CN110486188A - 电动导管风扇 - Google Patents
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- 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
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- 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
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- 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
- F02K3/04—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 plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—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 plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K5/00—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
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- 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
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/12—Stationary parts of the magnetic circuit
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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
- 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
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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
- 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
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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
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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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
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Abstract
本发明题为“电动导管风扇”。示出了一种用于飞行器的电动导管风扇。短舱限定了容纳具有风扇直径DF的推进式风扇的导管。电机被配置为驱动该风扇,并具有电磁有效长度LA和电磁有效直径DA,该长度和直径限定了0.8至2的长径比(LA/DA)。减速装置位于该电机和该风扇之间,并具有至少3:1的减速比。该电磁有效直径DA与该风扇直径DF之比(DA∕DF)为0.3至0.5。
Description
技术领域
本公开涉及用于飞行器的电动导管风扇的配置。
背景技术
与开放式推进器相比,导管风扇式推进器的效率更高,并且由于叶尖损失较少而降低了噪音,因此导管风扇推进器用于飞行器的大部分。涡轮风扇利用气体涡轮核心来驱动风扇,该风扇比核心大,以产生负责大部分推力的旁路流。
尽管在材料、压缩机和涡轮空气动力学以及燃烧效率方面取得了很大进步,但在涡轮风扇的核心里使用的气体涡轮引擎的热效率仍然非常低。具体地讲,气体涡轮体积越小,效率越低,这限制了在可以安装在机身上的引擎的数量方面的可能性。气体涡轮的燃料源也是不可再生的。此外,来自核心的高焓排气射流在与排出的旁路流混合时会产生大量噪音。
因此,希望在带导管风扇布置结构中使用电机来代替气体涡轮引擎,以减轻上述问题中的一些或全部。
发明内容
本发明涉及用于飞行器的电动导管风扇。
一种此类电动导管风扇包括限定导管的短舱,以及导管中具有风扇直径DF的推进式风扇。电机被配置为经由减速比为至少3:1的减速装置驱动该风扇。该电机具有电磁有效长度LA和电磁有效直径DA,该长度和直径限定了0.8至2的长径比(LA/DA)。电磁有效直径DA与风扇直径DF之比(DA∕DF)为0.3至0.5。
