GB789883A - High speed aerofoil - Google Patents

High speed aerofoil

Info

Publication number
GB789883A
GB789883A GB24360/54A GB2436054A GB789883A GB 789883 A GB789883 A GB 789883A GB 24360/54 A GB24360/54 A GB 24360/54A GB 2436054 A GB2436054 A GB 2436054A GB 789883 A GB789883 A GB 789883A
Authority
GB
United Kingdom
Prior art keywords
serrations
aerofoil
blade
leading edge
chord
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
GB24360/54A
Inventor
Ivor Macaulay Davidson
Brian Stapleton Stratford
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.)
Power Jets Research and Development Ltd
Original Assignee
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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB24360/54A priority Critical patent/GB789883A/en
Publication of GB789883A publication Critical patent/GB789883A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/10—Influencing air flow over aircraft surfaces by affecting boundary layer flow using other surface properties, e.g. roughness
    • 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
    • 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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • Y02T50/10—Drag reduction
    • 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)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

789,883. Turbine and compressor blades. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. Aug. 11, 1955 [Aug. 20, 1954], No. 24360/54. Classes 110 (1) and 110 (3). [Also in Group XXXIII] An aerofoil designed for use in a fluid stream flowing at a speed of the order of the speed of sound or above, for example a turbine or compressor blade, has a sharp leading edge formed with serrations. The serrations may be in the form of isosceles triangles having a base angle of 60 degrees, as in the compressor blade shown in the Figures. The depth D and the pitch P of the serrations are small compared with the aerofoil chord, for example they may be of the order of 1 to 5 per cent of the aerofoil chord. The pitch and the depth of the serrations may either be constant or vary along the length of the aerofoil. The leading edge may be formed with two superimposed sets of serrations of different depth and pitch. The object of the invention is to prevent boundary layer separation which takes place when a supersonic aerofoil having a leading edge of knife-edge form or of very small radius compared with the aerofoil chord, is operated at an angle of, say, more than 4 degrees from the design incidence. Each tooth 3 of the serrations constitutes a small delta wing which gives rise to a pair of oppositely rotating trailing vortices as indicated at 4 which extend rearwardly over the surface of the blade. The serrations may be cut in the material of the blade itself or they may be formed in a flat plate 5 set into the leading edge of the blade 1 as shown in Fig. 4. The serrations may alternatively be rectangular, trapezoidal, semi-circular or sinusoidal in form. A blade of bi-convex section with a small thickness compared with its chord and with sharp leading and trailing edges is shown in Specification 615,219.
GB24360/54A 1954-08-20 1954-08-20 High speed aerofoil Expired GB789883A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB24360/54A GB789883A (en) 1954-08-20 1954-08-20 High speed aerofoil

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB24360/54A GB789883A (en) 1954-08-20 1954-08-20 High speed aerofoil

Publications (1)

Publication Number Publication Date
GB789883A true GB789883A (en) 1958-01-29

Family

ID=10210504

Family Applications (1)

Application Number Title Priority Date Filing Date
GB24360/54A Expired GB789883A (en) 1954-08-20 1954-08-20 High speed aerofoil

Country Status (1)

