GB467394A - Improvements in or relating to the manufacture of turbine blades - Google Patents
Improvements in or relating to the manufacture of turbine bladesInfo
- Publication number
- GB467394A GB467394A GB2668436A GB2668436A GB467394A GB 467394 A GB467394 A GB 467394A GB 2668436 A GB2668436 A GB 2668436A GB 2668436 A GB2668436 A GB 2668436A GB 467394 A GB467394 A GB 467394A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- machined
- elements
- spacer
- brazing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
467,394. Making turbines. SHEPHERD, G. R. (Westinghouse Electric & Manufacturing Co.) Oct. 1, 1936, No. 26684. [Class 83 (ii)] Turbine blades or vanes are formed by brazing together a blade element and a spacer element, each cut from a length of section bar produced by rolling, drawing, or machining, the composite root of the blade being formed from the spacing element and the adjacent part of the blade element. A blade element 11 and a spacer element 13 are cut from lengths of section bars. The upper surface 14 of the element 13 is machined to provide an inclined surface thereon, and the elements 11, 13 are secured by tack welds 15 and, after cleaning or pickling, are dipped into a brazing bath, Fig. 7. The assembly is machined to remove excess brazing compound, and to provide a recess, or a T-root 29 for fastening purposes. Spacer elements may be employed which are wider than the blade elements, the lateral extensions being machined to form fastening tongues. A blade 32, Fig. 14, with a shrouding element 34 is similarly formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2668436A GB467394A (en) | 1936-10-01 | 1936-10-01 | Improvements in or relating to the manufacture of turbine blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2668436A GB467394A (en) | 1936-10-01 | 1936-10-01 | Improvements in or relating to the manufacture of turbine blades |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB467394A true GB467394A (en) | 1937-06-16 |
Family
ID=10247545
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2668436A Expired GB467394A (en) | 1936-10-01 | 1936-10-01 | Improvements in or relating to the manufacture of turbine blades |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB467394A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3056188A (en) * | 1956-06-27 | 1962-10-02 | Stalker Corp | Method and apparatus for continuous fabrication of compressor blades |
| CN100416043C (en) * | 2004-07-28 | 2008-09-03 | 斯奈克玛马达公司 | Method for producing hollow blade for turbine engine |
-
1936
- 1936-10-01 GB GB2668436A patent/GB467394A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3056188A (en) * | 1956-06-27 | 1962-10-02 | Stalker Corp | Method and apparatus for continuous fabrication of compressor blades |
| CN100416043C (en) * | 2004-07-28 | 2008-09-03 | 斯奈克玛马达公司 | Method for producing hollow blade for turbine engine |
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