JP4058000B2 - 脆化された先端部を有するファンブレード - Google Patents
脆化された先端部を有するファンブレード Download PDFInfo
- Publication number
- JP4058000B2 JP4058000B2 JP2003544306A JP2003544306A JP4058000B2 JP 4058000 B2 JP4058000 B2 JP 4058000B2 JP 2003544306 A JP2003544306 A JP 2003544306A JP 2003544306 A JP2003544306 A JP 2003544306A JP 4058000 B2 JP4058000 B2 JP 4058000B2
- Authority
- JP
- Japan
- Prior art keywords
- blade
- tip
- wall
- turbojet
- holding casing
- 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.)
- Expired - Lifetime
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
- 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
- F04D29/324—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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
-
- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
-
- 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
- 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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/30—Retaining components in desired mutual position
- F05B2260/301—Retaining bolts or nuts
- F05B2260/3011—Retaining bolts or nuts of the frangible or shear 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)
- Architecture (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Claims (6)
- シャフトによって駆動されるハブ(8)を有するファン(9)を備える航空機ターボジェットであり、前記シャフトが、挿置されたデカップリング装置を備えるベアリング支持部によってターボジェットの構造体に接続されている少なくとも1つのベアリングによって担持され、前記ハブが、複数のブレード(1)を周縁部で担持し、前記複数のブレード(1)が、前記ブレード(1)の先端部(2)と保持ケーシング(4)の内壁(5)との間の径方向クリアランスEを有して、保持ケーシング(4)の内側で移動し、前記内壁(5)が、回転するブレードの先端部によって削り取られるのに適した摩削可能な材料の層(6)で覆われる航空機ターボジェットであって、
前記ブレード(1)の先端部(2)が、前記デカップリング装置の動作のために必要なクリアランスJ>Eを得るように、ベアリングがデカップリングされることに至る不均衡の出現に続く衝撃の場合に、前記保持ケーシング(4)の内壁(5)によって分断されるのに適していることを特徴とする航空機ターボジェット。 - 前記ブレード(1)が、先端部(2)の近傍に、前記ブレード(1)の先端部(2)が前記保持ケーシング(4)の摩削可能な材料を削り取ることを可能にするのに十分強く、前記ブレード(1)の先端部(2)と前記保持ケーシング(4)の内壁(5)との間の激しい接触の出現の際に破損するのに十分弱い、それぞれの弱いゾーン(10)を有することを特徴とする、請求項1に記載のターボジェット。
- 前記弱いゾーン(10)が、前記ブレードを構成する基材内に各ブレードの1つの面に先端部(2)と平行に形成された溝(11)によって構成され、前記溝(11)が、前記面に空気力学的連続性を提供するように樹脂(13)で充填されていることを特徴とする、請求項2に記載のターボジェット。
- 前記溝(11)が、前記ブレード(1)の吸引側の面(12)に形成されることを特徴とする、請求項3に記載のターボジェット。
- 前記保持ケーシング(4)の内壁(5)が、不均衡の場合および摩削可能な材料が前記ブレードの先端部によって削り取られた後、前記ブレード(1)の先端部(2)の分断を容易にするように、実質上軸方向のリブ(17)を呈することを特徴とする、請求項1から4のいずれか一項に記載のターボジェット。
- 前記クリアランスEが、前記クリアランスJの3分の1よりも小さいことを特徴とする、請求項1から5のいずれか一項に記載のターボジェット。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0114690A FR2832191B1 (fr) | 2001-11-14 | 2001-11-14 | Aube de soufflante a sommet fragilise |
PCT/FR2002/003888 WO2003042504A1 (fr) | 2001-11-14 | 2002-11-14 | Aube de soufflante a sommet fragilise |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2005509775A JP2005509775A (ja) | 2005-04-14 |
JP4058000B2 true JP4058000B2 (ja) | 2008-03-05 |
Family
ID=8869364
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2003544306A Expired - Lifetime JP4058000B2 (ja) | 2001-11-14 | 2002-11-14 | 脆化された先端部を有するファンブレード |
Country Status (7)
Country | Link |
---|---|
US (1) | US7114912B2 (ja) |
EP (1) | EP1312762B1 (ja) |
JP (1) | JP4058000B2 (ja) |
CA (1) | CA2465837C (ja) |
DE (1) | DE60203870T2 (ja) |
FR (1) | FR2832191B1 (ja) |
WO (1) | WO2003042504A1 (ja) |
Families Citing this family (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2859002A1 (fr) * | 2003-08-18 | 2005-02-25 | Snecma Moteurs | Dispositif abradable sur carter de soufflante d'un moteur de turbine a gaz |
US7780410B2 (en) * | 2006-12-27 | 2010-08-24 | General Electric Company | Method and apparatus for gas turbine engines |
US7972109B2 (en) * | 2006-12-28 | 2011-07-05 | General Electric Company | Methods and apparatus for fabricating a fan assembly for use with turbine engines |
GB0813821D0 (en) * | 2008-07-29 | 2008-09-03 | Rolls Royce Plc | A fan casing for a gas turbine engine |
GB2469447B (en) * | 2009-04-15 | 2011-03-09 | Rolls Royce Plc | Gas turbine engine casing assembly |
GB201003634D0 (en) * | 2010-03-05 | 2010-04-21 | Rolls Royce Plc | Containment casing |
FR2987867B1 (fr) | 2012-03-09 | 2016-05-06 | Snecma | Aube de turbomachine comportant un insert de protection de la tete de l'aube |
GB201313594D0 (en) | 2013-07-30 | 2013-09-11 | Composite Technology & Applic Ltd | Fan Track Liner |
US11168702B2 (en) | 2017-08-10 | 2021-11-09 | Raytheon Technologies Corporation | Rotating airfoil with tip pocket |
US10533575B2 (en) | 2017-09-06 | 2020-01-14 | United Technologies Corporation | Fan blade tip with frangible strip |
