JP2002508043A - 圧縮機翼とその用途 - Google Patents
圧縮機翼とその用途Info
- Publication number
- JP2002508043A JP2002508043A JP50356299A JP50356299A JP2002508043A JP 2002508043 A JP2002508043 A JP 2002508043A JP 50356299 A JP50356299 A JP 50356299A JP 50356299 A JP50356299 A JP 50356299A JP 2002508043 A JP2002508043 A JP 2002508043A
- Authority
- JP
- Japan
- Prior art keywords
- wing
- chord
- tangent
- compressor
- airfoil
- 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.)
- Granted
Links
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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/301—Cross-sectional characteristics
-
- 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
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
- Y10S416/02—Formulas of curves
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)
Abstract
Description
Claims (1)
- 【特許請求の範囲】 1. a) 前縁(3)、 b) 後縁(4)、および c) 前縁(3)から後縁(4)まで延びる直線区間である翼弦(5)を有する 翼形断面(2)を持ち、 d) この翼形断面(2)が、前縁(3)と後縁(4)とを結ぶ凸面状に湾曲し た翼の背(6)と、この翼の背(6)と反対側に位置する翼の腹(13) とを有している 圧縮機翼(1)において、 翼の背(6)が、翼弦(5)の長さ(L)の5%の場所で翼弦(5)を直角に横 切る基準直線(8)との翼の背側の交点(7)において、翼弦(5)の長さ(L )の半分より小さい曲率半径(P)を有していることを特徴とする圧縮機翼。 2.翼形断面(2)が最大直径(D)の円(10)を閉じ込めており、この最大 直径(D)が最大翼厚(D)を規定し、円(10)の中心を通る中心直線(11 )が、翼弦(5)を直角に横切り、翼弦(5)の長さ(L)の32%より小さい 、特に翼弦(5)の長さ(L)の15〜30%の円距離(K)だけ、前縁(3) から間隔を隔てられて位置していることを特徴とする請求項1記載の圧縮機翼。 3.翼の背(6)が、基準直線(8)との翼の背における交点(7)に、翼の背 側の接線(12)を、翼の腹(13)が基準直線(8)との翼の腹における交点 (15)に翼の腹側の接線(14)を有し、翼の背側の接線(12)および翼の 腹側の接線(14)が、互いに5〜20°の接線角度(T)を成していることを 特徴とする請求項1又は2記載の圧縮機翼。 4. a) 前縁(3)、 b) 後縁(4)、 c) 前縁(3)から後縁(4)まで延びる直線区間である翼弦(5)、および d) それぞれ前縁(3)と後縁(4)とを結ぶ凸面状に湾曲した翼の背(6) とこの翼の背(6)と反対側に位置する翼の腹(13)を有する翼形断面 (2)を有しており、 e) この翼形断面(2)が、最大直径(D)の円(10)を閉じ込め、この最 大直径(D)が最大翼厚(D)を規定し、円(10)の中心を通る中心直 線(11)が、翼弦(5)を直角に横切り、円距離(K)だけ前縁(3) から間隔を隔てられている 圧縮機翼(1)において、円距離(K)が、翼弦(5)の長さ(L)の32%よ り小さく、特に翼弦(5)の長さ(L)の15〜30%であることを特徴とする 圧縮機翼。 5.翼の背(6)に、翼弦(5)の長さ(L)の5%の箇所で翼弦(5)を直角 に横切る基準直線(8)との翼の背側の交点(7)で翼の背側の接線(12)が 接し、翼の腹(13)に、基準直線(8)との翼の腹側の交点(15)で翼の腹 側の接線(14)が接し、翼の背側の接線(12)および翼の腹側の接線(14 )が互いに5〜20°の接線角度(T)を成することを特徴とする請求項4記載 の圧縮機翼。 6. a) 前縁(3)、 b) 後縁(4)、 c) 前縁(3)から後縁(4)まで延びる直線区間である翼弦(5)、 d) 翼弦(5)の長さ(L)の5%の場所で翼弦(5)を直角に横切る基準直 線(8)との翼の背側の交点(7)に、翼の背側の接線(12)を有する翼 の背(6)、 e) 翼の背(6)と反対側に位置し基準直線(8)との翼の腹側の交点(1 5)に翼の腹側の接線(14)を有する翼の腹(13) を有する翼形断面(2)を持つ圧縮機翼(1)において、翼の背側の接線(12 )および翼の腹側の接線(14)が互いに5〜20°の接線角度(T)を成すこ とを特徴とする圧縮機翼。 7.翼形断面(2)が最大直径(D)の円(10)を閉じ込め、この最大直径( D)が最大翼厚(D)を規定し、その場合、最大翼厚(D)をD、翼弦(5)の 長さ(L)をL、接線角度(T)をTとしたとき、相対接線角度TRが、 TR=(T/100)・(L/D) で規定され、この相対接線角度TRが1〜2.5、特に1.2〜2であることを 特徴とする請求項6記載の圧縮機翼。 8.翼の背(6)が所定の流入速度(A)の気体(20)によって洗流される場 合、最高速度(24)が発生する気体(20)の境界層(23)が生ずる請求項 1ないし7のいずれか1つに記載の圧縮機翼(1)において、翼形断面(2)が 、マッハ数0.4より大きい流入速度(A)の値において境界層(23)に遷移 個所(26)が生ずるように選定され、この遷移個所(26)において、気体の 流れが層流から乱流に変化し、かつ気体が最高速度(24)の少なくとも90% の遷移速度(25)を有していることを特徴とする圧縮機翼。 9.翼の背(6)の表面が気体(20)で洗流される際、翼弦(5)に沿って前 縁(3)から後縁(4)まで気体(20)の境界層(23)が生ずる圧縮機翼( 1)において、翼形断面(2)が、境界層(23)における最大場所(27)で 最高速度(24)が発生し、その最大場所(27)を通り翼弦(5)を垂直に横 切る最大直線(26)が、前縁(3)から、翼弦(5)の長さ(L)の15%よ り小さい最大距離(S)だけ間隔を隔てられていることを特徴とする請求項1な いし7のいずれか1つに記載の圧縮機翼。 10.翼形断面(2)が、翼弦の長さ(L)の1%から99%までの範囲にわた り、最大翼厚(D)の少なくとも18%の翼厚(d)を有していることを特徴と する請求項2、4、7のいずれか1つに記載の圧縮機翼。 11.定置形ガスタービン(31)の圧縮機(30)に利用されることを特徴と する請求項1ないし10のいずれか1つに記載の圧縮機翼(1)の用途。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19726847.1 | 1997-06-24 | ||
