CN111794860A - 用于飞行器的涡轮发动机 - Google Patents
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Abstract
本发明涉及一种用于飞行器的涡轮发动机(10),包括:被构造成向所述飞行器供应压缩空气的压缩空气供应装置(22);被供应至飞行器的压缩空气的冷却系统(20),该冷却系统(20)包括用于在次级流(F2)的流动管道(8)中收集空气的勺斗(12)和涡轮壳体(16)的直径的管理系统(15),该系统(15)被供应有从所述管道(8)收集的空气,并配置为控制该壳体(16)与涡轮转子叶片尖端之间的径向间隙。根据本发明,所述管理系统(15)通过冷却系统(20)的所述勺斗(12)被供应空气。
Description
技术领域
本发明涉及航空领域,更具体地涉及用于飞行器的涡轮发动机。
背景技术
现有技术尤其包括文献EP-A2-0 469 825、FR-A1-3 057 615、EP-A1-0 743 434和EP-A2-2 236 772。
用于飞行器的涡轮发动机通常在气体的流动方向上从上游到下游包括:一个或多个风扇,然后是包括一个或多个压缩机级(例如,低压LP压缩机和高压HP压缩机)的发动机部分,燃烧室,一个或多个涡轮级(例如,高压HP涡轮和低压LP涡轮)以及排气喷嘴。涡轮可以与每个压缩机相对应,二者通过轴连接,从而形成例如高压HP机体和低压LP机体。
压缩机包括转子,该转子包括分别旨在在将空气引入燃烧室之前压缩空气的叶片。同样地,涡轮的转子包括旨在由所述燃烧室产生的燃烧气体驱动以使所述转子旋转的叶片。所有转子被可旋转地安装在环形壳体中,该环形壳体被轴向接连地组装,以形成涡轮发动机的初级流总壳体。
围绕该初级流总壳体(即围绕涡轮发动机的发动机部分)流动的空气流被称为次级流,并由次级流动管道引导。
已知将来自涡轮发动机的空气例如收集到次级流动管道中,以对飞行器的尤其是用于冷却从涡轮发动机的压缩机行进到飞行器的空气的系统进行供给和对涡轮发动机的尤其是用于冷却涡轮环形壳体的系统进行供给,以控制该壳体与涡轮转子之间的间隙。
为了在正确的压力下重新获得这些空气流,将勺斗安装在次级流动管道中。这些勺斗可以是齐平的,即它们由次级流动管道的表面上的单个开口组成,或者可以是动态的,即它们侵入次级流动管道的流中,并具有盖系统以重新获得空气动力学。在任何情况下,这些勺斗都装有阀,这些阀可以调节相应系统的空气流,甚至可以完全切断该空气流。
从空气动力学的角度来看,理想的情况是使次级流动管道尽可能平滑。然而,这些勺斗无论是平齐的还是动态的、流动的或封闭的都是次级流动管道中总压力损失的来源,这直接导致发动机燃料消耗的增加。
此外,这些勺斗可能是风扇的次级流管管道的潜在压力增加的来源,这是噪音污染的气动弹性振动的来源并导致降低风扇的平均效率,以及降低喘振裕度。
另外,在没有产生静压变形和风扇之间的相互作用的该结构时,这些勺斗可能会由于勺斗形成的空腔的共振而成为额外噪音污染的根源。当不再需要对飞行器的系统或推进单元的系统进行冷却并且因此勺斗关闭时,主要出现该问题。
最后,增加勺斗和相关导管以及增加要制造和安装在发动机上的零件数量会增大集成难度。因此,存在与优化这些不同的系统相关的重量影响和生产成本影响。
本发明尤其旨在解决所有或一些上述问题。
发明内容
为此,本发明提出一种用于飞行器的涡轮发动机,该涡轮发动机包括:被构造成向所述飞行器供应压缩空气的压缩空气供应装置,被供应至飞行器的压缩空气的冷却系统,该冷却系统包括用于在次级流的流动管道中收集空气的勺斗以及涡轮壳体直径的管理系统,该系统被供应有从所述管道收集的空气,并且被配置为控制该壳体与涡轮转子叶片尖端之间的径向间隙。根据本发明,所述管理系统通过冷却系统的所述勺斗被供应有空气。
因此,本发明使得可以通过提出单个勺斗来满足多个系统、尤其是冷却系统和管理系统的需求来减少勺斗的数量。因此,本发明使得可以减少勺斗在次级流动管道中的总体侵入。因此,这减少了次级流动管道中的流的干扰。
此外,尤其是,单个勺斗使得无论是对于飞行器的系统还是对于涡轮发动机的系统一直处于流动,这限制了在关闭勺斗时发生的勺斗的声共振问题。
