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GB1366924A - Compressor blades - Google Patents

Compressor blades

Info

Publication number
GB1366924A
GB1366924A GB5218171A GB5218171A GB1366924A GB 1366924 A GB1366924 A GB 1366924A GB 5218171 A GB5218171 A GB 5218171A GB 5218171 A GB5218171 A GB 5218171A GB 1366924 A GB1366924 A GB 1366924A
Authority
GB
United Kingdom
Prior art keywords
blade
ribs
nov
tip
pair
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
GB5218171A
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.)
Pratt and Whitney Canada Corp
Original Assignee
United Aircraft of Canada 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 United Aircraft of Canada Ltd filed Critical United Aircraft of Canada Ltd
Publication of GB1366924A publication Critical patent/GB1366924A/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
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • F04D21/00—Pump involving supersonic speed of pumped fluids
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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

Landscapes

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

Abstract

1366924 Compressor blades UNITED AIRCRAFT OF CANADA Ltd 10 Nov 1971 [16 Nov 1970] 52181/71 Heading FIT To reduce foreign object damage, compressor rotor blades 1 of a gas turbine engine are each provided with at least one pair of chordwise ribs 17, 17' on their aerofoil surfaces, the ribs being nearer to the blade tip 7 than to root 3 in a region where the camber angle α of the blade is less than 30 degrees. Angle α of each blade decreases towards its tip. Each rib 17, 17' has a circumferential width (W), Fig. 4 (not shown) not greater than twice the maximum thickness 7 of the blade and a radial thickness not greater than T. They are cast with the blade and may be of rectangular or trapezoidal cross-section, the edges 19, 19' and 21, 21' being tapered to merge with the blade aerofoil surfaces. A further pair of ribs 23 (23') is provided outwardly of ribs 17, 17'.
GB5218171A 1970-11-16 1971-11-10 Compressor blades Expired GB1366924A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US8964070A 1970-11-16 1970-11-16

Publications (1)

Publication Number Publication Date
GB1366924A true GB1366924A (en) 1974-09-18

Family

ID=22218769

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5218171A Expired GB1366924A (en) 1970-11-16 1971-11-10 Compressor blades

Country Status (3)

Country Link
US (1) US3706512A (en)
FR (1) FR2114693A5 (en)
GB (1) GB1366924A (en)

Cited By (3)

* 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
US10641107B2 (en) 2012-10-26 2020-05-05 Rolls-Royce Plc Turbine blade with tip overhang along suction side

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2616486B1 (en) * 1987-06-10 1993-05-28 Snecma METHOD FOR MANUFACTURING A MOBILE VANE OF COMPRESSOR WITH REAR INTERMEDIATE HEELS
DE19913269A1 (en) * 1999-03-24 2000-09-28 Asea Brown Boveri Turbine blade
ITTO20011075A1 (en) * 2001-11-16 2003-05-16 Fiatavio Spa PALETTE ORGAN, IN PARTICULAR FOR AN AXIAL TURBINE OF AN AIRCRAFT ENGINE.
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
FR2867506A1 (en) * 2004-03-11 2005-09-16 Snecma Moteurs Guide vane for use on stator of jet engine, has rib directed in direction of gas flow traversing vane for dampening vibrations of vane, and placed at back side of vane closer to trailing edge than leading edge of vane
ITMI20060340A1 (en) * 2006-02-27 2007-08-28 Nuovo Pignone Spa SHOVEL OF A ROTOR OF A SECOND STAGE OF A COMPRESSOR
US9845683B2 (en) * 2013-01-08 2017-12-19 United Technology Corporation Gas turbine engine rotor blade
ITCO20130024A1 (en) * 2013-06-13 2014-12-14 Nuovo Pignone Srl COMPRESSOR IMPELLERS
FR3022295B1 (en) * 2014-06-17 2019-07-05 Safran Aircraft Engines TURBOMACHINE DAWN COMPRISING AN ANTIWINDER FIN
US10443390B2 (en) * 2014-08-27 2019-10-15 Pratt & Whitney Canada Corp. Rotary airfoil
WO2016164533A1 (en) 2015-04-08 2016-10-13 Horton, Inc. Fan blade surface features
US11421535B2 (en) * 2017-10-31 2022-08-23 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbine blade, turbocharger, and method of producing turbine blade
US10605087B2 (en) * 2017-12-14 2020-03-31 United Technologies Corporation CMC component with flowpath surface ribs
FR3081913B1 (en) * 2018-06-04 2021-01-08 Safran Aircraft Engines TURBOMACHINE VANE INCLUDING AN ANTI-SWIRL VANE
BE1026579B1 (en) * 2018-08-31 2020-03-30 Safran Aero Boosters Sa PROTUBERANCE VANE FOR TURBOMACHINE COMPRESSOR
FR3087828B1 (en) * 2018-10-26 2021-01-08 Safran Helicopter Engines MOBILE TURBOMACHINE BLADE
IT202100002240A1 (en) * 2021-02-02 2022-08-02 Gen Electric TURBINE ENGINE WITH REDUCED TRANSVERSE FLOW VANES

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA606617A (en) * 1960-10-11 M. Ganger Karl Ventilating fan with reversible motor
US2965180A (en) * 1954-12-20 1960-12-20 American Radiator & Standard Propeller fan wheel
US3012709A (en) * 1955-05-18 1961-12-12 Daimler Benz Ag Blade for axial compressors
GB840543A (en) * 1956-01-16 1960-07-06 Vickers Electrical Co Ltd Improvements in turbine blading

Cited By (7)

* 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
US10641107B2 (en) 2012-10-26 2020-05-05 Rolls-Royce Plc Turbine blade with tip overhang along suction side

Also Published As

Publication number Publication date
US3706512A (en) 1972-12-19
FR2114693A5 (en) 1972-06-30

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee
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