CN104968893A - 无涵道的推力产生系统体系结构 - Google Patents

无涵道的推力产生系统体系结构 Download PDF

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CN104968893A
CN104968893A CN201380055512.1A CN201380055512A CN104968893A CN 104968893 A CN104968893 A CN 104968893A CN 201380055512 A CN201380055512 A CN 201380055512A CN 104968893 A CN104968893 A CN 104968893A
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rotatable member
thrust
fixed element
produces
thrusts
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CN104968893B (zh
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D.T.扎托尔斯基
J.A.哈梅尔
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General Electric Co
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General Electric Co
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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • 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
    • 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
    • B64C11/001—Shrouded 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
    • B64C11/16—Blades
    • B64C11/18—Aerodynamic features
    • 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
    • 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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/20—Adaptations of gas-turbine plants for driving vehicles
    • F02C6/206—Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D2027/005—Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/12—Fluid guiding means, e.g. vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—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
    • 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
    • F05D2220/00—Application
    • F05D2220/90—Application in vehicles adapted for vertical or short take off and landing (v/stol vehicles)
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • 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
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet
    • 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
    • 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
    • F05D2260/14—Preswirling
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • 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
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/70—Wind energy
    • Y02E10/72—Wind turbines with rotation axis in wind direction
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Wind Motors (AREA)

Abstract

一种无涵道的推力产生系统具有带有旋转轴线的旋转元件和固定元件。旋转元件包括多个叶片，并且固定元件具有多个翼片，这多个翼片构造成使得工作流体的切向速度发生变化，该变化与由旋转元件造成的该旋转元件对其起作用的工作流体的切向速度的变化相反。该系统包括位于旋转元件和固定元件的前方的入口。

