JP2013137020A - 騒音を低減するための先端形状を含むエーロフォイルおよびそのエーロフォイルを作製するための方法 - Google Patents
騒音を低減するための先端形状を含むエーロフォイルおよびそのエーロフォイルを作製するための方法 Download PDFInfo
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
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- F04D29/26—Rotors specially for elastic fluids
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- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
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- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
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- B64D2027/005—Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
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- F01D1/24—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like
- F01D1/26—Non-positive-displacement machines or engines, e.g. steam turbines characterised by counter-rotating rotors subjected to same working fluid stream without intermediate stator blades or the like traversed by the working-fluid substantially axially
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- 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
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
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- 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
- F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
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- 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
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/712—Shape curved concave
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Abstract
【解決手段】エーロフォイル、ファン組立体およびアンダクテッド逆回転ファンエンジンが、前縁および後縁で一体に結合され、その間に延在する負圧面および正圧面を備える少なくとも1つのエーロフォイルを作製するステップを含む。エーロフォイルは、翼弦長を有する複数の翼弦区域を含む。エーロフォイルは、前縁から先端部分で少なくとも翼弦長の部分に沿って延在する下降斜面を画定する先端形状を含む。先端形状は、エーロフォイルの先端部分近傍の非常に不安定な圧力を低減するように構成される。
【選択図】図1
Description
12 エンジン組立体
14 翼
16 翼
18 長手方向中心線軸
20 上流方向
22 下流方向
24 外殻/外筒
26 コアエンジン
28 圧縮機
30 燃焼器
32 高圧タービン
34 34A/34B駆動軸
36 ディフューザ区域
38 出力タービン
40 一次タービンブレード列
42 二次タービンブレード列
44 前部ファン区域
46 一次ファンブレード列
48 内側逆回転軸
50 二次ファンブレード列
52 外側駆動軸
54 エーロフォイル
56 パイロン
60 従来技術のファンブレード
62 エーロフォイル部分
64 先端部分
66 翼根部
68 傾斜線
70 ファンブレード
72 エーロフォイル部分
74 プラットフォーム
76 翼根部
78 一体型ダブテール
80 一次曲面側壁
81 正圧面
82 二次曲面側壁
83 負圧面
84 前縁
86 後縁
88 先端部分
90 キャンバーおよび厚さ変化開始線
92 翼弦距離
94 翼弦長
96 翼弦区域
98 先端切り口
100 先端切り口形状
102 一次部分
104 一次斜面
106 二次部分
108 二次斜面
Claims (10)
- 先端部分(88)が翼根部(76)から半径方向外側に延在するように構成される翼根部(76)および先端部分(88)と、
前縁(84)、および前記前縁(84)から翼弦方向下流に離隔された後縁(86)で一体に結合される負圧面(83)および正圧面(81)と、
翼弦長(94)を有し、翼弦方向にエーロフォイル(72)の前記前縁(84)と前記後縁(86)との間に延在し、翼幅方向に前記翼根部(76)と前記先端部分(88)との間のエーロフォイル(72)の長さに沿って離隔された複数の翼弦区域(96)と、
前記前縁(84)から前記先端部分(88)で少なくとも前記翼弦長(94)の部分に沿って延在する下降斜面を画定する先端形状(100)と
を備え、前記先端形状(100)が、エーロフォイル(72)の前記先端部分(100)近傍の非常に不安定な圧力を低減するように構成される、エーロフォイル(72)。 - 前記前縁(84)から前記先端部分(88)で前記翼弦長(94)の少なくとも部分に沿って延在する一次下降斜面(104)を有する一次部分(102)、および前記一次部分(102)から前記後縁(86)に向かって前記翼弦長(94)の少なくとも部分に沿って延在する下降斜面(108)を有する少なくとも1つの追加部分(106)を画定する先端形状(100)をさらに含み、前記一次下降斜面(104)が前記少なくとも1つの追加部分(106)の前記下降斜面(108)よりも大きい、請求項1記載のエーロフォイル。
