CN107849937A - 涡轮中间框架辐条冷却系统及方法 - Google Patents
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Abstract
一种涡轮中间框架模块包括外结构环、内结构环,和将内结构环与外结构环在结构上相互连接的多个周向地间隔分开的辐条。所述管状辐条中的至少一个辐条容纳维护管线。不具有维护管线的其余辐条具有模拟装纳维护管线的所述至少一个辐条的空气冷却方案的内部构造,以便遍及所有辐条提供温度均匀性。
Description
相关申请的交叉引用
本申请要求于2015年7月24日提交的美国临时专利申请第62/196,380号、2015年7月24日提交的美国临时专利申请第62/196,500号以及2015年7月24日提交的美国临时专利申请第62/196,368号的优先权,上述申请的全部内容通过引用并入本文。
技术领域
本申请大体涉及燃气涡轮发动机,并且更具体地涉及用于冷却涡轮中间框架模块的结构辐条的冷却装置。
背景技术
已知使用结构辐条将载荷从轴承壳体传递到燃气涡轮发动机的外结构环。比如,可以在涡轮中间框架模块中找到这种辐条。每个辐条通常从外环径向地延伸通过气体路径中的支柱到达支撑轴承壳体的内环。在发动机操作期间,模块周围各处的辐条必须维持在大致相同的温度下,以防止由于辐条之间的不同热生长导致轴承变得偏离中心。
发明内容
在一方面中,提供一种涡轮中间框架模块,其包括外结构环、支撑轴承的内结构环、将所述内结构环与所述外结构环在结构上相互连接的多个周向间隔分开的管状辐条,所述管状辐条中的至少一个辐条容纳轴承维护管线,不具有轴承维护管线的其余管状辐条具有模拟所述至少一个辐条的空气冷却方案的内部构造以遍及所有所述辐条提供温度均匀性。
根据另一方面,在不装纳维护管线的所述管状辐条内侧提供管状插入件,在所述辐条和所述插入件之间限定环形间隙。
根据另一方面,提供流量校准孔以校准通过所述环形间隙的冷却空气。
根据另一方面,提供一种用于燃气涡轮发动机的涡轮中间框架,所述涡轮中间框架包括:外结构环、内结构环、所述内结构环与所述外结构环之间的环形气体路径、径向延伸穿过所述气体路径的多个周向地间隔分开的中空支柱、多个周向地间隔分开的管状辐条,所述管状辐条相应地在内部延伸通过所述中空支柱,所述管状辐条在结构上连接到所述内结构环和所述外结构环,所述管状辐条中的至少一个装纳维护管线,管状辐条中的其余辐条具有延伸穿过其的套筒,限定为居中地通过所述套筒的内部冷却剂流动通道和限定在套筒和管状辐条之间的环形冷却剂流动通道,内部冷却剂流动通道和环形冷却剂流动通道在其相应的邻近端部处以串行流动连通的方式连接并且与冷却剂液体源连接以提供从径向向内方向到径向向外方向的冷却剂反向流动路径。
根据另一方面,提供一种用于燃气涡轮发动机涡轮中间框架模块的辐条冷却装置,所述辐条冷却装置包括多个周向地间隔分开的管状辐条,所述管状辐条将内结构环与外结构环在结构上相互连接,所述管状辐条中的至少一个装纳维护管线,所述辐条冷却装置包括:主冷却剂流动通道,所述主冷却剂流动通道延伸通过每个不具有维护管线的辐条;以及反向流动通道,所述反向流动通道与所述主冷却剂流动通道串行地相互连接,以便使至少一部分冷却剂沿与主冷却剂流动通道的方向相对的方向回流至相关联的辐条中。
根据又一大体方面,提供一种冷却燃气涡轮发动机涡轮中间框架模块的结构辐条的方法,其中至少一个结构辐条装纳维护管线;对于每个不装纳维护管线的结构辐条,所述方法包括:引导冷却剂流径向向内地通过限定为轴向地通过所述结构辐条的主流动通道,并且将从所述主流动通道接收的所述冷却剂流的至少一部分径向向外地重新引导至轴向地延伸通过每个不具有维护管线的结构辐条的反向流动通道内。
附图说明
现在参考附图,附图中:
图1是燃气涡轮发动机的示意性横截面视图;
图2是安装在发动机外壳中的涡轮中间框架模块的等距视图;
图3是在没有发动机外壳的情况下示出的涡轮中间框架的等距视图;
