GB1071108A - Improvements in and relating to turbines and compressors - Google Patents

Improvements in and relating to turbines and compressors

Info

Publication number
GB1071108A
GB1071108A GB3915564A GB3915564A GB1071108A GB 1071108 A GB1071108 A GB 1071108A GB 3915564 A GB3915564 A GB 3915564A GB 3915564 A GB3915564 A GB 3915564A GB 1071108 A GB1071108 A GB 1071108A
Authority
GB
United Kingdom
Prior art keywords
cylinder
grooved
grooved rings
sept
turbines
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
GB3915564A
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.)
BBC Brown Boveri AG Germany
BBC Brown Boveri France SA
Original Assignee
Brown Boveri und Cie AG Germany
BBC Brown Boveri France SA
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 Brown Boveri und Cie AG Germany, BBC Brown Boveri France SA filed Critical Brown Boveri und Cie AG Germany
Publication of GB1071108A publication Critical patent/GB1071108A/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)

Abstract

1,071,108. Axial-flow compressors; turbines. BROWN BOVERI & CIE A. G. Sept. 25, 1964 [Sept. 27 1963], No. 39155/64. Headings F1C and F1T In a turbine or compressor having adjustable stator blades 26, Fig. 1, an adjusting cylinder 15 carries grooved rings 19, 20, 21 receiving slide blocks 23 on blade adjusting levers 24. The cylinder and grooved rings are each formed in two halves separated in the horizontal plane to permit individual assembly of the slide blocks in the grooves. Axial adjustment of the cylinder by rack 10 and pinion 8 adjusts the angularity of the stator blades 26. The grooved rings are each connected within the cylinder by bolts and a pin extending radially through the cylinder wall, or each grooved ring is received in a peripheral groove in the inner surface of the cylinder and secured by radially-directed bolts. In the embodiment in Fig. 2 (not shown), the adjusting cylinder (40) has welded thereto a number of grooved rings (41) each provided with a detachable side plate (42).
GB3915564A 1963-09-27 1964-09-25 Improvements in and relating to turbines and compressors Expired GB1071108A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1193763A CH404841A (en) 1963-09-27 1963-09-27 Turbomachinery with adjustable blades

Publications (1)

Publication Number Publication Date
GB1071108A true GB1071108A (en) 1967-06-07

Family

ID=4378305

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3915564A Expired GB1071108A (en) 1963-09-27 1964-09-25 Improvements in and relating to turbines and compressors

Country Status (2)

Country Link
CH (1) CH404841A (en)
GB (1) GB1071108A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010159749A (en) * 2009-01-06 2010-07-22 General Electric Co <Ge> Variable position guide vane actuation system and method
FR3082896A1 (en) * 2018-06-22 2019-12-27 Safran Aircraft Engines ASSEMBLY FOR VARIABLE TIMING VANE CONTROL

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010159749A (en) * 2009-01-06 2010-07-22 General Electric Co <Ge> Variable position guide vane actuation system and method
FR3082896A1 (en) * 2018-06-22 2019-12-27 Safran Aircraft Engines ASSEMBLY FOR VARIABLE TIMING VANE CONTROL
US11015477B2 (en) 2018-06-22 2021-05-25 Safran Aircraft Engines Assembly for controlling variable pitch blades

Also Published As

Publication number Publication date
CH404841A (en) 1965-12-31

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