US4303737A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Coating material
Assignee: Rolls Royce PLC
•
Filing: 1980-07-16
•
Granted: 1981-12-01
•
Expires: 2000-07-16
Abstract
Abstract A powder suitable for flame spraying comprising particles of an alumino silicate glass, each of the particles being hollow and coated with an alloy containing, by weight, 80% nickel, 2.5% aluminium, 15.7% chromium and 1.8% silicon. The resultant coating is particularly suitable for use as a thermal barrier.
Inventors
- 👤 William B. Litchfield
- 👤 John T. Gent
- 👤 James A. S. Graham
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 17:11
CPC Classifications
C; C23; C23C; C23C4/00; C23C4/04; C23C4/06; C23C4/02; Y; Y10; Y10T; Y10T428/00; Y10T428/29; Y10T428/2982; Y10T428/2991; Y10T428/2993; Y10T428/2996
Claims Analysis
Total Claims: 20
Claim 1
Independent Claim
47 words
A powder suitable for flame spraying comprising: particles of a glass, each of said particles being hollow and coated with a metal, said metal being selected from the group consisting of a cobalt based alloy and a nickel based alloy, said alloy containing aluminum, chromium and silicon.
Claim 2
Dependent Claim
47 words
A powder suitable for flame spraying comprising: particles of a glass, each of said particles being hollow and coated with a metal, said metal being selected from the group consisting of a cobalt based alloy and a nickel based alloy, said alloy containing aluminum, chromium and silicon.
Claim 3
Dependent Claim
16 words
A powder as claimed in claim 1 wherein said alloy contains at least one rare earth.
Claim 4
Dependent Claim
22 words
A powder as claimed in claims 1 or 2 wherein said glass constitutes from 5 to 90% by weight of each particle.
Claim 5
Dependent Claim
17 words
A powder as claimed in claims 1 or 2 wherein said glass is an alumino silicate glass.
Claim 6
Dependent Claim
21 words
A powder as claimed in claims 1 or 2 wherein said particles are within the size range 20 to 250 μm.
Claim 7
Dependent Claim
74 words
A powder suitable for flame spraying comprising particles of a glass, each of said particles being hollow and coated with an alloy comprising, by weight, 80% nickel, 2.5% aluminium, 15.7% chromium, and 1.8% silicon, said glass comprising by weight 31.9% Al 2 O 3 , 60.75% SiO 2 , 4.18% Fe 2 O 3 , 1.91% K 2 O and 0.81% Na 2 O and constituting 10% by weight of each of said particles.
Claim 8
Dependent Claim
74 words
A powder suitable for flame spraying comprising particles of a glass, each of said particles being hollow and coated with an alloy comprising, by weight, 80% nickel, 2.5% aluminium, 15.7% chromium, and 1.8% silicon, said glass comprising by weight 31.9% Al 2 O 3 , 60.75% SiO 2 , 4.18% Fe 2 O 3 , 1.91% K 2 O and 0.81% Na 2 O and constituting 10% by weight of each of said particles.
Claim 9
Independent Claim
120 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating which is sufficiently ductile to resist flaking off of the surface as a result of differing rates of thermal expansion of the surface and the coating comprising: forming a powder consisting of glass particles, each of said glass particles being hollow and being provided with a continuous metal coating; and flame spraying the powder on to the surface of the gas turbine engine to a depth within a range of 0.2 to 0.7 mm., the metal coating of the hollow glass particles bonding adjacent particles to each other and to the surface of the gas turbine engine to form the thermal barrier coating thereon.
Claim 10
Independent Claim
120 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating which is sufficiently ductile to resist flaking off of the surface as a result of differing rates of thermal expansion of the surface and the coating comprising: forming a powder consisting of glass particles, each of said glass particles being hollow and being provided with a continuous metal coating; and flame spraying the powder on to the surface of the gas turbine engine to a depth within a range of 0.2 to 0.7 mm., the metal coating of the hollow glass particles bonding adjacent particles to each other and to the surface of the gas turbine engine to form the thermal barrier coating thereon.
Claim 11
Dependent Claim
40 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating as claimed in claim 7 wherein said metal is selected from the group consisting of a cobalt based alloy and a nickel based alloy.
Claim 12
Dependent Claim
28 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating as claimed in claim 8 wherein said alloy contains aluminum and chromium.
Claim 13
Dependent Claim
30 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating as claimed in claim 9 wherein said alloy contains at least one rare earth.
Claim 14
Dependent Claim
26 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating as calimed in claim 9 wherein said alloy contains silicon.
Claim 15
Dependent Claim
26 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating as claimed in claim 10 wherein said alloy contains silicon.
Claim 16
Dependent Claim
34 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating as claimed in claim 7 wherein said glass constitutes from 5 to 90% by weight of each particle.
Claim 17
Dependent Claim
29 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating as claimed in claim 7 wherein said glass is an alumino silicate glass.
Claim 18
Dependent Claim
33 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating as claimed in claim 7 wherein said particles are within the size range 20 to 250 μm.
Claim 19
Dependent Claim
46 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating as claimed in claim 7 wherein a further coating is subsequently applied to said thermal barrier coating, said further coating being selected from the group consisting of metals and ceramics.
Claim 20
Dependent Claim
47 words
A method of providing a surface of a gas turbine engine with a thermal barrier coating as claimed in claim 7 wherein said powder is mixed with a further powder prior to flame spraying, said further powder being selected from the group consisting of metals and ceramics.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1984-11-30 | 1985-06-01 | 1985-12-01 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-11-30 | 1989-06-01 | 1989-12-01 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-11-30 | 1993-06-01 | 1993-12-01 | $7700.00 | Window Closed / Lapsed |