US20090022593A1 - Fan blade retaining structure - Google Patents

Fan blade retaining structure Download PDF

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Publication number
US20090022593A1
US20090022593A1 US12/162,865 US16286507A US2009022593A1 US 20090022593 A1 US20090022593 A1 US 20090022593A1 US 16286507 A US16286507 A US 16286507A US 2009022593 A1 US2009022593 A1 US 2009022593A1
Authority
US
United States
Prior art keywords
disk
dovetail
fan blade
retainer
circumferential direction
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.)
Abandoned
Application number
US12/162,865
Other languages
English (en)
Inventor
Takashi Oka
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.)
IHI Corp
Original Assignee
IHI Corp
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 IHI Corp filed Critical IHI Corp
Assigned to IHI CORPORATION reassignment IHI CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: OKA, TAKASHI
Publication of US20090022593A1 publication Critical patent/US20090022593A1/en
Abandoned legal-status Critical Current

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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
    • F04D29/322—Blade mountings
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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

Definitions

  • the second blade retainer 144 is provided so as to prevent the axial movement of the fan blades 122 by serving as a chock after the fan blades 122 move by a predetermined distance in a case where the axial movement of the fan blades 122 cannot be prevented by the first blade retainer 138 .
  • both the first blade retainer 138 and the second blade retainer 144 disperse the axial forward shock energy acting on the fan blades 122 so that each fan blade 122 is retained in the dovetail grooves 130 .
  • the ring-shape retainer member Since the ring-shape retainer member is used, it is possible to reduce the number of components.
  • FIG. 5A is a transverse sectional view illustrating an engine provided with the fan blade retaining structure according to the invention.
  • FIG. 4 is an overall perspective view illustrating a state where a fan blade retaining structure according to the invention is disassembled.
  • the fan blade retaining structure according to the invention is configured such that a plurality of fan blades 20 are attached to the outer periphery of a disk 10 which is rotationally driven by a turbine (not shown).
  • the dovetail grooves 12 are parallel to a shaft center 1 of a rotary shaft, but may be inclined with respect to the shaft center 1 .
  • each of the dovetail grooves 12 may be formed into a linear shape or a circular arc shape so long as each of the fan blades 20 is inserted and fitted in an axial direction from the front side.
  • an axial distance (thickness) from the rear surface 32 a of the retainer member 30 to each front surface 34 a of the retainer tooth parts 34 is set to be a smaller value than an axial distance from the front surface 22 a of the dovetail part 22 to each rear surface 16 a of the disk tooth parts 16 in a mounting state. It is desirable that the gap is set so that the retainer member 30 smoothly rotates about the shaft center 1 in a state where the retainer member is mounted.
  • the retainer member 30 can transmit the axial forward load acting on the fan blade 20 to the disk 10 via the rear surfaces 16 a of the disk tooth parts 16 while being fitted between the front surfaces 22 a of the dovetail parts 22 and the rear surfaces 16 a of the disk tooth parts 16 .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US12/162,865 2006-03-13 2007-03-13 Fan blade retaining structure Abandoned US20090022593A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2006067620A JP2007247406A (ja) 2006-03-13 2006-03-13 ファンブレードの保持構造
JP2006-067620 2006-03-13
PCT/JP2007/054871 WO2007105701A1 (fr) 2006-03-13 2007-03-13 Structure support pour pale de ventilateur

Publications (1)

Publication Number Publication Date
US20090022593A1 true US20090022593A1 (en) 2009-01-22

Family

ID=38509521

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/162,865 Abandoned US20090022593A1 (en) 2006-03-13 2007-03-13 Fan blade retaining structure

Country Status (5)