图4是涡轮中间框架的一部分的放大视图,其图示用于遍及整个模块均匀地分配冷却空气并避免在模块中形成局部冷点的进气装置;
图5是图4中所示的进气装置的横截面视图;
图6a是涡轮中间框架模块的一部分的横截面视图,其图示通过辐条中的一个的冷却流动方案;
图6b是图6a中所示的辐条冷却流动方案的径向内端部部分的放大视图;
图6c是图6a中所示的辐条冷却流动方案的径向外端部部分的放大视图;
图7a是涡轮中间框架模块的端视图,其图示用于不容纳任何维护管线的结构上专用的辐条的第一冷却回路,和用于与轴承壳体维护管线一体化的顶部辐条和底部辐条的第二冷却回路,这两个回路被分开以避免空气污染;
图7b是第一冷却回路的径向内部出口端部部分的放大横截面视图;和
图7c是第二冷却回路的径向外部出口端部部分的放大横截面视图。
具体实施方式
图1示出优选地设置为用于在亚音速飞机中使用的类型的涡轮风扇式燃气涡轮发动机10,其大体包括串行流动连通的风扇12,通过该风扇12推动周围空气;用于对空气加压的多级压缩机14;燃烧器16,在该燃烧器16中压缩空气与燃料混合并被点燃以便生成热燃烧气体的环形流;以及用于从燃烧气体提取能量的涡轮区段18。
图2和3示出涡轮区段18的一部分。更具体地,图2示出装纳在发动机外壳21内的涡轮中间框架模块20。如图3中所示,涡轮中间框架模块20包括适于接收和支撑轴承壳体23的内结构环22,该轴承壳体23相应地适于支撑发动机10的主轴。轴承壳体23可以借助于螺栓等可拆卸地安装于内环22。
内轴承支撑环22由外结构环24借助于多个周向分布的管状辐条26(在所示实施例中为6个)在结构上支撑。除了将载荷从内环22传递到外环24之外,辐条26还使内环22且因此使轴承壳体23相对于外环24居中。术语“管状辐条”在本文中旨在大体上指代中空的辐条结构,并且不限于任何具体横截面形状。
每个辐条26可以径向地延伸通过“浮动地”安装在内结构环22和外结构环24之间的非结构一体式支柱-叶片(ISV)壳体28的中空支柱29a、b(图6a),以便在两个轴向邻近的涡轮级之间导引燃烧气体。ISV壳体28具有径向外气体路径壁28a和径向内气体路径壁28b(图5和图6a),其间限定涡轮区段18的气体路径的一部分。根据所示实施例,ISV壳体28不起结构作用。即来自轴承壳体23的载荷不经由ISV壳体28传递至外壳体24。而是载荷被传递通过辐条26,辐条26由ISV壳体28的中空支柱29屏蔽免受热燃烧气体的影响。在这样的装置中,辐条能够被称为冷辐条。
在发动机操作期间,所有辐条26需要被保持在大致相同的温度下,以便防止轴承壳体23变得偏离中心。事实上,如果辐条26具有不同的热生长,则可能丧失内环22相对于外环24的同心度,并且因此轴承居中性受损。因此,需要遍及整个模块20将冷却剂均匀地分配到辐条26的一种方式,使得所有辐条26的温度大致相同。此外,当在模块20中引入冷却剂(例如压缩机引气)时,冷却剂应当被引导以避免在外环24上产生局部冷点,这也能够影响轴承居中性。
根据一个实施例,可以使用单个外部管子(未示出)以将诸如来自发动机10的压缩机的引气的冷却剂引导至涡轮中间框架模块20。如图2中所示,在发动机外壳21上设置有用于接收来自外部管子的冷却空气的端口30。然后将来自发动机外壳进气端口30的冷却空气引导至安装于外结构环24的进气管道32内。根据图4中所示的实施例,进气管道32可以以具有入口分支32a和一对出口分支32b的大体T形管道的形式设置,其中入口分支32a径向延伸通过限定在外环24中的孔34,该对出口分支32b在外环24的径向内侧上从入口分支32a的相对侧横向延伸。出口分支32b大体沿周向相对的方向延伸并具有连接到出口端口36的相应出口端部,所述出口端口36在孔34的相对侧上设置在外环24上。进气管道32可以由片材金属、铸件或任何其它合适的材料制成。