- 一次下降斜面(104)を有する前記一次部分(102)が前記前縁(84)から前記先端部分(88)で、翼弦方向に前記エーロフォイル(62)の前記翼弦長(94)の少なくとも25%延在する、請求項2記載のエーロフォイル。
- 一次下降斜面(104)を有する前記一次部分(102)が前記前縁(84)から前記先端部分(88)で、翼弦方向に前記エーロフォイル(62)の翼弦長(94)の25%未満延在する、請求項2記載のエーロフォイル。
- 前記前縁(84)から前記先端部分(88)で前記翼弦長(94)の少なくとも部分に沿って延在する一次下降斜面(104)を有する一次部分(102)、および前記一次部分(102)から前記後縁(86)まで前記翼弦長(94)の少なくとも部分に沿って延在する下降斜面(108)を有する二次部分(106)を画定する先端形状(100)をさらに含み、前記一次下降斜面(104)が前記二次下降斜面(108)よりも大きい、請求項2記載のエーロフォイル。
- 前記エーロフォイル(62)が、ダクテッドファンブレードまたはアンダクテッドファンブレード、ロータブレード、風力タービンブレード、あるいは航空機空気力学的表面の1つである、請求項1記載のエーロフォイル。
- ディスク(44)と、
前記ディスク(44)に結合された複数のファンブレード(46,50)と
を備えるファン組立体であって、前記複数のファンブレード(46,50)のそれぞれが、
翼根部(76)、先端部分(88)、ならびに前縁(84)で、および前記前縁(84)から翼弦方向下流に離隔された後縁(86)で一体に結合される負圧面(83)および正圧面(81)を備えるエーロフォイル(72)と、
翼弦長(94)を有し、翼弦方向に前記エーロフォイル(72)の前記前縁(84)と前記後縁(86)との間に延在し、翼幅方向に前記翼根部(76)と前記先端部分(88)との間の前記エーロフォイル(72)の長さに沿って離隔された複数の翼弦区域(96)と、
前記前縁(84)から前記先端部分(88)で少なくとも前記翼弦長(94)の部分に沿って延在する下降斜面(104)を画定する先端形状(100)と
を備え、前記先端形状(100)が、前記エーロフォイル(72)の前記先端部分(99)近傍の非常に不安定な圧力を低減するように構成される、ファン組立体。 - 前記エーロフォイル(72)が、突風/先端渦相互作用に関連する騒音を低減するよう促進するように構成される、請求項7記載のファン組立体。
- 一次ファンブレード列(46)および前記一次ファンブレード列(46)から軸方向後方に離隔された二次ファンブレード列(50)を含むアンダクテッドファン区域(44)を備えるアンダクテッド逆回転ファンエンジンであって、前記二次ファンブレード列(50)が複数のエーロフォイル(72)を含み、各エーロフォイルが、
先端部分(88)が翼根部(76)から半径方向外側に延在するように構成される翼根部(76)および先端部分(88)と、
前縁(84)、および前記前縁(84)から翼弦方向下流に離隔された後縁(86)で一体に結合される負圧面(83)および正圧面(81)と、
翼弦長(94)を有し、翼弦方向に前記エーロフォイル(72)の前記前縁(84)と前記後縁(86)との間に延在し、翼幅方向に前記翼根部(76)と前記先端部分(88)との間の前記エーロフォイル(72)の長さに沿って離隔された複数の翼弦区域(96)と、
前記前縁(84)から前記先端部分(88)で少なくとも前記翼弦長(94)の部分に沿って延在する下降斜面(104)を画定する先端形状(100)と
を備え、前記先端形状(100)が、前記エーロフォイル(72)の前記先端部分(88)近傍の非常に不安定な圧力を低減するように構成される、アンダクテッド逆回転ファンエンジン。 - エーロフォイルを作製する方法であって、
翼根部(76)、先端部分(88)、ならびに前縁(84)、および前記前縁(84)から翼弦方向下流に離隔された後縁(86)で一体に結合される負圧面(83)および正圧面(81)を備える少なくとも1つのエーロフォイル(72)を作製するステップを含み、
前記エーロフォイル(72)が、翼弦長(94)を有し、翼弦方向に前記エーロフォイル(72)の前記前縁(84)と前記後縁(86)との間に延在し、翼幅方向に前記翼根部(76)と前記先端部分(88)との間の前記エーロフォイル(72)の長さに沿って離隔される複数の翼弦区域(96)を含み、前記先端部分(88)が、
前記前縁(84)から前記先端部分(88)で少なくとも前記翼弦長(94)の部分に沿って延在する下降斜面(104)を画定する先端形状(100)を備え、前記先端形状(100)が、前記エーロフォイル(72)の前記先端部分(88)近傍の非常に不安定な圧力を低減するように構成される方法。
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US13/330,766 US9102397B2 (en) | 2011-12-20 | 2011-12-20 | Airfoils including tip profile for noise reduction and method for fabricating same |
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JP2016525756A (ja) * | 2013-07-29 | 2016-08-25 | スネクマ | 非流線型のプロペラブレードをモデル化する方法 |
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Also Published As
Publication number | Publication date |
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CN103174465A (zh) | 2013-06-26 |
EP2607231A3 (en) | 2017-04-12 |
US20130156583A1 (en) | 2013-06-20 |
US9102397B2 (en) | 2015-08-11 |
JP6103911B2 (ja) | 2017-03-29 |
CN103174465B (zh) | 2017-04-26 |
CA2798211A1 (en) | 2013-06-20 |
BR102012032435A2 (pt) | 2015-10-20 |
EP2607231A2 (en) | 2013-06-26 |
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