GB226203A - Improvements in stators and rotors for turbines - Google Patents

Improvements in stators and rotors for turbines

Info

Publication number
GB226203A
GB226203A GB29596/24A GB2959624A GB226203A GB 226203 A GB226203 A GB 226203A GB 29596/24 A GB29596/24 A GB 29596/24A GB 2959624 A GB2959624 A GB 2959624A GB 226203 A GB226203 A GB 226203A
Authority
GB
United Kingdom
Prior art keywords
edges
rotor blades
blades
stator
inlet
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
GB29596/24A
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.)
Rheinmetall Air Defence AG
Maschinenfabrik Oerlikon AG
Original Assignee
Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Maschinenfabrik Oerlikon 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 Werkzeugmaschinenfabrik Oerlikon Buhrle AG, Maschinenfabrik Oerlikon AG filed Critical Werkzeugmaschinenfabrik Oerlikon Buhrle AG
Publication of GB226203A publication Critical patent/GB226203A/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

226,203. Maschinenfabrik Oerlikon. Dec. 10, 1923, [Convention date]. Blades.-To obviate as far as possible periodical fluctuations in the action of the motive fluid on the rotor blades and to decrease oscillation of the rotor blades, the stator and rotor blades b. c are mutually inclined so that the projections g of the exit edges e of the stator blades b in the direction of flow upon the surface containing the inlet edges f of the rotor blades c intersect said inlet edges f. Either the edges e or the edges f may be radial, and two or more adjacent blade edges may be intersected in the said surface by each projected blade edge. The edges e, f may be curved or rectilinear. The stator and rotor blades may differ in number. Reference has been directed by the Comptroller to Specifications 18413/06 and 27409/06.
GB29596/24A 1923-12-10 1924-12-09 Improvements in stators and rotors for turbines Expired GB226203A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH226203X 1923-12-10

Publications (1)

Publication Number Publication Date
GB226203A true GB226203A (en) 1925-07-23

Family

ID=4454442

Family Applications (1)

Application Number Title Priority Date Filing Date
GB29596/24A Expired GB226203A (en) 1923-12-10 1924-12-09 Improvements in stators and rotors for turbines

Country Status (1)

Country Link
GB (1) GB226203A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3194487A (en) * 1963-06-04 1965-07-13 United Aircraft Corp Noise abatement method and apparatus
US3270953A (en) * 1963-05-21 1966-09-06 Jerie Jan Axial flow compressor, blower or ventilator with reduced noise production
US3471080A (en) * 1968-06-13 1969-10-07 United Aircraft Corp Low noise generation fan
US3574477A (en) * 1969-02-19 1971-04-13 Boeing Co Noise attenuating system for rotary engines
US3745629A (en) * 1972-04-12 1973-07-17 Secr Defence Method of determining optimal shapes for stator blades
US3995970A (en) * 1974-09-10 1976-12-07 Mitsubishi Jukogyo Kabushiki Kaisha Axial-flow fan
GB2266931A (en) * 1992-05-15 1993-11-17 Gec Alsthom Ltd Turbine guide blade assembly.

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3270953A (en) * 1963-05-21 1966-09-06 Jerie Jan Axial flow compressor, blower or ventilator with reduced noise production
US3194487A (en) * 1963-06-04 1965-07-13 United Aircraft Corp Noise abatement method and apparatus
US3471080A (en) * 1968-06-13 1969-10-07 United Aircraft Corp Low noise generation fan
US3574477A (en) * 1969-02-19 1971-04-13 Boeing Co Noise attenuating system for rotary engines
US3745629A (en) * 1972-04-12 1973-07-17 Secr Defence Method of determining optimal shapes for stator blades
US3995970A (en) * 1974-09-10 1976-12-07 Mitsubishi Jukogyo Kabushiki Kaisha Axial-flow fan
GB2266931A (en) * 1992-05-15 1993-11-17 Gec Alsthom Ltd Turbine guide blade assembly.
GB2266931B (en) * 1992-05-15 1995-08-30 Gec Alsthom Ltd Turbine blade assembly
US5575620A (en) * 1992-05-15 1996-11-19 Gec Alsthom Limited Turbine blade assembly

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