Description

无涵道的推力产生系统体系结构
相关申请的交叉引用
本申请涉及2013年10月23日提交的代理案卷号为No.264668-2、名为“无涵道的推力产生系统”的PCT/US13/XXXXX和2013年10月23日提交的代理案卷号为No.265517-2、名为“用于无涵道的推力产生系统的翼片(vane)组件”的PCT/US13/XXXXX。
背景技术
本说明书中所述的技术涉及一种无涵道的(unducted)推力产生系统，特别是用于这种系统的体系结构。该技术在应用于“开式转子(open rotor)”燃气涡轮发动机时是特别有益的。
利用开式转子设计体系结构的燃气涡轮发动机是已知的。涡轮风扇发动机按照下列原理运转，即：中央燃气涡轮机芯部(core)驱动旁路风扇，该风扇定位在位于发动机的机舱与发动机芯部之间的径向位置处。而开式转子发动机则按照下列原理运转，即：使旁路风扇定位于发动机机舱的外侧。这允许使用与涡轮风扇发动机相比能够对更大的空气体积起作用的大型风扇叶片，并且由此与常规发动机设计相比改进了推进效率。
在开式转子设计具有由两个反转的转子组件提供的风扇，每一个转子组件承载定位于发动机机舱外侧的翼型件叶片的阵列的情况下，已经发现了最佳性能。如在本说明书中所使用的那样，“反转关系”意指将第一和第二转子组件的叶片设置成彼此反向旋转。通常，将第一和第二转子组件的叶片设置成围绕共同的轴线沿相反方向旋转，并且沿该轴线轴向间隔开。例如，第一转子组件和第二转子组件的相应叶片可以是同轴安装且间隔开的，第一转子组件的叶片构造成围绕该轴线顺时针旋转并且第二转子组件的叶片构造成围绕该轴线逆时针旋转(或者反之亦然)。在外表上，开式转子发动机的风扇叶片类似于常规涡轮螺旋桨发动机的推进器叶片。
反转的转子组件的使用在从动力涡轮机传递动力以便沿相反的方向驱动相应的两个转子组件的叶片的方面中产生了技术难题。
所希望的是，提供一种开式转子推进系统，该系统利用类似于传统旁路风扇的单个旋转的推进器组件，这降低了设计复杂度、更是在重量显著降低且长度明显缩短的情况下产生了能够与反转的推进设计相比拟的推进效率水平。
发明内容
一种无涵道的推力产生系统具有带有旋转轴线的旋转元件和固定元件。该旋转元件包括多个叶片，并且该固定元件具有多个翼片，这多个翼片构造成使得工作流体的切向速度发生变化，该变化与由旋转元件造成的该旋转元件对其起作用的工作流体的切向速度的变化相反。该系统包括位于旋转元件和固定元件的前方的入口。
附图说明
结合在专利说明书中并构成该专利说明书的一部分的附图示出了一个或多个实施例并且与说明书一起说明这些实施例。在附图中：
图1是无涵道的推力产生系统的示例性实施例的横断面示意图；
图2是用于无涵道的推力产生系统的示例性翼片组件的替代实施例的插图；
图3是无涵道的推力产生系统的示例性实施例的局部横断面示意图，其描绘了示例性的复合齿轮箱构造；
图4是无涵道的推力产生系统的示例性实施例的局部横断面示意图，其描绘了另一示例性的齿轮箱构造；
图5是无涵道的推力产生系统的另一示例性实施例的横断面示意图；
图6是无涵道的推力产生系统的另一示例性实施例的横断面示意图；
图7是无涵道的推力产生系统的另一示例性实施例的横断面示意图；
图8是无涵道的推力产生系统的另一示例性实施例的横断面示意图；
图9是无涵道的推力产生系统的另一示例性实施例的横断面示意图；
图10是无涵道的推力产生系统的另一示例性实施例的横断面示意图；
图11是无涵道的推力产生系统的另一示例性实施例的横断面示意图；
图12是无涵道的推力产生系统的另一示例性实施例的横断面示意图；
图13是无涵道的推力产生系统的另一示例性实施例的横断面示意图；
图14是无涵道的推力产生系统的另一示例性实施例的横断面示意图；
图15是沿图14的线15-15获取的横断面示意图，其示出了图14的无涵道的推力产生系统的入口构造。
具体实施方式
在下列视图中的所有视图中，相似的附图标记用于遍及附图中描绘的多个实施例指代相似的元件。
