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US 8,484,942 B1Granted
Planetary gear system arrangement with auxiliary oil system
AssigneeUnited Technologies Corporation
InventorsMichael E. McCune, William G. Sheridan, Lawrence E. Portlock
Life of this patent
Estimating the term…
Abstract
A gas turbine engine has a fan, first and second compressor stages, first and second turbine stages. The first turbine stage drives the second compressor stage as a high spool. The second turbine stage drives the first compressor stage as part of a low spool. A gear train drives the fan with the low spool, such that the fan and first compressor stage rotate in the same direction. The high spool operates at higher pressures than the low spool. A lubrication system is also disclosed.
Claims10
A gas turbine engine comprising:
- a fan, a first compressor rotor and a second compressor rotor;
- a first turbine rotor and a second turbine rotor, and wherein said first turbine rotor drives said second compressor rotor as a high spool, and wherein said second turbine rotor drives said first compressor rotor as part of a low spool, and a gear reduction driving said fan with said low spool at a reduced speed, and such that said fan and said first compressor rotor rotate in the same direction, and wherein said high spool operates at higher pressures than said low spool;
- a lubrication system for lubricating components across a rotation gap, the lubrication system including a lubricant input, a stationary first bearing receiving lubricant from said lubricant input and having an inner first race in which lubricant flows, and a second bearing for rotation within said first bearing, said second bearing having a first opening in registration with said inner first race such that lubricant may flow from said inner first race through said first opening into a first conduit;
- and
- said first bearing also having an inner second race into which lubricant flows, and said second bearing having a second opening in registration with said inner second race such that lubricant may flow from said inner second race through said second opening into a second conduit, with said first and second conduits delivering lubricant to distinct locations.
2 more elements
A gas turbine engine comprising:
- a fan, a first compressor rotor and a second compressor rotor;
- a first turbine rotor and a second turbine rotor, and wherein said first turbine rotor drives said second compressor rotor as a high spool, and wherein said second turbine rotor drives said first compressor rotor as part of a low spool, and a gear reduction driving said fan with said low spool at a reduced speed, and such that said fan and said first compressor rotor rotate in the same direction, and wherein said high spool operates at higher pressures than said low spool;
- and
- a lubrication system for lubricating components across a rotation gap, the lubrication system including a lubricant input, a stationary first bearing receiving lubricant from said lubricant input and having an inner first race in which lubricant flows, and a second bearing for rotation within said first bearing, said second bearing having a first opening in registration with said inner first race such that lubricant may flow from said inner first race through said first opening into a first conduit;
- said first bearing and said second bearing are centered about a common axis;
- a rotating carrier for supporting a planetary gear wherein said second bearing extends from said rotating carrier about an axis;
- a first spray bar disposed on said carrier;
- and
- said first bearing has a second inner race and said second bearing has a second opening in registration with said second inner race and a second conduit for passing lubricant to said spray bar.
6 more elements
Dependencies are inferred from the claim text.