초록

To further isolate imbalances in a rotating structure such as a gas turbine engine, an effective length between two bearings may exceed an actual length. This may be achieved via one or more tapering bearing supports associated with at least one of the bearings.

대표청구항 ▼

What is claimed is: 1. A turbine engine comprising: a first spool; support structure; and a plurality of bearing systems coupling the first spool to the support structure, including: a first bearing system having an inner race coupled to a shaft of the first spool and an outer race coupled to the s

What is claimed is: 1. A turbine engine comprising: a first spool; support structure; and a plurality of bearing systems coupling the first spool to the support structure, including: a first bearing system having an inner race coupled to a shaft of the first spool and an outer race coupled to the support structure; and a second bearing system aft of the first bearing system and having an inner race coupled to the shaft of the first spool and an outer race coupled to the support structure, the first spool shaft having a main body portion and forwardly diverging web having a proximal root at the main body portion and a distal portion holding the second bearing system inner race. 2. The turbine engine of claim 1 wherein: an engine case duct portion of the support structure is coupled to the outer races of the first and second bearing systems by a forwardly and inwardly-extending structure having: an aft portion coupling the outer race of the second bearing system to the engine case duct portion; and a fore portion fusibly coupling the outer race of the first bearing system to the aft portion. 3. The turbine engine of claim 2 wherein said aft portion couples the outer race of the second bearing system to the engine case duct portion by: a rearwardly converging web having a proximal root at the aft body portion and a distal portion holding the second bearing system outer race. 4. The turbine engine of claim 1 wherein: the first bearing system is a frontmost of said plurality of bearing systems; and the second bearing system is a next aft of said plurality of bearing systems. 5. The turbine engine of claim 1 wherein: the forwardly diverging web is essentially a frustoconical sleeve. 6. The turbine engine of claim 5 wherein: the forwardly diverging web is unitarily formed with the main body portion of the shaft. 7. The turbine engine of claim 1 wherein: the web provides an effective post-fusing cantilever length in excess of an actual length between the first and second bearing systems. 8. The turbine engine of claim 7 wherein: said effective post-fusing cantilever length is in excess of 110% of said actual length. 9. A turbine engine comprising: a high spool; a low spool; a non-rotating structure; and a plurality of bearing systems coupling a first spool of high and low spools to the non-rotating structure and, including: a first bearing system having an inner race coupled to a shaft of the first spool and an outer race coupled to the non-rotating structure by a fusible coupling; and a second bearing system aft of the first bearing system by a first length and having an outer race coupled to the non-rotating structure and an inner race coupled to the shaft of the first spool by means for providing a post-fusing effective cantilever length of the first bearing system relative to the second bearing system in excess of the first length. 10. The turbine engine of claim 9 wherein: the first spool shaft has a main body portion; and the means comprises a forwardly diverging web having a proximal root at the main body portion and a distal portion holding the second bearing system inner race. 11. The turbine engine of claim 9 wherein the first spool is the high spool. 12. The turbine engine of claim 9 being a turbofan engine having a fan directly or indirectly coupled to the low spool.