图1示出了无涵道的推力产生系统10的示例性实施例的横断面正视图。如从图1所见，无涵道的推力产生系统10呈开式转子推进系统的形式，并具有描绘成推进器组件的旋转元件20，该旋转元件20包括围绕无涵道的推力产生系统10的中央纵向轴线11的翼型件叶片21的阵列。叶片21围绕中心线11成大致等间距间隔开的关系设置，并且每一个叶片21均具有根部23和尖端24以及限定在其间的翼展。无涵道的推力产生系统10包括具有燃气发生器(gasgenerator)40和低压涡轮机50的燃气涡轮发动机。左手或右手发动机构造可通过使21、31和50的翼型件成镜像来获得。作为替代方案，可选择的反转(reversing)齿轮箱55(如图3和4中所示定位于低压涡轮机50中或之后或者如图3中所示与动力齿轮箱60相结合或相关联)允许将共同的燃气发生器和低压涡轮机用于使风扇叶片顺时针或逆时针旋转，即，以便按照要求提供左手或右手构造，从而提供如可能为特定的航空设施所需要的一对反向旋转的发动机组件。在图1中所示的实施例中的无涵道的推力产生系统10还包括一体的驱动器(动力齿轮箱)60，该一体的驱动器60可包括用于降低推进器组件相对于低压涡轮机50的旋转速度的齿轮组。
在示例性实施例中，无涵道的推力产生系统10还包括不旋转的固定元件30，该固定元件30包括同样围绕中央轴线11设置的翼片31的阵列，并且每一个翼片31均具有根部33和尖端34以及限定在其间的翼展。这些翼片可被设置成使得它们并非全部与旋转组件间隔开相等距离，并且可以可选择地包括远离轴线11的环形护罩或涵道(duct)100(如图2中所示)或者可以是无护罩的。这些翼片可安装于固定框架并且并不相对于中央轴线11旋转，但可包括用于调整它们相对于它们的轴线90和/或相对于叶片21的取向的机构。出于说明的目的，图1还描绘了以箭头F表示的前向方向，其又限定了该系统的前向部分和后部部分。如在图1中所示，旋转元件20定位于“拉拔器(puller)”构造中的燃气发生器40的前方，并且排气装置80定位于固定元件30的后部。
除了降低噪音的益处之外，图2中所示的涵道100通过将固定翼片31联接成组件提供了固定翼片31的振动响应和结构完整性的益处，该组件形成了环形环或一个或多个圆周区段、即形成将诸如形成双联体(doublet)的成对件之类的两个或多个翼片31连结在一起的环形环的多个部分的节段。涵道100可使得翼片的桨距能够按照要求加以改变。
由所公开的风扇原理产生的噪音的较大部分、或许甚至是主要部分与由上游叶栅(blade-row)产生的紊流与尾流(wake)之间的相互作用及其加速度和在下游叶栅表面上的碰撞相关联。通过引入在固定翼片上方充当护罩的部分涵道，在翼片表面处产生的噪音可被屏蔽掉以便在远场中有效地产生阴影区(shadow zone)，从而降低整体干扰程度(annoyance)。当在轴向长度方面延长该涵道时，穿过该涵道的声辐射的效率进一步受到声截止(acoustic cut-off)的现象的影响，这如针对常规航空器发动机那样可用于将声辐射限制到远场中。此外，护罩的引入考虑到了结合声处理的机会，如当前针对常规航空器发动机所做的那样，以便在它反射或与衬套以其它方式相互作用时衰减声音。通过在位于固定翼片的上游和下游的护罩的内侧和轮毂表面上引入声学处理表面，可将从固定翼片发出的声波的多次反射基本上衰减掉。
在运行中，通过低压涡轮机经由齿轮箱60驱动旋转叶片21，使得它们围绕轴线11旋转并且产生推力以沿前向方向F推进无涵道的推力产生系统10并且由此推进它所关联的航空器。
可以希望的是，这多组叶片21和31中的任一者或两者结合有变距机构，使得叶片可以或者单独地或者彼此一起相对于桨距旋转轴线旋转。这种变距可被用于在多种运行状况下改变推力和/或涡旋效应，包括提供在诸如航空器着陆时之类的特定运行状况中会是有用的反推力特征。
叶片31被确定尺寸、成形、并构造成使流体产生起抵消作用的涡旋，使得在下流方向上，两排叶片的后部的流体具有大幅降低的涡旋程度，其转换成程度增大了的感应效率。叶片31可比叶片21具有较短的翼展，如在图1中所示，例如，叶片21的翼展的50％，或者可按照要求具有比叶片21长的翼展或与叶片21相同的翼展。翼片31可附接于与推进系统相关联的航空器结构，如图1中所示，或者附接于诸如机翼、外挂架(pylon)、或机身之类的另一航空器结构。固定元件的翼片31可在数量上比旋转元件的叶片21的数量少或多或者在数量上与旋转元件的叶片21的数量相同，并且通常在数量上大于两个或大于四个。
