US5085559A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Composite vane
Assignee: United States Department of the Air Force
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Filing: 1990-04-16
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Granted: 1992-02-04
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Expires: 2010-04-16
Abstract
Abstract Metal darts are captured either in bonded assembly or in riveted assembly with composite airfoil skins. The darts have a thin fin extending rearward with a dam at its rear end forming a hot air duct on either side of the fin. As hot compressor bleed air is diverted down through the fin duct, heat is transferred forward to the dart leading edge. The fin may contain ripples or other perturbances to improve heat transfer if necessary. Sufficient heat should be transferred to inhibit ice buildup on the final coating that covers the entire airfoil and further provides FOD protection by having a metal leading edge.
Inventors
- 👤 Lewis J. Stoffer
- 👤 Andrew MacGee
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 20:56
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/04; F02C7/047; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/18; F01D5/28; F01D5/282; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
161 words
An improved composite airfoil, said improved composite airfoil providing anti-icing and foreign object damage protection, the improvement comprising: a means for conducting heat to a leading edge of said airfoil, said means being composed of a metal, said means having composite skins thereon such that a plurality of air ducts are provided along the length of said means for conducting heat of said improved composite airfoil, said means for conducting heat being a metal dart comprising: a leading edge, said leading edge having an aerodynamic shape; a fin, said fin being connected to said leading edge at a rear section of said leading edge; at least one dam, said at least one dam being connected to a rearward edge of said fin and extending perpendicularly therefrom in both directions; and a plurality of opening means through said dart for the purpose of connecting the composite skins together, said composite skins and said dart forming a plurality of longitudinal hot air ducts.
Claim 2
Dependent Claim
161 words
An improved composite airfoil, said improved composite airfoil providing anti-icing and foreign object damage protection, the improvement comprising: a means for conducting heat to a leading edge of said airfoil, said means being composed of a metal, said means having composite skins thereon such that a plurality of air ducts are provided along the length of said means for conducting heat of said improved composite airfoil, said means for conducting heat being a metal dart comprising: a leading edge, said leading edge having an aerodynamic shape; a fin, said fin being connected to said leading edge at a rear section of said leading edge; at least one dam, said at least one dam being connected to a rearward edge of said fin and extending perpendicularly therefrom in both directions; and a plurality of opening means through said dart for the purpose of connecting the composite skins together, said composite skins and said dart forming a plurality of longitudinal hot air ducts.
Claim 3
Dependent Claim
44 words
An improved composite airfoil as defined in claim 1 wherein the composite skins comprise an upper skin and lower skin, each of the skins having a row of a plurality of tabs for bonding the upper skin to the lower skin through said openings.
Claim 4
Dependent Claim
44 words
An improved composite airfoil as defined in claim 1 wherein the composite skins comprise an upper skin and a lower skin, each of the skins having a row of a plurality of rivet holes for riveting the skins through said openings in said dart.
Claim 5
Dependent Claim
31 words
An improved composite airfoil as defined in claim 1 wherein said dart has a plurality of holes through said fin for the purpose of hot air flow between the air ducts.
Claim 6
Dependent Claim
27 words
An improved composite airfoil as defined in claim 2 wherein said fin further includes perturbances thereon for enhancing heat flow to said leading edge of said dart.
Claim 7
Dependent Claim
21 words
An improved composite airfoil as defined in claim 1 wherein said airfoil is an inlet guide vane for a jet engine.
Claim 8
Dependent Claim
15 words
An improved composite airfoil as defined in claim 1 wherein said airfoil is a strut.
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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) | 1995-02-03 | 1995-08-05 | 1996-02-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1999-02-03 | 1999-08-05 | 2000-02-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2003-02-03 | 2003-08-05 | 2004-02-04 | $7700.00 | Window Closed / Lapsed |