JP5489727B2 - 航空エンジン - Google Patents
航空エンジン Download PDFInfo
- Publication number
- JP5489727B2 JP5489727B2 JP2009548734A JP2009548734A JP5489727B2 JP 5489727 B2 JP5489727 B2 JP 5489727B2 JP 2009548734 A JP2009548734 A JP 2009548734A JP 2009548734 A JP2009548734 A JP 2009548734A JP 5489727 B2 JP5489727 B2 JP 5489727B2
- Authority
- JP
- Japan
- Prior art keywords
- propeller
- blades
- blade
- tip speed
- phase
- 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 - Fee Related
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
- B64C11/48—Units of two or more coaxial propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
- B64C11/50—Phase synchronisation between multiple propellers
-
- 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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- 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
-
- 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
- F05D2220/324—Application in turbines in gas turbines to drive unshrouded, 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
- F05D2220/325—Application in turbines in gas turbines to drive unshrouded, high 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
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
-
- 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
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
-
- 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)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
- Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
- Wind Motors (AREA)
Description
プロペラのうちの少なくとも一方のプロペラの先端速度を、離陸段階、上昇段階、又は着陸進入段階のうちの少なくともひとつの段階おいて、巡行中の先端速度よりも大きくする工程を含む、ことを特徴とする方法が提供される。
有利には、離陸段階、上昇段階、又は着陸進入段階の少なくとも一つの段階でのプロペラの先端速度は、巡行段階の先端速度よりも少なくとも10%高い。
好ましくは、プロペラは可変ピッチブレードを含み、前記方法は、ブレードを、巡行時のピッチから着陸進入時のピッチまで閉鎖方向に移動する工程を含む。
本発明の別の特徴では、前後のプロペラを持つ二重反転プロペラエンジンであって、前プロペラは少なくとも9枚のブレードを有し(Nf=9)、直径がDfであり、後プロペラの最大ブレード数Nrは、Nfから少なくとも3を減じた数であり、前後のプロペラは軸線方向隙間xによって離間されている、二重反転プロペラエンジンにおいて、
比x/Dfは0.15乃至0.4である、二重反転プロペラエンジンが提供される。
別の態様では、前プロペラは12枚のブレードを有し、後プロペラは7枚のブレードを有する。
有利には、前プロペラの直径は後プロペラよりも大きい。好ましくは、後プロペラの直径は、前プロペラよりも0.05Df乃至0.2Df小さい。
巡行段階にエンジンがほぼ一定のプロペラ先端速度で作動し、離陸段階、上昇段階、又は着陸進入段階に、プロペラアレイ23、24の一方又は両方の先端速度を、巡行段階の速度よりも高い所定の速度まで上昇する、二重反転プロペラエンジンの作動方法に関する。本出願人は、離陸時、上昇時、又は着陸進入時の先端速度が、巡行時の先端速度よりも大きい場合に、騒音減少の利点が明らかであり、離陸時、上昇時、又は着陸進入時の先端速度が、巡行時の先端速度よりも少なくとも10%大きい場合に、騒音減少の利点が特に顕著になり、先端速度が巡行時よりも20%±5%であるときに最適の騒音減少が得られるものと考える。
しかしながら、先端速度の上昇及びブレードピッチの適当な変化の組み合わせを使用し、プロペラがその揚力及び推力の要件を確実に満たすようにする。
10 ツインスプールド二重反転プロペラガスタービンエンジン
11 コアエンジン
12 空気取入口
14 中圧コンプレッサ(IPC)
15 高圧コンプレッサ(HPC)
16 燃焼器
17 高圧タービン(HPT)
18 低圧タービン(IPT)
19 自由出力タービン(LPT)
20 コア排気ノズル
21 ナセル
22 コア排気ダクト
23、24 二重反転プロペラアレイ
25、26 二重反転ブレードアレイ
Claims (10)
- 前後のプロペラ(23、24)を持つ二重反転プロペラエンジンの作動方法であって、
前記エンジンは、少なくとも離陸段階、上昇段階、巡行段階、及び着陸進入段階に作動し、巡行段階、エンジンはほぼ一定のプロペラ先端速度で作動する、エンジン作動方法において、
前記前後のプロペラ(23、24)の両プロペラの前記先端速度を、離陸段階、上昇段階、又は着陸進入段階のうちの少なくとも一つの段階の間、巡行段階の先端速度よりも大きくする工程を含み、
前記プロペラは、可変ピッチブレードを含み、
前記方法は、前記ブレードを、巡行時のピッチから着陸進入時のピッチまで閉鎖方向に移動する工程を含む、
ことを特徴とする方法。 - 請求項1に記載の方法において、
離陸段階、上昇段階、又は着陸進入段階のうちの少なくとも一つの段階での前記プロペラの先端速度が、巡行段階の先端速度よりも少なくとも10%大きい、方法。 - 請求項1に記載の方法において、