如图5中所示,进气管道的出口分支32b沿周向相对的方向将冷却空气排出到限定在发动机外壳21与外环24之间的环形腔40内。环形腔40围绕整个模块形成空气室。如图3中所示,空气室与辐条和辐条22定位在其中的中空支柱流动连通。通过在环形空气室中建立空气压力,可以遍及整个腔40将冷却空气均匀地分配至辐条26。这提供了内部核心通道构造,其以周向方式分配冷却空气以避免涡轮中间框架模块外环结构中的不相等的金属温度。而且,能够理解的是,进气管道32防止到来的冷却空气直接抵靠外环24局部地排出,由此避免邻近辐条26中的一个在其上产生局部冷点。而是进气管道32将到来的冷却空气流分开,并将其以径向向外和周向分量重新引导到外环24与发动机外壳21之间的环形腔40内。空气撞击在发动机外壳21上,并因此不撞击在用于使内轴承壳体23与辐条26居中的外环24上。这有助于保持轴承居中性。
而且,上述实施例消除了可能对发动机的总重量具有不可忽略的影响的多个空气冷却馈送管子的使用。其也允许在受限区域中引入冷却空气。也能够容易地更换空气管道内部进气(intake)。
根据实施例,使用六个辐条来支撑轴承壳体23并使其居中。辐条26中的两个(一个在模块的底部处且一个在模块的顶部处)也被用于容纳轴承壳体维护管线50,诸如油管路。图6a图示包含组合的结构辐条26a和轴承壳体维护管线50的第一中空翼型支柱29a和包含结构上专用的辐条26b(无油维护管线的辐条)的第二中空翼型支柱29b的示例。两个结构辐条26a及其内部轴承维护管线50和四个结构上专用的辐条26b必须被保持在大致相同的温度下以确保转子居中。这可以通过在四个结构上专用的辐条中的每个中设置模拟通过容纳轴承维护管线50的两个辐条的空气流通的内部构造来实现。
同时参考图6a至图6c,能够认识到的是,可以在四个结构上专用的辐条26b中的每个中设置套筒或管状插入件52,以形成内部环形间隙或环形反向流动通道54,其大体对应于组合的辐条26a和轴承壳体维护管线50与相关联的环绕支柱29a之间的那个内部环形间隙或环形反向流动通道。同时参考图6a至图6c和图7a,能够认识到的是,在环形腔40与四个结构上专用的辐条26b之间形成第一冷却回路。冷却空气从环形腔40径向向内流动通过由安装在结构上专用的辐条26b的每个内的管状插入件52限定的内部主冷却剂流动通道。如图7b中所示,从每个辐条26b的插入件52排出的空气被接收在限定在内环22与每个辐条26b的径向内端部之间的腔室80中。该空气的第一部分通过内环22中的孔82排出,并且然后被引导以净化邻近涡轮转子95的上游盘腔93。如图6b中最佳地示出的,从每个插入件52排出的冷却空气的其余部分在环形反向流动通道54中回流通过辐条26b。在每个辐条26b的径向外端部处设置流量校准孔或其它合适的流量校准设备56,以校准冷却空气经过每个环形间隙54的流量。孔56被校准,使得径向向外流动通过环形间隙54的冷却空气的那部分维持辐条26b大致处于与装纳内部轴承维护管线50的顶部和底部辐条26a的温度相同的温度。如图6c中所示,在辐条26b的径向外端部部分中限定出口孔58以排出ISV壳体28与外环24之间的冷却空气。该流动路径模拟围绕用于油管路/轴承维护管线50的顶部和底部辐条26a(图7a)的冷却流动路径。这种配置确保所有具有和不具有轴承壳体维护管线的结构辐条26均被保持在相同的温度下,由此确保贯穿发动机操作范围的轴承壳体居中性。在现有技术中,必须针对结构辐条和轴承维护管线使用单独的支柱。在新提出的装置中,维护管线和辐条能够定位在相同的中空支柱中。这减少了气体路径中大的中空支柱的数量。其允许冷辐条设计的涡轮中间框架被用于物理上更小的发动机中。不同类型的辐条之间的冷却流动的均匀性确保轴承壳体同心性,同时允许各种硬件组合横过ISV气体路径组合。
