JP2008261332A - ファンブレード - Google Patents

ファンブレード Download PDF

Info

Publication number
JP2008261332A
JP2008261332A JP2008095753A JP2008095753A JP2008261332A JP 2008261332 A JP2008261332 A JP 2008261332A JP 2008095753 A JP2008095753 A JP 2008095753A JP 2008095753 A JP2008095753 A JP 2008095753A JP 2008261332 A JP2008261332 A JP 2008261332A
Authority
JP
Japan
Prior art keywords
aerodynamic
fan blade
turbojet
fan
blades
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
JP2008095753A
Other languages
English (en)
Japanese (ja)
Other versions
JP2008261332A5 (enExample
Inventor
Olivier Belmonte
オリビエ・ベルモント
Amadou Lamine M'bengue
アマドー・ラミーヌ・ムバング
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of JP2008261332A publication Critical patent/JP2008261332A/ja
Publication of JP2008261332A5 publication Critical patent/JP2008261332A5/ja
Pending legal-status Critical Current

Links

Images

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
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/022—Multi-stage pumps with concentric rows of vanes
    • 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
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/326—Application in turbines in gas turbines to drive shrouded, low solidity propeller
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/327—Application in turbines in gas turbines to drive shrouded, high solidity propeller
    • 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)
  • Architecture (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
JP2008095753A 2007-04-13 2008-04-02 ファンブレード Pending JP2008261332A (ja)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0702682A FR2914943B1 (fr) 2007-04-13 2007-04-13 Aube de soufflante

Publications (2)

Publication Number Publication Date
JP2008261332A true JP2008261332A (ja) 2008-10-30
JP2008261332A5 JP2008261332A5 (enExample) 2013-03-07

Family

ID=38564352

Family Applications (1)

Application Number Title Priority Date Filing Date
JP2008095753A Pending JP2008261332A (ja) 2007-04-13 2008-04-02 ファンブレード

Country Status (8)

Country Link
US (1) US8257023B2 (enExample)
EP (1) EP1980753B1 (enExample)
JP (1) JP2008261332A (enExample)
CN (1) CN101307776B (enExample)
CA (1) CA2628626C (enExample)
DE (1) DE602008000360D1 (enExample)
FR (1) FR2914943B1 (enExample)
RU (1) RU2486346C2 (enExample)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITTO20090522A1 (it) * 2009-07-13 2011-01-14 Avio Spa Turbomacchina con girante a segmenti palettati
US20120324901A1 (en) * 2011-06-23 2012-12-27 United Technologies Corporation Tandem fan-turbine rotor for a tip turbine engine
ITMI20120569A1 (it) * 2012-04-06 2013-10-07 Franco Tosi Meccanica S P A Stadio rotorico di turbina assiale a rapporto corda/passo migliorato
CA2925842A1 (en) 2013-10-03 2015-04-09 Franco Tosi Meccanica S.P.A. Rotor stage of axial turbine with improved chord/pitch ratio
EP2977549B1 (fr) 2014-07-22 2017-05-31 Safran Aero Boosters SA Aubage de turbomachine axiale et turbomachine associée
EP2977548B1 (fr) * 2014-07-22 2021-03-10 Safran Aero Boosters SA Aube et turbomachine associée
EP2977550B1 (fr) 2014-07-22 2017-05-31 Safran Aero Boosters SA Aube de turbomachine axiale et turbomachine associée
US10767656B2 (en) * 2014-08-07 2020-09-08 Mitsubishi Electric Corporation Axial flow fan and air-conditioning apparatus having axial flow fan
RU2631850C2 (ru) * 2015-10-30 2017-09-26 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Рабочее колесо осевого компрессора газотурбинного двигателя
US10619483B2 (en) 2017-11-21 2020-04-14 United Technologies Corporation Partially shrouded gas turbine engine fan
FR3079007B1 (fr) * 2018-03-14 2020-11-20 Safran Aircraft Engines Ensemble pour une soufflante
FR3107078B1 (fr) 2020-02-07 2023-01-13 Safran Helicopter Engines Aube de rotor pour une turbomachine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59183099A (ja) * 1983-03-31 1984-10-18 Nippon Denso Co Ltd 軸流フアン
JPH09133089A (ja) * 1995-11-09 1997-05-20 Fujita Corp 流体駆動装置
JP2002180996A (ja) * 2000-10-31 2002-06-26 General Electric Co <Ge> ブリスク

