US3792586A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Bearing assembly systems
Assignee: Avco Corp
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Filing: 1973-01-22
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Granted: 1974-02-19
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Expires: 1993-01-22
Abstract
Abstract A mid-span bearing support for the power take-off shaft of a fan type gas turbine engine is described. The power take-off shaft extends radially through frame struts in the core engine inlet and fan ducts of the engine. These struts are separated by a gap in which a bearing assembly is mounted to journal the power takeoff shaft. This assembly includes a spring bellows which permits the height of the assembly to be reduced by a rotatable sleeve to permit retraction of interdigitating locating means in the installation and removal of the assembly. The spring bellows also provides sealing pressure of the assembly against opposed surfaces of the gap so that oil may flow through the struts and assembly for return to the engine''s oil pump.
Inventors
- 👤 J Kasmarik
- 👤 A Hoffmann
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 12:40
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/32; F01; F01D; F01D25/00; F01D25/16; F01D25/162; F02C7/06; F02K; F02K3/00; F02K3/02; F02K3/04; F02K3/06
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
216 words
A fan type gas turbine engine including a fan duct, a core engine inlet duct, a centrally disposed engine shaft, a frame defining, in part, said ducts and including hollow, radial struts, in the lower, 6 o''clock position, which span said ducts, said frame further defining, at least in part, an oil return sump having its low point at said inlet duct strut, a power take-off shaft extending radially through said struts and driven from said engine shaft, said frame struts being separated by a gap into which passageways from said hollow struts open, said gap having opposed parallel surfaces respectively surrounding said openings, a bearing assembly comprising upper and lower rings surrounding said power take-off shaft and respectively juxtaposed relative to said opposed surfaces for sealing relation therewith, a compressed spring bellows extending between said rings and urging them in opposite directions, a bearing mounted on one of said rings and journaling said power take-off shaft, means interdigitating axially between one of said rings and said frame for accurately locating said bearing relative to said frame and said power take-off shaft, and means connected between said rings for reducing the overall height of said bearing assembly to permit lateral removal of the bearing assembly from said gap when said power take-off shaft is withdrawn therefrom.
Claim 2
Dependent Claim
216 words
A fan type gas turbine engine including a fan duct, a core engine inlet duct, a centrally disposed engine shaft, a frame defining, in part, said ducts and including hollow, radial struts, in the lower, 6 o''clock position, which span said ducts, said frame further defining, at least in part, an oil return sump having its low point at said inlet duct strut, a power take-off shaft extending radially through said struts and driven from said engine shaft, said frame struts being separated by a gap into which passageways from said hollow struts open, said gap having opposed parallel surfaces respectively surrounding said openings, a bearing assembly comprising upper and lower rings surrounding said power take-off shaft and respectively juxtaposed relative to said opposed surfaces for sealing relation therewith, a compressed spring bellows extending between said rings and urging them in opposite directions, a bearing mounted on one of said rings and journaling said power take-off shaft, means interdigitating axially between one of said rings and said frame for accurately locating said bearing relative to said frame and said power take-off shaft, and means connected between said rings for reducing the overall height of said bearing assembly to permit lateral removal of the bearing assembly from said gap when said power take-off shaft is withdrawn therefrom.
Claim 3
Dependent Claim
30 words
A fan type gas turbine engine as in claim 1 wherein the interdigitating means extend between the frame and the ring on which the power take-off shaft bearing is mounted.
Claim 4
Dependent Claim
76 words
A fan type gas turbine engine as in claim 2 wherein the height reducing means comprise a sleeve surrounding said rings, said sleeve being threaded onto one of said rings and having an inturned flange underlying a circumferential rim formed on the other ring and further comprising means for preventing relative rotation between said assembly and said frame to facilitate rotation of said sleeve in varying the height of the assembly during its installation and removal.
Claim 5
Dependent Claim
60 words
A fan type gas turbine engine as in claim 3 wherein the interdigitating means comprise a pilot formed concentrically of said bearing and extending into a locating hole formed in said frame and further wherein said bearing is a roller bearing and said shaft has an enlarged land formed thereon and serving as the inner raceway for said roller bearing.
Claim 6
Dependent Claim
142 words
A fan type gas turbine engine as in claim 4 wherein the bearing is mounted on the upper of said rings, the core engine inlet duct strut has a portion surrounding said power take-off shaft in spaced relationship thereto for directing oil to said roller bearing and the locating hole for receiving the pilot of the interdigitating means is formed at the lower end of said strut portion, circumferential grooves are formed in the upper and lower faces of the upper and lower rings respectively and ''''O'''' rings are disposed therein to provide sealing engagement with said opposed parallel gap surfaces and the means preventing rotation between the bearing assembly and the frame comprise a bracket having a non-circular opening receiving a correspondingly shaped lower portion of the lower ring and means for removably securing said bracket to the adjacent frame structure.
References Cited (Backward Citations)
US2803943A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1977-02-18 | 1977-08-20 | 1978-02-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-02-18 | 1981-08-20 | 1982-02-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-02-18 | 1985-08-20 | 1986-02-19 | $7700.00 | Window Closed / Lapsed |