Country Link
US (1) US20090022593A1 (fr)
EP (1) EP1995467B1 (fr)
JP (1) JP2007247406A (fr)
CA (1) CA2637277C (fr)
WO (1) WO2007105701A1 (fr)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120244004A1 (en) * 2011-03-21 2012-09-27 Virkler Scott D Component lock for a gas turbine engine
CN102869851A (zh) * 2010-04-28 2013-01-09 斯奈克玛 涡轮喷气发动机风扇叶片支撑的耐磨部件
CN103080479A (zh) * 2010-08-10 2013-05-01 斯奈克玛 用于锁定转子叶片根部的装置
US20140133991A1 (en) * 2012-11-15 2014-05-15 United Technologies Corporation Gas turbine engine fan blade lock assembly
US9151168B2 (en) 2011-05-06 2015-10-06 Snecma Turbine engine fan disk
CN105114349A (zh) * 2015-08-17 2015-12-02 南方泵业股份有限公司 一种离心泵活动法兰结构
US20160298642A1 (en) * 2013-11-29 2016-10-13 Snecma Fan, in particular for a turbine engine
US20170269006A1 (en) * 2014-08-19 2017-09-21 Tsinghua University Apparatus and method for inspecting moving target
US20170328226A1 (en) * 2014-11-27 2017-11-16 Hanwha Techwin Co., Ltd. Turbine apparatus
US10323519B2 (en) * 2016-06-23 2019-06-18 United Technologies Corporation Gas turbine engine having a turbine rotor with torque transfer and balance features
US10344622B2 (en) 2016-07-22 2019-07-09 United Technologies Corporation Assembly with mistake proof bayoneted lug
CN112324520A (zh) * 2020-10-27 2021-02-05 中国船舶重工集团公司第七0三研究所 一种燃气轮机静叶环结构
US11085309B2 (en) 2017-09-22 2021-08-10 General Electric Company Outer drum rotor assembly
US11313239B2 (en) * 2018-05-23 2022-04-26 Safran Aircraft Engines Turbmachine fan disc
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
US20240125242A1 (en) * 2022-10-14 2024-04-18 Rtx Corporation Platform for an airfoil of a gas turbine engine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2955889B1 (fr) * 2010-01-29 2012-11-16 Snecma Moyen de blocage d'un flasque d'etancheite sur un disque de turbine
FR2955904B1 (fr) * 2010-02-04 2012-07-20 Snecma Soufflante de turbomachine
US9624775B2 (en) 2014-05-30 2017-04-18 Rolls-Royce Plc Developments in or relating to rotor balancing
EP2792849B1 (fr) * 2014-05-30 2016-07-13 Rolls-Royce plc Perfectionnements à ou se rapportant à l'équilibrage d'un rotor

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3888601A (en) * 1974-05-23 1975-06-10 Gen Electric Turbomachine with balancing means
US4304523A (en) * 1980-06-23 1981-12-08 General Electric Company Means and method for securing a member to a structure
US4470756A (en) * 1982-04-08 1984-09-11 S.N.E.C.M.A. Device for axial securing of blade feet of a gas turbine disk
US4803893A (en) * 1987-09-24 1989-02-14 United Technologies Corporation High speed rotor balance system
US5282720A (en) * 1992-09-15 1994-02-01 General Electric Company Fan blade retainer
US5630703A (en) * 1995-12-15 1997-05-20 General Electric Company Rotor disk post cooling system
US6488473B1 (en) * 1999-12-17 2002-12-03 Rolls-Royce Deutschland Ltd & Co Kg Retaining arrangement for rotor blades of axial-flow turbomachinery
US6494684B1 (en) * 1999-10-27 2002-12-17 Rolls-Royce Plc Locking devices
US20070020089A1 (en) * 2005-07-21 2007-01-25 Snecma A device for damping vibration of a ring for axially retaining turbomachine fan blades

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4344740A (en) * 1979-09-28 1982-08-17 United Technologies Corporation Rotor assembly
JPS6247703U (fr) * 1985-09-13 1987-03-24
FR2715975B1 (fr) 1994-02-10 1996-03-29 Snecma Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées.
JPH1136802A (ja) * 1997-07-25 1999-02-09 Ishikawajima Harima Heavy Ind Co Ltd タービンロータ
CZ20002685A3 (cs) * 1999-12-20 2001-08-15 General Electric Company Zařízení pro uchycení lopatek otáčivého stroje a způsob jejich uchycení
FR2803623B1 (fr) * 2000-01-06 2002-03-01 Snecma Moteurs Agencement de retenue axiale d'aubes dans un disque
FR2819289B1 (fr) * 2001-01-11 2003-07-11 Snecma Moteurs Systeme de retention des aubes de type combine ou cascade

