GB828248A - Improvements in turbine and compressor blade cover assembly - Google Patents

Improvements in turbine and compressor blade cover assembly

Info

Publication number
GB828248A
GB828248A GB8791/57A GB879157A GB828248A GB 828248 A GB828248 A GB 828248A GB 8791/57 A GB8791/57 A GB 8791/57A GB 879157 A GB879157 A GB 879157A GB 828248 A GB828248 A GB 828248A
Authority
GB
United Kingdom
Prior art keywords
tenons
ribs
blade
shroud band
turbine
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
GB8791/57A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB828248A publication Critical patent/GB828248A/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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

828,248. Turbine and compressor blade assemblies. GENERAL ELECTRIC CO. March 18, 1957 [April 16, 1956], No. 8791/57. Class 110 (3). In a bladed turbine or compressor rotor assembly in which an arcuate shroud band connects the tips of a group of blades, the shroud band is provided with at least three radiallyprojecting, circumferentially-extending ribs and each blade is provided with at least two tenons extending radially from the tip thereof, the shroud band having openings between the ribs to receive the tenons, and the blade tenons being secured to the ribs on the shroud band. The shroud band 1 is provided with three radiallyprojecting, circumferentially-extending ribs 1b and pairs of openings 1c are provided between the ribs to receive the tenons 2b at the tips 2a of the rotor blades 2. The openings 1c are of the same width as the blade tenons but they are somewhat longer in the circumferential direction than the blade tenons. Axially-extending pins 3 are passed through aligned holes in the tenons and ribs, the ends of the pins being riveted over.
GB8791/57A 1956-04-16 1957-03-18 Improvements in turbine and compressor blade cover assembly Expired GB828248A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US828248XA 1956-04-16 1956-04-16

Publications (1)

Publication Number Publication Date
GB828248A true GB828248A (en) 1960-02-17

Family

ID=22173691

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8791/57A Expired GB828248A (en) 1956-04-16 1957-03-18 Improvements in turbine and compressor blade cover assembly

Country Status (1)

Country Link
GB (1) GB828248A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0399879A1 (en) * 1989-05-23 1990-11-28 Societe Europeenne De Propulsion Stator assembly for turbojet and its method of manufacture
WO2014137441A1 (en) * 2012-12-21 2014-09-12 General Electric Company Rotor blade and corresponding manufacturing method

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0399879A1 (en) * 1989-05-23 1990-11-28 Societe Europeenne De Propulsion Stator assembly for turbojet and its method of manufacture
FR2647502A1 (en) * 1989-05-23 1990-11-30 Europ Propulsion TURBINE DISTRIBUTOR FOR TURBO-REACTOR AND MANUFACTURING METHOD THEREOF
US5074749A (en) * 1989-05-23 1991-12-24 Societe Europeenne De Propulsion Turbine stator for a turbojet, and method of manufacture
WO2014137441A1 (en) * 2012-12-21 2014-09-12 General Electric Company Rotor blade and corresponding manufacturing method

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