对该单个勺斗的形状进行优化使得可以向系统提供更高的性能(可能使系统被更好地设计尺寸,以实现相同的功能)。
根据本发明的涡轮发动机可包括以下特征中的一个或多个,这些特征可彼此独立地或彼此组合地采用:
-所述勺斗位于使中间壳体的辅助装置通过的管状臂上,
-所述臂位于次级流的成环形排布置的整流器的下游,这些整流器位于风扇的下游,
-整流器的前缘和臂的前缘基本上位于同一平面中,该平面与涡轮发动机的纵向轴线垂直,
-勺斗位于所述臂与限定所述管道的内表面的内环形壁之间的接合部处,
-所述内环形壁包括压缩机的至少一个用于排出空气的出口格栅,
-所述至少一个格栅相对于次级流的流动位于所述勺斗的上游,
-勺斗通过支路分别连接到管理系统和冷却系统的两个供应通道,该支路位于所述臂中。
附图说明
通过阅读作为非限制性示例提供的并参考附图进行的以下描述,将更好地理解本发明,并且本发明的其他细节、特征和优点将更加清楚地显现,其中:
图1是根据本发明的涡轮发动机的纵向截面局部示意图。
具体实施方式
参考图1,双流涡轮发动机通常在气流的方向上从上游到下游包括:一个或多个风扇1;然后是发动机部分,发动机部分包括一个或多个低压2然后是高压3压缩机级;燃烧室4;一个或多个高压5然后是低压6涡轮级;以及主气体的排放喷嘴7。绕涡轮发动机的纵向轴线LL旋转并且能够通过不同的传动系统和齿轮联接在一起的转子对应于这些不同的元件。压缩机转子可旋转地安装在环形压缩机壳体中。以相同的方式,涡轮转子可旋转地安装在环形涡轮壳体16中。压缩机和涡轮壳体接连轴向地组装以形成总壳体。
在此,由风扇驱动的空气流被分成进入与发动机部分相对应的主回路的部分F1(即,进入总壳体内部的部分)和次级流部分F2,次级流部分明显有助于由涡轮发动机提供的推力。次级流F2在次级流F2的流动管道8中围绕发动机部分通过。管道8包括相对于纵向轴线LL同轴的两个环形壁31、32,分别是内环形壁31和外环形壁32。
通常,涡轮发动机配备有至少一个用于使辅助装置(例如空气导管、油导管、电缆等)通过的系统18,使得辅助装置可以穿过管道(例如次级流F2的流动管道8),从而使该流的干扰最小化。
辅助装置可以将径向地位于管道内部的第一设备连接到径向地位于管道外部的第二设备(相对于涡轮发动机的纵向轴线LL使用表述“径向地”)。
如图1所示,用于使辅助装置在管道8中通过的系统18通常包括中间壳体,该中间壳体具有两个环形且同轴的护罩,分别是内护罩10和外护罩9。
这两个护罩9、10通过至少一个基本径向的管状臂11连接,该臂包括用于使辅助装置通过的内部容纳空间。护罩9、10在用于使辅助装置通过的系统18的水平处形成管道8的内环形壁31和外环形壁32的连续性。
通常,用于使辅助装置通过的系统18的一个或多个臂11沿管道8中的空气流的主要流动方向成形并与该方向对准,以限制该流的扰动并减小压降。臂11在此包括前缘13,次级流F2旨在通过前缘13与臂11发生接触,前缘被成形以限制由次级流F2引起的干扰。
涡轮发动机10进一步包括压缩空气的供应装置22,该压缩空气的供应装置被构造成将压缩空气供应到飞行器。
涡轮发动机还包括冷却系统20,该冷却系统旨在冷却由供应装置22供应给飞行器的压缩空气。冷却系统20包括用于在次级流F2的流动管道8中收集空气的勺斗12。冷却系统20在此包括供应通道17,使得可以将由勺斗12收集的空气输送到供应装置22。
涡轮发动机10进一步包括涡轮发动机壳体16的(尤其是低压涡轮6的)直径的管理系统15,该管理系统15被配置成尤其是通过对壳体16进行冷却来控制该壳体16与涡轮转子的叶片尖端之间的径向间隙。
根据本发明,管理系统15通过冷却系统20的勺斗12被供应空气。管理系统15在此包括供应通道14,该供应通道14可以将勺斗12收集的空气输送到涡轮壳体16。
因此,本发明可以使用单个勺斗12来向冷却系统20和管理系统15两者供应冷却空气。
管理系统15和冷却系统20的两个相应的供应通道14、17形成支路,该支路在此位于臂11中。具体地,勺斗12位于臂11中,使得支路在臂11内部被连接至勺斗12。
