GB606560A - Improvements relating to axial flow compressors - Google Patents

Improvements relating to axial flow compressors

Info

Publication number
GB606560A
GB606560A GB7062/45A GB706245A GB606560A GB 606560 A GB606560 A GB 606560A GB 7062/45 A GB7062/45 A GB 7062/45A GB 706245 A GB706245 A GB 706245A GB 606560 A GB606560 A GB 606560A
Authority
GB
United Kingdom
Prior art keywords
blades
rotor
control element
compressor
axially
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
GB7062/45A
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.)
JOHN NORMAN JUSTICE ROWLEY
Power Jets Research and Development Ltd
Original Assignee
JOHN NORMAN JUSTICE ROWLEY
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 JOHN NORMAN JUSTICE ROWLEY, Power Jets Research and Development Ltd filed Critical JOHN NORMAN JUSTICE ROWLEY
Priority to GB7062/45A priority Critical patent/GB606560A/en
Publication of GB606560A publication Critical patent/GB606560A/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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • F04D29/323—Blade mountings adjustable
    • 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
    • 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
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources

Landscapes

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

Abstract

606,560. Screw fans etc.; turbines, elastic fluid. POWER JETS (RESEARCH & DEVELOPMENT), Ltd., ROWLEY, J. N. J., MORRIS, C., and ROBSON, A. R. D. March 20, 1945, No. 7062. [Classes 110 (i) and 110 (iii)] A multi-stage axial flow compressor of the kind which has blades of radial length substantially less than their extreme radius of rotation, is provided with either or both rotor and stator blades rotatably mounted to permit variation of their pitch angle. All the rotatable blades or at least all those of any one stage are coupled in common to an actuating cylindrical control element which is co-axial with the axis of the rotor and is movable axially or rotationally or both axially and rotationally in relation to said axis. The control element may be operated by means responsive to an operational condition of the machine, e.g. fluid delivery pressure so as to tend to maintain constant its speed of rotation. In Fig. 1, the rotor blades 2 are provided with cranks 3 which engage peripheral grooves 8 in the control element 7 which is axially movable on the shaft 6 by means of the lever 9. In Fig. 3, the cylindrical control element 7 is provided with axial grooves which engage the pegs 4 attached to cranks 3 and is interengaged with the rotor through helical splines 19. The. discharge pressure acting on the end 20 of the element 7 via radial ports 23 serves to adjust the setting of the blades in accordance with the delivery pressure. The compressor may be combined with an internal combustion turbine of the continuous flow type whose air supply is derived from the compressor.
GB7062/45A 1945-03-20 1945-03-20 Improvements relating to axial flow compressors Expired GB606560A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7062/45A GB606560A (en) 1945-03-20 1945-03-20 Improvements relating to axial flow compressors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB7062/45A GB606560A (en) 1945-03-20 1945-03-20 Improvements relating to axial flow compressors

Publications (1)

Publication Number Publication Date
GB606560A true GB606560A (en) 1948-08-17

Family

ID=9825883

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7062/45A Expired GB606560A (en) 1945-03-20 1945-03-20 Improvements relating to axial flow compressors

Country Status (1)

Country Link
GB (1) GB606560A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2947466A (en) * 1956-08-31 1960-08-02 Konink Machinenfabriek Gebr St Axial flow fans
US3422625A (en) * 1966-08-05 1969-01-21 Garrett Corp Jet engine with an axial flow supersonic compressor
EP0533319A1 (en) * 1991-09-17 1993-03-24 ROLLS-ROYCE plc Aerofoil members for gas turbine engines
FR2681640A1 (en) * 1991-09-25 1993-03-26 Snecma TURBOMACHINE WITH STATOR AUBES WITH VARIABLE TIMING.
CN101975190A (en) * 2010-09-30 2011-02-16 北京理工大学 Differential guide vane section and guide vane adjusting device for vane compressor
CN102536901A (en) * 2012-01-12 2012-07-04 北京理工大学 Adjusting device for elastic guide vanes at inlet of air compressor of automobile turbocharger
CN115076150A (en) * 2022-07-25 2022-09-20 沈阳鼓风机集团股份有限公司 Moving blade adjusting mechanism of multistage axial flow fan

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2947466A (en) * 1956-08-31 1960-08-02 Konink Machinenfabriek Gebr St Axial flow fans
US3422625A (en) * 1966-08-05 1969-01-21 Garrett Corp Jet engine with an axial flow supersonic compressor
EP0533319A1 (en) * 1991-09-17 1993-03-24 ROLLS-ROYCE plc Aerofoil members for gas turbine engines
FR2681640A1 (en) * 1991-09-25 1993-03-26 Snecma TURBOMACHINE WITH STATOR AUBES WITH VARIABLE TIMING.
US5224820A (en) * 1991-09-25 1993-07-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Operating mechanism for variably settable blades of a turbomachine
CN101975190A (en) * 2010-09-30 2011-02-16 北京理工大学 Differential guide vane section and guide vane adjusting device for vane compressor
CN101975190B (en) * 2010-09-30 2012-05-23 北京理工大学 Differential guide vane slicing and adjustable guide vane device of vane compressor
CN102536901A (en) * 2012-01-12 2012-07-04 北京理工大学 Adjusting device for elastic guide vanes at inlet of air compressor of automobile turbocharger
CN115076150A (en) * 2022-07-25 2022-09-20 沈阳鼓风机集团股份有限公司 Moving blade adjusting mechanism of multistage axial flow fan

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