GB991357A - Axial fluid flow machine such as a compressor or turbine - Google Patents

Axial fluid flow machine such as a compressor or turbine

Info

Publication number
GB991357A
GB991357A GB4800463A GB4800463A GB991357A GB 991357 A GB991357 A GB 991357A GB 4800463 A GB4800463 A GB 4800463A GB 4800463 A GB4800463 A GB 4800463A GB 991357 A GB991357 A GB 991357A
Authority
GB
United Kingdom
Prior art keywords
compressor
turbine
members
vanes
mounting
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
GB4800463A
Inventor
Arthur Bill
Thomas Steel
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 GB4800463A priority Critical patent/GB991357A/en
Priority to FR995130A priority patent/FR1414372A/en
Priority to US441143A priority patent/US3339833A/en
Publication of GB991357A publication Critical patent/GB991357A/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

991,357. Turbine and compressor blade mounting. ROLLS-ROYCE Ltd. Dec. 4, 1963, No. 48004/63. Heading F1T. An axial flow turbine or compressor blade has a root portion of dove-tail shape mounted within a corresponding slot in a mounting member such that the root portion extends radially through the slot to project radially from a surface of the mounting member remote from the blade working portion, the projecting portion being bonded to the surface. The compressor stator vanes 16 of a gas turbine engine are connected to an outer annular member 30 forming part of the compressor casing and to a similar inner member 31, Fig. 2. The connection comprises dove-tail roots 40, 55 on vanes 16 engaging in corresponding slots 38, 54 in annular members 30, 31 respectively. Members 30, 31 are of substantially channel section Fig. 4 and the vane roots 40, 55 project radially above the base surfaces 37, 56 of the channel sections and are bonded thereto by welding or brazing in the case of metallic components or by an adhesive or resin when the vanes 16 and members 30, 31 are formed of fibre reinforced synthetic resin material. Member 31 may support a rotor shaft bearing. The construction is applicable also to rotor blade mounting.
GB4800463A 1963-12-04 1963-12-04 Axial fluid flow machine such as a compressor or turbine Expired GB991357A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB4800463A GB991357A (en) 1963-12-04 1963-12-04 Axial fluid flow machine such as a compressor or turbine
FR995130A FR1414372A (en) 1963-12-04 1964-11-16 Axial fluid flow machine
US441143A US3339833A (en) 1963-12-04 1965-03-19 Axial fluid flow machine such as a compressor or turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4800463A GB991357A (en) 1963-12-04 1963-12-04 Axial fluid flow machine such as a compressor or turbine

Publications (1)

Publication Number Publication Date
GB991357A true GB991357A (en) 1965-05-05

Family

ID=10447020

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4800463A Expired GB991357A (en) 1963-12-04 1963-12-04 Axial fluid flow machine such as a compressor or turbine

Country Status (1)

Country Link
GB (1) GB991357A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1551201B1 (en) * 1965-09-16 1970-11-19 Rolls Royce Method for fastening a ring of guide vanes in the housing of axial flow machines
FR2606071A1 (en) * 1986-10-29 1988-05-06 Snecma Stator stage and turbine engine compressor comprising it
EP0277884A2 (en) * 1987-02-05 1988-08-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Outer stator shroud of a fan jet engine fitted on the fan housing
EP1111246A1 (en) * 1999-12-21 2001-06-27 Techspace Aero S.A. Stiffened annular part
CZ308913B6 (en) * 2015-12-28 2021-08-25 Vlastimil Sedláček Method of anchoring blades in a space circle

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1551201B1 (en) * 1965-09-16 1970-11-19 Rolls Royce Method for fastening a ring of guide vanes in the housing of axial flow machines
FR2606071A1 (en) * 1986-10-29 1988-05-06 Snecma Stator stage and turbine engine compressor comprising it
EP0277884A2 (en) * 1987-02-05 1988-08-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Outer stator shroud of a fan jet engine fitted on the fan housing
FR2610673A1 (en) * 1987-02-05 1988-08-12 Snecma TURBOREACTOR MULTIFLUX WITH EXTERNAL CROWN OF BLOWER RECTIFIER FREQUENCY ON THE CARTER
US4940386A (en) * 1987-02-05 1990-07-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Multiple flow turbojet engine with an outer ring of the fan outlet shrunk onto the case
EP0277884A3 (en) * 1987-02-05 1990-07-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Outer stator shroud of a fan jet engine fitted on the fan housing
EP1111246A1 (en) * 1999-12-21 2001-06-27 Techspace Aero S.A. Stiffened annular part
CZ308913B6 (en) * 2015-12-28 2021-08-25 Vlastimil Sedláček Method of anchoring blades in a space circle

Similar Documents

Publication Publication Date Title
GB1040825A (en) Improvements in rotor blades and/or stator blades for gas turbine engines
GB1008526A (en) Axial flow bladed rotor, e.g. for a turbine
GB1093568A (en) Improvements in or relating to bladed rotors such as compressor rotors
GB1195012A (en) Rotor for Bladed Fluid Flow Machines.
GB1148590A (en) Improvements in stator vane assembly having composite sectors
GB1272200A (en) Axial-flow turbomachine rotors
GB1020900A (en) A seal between the rotor blades and the casing of axial-flow turbo-machines
GB1506360A (en) Ceramic turbine structures
GB1095830A (en) Bladed rotor for a fluid flow machine such as a gas turbine engine
GB1528421A (en) Shroud for rotor or impeller of a turbine or compressor with abradable seal layer on inside to establish minimized running clearance
GB831412A (en) Improvements relating to axial-flow turbines
GB1276100A (en) Bladed member for a fluid flow machine
GB767656A (en) Improvements in or relating to axial-flow fluid machines such as turbines and compressors
GB991357A (en) Axial fluid flow machine such as a compressor or turbine
GB902064A (en) Blade damping means for compressors and turbines
GB621551A (en) Improvements in or relating to axial-flow compressors and turbines
GB1141280A (en) Bladed rotor for a fluid flow machine
GB1116580A (en) Stator blade assemblies for axial-flow turbine engines
GB1284710A (en) Turbomachine rotors
GB1524969A (en) Stator vane assembly
GB1514096A (en) Axial flow rotor or stator assembly
GB994568A (en) Bladed structure
GB981476A (en) Gas turbine engine vane assembly
GB1306891A (en) Method and blade arrangement to reduce the serpentine motion of a mass particle flowing through a turbomachine
GB1194781A (en) Improvements in Multistage Axial Flow Machines of the Turbine Type