因此,供应通道14进入臂11并穿过护罩10,以将从次级流F2收集的冷却空气带到管理系统15,从而调节涡轮壳体16与涡轮转子的叶片之间的间隙。以相同的方式,供应通道17进入臂11并穿过护罩9,以便向压缩空气供应系统22供应冷却空气。
将勺斗12和支路定位在臂11中的作用是使得可以释放涡轮发动机的发动机部分中的空间,鉴于发动机部分非常笨重的事实,这是特别有利的。
勺斗12可以是齐平的,即勺斗由在管道8的表面上的单个开口组成,或者是动态的,即勺斗侵入管道8的流中,并且具有盖系统以重新获得空气动力学。在任何情况下,勺斗都配备有一个或多个阀,这些阀可以调节相应系统的空气流,甚至可以完全切断空气流。
在所示的示例中,勺斗12包括第一阀19,该第一阀具体位于供应通道17的入口处,并且可以调节由勺斗12收集并被冷却装置20输送的空气流。在该示例中,勺斗12包括第二阀21,第二阀具体位于供应通道14的入口处,并且可以调节由勺斗12收集并被管理系统15输送的空气流。
在未示出的实施例中,涡轮发动机包括单个调控阀,单个调控阀被布置成既调节供应通道14的流,又调节供应通道17的流。
勺斗12例如位于臂11的前缘13附近。勺斗具体位于臂11与限定管道的内表面的内环形壁31之间的接合部处。
涡轮发动机10进一步包括次级流8的成环形排布置的整流器23(在图1中以虚线表示)。
整流器23包括前缘24,在这种情况下,前缘24与臂11的前缘13一起位于同一平面中,该平面与涡轮发动机的纵向轴线LL垂直,该平面是图1的图平面。
内环形壁31包括一个或多个压缩机2、3的至少一个空气排放出口格栅26。格栅26相对于次级流F2的流动位于勺斗12的上游。
Claims (8)
1.一种用于飞行器的涡轮发动机(10),包括:
-压缩空气供应装置(22),所述压缩空气供应装置被构造成向所述飞行器供应压缩空气,
-被供应至所述飞行器的压缩空气的冷却系统(20),该冷却系统(20)包括用于在次级流(F2)的流动管道(8)中收集空气的勺斗(12),以及
-涡轮壳体(16)的直径的管理系统(15),该系统(15)被供应有从所述管道(8)收集的空气,并且被配置为控制该壳体(16)与涡轮转子叶片尖端之间的径向间隙,
其特征在于,所述管理系统(15)通过所述冷却系统(20)的所述勺斗(12)被供应空气。
2.根据权利要求1所述的涡轮发动机(10),其特征在于,所述勺斗(12)位于使中间壳体的辅助装置通过的管状臂(11)上。
3.根据权利要求2所述的涡轮发动机(10),其特征在于,所述臂(11)位于所述次级流(28)的成环形排布置的整流器(23)的下游,这些整流器位于风扇(1)的下游。
4.根据权利要求3所述的涡轮发动机(10),其特征在于,所述整流器(23)的前缘(24)和所述臂(11)的前缘(13)基本上位于同一平面中,该平面与所述涡轮发动机(10)的纵向轴线(LL)垂直。
5.根据权利要求2至4中任一项所述的涡轮发动机(10),其特征在于,所述勺斗(12)位于所述臂(11)与限定所述管道(8)的内表面的内环形壁(31)之间的接合部处。
6.根据权利要求5所述的涡轮发动机(10),其特征在于,所述内环形壁(31)包括压缩机的至少一个空气排放出口格栅(26)。
7.根据权利要求6所述的涡轮发动机(10),其特征在于,所述至少一个格栅(26)相对于所述次级流(F2)的流动位于所述勺斗(12)的上游。
8.根据权利要求2至7中任一项所述的涡轮发动机(10),其特征在于,所述勺斗(12)通过支路连接至所述管理系统(15)和所述冷却系统(20)的两个相应的供应通道(14,17),该支路位于所述臂(11)中。
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EP3722559A1 (fr) | 2020-10-14 |
FR3095005A1 (fr) | 2020-10-16 |
FR3095005B1 (fr) | 2021-03-19 |
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