CN102900514A - 具有先导子室的旋转内燃发动机 - Google Patents
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Abstract
本发明涉及具有先导子室的旋转内燃发动机。具体地,一种汪克尔发动机系统具有:在转子主体的周围壁中的插入件,所述插入件由耐热性大于所述周围壁的耐热性的材料制成,具有限定在其内的子室并具有与所述腔接界的内表面,所述子室通过限定在所述内表面中的至少一个开口与所述腔连通,所述子室的形状在邻近于所述开口处形成减小的横截面;先导燃料喷射器,所述先导燃料喷射器具有被接收在所述子室内的尖端;点火元件,所述点火元件具有被接收在所述子室内的尖端;和主燃料喷射器,所述主燃料喷射器延伸穿过所述壳体并具有在与所述插入件间隔开的位置处与所述腔连通的尖端。
Description
相关申请的交叉引用
本申请要求2011年7月28日提交的美国临时申请No. 61/512,593的优先权,其全部内容通过引用并入本文中。
技术领域
本申请一般地涉及包括旋转内燃发动机的复合发动机系统,更具体地涉及采用重质燃料的此类系统。
背景技术
旋转发动机(例如汪克尔发动机)使用活塞的偏心旋转将压力转换为旋转运动,而不是使用往复式活塞。在这些发动机中,转子包括多个顶点或密封件分,其在转子的整个旋转运动期间保持与发动机的转子腔的周围壁接触以在转子旋转时产生多个旋转室。
汪克尔发动机通常使用汽油或类似的燃料,具有单个燃料喷射器或者具有两个间隔开的燃料喷射器。(一个或多个)燃料喷射器可位于在燃烧室附近的且被一体地限定穿过发动机壳体的凹陷中,以与诸如火花塞的点火构件连通。然而,已知的装置没有针对在复合循环发动机系统中使用和/或与所谓的重质燃料(例如煤油)一起使用进行优化,因而存在改进的空间。
发明内容
在一个方面中,提供了一种旋转发动机,其包括:具有内腔的定子主体,所述内腔由两个轴向间隔开的端壁以及在所述端壁之间延伸的周围壁限定,所述腔具有限定了两个凸角(lobe)的外旋轮线;具有三个周向间隔的顶点部分的转子主体,所述转子主体接合到轴的偏心部分以在所述腔内旋转并进行轨道公转,其中,所述顶点部分的每一个保持与所述周围壁密封接合并且分开三个可变体积的旋转室,所述旋转室围绕所述转子主体被限定在所述腔中;在所述转子主体的周围壁中的插入件,所述插入件由耐热性大于所述周围壁的耐热性的材料制成,所述插入件具有限定在其内的子室并具有与所述腔接界的内表面,所述子室通过限定在所述内表面中的至少一个开口与所述腔连通,所述子室的形状在邻近于所述开口处形成减小的横截面;先导燃料喷射器,所述先导燃料喷射器具有被接收在所述子室内的尖端;点火元件,所述点火元件具有被接收在所述子室内的尖端;和主燃料喷射器,所述主燃料喷射器延伸穿过所述壳体并具有在与所述插入件间隔开的位置处与所述腔连通的尖端。
在另一方面中,提供了一种汪克尔发动机的定子主体,包括:两个轴向间隔开的端壁;周围壁,所述周围壁在所述端壁之间延伸并且与所述端壁一起限定内腔,所述腔具有限定了两个凸角的外旋轮线;在所述转子主体的周围壁中的插入件,所述插入件由耐热性大于所述周围壁的耐热性的材料制成,所述插入件具有限定在其内的子室并具有与所述腔接界的内表面,所述子室通过限定在所述内表面中的至少一个开口与所述腔连通,所述子室的形状在邻近于所述开口处形成减小的横截面;所述插入件和所述周围壁中的至少一个具有被限定穿过其中的先导燃料喷射器伸长孔,所述先导燃料喷射器伸长孔与所述子室连通并且所述先导燃料喷射器伸长孔的尺寸设置成在其内接收先导燃料喷射器;所述插入件和所述周围壁中的至少一个具有被限定穿过其中的点火元件伸长孔,所述点火元件伸长孔与所述子室连通并且所述点火元件伸长孔的尺寸设置成在其内接收点火元件;并且所述周围壁具有被限定穿过其中的主燃料喷射器伸长孔,所述主燃料喷射器伸长孔与所述插入件间隔开并且所述主燃料喷射器伸长孔的尺寸设置成在其内接收主燃料喷射器。
