CN112032105B - 转子叶尖间隙控制方法及利用该方法制造的转子叶片 - Google Patents
转子叶尖间隙控制方法及利用该方法制造的转子叶片 Download PDFInfo
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Abstract
本发明涉及一种转子叶尖间隙控制方法,包括以下步骤:使转子叶片(20)的重心(GB)与支承转子叶片(20)的转子轮盘(10)的重心(GD)在所述航空发动机的轴向方向(D)上重合;使转子轮盘(10)转动,测量转子叶片(20)的前缘(21)的前缘变形量(Δ1);测量转子叶片(20)的后缘(22)的后缘变形量(Δ2);比较前缘变形量(Δ1)和后缘变形量(Δ2);调整转子轮盘(10)的重心(GD),直至前缘变形量(Δ1)与后缘变形量(Δ2)趋于大致相等。该方法能够有效改善甚至解决转子叶尖在工作时前缘和尾缘径向位移不一致的问题。
Description
技术领域
本发明涉及一种转子叶尖间隙控制方法及利用该方法制造的转子叶片。
背景技术
压气机是燃气涡轮发动机中利用高速旋转的叶轮叶片(或称为“转子叶片”)给空气作功以提高空气压力的部件。增压级则是为改善前置风扇和压气机的气动性能并提高压气机入口处的压力而专门设置在风扇和压气机间的压气机级。增压级压气机通常被用作为航空发动机,其转子叶片的前端部分(或称为“叶尖”或“转子叶尖”)通常呈弯曲状,其作用是将气体无冲击地导入工作中的转子,减小气流冲击所导致的动能损失。
压气机的机匣设有供气流进入和离开的进口和出口。机匣进口通常为轴向布置,其流道布置为略呈渐缩的型式,以减小气流进入的阻力。机匣出口通常设计成流道沿周向方向具有渐扩的蜗壳形状,致使高速气流在其中继续扩压,以提高增压级压气机的总体效率。
高速旋转的转子叶片在由机匣、轮毂等组合形成的气流通道内作业。为了避免摩擦发热或者因碰撞而损坏转子叶片,通常会在叶尖与机匣内壁之间留有一定的径向间隙。该径向间隙被称为“转子叶尖间隙”。众所周知,转子叶尖间隙的大小对于压气机的稳定工作范围以及其压缩部件的气动性能参数(例如,效率、裕度等)具有较大的影响。显然,转子叶尖间隙并不是越小越好,也不是越大越好。对每台特定的压气机来说,都存在一个最佳的转子叶尖间隙。当压气机在该最佳转子叶尖间隙的状态下运行时,会具有最大的稳定工作范围以及最佳的气动性能参数。
目前,在增压级压气机的压缩部件工作时,转子叶尖间隙通常会存在以下问题:
在设计转子叶片的叶型时,主要考虑气动性能及叶身应力,因此有时无法兼顾转子叶片的叶身径向变形沿弦长方向的差异,使得叶尖在工作时,前缘和尾缘的径向位移不一致,存在一端的转子叶尖间隙相对偏大,而另一端的转子叶尖间隙相对偏小的问题。
一般来说,转子叶尖间隙偏大的一端会导致叶尖处的气流泄漏,进而影响压缩部件的气动性能;而转子叶尖间隙偏小的一端会产生不期望的刮磨机匣内壁的风险,尤其是在非预期地刮磨涂覆有耐磨涂层的机匣时,会严重影响航空发动机的安全运转。
目前,业内存在一些控制转子叶尖间隙的方法。
例如,在三菱重工业株式会社于2015年8月18日提交的PCT国际申请WO2016/063604(2016年12月15日进入中国国内阶段,申请号为201580032222.4)中,提出了一种轴流式涡轮及增压机,其中,该轴流式涡轮具备:在外周具有多个可动叶片的转子;以及设置于转子的外周侧,且具有与可动叶片的叶尖面相对的环状壁面的静止部件在轴流式涡轮停止时,可动叶片的后缘侧处的叶尖面与环状壁面之间的间隙比可动叶片的前缘侧处的叶尖面与环状壁面之间的间隙大。
