GB743782A - Nozzle assemblies for bladed fluid flow machines such as turbines and compressors - Google Patents

Nozzle assemblies for bladed fluid flow machines such as turbines and compressors

Info

Publication number
GB743782A
GB743782A GB2816452A GB2816452A GB743782A GB 743782 A GB743782 A GB 743782A GB 2816452 A GB2816452 A GB 2816452A GB 2816452 A GB2816452 A GB 2816452A GB 743782 A GB743782 A GB 743782A
Authority
GB
United Kingdom
Prior art keywords
platforms
guide
nozzle
operating ring
vane
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
GB2816452A
Inventor
Georges Henry Roesch
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development 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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB2816452A priority Critical patent/GB743782A/en
Publication of GB743782A publication Critical patent/GB743782A/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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line

Landscapes

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

Abstract

743,782. Turbines and compressors. POWER JETS (RESEARCH & DEVELOPMENT). Ltd. Jan. 21, 1954 [Nov. 7, 1952], No. 28164/52. Classes 110(1) and 110(3) An annular nozzle assembly for a bladed fluid flow machine such as a steam or gas turbine or a compresser through which fluids flows with both axial and radial components of flow, is provided with adjustable flow-directing nozzle vanes. The inner and outer walls of the nozzle passage form parts of concentric spheres and each vane is rotatable about an axis passing through the centre of the sphere and inclined to a plane normal to the axis of the nozzle passage. The gas turbine shown comprises a rotor 4 and shaft 3 mounted on a bearing in casing 1. Hot gas is supplied to the rotor blades from a volute 6 through the adjustable inlet nozzle guide vanes 11. The inner wall of the nozzle passage is constituted by the guide vane platforms 10 and the inner wall and the outer wall 7 are curved and form parts of concentric spheres whose common centre is O. The guide vane platforms 10 are formed with spindles 10a rotatably mounted in the diaphragm 5 secured to the casing 1 and the axes of the spindles pass through the common centre O. The guide vanes are adjustable by means of a pivoted lever 13 the spherical end 13a of which engages in an operating ring 12 which is movable axially and circumferentially. The operating ring 12 carries spherical-ended pegs 12a which engage in sockets 10 in the guide. vane platforms. The gaps between the platforms 10 are closed by projections 5b. The guide vanes may alternatively be adjusted by means of bevel teeth formed on the operating ring and vane platforms, or the operating ring and platforms may be connected by links,
GB2816452A 1952-11-07 1952-11-07 Nozzle assemblies for bladed fluid flow machines such as turbines and compressors Expired GB743782A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2816452A GB743782A (en) 1952-11-07 1952-11-07 Nozzle assemblies for bladed fluid flow machines such as turbines and compressors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2816452A GB743782A (en) 1952-11-07 1952-11-07 Nozzle assemblies for bladed fluid flow machines such as turbines and compressors

Publications (1)

Publication Number Publication Date
GB743782A true GB743782A (en) 1956-01-25

Family

ID=10271297

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2816452A Expired GB743782A (en) 1952-11-07 1952-11-07 Nozzle assemblies for bladed fluid flow machines such as turbines and compressors

Country Status (1)

Country Link
GB (1) GB743782A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4100224A1 (en) * 1991-01-07 1992-07-09 Daimler Benz Ag Diffuser holder for turbine housing - has holder bushes of adjusting shafts acting as sole diffusor support
WO2005085601A1 (en) * 2004-03-02 2005-09-15 Siemens Aktiengesellschaft Stationary axial flow gas turbine
EP3109408A1 (en) * 2015-06-25 2016-12-28 Rolls-Royce Deutschland Ltd & Co KG Stator device for a turbo engine with a housing device and multiple guide vanes
US10344616B2 (en) 2015-06-25 2019-07-09 Rolls-Royce Deutschland Ltd & Co Kg Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes
EP4036378A1 (en) * 2021-01-28 2022-08-03 Siemens Energy Global GmbH & Co. KG Turbomachine, especially radial expander

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4100224A1 (en) * 1991-01-07 1992-07-09 Daimler Benz Ag Diffuser holder for turbine housing - has holder bushes of adjusting shafts acting as sole diffusor support
WO2005085601A1 (en) * 2004-03-02 2005-09-15 Siemens Aktiengesellschaft Stationary axial flow gas turbine
EP3109408A1 (en) * 2015-06-25 2016-12-28 Rolls-Royce Deutschland Ltd & Co KG Stator device for a turbo engine with a housing device and multiple guide vanes
US10344616B2 (en) 2015-06-25 2019-07-09 Rolls-Royce Deutschland Ltd & Co Kg Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes
EP4036378A1 (en) * 2021-01-28 2022-08-03 Siemens Energy Global GmbH & Co. KG Turbomachine, especially radial expander

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