US5408826A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine casing construction
Assignee: Rolls Royce PLC
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Filing: 1994-03-24
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Granted: 1995-04-25
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Expires: 2014-03-24
Abstract
Abstract A casing assembly for a ducted fan gas turbine engine comprises a casing around which extend two annular, axially spaced apart, frangible rails. Pieces of cloth woven from an aromatic polyamide fibre are positioned on the casing radially outer surface between the rails. Continuous layers of the cloth are wound around the casing radially outwardly of the rails and cloth pieces. The arrangement provided enhanced containment of any fan blades of the engine which may become detached from the gas turbine engine which carries the casing assembly.
Inventors
- 👤 Ian F. Stewart
- 👤 Sivasubramaniam K. Sathianathan
- 👤 David J. Chisholm
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 10:50
CPC Classifications
F; F01; F01D; F01D21/00; F01D21/04; F01D21/045; F05; F05B; F05B2260/00; F05B2260/30; F05B2260/301; F05B2260/3011; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10S; Y10S60/00; Y10S60/909
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
121 words
A gas turbine engine casing assembly comprising an annular cross-section casing configured to surround an annular array or rotary aerofoil blades, said casing defining a radially outer surface and having at least two annular, axially spaced apart, rail members on said radially outer surface and positioned coaxially therewith discrete pieces of flexible containment material located as discontinuous layers on said casing radially outer surface between, and by, said rail members, and a plurality of layers of flexible containment material wound as continuous lengths around said casing radially outwardly of said rail members and said discrete pieces, said rail members and said discrete pieces being completely covered by said plurality of layers, said plurality of layers being noncoextensive relative to each other.
Claim 2
Dependent Claim
121 words
A gas turbine engine casing assembly comprising an annular cross-section casing configured to surround an annular array or rotary aerofoil blades, said casing defining a radially outer surface and having at least two annular, axially spaced apart, rail members on said radially outer surface and positioned coaxially therewith discrete pieces of flexible containment material located as discontinuous layers on said casing radially outer surface between, and by, said rail members, and a plurality of layers of flexible containment material wound as continuous lengths around said casing radially outwardly of said rail members and said discrete pieces, said rail members and said discrete pieces being completely covered by said plurality of layers, said plurality of layers being noncoextensive relative to each other.
Claim 3
Dependent Claim
20 words
A gas turbine engine casing assembly as claimed in claim 1 wherein said casing assembly is a fan casing assembly.
Claim 4
Dependent Claim
77 words
A gas turbine engine casing assembly as claimed in claim 2 wherein said plurality of layers of flexible containment material wound as continuous lengths around said casing radially outwardly of said rail members and said discrete pieces comprises two continuous extents of said material, the first of said extents being positioned radially inwardly of the second of said extents, said first extent being of greater axial extent than said second extent to extend downstream of said rails.
Claim 5
Dependent Claim
50 words
A gas turbine engine casing assembly as claimed in claim 3 wherein a third continuous extent of said flexible containment material is wound around said casing, said third continuous extent being wound around the portion of said casing downstream of said rail members radially inwardly of said second continuous extent.
Claim 6
Dependent Claim
27 words
A gas turbine engine casing assembly as claimed in claim 1 wherein said discrete pieces of flexible containment material are loosely stitched together with readily frangible threads.
Claim 7
Dependent Claim
18 words
A gas turbine engine casing assembly as claimed claim 5 wherein said readily frangible threads are of cotton.
Claim 8
Dependent Claim
22 words
A gas turbine engine casing assembly as claimed claim 1 wherein said flexible containment material comprises fabric woven from aromatic polyamide fibres.
Claim 9
Dependent Claim
28 words
A gas turbine engine casing assembly as claimed in claim 1 wherein said casing is provided on its radially outer surface with a network of integral reinforcing ribs.
Claim 10
Dependent Claim
23 words
A gas turbine engine casing assembly as claimed in claim 8 wherein said integral reinforcing ribs are in the form of inter-connected triangles.
Claim 11
Dependent Claim
16 words
A gas turbine engine casing assembly as claimed in claim 1 wherein rail members are frangible.
Claim 12
Dependent Claim
25 words
A gas turbine engine casing assembly as claimed in claim 10 wherein said frangible rail members are in the form of hollow, rectangular cross-section tubes.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1998-04-24 | 1998-10-24 | 1999-04-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2002-04-24 | 2002-10-24 | 2003-04-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2006-04-24 | 2006-10-24 | 2007-04-25 | $7700.00 | Window Closed / Lapsed |