以此类方式构造的电动导管风扇具有各种优点,诸如减小短舱阻力、缩短挂架以及增加离地净高。
附图说明
现在将仅通过示例的方式参考附图来描述实施方案,附图仅为示意图并且未按比例绘制,并且在附图中:
图1示出了使用电机来经由减速装置驱动风扇的电动导管风扇推进器;
图2示出各种几何参数的定义;
图3A示出了使用星形齿轮箱作为该减速装置的图1的推进器;
图3B示出了使用行星式齿轮箱作为该减速装置的图1的推进器;
图4示出了该电机的一种配置;并且
图5示出了该电机的另一种配置。
具体实施方式
图1示出了一种电动导管风扇推进器。
该推进器通常以101示出,其通过挂架103附接到飞行器(未示出)的翼部102。
作为带导管风扇,推进器101包括短舱104,该短舱限定了具有入口106和喷嘴107的导管105,并且推进式风扇108位于该短舱中。在操作中,风扇108使进气的压力升高,气流中的涡流被出口导叶109移除。气流被引导穿过喷嘴107以产生推力。
在图1的实施方案中,风扇108由电机110与减速装置111组合来驱动。
在本实施方案中,电机110的额定最大连续功率介于100千瓦和100兆瓦之间。在具体实施方案中,电机110的额定最大连续功率介于1兆瓦和10兆瓦之间。在更具体的实施方案中,电机110的额定最大连续功率为2兆瓦。
在本示例中,减速装置111是周转齿轮箱,但也可以是另一种形式的减速装置,诸如基于副轴的齿轮系统或其他合适的设计。在一个示例中,该周转齿轮箱是星形齿轮系统。将参考图3A描述此类布置结构。在另一个示例中,该周转齿轮箱是行星齿轮系统。将参考图3B描述此类布置结构。
减速装置111的使用允许电机以更高的速度运转,并允许风扇以更低的速度运转。这样,两个部件都以其各自更高效率的方式运转。此外,由于尖端速度降低,允许使用更大的风扇,并且允许使用更小的电机。
因此,如图2所示,图1的布置允许具有高毂尖比的风扇与高长径比的电机在其长度比直径方面进行组合。
在本示例中,风扇108的毂尖比是风扇叶片201的前缘的直径DF与风扇叶片201的前缘203处的毂202的直径DH(即,风扇108的内部气体洗涤表面的直径)之比。应当理解,毂尖比是风扇、压缩机或涡轮级的标准公知特性。
如本文所定义的电机的长度是电磁有效部件的最大长度LA,而如本文所定义的电机的直径是电磁有效部件的最大直径DA。将参考图4和图5进一步描述应用于具体机器类型的长度LA和直径DA的定义的示例。
通过为推进器101指定以下参数来获得益处:
(i)电机110的长径比LA∕DA(即,LA除以DA的值)为0.8至2;
(ii)该减速装置的减速比为至少3:1;
(iii)电机和风扇中的电磁有效部件的直径之比DA∕DF(即,DA除以DF的值)为0.3至0.5。
具体地讲,发明人已经发现,这种值组合有利地使得推进器101具有较小直径的喷嘴107以获得相同的整体风扇压力比,这允许挂架103被制得更短。对于特定的风扇直径DF,这导致离地净高更大,或者对于特定的离地净高,这导致风扇直径DF更大。此外,挂架长度和高度的减小导致翼部102上的力矩减小以及重量减轻。
在具体实施方案中,比率LA/DA为1.1至1.7。发明人已经发现,这允许使用狭窄的喷嘴以及更高速的机器。在另一个具体实施方案中,LA/DA为1.3至1.5。在更具体的实施方案中,LA∕DA为1.4。
在附加的或另选的实施方案中,比率DA∕DF为0.35至0.45。在具体实施方案中,比率DA∕DF为0.37至0.43。在更具体的实施方案中,比率DA∕DF可为0.4。
风扇108的毂尖比即DT∕DH的值可为0.25至0.31。在具体实施方案中,该毂尖比可为0.27至0.29。在更具体的实施方案中,毂尖比可为0.28。
在一个实施方案中,风扇108的尖端压力比(即,紧接在风扇叶片201的尖端的上游和紧接在风扇叶片201的下游的滞止压力之比)在海平面以上35,000英尺的海拔和零下54℃的温度(即,ISA+0标准条件)下以及在0.85马赫的真空速下(即,在巡航状态期间)为1.3至1.7。在具体实施方案中,尖端压力比在上述条件下可为1.4至1.6。在更具体的实施方案中,尖端压力比在上述条件下可为1.5。在另一个具体实施方案中,尖端压力比在上述条件下可为1.38。
推进器101的一个实施方案的图在图3A中示出,其中减速装置111是星形周转齿轮箱,通常用301表示。电机110经由输入轴联接到太阳齿轮302,该太阳齿轮与安装到静态载体304的行星齿轮303啮合。行星齿轮303将扭矩传递到环形齿轮305,该环形齿轮驱动风扇108。在一个实施方案中,星形齿轮箱301的减速比为3:1至3.7:1。由于固定的载体,使用星形齿轮箱可有助于降低例如关于润滑系统的安装复杂性。
推进器101的另一个实施方案的图在图3B中示出,其中减速装置111是行星式周转齿轮箱,通常用311表示。电机110经由输入轴联接到太阳齿轮312,该太阳齿轮与安装在旋转载体314中的行星齿轮313啮合。行星齿轮313将扭矩传递到静态环形齿轮315,其中载体驱动风扇108。在一个实施方案中,行星齿轮箱311的减速比为3:1至4.7:1。使用行星齿轮箱可有助于为给定数量的齿轮齿提供更大的减速比。
