GB907323A - Improvements in or relating to axial flow compressors - Google Patents

Improvements in or relating to axial flow compressors

Info

Publication number
GB907323A
GB907323A GB4181058A GB4181058A GB907323A GB 907323 A GB907323 A GB 907323A GB 4181058 A GB4181058 A GB 4181058A GB 4181058 A GB4181058 A GB 4181058A GB 907323 A GB907323 A GB 907323A
Authority
GB
United Kingdom
Prior art keywords
blades
rings
ring
actuating
cranks
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
GB4181058A
Inventor
Heinz Schuler
Johannes Leonhardt
Werner Held
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.)
ENTWICKLUNGSBAU PIRNA VEB
Original Assignee
ENTWICKLUNGSBAU PIRNA VEB
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 ENTWICKLUNGSBAU PIRNA VEB filed Critical ENTWICKLUNGSBAU PIRNA VEB
Priority to GB4181058A priority Critical patent/GB907323A/en
Publication of GB907323A publication Critical patent/GB907323A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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

907,323. Axial-flow compressors. ENTWICKLUNGSBAU PIRNA VEB. Dec. 29, 1958, No. 41810/58. Class 110 (1). In a multi-stage axial-flow compressor operating at variable rotor speeds and having a number of consecutive rings of adjustable stator or rotor blades, or both, following the first rotor blades, the pitch of the adjustable blades is adjusted in dependence upon the flow coefficient (i.e. the ratio between the axial velocity of the fluid and the circumferential speed). Fig. 7 shows a ring of stator blades 4<SP>3</SP>, journalled at their outer ends in bearings 36, 37 carried by the compressor casing and steadied at their inner ends by the engagement of pins 6<SP>3</SP> with a ring 3<SP>3</SP> which is not connected to the outer casing. The blades are connected to a channel-section actuating ring 7<SP>3</SP> by means of levers 25<SP>3</SP> and pins 41. The actuating rings 7<SP>3</SP> and the actuating rings 7<SP>31</SP>, 7<SP>311</SP>, Fig. 6, of two further stages are turned in unison by means of a common control rod 45, connected to the rings through bell-cranks 47, 49, 51 and links 55, 56, 57. The bell-cranks 47, 49, 51 differ in size as shown to give different amounts of blade pitch adjustment in the three stages. The control of the blade pitch is effected automatically through electrical or hydraulic means in accordance with the flow coefficient. In a modification, the actuating rings are connected to cranks attached to the inner pins of the stator blades, the control means being connected to the outer pin of one, or each of several, of the blades of each ring of stator blades.
GB4181058A 1958-12-29 1958-12-29 Improvements in or relating to axial flow compressors Expired GB907323A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB4181058A GB907323A (en) 1958-12-29 1958-12-29 Improvements in or relating to axial flow compressors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4181058A GB907323A (en) 1958-12-29 1958-12-29 Improvements in or relating to axial flow compressors

Publications (1)

Publication Number Publication Date
GB907323A true GB907323A (en) 1962-10-03

Family

ID=10421469

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4181058A Expired GB907323A (en) 1958-12-29 1958-12-29 Improvements in or relating to axial flow compressors

Country Status (1)

Country Link
GB (1) GB907323A (en)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006060000A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
EP1746258A2 (en) 2005-07-20 2007-01-24 United Technologies Corporation Rack and pinion variable van synchronizing mechanism for inner diameter vane shroud
WO2009077737A2 (en) * 2007-12-14 2009-06-25 Nuaire Limited Motor mounting assembly for an axial fan
US7753647B2 (en) 2005-07-20 2010-07-13 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7901178B2 (en) 2005-07-20 2011-03-08 United Technologies Corporation Inner diameter vane shroud system having enclosed synchronizing mechanism
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
WO2006060000A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8276362B2 (en) 2004-12-01 2012-10-02 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
EP1746258A2 (en) 2005-07-20 2007-01-24 United Technologies Corporation Rack and pinion variable van synchronizing mechanism for inner diameter vane shroud
US7901178B2 (en) 2005-07-20 2011-03-08 United Technologies Corporation Inner diameter vane shroud system having enclosed synchronizing mechanism
US7753647B2 (en) 2005-07-20 2010-07-13 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
EP1746258A3 (en) * 2005-07-20 2010-04-07 United Technologies Corporation Rack and pinion variable van synchronizing mechanism for inner diameter vane shroud
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
WO2009077737A3 (en) * 2007-12-14 2009-08-20 Nuaire Ltd Motor mounting assembly for an axial fan
WO2009077737A2 (en) * 2007-12-14 2009-06-25 Nuaire Limited Motor mounting assembly for an axial fan

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