GB996041A - Improvements in compressor or turbine blading - Google Patents

Improvements in compressor or turbine blading

Info

Publication number
GB996041A
GB996041A GB42174/63A GB4217463A GB996041A GB 996041 A GB996041 A GB 996041A GB 42174/63 A GB42174/63 A GB 42174/63A GB 4217463 A GB4217463 A GB 4217463A GB 996041 A GB996041 A GB 996041A
Authority
GB
United Kingdom
Prior art keywords
blades
flow
vanes
compressor
rotor
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
GB42174/63A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB996041A publication Critical patent/GB996041A/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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially 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
    • 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
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • 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
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Landscapes

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

Abstract

996,041. Axial-flow compressors; turbine blades. GENERAL ELECTRIC CO. Oct. 25, 1963 [Oct. 29, 1962], No. 42174/63. Headings F1C and FIT. [Also in Division F2] Auxiliary blading for the rotor or stator blades of a compressor or turbine to augment and turn the secondary fluid flow between adjacent blades thereof, comprises flow directing vanes radically disposed on the blades substantially at the surfaces of the boundary layer and so disposed that the secondary, fluid flow passing near the concave surfaces of the blades is directed toward the convex surfaces of adjacent blades. Auxiliary vanes 16, Fig. 4, which may be flat but preferably are cambered, are provided at the root portions of compressor rotor blades 12 substantially at the surface of the boundary layer air at the rotor hub 10. The secondary air, which flows essentially normal to the main flow and, at the hub, flows radially inwardly on the concave surfaces of the blades and radially outwardly on the convex surfaces of adjacent blades, is augmented by some of the main flow by means of the vanes 16 which are oriented to promote flow in this direction. Consequently, more boundary layer air is turned into the main stream to mix therewith, and this results in a higher pressure rise across the compressor before stall. Alternatively, or in addition to, the vanes 16 may be positioned at the tip portions of the blades 12 to augment the secondary flow at the outer casing, in which case the vanes 16 will be oriented to direct flow radially outwardly at the concave surfaces of the blades 12. In an alternative embodiment, Fig. 5 (not shown), flat curved vanes are provided at the root and tip portions of the rotor blades on their concave surfaces only.
GB42174/63A 1962-10-29 1963-10-25 Improvements in compressor or turbine blading Expired GB996041A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US233661A US3193185A (en) 1962-10-29 1962-10-29 Compressor blading

Publications (1)

Publication Number Publication Date
GB996041A true GB996041A (en) 1965-06-23

Family

ID=22878175

Family Applications (1)

Application Number Title Priority Date Filing Date
GB42174/63A Expired GB996041A (en) 1962-10-29 1963-10-25 Improvements in compressor or turbine blading

Country Status (6)

Country Link
US (1) US3193185A (en)
BE (1) BE638547A (en)
CH (1) CH417837A (en)
DE (1) DE1428110A1 (en)
GB (1) GB996041A (en)
SE (1) SE307216B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2357808A (en) * 1999-11-30 2001-07-04 Mtu Muenchen Gmbh Blade with ribs to optimize vibration behaviour
GB2373548A (en) * 2001-03-21 2002-09-25 Rolls Royce Plc Gas trubine engine aerofoils