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3888601A (en) * 1974-05-23 1975-06-10 Gen Electric Turbomachine with balancing means
US4304523A (en) * 1980-06-23 1981-12-08 General Electric Company Means and method for securing a member to a structure
US4470756A (en) * 1982-04-08 1984-09-11 S.N.E.C.M.A. Device for axial securing of blade feet of a gas turbine disk
US4803893A (en) * 1987-09-24 1989-02-14 United Technologies Corporation High speed rotor balance system
US5282720A (en) * 1992-09-15 1994-02-01 General Electric Company Fan blade retainer
US5630703A (en) * 1995-12-15 1997-05-20 General Electric Company Rotor disk post cooling system
US6494684B1 (en) * 1999-10-27 2002-12-17 Rolls-Royce Plc Locking devices
US6488473B1 (en) * 1999-12-17 2002-12-03 Rolls-Royce Deutschland Ltd & Co Kg Retaining arrangement for rotor blades of axial-flow turbomachinery
US20070020089A1 (en) * 2005-07-21 2007-01-25 Snecma A device for damping vibration of a ring for axially retaining turbomachine fan blades
US7458769B2 (en) * 2005-07-21 2008-12-02 Snecma Device for damping vibration of a ring for axially retaining turbomachine fan blades

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102869851A (zh) * 2010-04-28 2013-01-09 斯奈克玛 涡轮喷气发动机风扇叶片支撑的耐磨部件
US9500091B2 (en) 2010-04-28 2016-11-22 Snecma Wear-resistant part for the support of a blade of a turbojet fan
CN103080479A (zh) * 2010-08-10 2013-05-01 斯奈克玛 用于锁定转子叶片根部的装置
US20120244004A1 (en) * 2011-03-21 2012-09-27 Virkler Scott D Component lock for a gas turbine engine
US8840375B2 (en) * 2011-03-21 2014-09-23 United Technologies Corporation Component lock for a gas turbine engine
US9151168B2 (en) 2011-05-06 2015-10-06 Snecma Turbine engine fan disk
US20140133991A1 (en) * 2012-11-15 2014-05-15 United Technologies Corporation Gas turbine engine fan blade lock assembly
US9376926B2 (en) * 2012-11-15 2016-06-28 United Technologies Corporation Gas turbine engine fan blade lock assembly
US10436212B2 (en) * 2013-11-29 2019-10-08 Safran Aircraft Engines Fan, in particular for a turbine engine
US20160298642A1 (en) * 2013-11-29 2016-10-13 Snecma Fan, in particular for a turbine engine
US20170269006A1 (en) * 2014-08-19 2017-09-21 Tsinghua University Apparatus and method for inspecting moving target
US20170328226A1 (en) * 2014-11-27 2017-11-16 Hanwha Techwin Co., Ltd. Turbine apparatus
US10563526B2 (en) * 2014-11-27 2020-02-18 Hanwha Aerospace Co., Ltd. Turbine apparatus
CN105114349A (zh) * 2015-08-17 2015-12-02 南方泵业股份有限公司 一种离心泵活动法兰结构
US10323519B2 (en) * 2016-06-23 2019-06-18 United Technologies Corporation Gas turbine engine having a turbine rotor with torque transfer and balance features
US10344622B2 (en) 2016-07-22 2019-07-09 United Technologies Corporation Assembly with mistake proof bayoneted lug
US11085309B2 (en) 2017-09-22 2021-08-10 General Electric Company Outer drum rotor assembly
US11313239B2 (en) * 2018-05-23 2022-04-26 Safran Aircraft Engines Turbmachine fan disc
CN112324520A (zh) * 2020-10-27 2021-02-05 中国船舶重工集团公司第七0三研究所 一种燃气轮机静叶环结构
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
US20240125242A1 (en) * 2022-10-14 2024-04-18 Rtx Corporation Platform for an airfoil of a gas turbine engine
US12012857B2 (en) * 2022-10-14 2024-06-18 Rtx Corporation Platform for an airfoil of a gas turbine engine

Also Published As

Publication number Publication date
EP1995467B1 (fr) 2014-05-07
CA2637277A1 (fr) 2007-09-20
EP1995467A4 (fr) 2013-01-02
WO2007105701A1 (fr) 2007-09-20
JP2007247406A (ja) 2007-09-27
EP1995467A1 (fr) 2008-11-26
CA2637277C (fr) 2012-10-09

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Legal Events

Date Code Title Description
AS Assignment

Owner name: IHI CORPORATION, JAPAN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:OKA, TAKASHI;REEL/FRAME:021323/0444

Effective date: 20080526

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION