GB1262182A - Improvements in or relating to turbine rotor blades - Google Patents

Improvements in or relating to turbine rotor blades

Info

Publication number
GB1262182A
GB1262182A GB2304869A GB2304869A GB1262182A GB 1262182 A GB1262182 A GB 1262182A GB 2304869 A GB2304869 A GB 2304869A GB 2304869 A GB2304869 A GB 2304869A GB 1262182 A GB1262182 A GB 1262182A
Authority
GB
United Kingdom
Prior art keywords
blade
peak
bulge
turbine rotor
given
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
GB2304869A
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.)
Moskovsky Energetichesky Institut
Original Assignee
Moskovsky Energetichesky Institut
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 Moskovsky Energetichesky Institut filed Critical Moskovsky Energetichesky Institut
Publication of GB1262182A publication Critical patent/GB1262182A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • B64C2003/142—Aerofoil profile with variable camber along the airfoil chord
    • 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
    • F05D2240/301—Cross-sectional characteristics

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Hydraulic Turbines (AREA)

Abstract

1,262,182. Turbine blades. MOSKOVSKY ORDENA LENINA ENERGETICHESKY INSTITUT. May 6, 1969 [May 12, 1968], No.23048/69. Heading F1T. A steam or gas turbine rotor blade which is twisted and of varying cross-section from root to tip has a wave-shaped bulge 2 in the mainly concave pressure face, the peak m of the bulge being situated between the blade leading edge a and the mid-point of the concave face. At the blade cross section being considered, the distance I of the bulge peak m from the leading edge a is given by the formula: - where B is the chord length and # is the angle between the chord and the plane of rotor rotation. The blade thickness y at the peak m is given by: -
GB2304869A 1968-05-12 1969-05-06 Improvements in or relating to turbine rotor blades Expired GB1262182A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU1239940A SU411214A1 (en) 1968-05-12 1968-05-12

Publications (1)

Publication Number Publication Date
GB1262182A true GB1262182A (en) 1972-02-02

Family

ID=20442451

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2304869A Expired GB1262182A (en) 1968-05-12 1969-05-06 Improvements in or relating to turbine rotor blades

Country Status (5)

Country Link
CH (1) CH489696A (en)
DE (1) DE1923535C3 (en)
FR (1) FR2014127A1 (en)
GB (1) GB1262182A (en)
SU (1) SU411214A1 (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2151310A (en) * 1983-12-12 1985-07-17 Gen Electric Gas turbine engine blade
EP1225303A2 (en) * 2001-01-12 2002-07-24 Mitsubishi Heavy Industries, Ltd. Blade structure in a gas turbine
GB2373548A (en) * 2001-03-21 2002-09-25 Rolls Royce Plc Gas trubine engine aerofoils
EP1211382A3 (en) * 2000-11-30 2004-01-02 United Technologies Corporation Turbomachine rotor with blades of different frequency
EP1564374A1 (en) * 2004-02-12 2005-08-17 Siemens Aktiengesellschaft Turbine blade for a turbomachine
WO2005106207A1 (en) * 2004-04-27 2005-11-10 Siemens Aktiengesellschaft Compressor blade and compressor

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL7909125A (en) * 1979-12-19 1981-07-16 Philips Nv PLAY-FREE HOOK JOINT.
US4641796A (en) * 1983-09-30 1987-02-10 The Boeing Company Airfoil
CA1262409A (en) * 1985-05-01 1989-10-24 Kenneth Odell Johnson Counter rotation power turbine
US5197854A (en) * 1991-09-05 1993-03-30 Industrial Design Laboratories, Inc. Axial flow fan
FR2907157A1 (en) * 2006-10-13 2008-04-18 Snecma Sa MOBILE AUB OF TURBOMACHINE
DE102009036406A1 (en) * 2009-08-06 2011-02-10 Mtu Aero Engines Gmbh airfoil
US8393872B2 (en) * 2009-10-23 2013-03-12 General Electric Company Turbine airfoil

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR776676A (en) * 1933-10-23 1935-01-31 Helical turbine
NL300321A (en) * 1962-11-30

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2151310A (en) * 1983-12-12 1985-07-17 Gen Electric Gas turbine engine blade
EP1211382A3 (en) * 2000-11-30 2004-01-02 United Technologies Corporation Turbomachine rotor with blades of different frequency
EP1225303A2 (en) * 2001-01-12 2002-07-24 Mitsubishi Heavy Industries, Ltd. Blade structure in a gas turbine
EP1225303A3 (en) * 2001-01-12 2004-07-28 Mitsubishi Heavy Industries, Ltd. Blade structure in a gas turbine
US6887042B2 (en) 2001-01-12 2005-05-03 Mitsubishi Heavy Industries, Ltd. Blade structure in a gas turbine
US7229248B2 (en) 2001-01-12 2007-06-12 Mitsubishi Heavy Industries, Ltd. Blade structure in a gas turbine
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
EP1564374A1 (en) * 2004-02-12 2005-08-17 Siemens Aktiengesellschaft Turbine blade for a turbomachine
WO2005106207A1 (en) * 2004-04-27 2005-11-10 Siemens Aktiengesellschaft Compressor blade and compressor

Also Published As

Publication number Publication date
DE1923535B2 (en) 1971-12-16
SU411214A1 (en) 1974-01-15
FR2014127A1 (en) 1970-04-17
DE1923535A1 (en) 1970-01-29
DE1923535C3 (en) 1973-07-19
CH489696A (en) 1970-04-30

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