CN102333694B - 具有包括螺旋桨桨距改变机构的逆旋螺旋桨的装置 - Google Patents
具有包括螺旋桨桨距改变机构的逆旋螺旋桨的装置 Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H5/00—Arrangements on vessels of propulsion elements directly acting on water
- B63H5/07—Arrangements on vessels of propulsion elements directly acting on water of propellers
- B63H5/08—Arrangements on vessels of propulsion elements directly acting on water of propellers of more than one propeller
- B63H5/10—Arrangements on vessels of propulsion elements directly acting on water of propellers of more than one propeller of coaxial type, e.g. of counter-rotative type
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H3/00—Propeller-blade pitch changing
- B63H3/06—Propeller-blade pitch changing characterised by use of non-mechanical actuating means, e.g. electrical
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H3/00—Propeller-blade pitch changing
- B63H3/06—Propeller-blade pitch changing characterised by use of non-mechanical actuating means, e.g. electrical
- B63H3/08—Propeller-blade pitch changing characterised by use of non-mechanical actuating means, e.g. electrical fluid
- B63H3/081—Propeller-blade pitch changing characterised by use of non-mechanical actuating means, e.g. electrical fluid actuated by control element coaxial with the propeller shaft
- B63H3/082—Propeller-blade pitch changing characterised by use of non-mechanical actuating means, e.g. electrical fluid actuated by control element coaxial with the propeller shaft the control element being axially reciprocatable
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- 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
- B64C11/30—Blade pitch-changing mechanisms
- B64C11/306—Blade pitch-changing mechanisms specially adapted for contrarotating propellers
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
- B64D35/06—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating
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- 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
- F01D7/00—Rotors with blades adjustable in operation; Control thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/12—Combinations with mechanical gearing
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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
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/324—Application in turbines in gas turbines to drive unshrouded, low solidity propeller