参照图7a和7c,能够认识到的是,冷却系统包括第二冷却回路,该第二冷却回路与上文所描述的用于四个结构上专用的辐条26b的第一冷却回路分开。第二冷却回路向装纳维护管线50的顶部辐条和底部辐条26a提供冷却。如从图7a能够认识到的,底部辐条26a与延伸通过其的维护管线50之间的环形间隙以流体流动连通方式与环形腔或空气室40连接。空气从底部辐条26a排入限定在内环22、轴承壳体23和螺栓连接到内环22的后盖92(图7b)之间的密封的环形腔室或腔90。冷却空气从底部辐条26a周向地行进通过环形腔90到达顶部辐条26a。如图7a中所示,冷却空气经由限定在顶部辐条26a与延伸通过其的维护管线50之间的环形间隙离开环形腔90。如图7c中所示,空气通过出口孔94在维护管线50的径向外端部处排出。本领域技术人员将认识到的是,在发生油失效的情况下,顶部辐条和底部辐条26a被用于排放管线的馈送/净化空气和油。在发生油泄漏的情形中,通过四个结构上专用的辐条26b的第一回路中的空气将不会被流动通过装纳维护管线50的顶部辐条和底部辐条的空气污染。
使用四个结构上专用的辐条26b将二次冷却空气从腔40馈送到上游转子的腔盘也有助于减少管子和管路的数量。实际上,辐条被用作空气馈送管路,以将冷却空气引导到邻近涡轮部件,由此减少待安装在发动机上的零件的数量。
以上描述仅意在是示例性的,并且本领域技术人员将认识到的是,可以在不背离所公开的本发明的范围的情况下对所描述的实施例做出改变。根据对本公开的审视,落入本发明的范围内的任何修改对于本领域技术人员而言都将是显而易见的,并且此类修改旨在落入所附权利要求内。
Claims (20)
1.一种用于燃气涡轮发动机的涡轮中间框架,所述涡轮中间框架包括:外结构环、内结构环、所述内结构环与所述外结构环之间的环形气体路径、径向地延伸穿过所述气体路径的多个周向地间隔分开的中空支柱、多个周向地间隔分开的管状辐条,所述管状辐条相应地在内部延伸通过所述中空支柱,所述管状辐条在结构上连接到所述内结构环和所述外结构环,所述管状辐条中的至少一个装纳维护管线,所述管状辐条中的其余管状辐条具有延伸通过其的套筒,内部冷却剂流动通道限定为居中地通过所述套筒,且环形冷却剂流动通道限定在所述套筒和所述管状辐条之间,所述内部冷却剂流动通道和所述环形冷却剂流动通道在其相应的邻近端部处以串行流动连通方式连接,并且与冷却剂液体源连接以提供从径向向内方向至径向向外方向的冷却剂反向流动路径。
2.根据权利要求1所述的涡轮中间框架,其特征在于,还包括位于所述内部冷却剂流动通道与所述环形冷却剂流动通道之间的流量校准设备。
3.根据权利要求2所述的涡轮中间框架,其特征在于,所述流量校准设备以限定在所述管状辐条中的所述其余管状辐条的径向内端部处的流量校准孔的形式提供。
4.根据权利要求1所述的涡轮中间框架,其特征在于,所述内环与所述管状辐条中的所述其余管状辐条的径向内端部之间限定腔室,所述腔室与所述内部冷却剂流动通道和所述环形冷却剂流动通道二者流体流动连通,并且其中净化孔被限定在所述腔室中,所述净化孔与邻近涡轮转子的上游盘腔流动连通。
5.根据权利要求1所述的涡轮中间框架,其特征在于,所述外结构环由环形空气室围绕,并且其中所述管状辐条中的所述其余管状辐条在其径向外端部处与所述环形空气室以流体流动连通方式连接。
6.根据权利要求5所述的涡轮中间框架,其特征在于,还包括进气管道,所述进气管道具有入口分支和从所述入口分支的相对侧横向延伸的一对出口分支,所述出口分支大体沿周向相对的方向延伸并且具有相应的与所述环形空气室流动连通的出口端部。
7.根据权利要求6所述的涡轮中间框架,其特征在于,所述进气管道安装于所述外结构环的径向内侧,并且其中所述出口分支的出口端部连接到限定为在限定在所述外结构环中的中央入口端口的相对侧上通过所述外结构环的相应出口端口,并且所述进气管道的入口分支安装于所述中央入口端口。
8.根据权利要求1所述的涡轮中间框架,其特征在于,所述管状辐条中的所述其余管状辐条和安装在其中的所述套筒一起限定内部构造,所述内部构造模拟装纳所述维护管线的所述至少一个辐条的空气冷却方案,由此允许遍及所有所述结构辐条的温度均匀性。
9.根据权利要求1所述的涡轮中间框架,其特征在于,出口孔限定在所述管状辐条中的所述其余管状辐条的径向外端部部分中,以从所述环形冷却剂流动通道排出冷却剂。