在又一方面中,提供了一种将重质燃料喷射到汪克尔发动机中的方法,所述汪克尔发动机具有多个旋转室,每个旋转室的体积在最小体积和最大体积之间变化,所述方法包括:将所述重质燃料的小部分喷射到子室中,所述子室被限定成邻近于并顺序地连通每个旋转室并且具有子室体积,所述子室体积对应于所述最小体积和所述子室体积的总和的从5%到25%;在所述子室内点燃所述重质燃料;部分地约束被点燃的重质燃料从所述子室到所述旋转室的流动;以及与所述子室独立且间隔开地将所述重质燃料的剩余部分顺序地喷射到每个旋转室中。
附图说明
现在参照附图,其中:
图1是根据一个具体实施例的旋转内燃发动机的局部示意性剖面图;
图2是图1的发动机的插入件的示意性剖面图;
图3是根据另一实施例的插入件的示意性剖面图;
图4是根据又一实施例的插入件的示意性剖面图。
具体实施方式
参照图1,示意性地且局部地示出了称为汪克尔发动机的旋转内燃发动机10。在一个具体实施例中,旋转发动机10用在复合循环发动机系统中,例如2010年7月13日授权的Lents等人的美国专利No. 7,753,036或者2010年8月17日授权的Julien等人的美国专利No. 7,775,044中描述的复合循环发动机系统,两项专利的全部内容通过引用并入本文中。复合循环发动机系统可用作例如飞机或其他交通工具上的原动机发动机,或者可用于任何其他合适的应用中。无论如何,在此类系统中,空气被压缩机压缩,然后进入汪克尔发动机,该发动机驱动复合发动机的一个或多个涡轮。在另一实施例中,在没有涡轮增压器并且空气处于大气压力的情况下使用旋转发动机10。
发动机10包括外主体12,外主体20具有轴向间隔的端壁14,周围壁18在它们之间延伸以形成转子腔20。腔20的周围壁18的内表面19具有限定了两个凸角(lobe)的轮廓,其优选地为外旋轮线。
内主体或转子24被接收在腔20中,转子24的几何轴线从外主体12的轴线偏移并且平行于外主体12的轴线。转子24具有邻近于外主体端壁14的轴向间隔的端面26以及在它们之间延伸的周围面28。周围面28限定了三个周向间隔的顶点部分30(仅示出了其中一个)以及具有向外弓形边的大致三角形轮廓。顶点部分30与周围壁18的内表面密封接合以在内转子24和外主体12之间形成三个旋转工作室32(仅部分地示出其中两个)。凹陷38在每对相邻顶点部分30之间被限定在转子24的周围面28中,以形成对应的室32的一部分。
工作室32被密封。每个转子顶点部分30具有顶点密封件52,其从一个端面26延伸到另一个端面并且从周围面28径向突出。每个顶点密封件52通过各自弹簧被径向向外偏压抵靠周围壁18。端部密封件54接合每个顶点密封件52的每个端部,并且通过合适的弹簧被偏压抵靠各自的端壁14。转子24的每个端面26具有至少一个弧形面密封件60,其从每个顶点部分30延伸到每个相邻的顶点部分30,在其整个长度上相邻于转子周围但是在转子周围内侧。弹簧轴向向外地推每个面密封件60,从而面密封件60轴向地突出远离相邻转子端面26并与腔中的相邻端壁14密封接合。每个面密封件60与相邻于其端部的端部密封件54密封接合。
尽管图中未示出,但转子24轴承架设在轴的偏心部分上并且包括与转子轴线共轴的相位调整齿轮,该相位调整齿轮与固定定子相位调整齿轮啮合,固定定子相位调整齿轮与所述轴共轴地被固定到外主体。轴使得转子24旋转,并且啮合的齿轮引导转子24以在定子腔内进行轨道公转。油密封件被设置在相位调整齿轮周围以防止润滑油在各自的转子端面26和外主体端壁14之间从相位调整齿轮径向向外地泄漏流动。
