US4714624A
Expired / Lapsed
US
⏱️ 0.0 years remaining
High temperature oxidation/corrosion resistant coatings
Assignee: Honeywell International Inc
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Filing: 1986-02-21
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Granted: 1987-12-22
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Expires: 2006-02-21
Abstract
Abstract Disclosed is a novel high temperature coating system comprised of two successively deposited layers of different respective materials which may be applied to turbine engine components to provide improved oxidation and corrosion resistance. The second applied layer is a composition having the general formula MCrAlY wherein M is a solid solution of molybdenum in nickel, cobalt or nickel plus cobalt. The first applied layer or interlayer, which is applied directly to the turbine engine component, is an aluminum coating.
Inventors
- 👤 Subhash K. Naik
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 11:56
CPC Classifications
C; C23; C23C; C23C26/00; C23C30/00
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
112 words
A process for manufacturing an individual engine component having a simplified airfoil shape which comprises first aluminide-coating said component; then overcoating same with a MCrAlY composition wherein M is a solid solution of molybdenum and a second metal selected from the group consisting of nickel, cobalt and mixtures thereof, the composition being comprised of from about 0.1 to about 18% by weight of molybdenum, about 30 to about 70% by weight of the second metal, about 10 to about 40% by weight of chromium about 6 to about 20% by weight of aluminum and about 0.01 to about 3% by weight of yttrium; and then subjecting said component to diffusional heat treatment.
Claim 2
Dependent Claim
112 words
A process for manufacturing an individual engine component having a simplified airfoil shape which comprises first aluminide-coating said component; then overcoating same with a MCrAlY composition wherein M is a solid solution of molybdenum and a second metal selected from the group consisting of nickel, cobalt and mixtures thereof, the composition being comprised of from about 0.1 to about 18% by weight of molybdenum, about 30 to about 70% by weight of the second metal, about 10 to about 40% by weight of chromium about 6 to about 20% by weight of aluminum and about 0.01 to about 3% by weight of yttrium; and then subjecting said component to diffusional heat treatment.
Claim 3
Dependent Claim
16 words
The process of claim 1 wherein said engine component comprises a single blade or single vane.
Claim 4
Dependent Claim
132 words
A process for manufacturing either an individual engine component with complex airfoils or an integral segmented component which comprises first aluminide-coating said component over the airfoil surfaces; then overcoating same with a MCrAlY composition at selected regions of the airfoil requiring superior oxidation and corrosion resistance wherein M is a solid solution of molybdenum and a second metal selected from the group consisting of nickel, cobalt and mixtures thereof, the composition being comprised of from about 0.1 to about 18% by weight of molybdenum, about 30 to about 70% by weight of the second metal, about 10 to about 40% by weight of chromium, about 6 to about 20% by weight of aluminum and about 0.01 to about 3% by weight of yttrium; and then subjecting the component to diffusional heat treatment.
Claim 5
Dependent Claim
132 words
A process for manufacturing either an individual engine component with complex airfoils or an integral segmented component which comprises first aluminide-coating said component over the airfoil surfaces; then overcoating same with a MCrAlY composition at selected regions of the airfoil requiring superior oxidation and corrosion resistance wherein M is a solid solution of molybdenum and a second metal selected from the group consisting of nickel, cobalt and mixtures thereof, the composition being comprised of from about 0.1 to about 18% by weight of molybdenum, about 30 to about 70% by weight of the second metal, about 10 to about 40% by weight of chromium, about 6 to about 20% by weight of aluminum and about 0.01 to about 3% by weight of yttrium; and then subjecting the component to diffusional heat treatment.
Claim 6
Dependent Claim
40 words
The process of claims 1, 2 or 3 wherein said diffusional heat treatment takes place at about 1975° F. for about 4 hours in either an argon atmosphere or in a vacuum under a pressure of about 10 -3 Torr.
Claim 7
Dependent Claim
34 words
The process of claim 4 wherein the MCrAlY coating layer further contains about 0.1 to about 10% by weight of a metal selected from the group consisting of Hf, Si, Ti, Mn and Pt.
Claim 8
Dependent Claim
27 words
The process of claim 4 wherein the aluminide coating deposit has a composition which contains about 22 to about 40% by weight aluminum, the balance being nickel.
Claim 9
Dependent Claim
28 words
The process of claim 4 wherein the aluminide coating is about 25 to about 75 μm thick and the MCrAlY composition is about 25 to about 150μm thick.
Claim 10
Dependent Claim
17 words
The process of claim 4 wherein the component is comprised of a nickel-base or a cobalt-base super-alloy.
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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) | 1990-12-21 | 1991-06-22 | 1991-12-22 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1994-12-21 | 1995-06-22 | 1995-12-22 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1998-12-21 | 1999-06-22 | 1999-12-22 | $7700.00 | Window Closed / Lapsed |