GB133862A - - Google Patents

Info

Publication number
GB133862A
GB133862A GB133862DA GB133862A GB 133862 A GB133862 A GB 133862A GB 133862D A GB133862D A GB 133862DA GB 133862 A GB133862 A GB 133862A
Authority
GB
United Kingdom
Prior art keywords
projections
blades
engage
guide
disks
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
Publication date
Publication of GB133862A publication Critical patent/GB133862A/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

133,862. British Thomson - Houston Co., (General Electric Co.). Jan. 13, 1919. Casings; nozzles. - A diaphragm for turbines of the disk type comprises two annular disks 11, 12 having inturned flanges 15 which support the shaft packing 10, and inturned flanges 16, 17, which engage the roots 22 of guide-blades 20. The outer ends of the guide-blades are provided with projections 21 which are engaged by spacing pieces 25. Annular rings 28, 29, engage the projections 21 and spacing pieces 25. The assembly is held together by bolts 14, 24, and 32. One of the rings 29 has a flange 35 which serves as a spacer to space apart adjacent diaphragms. Alternatively, a separate spacing ring may be used. The disks 11, 12, are split in a horizontal plane to facilitate assembling.
GB133862D Expired GB133862A (en)

Publications (1)

Publication Number Publication Date
GB133862A true GB133862A (en) 1900-01-01

Family

ID=1727256

Family Applications (1)

Application Number Title Priority Date Filing Date
GB133862D Expired GB133862A (en)

Country Status (1)

Country Link
GB (1) GB133862A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2220008A1 (en) * 1973-03-02 1974-09-27 Carrier Corp
JP2012510582A (en) * 2008-12-05 2012-05-10 シーメンス アクティエンゲゼルシャフト Guide vane array structure for axial turbomachinery

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2220008A1 (en) * 1973-03-02 1974-09-27 Carrier Corp
JP2012510582A (en) * 2008-12-05 2012-05-10 シーメンス アクティエンゲゼルシャフト Guide vane array structure for axial turbomachinery

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