US3779006A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Flame shield for a gas turbine engine
Assignee: UK Secretary of State for Defence
•
Filing: 1971-11-04
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Granted: 1973-12-18
•
Expires: 1991-11-04
Abstract
Abstract A flame shield for a gas turbine engine comprises a sheet of refractory metal, preferably tantalum, having at least on the side subject to flame attack a material which prevents oxidation of the sheet and on the other side an insulating layer. The flame shield is so positioned and so dimensioned that in the event of failure of the combustion equipment of a gas turbine engine in an aircraft, any flame issuing therefrom is prevented from coming into contact with other parts of the engine or the aircraft fuselage for a predetermined length of time.
Inventors
- 👤 B Lewis
- 👤 G Miller
- 👤 K Brooks
- 👤 A Goss
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 19:33
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/24; F02C7/25; E; E04; E04B; E04B1/00; E04B1/62; E04B1/92; E04B1/94; E04B1/941; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
33 words
A gas turbine engine as claimed in claim 1 wherein the material of said coating is selected from the group comprising a silicide-based compound, alumina, a hafnium based alloy and an aluminium-tin alloy.
Claim 2
Dependent Claim
16 words
A gas turbine engine as claimed in claim 2 wherein said hafnium based alloy contains tantalum.
Claim 3
Dependent Claim
23 words
A gas turbine engine as claimed in claim 2 wherein said aluminium-tin alloy contains substantially equal amounts by weight of aluminium and tin.
Claim 4
Dependent Claim
30 words
A gas turbine engine as claimed in claim 1 wherein said insulating layer comprises a first layer of an asbestos-containing material and a second layer of a quartz containing material.
Claim 5
Dependent Claim
32 words
A gas turbine engine as claimed in claim 1 in which a further sheet is provided, said insulating layer being sandwiched between the said sheet of refractory metal and said further sheet.
Claim 6
Dependent Claim
17 words
A gas turbine engine as claimed in claim 6 wherein said further sheet is made of steel.
Claim 7
Dependent Claim
33 words
A gas turbine engine as claimed in claim 1 wherein the said refractory metal is selected from the group comprising tantalum, niobium, molybdenum, tungsten, ductile chromium and any alloy of these refractory metals.
Claim 8
Dependent Claim
51 words
A gas turbine engine as claimed in claim 1 including a fan mounted within a fan duct and mounting means comprising a strut extending across said fan duct, said strut being a part of the aircraft to be protected, said flame shield being disposed between said combustion equipment and said strut.
Claim 9
Dependent Claim
30 words
A gas turbine engine as claimed in claim 9 wherein said flame shield is arcuate, the ends of said flame shield subtending an angle of 85* at the engine axis.
Claim 10
Dependent Claim
32 words
A gas turbine engine as claimed in claim 1 wherein said insulating layer comprises a first layer of asbestos fibers impregnated with a phenolic resin and a second layer of silica fibers.
References Cited (Backward Citations)
US2711631A
Cited
US2706382A
Cited
US2805192A
Cited
GB868197A
Cited
US3122883A
Cited
US3264135A
Cited
US3321922A
Cited
US3357657A
Cited
US3460759A
Cited
DE1946085A1
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-12-17 | 1977-06-18 | 1977-12-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-12-17 | 1981-06-18 | 1981-12-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-12-17 | 1985-06-18 | 1985-12-18 | $7700.00 | Window Closed / Lapsed |