CN101144394B - 可变几何涡轮 - Google Patents
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Abstract
一种可变几何涡轮,特别是燃气涡轮,包括外壳(22)、涡轮转子(4)、环绕所述涡轮转子的流体入口(1)和设置在所述流体入口和所述涡轮转子之间用于加速流体流动的叶片式喷嘴,所述喷嘴包括用于改变喷嘴间隙(23)并有轴向划界所述喷嘴间隙的壁(19)的轴向可调节环(25),所述壁具有连接所述喷嘴间隙与所述外壳和所述环界定的室(12)的平衡孔(26、26’),其特征在于:所述孔和所述壁面向所述喷嘴间隙的表面(18)所形成的边缘(16)在孔的关于流体流动的下游的部分(17、17’)形成宽大倒圆角。含有所述涡轮的涡轮增压器和增压式内燃机。
Description
技术领域
本发明涉及一种特别是用于增压式内燃机的涡轮增压器的可变几何涡轮,以及该涡轮增加器和发动机。
背景技术
现有的可变几何涡轮(VGT)具有环绕涡轮转子的涡管形式的驱动流体入口和设置在所述入口涡管和涡轮转子之间的叶片式环形喷嘴。在移动壁(movingwall)型的可变几何涡轮上,喷嘴间隙轴向可调,以控制涡轮功率,以及在增压式内燃机的可变几何涡轮增压器的情况下,控制发动机的排气歧管的背压(当作为排气制动时,这尤为有用)。
图1展示了一个典型的移动壁型的可变几何涡轮。该图展示了根据包含涡轮转子4的轴10的平面的纵向截面。流体入口涡管用1表示。使得流体从进口涡管进入涡轮转子3的环形喷嘴间隙用3表示,喷嘴的叶片由7表示。叶片固定在轴向可调环5,可在箭头A方向移动。在一个方向移动减少喷嘴间隙,相反方向移动则增加喷嘴间隙。当可调环沿闭合方向移动时,叶栅进入设置在涡轮壳2的环形腔11中。穿通的垫8,其槽口对应于叶栅的形状,可以用于防止流体溢出喷嘴间隙。作为选择,可以设置这样的结构:固定的叶栅设置在壁上并与轴向可调环相对,该轴向可调节环设置有容纳叶片的槽。可调节环可设计成环形活塞,该环形活塞可被容纳在环形室12内,并可以移动出,伸入喷嘴间隙;密封元件13,例如外密封环和内密封环,设置在可调节环和所述室的墙壁之间。执行***(图中未显示)用来根据需要控制可调节环的轴向位置。该执行器可以为气动、液动或电动,并可包括复位弹簧,可被设置在可变几何涡轮外壳的内部或外部。它可通过,例如,沿轴向可调节环的运动方向延伸的杆起作用,该杆依附在环形室12侧面的环5上。所述杆(或者任何类似的导向***)可以防止可调节环绕轴10旋转,这种旋转是由流体力作用倾斜的叶片而产生的。执行器必须支撑流体压力作用在轴向可调节环上的复位力,该复位力可具有相当大。为了减少作用在执行器和执行机构的复位负载,通常在可调节环的轴向壁上设置平衡孔6,通常每个在两个相邻叶片之间的流体通道设有一个孔,如图2所示,以平衡喷嘴间隙3和室12之间的压力。
在排气驱动涡轮上,平衡孔的尺寸必须设置为允许往复式发动机产生的排气波适当传输,该发动机例如标准内燃机。否则,压力波可产生振动而磨损整个可变几何涡轮执行机构,以及其他元件,比如密封件和轴衬。此外,压力波能引起执行机构的明显振动,至少是对一定类型的执行器,特别是气动和电动的执行器。为了保持在可以接受的程度上振动,平衡孔的尺寸必须相对大,其直径可达到流体通道宽度的90%。这包含的缺点是,平衡孔导致了对流经喷嘴间隙的流体的相当大扰乱。降低喷嘴间隙,即分别缩窄相邻叶片间的流体通道,增加了孔和流体流的干涉。在很狭窄的喷嘴间隙,喷嘴间隙的剩余流动面积变得小于平衡孔的总体面积。在这种情况下,平衡孔使流动产生明显下沉,导致流体大量流入孔中,平衡孔的下游边缘存在明显流体动力障碍。
在现有的平衡孔中,平衡孔为机械或者激光切割,并具有相对锋利边缘(从流体动力的角度),尽管可以设置小沉头来去除毛刺。从而,平衡孔边缘的下游部分可以引起分流,导致流动通道下游的孔内不希望的压力下降,从而导致作用在可调节环的复位力减小。这种效果在小喷嘴间隙和扼流情况下特别明显,这种情况下在喷嘴间隙达到声速。在该情况下,最终作用在轴向可调节环的复位力将急剧下降,并可产生相反的力方向。
在图3中,典型的作用在可调节环上从而作用在整个执行机构的复位力F(纵坐标)表示为喷嘴间隙L(横坐标)的函数。随着喷嘴间隙的减少,几乎整个可调节区域的复位力逐渐增加,同时在狭窄的喷嘴间隙,由于孔和流体流动的干涉,力衰弱。在小喷嘴间隙安全控制可变几何喷嘴变得不可能,限制了可接受的喷嘴间隙值,这些值远大于在特定操作情况下所需的值。一般而言,现有***的控制不能满足小的喷嘴间隙。因此,可变几何涡轮增压式发动机的涡轮制动力(发动机制动力)受到限制,瞬态工况下发动机的响应也受限制。
发明内容
本发明解决了上述问题,在平衡孔的下游边缘形成大倒圆,处于面向流体流动的平衡孔的口。
