GB630747A - Improvements in or relating to multi-stage axial-flow compressors - Google Patents

Improvements in or relating to multi-stage axial-flow compressors

Info

Publication number
GB630747A
GB630747A GB18201/47A GB1820147A GB630747A GB 630747 A GB630747 A GB 630747A GB 18201/47 A GB18201/47 A GB 18201/47A GB 1820147 A GB1820147 A GB 1820147A GB 630747 A GB630747 A GB 630747A
Authority
GB
United Kingdom
Prior art keywords
blades
flow compressors
relating
secured
stage axial
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
GB18201/47A
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.)
GEORGE STANLEY TAYLOR
Original Assignee
GEORGE STANLEY TAYLOR
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 GEORGE STANLEY TAYLOR filed Critical GEORGE STANLEY TAYLOR
Priority to GB18201/47A priority Critical patent/GB630747A/en
Publication of GB630747A publication Critical patent/GB630747A/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
    • F04D29/324—Blades
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

630,747. Axial-flow compressors. TAYLOR, G. S. July 9,1947, No. 18201. [Classes 110(i) and 110(iii)] Auxiliary blades are mounted between the main blades of a multi-stage rotor or stator to prevent stalling. Each auxiliary blade 15 is secured to the inner platform 13 of an adjacent main stator blade 11. The blades 15, which may be used in the first few stages only, have a chordal width of ¢-2/3 of that of the blades 11 and are somewhat less than half the length of the latter. The trailing edges of all the blades lie in the s a m e transverse plane. A wire 16 is threaded through the blades and welded or otherwise secured to them.
GB18201/47A 1947-07-09 1947-07-09 Improvements in or relating to multi-stage axial-flow compressors Expired GB630747A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB18201/47A GB630747A (en) 1947-07-09 1947-07-09 Improvements in or relating to multi-stage axial-flow compressors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB18201/47A GB630747A (en) 1947-07-09 1947-07-09 Improvements in or relating to multi-stage axial-flow compressors

Publications (1)

Publication Number Publication Date
GB630747A true GB630747A (en) 1949-10-20

Family

ID=10108386

Family Applications (1)

Application Number Title Priority Date Filing Date
GB18201/47A Expired GB630747A (en) 1947-07-09 1947-07-09 Improvements in or relating to multi-stage axial-flow compressors

Country Status (1)

Country Link
GB (1) GB630747A (en)

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2797044A (en) * 1949-06-16 1957-06-25 Rolls Royce Means for regulating the characteristics of multi-stage axial-flow compressors
US2839239A (en) * 1954-06-02 1958-06-17 Edward A Stalker Supersonic axial flow compressors
US2920864A (en) * 1956-05-14 1960-01-12 United Aircraft Corp Secondary flow reducer
US2938662A (en) * 1953-03-24 1960-05-31 Daimler Benz Ag Turbo compressor
US2953295A (en) * 1954-10-22 1960-09-20 Edward A Stalker Supersonic compressor with axially transverse discharge
US3020386A (en) * 1959-06-10 1962-02-06 Naxon Irving Electric heaters
US3193185A (en) * 1962-10-29 1965-07-06 Gen Electric Compressor blading
US3244400A (en) * 1964-10-30 1966-04-05 Saunders Walter Selden Extended range cascade for torque converters and turbo-machinery
US4022544A (en) * 1975-01-10 1977-05-10 Anatoly Viktorovich Garkusha Turbomachine rotor wheel
US4512718A (en) * 1982-10-14 1985-04-23 United Technologies Corporation Tandem fan stage for gas turbine engines
US5299914A (en) * 1991-09-11 1994-04-05 General Electric Company Staggered fan blade assembly for a turbofan engine
US5540551A (en) * 1994-08-03 1996-07-30 Westinghouse Electric Corporation Method and apparatus for reducing vibration in a turbo-machine blade
EP0781929A1 (en) * 1995-12-28 1997-07-02 Institut Francais Du Petrole Device for pumping or compressing a multi-phase fluid comprising tandem blading
WO2008097287A2 (en) * 2006-12-15 2008-08-14 Siemens Energy, Inc. Aero-mixing of rotating blade structures
US7604458B2 (en) * 2004-08-04 2009-10-20 Hitachi Plant Technologies, Ltd. Axial flow pump and diagonal flow pump
FR2939852A1 (en) * 2008-12-15 2010-06-18 Snecma Stator blade stage for compressor of turboshaft engine e.g. turbopropeller engine, has intermediate blades with axial length or radial height less than that of rectifier blades and extend radially between rectifier blades
RU2557830C2 (en) * 2012-07-20 2015-07-27 Юрий Васильевич Дробышевский Creation of propulsive force for aircraft displacement and turbojet to this end
US20160186773A1 (en) * 2014-12-29 2016-06-30 General Electric Company Axial compressor rotor incorporating splitter blades
US20180017019A1 (en) * 2016-07-15 2018-01-18 General Electric Company Turbofan engine wth a splittered rotor fan
US20180017079A1 (en) * 2016-07-15 2018-01-18 General Electric Company Variable-cycle compressor with a splittered rotor
US9938984B2 (en) 2014-12-29 2018-04-10 General Electric Company Axial compressor rotor incorporating non-axisymmetric hub flowpath and splittered blades
US20180156124A1 (en) * 2016-12-01 2018-06-07 General Electric Company Turbine engine frame incorporating splitters
CN112119204A (en) * 2018-05-17 2020-12-22 赛峰飞机发动机公司 Turbomachine stator element
US11149552B2 (en) 2019-12-13 2021-10-19 General Electric Company Shroud for splitter and rotor airfoils of a fan for a gas turbine engine
US12037921B2 (en) 2022-08-04 2024-07-16 General Electric Company Fan for a turbine engine