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US3334807A (en) * 1966-03-28 1967-08-08 Rotron Mfg Co Fan
FR1502832A (en) * 1966-09-26 1967-11-24 Nord Aviation Diffusion faired propeller
US3692425A (en) * 1969-01-02 1972-09-19 Gen Electric Compressor for handling gases at velocities exceeding a sonic value
US3767324A (en) * 1969-06-11 1973-10-23 D Ericson Fan apparatus
US4116584A (en) * 1973-10-12 1978-09-26 Gutehoffnungshutte Sterkrade Ag Device for extending the working range of axial flow compressors
US4128363A (en) * 1975-04-30 1978-12-05 Kabushiki Kaisha Toyota Chuo Kenkyusho Axial flow fan
FR2361531A1 (en) * 1976-08-13 1978-03-10 Europ Turb Vapeur COMPRESSIBLE FLUID TURBINE
JPS5377321A (en) * 1976-12-20 1978-07-08 Toyota Central Res & Dev Lab Inc Axial-flow fan with supplementary blade
JPS5377320A (en) * 1976-12-20 1978-07-08 Toyota Central Res & Dev Lab Inc Axial-flow fan with supplementary blade
US4108573A (en) * 1977-01-26 1978-08-22 Westinghouse Electric Corp. Vibratory tuning of rotatable blades for elastic fluid machines
DE2715729B2 (en) * 1977-04-07 1979-04-26 Alberto 8131 Berg Kling Rotor for a turbine
JPS5472507A (en) * 1977-11-22 1979-06-11 Toyota Central Res & Dev Lab Inc Axial flow fan with supplementary blades
JPS55144896U (en) * 1979-04-06 1980-10-17
DE3017226A1 (en) * 1979-05-12 1980-11-20 Papst Motoren Kg FAN BLADE
US4255085A (en) * 1980-06-02 1981-03-10 Evans Frederick C Flow augmenters for vertical-axis windmills and turbines
JPS5891376A (en) * 1981-11-25 1983-05-31 Masao Yasugata Wind turbine
US4512718A (en) * 1982-10-14 1985-04-23 United Technologies Corporation Tandem fan stage for gas turbine engines
GB2177163B (en) * 1985-06-28 1988-12-07 Rolls Royce Improvements in or relating to aerofoil section members for gas turbine engines
US5112187A (en) * 1990-09-12 1992-05-12 Westinghouse Electric Corp. Erosion control through reduction of moisture transport by secondary flow
US5460488A (en) * 1994-06-14 1995-10-24 United Technologies Corporation Shrouded fan blade for a turbine engine
US5732872A (en) * 1994-06-17 1998-03-31 Heartport, Inc. Surgical stapling instrument
ES2163678T3 (en) * 1996-03-28 2002-02-01 Mtu Aero Engines Gmbh PALETTE SHEET FOR TURBINES.
WO1998044240A1 (en) 1997-04-01 1998-10-08 Siemens Aktiengesellschaft Surface structure for the wall of a flow channel or a turbine blade
DE19834647C2 (en) * 1998-07-31 2000-06-29 Deutsch Zentr Luft & Raumfahrt Blade arrangement for a turbomachine
EP0978633A1 (en) * 1998-08-07 2000-02-09 Asea Brown Boveri AG Turbomachine blade
DE19913269A1 (en) * 1999-03-24 2000-09-28 Asea Brown Boveri Turbine blade
EP1247991B1 (en) * 2001-04-05 2005-10-12 Hitachi, Ltd. Centrifugal pump
US7270519B2 (en) * 2002-11-12 2007-09-18 General Electric Company Methods and apparatus for reducing flow across compressor airfoil tips
US6779979B1 (en) * 2003-04-23 2004-08-24 General Electric Company Methods and apparatus for structurally supporting airfoil tips
US6905309B2 (en) * 2003-08-28 2005-06-14 General Electric Company Methods and apparatus for reducing vibrations induced to compressor airfoils
WO2005100752A1 (en) * 2004-04-09 2005-10-27 Norris Thomas R Externally mounted vortex generators for flow duct passage
US7189055B2 (en) * 2005-05-31 2007-03-13 Pratt & Whitney Canada Corp. Coverplate deflectors for redirecting a fluid flow
US7189056B2 (en) * 2005-05-31 2007-03-13 Pratt & Whitney Canada Corp. Blade and disk radial pre-swirlers
US7244104B2 (en) * 2005-05-31 2007-07-17 Pratt & Whitney Canada Corp. Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
ITMI20060340A1 (en) * 2006-02-27 2007-08-28 Nuovo Pignone Spa SHOVEL OF A ROTOR OF A SECOND STAGE OF A COMPRESSOR
EP2093378A1 (en) * 2008-02-25 2009-08-26 ALSTOM Technology Ltd Upgrading method for a blade by retrofitting a winglet, and correspondingly upgraded blade