DE19726847 | 1997-06-24 | ||
PCT/DE1998/001620 WO1998059175A1 (de) | 1997-06-24 | 1998-06-15 | Verdichterschaufel und verwendung einer verdichterschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2002508043A true JP2002508043A (ja) | 2002-03-12 |
JP4087461B2 JP4087461B2 (ja) | 2008-05-21 |
Family
ID=7833531
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP50356299A Expired - Lifetime JP4087461B2 (ja) | 1997-06-24 | 1998-06-15 | 圧縮機翼とその用途 |
Country Status (6)
Country | Link |
---|---|
US (1) | US6264429B1 (ja) |
EP (2) | EP0991866B2 (ja) |
JP (1) | JP4087461B2 (ja) |
DE (3) | DE29825097U1 (ja) |
RU (1) | RU2191930C2 (ja) |
WO (1) | WO1998059175A1 (ja) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2010151137A (ja) * | 1998-07-20 | 2010-07-08 | Minebea Co Ltd | インペラ用の羽根、該羽根を用いたインペラ、該インペラを用いた軸流ファン |
WO2018216255A1 (ja) * | 2017-05-24 | 2018-11-29 | 株式会社Ihi | ファン及び圧縮機の翼 |
WO2020129192A1 (ja) * | 2018-12-19 | 2020-06-25 | 三菱重工エンジン&ターボチャージャ株式会社 | ノズルベーン |
Families Citing this family (44)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4545862B2 (ja) * | 1999-12-08 | 2010-09-15 | 本田技研工業株式会社 | 軸流型圧縮機の静翼および静翼列 |
US6457938B1 (en) * | 2001-03-30 | 2002-10-01 | General Electric Company | Wide angle guide vane |
US6709232B1 (en) * | 2002-09-05 | 2004-03-23 | Honeywell International Inc. | Cambered vane for use in turbochargers |
DE10352253A1 (de) | 2003-11-08 | 2005-06-09 | Alstom Technology Ltd | Verdichterlaufschaufel |
US7878759B2 (en) * | 2003-12-20 | 2011-02-01 | Rolls-Royce Deutschland Ltd & Co Kg | Mitigation of unsteady peak fan blade and disc stresses in turbofan engines through the use of flow control devices to stabilize boundary layer characteristics |
DE502004002003D1 (de) * | 2004-03-25 | 2006-12-28 | Rolls Royce Deutschland | Verdichter für ein Flugzeugtriebwerk |
DE502004010281D1 (de) * | 2004-06-02 | 2009-12-03 | Rolls Royce Deutschland | Verdichterschaufel, insbesondere für den Fan von Flugzeugtriebwerken |
US20090104023A1 (en) * | 2005-07-19 | 2009-04-23 | Frederic Favray | Variable Nozzle Turbocharger |
US8313300B2 (en) * | 2007-06-14 | 2012-11-20 | Christianson Systems, Inc. | Rotor for centrifugal compressor |
JP2009008014A (ja) * | 2007-06-28 | 2009-01-15 | Mitsubishi Electric Corp | 軸流ファン |
EP2299124A1 (de) | 2009-09-04 | 2011-03-23 | Siemens Aktiengesellschaft | Verdichterlaufschaufel für einen Axialverdichter |
US9309769B2 (en) * | 2010-12-28 | 2016-04-12 | Rolls-Royce Corporation | Gas turbine engine airfoil shaped component |
DE112013004639T5 (de) * | 2012-09-21 | 2015-06-25 | Mitsubishi Hitachi Power Systems, Ltd. | Verfahren zum Verschweißen von erosionsbeständigem Metallmaterial und Turbinenschaufel |
BR112015027090A2 (pt) * | 2013-05-14 | 2017-07-25 | Gen Electric | método de formação de uma pá-guia de saída de tecido compósito e pá-guia de saída |