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2797044A (en) * 1949-06-16 1957-06-25 Rolls Royce Means for regulating the characteristics of multi-stage axial-flow compressors
US2938662A (en) * 1953-03-24 1960-05-31 Daimler Benz Ag Turbo compressor
US2839239A (en) * 1954-06-02 1958-06-17 Edward A Stalker Supersonic axial flow compressors
US2953295A (en) * 1954-10-22 1960-09-20 Edward A Stalker Supersonic compressor with axially transverse discharge
US2920864A (en) * 1956-05-14 1960-01-12 United Aircraft Corp Secondary flow reducer
US3020386A (en) * 1959-06-10 1962-02-06 Naxon Irving Electric heaters
US3193185A (en) * 1962-10-29 1965-07-06 Gen Electric Compressor blading
US3244400A (en) * 1964-10-30 1966-04-05 Saunders Walter Selden Extended range cascade for torque converters and turbo-machinery
US4022544A (en) * 1975-01-10 1977-05-10 Anatoly Viktorovich Garkusha Turbomachine rotor wheel
US4512718A (en) * 1982-10-14 1985-04-23 United Technologies Corporation Tandem fan stage for gas turbine engines
US5299914A (en) * 1991-09-11 1994-04-05 General Electric Company Staggered fan blade assembly for a turbofan engine
US5540551A (en) * 1994-08-03 1996-07-30 Westinghouse Electric Corporation Method and apparatus for reducing vibration in a turbo-machine blade
EP0781929A1 (en) * 1995-12-28 1997-07-02 Institut Francais Du Petrole Device for pumping or compressing a multi-phase fluid comprising tandem blading
US7604458B2 (en) * 2004-08-04 2009-10-20 Hitachi Plant Technologies, Ltd. Axial flow pump and diagonal flow pump
WO2008097287A2 (en) * 2006-12-15 2008-08-14 Siemens Energy, Inc. Aero-mixing of rotating blade structures
WO2008097287A3 (en) * 2006-12-15 2008-12-24 Siemens Energy Inc Aero-mixing of rotating blade structures
US7753652B2 (en) 2006-12-15 2010-07-13 Siemens Energy, Inc. Aero-mixing of rotating blade structures
FR2939852A1 (en) * 2008-12-15 2010-06-18 Snecma Stator blade stage for compressor of turboshaft engine e.g. turbopropeller engine, has intermediate blades with axial length or radial height less than that of rectifier blades and extend radially between rectifier blades
RU2557830C2 (en) * 2012-07-20 2015-07-27 Юрий Васильевич Дробышевский Creation of propulsive force for aircraft displacement and turbojet to this end
US9874221B2 (en) * 2014-12-29 2018-01-23 General Electric Company Axial compressor rotor incorporating splitter blades
US20160186773A1 (en) * 2014-12-29 2016-06-30 General Electric Company Axial compressor rotor incorporating splitter blades
US9938984B2 (en) 2014-12-29 2018-04-10 General Electric Company Axial compressor rotor incorporating non-axisymmetric hub flowpath and splittered blades
US20180017079A1 (en) * 2016-07-15 2018-01-18 General Electric Company Variable-cycle compressor with a splittered rotor
WO2018013422A3 (en) * 2016-07-15 2018-02-22 General Electric Company Axial flow compressor with splitter blades
US20180017019A1 (en) * 2016-07-15 2018-01-18 General Electric Company Turbofan engine wth a splittered rotor fan
CN109416050A (en) * 2016-07-15 2019-03-01 通用电气公司 Axial Flow Compressor with current divider blade
CN109416050B (en) * 2016-07-15 2022-03-29 通用电气公司 Axial compressor with splitter blades
US20180156124A1 (en) * 2016-12-01 2018-06-07 General Electric Company Turbine engine frame incorporating splitters
CN108131168A (en) * 2016-12-01 2018-06-08 通用电气公司 Turbogenerator rack including separator
CN108131168B (en) * 2016-12-01 2022-02-15 通用电气公司 Turbine engine frame including a separator
CN112119204A (en) * 2018-05-17 2020-12-22 赛峰飞机发动机公司 Turbomachine stator element
US11149552B2 (en) 2019-12-13 2021-10-19 General Electric Company Shroud for splitter and rotor airfoils of a fan for a gas turbine engine
US12037921B2 (en) 2022-08-04 2024-07-16 General Electric Company Fan for a turbine engine

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