根据本发明的一个优选实施例,涡轮为燃气涡轮,特别是增压式内燃机的涡轮增压器的涡轮,所述涡轮增压器和发动机为本发明的进一步实施方式。
附图说明
下面将结合附图和具体实施例对本发明作进一步描述,其中:
图1为现有技术的可变几何涡轮的纵剖面示意图(以上已经描述);
图2为图1的可变几何涡轮中从喷嘴间隙向着轴向可调节环的平面示意图(以上已经描述);
图3示意性地展示了根据现有技术的设置有轴向可调节环的可变几何涡轮中,作用在轴向可调节环的复位力与喷嘴间隙的函数关系(以上已经描述);
图4示意性地展示了根据本发明的可变几何涡轮的轴向可调节环的剖视图;
图5示意性地展示了根据本发明的可变几何涡轮中从喷嘴间隙向着轴向可调节环的平面图;
图6为图5的可调节环的VI-VI剖视示意图;
图7为根据本发明另一实施例的可变几何涡轮中从喷嘴间隙向着轴向可调节环的平面示意图;
图8为图7的可调节环的VIII-VIII剖视示意图;
图9为根据本发明另一实施例的从喷嘴间隙向着可变几何涡轮的轴向可调节环的平面示意图;
图10为图9中的轴向可调节环的X-X剖视示意图;
图11为根据本发明的可变几何涡轮中,作用在可调节环的复位力与喷嘴间隙的函数关系。
具体实施方式
根据本发明的可变几何涡轮可以用以上描述的现有涡轮的类似方法设计制造,除了平衡孔口的形状。图4为细节剖面图,该剖面沿平行于通过根据本发明的可变几何涡轮的喷嘴间隙的流体的流动线路。轴向可调节环25处于最小喷嘴间隙,从入口涡管至涡轮转子的流动用箭头20表示。平衡孔26设置在壁19上,该壁的表面18面对着喷嘴间隙23。边缘16在孔关于流体流动的下游,该边缘从表面18界定出孔26形成倒圆角部分。
根据一个优选实施例,不是所有的所述边缘都为倒圆角,也不是都为均匀曲率。该边缘的曲率可以从较不相关区域的0(锐利边缘)或从最小值逐渐变化至关于孔中心的下游区域的最大值。这产生了沿流体流动方向延伸的倒圆角区域。图5为面向喷嘴间隙23的环表面18的局部视图。图中显示了叶片27和带倒圆角部分17的平衡孔26,箭头20表示流体的方向。叶片界定了一系列通道14。根据另一优选实施例,通道设置有孔26,该孔26位于界定通道的两个叶片的中间。倒圆角部分可以与表面19形成边界15,该边界15的形状取决于倒圆角如何形成(例如抛物线形或椭圆形)。
在曲率半径最大值的边缘部分,曲率半径R必须大于经过孔区的平均流体流动方向的孔的最大宽度S(没有考虑倒圆)的20%,以达到有用效果。参见图6,显示了图5的截面VI-VI,当孔为圆形时,尺寸S可以为孔的直径。图7和8展示了一个优选实施例,其中宽大倒圆17’向边界15’下游延伸。平衡孔可以具有圆形截面或其他形状。平衡孔的内壁(没有考虑圆形区域)可垂直于或倾斜于可调节环的壁。根据一个可能的实施例,内壁可以一定程度上倾斜于流体流动方向。这进一步提高了复位特性。图9和图10展示了喷嘴环,该喷嘴环具有带非圆形截面的倾斜孔。
这些孔和倒圆可以由任何适合的现有技术制造。它们可以通过三轴铣床制造,利用半径或圆环面铣刀,刀具的直径等于或稍小于平衡孔的直径。
如现有技术中,可调节环可以为叶片式,或者可以具有适合容纳相反固定的叶片珊格的叶片的槽。所有通常应用在“移动壁”(moving wall)型的可变几何涡轮的技术方案都可以采用,并做适当调整。可调节环可以由如上所述的各种执行器操控。
平衡孔在环上的位置及其尺寸可以,如已在现有技术中出现过,根据环后面的室中所需的压力选择,记住,沿着喷嘴,向着内涡管的静态压力较高,而向着涡轮转子的静态压力较低。孔的直径可以为相关叶片通道的宽度的50-90%,或者在非圆形截面时具有相当的尺寸。根据本发明的可变几何涡轮带来明显的优点。避免了在很小的喷嘴间隙中孔的干涉所引起的压力骤降。在图11中,示意性地显示了根据本发明的可变几何涡轮的复位力和喷嘴间隙的函数关系。由于没有出现力的衰竭(与图3相比),可以允许喷嘴间隙的缩小至远小于现有技术的值,例如在增压式内燃机的涡轮增压器的情况下,达到较高的发动机制动功率和较好的瞬变状态性能,以及提高了控制稳定性。
另一个优点是降低了喷嘴的流体压力损失,当从流体***恢复能量时涡轮产生较高的效率。
Claims (8)
1.一种可变几何涡轮,包括外壳(22)、涡轮转子(4)、环绕所述涡轮转子的流体入口(1)和设置在所述流体入口和所述涡轮转子之间用于加速流体流动的叶片式喷嘴,所述喷嘴包括用于改变喷嘴间隙(23)并有轴向界定所述喷嘴间隙的壁(19)的轴向可调节环(25),所述壁具有连接所述喷嘴间隙与所述外壳和所述环界定的室(12)的平衡孔(26、26’),其特征在于:所述孔和所述壁面向所述喷嘴间隙的表面(18)所形成的边缘(16)在孔的关于流体流动的下游的部分(17、17’)形成宽大倒圆角。
2.根据权利要求1所述的涡轮,其特征在于:所述边缘(16)在其曲率半径为最大值时,具有曲率半径R,该曲率半径R大于经过孔区的平均流体流动方向上的、所述平衡孔的最大宽度(S)的20%。