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- 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
Abstract
所述装置包括一对具有可变桨距的逆旋螺旋桨,该桨距可通过位于轴的中心腔中的致动器(31)来改变。将能量传输到致动器(31)的系统包括:导管(34),其在外摆线齿轮系(17)附近穿入静止壳(5);然后的控制导管(38),其通向致动器(31)并穿过外摆线齿轮系(17)的行星载架(14)。接合受到具有收集器的动态接头的影响。此传输路径避开高温涡轮。
Description
技术领域
本发明的主题是具有包括螺旋桨桨距改变机构的逆旋螺旋桨的装置,其被供应以能量,通常来自可被加压的油的能量,所述机构于是为液压致动器。
背景技术
具有逆旋螺旋桨的装置在多种形式的飞机是已知的,并由于其允许节省燃料而受到欢迎。一些装置包括具有可变桨距的螺旋桨和改变桨距的机构。一种困难于是包括:以适合方式将能量送到致动器,因为未被占据的空间不是很大,且所述装置包括的以多种不同速度旋转的部分的组件不得不交叉。这种问题始终存在,其中传动器显示为外摆线齿轮系,由此,涡轮的能量可在螺旋桨的两个驱动轴中分配,同时确保以期望的速度比逆旋。致动器可安置在螺旋桨的近处,并处于由两个驱动轴包围的腔中。尝试使动力线路沿驱动轴、穿过外摆线齿轮系并沿另一中空轴(其结合到低压涡轮并通过驱动而支撑外摆线齿轮系)穿入装置的此中心腔中;作为此线路的延伸,采取穿过涡轮的径向的固定和弯曲线路沿装置的旋转轴线定位。这种装置将特别简单,但可见的是,使油穿过极热涡轮能够产生炼焦,这对致动器的性能有害。
发明内容
因此,在此推荐另一种将能量供应到致动器的机构,其没有此类缺点。在整体形式上,本发明涉及一种具有逆旋螺旋桨的装置,其包括:用于改变所述螺旋桨的桨距的机构,和在驱动涡轮与所述螺旋桨之间的外摆线齿轮系传动器;所述桨距改变机构包括:致动器,其被供应以能量并被装容在由共心轴包围的腔中,其中所述共心轴将所述外摆线齿轮系连接到所述螺旋桨;以及用于将定子的能量传输到所述致动器的系统,其特征在于,所述传输系统包括:动力供应导管穿过所述定子的固定壳,所述固定壳在所述涡轮与所述外摆线齿轮系之间延伸;然后的动态接头,其在所述导管的一端与旋转环形收集器之间;和最后的控制导管,其将所述收集器连接到所述致动器,所述控制导管穿过所述外摆线齿轮系的行星载架。
附图说明
现在将利用以下附图更详细地描述本发明的各方面以及其他方面:
图1和2例示出螺旋桨装置的两幅图,其中未例示本发明。
图3和4详细例示出本发明的特征。
图5例示出可替代的实施例。
图6是支承螺旋桨的毂的独立图。
具体实施方式
参见图1和2。作为本发明一部分的引擎包括两个螺旋桨1和2,螺旋桨1和2相继定位并围绕相同轴线X旋转。上游螺旋桨1安装在第一中空轴3上,下游螺旋桨2安装在第二中空轴4上。第一中空轴3通过一对滚柱轴承6和7支撑在静止壳5上,并在滚柱轴承6和7之外开放为锥形套8,且终止为内齿冠10。第二中空轴4利用两个滚柱轴承11和12由第一中空轴3支撑,并张开为第二锥形套13,第二锥形套13容纳在第一锥形套8中并连接到行星载架14。行星载架14具有行星齿轮15,行星齿轮15在圆周上分布并向外与冠10啮合且向内与行星轮16啮合。所述组件形成在图4中例示的外摆线齿轮系17。图6例示出支承螺旋桨1和2的毂51。
低压涡轮18位于静止壳5的另一侧上。它包括第三中空轴,第三中空轴是涡轮轴19,用于使其利用两个滚柱轴承20和21由静止壳5支撑。涡轮轴19延伸至其支撑的行星轮16。
第二中空轴4封闭装置轴线X穿过其中的腔30。此腔30包含致动器31,用于修改螺旋桨1和2的桨距。该致动器31例如为被供应以油的液压致动器;该致动器31可以是另一类型的致动器(例如电动马达),通过另一方式被提供动力以向该致动器提供其操作所需的能量(例如电能)。致动器31在此为双致动器,以分别控制螺旋桨1和2的桨距。这种类型的致动器是已知的,只要所需传动器将动力不仅提供到第二螺旋桨2(其牢固紧固到同样驱动致动器31旋转的第二中空轴4),而且提供到沿相反方向旋转的第一螺旋桨1即可,这将不再进一步描述。腔30不仅延伸到中空轴3和4中,而且延伸穿过外摆线齿轮系17和支撑行星轮16的涡轮轴19。自然地,已想到使得向致动器提供动力的线路沿轴向穿过腔30。所述线路于是将包括大致径向的动力线路45,该线路穿过在涡轮18两部分之间的定子33的臂30,并包括弯曲部46,然后穿过动态接头47、控制线路48而通向致动器31以及轴线X。动态接头47并非强制地位于指定位置,其可定位而更接近于致动器31。如前所述,这种设计具有的缺点是,使油暴露于对臂32的显著加热。
图3显示类似于本发明的不同设想的设计,根据这种设计,动力线路34沿径向延伸穿过静止壳5。其在接近于外摆线齿轮系17的开放端35处中断,开放端35向外开放至环形收集器36中,收集器36具有动态接头50的槽截面,动态接头50进一步包括法兰37以支承抵靠行星载架14。收集器36因而连接到行星载架14并随其旋转。通过供应导管34排出的油停留在收集器36中,直到油的压力使其透入具有双壁的中空的法兰37中。各控制线路38在法兰37的中空部与致动器31之间延伸,并穿过行星载架14且在衔接于腔30之前到达第二锥形套13时聚集在一起。各控制线路38的数量可为四个,两个用于螺旋桨1和2中的每一个,一个用于油的外流和回流。
控制线路38穿过钻孔39和40,钻孔39和40构建在形成行星载架14(处于行星15之间)的框架的环42中,或者构建为穿过以轴承44支撑行星15的轴43。第一种设计显示在图3和4中。另一设计显示在图5中,其中可见控制线路(现在以38’表示)占据钻孔40的截面的一部分,同时使部分油流到轴承44。钻孔39于是显然可被省略。