至少一个进入端口(未示出)被限定穿过端壁14之一或周围壁18,以便允许空气(大气或压缩空气)进入工作室32中的一个,并且至少一个排出端口(未示出)被限定穿过端壁14之一或周围壁18,以便允许空气(大气或压缩空气)将排气从工作室32排出。进入和排出端口相对于彼此并相对于点火构件和燃料喷射器(下面进一步描述)定位成使得在转子24的一个轨道公转期间,每个室32在可变体积的情况下围绕定子腔20移动,以经历进气、压缩、膨胀和排气的四个相位,这些相位类似于具有四冲程循环的往复式内燃发动机中的冲程。
在一个具体实施例中,这些端口被布置成使得旋转发动机10在米勒或阿特金森循环的原理下操作,其体积压缩比低于其体积膨胀比。在另一个实施例中,端口被布置成使得体积压缩比和体积膨胀比是彼此相等或近似的。
插入件34被接收在中,用于先导燃料喷射和点火,对应孔36被限定穿过外主体12的周围壁18。周围壁18还具有被限定穿过其中的主喷射器伸长孔40,其与旋转腔20连通并且与插入件34间隔开。主燃料喷射器42被接收并保持在其对应孔40中,主喷射器42的尖端44在与插入件34间隔开的点处与腔20连通。主喷射器42相对于转子旋转和公转的方向R定位在插入件34后方,并且是倾斜的以将燃料向前顺序地引导到每个旋转室32中,具有被设计成用于充分喷洒的尖端孔图案。
特别地参照图2,该插入件包括伸长主体46,伸长主体46延伸穿过周围壁18的厚度,在其外端处具有放大凸缘48,放大凸缘48被偏压离开限定在周围壁18中的肩部50并且抵靠由适当类型的耐热材料(例如基于二氧化硅的材料)制成的衬垫(未示出)。垫圈56(例如钢或钛垫圈)和弹簧58(例如波形弹簧或贝氏弹簧)被设置在凸缘48和周围壁18的肩部50之间。弹簧58偏压主体46抵靠盖62,盖62的横截面大于孔36的横截面,并且盖62在周围壁18的外表面64上延伸。盖62例如通过铜焊连接到周围壁18。也可使用替代类型的连接,包括但不限于经由诸如螺栓的紧固件的连接,以帮助促进插入件的更换(如果需要的话)。
插入件主体46具有内表面66,内表面66与周围壁20的内表面19是连续的,以限定腔20。壁18中的插入件孔36限定了凸缘68,凸缘68在内表面19附近延伸到插入件孔36中,并且插入件主体46的内端具有互补的形状以接合该凸缘68,衬垫70被接收在它们之间。
插入件主体46由耐热性大于周围壁18的材料制成,在一个具体实施例中,周围壁18由铝制成。在该具体实施例中,插入件主体46由适当类型的陶瓷制成。
插入件主体46具有限定在其中的先导子室72,先导子室72与转子腔20连通。在所示的实施例中,子室72具有圆形横截面;替代的形状也是可能的。子室72通过限定在内表面66中的至少一个开口74与腔连通。子室72的形状在邻近于开口74处形成了的减小的横截面,使得开口74限定对于子室72和腔20之间的流动的约束。开口74可具有各种形状和/或由形成图案的多个孔限定。
周围壁18具有被限定穿过其中的先导喷射器伸长孔76,先导喷射器伸长孔76相对于插入件34成一角度并且与子室72连通。先导燃料喷射器78被接收并保持在对应孔76中,先导喷射器78的尖端80被接收在子室72中。
插入件主体46和盖62具有限定在其中的点火元件伸长孔82,点火元件伸长孔82沿外主体12的横向轴线T的方向延伸并且也与子室72连通。点火元件84被接收并保持在对应孔82中,点火元件84的尖端86被接收在子室72中。在所示的实施例中,点火元件84是电热塞。可以使用的替代类型的点火元件84包括但不限于等离子体点火、激光点火、火花塞、微波等。