3.根据权利要求1所述的涡轮,其特征在于:在流动方向(20)上的所述倒圆角为抛物线形或椭圆形。
4.根据以上任意一项权利要求所述的涡轮,其特征在于:所述倒圆角区域的边界(15,15’)在流体流动方向上伸长。
5.根据权利要求1所述的涡轮,其特征在于:所述倒圆角区域具有可由带半径铣刀的三轴铣床加工成的几何形状。
6.根据权利要求1所述的涡轮,其特征在于:所述涡轮为燃气涡轮。
7.一种增压式内燃机的涡轮增压器,其特征在于:包括根据权利要求6所述的涡轮。
8.一种用于车辆的增压式内燃机,其特征在于:包括根据权利要求7所述的涡轮增压器。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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ITMI2006A001738 | 2006-09-12 | ||
IT001738A ITMI20061738A1 (it) | 2006-09-12 | 2006-09-12 | Turbina a geometria variabile |
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CN101144394A CN101144394A (zh) | 2008-03-19 |
CN101144394B true CN101144394B (zh) | 2012-06-27 |
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CN200710147439.7A Expired - Fee Related CN101144394B (zh) | 2006-09-12 | 2007-09-12 | 可变几何涡轮 |
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US (1) | US7955047B2 (zh) |
EP (1) | EP1900908B8 (zh) |
JP (1) | JP4944717B2 (zh) |
CN (1) | CN101144394B (zh) |
BR (1) | BRPI0704032A (zh) |
ES (1) | ES2401455T3 (zh) |
IT (1) | ITMI20061738A1 (zh) |
Families Citing this family (13)
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GB0521354D0 (en) * | 2005-10-20 | 2005-11-30 | Holset Engineering Co | Variable geometry turbine |
GB0615495D0 (en) * | 2006-08-04 | 2006-09-13 | Cummins Turbo Tech Ltd | Variable geometry turbine |
GB0805519D0 (en) * | 2008-03-27 | 2008-04-30 | Cummins Turbo Tech Ltd | Variable geometry turbine |
GB0921350D0 (en) | 2009-12-05 | 2010-01-20 | Cummins Turbo Tech Ltd | Vaariable geometry turbomachine |
GB201015679D0 (en) * | 2010-09-20 | 2010-10-27 | Cummins Ltd | Variable geometry turbine |
GB2497786B (en) | 2011-12-21 | 2016-09-07 | Cummins Ltd | Variable geometry turbine having vane slots with portions of increased clearance |
EP2984299B1 (en) | 2013-04-10 | 2018-10-03 | Cummins Ltd | Variable geometry turbine |
US9650911B1 (en) * | 2014-10-10 | 2017-05-16 | Cummins Ltd | Variable geometry turbine |
DE102015219374B4 (de) | 2015-10-07 | 2022-05-25 | Vitesco Technologies GmbH | Verfahren zum Einbringen einer Wuchtmarke in das Verdichterrad eines Abgasturboladers und Abgasturbolader mit einem eine Wuchtmarke aufweisenden Verdichterrad |