描述了被供应以油的液压致动器31。尽管本发明这样特别有利,但其不限于这些致动器,而是可应用于例如安置在相同位置的电致动器31,形成导管的液压线路被替代为电力导管(以电缆的刚性鞘表示)和具有适合动态接头(例如具有刷)的动态接头50,收集器因而为环形的传导轨道,该轨道擦接所述刷而终止被构建为穿过所述壳的电缆。所述系统的整体布置将不会改变。
Claims (5)
1.一种具有逆旋螺旋桨(1,2)的装置,包括:所述螺旋桨的桨距改变机构,和在驱动涡轮(18)与所述螺旋桨之间的外摆线齿轮系(17);所述桨距改变机构包括:致动器(31),其被供应以能量并被装容在由共心轴(3,4)包围的腔(30)中,其中所述共心轴(3,4)将所述外摆线齿轮系(17)连接到所述螺旋桨(1,2);以及用于将定子(33)的能量传输到所述致动器的传输系统,其特征在于,
所述传输系统包括:供应导管(34),该供应导管穿过所述定子的静止壳(5),所述静止壳在所述涡轮(18)与所述外摆线齿轮系(17)之间延伸;然后是动态接头(50),其在所述供应导管的一端与旋转环形收集器(36)之间;最后是控制导管(38,38’),该控制导管将所述收集器连接到所述致动器,所述控制导管穿过所述外摆线齿轮系的行星载架(14)。
2.根据权利要求1所述的装置,其特征在于,所述能量是电能,所述致动器是电致动器,所述动态接头因而为电接头。
3.根据权利要求1所述的装置,其特征在于,所述传输系统进一步包括润滑导管(51),该润滑导管从所述环形收集器延伸到轴承(44),所述轴承(44)支撑所述行星载架(14)上的行星齿轮(15)。
4.根据权利要求3所述的装置,其特征在于,所述行星齿轮的轴承包括:钻孔(40),所述钻孔(40)穿过建立在所述行星载架上的轴(43),所述控制导管(38′)穿过所述钻孔延伸。
5.根据权利要求1所述的装置,其特征在于,所述控制导管(38)穿过形成所述行星载架(14)框架的环(42)。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
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FR0951259 | 2009-02-27 | ||
FR0951259A FR2942615B1 (fr) | 2009-02-27 | 2009-02-27 | Dispositif a helices contrarotatives ayant un moyen de changement de pas des helices |
PCT/EP2010/052421 WO2010097440A1 (fr) | 2009-02-27 | 2010-02-25 | Dispositif a hélices contrarotatives ayant un moyen de changement de pas des hélices |
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CN102333694A CN102333694A (zh) | 2012-01-25 |
CN102333694B true CN102333694B (zh) | 2014-01-29 |
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US (1) | US8834119B2 (zh) |
EP (1) | EP2401197B1 (zh) |
CN (1) | CN102333694B (zh) |
BR (1) | BRPI1008619B1 (zh) |
CA (1) | CA2753045C (zh) |
FR (1) | FR2942615B1 (zh) |
RU (1) | RU2515954C2 (zh) |
WO (1) | WO2010097440A1 (zh) |
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CN108620691B (zh) * | 2018-03-21 | 2019-10-11 | 湖北工业大学 | 一种摆线轮齿廓修形方法及摆线轮、rv减速器 |
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CN111706432B (zh) * | 2020-05-28 | 2022-03-25 | 中国航发湖南动力机械研究所 | 桨扇发动机及具有其的推进装置 |
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US4772181A (en) * | 1985-09-28 | 1988-09-20 | Dowty Rotol Limited | Bladed rotor assembly and a control system therefor |
US4963108A (en) * | 1988-11-30 | 1990-10-16 | Mitsubishi Jukogyo Kabushiki Kaisha | Marine contra-rotating propeller drive system |
CN1164212A (zh) * | 1994-09-26 | 1997-11-05 | 罗恩·卡梅伦 | 对转叶轮机构 |
Family Cites Families (8)
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US3904315A (en) * | 1974-07-31 | 1975-09-09 | United Aircraft Corp | Pitch change signal means with differential gearing |
