US3802046A
Expired / Lapsed
US
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Method of making or reconditioning a turbine-nozzle or the like assembly
Assignee: Chromalloy American Corp
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Filing: 1972-01-27
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Granted: 1974-04-09
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Expires: 1992-01-27
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
- 👤 R Wachtell
- 👤 E Palmenberg
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 18:15
CPC Classifications
B; B23; B23P; B23P6/00; B23P6/002; B23P6/005; B23H; B23H9/00; B23H9/10; F; F01; F01D; 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; Y10T29/49718; Y10T29/49732; Y10T29/49734; Y10T29/49737
Claims Analysis
Total Claims: 23
Claim 1
Independent Claim
201 words
The method of reconditioning a gas-turbine vane assembly comprising base members integrally united at opposed inner faces to a blade of span extending between said members, said method comprising removing all blade material between said faces, such removal being to the extent of establishing a predetermined reference inner-face surface on each base member, recessing said inner-face surfaces with a section corresponding to desired reconditioned blade section and to a depth less than base-member thickness, selecting a new blade element (a) of length corresponding to said span plus the combined effective depth of said recesses and (b) of said reconditioned blade section, assembling said blade element to the recessed regions of said bAse members, and permamently securing said assembly; said recessing step comprising the further steps of selecting an elongate boring-tool element of desired bore section, mounting the two base members with their inner faces opposed at a spacing which exceeds the length of the tool element, supporting and operating said tool element with its elongation axis extending between said faces, and progressively feeding said base members with respect to each other and with respect to said tool element to the extent of said tool recessing both base members to said depth.
Claim 2
Independent Claim
201 words
The method of reconditioning a gas-turbine vane assembly comprising base members integrally united at opposed inner faces to a blade of span extending between said members, said method comprising removing all blade material between said faces, such removal being to the extent of establishing a predetermined reference inner-face surface on each base member, recessing said inner-face surfaces with a section corresponding to desired reconditioned blade section and to a depth less than base-member thickness, selecting a new blade element (a) of length corresponding to said span plus the combined effective depth of said recesses and (b) of said reconditioned blade section, assembling said blade element to the recessed regions of said bAse members, and permamently securing said assembly; said recessing step comprising the further steps of selecting an elongate boring-tool element of desired bore section, mounting the two base members with their inner faces opposed at a spacing which exceeds the length of the tool element, supporting and operating said tool element with its elongation axis extending between said faces, and progressively feeding said base members with respect to each other and with respect to said tool element to the extent of said tool recessing both base members to said depth.
Claim 3
Dependent Claim
27 words
The method of claim 1, wherein said securing step includes filling and fusing all adjacent surface areas of said blade element at assembly thereof to said recesses.
Claim 4
Dependent Claim
54 words
The method of claim 1, wherein blade material is removed by first cutting the blade in a location between said base members, thereby defining separate base members each with an integral truncated fraction of a blade, and for each thus-separated member removing the truncated-blade material to the extent of said predetermined reference inner-face surface.
Claim 5
Dependent Claim
23 words
The method of claim 1, wherein said tool element is operated by subjecting said base members and tool element to an EDM environment.
Claim 6
Independent Claim
148 words
The method of reconditioning a gas-turbine vane assembly comprising base members integrally united at opposed inner faces to a blade of span extending between said members, said method comprising removing all blade material between said faces, such removal being by the steps of first cutting the blade at a location between said base members, thereby defining separate base members each with an integral truncated fraction of a blade, and for each thus-separated member removing the truncated-blade material to a predetermined reference inner-face surface; recessing said inner-face surfaces with a section corresponding to desired reconditioned blade section and to a depth less than base-member thickness, selecting a new blade element (a) of length corresponding to said span plus the combined effective depth of said recesses and (b) of said reconditioned blade section, assembling said blade element to the recessed regions of said base members, and permanently securing said assembly.
