture and associated method of disassembly

• US 10,393,027 B2
• Filed: 01/17/2017
• Issued: 08/27/2019
• 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, Pietrobon, John
• Primary Examiner(s): Sung, Gerald L
• Assistant Examiner(s): Amar, Marc J
• Application Number:
  US15/407,423
• Publication Number:
  US 20180023471A1
• Time in Patent Office: 952 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 about a central axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. An accessory gear box (AGB) is drivingly connected to the HP spool. The LP compressor is disposed axially between the HP compressor and the AGB. A gear train drivingly couples the LP compressor to the LP turbine. The gear train is integrated to the AGB.

Claims

1. A boosted reverse flow gas turbine engine comprising:

a low pressure (LP) spool and a high pressure (HP) spool rotatable independently of one another about an engine axis;

the LP spool comprising a LP turbine, a LP compressor disposed aft of the LP turbine relative to a direction of forward travel of the engine, a LP compressor drive shaft drivingly connecting the LP turbine to the LP compressor, and a hollow LP turbine shaft projecting axially forward from the LP turbine and drivingly connected to the LP turbine for driving a rotatable load;

the LP compressor drive shaft being coaxial to the hollow LP turbine shaft and axially removable through the hollow LP turbine shaft.

2. The boosted reverse flow gas turbine engine defined in claim 1, further comprising a hollow propeller shaft coaxial to the hollow LP turbine shaft and drivingly connected thereto, the LP compressor drive shaft being axially insertable/removable through the hollow LP turbine shaft and the hollow propeller shaft.

3. The boosted reverse flow gas turbine engine defined in claim 2, wherein the hollow propeller shaft is drivingly connected to the hollow LP turbine shaft via a reduction gearbox (RGB), the hollow propeller shaft extending forwardly from the RGB.

4. The boosted reverse flow gas turbine engine defined in claim 2, wherein the hollow propeller shaft and the hollow LP turbine shaft are coaxial and jointly define a central passage along the engine axis, the LP compressor drive shaft being axially movable through said central passage, axially extending splines drivingly coupling the LP compressor drive shaft to the LP turbine and the LP compressor.

5. The boosted reverse flow gas turbine engine defined in claim 1, wherein a retaining nut is threadably engaged with a forward end of the hollow LP turbine shaft to prevent axial withdrawal of the LP compressor drive shaft from the hollow LP turbine shaft.

6. The boosted reverse flow gas turbine engine defined in claim 5, further comprising a hollow propeller shaft coaxial to the hollow LP turbine shaft and drivingly coupled to the hollow LP turbine shaft, the hollow propeller shaft extending forward of the hollow LP turbine shaft, the retaining nut being accessible via a central passage extending axially through the hollow propeller shaft.

7. The boosted reverse flow gas turbine engine defined in claim 1, wherein the LP compressor drive shaft is drivingly coupled to the LP turbine and the LP compressor via axially extending splines.

8. The boosted reverse flow gas turbine engine defined in claim 1, wherein the HP spool comprises a HP turbine, a HP compressor and a HP shaft drivingly connecting the HP turbine to the HP compressor, the HP compressor disposed forward of the LP compressor and in fluid communication with the LP compressor, the HP turbine disposed aft of the LP turbine and in fluid communication with the LP turbine.

9. A turboprop engine comprising:

a propeller shaft rotatable about an engine axis;

a low pressure (LP) turbine shaft rotatable about the engine axis and drivingly coupled to the propeller shaft;

a LP turbine drivingly connected to the LP turbine shaft;

a LP compressor drive shaft rotatable about the engine axis and drivingly coupled to the LP turbine; and

a LP compressor drivingly coupled to the LP compressor drive shaft, the LP turbine disposed axially between the propeller shaft and the LP compressor;

the LP compressor drive shaft being removable from the engine through a central passage extending axially through the propeller shaft and the LP turbine shaft.

10. The turboprop defined in claim 9, wherein the LP turbine, the LP compressor, the LP compressor drive shaft and the LP turbine shaft form part of a LP spool, and wherein the turboprop engine further comprises a high pressure (HP) spool rotatable about the engine axis independently of the LP spool, the HP spool comprising a HP turbine, a HP compressor, and a HP shaft drivingly connecting the HP turbine to the HP compressor, the HP compressor disposed downstream of the LP compressor and being in fluid communication with the LP compressor, the HP turbine disposed upstream of the LP turbine and in fluid communication with the LP turbine.

11. The turboprop engine defined in claim 9, wherein axially extending splines drivingly couple the LP compressor drive shaft to the LP turbine and the LP compressor.

12. The turboprop engine defined in claim 11, wherein the LP compressor drive shaft extends axially through the LP turbine shaft.

13. The turboprop engine defined in claim 9, wherein a reduction gearbox (RGB) drivingly couples the LP turbine shaft to the propeller shaft, the LP compressor drive shaft extending axially through the RGB.

14. The turboprop engine defined in claim 9, wherein a retaining nut releasably prevents axial withdrawal of the LP compressor drive shaft from the LP turbine shaft, and wherein the retaining nut is accessible via the central passage extending through the propeller shaft.

15. A method of removing a shaft from a turboprop engine having a low pressure (LP) compressor drivingly coupled to a LP turbine via a LP compressor drive shaft wherein the LP compressor is axially aft of the LP turbine, the LP turbine drivingly coupled to a propeller shaft of a propeller, the method comprising:

removing the propeller from the propeller shaft, the propeller shaft defining an axially extending passage providing access to the LP compressor drive shaft, axially unlocking the LP compressor drive shaft, and axially extracting the LP compressor drive shaft through the axially extending passage of the propeller shaft.

16. The method defined in claim 15, wherein axially unlocking comprises accessing, via the axially extending passage, a retaining nut and untightening the retaining nut.

17. The method defined in claim 16, wherein the LP turbine has a hollow LP turbine shaft coaxial to the propeller shaft and drivingly coupled to the propeller shaft, the LP compressor drive shaft being received in said LP turbine shaft, and wherein untightening the retaining nut comprises untightening the retaining nut from a distal end of the LP turbine shaft.

18. The method defined in claim 15, wherein the LP compressor drive shaft is axially unlocked from the LP turbine.

19. A method of conducting a hot section inspection (HSI) comprising:

detaching a power section module of the turboprop engine from a remainder of the engine after having removed the LP compressor drive shaft from the turboprop engine as defined in claim 15, and then inspecting hot section engine components.