US4657484A (en) * | 1984-09-04 | 1987-04-14 | General Electric Company | Blade pitch varying means |
JPS6393697A (ja) * | 1986-10-08 | 1988-04-23 | Ishikawajima Harima Heavy Ind Co Ltd | 二重反転プロペラの推進方法およびその装置 |
DE3905282C1 (en) * | 1987-10-13 | 1990-05-31 | Karl Dipl.-Ing. 2742 Gnarrenburg De Kastens | Propeller fan |
SU1576424A1 (ru) * | 1988-09-19 | 1990-07-07 | Войсковая часть 27177 | Судова энергетическа установка |
JP3064115B2 (ja) * | 1992-08-06 | 2000-07-12 | 三菱重工業株式会社 | 差動歯車を用いた二重反転プロペラ用内外軸連動装置 |
FR2911930A1 (fr) | 2007-01-26 | 2008-08-01 | Snecma Sa | Turbopropulseur a helice a pas reglable |
FR2937678B1 (fr) | 2008-10-23 | 2013-11-22 | Snecma | Dispositif de commande de l'orientation des pales de soufflante d'un turbopropulseur |
-
2009
- 2009-02-27 FR FR0951259A patent/FR2942615B1/fr not_active Expired - Fee Related
-
2010
- 2010-02-25 RU RU2011139298/11A patent/RU2515954C2/ru active
- 2010-02-25 CN CN201080009803.3A patent/CN102333694B/zh active Active
- 2010-02-25 EP EP10706211.9A patent/EP2401197B1/fr active Active
- 2010-02-25 US US13/203,154 patent/US8834119B2/en active Active
- 2010-02-25 BR BRPI1008619-6A patent/BRPI1008619B1/pt active IP Right Grant
- 2010-02-25 WO PCT/EP2010/052421 patent/WO2010097440A1/fr active Application Filing
- 2010-02-25 CA CA2753045A patent/CA2753045C/fr active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3163231A (en) * | 1963-04-29 | 1964-12-29 | United Aircraft Corp | Two-part pitch changing mechanism |
US4772181A (en) * | 1985-09-28 | 1988-09-20 | Dowty Rotol Limited | Bladed rotor assembly and a control system therefor |
US4963108A (en) * | 1988-11-30 | 1990-10-16 | Mitsubishi Jukogyo Kabushiki Kaisha | Marine contra-rotating propeller drive system |
CN1164212A (zh) * | 1994-09-26 | 1997-11-05 | 罗恩·卡梅伦 | 对转叶轮机构 |
Also Published As
Publication number | Publication date |
---|---|
US8834119B2 (en) | 2014-09-16 |
BRPI1008619B1 (pt) | 2020-10-06 |
CA2753045A1 (fr) | 2010-09-02 |
CA2753045C (fr) | 2016-05-03 |
RU2515954C2 (ru) | 2014-05-20 |
US20110305575A1 (en) | 2011-12-15 |
EP2401197B1 (fr) | 2015-07-08 |
CN102333694A (zh) | 2012-01-25 |
WO2010097440A1 (fr) | 2010-09-02 |
FR2942615B1 (fr) | 2011-04-01 |
FR2942615A1 (fr) | 2010-09-03 |
EP2401197A1 (fr) | 2012-01-04 |
RU2011139298A (ru) | 2013-04-10 |
BRPI1008619A2 (pt) | 2016-03-15 |
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