JPS54151707A - Turbine blade lattice structure - Google Patents

Turbine blade lattice structure

Info

Publication number
JPS54151707A
JPS54151707A JP5992778A JP5992778A JPS54151707A JP S54151707 A JPS54151707 A JP S54151707A JP 5992778 A JP5992778 A JP 5992778A JP 5992778 A JP5992778 A JP 5992778A JP S54151707 A JPS54151707 A JP S54151707A
Authority
JP
Japan
Prior art keywords
blade
root
lattice
blade lattice
turbine blade
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.)
Pending
Application number
JP5992778A
Other languages
Japanese (ja)
Inventor
Toshio Shinohara
Takamitsu Taki
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.)
Hitachi Ltd
Original Assignee
Hitachi 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 Hitachi Ltd filed Critical Hitachi Ltd
Priority to JP5992778A priority Critical patent/JPS54151707A/en
Publication of JPS54151707A publication Critical patent/JPS54151707A/en
Pending 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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE:To prevent secondary flow produced at the root portion of turbine blade lattice by forming smooth gradient surface on the root wall surface at the outlets of the blade lattice. CONSTITUTION:Smooth gradient surface is formed on the root wall surface 5 at the outlets of the blade lattice so that the root position of the inside surface 4 of the blade is higher than the root position of the back surface 3 of the blade. When the blade 1 thus constructed turns, a flow 11 from the back surface 3 toward the inside surface 4 of the blade occurs in the boundary layer on the root wall surface 5 by means of centrifugal force. Accordingly, secondary flow 9 is suppressed due to this flow 11 so as to reduce the loss occurred in the blade lattice.
JP5992778A 1978-05-22 1978-05-22 Turbine blade lattice structure Pending JPS54151707A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP5992778A JPS54151707A (en) 1978-05-22 1978-05-22 Turbine blade lattice structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP5992778A JPS54151707A (en) 1978-05-22 1978-05-22 Turbine blade lattice structure

Publications (1)

Publication Number Publication Date
JPS54151707A true JPS54151707A (en) 1979-11-29

Family

ID=13127238

Family Applications (1)

Application Number Title Priority Date Filing Date
JP5992778A Pending JPS54151707A (en) 1978-05-22 1978-05-22 Turbine blade lattice structure

Country Status (1)

Country Link
JP (1) JPS54151707A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2485620A1 (en) * 1980-06-24 1981-12-31 Mtu Muenchen Gmbh DEVICE FOR REDUCING SECONDARY LOSSES IN A TURBOMACHINE FLOW CONDUIT WITH AUBAGES
US5395213A (en) * 1992-10-21 1995-03-07 Societe Nationale D'etude Et De Construction De Motors D'aviation "Snecma" Turbojet engine rotor
US6213711B1 (en) * 1997-04-01 2001-04-10 Siemens Aktiengesellschaft Steam turbine and blade or vane for a steam turbine
US20080095614A1 (en) * 2006-10-20 2008-04-24 Snecma Fan platform fin
JP2009209745A (en) * 2008-03-03 2009-09-17 Mitsubishi Heavy Ind Ltd Turbine stage of axial flow type turbo machine, and gas turbine
EP2789802A1 (en) * 2013-04-09 2014-10-15 MTU Aero Engines GmbH Blade row for a turbomachine and corresponding manufacturing method
FR3014943A1 (en) * 2013-12-18 2015-06-19 Snecma TURBOMACHINE PIECE WITH NON-AXISYMETRIC SURFACE

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2485620A1 (en) * 1980-06-24 1981-12-31 Mtu Muenchen Gmbh DEVICE FOR REDUCING SECONDARY LOSSES IN A TURBOMACHINE FLOW CONDUIT WITH AUBAGES
US5395213A (en) * 1992-10-21 1995-03-07 Societe Nationale D'etude Et De Construction De Motors D'aviation "Snecma" Turbojet engine rotor
US6213711B1 (en) * 1997-04-01 2001-04-10 Siemens Aktiengesellschaft Steam turbine and blade or vane for a steam turbine
US20080095614A1 (en) * 2006-10-20 2008-04-24 Snecma Fan platform fin
US8303258B2 (en) * 2006-10-20 2012-11-06 Snecma Fan platform fin
JP2009209745A (en) * 2008-03-03 2009-09-17 Mitsubishi Heavy Ind Ltd Turbine stage of axial flow type turbo machine, and gas turbine
EP2789802A1 (en) * 2013-04-09 2014-10-15 MTU Aero Engines GmbH Blade row for a turbomachine and corresponding manufacturing method
US10190416B2 (en) 2013-04-09 2019-01-29 MTU Aero Engines AG Blade cascade for turbo machine
FR3014943A1 (en) * 2013-12-18 2015-06-19 Snecma TURBOMACHINE PIECE WITH NON-AXISYMETRIC SURFACE
US10519980B2 (en) 2013-12-18 2019-12-31 Safran Aircraft Engines Turbomachine component or collection of components and associated turbomachine

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