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB189131A (en) * 1921-11-16 1923-03-01 Rateau Soc Improvements in or relating to turbine blades
GB460781A (en) * 1935-08-06 1937-02-04 William Wycliffe Spooner Improvements in or relating to fans, rotors, and the like
US2509442A (en) * 1945-04-17 1950-05-30 Matheisel Rudolph Inverse rotor
US3044559A (en) * 1959-07-14 1962-07-17 Chajmik Joseph Propeller
US7216475B2 (en) * 2003-11-21 2007-05-15 General Electric Company Aft FLADE engine
US7144221B2 (en) * 2004-07-30 2006-12-05 General Electric Company Method and apparatus for assembling gas turbine engines
US7631484B2 (en) * 2006-03-13 2009-12-15 Rollin George Giffin High pressure ratio aft fan
US7758303B1 (en) * 2006-07-31 2010-07-20 General Electric Company FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59183099A (ja) * 1983-03-31 1984-10-18 Nippon Denso Co Ltd 軸流フアン
JPH09133089A (ja) * 1995-11-09 1997-05-20 Fujita Corp 流体駆動装置
JP2002180996A (ja) * 2000-10-31 2002-06-26 General Electric Co <Ge> ブリスク

Also Published As

Publication number Publication date
FR2914943B1 (fr) 2011-04-01
CA2628626A1 (fr) 2008-10-13
EP1980753A1 (fr) 2008-10-15
FR2914943A1 (fr) 2008-10-17
DE602008000360D1 (de) 2010-01-21
US20090028717A1 (en) 2009-01-29
RU2486346C2 (ru) 2013-06-27
EP1980753B1 (fr) 2009-12-09
CN101307776B (zh) 2011-09-21
CA2628626C (fr) 2014-12-23
RU2008114256A (ru) 2009-10-20
CN101307776A (zh) 2008-11-19
US8257023B2 (en) 2012-09-04

Similar Documents

Publication Publication Date Title
JP2008261332A (ja) ファンブレード
JP2008261332A5 (enExample)
US8834129B2 (en) Turbofan flow path trenches
CN108425883B (zh) 燃气涡轮发动机风扇叶片
US7955054B2 (en) Internally damped blade
CN108425884B (zh) 燃气涡轮发动机风扇叶片
CN109538352B (zh) 外鼓转子组件和燃气涡轮发动机
CA2566584A1 (en) Fan blade curvature distribution for high core pressure ratio fan
US20180017079A1 (en) Variable-cycle compressor with a splittered rotor
EP3578761A1 (en) Gas turbine engine compressor with a variable stator vane arrangement
CN116209821A (zh) 设置有螺旋桨和偏置定子轮叶的涡轮机模块
EP2971570B1 (en) Fan blade dovetail and spacer
US12065942B2 (en) Gas turbine engine fan
US9765637B2 (en) Blisk with low stresses at blade root, preferably for an aircraft turbine engine fan
US9617860B2 (en) Fan blades for gas turbine engines with reduced stress concentration at leading edge
US20240044253A1 (en) Fan for a turbine engine
US20240077047A1 (en) Geared turbofan low-pressure turbine with flat hub
EP3486496A1 (en) Fan for gas turbine engines having mid-span shroud
CA2928479A1 (en) Compressor system and airfoil assembly
EP3828385A2 (en) Gas turbine engine fan
US12188371B1 (en) Turbine rotor dovetail structure with splines
CN111878259A (zh) 具有改善的抗弯性的气体涡轮引擎
US12352175B2 (en) Annulus filler for a gas turbine engine
US20200256202A1 (en) Blade for a gas turbine engine
US20200063604A1 (en) Gas turbine engine

Legal Events

Date Code Title Description
A621 Written request for application examination

Free format text: JAPANESE INTERMEDIATE CODE: A621

Effective date: 20110401

A977 Report on retrieval

Free format text: JAPANESE INTERMEDIATE CODE: A971007

Effective date: 20121009

A131 Notification of reasons for refusal

Free format text: JAPANESE INTERMEDIATE CODE: A131

Effective date: 20121016

RD02 Notification of acceptance of power of attorney

Free format text: JAPANESE INTERMEDIATE CODE: A7422

Effective date: 20121119

A521 Request for written amendment filed

Free format text: JAPANESE INTERMEDIATE CODE: A523

Effective date: 20130115

A524 Written submission of copy of amendment under article 19 pct

Free format text: JAPANESE INTERMEDIATE CODE: A524

Effective date: 20130115

RD04 Notification of resignation of power of attorney

Free format text: JAPANESE INTERMEDIATE CODE: A7424

Effective date: 20130115

A131 Notification of reasons for refusal

Free format text: JAPANESE INTERMEDIATE CODE: A131

Effective date: 20130205

A601 Written request for extension of time

Free format text: JAPANESE INTERMEDIATE CODE: A601

Effective date: 20130501

A602 Written permission of extension of time

Free format text: JAPANESE INTERMEDIATE CODE: A602

Effective date: 20130508

A02 Decision of refusal

Free format text: JAPANESE INTERMEDIATE CODE: A02

Effective date: 20131105