US8147207B2 (en) * 2008-09-04 2012-04-03 Siemens Energy, Inc. Compressor blade having a ratio of leading edge sweep to leading edge dihedral in a range of 1:1 to 3:1 along the radially outer portion
US8770460B2 (en) * 2008-12-23 2014-07-08 George E. Belzer Shield for surgical stapler and method of use
EP2336492A1 (en) * 2009-12-16 2011-06-22 Siemens Aktiengesellschaft Guide vane with a winglet for an energy converting machine and machine for converting energy comprising the guide vane
US8591195B2 (en) 2010-05-28 2013-11-26 Pratt & Whitney Canada Corp. Turbine blade with pressure side stiffening rib
DE102011115455A1 (en) * 2011-09-12 2013-03-14 Brose Fahrzeugteile GmbH & Co. Kommanditgesellschaft, Würzburg Breathing electric motor
US8944774B2 (en) * 2012-01-03 2015-02-03 General Electric Company Gas turbine nozzle with a flow fence
US9359900B2 (en) * 2012-10-05 2016-06-07 General Electric Company Exhaust diffuser
EP2799721B8 (en) * 2013-05-03 2016-12-07 Safran Aero Booster S.A. Axial turbomachine stator guide with auxiliary vanes on the vane feet
US9874221B2 (en) 2014-12-29 2018-01-23 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
WO2016164533A1 (en) 2015-04-08 2016-10-13 Horton, Inc. Fan blade surface features
US10060441B2 (en) * 2015-05-26 2018-08-28 Pratt & Whitney Canada Corp. Gas turbine stator with winglets
GB2545711B (en) * 2015-12-23 2018-06-06 Rolls Royce Plc Gas turbine engine vane splitter
US10450867B2 (en) * 2016-02-12 2019-10-22 General Electric Company Riblets for a flowpath surface of a turbomachine
US20180017019A1 (en) * 2016-07-15 2018-01-18 General Electric Company Turbofan engine wth a splittered rotor fan
GB2559351B (en) * 2017-02-01 2020-03-18 Rolls Royce Plc A geared gas turbine engine
US10605087B2 (en) * 2017-12-14 2020-03-31 United Technologies Corporation CMC component with flowpath surface ribs
CN108223017A (en) * 2017-12-27 2018-06-29 中国航发四川燃气涡轮研究院 A kind of turbine rotor blade of the multiple rows of non-homogeneous winglet of listrium import band
DE102018206601A1 (en) * 2018-04-27 2019-10-31 MTU Aero Engines AG Blade, blade segment and assembly for a turbomachine and turbomachinery
EP3608505B1 (en) * 2018-08-08 2021-06-23 General Electric Company Turbine incorporating endwall fences
CN110067774A (en) * 2019-04-16 2019-07-30 中国航发湖南动力机械研究所 The compressor of combined impeller and gas-turbine unit
US11401824B2 (en) * 2019-10-15 2022-08-02 General Electric Company Gas turbine engine outlet guide vane assembly
KR102403823B1 (en) * 2019-12-13 2022-05-30 두산에너빌리티 주식회사 Strut structure with strip for exhaust diffuser and gas turbine having the same
IT202100002240A1 (en) 2021-02-02 2022-08-02 Gen Electric TURBINE ENGINE WITH REDUCED TRANSVERSE FLOW VANES
CN113513368B (en) * 2021-07-08 2022-09-02 哈尔滨工程大学 Turbine capable of directly backing with primary and secondary moving blade structures

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2357808A (en) * 1999-11-30 2001-07-04 Mtu Muenchen Gmbh Blade with ribs to optimize vibration behaviour
US6503053B2 (en) 1999-11-30 2003-01-07 MTU Motoren-und Turbinen München GmbH Blade with optimized vibration behavior
GB2357808B (en) * 1999-11-30 2003-08-27 Mtu Muenchen Gmbh Blade with optimized vibration behaviour
GB2373548A (en) * 2001-03-21 2002-09-25 Rolls Royce Plc Gas trubine engine aerofoils
US6572332B2 (en) 2001-03-21 2003-06-03 Rolls-Royce Plc Gas turbine engine aerofoils
GB2373548B (en) * 2001-03-21 2004-06-09 Rolls Royce Plc Gas turbine engine aerofoils

Also Published As

Publication number Publication date
DE1428110A1 (en) 1969-02-13
BE638547A (en) 1900-01-01
SE307216B (en) 1968-12-23
US3193185A (en) 1965-07-06
CH417837A (en) 1966-07-31

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