GB732920A - Improvements relating to blade assemblies of turbo-machines such as compressors and turbines - Google Patents

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

Info

Publication number
GB732920A
GB732920A GB1842952A GB1842952A GB732920A GB 732920 A GB732920 A GB 732920A GB 1842952 A GB1842952 A GB 1842952A GB 1842952 A GB1842952 A GB 1842952A GB 732920 A GB732920 A GB 732920A
Authority
GB
United Kingdom
Prior art keywords
compressors
turbines
blades
blade
turbo
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
GB1842952A
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 GB1842952A priority Critical patent/GB732920A/en
Publication of GB732920A publication Critical patent/GB732920A/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3076—Sheet metal discs

Abstract

732,920. Turbines and compressors. ROLLSROYCE, Ltd. July 14, 1953 [July 21, 1952], No. 18429/52. Class 110 (3). In a turbine or compressor, blade elements are formed from strip material and each blade is mounted by passing an end through a corresponding slot in a supporting structure and is connected thereto by a bracket member secured to the end of the blade and to a surface of the supporting structure which lies outside the working fluid passage of the machine. The stator of an axial-flow compressor comprises an inner sheet metal skin 11 and an outer skin 12 and the blades 10 are passed through slots 14 in the inner shell 11. The blades are secured by brackets 15 welded to the outer surface of the skin 11 and welded or bolted to the ends 10a of the blades.
GB1842952A 1952-07-21 1952-07-21 Improvements relating to blade assemblies of turbo-machines such as compressors and turbines Expired GB732920A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1842952A GB732920A (en) 1952-07-21 1952-07-21 Improvements relating to blade assemblies of turbo-machines such as compressors and turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1842952A GB732920A (en) 1952-07-21 1952-07-21 Improvements relating to blade assemblies of turbo-machines such as compressors and turbines

Publications (1)

Publication Number Publication Date
GB732920A true GB732920A (en) 1955-06-29

Family

ID=10112296

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1842952A Expired GB732920A (en) 1952-07-21 1952-07-21 Improvements relating to blade assemblies of turbo-machines such as compressors and turbines

Country Status (1)

Country Link
GB (1) GB732920A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2959393A (en) * 1956-04-16 1960-11-08 Gen Electric Turbine bucket cover assembly
US4452564A (en) * 1981-11-09 1984-06-05 The Garrett Corporation Stator vane assembly and associated methods
US5320490A (en) * 1991-12-18 1994-06-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Structural arm of the casing of a turbo-engine
US5332360A (en) * 1993-09-08 1994-07-26 General Electric Company Stator vane having reinforced braze joint
JP2007255224A (en) * 2006-03-20 2007-10-04 Mitsubishi Heavy Ind Ltd Turbine blade and gas turbine
US8057170B2 (en) 2006-09-27 2011-11-15 Rolls-Royce Plc Intermediate casing for a gas turbine engine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2959393A (en) * 1956-04-16 1960-11-08 Gen Electric Turbine bucket cover assembly
US4452564A (en) * 1981-11-09 1984-06-05 The Garrett Corporation Stator vane assembly and associated methods
US5320490A (en) * 1991-12-18 1994-06-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Structural arm of the casing of a turbo-engine
US5332360A (en) * 1993-09-08 1994-07-26 General Electric Company Stator vane having reinforced braze joint
JP2007255224A (en) * 2006-03-20 2007-10-04 Mitsubishi Heavy Ind Ltd Turbine blade and gas turbine
US8057170B2 (en) 2006-09-27 2011-11-15 Rolls-Royce Plc Intermediate casing for a gas turbine engine

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