10.根据权利要求1所述的涡轮中间框架,其特征在于,所述内部冷却剂流动通道具有分别设置在所述套筒的径向外端部和径向内端部处的入口和出口,并且其中所述环形冷却剂流动通道具有分别设置在相关联的所述辐条的径向内端部和径向外端部处的入口以及出口。
11.根据权利要求1所述的涡轮中间框架,其特征在于,所述内结构环支撑轴承壳体,并且其中所述维护管线包括轴承壳体维护管线。
12.一种用于燃气涡轮发动机涡轮中间框架模块的辐条冷却装置,其包括多个周向地间隔分开的管状辐条,所述管状辐条将内结构环与外结构环在结构上相互连接,所述管状辐条中的至少一个装纳维护管线,所述辐条冷却装置包括:主冷却剂流动通道,其延伸通过每个不具有维护管线的辐条;以及反向流动通道,其串行地与所述主冷却剂流动通道相互连接,以便使所述冷却剂的至少一部分沿与所述主冷却剂流动通道的方向相对的方向回流至相关联的所述辐条中。
13.根据权利要求12所述的辐条冷却装置,其特征在于,所述主冷却剂流动通道具有分别设置在相关联的所述管状辐条的径向外端部和径向内端部处的入口和出口,并且其中所述反向流动通道具有分别设置在相关联的所述管状辐条的径向内端部和径向外端部处的入口和出口。
14.根据权利要求12所述的辐条冷却装置,其特征在于,在使用中,冷却剂沿径向向内方向行进通过所述主冷却剂流动通道,所述反向流动通道接收来自所述主冷却剂流动通道的冷却剂,以便使其沿径向向外方向回流通过相关联的所述辐条。
15.根据权利要求12所述的辐条冷却装置,其特征在于,管状插入件设置在每个所述不具有维护管线的管状辐条内,所述主冷却剂流动通道延伸穿过所述管状插入件,并且其中所述反向流动通道由所述管状插入件和相关联的所述管状辐条之间的环形部限定。
16.根据权利要求12所述的辐条冷却装置,其特征在于,还包括位于所述主冷却剂流动通道和所述反向流动通道之间的流量校准设备。
17.根据权利要求16所述的辐条冷却装置,其特征在于,所述流量校准设备以被限定在每个所述不具有维护管线的管状辐条的径向内端部处的流量校准孔的形式提供。
18.根据权利要求12所述的辐条冷却装置,其特征在于,每个所述管状辐条由中空支柱屏蔽开所述内结构环和所述外结构环之间的环形气体路径。
19.一种冷却燃气涡轮发动机涡轮中间框架模块的结构辐条的方法,其中,至少一个所述结构辐条装纳维护管线;针对每个不装纳维护管线的所述结构辐条,所述方法包括:引导冷却剂流径向向内地通过限定为轴向通过所述结构辐条的主流动通道,并且将从所述主流动通道接收的所述冷却剂流的至少一部分径向向外地重新引导至轴向地延伸通过每个不具有维护管线的结构辐条的反向流动通道内。
20.根据权利要求19所述的方法,其特征在于,在每个不具有维护管线的结构辐条中设置管状插入件,并且其中引导所述冷却剂流径向向内地通过主流动通道包括引导所述冷却剂径向向内通过所述管状插入件,并且其中引导所述冷却剂流径向向外进入反向流动通道中包括引导从所述管状插入件接收的所述冷却剂流进入所述管状插入件与相关联的所述结构辐条之间的环形部内。
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US10914193B2 (en) | 2021-02-09 |
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CA2936180A1 (en) | 2017-01-24 |
US20170107851A1 (en) | 2017-04-20 |
US10920612B2 (en) | 2021-02-16 |
CN107849937B (zh) | 2020-06-19 |
WO2017015746A1 (en) | 2017-02-02 |
CA2936182C (en) | 2023-08-15 |
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