先导喷射器78和主喷射器42将诸如柴油、煤油(航空涡轮发动机燃料)、等效生物燃料等的重质燃料喷射到室32中。在一个具体实施例中,至少0.5%并且高至20%的燃料通过先导喷射器78喷射,而剩余燃料通过主喷射器42喷射。在另一具体实施例中,至多10%的燃料通过先导喷射器78喷射。在另一具体实施例中,至多5%的燃料通过先导喷射器78喷射。主喷射器42喷射燃料,使得每个旋转室32当处于燃烧相位时均包含空气和燃料的贫燃混合物(lean mixture)。
参照图3,示出了根据另一实施例的插入件134,其接合到相同的外主体12。插入件134延伸穿过周围壁18的厚度并且包括内主体部分146和外主体部分162,内主体部分146和外主体部分162例如通过高温铜焊接头188附接到一起。外主体部分162在其外端具有放大凸缘148,放大凸缘148邻接周围壁18的外表面64并且例如通过螺栓在适当密封的情况下连接到外表面64,所述密封例如为衬垫或挤压密封(未示出)。也可使用替代类型的连接,包括但不限于铜焊连接。
内主体部分146具有内表面166,内表面166与周围壁18的内表面19是连续的,以限定腔20。内主体部分146的内端具有互补的形状以接合在内表面19附近延伸到插入件孔36中的凸缘68,衬垫70被接收在它们之间。
在该具体实施例中,主体部分146、162由适当类型的超级合金制成,例如镍基超级合金。
先导子室72在主体部分146、162之间的结合部处限定在插入件134中,内主体部分146限定了开口74,用于子室72和腔20之间的连通。外主体部分162具有限定在其中的点火元件伸长孔82,点火元件伸长孔82沿横向轴线T的方向并且与子室72连通。点火元件84例如通过螺纹接合被接收并保持在对应孔82中。如前面的实施例中那样,点火元件84的尖端86被接收在子室72中。
参照图4,示出了根据另一实施例的插入件234。插入件234被接收在对应孔236中,对应孔236被限定穿过周围壁18。插入件234包括内主体部分246和外主体部分262,内主体部分246和外主体部分262例如通过高温铜焊接头附接到一起,子室72被限定在两个部分246、262的结合部处。内主体部分246限定了开口74,用于子室72和腔20之间的连通。
外主体部分262具有被限定穿过其中的点火元件伸长孔82,点火元件伸长孔82与子室72连通。外主体部分262包括内放大区段245,其连接到内主体部分246并限定子室72。放大区段245围绕子室72基本上延伸跨过孔236的宽度,然后渐缩到从其延伸的宽度减小区段247。宽度减小区段247在其外端处具有放大凸缘248,其邻接肩部250,肩部250限定在围绕孔236的周围壁18的外表面64中。外区段249(其在所示实施例中具有介于区段245和247之间的宽度)从凸缘248向外延伸。凸缘例如通过螺栓(未示出)在适当密封的情况下连接到肩部,所述密封例如是凸缘248和肩部250之间的由高温材料制成的挤压密封或衬垫(未示出),所述高温材料例如是基于二氧化硅的材料或弹性石墨(grafoil)。也可使用替代类型的连接。
内主体部分具有内表面266,内表面266与周围壁18的内表面19是连续的,以限定腔20。内主体部分246包括在内表面266附近限定在其周围的沟槽,适当的密封件251(例如基于二氧化硅的衬垫带)被接收在沟槽内并且与插入件孔236的壁接触。在该实施例中,插入件孔236的壁在内表面19附近是直的,即在内表面19附近没有凸缘。
插入件34、134、234的子室72的体积被选择成在点火附近的可接受的延迟内获得化学计量的混合物,来自前一燃烧循环的排气产物中的一些留在子室72内。在一个具体实施例中,子室72的体积为排量(排代体积)的至少0.5%并高至3.5%,其中,排量定义为一个室32的最大和最小体积之间的差。在另一具体实施例中,子室72的体积对应于排量的从大约0.625%到大约1.25%。
