JP4705333B2 - ターボジェット用後退翼 - Google Patents
ターボジェット用後退翼 Download PDFInfo
- Publication number
- JP4705333B2 JP4705333B2 JP2004035958A JP2004035958A JP4705333B2 JP 4705333 B2 JP4705333 B2 JP 4705333B2 JP 2004035958 A JP2004035958 A JP 2004035958A JP 2004035958 A JP2004035958 A JP 2004035958A JP 4705333 B2 JP4705333 B2 JP 4705333B2
- Authority
- JP
- Japan
- Prior art keywords
- wing
- turbojet
- inclination angle
- respect
- radial axis
- 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
- 230000005484 gravity Effects 0.000 claims description 8
- 210000001015 abdomen Anatomy 0.000 description 6
- 230000008901 benefit Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
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
- 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
-
- 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
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
-
- 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)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
4 ディスクまたはハブ
6 根部
8 プラットホーム
10 内壁
12 空気流
14 壁
15 重心線
16 基部
18 先端部
20 前縁
22 後縁
24 下部
26 中間部
28 上部
30 下限
32 上限
33 前縁線
Claims (9)
- 縦方向の気体流の影響を受けるターボジェットの回転翼であって、前記翼(2)は、複数の翼部であって前記翼の基部(16)および先端部(18)の間で該翼部の重心線(15)に沿って延設される翼部を含み、前記翼は、前記ターボジェットの縦軸(X−X)に関して前方に位置する前縁部(20)および後方に位置する後縁部(22)を有しており、前記翼は、前記ターボジェットの放射軸(Z−Z)に沿って下部(24)、中間部(26)および上部(28)を有し、前記下部は前記翼の基部(16)から前記中間部の下限(30)まで続き、前記上部は前記中間部の上限(32)から前記翼の先端部(18)まで続き、
前記下部(24)が前縁線(33)において前方への縦傾斜角αを成し、前記中間部(26)が前記前縁線において後方への縦傾斜角βを成し、前記上部(28)は、前記前縁線において後方への縦傾斜角γを成すと共に、前記翼部の前記重心線(15)において前記翼の回転方向とは逆方向の接線傾斜角δを成しており、前記縦傾斜角α、β及びγが−α<β<γの関係を満たし、前記接線傾斜角δは前記放射軸(Z−Z)に対して接線方向への傾斜角であり、前記上部(28)が更に、前記前縁線(33)が前方への縦傾斜角を有する前記翼の先端部(18)へ放射状に延びる先端区域を含み、
前記翼の前記中間部(26)の下限(30)が、前記基部(16)および前記先端部(18)の間の前記翼の半径高さの40%から75%の範囲内にあることを特徴とする、前記翼。 - 前記下部(24)の前記前縁線の縦傾斜角αは、前記ターボジェットの前記放射軸(Z−Z)に対して−5°から15°の範囲内であることを特徴とする、請求項1に記載の翼。
- 中間部(26)の前縁線の後方への縦傾斜角βは、前記ターボジェットの前記放射軸(Z−Z)に対して5°から20°の範囲内であることを特徴とする、請求項1または2に記載の翼。
- 前記上部(28)の前縁線の後方への縦傾斜角γは、前記ターボジェットの前記放射軸(Z−Z)に対して20°から50°の範囲内であり、前記上部(28)の翼部の重心線(15)の接線傾斜角δは、前記ターボジェットの前記放射軸(Z−Z)に対して20°から50°の範囲内であることを特徴とする、請求項1から3のいずれか一項に記載の翼。
- 前記下部(24)は更に、前記ターボジェットの放射軸(Z−Z)に対して−5°から15°の範囲内にある、前記翼部の中心線(15)の接線傾斜角φを有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翼。
- 前記中間部(26)は更に、前記ターボジェットの前記放射軸(Z−Z)に対して−5°から15°の範囲内にある、前記翼部の重心線(15)の接線傾斜角εを有することを特徴とする、請求項1から5のいずれか一項に記載の翼。
- 気体の流れを通過させる回転式のターボジェットの機械であって、請求項1から6のいずれか一項に記載の複数の翼を含むことを特徴とする、機械。
- ターボジェットのファンを構成することを特徴とする、請求項7に記載の機械。
- ターボジェットのコンプレッサーを構成することを特徴とする、請求項7に記載の機械。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0302380A FR2851798B1 (fr) | 2003-02-27 | 2003-02-27 | Aube en fleche de turboreacteur |
FR0302380 | 2003-02-27 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2008243691A Division JP2008303889A (ja) | 2003-02-27 | 2008-09-24 | ターボジェット用後退翼 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2004257380A JP2004257380A (ja) | 2004-09-16 |