離陸段階又は着陸進入段階のうちの少なくとも一方の段階での前記プロペラの先端速度が、巡行段階の先端速度よりも20%±5%大きい、方法。 - 請求項1乃至3のうちのいずれか一項に記載の方法において、
前記プロペラは可変ピッチブレードを含み、
前記方法は、前記ブレードを、離陸時のピッチから巡行時のピッチまで開放方向に移動する工程を含む、方法。 - 請求項1乃至4のうちのいずれか一項に記載の方法において、
前プロペラ(23)は少なくとも9枚のブレードを有し(Nf=9)、直径がDfであり、
後プロペラ(24)の最大ブレード数Nrは、Nfから少なくとも3を減じた数であり、
前記前後のプロペラ(23、24)は軸線方向隙間xによって離間されており、
比x/Dfは0.15乃至0.4である、方法。 - 請求項5に記載の方法において、
前記前プロペラ(23)は12枚のブレードを有し、前記後プロペラ(24)は9枚のブレードを有する、方法。 - 請求項5に記載の方法において、
前記前プロペラ(23)は12枚のブレードを有し、前記後プロペラ(24)は7枚のブレードを有する、方法。 - 請求項5に記載の方法において、
前記前プロペラ(23)は12枚のブレードを有し、前記後プロペラ(24)は5枚のブレードを有する、方法。 - 請求項5乃至8のうちのいずれか一項に記載の方法において、
前記前プロペラ(23)の直径は、前記後プロペラ(24)の直径よりも大きい、方法。 - 請求項9に記載の方法において、
前記後プロペラ(24)の直径は、前記前プロペラ(23)よりも、0.05Df乃至0.2Df小さい、方法。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB0702608.1 | 2007-02-10 | ||
GBGB0702608.1A GB0702608D0 (en) | 2007-02-10 | 2007-02-10 | Aeroengine |
PCT/GB2008/000401 WO2008096124A2 (en) | 2007-02-10 | 2008-02-06 | Method of operating a counter-rotating propeller engine for noise reduction and such an engine |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2013056075A Division JP2013144545A (ja) | 2007-02-10 | 2013-03-19 | 航空エンジン |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2010517859A JP2010517859A (ja) | 2010-05-27 |
JP5489727B2 true JP5489727B2 (ja) | 2014-05-14 |
Family
ID=37899098
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2009548734A Expired - Fee Related JP5489727B2 (ja) | 2007-02-10 | 2008-02-06 | 航空エンジン |
JP2013056075A Pending JP2013144545A (ja) | 2007-02-10 | 2013-03-19 | 航空エンジン |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2013056075A Pending JP2013144545A (ja) | 2007-02-10 | 2013-03-19 | 航空エンジン |
Country Status (9)
Country | Link |
---|---|
US (1) | US8382430B2 (ja) |
EP (1) | EP2118444B1 (ja) |
JP (2) | JP5489727B2 (ja) |
CN (2) | CN102390523A (ja) |
BR (1) | BRPI0807050A2 (ja) |
CA (1) | CA2676850A1 (ja) |
GB (1) | GB0702608D0 (ja) |
RU (1) | RU2472942C2 (ja) |
WO (1) | WO2008096124A2 (ja) |
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2007
- 2007-02-10 GB GBGB0702608.1A patent/GB0702608D0/en not_active Ceased
-
2008
- 2008-02-06 RU RU2009133692/06A patent/RU2472942C2/ru not_active IP Right Cessation
- 2008-02-06 US US12/449,196 patent/US8382430B2/en active Active
- 2008-02-06 EP EP08702060.8A patent/EP2118444B1/en active Active
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Also Published As
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CN101657607A (zh) | 2010-02-24 |
US8382430B2 (en) | 2013-02-26 |
CN101657607B (zh) | 2013-02-27 |
JP2010517859A (ja) | 2010-05-27 |
US20100047068A1 (en) | 2010-02-25 |
BRPI0807050A2 (pt) | 2014-04-15 |
EP2118444A2 (en) | 2009-11-18 |
RU2009133692A (ru) | 2011-03-20 |
RU2472942C2 (ru) | 2013-01-20 |
CA2676850A1 (en) | 2008-08-14 |
WO2008096124A2 (en) | 2008-08-14 |
WO2008096124A3 (en) | 2008-10-09 |
CN102390523A (zh) | 2012-03-28 |
EP2118444B1 (en) | 2019-04-10 |
JP2013144545A (ja) | 2013-07-25 |
GB0702608D0 (en) | 2007-03-21 |
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