子室72的体积也可被定义为燃烧体积的一部分,燃烧体积是最小室体积Vmin(包括凹陷38)和子室自身的体积V2的总和。在一个具体实施例中,子室72的体积对应于燃烧体积的从5%到25%,即V2=(V2+Vmin)的5%到25%。在另一具体实施例中,子室72的体积对应于燃烧体积的从10%到12%,即V2=(V2+Vmin)的10%到12%。
子室72可帮助产生稳定且强有力的点火区以点燃总体上贫燃的主燃烧室32,以产生分层冲量燃烧。子室72可改善燃烧稳定性,尤其但不排他地针对旋转发动机而言,旋转发动机用重质燃料在燃料的自点火以下操作。由耐热材料制成的插入件34、134可有利地产生子室周围的热壁,这可进一步有助于燃烧稳定性。
以上描述仅仅意图是示例性的,并且本领域技术人员将会意识到在不偏离所公开的(一个或多个)发明的范围的情况下可对所描述的实施例进行改变。例如,上文描述的汪克尔发动机的机械布置仅仅是适合用于本文的(一个或多个)发明的许多可能构造中的一个示例。可使用任何合适的喷射器构造和布置。因此,根据对本公开的回顾,本领域技术人员将会明白落入本发明范围内的许多修改,并且此类修改意图落入所附权利要求的范围内。
Claims (20)
1.一种旋转发动机,包括:
具有内腔的定子主体,所述内腔由两个轴向间隔开的端壁以及在所述端壁之间延伸的周围壁限定,所述腔具有限定了两个凸角的外旋轮线形状;
具有三个周向间隔的顶点部分的转子主体,所述转子主体接合到轴的偏心部分以在所述腔内旋转并进行轨道公转,其中,所述顶点部分的每一个保持与所述周围壁密封接合并且分开三个可变体积的旋转室,所述旋转室围绕所述转子主体被限定在所述腔中;
在所述转子主体的周围壁中的插入件,所述插入件由耐热性大于所述周围壁的耐热性的材料制成,所述插入件具有限定在其内的子室并具有与所述腔接界的内表面,所述子室通过限定在所述内表面中的至少一个开口与所述腔连通,所述子室的形状在邻近于所述开口处形成减小的横截面;
先导燃料喷射器,所述先导燃料喷射器具有被接收在所述子室内的尖端;
点火元件,所述点火元件具有被接收在所述子室内的尖端;和
主燃料喷射器,所述主燃料喷射器延伸穿过所述壳体并具有在与所述插入件间隔开的位置处与所述腔连通的尖端。
2.如权利要求1所述的发动机,其中,每个室的体积在最小体积和最大体积之间变化,所述最大体积和所述最小体积之间的差限定排量,所述子室的体积至少为所述排量的大约0.5%并且至多为所述排量的大约3.5%。
3.如权利要求2所述的发动机,其中,所述子室的体积至少为所述排量的0.625%。
4.如权利要求2所述的发动机,其中,所述子室的体积为所述排量的大约1.25%。
5.如权利要求1所述的发动机,其中,每个室的体积在最小体积和最大体积之间变化,所述子室的体积对应于所述最小体积和所述子室体积的总和的从5%到25%。
6.如权利要求4所述的发动机,其中,所述子室的体积对应于所述最小体积和所述子室体积的总和的从10%到12%。
7.如权利要求1所述的发动机,其中,所述插入件由陶瓷或超级合金制成。
8.如权利要求1所述的发动机,其中,所述先导喷射器相对于所述插入件成一角度地延伸穿过所述周围壁,所述先导喷射器的仅一部分延伸在所述插入件内。
9.如权利要求1所述的发动机,还包括与所述燃料喷射器连通的重质燃料源。
10.一种汪克尔发动机的定子主体,包括:
两个轴向间隔开的端壁;
周围壁,所述周围壁在所述端壁之间延伸并且与所述端壁一起限定内腔,所述腔具有限定了两个凸角的外旋轮线;
在所述转子主体的周围壁中的插入件,所述插入件由耐热性大于所述周围壁的耐热性的材料制成,所述插入件具有限定在其内的子室并具有与所述腔接界的内表面,所述子室通过限定在所述内表面中的至少一个开口与所述腔连通,所述子室的形状在邻近于所述开口处形成减小的横截面;