JP4705333B2 true JP4705333B2 (ja) | 2011-06-22 |
Family
ID=32749736
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2004035958A Expired - Lifetime JP4705333B2 (ja) | 2003-02-27 | 2004-02-13 | ターボジェット用後退翼 |
JP2008243691A Withdrawn JP2008303889A (ja) | 2003-02-27 | 2008-09-24 | ターボジェット用後退翼 |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2008243691A Withdrawn JP2008303889A (ja) | 2003-02-27 | 2008-09-24 | ターボジェット用後退翼 |
Country Status (9)
Country | Link |
---|---|
US (1) | US7108486B2 (ja) |
EP (1) | EP1452741B1 (ja) |
JP (2) | JP4705333B2 (ja) |
CA (1) | CA2458417C (ja) |
DE (1) | DE602004005906T2 (ja) |
ES (1) | ES2283954T3 (ja) |
FR (1) | FR2851798B1 (ja) |
RU (1) | RU2336421C2 (ja) |
UA (1) | UA82649C2 (ja) |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102004011607B4 (de) * | 2004-03-10 | 2016-11-24 | MTU Aero Engines AG | Verdichter einer Gasturbine sowie Gasturbine |
DE102005042115A1 (de) * | 2005-09-05 | 2007-03-08 | Rolls-Royce Deutschland Ltd & Co Kg | Schaufel einer Strömungsarbeitsmaschine mit blockweise definierter Profilskelettlinie |
JP4863162B2 (ja) * | 2006-05-26 | 2012-01-25 | 株式会社Ihi | ターボファンエンジンのファン動翼 |
FR2908152B1 (fr) * | 2006-11-08 | 2009-02-06 | Snecma Sa | Aube en fleche de turbomachine |
US7806653B2 (en) * | 2006-12-22 | 2010-10-05 | General Electric Company | Gas turbine engines including multi-curve stator vanes and methods of assembling the same |
DE102007020476A1 (de) * | 2007-04-27 | 2008-11-06 | Rolls-Royce Deutschland Ltd & Co Kg | Vorderkantenverlauf für Turbomaschinenkomponenten |
JP4923073B2 (ja) * | 2009-02-25 | 2012-04-25 | 株式会社日立製作所 | 遷音速翼 |
FR2967202B1 (fr) * | 2010-11-10 | 2013-01-11 | Snecma | Procede d'optimisation du profil d'une aube en materiau composite pour roue mobile de turbomachine |
FR2969230B1 (fr) | 2010-12-15 | 2014-11-21 | Snecma | Aube de compresseur a loi d'empilage amelioree |
US8684698B2 (en) * | 2011-03-25 | 2014-04-01 | General Electric Company | Compressor airfoil with tip dihedral |
FR2986285B1 (fr) * | 2012-01-30 | 2014-02-14 | Snecma | Aube pour soufflante de turboreacteur |
US20130202443A1 (en) * | 2012-02-07 | 2013-08-08 | Applied Thermalfluid Analysis Center, Ltd. | Axial flow device |
FR2989107B1 (fr) * | 2012-04-04 | 2017-03-31 | Snecma | Aube de rotor de turbomachine |
US9121285B2 (en) * | 2012-05-24 | 2015-09-01 | General Electric Company | Turbine and method for reducing shock losses in a turbine |
FR2991373B1 (fr) * | 2012-05-31 | 2014-06-20 | Snecma | Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied |
FR2993323B1 (fr) * | 2012-07-12 | 2014-08-15 | Snecma | Aube de turbomachine ayant un profil configure de maniere a obtenir des proprietes aerodynamiques et mecaniques ameliorees |
JP5705945B1 (ja) * | 2013-10-28 | 2015-04-22 | ミネベア株式会社 | 遠心式ファン |
US9845684B2 (en) * | 2014-11-25 | 2017-12-19 | Pratt & Whitney Canada Corp. | Airfoil with stepped spanwise thickness distribution |
