GB753229A - Improvements in or relating to rotor blades for axial flow turbines, compressors or pumps - Google Patents
Improvements in or relating to rotor blades for axial flow turbines, compressors or pumpsInfo
- Publication number
- GB753229A GB753229A GB23170/53A GB2317053A GB753229A GB 753229 A GB753229 A GB 753229A GB 23170/53 A GB23170/53 A GB 23170/53A GB 2317053 A GB2317053 A GB 2317053A GB 753229 A GB753229 A GB 753229A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rotor
- root
- blade
- seating surfaces
- groove
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3084—Fixing blades to rotors; Blade roots ; Blade spacers the blades being made of ceramics
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
753,229. Turbine, pump and compressor blades. MASCHINENFABRIK AUGSBURG-NURNBERG AKT.-GES. Aug. 21, 1953 [Sept. 6, 1952], No. 23170/53. Class 110(3) Ceramic rotor blades for an axial-flow turbine, pump or compressor are held in a peripheral groove in the rotor, the groove profile being circularly curved and the blade roots conforming to the groove profile, with a clearance between the roots and the groove which permits each blade to rotate to a small extent about two mutually perpendicular axes, one of which is directly axially with respect to the rotor, while the other is directed longentially with respect to the rotor. In a gas turbine rotor, Figs. 1 and 3, the root 4 of each rotor blade 3 is mounted in a circumferential slot 2 of the rotor disc 1, the radius of curvature r of the seating surfaces of the root being made smaller than the radius of curvature of the corresponding surfaces of the slot 2. The root 4 is convex where it makes contact with the root of the adjacent blade, the convexity being substantially on a level with the seating surfaces. This construction permits the blade 3 to pivot simultaneously both in the plane of the rotor and in a plane through the rotor axis. In a modification, Fig. 2, the root 14 of each alternate blade 13 is inserted in a U-shaped member 15, which may be of copper sheet, having beaded flanges 16. In an alternative construction, the root may be mounted in a sheath of, say, copper sheet, the root having two pairs of seating surfaces arranged according to Specification 703,905 to provide a temperature-independent connection between the root and the sheath. Specification 664,986 also is referred to.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE317252X | 1952-09-06 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB753229A true GB753229A (en) | 1956-07-18 |
Family
ID=6150718
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB23170/53A Expired GB753229A (en) | 1952-09-06 | 1953-08-21 | Improvements in or relating to rotor blades for axial flow turbines, compressors or pumps |
Country Status (2)
Country | Link |
---|---|
CH (1) | CH317252A (en) |
GB (1) | GB753229A (en) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3292900A (en) * | 1962-08-10 | 1966-12-20 | Bbc Brown Boveri & Cie | Vibration-damping fixing of moving blades for axial-flow turbo-machines |
US3752600A (en) * | 1971-12-09 | 1973-08-14 | United Aircraft Corp | Root pads for composite blades |
US3784320A (en) * | 1971-02-20 | 1974-01-08 | Motoren Turbinen Union | Method and means for retaining ceramic turbine blades |
US4022545A (en) * | 1974-09-11 | 1977-05-10 | Avco Corporation | Rooted aerodynamic blade and elastic roll pin damper construction |
US4051585A (en) * | 1976-07-26 | 1977-10-04 | United Technologies Corporation | Method of forming a turbine rotor |
US4102602A (en) * | 1976-08-31 | 1978-07-25 | Volkswagenwerk Aktiengesellschaft | Rotor for an axial turbine |
US4169694A (en) * | 1977-07-20 | 1979-10-02 | Electric Power Research Institute, Inc. | Ceramic rotor blade having root with double curvature |
GB2119026A (en) * | 1981-03-25 | 1983-11-09 | Rolls Royce | Aerofoil blade mounting |
CN102588003A (en) * | 2012-03-15 | 2012-07-18 | 北京航空航天大学 | Low-stress double-arc surface straight tenon connecting structure |
US9932831B2 (en) | 2014-05-09 | 2018-04-03 | United Technologies Corporation | High temperature compliant metallic elements for low contact stress ceramic support |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB8922339D0 (en) * | 1989-10-04 | 1989-11-22 | Rolls Royce Plc | Improvements in or relating to labyrinth seal structures |
-
1953
- 1953-07-10 CH CH317252D patent/CH317252A/en unknown
- 1953-08-21 GB GB23170/53A patent/GB753229A/en not_active Expired
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3292900A (en) * | 1962-08-10 | 1966-12-20 | Bbc Brown Boveri & Cie | Vibration-damping fixing of moving blades for axial-flow turbo-machines |
US3784320A (en) * | 1971-02-20 | 1974-01-08 | Motoren Turbinen Union | Method and means for retaining ceramic turbine blades |
US3752600A (en) * | 1971-12-09 | 1973-08-14 | United Aircraft Corp | Root pads for composite blades |
US4022545A (en) * | 1974-09-11 | 1977-05-10 | Avco Corporation | Rooted aerodynamic blade and elastic roll pin damper construction |
US4051585A (en) * | 1976-07-26 | 1977-10-04 | United Technologies Corporation | Method of forming a turbine rotor |
US4102602A (en) * | 1976-08-31 | 1978-07-25 | Volkswagenwerk Aktiengesellschaft | Rotor for an axial turbine |
US4169694A (en) * | 1977-07-20 | 1979-10-02 | Electric Power Research Institute, Inc. | Ceramic rotor blade having root with double curvature |
GB2119026A (en) * | 1981-03-25 | 1983-11-09 | Rolls Royce | Aerofoil blade mounting |
US4451204A (en) * | 1981-03-25 | 1984-05-29 | Rolls-Royce Limited | Aerofoil blade mounting |
CN102588003A (en) * | 2012-03-15 | 2012-07-18 | 北京航空航天大学 | Low-stress double-arc surface straight tenon connecting structure |
US9932831B2 (en) | 2014-05-09 | 2018-04-03 | United Technologies Corporation | High temperature compliant metallic elements for low contact stress ceramic support |
US10883369B2 (en) | 2014-05-09 | 2021-01-05 | United Technologies Corporation | High temperature compliant metallic elements for low contact stress ceramic support |
Also Published As
Publication number | Publication date |
---|---|
CH317252A (en) | 1956-11-15 |
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