PLANETARY GEAR SYSTEM ARRANGEMENT WITH AUXILIARY OIL SYSTEM
First Claim
Patent Images
1. A gas turbine engine comprising:
- a fan, a first compressor stage and a second compressor stage;
a first turbine stage and a second turbine stage, and wherein said first turbine stage drives said second compressor stage as a high spool, and wherein said second turbine stage drives said first compressor stage as part of a low spool; and
a gear train driving said fan with said low spool, and such that said fan and said first compressor stage rotate in the same direction, and wherein said high spool operates at higher pressures than said low spool.
4 Assignments
0 Petitions
Accused Products
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.
-
Citations
23 Claims
-
1. A gas turbine engine comprising:
-
a fan, a first compressor stage and a second compressor stage; a first turbine stage and a second turbine stage, and wherein said first turbine stage drives said second compressor stage as a high spool, and wherein said second turbine stage drives said first compressor stage as part of a low spool; and a gear train driving said fan with said low spool, and such that said fan and said first compressor stage rotate in the same direction, and wherein said high spool operates at higher pressures than said low spool. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
-
-
12. 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. - View Dependent Claims (13, 14, 15, 16, 17, 18, 19, 20)
-
-
21. A gas turbine engine comprising:
-
a fan, a first compressor stage and a second compressor stage; a first turbine stage and a second turbine stage, and wherein said first turbine stage drives said second compressor stage as a high spool, and wherein said second turbine stage drives said first compressor stage as part of a low spool; a gear train driving said fan with said low spool, and such that said fan and said first compressor stage rotate in the same direction, and wherein said high spool operates at higher pressures than said low spool; said gear train having a planetary gear, a sun gear, a stationary ring gear, a carrier in which said planetary gear is mounted, and said carrier mounted for rotation about said sun gear and driving said fan; a lubricating system provided for said gear train; and said ring gear having a recess radially outward of gear teeth on said ring gear. - View Dependent Claims (22, 23)
-
Specification