Claim 7
Independent Claim
148 words
The method of reconditioning a gas-turbine vane assembly comprising base members integrally united at opposed inner faces to a blade of span extending between said members, said method comprising removing all blade material between said faces, such removal being by the steps of first cutting the blade at a location between said base members, thereby defining separate base members each with an integral truncated fraction of a blade, and for each thus-separated member removing the truncated-blade material to a predetermined reference inner-face surface; recessing said inner-face surfaces with a section corresponding to desired reconditioned blade section and to a depth less than base-member thickness, selecting a new blade element (a) of length corresponding to said span plus the combined effective depth of said recesses and (b) of said reconditioned blade section, assembling said blade element to the recessed regions of said base members, and permanently securing said assembly.
Claim 8
Dependent Claim
60 words
The method of claim 5 including the further step of forming a through-passage in each base member from the bottom of the recess to the outer face of the base member, said through-passage being of section less than the recess section, and wherein the selected blade element includes integral axial end projections received in the respective through-passages upon said assembly.
Claim 9
Dependent Claim
22 words
The method of claim 6, in which said securing step includes welding said projections to adjacent outer regions of said base members.
Claim 10
Independent Claim
201 words
The method of reconditioning a gas-turbine vane assembly comprising base members integrally united at opposed inner faces to a blade of span extending between said members, said method comprising removing all blade material between said faces, such removal being to the extent of establishing a predetermined reference inner-face surface on each base member, recessing said inner-face surfaces with a section corresponding to desired reconditioned blade section and to the extent of local base-member thickness; selecting a new blade element (a) of length corresponding to said span plus the combined effective depth of said recesses and (b) of said reconditioned blade section, assembling said blade element to the recessed regions of said base members, and permanently securing said assembly; said recessing step comprising the further steps of selecting an elongate boring-tool element of desired bore section, mounting the two base members with their inner faces opposed at a spacing which exceeds the length of the tool element, supporting and operating said tool element with its elongation axis extending between said faces, and progressively feeding said base members with respect to each other and with respect to said tool element to the extent of said tool recessing boTh base members to said depth.
Claim 11
Independent Claim
201 words
The method of reconditioning a gas-turbine vane assembly comprising base members integrally united at opposed inner faces to a blade of span extending between said members, said method comprising removing all blade material between said faces, such removal being to the extent of establishing a predetermined reference inner-face surface on each base member, recessing said inner-face surfaces with a section corresponding to desired reconditioned blade section and to the extent of local base-member thickness; selecting a new blade element (a) of length corresponding to said span plus the combined effective depth of said recesses and (b) of said reconditioned blade section, assembling said blade element to the recessed regions of said base members, and permanently securing said assembly; said recessing step comprising the further steps of selecting an elongate boring-tool element of desired bore section, mounting the two base members with their inner faces opposed at a spacing which exceeds the length of the tool element, supporting and operating said tool element with its elongation axis extending between said faces, and progressively feeding said base members with respect to each other and with respect to said tool element to the extent of said tool recessing boTh base members to said depth.
Claim 12
Dependent Claim
45 words
The method of claim 8, wherein said securing step includes welding the outer ends of said blade element to adjacent outer regions of said base members, and filling and fusing all remaining adjacent interface areas at assembly of the blade element to the base members.
Claim 13
Independent Claim
151 words
The method of reconditioning an annular nozzle assembly for a gas-turbine, such assembly comprising an integral structure of annular base members axially spaced by plural angularly spaced bridging nozzle-blade span connections, which method comprises cutting all bridge connections to create two separate base members each with plural integral truncated blade stumps, removing blade-stump material from each such base member to a predetermined reference surface, thus defining a reference-surface inner face, recessing said faces at plural angularly spaced blade-positioning locations, said recesses being with predetermined blade section and incidence and to a depth less than base-member thickness, selecting a plurality of blade elements of said predetermined section and of length corresponding to said span plus the combined effective depth of recesses in both base members, assembling the blade elements to corresponding opposed pairs of recesses in said base members, and fusing all blade elements to said base members in such assembled relation.