GB2523133B (en) * | 2014-02-13 | 2016-06-01 | X-Wind Power Ltd | Vertical axis wind turbine rotor and aerofoil |
EP2927427A1 (de) * | 2014-04-04 | 2015-10-07 | MTU Aero Engines GmbH | Gasturbinenschaufel |
JP6320134B2 (ja) * | 2014-04-07 | 2018-05-09 | 三菱日立パワーシステムズ株式会社 | 動翼、エロージョンシールドの形成方法及び動翼製造方法 |
US9638138B2 (en) | 2015-03-09 | 2017-05-02 | Caterpillar Inc. | Turbocharger and method |
US9739238B2 (en) | 2015-03-09 | 2017-08-22 | Caterpillar Inc. | Turbocharger and method |
US10006341B2 (en) | 2015-03-09 | 2018-06-26 | Caterpillar Inc. | Compressor assembly having a diffuser ring with tabs |
US9822700B2 (en) | 2015-03-09 | 2017-11-21 | Caterpillar Inc. | Turbocharger with oil containment arrangement |
US9752536B2 (en) | 2015-03-09 | 2017-09-05 | Caterpillar Inc. | Turbocharger and method |
US9890788B2 (en) | 2015-03-09 | 2018-02-13 | Caterpillar Inc. | Turbocharger and method |
US10066639B2 (en) | 2015-03-09 | 2018-09-04 | Caterpillar Inc. | Compressor assembly having a vaneless space |
US9915172B2 (en) | 2015-03-09 | 2018-03-13 | Caterpillar Inc. | Turbocharger with bearing piloted compressor wheel |
US9903225B2 (en) | 2015-03-09 | 2018-02-27 | Caterpillar Inc. | Turbocharger with low carbon steel shaft |
US9777747B2 (en) | 2015-03-09 | 2017-10-03 | Caterpillar Inc. | Turbocharger with dual-use mounting holes |
US9879594B2 (en) | 2015-03-09 | 2018-01-30 | Caterpillar Inc. | Turbocharger turbine nozzle and containment structure |
US9732633B2 (en) | 2015-03-09 | 2017-08-15 | Caterpillar Inc. | Turbocharger turbine assembly |
US9650913B2 (en) | 2015-03-09 | 2017-05-16 | Caterpillar Inc. | Turbocharger turbine containment structure |
US9810238B2 (en) | 2015-03-09 | 2017-11-07 | Caterpillar Inc. | Turbocharger with turbine shroud |
US9683520B2 (en) | 2015-03-09 | 2017-06-20 | Caterpillar Inc. | Turbocharger and method |
CN105257597B (zh) * | 2015-11-12 | 2018-04-20 | 珠海格力电器股份有限公司 | 轴流风机及其轴流风叶 |
CN105351248B (zh) * | 2015-12-17 | 2017-12-12 | 新昌县三新空调风机有限公司 | 一种风扇用高性能翼型 |
EP3231996B1 (en) * | 2016-04-11 | 2020-06-17 | Rolls-Royce plc | A blade for an axial flow machine |
DE102016206022A1 (de) | 2016-04-12 | 2017-10-12 | Siemens Aktiengesellschaft | Dichtung für Strömungsmaschinen |
CN106089801B (zh) * | 2016-08-11 | 2018-08-24 | 中国航空工业集团公司沈阳发动机设计研究所 | 一种压气机叶片造型方法 |
US10801325B2 (en) * | 2017-03-27 | 2020-10-13 | Raytheon Technologies Corporation | Turbine blade with tip vortex control and tip shelf |
US10859094B2 (en) | 2018-11-21 | 2020-12-08 | 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 |
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 |
FR3108141B1 (fr) * | 2020-03-10 | 2022-08-12 | Safran Aircraft Engines | Aube de compresseur de turbomachine, compresseur et turbomachine munis de celle-ci |
DE102021123281A1 (de) * | 2021-09-08 | 2023-03-09 | MTU Aero Engines AG | Schaufelblatt für einen Verdichter einer Strömungsmaschine |
US11873730B1 (en) | 2022-11-28 | 2024-01-16 | Rtx Corporation | Gas turbine engine airfoil with extended laminar flow |