在图1中所示的实施例中，环形的360度入口70定位在风扇叶片组件20与静止的或固定的叶片组件30之间，并提供用于使引入的大气相对于固定元件30径向向内地进入燃气发生器40的路径。这种位置出于多种原因而可能是有利的，其原因包括管理结冰性能以及保护入口70免受可能在运行中遇到的多种物体和材料的影响。
图5示出了燃气涡轮发动机10的另一示例性实施例，与图1的实施例的不同之处在于入口71的位置位于旋转元件20和固定元件30的前方并位于旋转元件20的径向内侧。
图1和图5均示出了可被称之为“拉拔器”构造的结构，在该构造中，产生推力的旋转元件20定位于燃气发生器40的前方。图6在另一方面示出了可被称之为“推进器”构造实施例的结构，在该构造中，燃气发生器40定位在旋转元件20的前方。如同图5的实施例的情况一样，入口71定位在旋转元件20和固定元件30的前方并定位在旋转元件20的径向内侧。排气装置80定位在旋转元件20和固定元件30的内侧及后部。图6中所绘的系统还示出了固定元件30定位在旋转元件20的前方的构造。
对于“拉拔器”构造或“推进器”构造的选择可与对于相对于预期航空器应用的飞机机身的安装取向的选择相一致地来进行，并且取决于安装位置和取向是机翼安装的构造、机身安装的构造、还是机尾安装的构造，一些在结构上或在运行上会是有利的。
图7和图8示出了与图6相似的“推进器”实施例，但其中，排气装置80定位在固定元件30与旋转元件20之间。尽管在这两种实施例中旋转元件20定位在固定元件30的后部，但图7和图8彼此不同之处在于，图7的旋转元件20结合了比图8的实施例相对长的叶片，使得图7的叶片的根部23凹入到来自固定元件30的气流拖尾后部下方，并且来自燃气发生器40的排气被朝向旋转元件20的前缘引导。在图8的实施例中，旋转元件20在长度上越发是几乎能够与固定元件30相比较的，并且排气80被在旋转元件20与固定元件30之间更为径向向外地引导。
图9、图10、和图11描绘了其它示例性“推进器”构造实施例，其中，旋转元件20定位在固定元件30的前方，两种元件均位于燃气发生器40的后部。在图9的实施例中，排气装置80定位在旋转元件20和固定元件30的后部。在图10的实施例中，排气装置80定位在旋转元件20和固定元件30的前方。最终，在图11的实施例中，排气装置80定位在旋转元件20与固定元件30之间。
图12和图13示出了燃气发生器40、低压涡轮机50和旋转元件20的不同结构。在图12中，旋转元件20和助力器(booster)300由与助力器300直接联接并经由减速装置60连接至旋转元件20的低压涡轮机50驱动。高压压缩机301由高压涡轮机302直接驱动。在图13中，旋转元件20由低压涡轮机50经由减速装置60驱动，助力器303直接由中间压力涡轮机306驱动，并且高压压缩机304由高压涡轮机305驱动。
图15是沿图14的线15-15获取的横断面示意图，其将图14的无涵道的推力产生系统的入口构造示出为非轴对称的、非环形的入口。在所示构造中，入口70呈一对径向相对的入口72的形式，每一个入口72均馈送到芯部中。
用作动力源的燃气涡轮机或内燃机可在压缩过程中利用中间冷却元件。同样，燃气涡轮发动机可利用位于动力涡轮机的下游的回收装置。
在多个实施例中，用以驱动旋转元件20的动力源可以是由喷气燃料或液态天然气供应燃料的燃气涡轮发动机、电动马达、内燃机、或任何其它适用的扭矩和动力源并且可定位在旋转元件20的附近或可相对于适当构造的诸如配电模块系统之类的传动装置远程定位。
除了适合于与旨在用于水平飞行的常规航空器平台一起使用的构造之外，本说明书中所述的技术可还被用于直升机和倾斜转子应用和其它提升装置以及悬停装置。
可以预期的是，结合在共同转让的待审申请[]和[]中描述的技术来利用本说明书中所述的技术。
仅出于说明的目的提供了对于本发明的实施例的前述说明，并且该前述说明并非旨在限制如在所附权利要求中限定的本发明的范围。
本申请涉及2013年10月23日提交的代理案卷号为No.264668-2、名为“无涵道的推力产生系统”的PCT/US13/XXXXX和2013年10月23日提交的代理案卷号为No.265517-2、名为“用于无涵道的推力产生系统的翼片组件”的PCT/US13/XXXXX，这两篇文件的全部内容均被以参引的方式结合到本说明书中。

