US4152488A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine blade tip alloy and composite
Assignee: RTX Corp
•
Filing: 1977-05-03
•
Granted: 1979-05-01
•
Expires: 1997-05-03
Abstract
Abstract A nickel base superalloy having a composition which provides a desirable combination of good oxidation and corrosion resistance and hot hardness is described. The alloy contains 21-25% Cr, 4.5-7% Al, 4-10% W, 2.5-7% Ta, 0.5-0.15% Y and 0.1-0.3% C. This alloy is useful as a blade tip element in a composite gas turbine blade.
Inventors
- 👤 Peter W. Schilke
- 👤 David N. Duhl
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 19:46
CPC Classifications
C; C22; C22C; C22C19/00; C22C19/03; C22C19/05; C22C19/051; C22C19/055; Y; Y10; Y10T; Y10T428/00; Y10T428/12; Y10T428/12493; Y10T428/12771; Y10T428/12861; Y10T428/12931; Y10T428/12944
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
38 words
A corrosion resistant nickel base superalloy having high, hot hardness and high abrasion resistance consisting essentially of: about 21-27% Cr, about 4.5-7% Al, about 5-10% W, about 2.5-7% Ta, about 0.02-0.15% Y, about 0.1-0.3% C, balance essentially nickel.
Claim 2
Dependent Claim
38 words
A corrosion resistant nickel base superalloy having high, hot hardness and high abrasion resistance consisting essentially of: about 21-27% Cr, about 4.5-7% Al, about 5-10% W, about 2.5-7% Ta, about 0.02-0.15% Y, about 0.1-0.3% C, balance essentially nickel.
Claim 3
Dependent Claim
14 words
An alloy as in claim 1 which also contains up to about 20% cobalt.
Claim 4
Dependent Claim
42 words
An alloy as in claim 1 wherein up to about one-fifth of the aluminum content is replaced by an equal atomic amount of titanium and up to about one-fifth of the tantalum content is replaced by an equal atomic amount of titanium.
Claim 5
Dependent Claim
40 words
An alloy as in claim 1 wherein up to about one-half of the yttrium content is replaced by an equal atomic amount of an oxygen active element selected from the group consisting of Ce, La, Hf, Zr, and mixtures thereof.
Claim 6
Dependent Claim
29 words
An alloy as in claim 1 which contains about 23-27% Cr, about 5-7% Al, about 7-9% W, about 3-5% Ta, about 0.05-0.15% Y, about 0.15-0.25% C, balance essentially nickel.
Claim 7
Dependent Claim
81 words
A composite blade useful in gas turbine engine consisting of a nickel base superalloy root and blade portion and a tip portion bonded thereto consisting of about 21-27% Cr, about 4.5-7% Al, about 5-10% W, about 2.5-7% Ta, about 0.02-0.15% Y, about 0.1-0.3% C, balance essentially nickel, said tip portion, having hot hardness properties similar to those of the root and blade portion and having oxidation and hot corrosion properties which are superior to those of the root and blade portion.
Claim 8
Dependent Claim
81 words
A composite blade useful in gas turbine engine consisting of a nickel base superalloy root and blade portion and a tip portion bonded thereto consisting of about 21-27% Cr, about 4.5-7% Al, about 5-10% W, about 2.5-7% Ta, about 0.02-0.15% Y, about 0.1-0.3% C, balance essentially nickel, said tip portion, having hot hardness properties similar to those of the root and blade portion and having oxidation and hot corrosion properties which are superior to those of the root and blade portion.
Claim 9
Dependent Claim
33 words
A composite blade as in claim 6 wherein the blade tip contains about 23-27% Cr, about 5-7% Al, about 7-9% W, about 3-6% Ta, about 0.05-0.15% Y, about 0.15-0.25% C, balance essentially nickel.
Claim 10
Dependent Claim
18 words
A composite blade as in claim 6 wherein the root and blade portion have an equiaxed polycrystalline microstructure.
Claim 11
Dependent Claim
18 words
A composite blade as in claim 6 wherein the root and blade portion have a polycrystalline columnar microstructure.
Claim 12
Dependent Claim
18 words
A composite blade as in claim 6 wherein the root and blade portion have a single crystal microstructure.
Claim 13
Independent Claim
53 words
A method for protecting gas turbine blade tips from oxidation, corrosion, and abrasion, which comprises alloying a layer of a nickel base superalloy to the blade tip, said superalloy consisting essentially of about 21-27% Cr, about 4.5-7% Al, about 5-10% W, about 2.5-7% Ta, about 0.02-0.15% Y, about 0.1-0.3% C, balance essentially nickel.
Claim 14
Independent Claim
53 words
A method for protecting gas turbine blade tips from oxidation, corrosion, and abrasion, which comprises alloying a layer of a nickel base superalloy to the blade tip, said superalloy consisting essentially of about 21-27% Cr, about 4.5-7% Al, about 5-10% W, about 2.5-7% Ta, about 0.02-0.15% Y, about 0.1-0.3% C, balance essentially nickel.
References Cited (Backward Citations)
US3754902A
Cited
US4013424A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1982-04-30 | 1982-10-30 | 1983-05-01 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-04-30 | 1986-10-30 | 1987-05-01 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-04-30 | 1990-10-30 | 1991-05-01 | $7700.00 | Window Closed / Lapsed |