Patent US4530885A successfully refreshed from Google Patents.
US4530885A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Nickel or cobalt alloy composite
Assignee: Qinetiq Ltd
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Filing: 1982-04-12
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Granted: 1985-07-23
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Expires: 2002-04-12
Abstract
Abstract An alloy having the nominal composition Ni--30/40 wt % Cr--1/5 wt % Ti--2/8 wt % Al is used for coating gas turbine components to give protection against oxidation--and sulphidation--corrosion. A specific alloy having the composition Ni--37 Cr--3 Ti--2Al is applied to a blade fabricated from a nickel superalloy by sputter ion plating to give an overlay coating up to 100 μm thick. Preferably a platinum intermediate layer is flashed on to the substrate before coating. The coating alloy can additionally include rare earths, hafnium or silicon.
Inventors
- 👤 James E. Restall
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 23:26
CPC Classifications
C; C23; C23C; C23C30/00; C22; C22C; C22C19/00; C22C19/03; C22C19/05; C22C19/07; C23C28/00; C23C28/02; C23C28/023; F; F01; F01D; F01D5/00; F01D5/12; F01D5/28; F01D5/288; Y; Y10; Y10T; Y10T428/00; Y10T428/12; Y10T428/12493; Y10T428/12771; Y10T428/12861; Y10T428/12875; Y10T428/12944
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
92 words
A gas turbine engine component having an overlay coating and an intermediate layer between said component and said overlay coating, said coating being particularly resistant to sulphidation corrosion of the type experienced at 750° C., said coating having a composition consisting essentially of, in weight percent: chromium: 30 to 40 titanium: 1 to 5 aluminum: 2 to 10 remainder selected from the group consisting of nickel, cobalt and nickel plus cobalt, and said intermediate layer not exceeding 25 μm of a metal selected from the group consisting of platinum, rhodium and nickel.
Claim 2
Dependent Claim
92 words
A gas turbine engine component having an overlay coating and an intermediate layer between said component and said overlay coating, said coating being particularly resistant to sulphidation corrosion of the type experienced at 750° C., said coating having a composition consisting essentially of, in weight percent: chromium: 30 to 40 titanium: 1 to 5 aluminum: 2 to 10 remainder selected from the group consisting of nickel, cobalt and nickel plus cobalt, and said intermediate layer not exceeding 25 μm of a metal selected from the group consisting of platinum, rhodium and nickel.
Claim 3
Dependent Claim
54 words
A gas turbine engine component having an overlay coating, the coating being particularly resistant to sulphidation corrosion of the type experienced at 750° C., said coating having a composition consisting essentially of, in weight percent: chromium: 37 titanium: 3 aluminium: 2 remainder selected from the group consisting of nickel, cobalt and nickel plus cobalt.
Claim 4
Dependent Claim
54 words
A gas turbine engine component having an overlay coating, the coating being particularly resistant to sulphidation corrosion of the type experienced at 750° C., said coating having a composition consisting essentially of, in weight percent: chromium: 37 titanium: 3 aluminium: 2 remainder selected from the group consisting of nickel, cobalt and nickel plus cobalt.
Claim 5
Dependent Claim
92 words
A gas turbine engine component having an overlay coating and an intermediate layer between said component and said overlay coating, said coating being particularly resistant to sulphidation corrosion of the type experienced at 750° C., said cotating having a composition consisting of, in weight percent: chromium: 30 to 40 titanium: 1 to 5 aluminum: 2 to 10 remainder selected from the group consisting of nickel, cobalt and nickel plus cobalt, and said intermediate layer not exceeding 25 μm of a layer metal selected from the group consisting of platinum, rhodium and nickel.
Claim 6
Dependent Claim
92 words
A gas turbine engine component having an overlay coating and an intermediate layer between said component and said overlay coating, said coating being particularly resistant to sulphidation corrosion of the type experienced at 750° C., said cotating having a composition consisting of, in weight percent: chromium: 30 to 40 titanium: 1 to 5 aluminum: 2 to 10 remainder selected from the group consisting of nickel, cobalt and nickel plus cobalt, and said intermediate layer not exceeding 25 μm of a layer metal selected from the group consisting of platinum, rhodium and nickel.
Claim 7
Dependent Claim
56 words
A gas turbine engine component having an overlay coating, the coating being particularly resistant to sulphidation corrosion of the type experienced at 750° C., said coating having a composition consisting essentially of, in weight percent: chromium: 30 titanium: 2 aluminium: 8 silicon: 5 remainder selected from the group consisting of nickel, cobalt and nickel plus cobalt.
Claim 8
Dependent Claim
56 words
A gas turbine engine component having an overlay coating, the coating being particularly resistant to sulphidation corrosion of the type experienced at 750° C., said coating having a composition consisting essentially of, in weight percent: chromium: 30 titanium: 2 aluminium: 8 silicon: 5 remainder selected from the group consisting of nickel, cobalt and nickel plus cobalt.
Claim 9
Dependent Claim
34 words
A gas turbine engine component according to claim 1, wherein the overlay coating contains from 0.1 to 3 weight percent of rare earth metal selected from the group consisting of yttrium, scandium and lanthanum.
Claim 10
Dependent Claim
20 words
A gas turbine engine component according to claim 1, wherein the overlay coating contains up to 10 weight percent hafnium.
Claim 11
Dependent Claim
22 words
A gas turbine engine component according to claim 1, wherein said overlay coating contains about 2 to about 8 weight percent aluminum.
Claim 12
Dependent Claim
22 words
A gas turbine engine component according to claim 3, wherein said overlay coating contains about 2 to about 8 weight percent aluminum.
References Cited (Backward Citations)
US4054723A
Cited
US4214042A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1988-07-22 | 1989-01-21 | 1989-07-23 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-07-22 | 1993-01-21 | 1993-07-23 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-07-22 | 1997-01-21 | 1997-07-23 | $7700.00 | Window Closed / Lapsed |