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GB732919A - Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines - Google Patents

Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines

Info

Publication number
GB732919A
GB732919A GB1791652A GB1791652A GB732919A GB 732919 A GB732919 A GB 732919A GB 1791652 A GB1791652 A GB 1791652A GB 1791652 A GB1791652 A GB 1791652A GB 732919 A GB732919 A GB 732919A
Authority
GB
United Kingdom
Prior art keywords
flange
wall
blades
edge
slots
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
GB1791652A
Inventor
Nelson Hector Kent
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB1791652A priority Critical patent/GB732919A/en
Publication of GB732919A publication Critical patent/GB732919A/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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

732,919. Turbines and compressors. ROLLSROYCE, Ltd. July 14, 1953 [July 16, 1953], No. 17916/52. Class 110 (3). In a turbine or compressor, a blade-supporting structure comprises an inner wall 11 which is a wall of the workmg fluid passage, and an axiallyextending flange 16 disposed radially outwardly of the inner wall. Pairs of aligned slots 14, 17 are formed in the inner wall and flange, the slots in the flange being open at any edge of the flange and blades 10 are mounted in the slots and a locking wire 18 extends through holes formed in the ends of the blades and through a retaining channel formed by turning over the edge of the parts of the flange between the slots. The blades are formed from strip material and the leading and trailing edges at the root end may be cut away to form surfaces which abut against the inner surface of the wall 11. The compressor casing shown comprises also a sheet metal skin 12 and the flange 16 is formed with a radial flange 15 which is secured to a channelsection member 13 secured between the walls 11, 12. The edge of the flange may be in the form of a hollow bead through which the locking wire is threaded or the edge of the flange may be turned over on to the locking wire during assembly. The blades' may in addition be welded at 19 to the supporting structure.
GB1791652A 1953-07-15 1953-07-15 Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines Expired GB732919A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1791652A GB732919A (en) 1953-07-15 1953-07-15 Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1791652A GB732919A (en) 1953-07-15 1953-07-15 Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines

Publications (1)

Publication Number Publication Date
GB732919A true GB732919A (en) 1955-06-29

Family

ID=10103500

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1791652A Expired GB732919A (en) 1953-07-15 1953-07-15 Improvements in or relating to blade assemblies of turbo-machines such as compressors and turbines

Country Status (1)

Country Link
GB (1) GB732919A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2272027A (en) * 1992-10-28 1994-05-04 Snecma Interlocking the ends of blades
EP1213484A1 (en) * 2000-12-06 2002-06-12 Techspace Aero S.A. Compressor stator stage
EP1548233A1 (en) * 2003-12-18 2005-06-29 Techspace Aero S.A. Fastening device for stator blades and compressor stator stage comprising such a fastening device
EP2204546A1 (en) 2008-12-24 2010-07-07 Techspace Aero SA Bladed stator stage of a compressor, corresponding compressor and method of retention of vanes in such a stator stage
FR2964427A1 (en) * 2010-09-06 2012-03-09 Messier Dowty Sa CARTRIDGE OF TURBOJET AND TURBOJET RECEIVING SUCH CARTERS
ITUB20161158A1 (en) * 2016-02-29 2017-08-29 Exergy Spa Method for the construction of bladed rings for radial turbomachinery and bladed ring obtained by this method
EP4488489A1 (en) * 2023-07-06 2025-01-08 Pratt & Whitney Canada Corp. Cantilever stator vane with damper

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2272027A (en) * 1992-10-28 1994-05-04 Snecma Interlocking the ends of blades
GB2272027B (en) * 1992-10-28 1996-04-10 Snecma System for interlocking the ends of blades
EP1213484A1 (en) * 2000-12-06 2002-06-12 Techspace Aero S.A. Compressor stator stage
US6595747B2 (en) 2000-12-06 2003-07-22 Techspace Aero S.A. Guide vane stage of a compressor
EP1548233A1 (en) * 2003-12-18 2005-06-29 Techspace Aero S.A. Fastening device for stator blades and compressor stator stage comprising such a fastening device
US8764392B2 (en) 2008-12-24 2014-07-01 Techspace Aero S.A. Blade retention at a compressor rectifier stage for impact resistance
EP2204546A1 (en) 2008-12-24 2010-07-07 Techspace Aero SA Bladed stator stage of a compressor, corresponding compressor and method of retention of vanes in such a stator stage
FR2964427A1 (en) * 2010-09-06 2012-03-09 Messier Dowty Sa CARTRIDGE OF TURBOJET AND TURBOJET RECEIVING SUCH CARTERS
WO2012032017A1 (en) * 2010-09-06 2012-03-15 Messier-Bugatti-Dowty Turbojet casing and turbojet receiving such casings
CN103080562A (en) * 2010-09-06 2013-05-01 梅西耶-布加蒂-道提公司 Turbojet casing and turbojet receiving such casings
RU2544107C2 (en) * 2010-09-06 2015-03-10 Эрсэль Housing of jet-turbine engine, and jet-turbine engine containing such housings
ITUB20161158A1 (en) * 2016-02-29 2017-08-29 Exergy Spa Method for the construction of bladed rings for radial turbomachinery and bladed ring obtained by this method
WO2017149414A1 (en) * 2016-02-29 2017-09-08 Exergy S.P.A. Method of manufaturing bladed rings for radial turbomachines using stop elements with localised welds; corresponding bladed ring
EP4488489A1 (en) * 2023-07-06 2025-01-08 Pratt & Whitney Canada Corp. Cantilever stator vane with damper

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