所述插入件和所述周围壁中的至少一个具有被限定穿过其中的先导燃料喷射器伸长孔,所述先导燃料喷射器伸长孔与所述子室连通并且所述先导燃料喷射器伸长孔的尺寸设置成在其内接收先导燃料喷射器;
所述插入件和所述周围壁中的至少一个具有被限定穿过其中的点火元件伸长孔,所述点火元件伸长孔与所述子室连通并且所述点火元件伸长孔的尺寸设置成在其内接收点火元件;并且
所述周围壁具有被限定穿过其中的主燃料喷射器伸长孔,所述主燃料喷射器伸长孔与所述插入件间隔开并且所述主燃料喷射器伸长孔的尺寸设置成在其内接收主燃料喷射器。
11.如权利要求10所述的定子主体,其中,所述插入件由陶瓷或超级合金制成。
12.如权利要求10所述的定子主体,其中,所述先导燃料喷射器伸长孔的主要部分被限定穿过所述周围壁。
13.如权利要求10所述的定子主体,其中,所述点火元件伸长孔被限定仅仅穿过所述插入件。
14.一种将重质燃料喷射到汪克尔发动机中的方法,所述汪克尔发动机具有多个旋转室,每个旋转室的体积在最小体积和最大体积之间变化,所述方法包括:
将所述重质燃料的小部分喷射到子室中,所述子室被限定成邻近于并顺序地连通每个旋转室并且具有子室体积,所述子室体积对应于所述最小体积和所述子室体积的总和的从5%到25%;
在所述子室内点燃所述重质燃料;
部分地约束被点燃的重质燃料从所述子室到所述旋转室的流动;以及
与所述子室独立且间隔开地将所述重质燃料的剩余部分顺序地喷射到每个旋转室中。
15.如权利要求14所述的方法,其中,将所述重质燃料的小部分喷射到子室中包括喷射所述重质燃料的从0.5%到20%。
16.如权利要求14所述的方法,其中,将所述重质燃料的小部分喷射到子室中包括喷射所述重质燃料的从5%到10%。
17.如权利要求14所述的方法,其中,在所述子室体积对应于所述最小体积和所述子室体积的总和的从10%到12%的情况下,完成将所述重质燃料的所述小部分喷射到所述子室中。
18.如权利要求14所述的方法,其中,通过所述发动机的周围壁中的插入件并且在所述子室被限定在所述插入件中的情况下,完成所述重质燃料的所述小部分的喷射。
19.如权利要求14所述的方法,其中,以相对于所述发动机的定子的中心横向轴线的倾斜方向完成所述重质燃料的所述小部分的喷射。
20.如权利要求14所述的方法,还包括通过将所述子室设置在由相比所述发动机的定子的其余部分更加耐高温的材料制成的插入件中,用所述子室周围的热壁来帮助燃烧。
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US10697365B2 (en) | 2020-06-30 |
US9038594B2 (en) | 2015-05-26 |
CN102900514B (zh) | 2016-07-13 |
EP2551448A2 (en) | 2013-01-30 |
EP3772566A1 (en) | 2021-02-10 |
CA2782749A1 (en) | 2013-01-28 |
US20190055882A1 (en) | 2019-02-21 |
EP2551448A3 (en) | 2017-03-08 |
ES2830299T3 (es) | 2021-06-03 |
PL2551448T3 (pl) | 2021-07-19 |
EP2551448B1 (en) | 2020-09-02 |
CA2782749C (en) | 2020-10-20 |
US10125676B2 (en) | 2018-11-13 |
US20150240710A1 (en) | 2015-08-27 |
US20130025567A1 (en) | 2013-01-31 |
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