US3909157A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbine nozzle-vane construction
Assignee: Chromalloy American Corp
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Filing: 1973-11-21
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Granted: 1975-09-30
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Expires: 1993-11-21
Abstract
Abstract The invention contemplates a multi-part construction for a turbine-nozzle assembly, to take the place of certain singlepiece investment castings currently in use for such assemblies, intended primarily for gas-turbine application. The construction basically employs a blade element of desired airfoil-section development, and two base members, each locally recessed to define a locating socket or opening for the respective longitudinal ends of the blade. The recesses are carefully controlled in their location with respect to base-member geometry, to the end that the assembly may produce a given performance-class number for the resulting nozzle, once assembled and united into an integral whole, by welding, brazing, coating and the like finishing steps. The construction is described in the context of methods of achieving the same (a) as new construction and (b) as repair of worn conventional constructions, i.e., constructions which were originally fabricated as single-piece investment castings, but which have served their normal life span and are therefore consigned to disposal as scrap. The invention is also described in the context of application (a) to a single-piece gas-turbine nozzle assembly or stage, and (b) to a single-piece nozzle-component assembly.
Inventors
- 👤 Richard L Wachtell
- 👤 Edward C Palmenberg
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 02:35
CPC Classifications
B; B23; B23P; B23P6/00; B23P6/002; B23P6/005; F; F01; F01D; F01D5/00; F01D5/005; F01D9/00; F01D9/02; F01D9/04; F01D9/045; F05; F05D; F05D2220/00; F05D2220/50; Y; Y10; Y10T; Y10T29/00; Y10T29/49; Y10T29/49316; Y10T29/49318
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
191 words
As an article of manufacture, a nozzle-vane assembly comprising a longitudinally extending blade element of desired airfoil section, spaced first and second unitary base members having opposed adjacent smooth inner faces and having outer faces spaced from said inner faces, each of said inner faces having a straight-walled recess of constant section corresponding to that of one end of said blade, the spacing between said inner faces being a given blade span, the airfoil of said blade element extending longitudinally for a span which exceeds said given blade span by an amount at least no greater than the combined depths of said recesses, the profile and profile orientation of each recess and of the blade section fitted thereto being so precise as to establish by such fit alone the correct blade-base member orientation for the design class nUmber of the nozzle-vane assembly, said blade element and base members being welded at and for retention of their interfit, and means including a fused filler flux-drawn into the regions of interfit and further uniting the ends of the airfoil section of said blade element to adjacent overlapped regions of said unitary base members.
Claim 2
Dependent Claim
191 words
As an article of manufacture, a nozzle-vane assembly comprising a longitudinally extending blade element of desired airfoil section, spaced first and second unitary base members having opposed adjacent smooth inner faces and having outer faces spaced from said inner faces, each of said inner faces having a straight-walled recess of constant section corresponding to that of one end of said blade, the spacing between said inner faces being a given blade span, the airfoil of said blade element extending longitudinally for a span which exceeds said given blade span by an amount at least no greater than the combined depths of said recesses, the profile and profile orientation of each recess and of the blade section fitted thereto being so precise as to establish by such fit alone the correct blade-base member orientation for the design class nUmber of the nozzle-vane assembly, said blade element and base members being welded at and for retention of their interfit, and means including a fused filler flux-drawn into the regions of interfit and further uniting the ends of the airfoil section of said blade element to adjacent overlapped regions of said unitary base members.
Claim 3
Dependent Claim
24 words
The article of claim 1, in which said fused filler includes an integral fillet at intersection of said blade element with each inner face.
Claim 4
Dependent Claim
14 words
The article of claim 1, in which each base member is a vane buttress.
Claim 5
Dependent Claim
42 words
The article of claim 2, in which said base members are axially spaced rings, and in which the recess in each inner face is one of a plurality of uniformly angularly spaced recesses, said blade element being one of a corresponding plurality.
Claim 6
Dependent Claim
59 words
The article of claim 4, in which a second plurality of recesses in said inner faces is interlaced between those of said first plurality, the recesses of said second plurality being of said airfoil section and of depth less than ring thickness, and a second plurality of blades of said section received in the recesses of said second plurality.
Claim 7
Dependent Claim
275 words
As an article of manufacture, a nozzle-vane assembly comprising a longitudinally extending blade element of desired airfoil section, the profile of said section having axial ends each of which terminates in a transverse plane of relief from such profile, thereby defining an end-abutment seat adjacent such profile at each axial end, spaced first and second unitary base members having opposed adjacent inner faces and having outer faces spaced from said inner faces, each of said inner faces having a flat-bottomed straight-walled recess of constant section corresponding to that of one end of said blade and of depth less than the inner-to-outer face thickness of the particular base member, each base member having at its recess a longitudinally extending through-aperture of less than said airfoil-section area, the spacing between said inner faces being a given blade span, the airfoil section of said blade element extending longitudinally for a span which exceeds said given blade span by an amount at least no greater than the combined depth of said recesses, the profile and profile orientation of each recess and of the blade section fitted thereto being so precise as to establish by such fit alone the correct blade-base member orientation for the design class number of the nozzle-vane assembly, said end-abutment seats engaging the flat-bottom regions of the recesses to which they are fitted, fastening means including members passing through said respective apertures and rigidly welded to said base members at the respective outer faces thereof to retain the interfit of all blade elements at their recesses, and fused filler material flux-drawn into the regions in interfit and further uniting said blade elements to said base members.
Claim 8
Dependent Claim
275 words
As an article of manufacture, a nozzle-vane assembly comprising a longitudinally extending blade element of desired airfoil section, the profile of said section having axial ends each of which terminates in a transverse plane of relief from such profile, thereby defining an end-abutment seat adjacent such profile at each axial end, spaced first and second unitary base members having opposed adjacent inner faces and having outer faces spaced from said inner faces, each of said inner faces having a flat-bottomed straight-walled recess of constant section corresponding to that of one end of said blade and of depth less than the inner-to-outer face thickness of the particular base member, each base member having at its recess a longitudinally extending through-aperture of less than said airfoil-section area, the spacing between said inner faces being a given blade span, the airfoil section of said blade element extending longitudinally for a span which exceeds said given blade span by an amount at least no greater than the combined depth of said recesses, the profile and profile orientation of each recess and of the blade section fitted thereto being so precise as to establish by such fit alone the correct blade-base member orientation for the design class number of the nozzle-vane assembly, said end-abutment seats engaging the flat-bottom regions of the recesses to which they are fitted, fastening means including members passing through said respective apertures and rigidly welded to said base members at the respective outer faces thereof to retain the interfit of all blade elements at their recesses, and fused filler material flux-drawn into the regions in interfit and further uniting said blade elements to said base members.
Claim 9
Dependent Claim
64 words
The article of claim 6, in which said fastening members are end tangs projecting integrally beyond the respective ends of the airfoil section length of said blade element, each of said apertures communicating with the bottom of one of said recesses in aligned registry with one of said tangs when an end of the airfoil section of the blade is received in its recess.
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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) | 1978-09-29 | 1979-03-31 | 1979-09-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-09-29 | 1983-03-31 | 1983-09-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-09-29 | 1987-03-31 | 1987-09-30 | $7700.00 | Window Closed / Lapsed |