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 pumps

Info

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
Application number
GB23170/53A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MAN AG
Original Assignee
MAN Maschinenfabrik Augsburg Nuernberg AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MAN Maschinenfabrik Augsburg Nuernberg AG filed Critical MAN Maschinenfabrik Augsburg Nuernberg AG
Publication of GB753229A publication Critical patent/GB753229A/en
Expired legal-status Critical Current

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.
GB23170/53A 1952-09-06 1953-08-21 Improvements in or relating to rotor blades for axial flow turbines, compressors or pumps Expired GB753229A (en)

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)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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

Cited By (12)

* Cited by examiner, † Cited by third party
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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