GB191224657A - Improvements relating to Blades for Turbines. - Google Patents

Improvements relating to Blades for Turbines.

Info

Publication number
GB191224657A
GB191224657A GB191224657DA GB191224657A GB 191224657 A GB191224657 A GB 191224657A GB 191224657D A GB191224657D A GB 191224657DA GB 191224657 A GB191224657 A GB 191224657A
Authority
GB
United Kingdom
Prior art keywords
blades
strip
morcom
sets
turbines
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
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.)
Belliss and Morcom Ltd
Original Assignee
Belliss and Morcom Ltd
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 Belliss and Morcom Ltd filed Critical Belliss and Morcom Ltd
Application granted granted Critical
Publication of GB191224657A publication Critical patent/GB191224657A/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

24,657. Belliss & Morcom, Morcom, R. K., and Jude, A. Oct. 28. Blades.-Sets of turbine blades are attached at the end near the stator casing to a bar of channel section c and at the inner end to an angle-strip b. The sets of blades are inserted in openings in the plate e and are held in position by a stud f. A strip of metal g embossed with a tortuous ridge extending mainly transversely to the direction of rotation is fixed to the edge of the plate e and offers but little resistance if the strip comes into contact with the rotor.
GB191224657D 1912-10-28 1912-10-28 Improvements relating to Blades for Turbines. Expired GB191224657A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB191224657T 1912-10-28

Publications (1)

Publication Number Publication Date
GB191224657A true GB191224657A (en) 1913-01-23

Family

ID=32369661

Family Applications (1)

Application Number Title Priority Date Filing Date
GB191224657D Expired GB191224657A (en) 1912-10-28 1912-10-28 Improvements relating to Blades for Turbines.

Country Status (1)

Country Link
GB (1) GB191224657A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2497041A (en) * 1945-03-27 1950-02-07 United Aircraft Corp Nozzle ring for gas turbines
US3544231A (en) * 1968-03-22 1970-12-01 Sulzer Ag Stator-blade assembly for turbomachines
US4370094A (en) * 1974-03-21 1983-01-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2497041A (en) * 1945-03-27 1950-02-07 United Aircraft Corp Nozzle ring for gas turbines
US3544231A (en) * 1968-03-22 1970-12-01 Sulzer Ag Stator-blade assembly for turbomachines
US4370094A (en) * 1974-03-21 1983-01-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors

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