DE102017123819A1 (de) * | 2017-10-12 | 2019-04-18 | Ihi Charging Systems International Germany Gmbh | Laufrad für einen Abgasturbolader, Abgasturbolader und Verfahren zum Auswuchten eines Laufzeugs für einen Abgasturbolader |
CN109505663B (zh) * | 2018-11-29 | 2021-08-17 | 江西省萍乡市三善机电有限公司 | 一种涡轮增压器上用的喷嘴环 |
GB202108695D0 (en) * | 2021-06-17 | 2021-08-04 | Cummins Ltd | Nozzle ring for a variable geometry turbine |
CN113513373B (zh) * | 2021-07-08 | 2023-05-30 | 哈尔滨工程大学 | 一种变几何涡轮一维气动设计方法 |
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2006
- 2006-09-12 IT IT001738A patent/ITMI20061738A1/it unknown
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2007
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- 2007-09-11 JP JP2007234878A patent/JP4944717B2/ja not_active Expired - Fee Related
- 2007-09-11 EP EP07116130A patent/EP1900908B8/en not_active Not-in-force
- 2007-09-11 ES ES07116130T patent/ES2401455T3/es active Active
- 2007-09-12 CN CN200710147439.7A patent/CN101144394B/zh not_active Expired - Fee Related
- 2007-09-12 BR BRPI0704032-6A patent/BRPI0704032A/pt not_active IP Right Cessation
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US5522697A (en) * | 1993-11-19 | 1996-06-04 | Holset Engineering Company, Ltd. | Load reducing variable geometry turbine |
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CN1508410A (zh) * | 2002-11-19 | 2004-06-30 | 奥尔塞特工程有限公司 | 可变几何形状涡轮 |
Also Published As
Publication number | Publication date |
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EP1900908A2 (en) | 2008-03-19 |
EP1900908A3 (en) | 2011-09-28 |
EP1900908B1 (en) | 2012-12-19 |
EP1900908B8 (en) | 2013-01-23 |
ITMI20061738A1 (it) | 2008-03-13 |
US7955047B2 (en) | 2011-06-07 |
US20090097969A1 (en) | 2009-04-16 |
BRPI0704032A (pt) | 2008-04-29 |
ES2401455T3 (es) | 2013-04-19 |
CN101144394A (zh) | 2008-03-19 |
JP2008069779A (ja) | 2008-03-27 |
JP4944717B2 (ja) | 2012-06-06 |
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