US3650635A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbine vanes
Assignee: Chromalloy American Corp
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Filing: 1970-03-09
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Granted: 1972-03-21
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Expires: 1990-03-09
Abstract
Abstract An improved airfoil is provided for turbine engines having locating buttresses at opposite ends thereof, said airfoil having a leading edge and a trailing edge. The body of the airfoil section has a polycrystalline structure of equiaxed grains, at least one of the airfoil edges being comprised of a welded insert having grains running longitudinally of said edge.
Inventors
- 👤 Richard Lloyd Wachtell
- 👤 Edward C Palmenberg
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 13:26
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/005; B; B22; B22D; B22D27/00; B22D27/04; B22D27/045; B23; B23P; B23P6/00; B23P6/002; B23P6/005; C; C30; C30B; C30B11/00; C30B29/00; C30B29/10; C30B29/52; F01D5/12; F01D5/14; F01D5/18; F01D5/28; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10T; Y10T29/00; Y10T29/49; Y10T29/49316; Y10T29/49336; Y10T29/49337; Y10T29/49718; Y10T29/49732; Y10T29/49734; Y10T29/49737
Claims Analysis
Total Claims: 17
Claim 1
Independent Claim
42 words
An improved airfoil thermal element for turbine engines, substantially the body of which has a polycrystalline structure with equiaxed grains, an airfoil edge of which is formed as a welded insert having columnar grains which are substantially parallel to said airfoil edge.
Claim 2
Dependent Claim
42 words
An improved airfoil thermal element for turbine engines, substantially the body of which has a polycrystalline structure with equiaxed grains, an airfoil edge of which is formed as a welded insert having columnar grains which are substantially parallel to said airfoil edge.
Claim 3
Dependent Claim
11 words
The improved airfoil of claim 1, wherein the airfoil is hollow.
Claim 4
Dependent Claim
15 words
The improved airfoil of claim 1, wherein the airfoil edge insert is a trailing edge.
Claim 5
Dependent Claim
33 words
The improved airfoil of claim 3, wherein the airfoil is hollow, and wherein said trailing edge has cooling holes disposed transversely of said trailing edge which communicate with the hollow of said vane.
Claim 6
Dependent Claim
49 words
An improved turbine guide vane of a heat resistant alloy having an airfoil section substantially the body of which has a polycrystalline structure with equiaxed grains, an airfoil edge of the vane being formed as a welded insert having columnar grains which are substantially parallel to said airfoil edge.
Claim 7
Dependent Claim
49 words
An improved turbine guide vane of a heat resistant alloy having an airfoil section substantially the body of which has a polycrystalline structure with equiaxed grains, an airfoil edge of the vane being formed as a welded insert having columnar grains which are substantially parallel to said airfoil edge.
Claim 8
Dependent Claim
13 words
The improved turbine guide vane of claim 5, wherein the vane is hollow.
Claim 9
Dependent Claim
17 words
The improved turbine guide vane of claim 5, wherein the airfoil edge insert is a trailing edge.
Claim 10
Dependent Claim
35 words
The improved turbine guide vane of claim 7, wherein the vane is hollow and wherein said trailing edge has cooling holes disposed transversely of said trailing edge which communicate with the hollow of said vane.
Claim 11
Dependent Claim
27 words
The improved turbine guide vane of claim 5, wherein the heat resistant alloy of the vane is selected from the group consisting of nickel-base and cobalt-base superalloys.
Claim 12
Dependent Claim
66 words
A turbine guide vane of a heat resistant alloy comprising an airfoil section with locating buttresses at opposite ends thereof, said airfoil section having a leading edge and a trailing edge, substantially the body of said airfoil section having a polycrystalline structure with equiaxed grains, at least one of the airfoil edges being a welding insert having columnar grains running substantially parallel to said airfoil edge.
Claim 13
Dependent Claim
66 words
A turbine guide vane of a heat resistant alloy comprising an airfoil section with locating buttresses at opposite ends thereof, said airfoil section having a leading edge and a trailing edge, substantially the body of said airfoil section having a polycrystalline structure with equiaxed grains, at least one of the airfoil edges being a welding insert having columnar grains running substantially parallel to said airfoil edge.
Claim 14
Dependent Claim
13 words
The improved turbine guide vane of claim 10, wherein the vane is hollow.
Claim 15
Dependent Claim
16 words
The improved turbine guide vane of claim 10, wherein the airfoil edge is the trailing edge.
Claim 16
Dependent Claim
29 words
The improved turbine guide vane of claim 12, wherein said trailing edge has cooling holes disposed transversely of said trailing edge which communicate with the hollow of said vane.
Claim 17
Dependent Claim
27 words
The improved turbine guide vane of claim 10, wherein the heat resistant alloy of the vane is selected from the group consisting of nickel-base and cobalt-base superalloys.
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) | 1975-03-21 | 1975-09-20 | 1976-03-21 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-03-21 | 1979-09-20 | 1980-03-21 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-03-21 | 1983-09-20 | 1984-03-21 | $7700.00 | Window Closed / Lapsed |