GB2436132B - Dovetail structure of fan - Google Patents

Dovetail structure of fan

Info

Publication number
GB2436132B
GB2436132B GB0703073A GB0703073A GB2436132B GB 2436132 B GB2436132 B GB 2436132B GB 0703073 A GB0703073 A GB 0703073A GB 0703073 A GB0703073 A GB 0703073A GB 2436132 B GB2436132 B GB 2436132B
Authority
GB
United Kingdom
Prior art keywords
fan
dovetail structure
dovetail
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.)
Active
Application number
GB0703073A
Other versions
GB0703073D0 (en
GB2436132A (en
Inventor
Tetsuji Fujimura
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
Publication of GB0703073D0 publication Critical patent/GB0703073D0/en
Publication of GB2436132A publication Critical patent/GB2436132A/en
Application granted granted Critical
Publication of GB2436132B publication Critical patent/GB2436132B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D5/30—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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
GB0703073A 2006-03-14 2007-02-16 Dovetail structure of fan Active GB2436132B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2006068517A JP4807113B2 (en) 2006-03-14 2006-03-14 Fan dovetail structure

Publications (3)

Publication Number Publication Date
GB0703073D0 GB0703073D0 (en) 2007-03-28
GB2436132A GB2436132A (en) 2007-09-19
GB2436132B true GB2436132B (en) 2008-05-14

Family

ID=37908789

Family Applications (1)

Application Number Title Priority Date Filing Date
GB0703073A Active GB2436132B (en) 2006-03-14 2007-02-16 Dovetail structure of fan

Country Status (5)

Country Link
US (1) US20070217915A1 (en)
JP (1) JP4807113B2 (en)
DE (1) DE102007012374B4 (en)
FR (1) FR2898646B1 (en)
GB (1) GB2436132B (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2007247407A (en) * 2006-03-13 2007-09-27 Ihi Corp Holding structure of fan blade
GB0803366D0 (en) 2008-02-26 2008-04-02 Rolls Royce Plc Nose cone assembly
FR2930595B1 (en) * 2008-04-24 2011-10-14 Snecma BLOWER ROTOR OF A TURBOMACHINE OR A TEST ENGINE
US8435006B2 (en) * 2009-09-30 2013-05-07 Rolls-Royce Corporation Fan
EP2971524A4 (en) 2013-03-12 2016-11-02 United Technologies Corp T-shaped platform leading edge anti-rotation tabs
WO2014143267A1 (en) * 2013-03-15 2014-09-18 United Technologies Corporation Gas turbine engine with low fan noise
WO2015047449A1 (en) 2013-09-30 2015-04-02 United Technologies Corporation Compressor area splits for geared turbofan
FR3033359B1 (en) * 2015-03-02 2017-04-07 Snecma MONOBLOC DRAWING DISK HAVING A HUB HAVING AN EVIDENCE FACED BY A BODY COMPRISING SAME
FR3048997B1 (en) * 2016-03-21 2020-03-27 Safran Aircraft Engines BLADE PLATFORM AND AERONAUTICAL TURBOMACHINE BLOWER DISC
FR3070183B1 (en) * 2017-08-18 2019-09-13 Safran Aircraft Engines TURBINE FOR TURBOMACHINE
US10738630B2 (en) * 2018-02-19 2020-08-11 General Electric Company Platform apparatus for propulsion rotor
US11280199B2 (en) 2018-11-21 2022-03-22 Honeywell International Inc. Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution
US11181120B2 (en) * 2018-11-21 2021-11-23 Honeywell International Inc. Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution
CN113738530B (en) * 2021-10-15 2022-06-17 清华大学 Multi-duct aero-engine casing structure with blade tip fan

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1523422A (en) * 1976-03-25 1978-08-31 Snecma Turbo-machines
US20020090300A1 (en) * 2001-01-11 2002-07-11 Douguet Charles Jean-Pierre Mounting arrangement for fixing a fan blade to a disk of a turbojet engine
EP1312756A2 (en) * 2001-11-14 2003-05-21 United Technologies Corporation Blade for turbine engine