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GB511645A (en) * | 1937-07-07 | 1939-08-22 | Talalmanykifejleszto Es Erteke | Improvements in or relating to turbo-compressors or pumps |
GB580806A (en) * | 1941-05-21 | 1946-09-20 | Alan Arnold Griffith | Improvements in compressor, turbine and like blades |
GB750305A (en) * | 1953-02-05 | 1956-06-13 | Rolls Royce | Improvements in axial-flow compressor, turbine and like blades |
DE1050016B (de) * | 1953-05-27 | 1959-02-05 | Power Jets Res & Dev Ltd | Beschaufelung von mehrstufigen Axialverdichtern |
US4431376A (en) * | 1980-10-27 | 1984-02-14 | United Technologies Corporation | Airfoil shape for arrays of airfoils |
CA1205709A (en) * | 1981-08-31 | 1986-06-10 | Elias H. Razinsky | Airfoil for high efficiency/high lift fan |
FR2590229B1 (fr) * | 1985-11-19 | 1988-01-29 | Onera (Off Nat Aerospatiale) | Perfectionnements apportes aux helices aeriennes en ce qui concerne le profil de leurs pales |
US5088892A (en) * | 1990-02-07 | 1992-02-18 | United Technologies Corporation | Bowed airfoil for the compression section of a rotary machine |
US5397215A (en) * | 1993-06-14 | 1995-03-14 | United Technologies Corporation | Flow directing assembly for the compression section of a rotary machine |
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1998
- 1998-06-15 WO PCT/DE1998/001620 patent/WO1998059175A1/de active IP Right Grant
- 1998-06-15 DE DE29825097U patent/DE29825097U1/de not_active Expired - Lifetime
- 1998-06-15 EP EP98936166A patent/EP0991866B2/de not_active Expired - Lifetime
- 1998-06-15 EP EP03010895A patent/EP1338799B2/de not_active Expired - Lifetime
- 1998-06-15 JP JP50356299A patent/JP4087461B2/ja not_active Expired - Lifetime
- 1998-06-15 DE DE59811402T patent/DE59811402D1/de not_active Expired - Lifetime
- 1998-06-15 RU RU2000101807/06A patent/RU2191930C2/ru not_active IP Right Cessation
- 1998-06-15 DE DE59809352T patent/DE59809352D1/de not_active Expired - Lifetime
-
1999
- 1999-12-27 US US09/472,225 patent/US6264429B1/en not_active Expired - Lifetime
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2010151137A (ja) * | 1998-07-20 | 2010-07-08 | Minebea Co Ltd | インペラ用の羽根、該羽根を用いたインペラ、該インペラを用いた軸流ファン |
WO2018216255A1 (ja) * | 2017-05-24 | 2018-11-29 | 株式会社Ihi | ファン及び圧縮機の翼 |
US11125085B2 (en) | 2017-05-24 | 2021-09-21 | Ihi Corporation | Blade of fan or compressor |
WO2020129192A1 (ja) * | 2018-12-19 | 2020-06-25 | 三菱重工エンジン&ターボチャージャ株式会社 | ノズルベーン |
US11428154B2 (en) | 2018-12-19 | 2022-08-30 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Nozzle vane |
Also Published As
Publication number | Publication date |
---|---|
EP0991866B2 (de) | 2011-06-01 |
US6264429B1 (en) | 2001-07-24 |
EP1338799B2 (de) | 2011-01-19 |
DE59811402D1 (de) | 2004-06-17 |
WO1998059175A1 (de) | 1998-12-30 |
JP4087461B2 (ja) | 2008-05-21 |
RU2191930C2 (ru) | 2002-10-27 |
EP1338799A1 (de) | 2003-08-27 |
DE59809352D1 (de) | 2003-09-25 |
EP1338799B1 (de) | 2004-05-12 |
EP0991866B1 (de) | 2003-08-20 |
EP0991866A1 (de) | 2000-04-12 |
DE29825097U1 (de) | 2005-03-24 |
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