GB771883A - Improvements in or relating to blade elements - Google Patents
Improvements in or relating to blade elementsInfo
- Publication number
- GB771883A GB771883A GB3566953A GB3566953A GB771883A GB 771883 A GB771883 A GB 771883A GB 3566953 A GB3566953 A GB 3566953A GB 3566953 A GB3566953 A GB 3566953A GB 771883 A GB771883 A GB 771883A
- Authority
- GB
- United Kingdom
- Prior art keywords
- tube
- trailing edge
- vane
- section
- aerofoil
- 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
771,883. Making hollow blades; destructible cores. ROLLS-ROYCE, Ltd. Jan. 14, 1955 [Dec. 22, 1953], No. 35669/53. Classes 83 (2) and 83 (4). A method of manufacturing a hollow blade element for a fluid machine comprises the steps of shaping a metal tube by a pressing or the like operation to give it a cross-section having a portion of desired aerofoil-section and an extra portion which extends beyond the location of the desired trailing edge, and connecting the walls of the aerofoil-section portion together and trimming off the extra portion. In the manufacture of hollow inlet guide vanes for a compressor of a gas-turbine engine, a rectangular sheet of metal is bent into a tube 11, Fig. 2, the edges being butt-welded together at 12; the weld is dressed and the tube annealed. The tube is then filled with wax and subjected to a first pressing operation which produces the shape shown in Fig. 3, the weld being at the trailing edge; the ends of the tube are milled parallel, the tube de-waxed by warming degreased and pickled. An auxiliary tube 14 of oval cross-section and which is shorter than the tube 13 is inserted within the tube 13 and secured therein by spot-welding 15. The tubes 13, 14 are filled with wax and subjected to a final shaping operation by pressing between dies, thus producing a vane as shown in Fig. 6, having a portion 16a of desired aerofoil crosssection and an extra portion 16b extending beyond the line 16c of the trailing edge of the desired aerofoil-section. The vane is de-waxed and surface-finished as by a planishing operation. After de-greasing, the concave and convex surfaces of the vane are welded together by seam welding along the line close to the desired trailing edge; the trailing edge of portion 16b may be opened as by a dressing operation with an emery wheel for ease of seam welding. The extra portion 16b is trimmed off along the line 16c of the trailing edge, and the trailing edge of the vane is radiused. The vane is trimmed to desired shape at its ends and given any desired surface finish, e.g. electro-polished. The extra portion 16b of the blade may be removed after the first shaping operation and before the final shaping operation; in this event the walls may be connected together after the trimming operation, preferably after the final shaping operation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3566953A GB771883A (en) | 1953-12-22 | 1953-12-22 | Improvements in or relating to blade elements |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB3566953A GB771883A (en) | 1953-12-22 | 1953-12-22 | Improvements in or relating to blade elements |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB771883A true GB771883A (en) | 1957-04-03 |
Family
ID=10380260
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB3566953A Expired GB771883A (en) | 1953-12-22 | 1953-12-22 | Improvements in or relating to blade elements |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB771883A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3848483A (en) * | 1972-07-17 | 1974-11-19 | Wall Machine Works | Method of making router bits |
-
1953
- 1953-12-22 GB GB3566953A patent/GB771883A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3848483A (en) * | 1972-07-17 | 1974-11-19 | Wall Machine Works | Method of making router bits |
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