US4425080A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine casing
Assignee: Rolls Royce PLC
•
Filing: 1982-01-05
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Granted: 1984-01-10
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Expires: 2002-01-05
Abstract
Abstract A containment ring for a gas turbine engine consists of a substantially rigid inner cylinder around the periphery of which is wound layers of fibrous material, a plurality of axially extending strips are located upon the outermost curved surface of the layers of fibrous material and are secured thereto by self-tapping screws.
Inventors
- 👤 William A. Stanton
- 👤 Jonathan Hazlewood
- 👤 Norman A. Kerridge
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 02:33
CPC Classifications
F; F01; F01D; F01D21/00; F01D21/04; F01D21/045; F05; F05D; F05D2220/00; F05D2220/30; F05D2220/32; F05D2220/327; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
174 words
In a gas turbine engine having a duct defining fixed structure and at least a rotating part positioned within the duct, the improvement of a containment ring carried by said duct and positioned radially outwardly of said rotating part for absorbing energy and retaining a missile thrown radially outwardly by said rotating part, said containment ring comprising: a substantially rigid cylinder coaxial with and carried by said duct, said rigid cylinder having an inner periphery and an outer periphery; a fibrous material having one end bonded to the outer periphery of said rigid cylinder and being wound around said rigid cylinder to define a plurality of layers, said fibrous material having another end bonded to an adjacent one of said layers, and said layers having an outermost curved surface; a plurality of axially extending and circumferentially spaced strips positioned upon the outermost curved surface of said plurality of layers; fastening means extending into said layers of fibrous material and securing said strips thereto; and second fastening means securing said strips to adjacent fixed structures.
Claim 2
Dependent Claim
174 words
In a gas turbine engine having a duct defining fixed structure and at least a rotating part positioned within the duct, the improvement of a containment ring carried by said duct and positioned radially outwardly of said rotating part for absorbing energy and retaining a missile thrown radially outwardly by said rotating part, said containment ring comprising: a substantially rigid cylinder coaxial with and carried by said duct, said rigid cylinder having an inner periphery and an outer periphery; a fibrous material having one end bonded to the outer periphery of said rigid cylinder and being wound around said rigid cylinder to define a plurality of layers, said fibrous material having another end bonded to an adjacent one of said layers, and said layers having an outermost curved surface; a plurality of axially extending and circumferentially spaced strips positioned upon the outermost curved surface of said plurality of layers; fastening means extending into said layers of fibrous material and securing said strips thereto; and second fastening means securing said strips to adjacent fixed structures.
Claim 3
Dependent Claim
33 words
In a gas turbine engine as claimed in claim 1 in which the axially extending and circumferentially spaced strips are equally spaced about the outermost curved surface of the layers of fibrous material.
Claim 4
Dependent Claim
25 words
In a gas turbine engine as claimed in claim 1 in which the fibrous material consists of aromatic polyamide fibre woven into an elongate tape.
Claim 5
Dependent Claim
38 words
In a gas turbine engine as claimed in claim 1 in which the fibrous material may be from any one of the group consisting of glass fibre, carbon fibre, and metallic fibre which is woven into suitable tape.
Claim 6
Dependent Claim
25 words
In a gas turbine engine as claimed in claim 1 in which the fastening means extending into the fibrous material layers consist of self-tapping screws.
Claim 7
Dependent Claim
31 words
In a gas turbine engine as claimed in claim 1 in which the strips are secured adjacent their ends by said second fastening means to adjacent fixed structure of said duct.
Claim 8
Dependent Claim
24 words
In a gas turbine engine as claimed in claim 1 in which the substantially rigid cylinder comprises a relatively thin section lightweight metal structure.
Claim 9
Dependent Claim
24 words
In a gas turbine engine as claimed in claim 1 in which the substantially rigid cylinder is manufactured from fibre reinforced resin composite material.
Claim 10
Dependent Claim
38 words
In a gas turbine engine as claimed in claim 1 in which the plurality of layers of fibrous material are covered with an impervious layer of material, which impervious layer of material may consist of a resin layer.
Claim 11
Dependent Claim
31 words
In a gas turbine engine as claimed in claim 1 including an impervious layer of material covering said plurality of layers of fibrous material, said impervious layer of material being metallic.
Claim 12
Dependent Claim
25 words
In a gas turbine engine as claimed in claim 1 wherein said duct is a fan duct and wherein said rotating part is a fan.
Claim 13
Dependent Claim
24 words
In a gas turbine engine as claimed in claim 1 wherein said plurality of layers of fibrous material is wound from a woven tape.
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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) | 1987-01-09 | 1987-07-11 | 1988-01-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-01-09 | 1991-07-11 | 1992-01-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-01-09 | 1995-07-11 | 1996-01-10 | $7700.00 | Window Closed / Lapsed |