电机101的配置的示例通过图4中的中心轴线A-A以截面示出。该特定配置是径向通量电机401,该电机包括围绕转子403的定子402。定子402包括已知类型的层压叠堆。在本示例中,电机是永磁电机,因此转子403包括永磁体,该永磁体与由定子402中的绕组产生的磁场相互作用以产生扭矩。也可采用另选机器类型诸如感应电机。作为径向通量电机,端部绕组404从定子402的叠片堆中轴向地出现。
如前所述,电机401可被描述为具有电磁有效长度LA和电磁有效直径DA。如本文所用,“电磁有效”是指负责在转子上产生扭矩的区域。因此,在本示例中,长度LA是定子402的层压叠堆的长度,并且不包括端部绕组404,因为它们不会在转子403上产生明显的扭矩。类似地,直径DA是定子302的层压叠堆的直径。
换句话说,电机401的“电磁有效”部分可被表征为在机器中形成扭矩产生磁电路的部分的那些部件。
本领域技术人员将理解可如何在替他机器类型(诸如,基于电磁铁的同步马达以及轴向通量电机)中读懂该定义,其中本文所述的长径比的定义也适用于这些类型的机器。
电机101的另一示例性配置通过图5的中心轴线B-B以截面示出。该特定配置是径向通量电机501,该电机包括围绕定子503的转子502。与电机401一样,该机器的电磁有效长度LA是定子503的层压叠堆的长度,不包括端部绕组504。然而,在该实施方案中,电磁有效直径DA是转子502的直径。同样,机器501是永磁电机,因此直径DA由其中磁体的最大径向范围界定。如果机器更换为感应电机,则直径DA将由转子铁的最大径向范围限定。
更一般地说,如参考图4所述,应当理解,电机501的“电磁有效”部分可被表征为在机器中形成扭矩产生磁电路的部分的那些部件。
已经描述了各种示例,每个示例都以各种特征组合为特征。本领域技术人员将理解,除非明显相互排斥,否则任何特征可单独使用或与任何其他特征组合使用,并且本发明扩展到并包括本文所述的一个或多个特征的所有组合和子组合。
Claims (15)
1.一种用于飞行器的电动导管风扇,所述电动导管风扇包括:
短舱,所述短舱限定导管;
推进式风扇,所述推进式风扇位于所述导管中具有风扇直径DF;
电机,所述电机被配置为驱动所述风扇,所述电机具有电磁有效长度LA和电磁有效直径DA,所述电磁有效长度LA和所述电磁有效直径DA限定了0.8至2的长径比(LA / DA);
减速装置,所述减速装置位于所述电机和所述风扇之间具有至少3:1的减速比;
并且其中所述电磁有效直径DA与所述风扇直径DF之比(DA∕DF)为0.3至0.5。
2.根据权利要求1所述的电动导管风扇,其中所述长径比(LA∕DA)为1.1至1.7。
3.根据权利要求2所述的电动导管风扇,其中所述长径比(LA∕DA)为1.4。
4.根据权利要求1所述的电动导管风扇,其中所述电磁有效直径DA与所述风扇直径DF之比(DA∕DF)为0.35至0.45。
5.根据权利要求4所述的电动导管风扇,其中所述电磁有效直径DA与所述风扇直径DF之比(DA∕DF)为0.37至0.43,例如0.4。
6.根据权利要求1所述的电动导管风扇,其中所述电机是径向通量电机。
7.根据权利要求6所述的电动导管风扇,其中定子位于转子的外部,所述电磁有效直径DA为定子叠堆的直径,并且所述电磁有效长度LA为所述定子叠堆的长度。
8.根据权利要求6所述的电动导管风扇,其中所述定子位于所述转子的内部,所述电磁有效直径DA为所述转子的直径,并且所述电磁有效长度LA为所述定子叠堆的长度。
9.根据权利要求1所述的电动导管风扇,其中所述风扇具有0.25至0.31的毂尖比。
10.根据权利要求9所述的电动导管风扇,其中所述风扇具有0.27至0.29、例如0.28的毂尖比。
11.根据权利要求1所述的电动导管风扇,其中所述推进式风扇在35,000英尺的高度以及0.85马赫的真空速下具有1.3至1.7的尖端压力比。
12.根据权利要求11所述的电动导管风扇,其中所述推进式风扇在35,000英尺的高度以及0.85马赫的真空速下具有1.3至1.5的尖端压力比。
13.根据权利要求12所述的电动导管风扇,其中所述推进式风扇在35,000英尺的高度以及0.85马赫的真空速下具有1.38的尖端压力比。
14.根据权利要求1至13中任一项所述的电动导管风扇,其中所述减速装置是减速比为至多3.7:1的星形齿轮箱。
15.根据权利要求1至13中任一项所述的电动导管风扇,其中所述减速装置是减速比为至多4.7:1的行星齿轮箱。
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GB202110536D0 (en) * | 2021-07-22 | 2021-09-08 | Rolls Royce Plc | Aircraft propulsion system |
GB2610571A (en) * | 2021-09-08 | 2023-03-15 | Rolls Royce Plc | An improved gas turbine engine |
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