GB656634A - Improvements in or relating to blades for turbines or compressors - Google Patents
Improvements in or relating to blades for turbines or compressorsInfo
- Publication number
- GB656634A GB656634A GB12649A GB12649A GB656634A GB 656634 A GB656634 A GB 656634A GB 12649 A GB12649 A GB 12649A GB 12649 A GB12649 A GB 12649A GB 656634 A GB656634 A GB 656634A
- Authority
- GB
- United Kingdom
- Prior art keywords
- portions
- blade
- machined
- recesses
- turbine
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
656,634. Turbine and compressor blades. ROLLS-ROYCE, Ltd. Jan. 3, 1949, No. 126. [Class 110(iii)] [Also in Group XXII] A hollow compressor or turbine blade is made by forming the leading portion 10a with an integral root part 10c and the trailing portion 11a with an integral root part 11c the two portions being shaped so as to abut over surfaces extending lengthwise of the blade, machining a longitudinal recess 13, 14 in at least one of the portions 10 or 11 and then permanently securing the portions together over their abutment surfaces Each portion is formed from a cast or forged blank and the abutment surfaces 16 and 17 are co - planar. Recesses 13 are machined in each part with a cutter of V-section and meet up with recesses 14 machined in the root portions. The blade tip may have a shroud 10b, 11b of parallelogram form. The two parts of the blade are joined by welding or brazing along the abutting surfaces.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB12649A GB656634A (en) | 1949-01-03 | 1949-01-03 | Improvements in or relating to blades for turbines or compressors |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB12649A GB656634A (en) | 1949-01-03 | 1949-01-03 | Improvements in or relating to blades for turbines or compressors |
Publications (1)
Publication Number | Publication Date |
---|---|
GB656634A true GB656634A (en) | 1951-08-29 |
Family
ID=9698866
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB12649A Expired GB656634A (en) | 1949-01-03 | 1949-01-03 | Improvements in or relating to blades for turbines or compressors |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB656634A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4893987A (en) * | 1987-12-08 | 1990-01-16 | General Electric Company | Diffusion-cooled blade tip cap |
WO2006108764A1 (en) * | 2005-04-14 | 2006-10-19 | Alstom Technology Ltd | Convectively cooled gas turbine blade |
CN103586647A (en) * | 2013-10-14 | 2014-02-19 | 西安航空动力股份有限公司 | Forming method of aeroengine hollow guide vane |
-
1949
- 1949-01-03 GB GB12649A patent/GB656634A/en not_active Expired
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4893987A (en) * | 1987-12-08 | 1990-01-16 | General Electric Company | Diffusion-cooled blade tip cap |
WO2006108764A1 (en) * | 2005-04-14 | 2006-10-19 | Alstom Technology Ltd | Convectively cooled gas turbine blade |
US7766619B2 (en) | 2005-04-14 | 2010-08-03 | Alstom Technology Ltd | Convectively cooled gas turbine blade |
CN103586647A (en) * | 2013-10-14 | 2014-02-19 | 西安航空动力股份有限公司 | Forming method of aeroengine hollow guide vane |
CN103586647B (en) * | 2013-10-14 | 2015-12-02 | 西安航空动力股份有限公司 | A kind of forming method of aeroengine hollow guide vane |
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