US10731470B2 (en) * | 2017-11-08 | 2020-08-04 | General Electric Company | Frangible airfoil for a gas turbine engine |
US10815798B2 (en) | 2018-02-08 | 2020-10-27 | General Electric Company | Turbine engine blade with leading edge strip |
US11346232B2 (en) | 2018-04-23 | 2022-05-31 | Rolls-Royce Corporation | Turbine blade with abradable tip |
FR3081914B1 (fr) | 2018-06-05 | 2020-08-28 | Safran Aircraft Engines | Aube de soufflante en materiau composite avec grand jeu integre |
CN109229321A (zh) * | 2018-09-27 | 2019-01-18 | 广船国际有限公司 | 一种推进系统保护方法及螺旋桨 |
US10920607B2 (en) * | 2018-09-28 | 2021-02-16 | General Electric Company | Metallic compliant tip fan blade |
US11286807B2 (en) | 2018-09-28 | 2022-03-29 | General Electric Company | Metallic compliant tip fan blade |
US11111815B2 (en) * | 2018-10-16 | 2021-09-07 | General Electric Company | Frangible gas turbine engine airfoil with fusion cavities |
US10746045B2 (en) | 2018-10-16 | 2020-08-18 | General Electric Company | Frangible gas turbine engine airfoil including a retaining member |
US11149558B2 (en) | 2018-10-16 | 2021-10-19 | General Electric Company | Frangible gas turbine engine airfoil with layup change |
US10837286B2 (en) | 2018-10-16 | 2020-11-17 | General Electric Company | Frangible gas turbine engine airfoil with chord reduction |
US11434781B2 (en) | 2018-10-16 | 2022-09-06 | General Electric Company | Frangible gas turbine engine airfoil including an internal cavity |
US10760428B2 (en) | 2018-10-16 | 2020-09-01 | General Electric Company | Frangible gas turbine engine airfoil |
FR3103215B1 (fr) | 2019-11-20 | 2021-10-15 | Safran Aircraft Engines | Aube de soufflante rotative de turbomachine, soufflante et turbomachine munies de celle-ci |
FR3108663B1 (fr) | 2020-03-26 | 2022-08-12 | Safran Aircraft Engines | Aube de soufflante rotative de turbomachine, soufflante et turbomachine munies de celle-ci |
FR3108662B1 (fr) | 2020-03-26 | 2022-12-02 | Safran Aircraft Engines | Aube de soufflante rotative de turbomachine, soufflante et turbomachine munies de celle-ci |
US11867082B2 (en) | 2021-04-21 | 2024-01-09 | General Electric Company | Rotor blade with detachable tip |
US11674399B2 (en) | 2021-07-07 | 2023-06-13 | General Electric Company | Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy |
US11668317B2 (en) | 2021-07-09 | 2023-06-06 | General Electric Company | Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1828409A (en) * | 1929-01-11 | 1931-10-20 | Westinghouse Electric & Mfg Co | Reaction blading |
US3096930A (en) * | 1961-06-26 | 1963-07-09 | Meyerhoff Leonard | Propeller design |
US4547122A (en) * | 1983-10-14 | 1985-10-15 | Aeronautical Research Associates Of Princeton, Inc. | Method of containing fractured turbine blade fragments |
GB9317530D0 (en) * | 1993-08-21 | 1993-10-06 | Westland Helicopters | Fusible support devices for rotating shafts |
FR2749883B1 (fr) | 1996-06-13 | 1998-07-31 | Snecma | Procede et support de palier permettant de maintenir en fonctionnement un turbomoteur pour aeronef apres apparition d'un balourd accidentel sur un rotor |
JPH11278980A (ja) * | 1998-03-25 | 1999-10-12 | Murata Mfg Co Ltd | 単結晶育成方法 |
US6203273B1 (en) * | 1998-12-22 | 2001-03-20 | United Technologies Corporation | Rotary machine |
US6290455B1 (en) * | 1999-12-03 | 2001-09-18 | General Electric Company | Contoured hardwall containment |
-
2001
- 2001-11-14 FR FR0114690A patent/FR2832191B1/fr not_active Expired - Fee Related
-
2002
- 2002-11-14 CA CA002465837A patent/CA2465837C/fr not_active Expired - Lifetime
- 2002-11-14 DE DE60203870T patent/DE60203870T2/de not_active Expired - Lifetime
- 2002-11-14 US US10/494,367 patent/US7114912B2/en not_active Expired - Lifetime
- 2002-11-14 EP EP02292826A patent/EP1312762B1/fr not_active Expired - Lifetime
- 2002-11-14 JP JP2003544306A patent/JP4058000B2/ja not_active Expired - Lifetime
- 2002-11-14 WO PCT/FR2002/003888 patent/WO2003042504A1/fr active Application Filing
Also Published As
Publication number | Publication date |
---|---|
US20050106002A1 (en) | 2005-05-19 |
EP1312762B1 (fr) | 2005-04-27 |
EP1312762A1 (fr) | 2003-05-21 |
DE60203870T2 (de) | 2006-01-19 |
WO2003042504A1 (fr) | 2003-05-22 |
DE60203870D1 (de) | 2005-06-02 |
FR2832191B1 (fr) | 2004-10-08 |
FR2832191A1 (fr) | 2003-05-16 |
CA2465837A1 (fr) | 2003-05-22 |
CA2465837C (fr) | 2010-01-12 |
JP2005509775A (ja) | 2005-04-14 |
US7114912B2 (en) | 2006-10-03 |
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