Country Link
GB (1) GB789883A (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2581708A1 (en) * 1985-05-09 1986-11-14 Snecma CAPOTAGE FOR TURBOJET ENGINE BLOWING BOLT ATTACK
US4913381A (en) * 1986-05-12 1990-04-03 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Aerodynamic components having leading edge devices
US5275535A (en) * 1991-05-31 1994-01-04 Innerspace Corporation Ortho skew propeller blade
US5533865A (en) * 1993-11-04 1996-07-09 Stork Product Engineering B.V. Wind turbine
GB2355288A (en) * 1999-10-12 2001-04-18 Rolls Royce Plc Gas turbine blade trailing edge
EP1277966A2 (en) * 2001-07-18 2003-01-22 General Electric Company Serrated fan blade
US9249666B2 (en) 2011-12-22 2016-02-02 General Electric Company Airfoils for wake desensitization and method for fabricating same
US20170058917A1 (en) * 2015-09-02 2017-03-02 Krista L. McKinney Single thickness blade with leading edge serrations on an axial fan
EP2672080A3 (en) * 2012-06-08 2017-07-19 General Electric Company Aerodynamic Element of Turbine Engine
CN107489646A (en) * 2017-08-02 2017-12-19 奥克斯空调股份有限公司 Sawtooth pattern noise reduction axial-flow leaf
CN108019237A (en) * 2017-11-28 2018-05-11 武汉大学 A kind of bionical blade profile of steam turbine for suppressing flow separation
CN112523809A (en) * 2020-11-30 2021-03-19 北京动力机械研究所 Method for inhibiting unsteady airflow excitation force of turbine rotor blade
CN113167120A (en) * 2018-10-18 2021-07-23 赛峰飞机发动机公司 Profile for an aircraft or turbine

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0202153A1 (en) * 1985-05-09 1986-11-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Protecting cap for the leading edge of a turbo fan blade
US4712980A (en) * 1985-05-09 1987-12-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Fairing for turbo-jet engine fan leading edge
FR2581708A1 (en) * 1985-05-09 1986-11-14 Snecma CAPOTAGE FOR TURBOJET ENGINE BLOWING BOLT ATTACK
US4913381A (en) * 1986-05-12 1990-04-03 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Aerodynamic components having leading edge devices
US5275535A (en) * 1991-05-31 1994-01-04 Innerspace Corporation Ortho skew propeller blade
US5533865A (en) * 1993-11-04 1996-07-09 Stork Product Engineering B.V. Wind turbine
GB2355288B (en) * 1999-10-12 2003-10-01 Rolls Royce Plc Improved turbine blade and manufacture thereof
GB2355288A (en) * 1999-10-12 2001-04-18 Rolls Royce Plc Gas turbine blade trailing edge
US6358013B1 (en) 1999-10-12 2002-03-19 Rolls-Royce Plc Turbine blade and manufacture thereof
EP1277966A3 (en) * 2001-07-18 2003-10-29 General Electric Company Serrated fan blade
EP1277966A2 (en) * 2001-07-18 2003-01-22 General Electric Company Serrated fan blade
US6733240B2 (en) 2001-07-18 2004-05-11 General Electric Company Serrated fan blade
US9249666B2 (en) 2011-12-22 2016-02-02 General Electric Company Airfoils for wake desensitization and method for fabricating same
EP2672080A3 (en) * 2012-06-08 2017-07-19 General Electric Company Aerodynamic Element of Turbine Engine
US20170058917A1 (en) * 2015-09-02 2017-03-02 Krista L. McKinney Single thickness blade with leading edge serrations on an axial fan
CN107489646A (en) * 2017-08-02 2017-12-19 奥克斯空调股份有限公司 Sawtooth pattern noise reduction axial-flow leaf
CN107489646B (en) * 2017-08-02 2024-01-12 奥克斯空调股份有限公司 Sawtooth type noise-reducing axial flow fan blade
CN108019237A (en) * 2017-11-28 2018-05-11 武汉大学 A kind of bionical blade profile of steam turbine for suppressing flow separation
CN113167120A (en) * 2018-10-18 2021-07-23 赛峰飞机发动机公司 Profile for an aircraft or turbine
US11668196B2 (en) * 2018-10-18 2023-06-06 Safran Aircraft Engines Profiled structure for an aircraft or turbomachine
CN113167120B (en) * 2018-10-18 2023-07-04 赛峰飞机发动机公司 Profiled structure for an aircraft or turbine
CN112523809A (en) * 2020-11-30 2021-03-19 北京动力机械研究所 Method for inhibiting unsteady airflow excitation force of turbine rotor blade

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