JPS57186004A - Structure of rotor for turbo-machine - Google Patents

Structure of rotor for turbo-machine

Info

Publication number
JPS57186004A
JPS57186004A JP7074481A JP7074481A JPS57186004A JP S57186004 A JPS57186004 A JP S57186004A JP 7074481 A JP7074481 A JP 7074481A JP 7074481 A JP7074481 A JP 7074481A JP S57186004 A JPS57186004 A JP S57186004A
Authority
JP
Japan
Prior art keywords
butt
blade
groove
rotor
securing
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
JP7074481A
Other languages
Japanese (ja)
Inventor
Toshio Hattori
Yasushi Mori
Yasunari Kashiwara
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 JP7074481A priority Critical patent/JPS57186004A/en
Publication of JPS57186004A publication Critical patent/JPS57186004A/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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE:To heighten the damping of vibration of blades, by providing a slit or circular hole between adjacent blade securing grooves on the peripheral surface of a rotor to facilitate local slippage between the butt of the blade and the securing groove. CONSTITUTION:The cross section of the butt 3 of each blade 2 is shaped as a dovetail. The butt 3 is inserted in a blade securing groove 4. The axial movement of the butt 3 is restrained by blocks 5. A slit 9 is provided between the adjacent grooves 4 so that the pressure between the butt 3 of the blade 2 and the groove 4 is reduced on the peripheral surface. As a result, local slippage is easily caused between the butt 3 and the securing groove 4 by the vibratory force of the blade 2 to heighten the damping of its vibration.
JP7074481A 1981-05-13 1981-05-13 Structure of rotor for turbo-machine Pending JPS57186004A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP7074481A JPS57186004A (en) 1981-05-13 1981-05-13 Structure of rotor for turbo-machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP7074481A JPS57186004A (en) 1981-05-13 1981-05-13 Structure of rotor for turbo-machine

Publications (1)

Publication Number Publication Date
JPS57186004A true JPS57186004A (en) 1982-11-16

Family

ID=13440322

Family Applications (1)

Application Number Title Priority Date Filing Date
JP7074481A Pending JPS57186004A (en) 1981-05-13 1981-05-13 Structure of rotor for turbo-machine

Country Status (1)

Country Link
JP (1) JPS57186004A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
JPS61155602A (en) * 1984-12-20 1986-07-15 ゼネラル・エレクトリツク・カンパニイ Seal of blade root
US5151013A (en) * 1990-12-27 1992-09-29 United Technologies Corporation Blade lock for a rotor disk and rotor blade assembly
EP1219782A2 (en) * 2000-12-21 2002-07-03 United Technologies Corporation Bladed rotor assembly
GB2401657A (en) * 2003-04-25 2004-11-17 Gen Electric Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US6902376B2 (en) 2002-12-26 2005-06-07 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US7121803B2 (en) 2002-12-26 2006-10-17 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
EP1855011A1 (en) * 2006-05-12 2007-11-14 Snecma Moteurs Assembly for the engine compressor of an aircraft comprising tilted-head hammer attachment vanes
EP2535520A3 (en) * 2011-06-17 2018-01-03 General Electric Company Method and apparatus to repair a turbomachine rotor wheel

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
JPS61155602A (en) * 1984-12-20 1986-07-15 ゼネラル・エレクトリツク・カンパニイ Seal of blade root
US5151013A (en) * 1990-12-27 1992-09-29 United Technologies Corporation Blade lock for a rotor disk and rotor blade assembly
EP1219782A2 (en) * 2000-12-21 2002-07-03 United Technologies Corporation Bladed rotor assembly
EP1219782A3 (en) * 2000-12-21 2003-10-08 United Technologies Corporation Bladed rotor assembly
US6902376B2 (en) 2002-12-26 2005-06-07 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US7121803B2 (en) 2002-12-26 2006-10-17 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US7165944B2 (en) 2002-12-26 2007-01-23 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
GB2401657A (en) * 2003-04-25 2004-11-17 Gen Electric Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
EP1855011A1 (en) * 2006-05-12 2007-11-14 Snecma Moteurs Assembly for the engine compressor of an aircraft comprising tilted-head hammer attachment vanes
FR2900989A1 (en) * 2006-05-12 2007-11-16 Snecma Sa AIRCRAFT ENGINE COMPRESSOR ASSEMBLY COMPRISING AUBES WITH FOOT HAMMER ATTACHMENT
US7959410B2 (en) 2006-05-12 2011-06-14 Snecma Assembly for an aircraft engine compressor comprising blades with hammer attachment with inclined root
EP2535520A3 (en) * 2011-06-17 2018-01-03 General Electric Company Method and apparatus to repair a turbomachine rotor wheel

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