Claims (34)

1.一种无涵道的推力产生系统，所述推力产生系统包括旋转元件、固定元件、和位于所述旋转元件和所述固定元件的前方的入口。
2.根据权利要求1所述的推力产生系统，其特征在于，所述旋转元件具有旋转轴线和多个叶片，并且所述固定元件具有多个翼片，所述多个翼片构造成使得空气的切向速度发生变化，所述变化与由所述旋转元件造成的空气的切向速度的变化相反。
3.根据权利要求2所述的推力产生系统，其特征在于，所述翼片中的至少一个包括远离所述轴线的护罩。
4.根据权利要求1所述的推力产生系统，其特征在于，所述翼片中的至少一个附接于航空器结构。
5.根据权利要求1所述的推力产生系统，其特征在于，所述固定元件包括多于两个翼片。
6.根据权利要求5所述的推力产生系统，其特征在于，所述固定元件包括多于四个翼片。
7.根据权利要求1所述的推力产生系统，其特征在于，所述无涵道的推力产生系统是倾斜转子系统。
8.根据权利要求1所述的推力产生系统，其特征在于，所述无涵道的推力产生系统是直升机提升系统。
9.根据权利要求1所述的推力产生系统，其特征在于，所述旋转元件经由扭矩产生装置驱动。
10.根据权利要求9所述的推力产生系统，其特征在于，所述扭矩产生装置从以下组中选出，所述组包括电动马达、燃气涡轮机、齿轮驱动系统、液压马达、及其组合。
11.根据权利要求1所述的推力产生系统，其特征在于，所述无涵道的推力产生系统是推进器系统。
12.根据权利要求1所述的推力产生系统，其特征在于，所述无涵道的推力产生系统是开式转子系统。
13.一种无涵道的推力产生系统，所述推力产生系统包括旋转元件、固定元件、和处于所述旋转元件与所述固定元件之间的入口，其中，所述入口径向地穿过所述固定元件的内部。
14.根据权利要求13所述的推力产生系统，其特征在于，所述旋转元件具有旋转轴线和多个叶片，并且所述固定元件具有多个翼片，所述多个翼片构造成使得空气的切向速度发生变化，所述变化与由所述旋转元件造成的空气的切向速度的变化相反。
15.根据权利要求14所述的推力产生系统，其特征在于，所述翼片中的至少一个包括远离所述轴线的护罩。
16.根据权利要求13所述的推力产生系统，其特征在于，所述翼片中的至少一个附接于航空器结构。
17.根据权利要求13所述的推力产生系统，其特征在于，所述固定元件包括多于两个翼片。
18.根据权利要求17所述的推力产生系统，其特征在于，所述固定元件包括多于四个翼片。
19.根据权利要求13所述的推力产生系统，其特征在于，所述无涵道的推力产生系统是倾斜转子系统。
20.根据权利要求13所述的推力产生系统，其特征在于，所述无涵道的推力产生系统是直升机提升系统。
21.根据权利要求13所述的推力产生系统，其特征在于，所述旋转元件经由扭矩产生装置驱动。
22.根据权利要求21所述的推力产生系统，其特征在于，所述扭矩产生装置从以下组中选出，所述组包括电动马达、燃气涡轮机、齿轮驱动系统、液压马达、及其组合。
23.根据权利要求13所述的推力产生系统，其特征在于，所述无涵道的推力产生系统是推进器系统。
24.根据权利要求13所述的推力产生系统，其特征在于，所述无涵道的推力产生系统是开式转子系统。
25.一种无涵道的推力产生系统，所述推力产生系统包括旋转元件、固定元件、和位于这两种元件的后部的非环形的入口。
26.根据权利要求25所述的推力产生系统，其特征在于，所述旋转元件具有旋转轴线和多个叶片，并且所述固定元件具有多个翼片，所述多个翼片构造成使得空气的切向速度发生变化，所述变化与由所述旋转元件造成的空气的切向速度的变化相反。
27.一种无涵道的推力产生系统，所述推力产生系统包括旋转元件和固定元件，其中，所述旋转元件经由定位在所述旋转元件和所述固定元件的前方的减速装置驱动。
28.一种无涵道的推力产生系统，所述推力产生系统包括旋转元件和具有后缘的固定元件，其中，所述旋转元件经由定位在所述旋转元件与所述后缘之间的减速装置驱动。
29.一种无涵道的推力产生系统，所述推力产生系统包括旋转元件、固定元件、和位于所述旋转元件和所述固定元件的前方的排气装置。
30.一种无涵道的推力产生系统，所述推力产生系统包括旋转元件、固定元件、和位于所述旋转元件与所述固定元件之间的排气装置。
31.一种无涵道的推力产生系统，所述推力产生系统包括旋转元件、固定元件、和位于所述旋转元件和所述固定元件的后部的排气装置。
32.一种无涵道的推力产生系统，所述推力产生系统包括多个旋转元件和多个固定元件，其中，至少一个旋转元件沿与至少一个其它旋转元件相反的方向旋转，并且其中，所述固定元件的翼展至少为所述旋转元件的翼展的25％。
33.一种无涵道的推力产生系统，所述推力产生系统包括旋转元件、固定元件、和燃气涡轮发动机，所述燃气涡轮发动机包括芯部、助力器、和低压涡轮机，其中，所述旋转元件和所述助力器由所述低压涡轮机驱动，所述低压涡轮机与所述助力器直接联接并经由所述减速装置连接至所述旋转元件。
34.一种无涵道的推力产生系统，所述推力产生系统包括旋转元件、固定元件、和燃气涡轮发动机，所述燃气涡轮发动机包括芯部，所述芯部具有中间压力涡轮机和助力器，其中，所述旋转元件由所述低压涡轮机经由减速装置驱动，并且其中，所述助力器经由与所述助力器直接联接的所述中间压力涡轮机驱动。
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CN112594087A (zh) 2021-04-02
CA2887262A1 (en) 2014-05-01
JP6360063B2 (ja) 2018-07-18
BR112015009059A2 (pt) 2017-07-04
CA2902826C (en) 2021-05-18
JP2016501761A (ja) 2016-01-21
US11988099B2 (en) 2024-05-21
US20200271010A1 (en) 2020-08-27
EP2948633A1 (en) 2015-12-02
BR112015007799A2 (pt) 2018-04-24
EP2912271A2 (en) 2015-09-02
CN112594087B (zh) 2024-08-13
US20200308979A1 (en) 2020-10-01
CA2887260A1 (en) 2014-05-01
CN104755703B (zh) 2017-10-27
EP4098843A1 (en) 2022-12-07
WO2014066515A1 (en) 2014-05-01
US20150284070A1 (en) 2015-10-08
US10704410B2 (en) 2020-07-07
BR112015009059B1 (pt) 2021-02-09
BR112015007799B1 (pt) 2022-01-04
JP2015533354A (ja) 2015-11-24

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