Claim 14
Independent Claim
151 words
The method of reconditioning an annular nozzle assembly for a gas-turbine, such assembly comprising an integral structure of annular base members axially spaced by plural angularly spaced bridging nozzle-blade span connections, which method comprises cutting all bridge connections to create two separate base members each with plural integral truncated blade stumps, removing blade-stump material from each such base member to a predetermined reference surface, thus defining a reference-surface inner face, recessing said faces at plural angularly spaced blade-positioning locations, said recesses being with predetermined blade section and incidence and to a depth less than base-member thickness, selecting a plurality of blade elements of said predetermined section and of length corresponding to said span plus the combined effective depth of recesses in both base members, assembling the blade elements to corresponding opposed pairs of recesses in said base members, and fusing all blade elements to said base members in such assembled relation.
Claim 15
Dependent Claim
89 words
The method of claim 10, including the further step of forming at each of at least some of the corresponding recess locations of both base members a through-passage from the bottom of each such recess to the outer face of the base member, said through-passages being of section less than the recess section, and the blade elements which are selected for assembly at through-passage recesses being further selected with integral end projections fitted to said through-passages, and welding the end projections to adjacent outer regions of said base members.
Claim 16
Independent Claim
200 words
The method of making a gas-turbine vane assembly comprising the steps of selecting two base members to be united at opposed inner faces to a blade of span extending between said members, forming each of said faces with a recess having a section corresponding to desired blade section and to a depth less than base-member thickness, selecting a blade element of said blade section and of length corresponding to said span plug the combined effective depth of said recesses, assembling said blade element to the recessed regions of said base members, and permanently securing said assembly, said recess-forming step comprising the further steps of selecting an elongate boring-tool element of desired bore section, mounting the two base members with their inner faces opposed at a spacing which exceeds the length of said tool element, supporting said tool element with its elongation axis extending between said faces, subjecting said base members and tool element to an EDM environment wherein the tool element determines the section of bored removal of base-member material, and progressively feeding said base members with respect to each other and with respect to said tool element to the extent of tool boring both base members to said depth.
Claim 17
Independent Claim
200 words
The method of making a gas-turbine vane assembly comprising the steps of selecting two base members to be united at opposed inner faces to a blade of span extending between said members, forming each of said faces with a recess having a section corresponding to desired blade section and to a depth less than base-member thickness, selecting a blade element of said blade section and of length corresponding to said span plug the combined effective depth of said recesses, assembling said blade element to the recessed regions of said base members, and permanently securing said assembly, said recess-forming step comprising the further steps of selecting an elongate boring-tool element of desired bore section, mounting the two base members with their inner faces opposed at a spacing which exceeds the length of said tool element, supporting said tool element with its elongation axis extending between said faces, subjecting said base members and tool element to an EDM environment wherein the tool element determines the section of bored removal of base-member material, and progressively feeding said base members with respect to each other and with respect to said tool element to the extent of tool boring both base members to said depth.
Claim 18
Dependent Claim
107 words
The method of claim 10, wherein said recessing step is performed by a tool element of said predetermined section, mounting said base members with their reference surfaces in face-to-face relation at a spacing which exceeds the length of said tool element, supporting said tool element with its elongation axis extending between said faces, subjecting said base members and tool element to an EDM environment wherein the tool element determines the section of bored removal of base-member material, and progressively feeding said base members with respect to each other and with respect to said tool element to the extent of tool boring both base members to said depth.
Claim 19
Dependent Claim
53 words
The method of claim 13, in which said tool element is one of a plurality of elements of said section, the same being supported in angularly spaced relation corresponding to those oF said blade-positioning locations, whereby all blade-section recesses are formed in both base members in one tool-boring feed cycle to said depth.
