Multi-spool gas turbine engine architecture
AssigneePratt & Whitney Canada Corp.
InventorGuy LEFEBVRE
Life of this patent
Estimating the term…
Abstract
A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool. The LP spool and the HP spool are independently rotatable about an 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 axially mounted at one end of the engine. The LP compressor is axially positioned between the HP compressor and the AGB. The AGB is drivingly connected to the HP spool through the center of the LP compressor.
Claims22
A multi-spool gas turbine engine comprising:
- a low pressure (LP) spool;
- a high pressure (HP) spool, the LP spool and the HP spool being independently rotatable from one another about a central axis, the LP pressure spool comprising an LP compressor and an LP turbine, the HP spool comprising an HP turbine and an HP compressor;
- and an accessory gear box (AGB) mounted in axial series at one end of the engine, the LP compressor being positioned between the HP compressor and the AGB, the AGB being drivingly connected to the HP spool through the center of the LP compressor.
A multi-spool gas turbine engine comprising:
- a low pressure (LP) spool;
- a high pressure (HP) spool;
- the LP spool and the HP spool being mounted for rotation about a central axis;
- the LP pressure spool comprising an LP compressor and an LP turbine, the HP spool comprising an HP turbine and an HP compressor;
- and an accessory gear box (AGB) drivingly connected to the HP spool, the LP compressor being axially positioned between the HP compressor and the AGB and drivingly connected to the LP turbine via a gear train.
The multi-spool gas turbine engine defined 11, wherein the gear train comprises a first gear mounted to said one end of the LP shaft, said first gear being in meshing engagement with a second gear provided at a first end of a transfer shaft, a third gear provided at a second end of the transfer shaft, and a fourth gear provided on said LP compressor, the fourth gear being in meshing engagement with the third gear.
A turboprop or turboshaft engine comprising:
- an output drive shaft configured to drivingly engage a rotatable load;
- a low pressure (LP) spool comprising an LP turbine and an LP compressor, the output drive shaft being drivingly connected to the LP turbine, the LP compressor being drivingly connected to the LP turbine via a first gear train;
- a high pressure (HP) spool rotatable independently of the LP spool, and an accessory gearbox (AGB) drivingly connected to the HP compressor, the LP compressor being positioned axially between the AGB and the HP compressor, and wherein the AGB has an input axis coaxial to a centerline of the LP compressor.
A reverse flow gas turbine engine, comprising:
- an output drive shaft having a front end configurable to drivingly engage a rotatable load;
- a low pressure (LP) spool including an LP turbine drivingly engaged to the output drive shaft, and an LP compressor drivingly connected to the LP turbine via a gear train, the LP turbine disposed forward of the LP compressor relative to a front end of the output drive shaft;
- and
- a high pressure HP spool including an HP turbine and an HP compressor drivingly engaged to an HP shaft rotatable independently of the LP spool, the HP compressor disposed forward of the LP compressor and in fluid communication therewith, and the HP turbine disposed aft of the LP turbine and in fluid communication therewith.
Dependencies are inferred from the claim text.