Gear train architecture for a multi-spool gas turbine engine
First Claim
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1. An aircraft engine comprising:
- a low pressure (LP) spool;
a high pressure (HP) spool fluidly connected to the LP spool by a gaspath, the LP spool comprising an LP compressor and an LP turbine, the HP spool comprising an HP turbine and an HP compressor;
an accessory gear box (AGB), the LP compressor positioned between the HP compressor and the AGB; and
first and second gear trains positioned between the HP compressor and the LP compressor and radially inwardly from the gaspath, the first gear train coupling the LP turbine to the LP compressor, the second gear train coupling the HP spool to the AGB, wherein the aircraft engine has a reverse flow configuration including an air inlet disposed aft of the LP compressor along an intended direction of travel of the aircraft engine, and wherein the AGB is disposed aft of the air inlet.
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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. The LP compressor is axially positioned between the HP compressor and an accessory gear box (AGB). The AGB is drivingly connected to the HP spool through the center of the LP compressor.
188 Citations
15 Claims
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1. An aircraft engine comprising:
- a low pressure (LP) spool;
a high pressure (HP) spool fluidly connected to the LP spool by a gaspath, the LP spool comprising an LP compressor and an LP turbine, the HP spool comprising an HP turbine and an HP compressor;
an accessory gear box (AGB), the LP compressor positioned between the HP compressor and the AGB; and
first and second gear trains positioned between the HP compressor and the LP compressor and radially inwardly from the gaspath, the first gear train coupling the LP turbine to the LP compressor, the second gear train coupling the HP spool to the AGB, wherein the aircraft engine has a reverse flow configuration including an air inlet disposed aft of the LP compressor along an intended direction of travel of the aircraft engine, and wherein the AGB is disposed aft of the air inlet. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
- a low pressure (LP) spool;
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9. A multi-spool gas turbine engine comprising:
- a low pressure (LP) spool;
a high pressure (HP) spool fluidly connected to the LP spool via a gaspath, the LP spool and the HP spool being mounted for rotation about a central axis;
the LP spool comprising an LP compressor and an LP turbine, the HP spool comprising an HP turbine and an HP compressor;
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 positioned axially between the HP compressor and the LP compressor and radially inwardly from the gaspath, wherein the LP turbine is drivingly mounted to an LP shaft extending axially along the central axis within an HP shaft connecting the HP turbine to the HP compressor, the LP shaft having one end thereof projecting axially out of the HP shaft, said gear train being provided at said one end of the LP shaft, 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. - View Dependent Claims (10, 11, 12, 13)
- a low pressure (LP) spool;
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14. A reverse flow gas turbine engine, comprising:
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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 via a gaspath, and the HP turbine disposed aft of the LP turbine and in fluid communication therewith through said gaspath; wherein the gear train coupling the LP compressor to the LP turbine is disposed between the LP compressor and the HP compressor and radially inwardly from the gaspath, further comprising an accessory gearbox (AGB), the AGB being mounted aft of the LP compressor and wherein the AGB has an input shaft extending through a central bore of the LP compressor, the input shaft being drivingly connected to the HP spool via a further gear train, the gear train and the further gear train being housed in a same chamber circumscribed by an inner gaspath wall of the gaspath. - View Dependent Claims (15)
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Specification