Family Cites Families (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2755868A (en) * 1953-09-17 1956-07-24 United Aircraft Corp Spinner construction for an aeronautical propeller
US4621979A (en) * 1979-11-30 1986-11-11 United Technologies Corporation Fan rotor blades of turbofan engines
FR2502690B1 (en) * 1981-03-27 1985-09-13 Snecma DEVICE FOR LOCKING BLOWER VANES AND FOR FIXING A FRONT HOOD OF A TURBO-JET
FR2507679A1 (en) * 1981-06-12 1982-12-17 Snecma DEVICE FOR LOCKING A TURBOMACHINE ROTOR BLADE
FR2514409B1 (en) * 1981-10-09 1986-03-21 Snecma DEVICE FOR LAYING BLADES IN SECTORS ON A TURBOMACHINE ROTOR DISC
US4451205A (en) * 1982-02-22 1984-05-29 United Technologies Corporation Rotor blade assembly
FR2566061B1 (en) * 1984-06-14 1988-09-02 Snecma AXIAL LOCKING DEVICE OF A TURBOMACHINE BLADE
US5022822A (en) * 1989-10-24 1991-06-11 United Technologies Corporation Compressor blade attachment assembly
US5067876A (en) * 1990-03-29 1991-11-26 General Electric Company Gas turbine bladed disk
US5112193A (en) * 1990-09-11 1992-05-12 Pratt & Whitney Canada Fan blade axial retention device
FR2669686B1 (en) * 1990-11-28 1994-09-02 Snecma BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE.
US5197857A (en) * 1991-06-06 1993-03-30 General Electric Company Multiple rotor disk assembly
US5281096A (en) * 1992-09-10 1994-01-25 General Electric Company Fan assembly having lightweight platforms
JP3306998B2 (en) * 1993-06-10 2002-07-24 石川島播磨重工業株式会社 Turbine rotor
US5443365A (en) * 1993-12-02 1995-08-22 General Electric Company Fan blade for blade-out protection
US5486095A (en) * 1994-12-08 1996-01-23 General Electric Company Split disk blade support
GB2299834B (en) * 1995-04-12 1999-09-08 Rolls Royce Plc Gas turbine engine rotary disc
GB9615826D0 (en) * 1996-07-27 1996-09-11 Rolls Royce Plc Gas turbine engine fan blade retention
GB9814567D0 (en) * 1998-07-07 1998-09-02 Rolls Royce Plc A rotor assembly
US6149380A (en) * 1999-02-04 2000-11-21 Pratt & Whitney Canada Corp. Hardwall fan case with structured bumper
JP4316168B2 (en) * 2001-08-30 2009-08-19 株式会社東芝 Method for selecting blade material and shape of steam turbine blade and steam turbine
GB2382382B (en) * 2001-11-23 2005-08-10 Rolls Royce Plc A fan for a turbofan gas turbine engine
JP4352757B2 (en) * 2003-05-14 2009-10-28 株式会社Ｉｈｉ Jet engine fan and fan spacer
FR2930595B1 (en) * 2008-04-24 2011-10-14 Snecma BLOWER ROTOR OF A TURBOMACHINE OR A TEST ENGINE

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1523422A (en) * 1976-03-25 1978-08-31 Snecma Turbo-machines
US20020090300A1 (en) * 2001-01-11 2002-07-11 Douguet Charles Jean-Pierre Mounting arrangement for fixing a fan blade to a disk of a turbojet engine
EP1312756A2 (en) * 2001-11-14 2003-05-21 United Technologies Corporation Blade for turbine engine

Also Published As

Publication number Publication date
DE102007012374B4 (en) 2015-06-03
GB0703073D0 (en) 2007-03-28
JP2007247427A (en) 2007-09-27
US20070217915A1 (en) 2007-09-20
JP4807113B2 (en) 2011-11-02
FR2898646B1 (en) 2011-12-16
DE102007012374A1 (en) 2007-09-20
GB2436132A (en) 2007-09-19
FR2898646A1 (en) 2007-09-21

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