GB622078A - Improvements relating to gas turbine engines - Google Patents

Improvements relating to gas turbine engines

Info

Publication number
GB622078A
GB622078A GB681847A GB681847A GB622078A GB 622078 A GB622078 A GB 622078A GB 681847 A GB681847 A GB 681847A GB 681847 A GB681847 A GB 681847A GB 622078 A GB622078 A GB 622078A
Authority
GB
United Kingdom
Prior art keywords
platforms
recesses
gas turbine
turbine engines
improvements relating
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
GB681847A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB681847A priority Critical patent/GB622078A/en
Publication of GB622078A publication Critical patent/GB622078A/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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Landscapes

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

Abstract

622,078. Gas turbines. RUBBRA, A. A. March 11, 1947, No. 6818. [Class 110(iii)] The stator and nozzle blades 16 of a gas turbine are cast in pairs or groups with integral inner and outer segmental platforms 17, 18. The platforms are received in annular recesses 12, 14 in supporting rings 10, 11. They are located circumferentially by cross ribs in the supporting rings between the platforms, or, by projections on the platforms which engage recesses in the floors of the recesses 12, 14. There is a radial clearance between the platforms and the floors of the recesses and the blades are located radially by stepped flanges 19 on the inner platforms 17 which are held between the ring 10 and a casing part 24.
GB681847A 1947-03-11 1947-03-11 Improvements relating to gas turbine engines Expired GB622078A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB681847A GB622078A (en) 1947-03-11 1947-03-11 Improvements relating to gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB681847A GB622078A (en) 1947-03-11 1947-03-11 Improvements relating to gas turbine engines

Publications (1)

Publication Number Publication Date
GB622078A true GB622078A (en) 1949-04-26

Family

ID=9821313

Family Applications (1)

Application Number Title Priority Date Filing Date
GB681847A Expired GB622078A (en) 1947-03-11 1947-03-11 Improvements relating to gas turbine engines

Country Status (1)

Country Link
GB (1) GB622078A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2962260A (en) * 1954-12-13 1960-11-29 United Aircraft Corp Sweep back in blading

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2962260A (en) * 1954-12-13 1960-11-29 United Aircraft Corp Sweep back in blading

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