Claim 20
Independent Claim
260 words
The method of making an annular nozzle assembly for a gas-turbine, comprising the steps of selecting two annular base members to be united at opposed inner faces to a plurality of like blades of span extending between said members, each of said faces having recesses at a plurality of angularly spaced blade-positioning locations, said recesses being with predetermined blade section and incidence and to a depth less than base-member thickness; said recessing step being performed by a plurality of tool elements of said predetermined section, mounting said base members with their reference surfaces in face-to-face relation at a spacing which exceeds the length of said tool element, supporting said tool elements with their elongation axes extending between said faces and in angularly spaced relation and incidence corresponding to those of said blade-positioning locations, subjecting said base members and tool element to an EDM environment wherein the tool element determines the section of bored removal of base-member material, and progressively feeding said base members with respect to each other and with respect to said tool element to the extent of tool boring both base members to said depth, whereby all blade-section recesses are formed in both base members in one tool-boring feed cycle to said depth; selecting a plurality of blade elements of said predetermined section and a length corresponding to said span plus the combined effective depth of recesses in both base members, assembling the blade elements to corresponding opposed pairs of recesses in said base members, and fusing all blade elements to said base members in such assembled relation.
Claim 21
Independent Claim
260 words
The method of making an annular nozzle assembly for a gas-turbine, comprising the steps of selecting two annular base members to be united at opposed inner faces to a plurality of like blades of span extending between said members, each of said faces having recesses at a plurality of angularly spaced blade-positioning locations, said recesses being with predetermined blade section and incidence and to a depth less than base-member thickness; said recessing step being performed by a plurality of tool elements of said predetermined section, mounting said base members with their reference surfaces in face-to-face relation at a spacing which exceeds the length of said tool element, supporting said tool elements with their elongation axes extending between said faces and in angularly spaced relation and incidence corresponding to those of said blade-positioning locations, subjecting said base members and tool element to an EDM environment wherein the tool element determines the section of bored removal of base-member material, and progressively feeding said base members with respect to each other and with respect to said tool element to the extent of tool boring both base members to said depth, whereby all blade-section recesses are formed in both base members in one tool-boring feed cycle to said depth; selecting a plurality of blade elements of said predetermined section and a length corresponding to said span plus the combined effective depth of recesses in both base members, assembling the blade elements to corresponding opposed pairs of recesses in said base members, and fusing all blade elements to said base members in such assembled relation.
Claim 22
Independent Claim
147 words
The method of reconditioning a gas-turbine vane assembly comprising base members integrally united at opposed inner faces to a blade of span extending between said members, said method comprising removing all blade material between said faces; such blade material being removed by first cutting the blade in a location between said base members, thereby defining separate base members each with an integral truncated fraction of a blade, and for each thus-separated member removing the truncated-blade material to a predetermined reference inner-face surface; recessing said inner surfaces with a section corresponding to desired reconditioned blade section and to the extent of local base-member thickness; selecting a new blade element (a) of length corresponding to said span plus the combined effective depth of said recesses and (b) of said reconditioned blade section; assembling said blade element to the recessed regions of said base members; and permanently securing said assembly.
Claim 23
Independent Claim
147 words
The method of reconditioning a gas-turbine vane assembly comprising base members integrally united at opposed inner faces to a blade of span extending between said members, said method comprising removing all blade material between said faces; such blade material being removed by first cutting the blade in a location between said base members, thereby defining separate base members each with an integral truncated fraction of a blade, and for each thus-separated member removing the truncated-blade material to a predetermined reference inner-face surface; recessing said inner surfaces with a section corresponding to desired reconditioned blade section and to the extent of local base-member thickness; selecting a new blade element (a) of length corresponding to said span plus the combined effective depth of said recesses and (b) of said reconditioned blade section; assembling said blade element to the recessed regions of said base members; and permanently securing said assembly.
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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) | 1977-04-08 | 1977-10-08 | 1978-04-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-04-08 | 1981-10-08 | 1982-04-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-04-08 | 1985-10-08 | 1986-04-09 | $7700.00 | Window Closed / Lapsed |