EP3879072B1 (en) | 2018-11-05 | 2024-07-17 | IHI Corporation | Rotor blade of axial-flow fluid machine |
DE102019107839A1 (de) * | 2019-03-27 | 2020-10-01 | Rolls-Royce Deutschland Ltd & Co Kg | Rotor-Schaufelblatt einer Strömungsmaschine |
IT202100032258A1 (it) * | 2021-12-22 | 2023-06-22 | Cofimco Srl | Pala di ventilatore assiale industriale |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3989406A (en) * | 1974-11-26 | 1976-11-02 | Bolt Beranek And Newman, Inc. | Method of and apparatus for preventing leading edge shocks and shock-related noise in transonic and supersonic rotor blades and the like |
US5642985A (en) * | 1995-11-17 | 1997-07-01 | United Technologies Corporation | Swept turbomachinery blade |
GB9607316D0 (en) * | 1996-04-09 | 1996-06-12 | Rolls Royce Plc | Swept fan blade |
US6071077A (en) * | 1996-04-09 | 2000-06-06 | Rolls-Royce Plc | Swept fan blade |
DE19812624A1 (de) * | 1998-03-23 | 1999-09-30 | Bmw Rolls Royce Gmbh | Rotor-Schaufelblatt einer Axialströmungsmaschine |
US6331100B1 (en) * | 1999-12-06 | 2001-12-18 | General Electric Company | Doubled bowed compressor airfoil |
US6338609B1 (en) * | 2000-02-18 | 2002-01-15 | General Electric Company | Convex compressor casing |
US6524070B1 (en) * | 2000-08-21 | 2003-02-25 | General Electric Company | Method and apparatus for reducing rotor assembly circumferential rim stress |
-
2003
- 2003-02-27 FR FR0302380A patent/FR2851798B1/fr not_active Expired - Fee Related
-
2004
- 2004-02-04 EP EP04290292A patent/EP1452741B1/fr not_active Expired - Lifetime
- 2004-02-04 DE DE602004005906T patent/DE602004005906T2/de not_active Expired - Lifetime
- 2004-02-04 ES ES04290292T patent/ES2283954T3/es not_active Expired - Lifetime
- 2004-02-12 US US10/776,274 patent/US7108486B2/en not_active Expired - Lifetime
- 2004-02-13 JP JP2004035958A patent/JP4705333B2/ja not_active Expired - Lifetime
- 2004-02-26 RU RU2004105544/06A patent/RU2336421C2/ru active
- 2004-02-27 UA UA2004021455A patent/UA82649C2/uk unknown
- 2004-02-27 CA CA2458417A patent/CA2458417C/fr not_active Expired - Lifetime
-
2008
- 2008-09-24 JP JP2008243691A patent/JP2008303889A/ja not_active Withdrawn
Also Published As
Publication number | Publication date |
---|---|
US20040170502A1 (en) | 2004-09-02 |
JP2008303889A (ja) | 2008-12-18 |
US7108486B2 (en) | 2006-09-19 |
JP2004257380A (ja) | 2004-09-16 |
ES2283954T3 (es) | 2007-11-01 |
RU2004105544A (ru) | 2005-08-10 |
RU2336421C2 (ru) | 2008-10-20 |
DE602004005906D1 (de) | 2007-05-31 |
UA82649C2 (uk) | 2008-05-12 |
CA2458417C (fr) | 2011-09-20 |
FR2851798A1 (fr) | 2004-09-03 |
CA2458417A1 (fr) | 2004-08-27 |
EP1452741B1 (fr) | 2007-04-18 |
DE602004005906T2 (de) | 2008-01-17 |
EP1452741A1 (fr) | 2004-09-01 |
FR2851798B1 (fr) | 2005-04-29 |
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