然而,上述现有技术主要通过对壁面施力使其变形来改变其与叶尖之间的间隙。这需要配备额外的控制设备,不仅增加了成本,而且加大了零件发生故障导致调整失效的风险。
为此,设想提出一种用于控制转子叶尖间隙的方法,该方法能够有效改善甚至解决转子叶尖在工作时前缘和尾缘径向位移不一致的问题。
发明内容
本发明的目的在于提供一种能够有效改善转子叶尖在工作时前缘、尾缘径向位移不一致问题的转子叶尖间隙控制方法。
本发明的另一目的在于提供一种利用该方法制造的转子叶片。
本发明的第一方面涉及一种转子叶尖间隙控制方法,该控制方法用于航空发动机,包括以下步骤:
使转子叶片的重心与支承转子叶片的转子轮盘的重心在航空发动机的轴向方向上重合;
使转子轮盘转动。
该方法还包括:
测量转子叶片的前缘的前缘变形量;
测量转子叶片的后缘的后缘变形量;
当前缘变形量和后缘变形量之间的差异大于规定范围时,比较前缘变形量和后缘变形量;以及
根据比较后的结果调整转子轮盘的重心,直至前缘变形量与后缘变形量趋于大致相同。
需要说明的是,术语“大致相同”是指在可以容许的误差范围内达到数值在同一数量级基本上接近。
在一个优选实施例中,可以通过将转子轮盘的重心朝向前缘和后缘中具有较小变形量的一者偏置预定的偏移量来调整转子轮盘的重心。
术语“较小变形量的一者”指代的是前缘变形量与后缘变形量中数值较小的那一个。也就是说,当前缘变形量大于后缘变形量时,该术语指代的是后缘;当前缘变形量小于后缘变形量时,该术语指代的是前缘。
更佳地,根据所述转子轮盘的转速可以确定预定的偏移量。
在另一个优选实施例中,规定范围被规定如下:
对于叶高小于20mm的叶片,规定范围为叶高的0.5%-1.5%;
对于叶高为20mm至40mm的叶片,规定范围为叶高的0.25%-2%;
对于叶高为40mm至100mm的叶片,规定范围为叶高的0.2%-1%;
对于叶高大于100mm的叶片,规定范围为叶高的0.2%-0.6%。
尤其是,航空发动机可以为增压级压气机。
此外,还可以利用变形模量测试仪测量转子叶片的前缘的前缘变形量以及转子叶片的后缘的后缘变形量。
本发明的第二方面涉及一种利用如本发明的第一方面所述的控制方法制造的转子叶片,其中,转子叶片支承在带重心偏置特征的转子轮盘上。
需要说明的是,术语“重心偏置特征”指的是在利用调整重心来控制转子叶尖间隙的方法中,转子叶片的重心被调整之后所呈现的特征。
具体来说,在一个较佳实施例中,重心偏置特征实现为转子叶片的重心与转子轮盘的重心在航空发动机的轴向方向上存在预定的偏移量。
在另一个较佳实施例中,重心偏置特征实现为转子轮盘的对称中心线基本上垂直于航空发动机的轴向方向。
在又一个较佳实施例中,重心偏置特征实现为转子轮盘的非对称特征。
根据本发明的转子叶尖间隙控制方法以及利用该方法制造的转子叶片具有以下优点:
(1)通过偏移转子轮盘的重心,在不引入冗余零件和机构的情况下,简单方便地解决了作为航空发动机的增压级压气机工作时叶尖前缘与尾缘径向位移不一致的问题;
(2)通过将增压级压气机的转子叶尖与机匣之间彼此不同的径向间隙调整为趋于一致,改善了其压缩部件的气动性能参数,尤其是效率及裕度;以及
(3)在改善压缩部件的气动性能参数的同时,确保转子叶尖间隙不会对航空发动机的安全运转产生任何不利影响。
附图说明
为了进一步说明根据本发明的转子叶尖间隙控制方法以及利用该方法制造的转子叶片,下面将结合附图和具体实施方式对本发明进行详细说明,其中:
图1是安装有单个转子叶片的转子轮盘的局部剖视图,其中转子轮盘的重心未偏移;
图2是安装在图1所述的转子轮盘上的转子叶片的放大示意图;
图3是与图1类似、但其重心经偏移的转子轮盘的局部剖视图;以及
图4是安装在图3所述的转子轮盘上的转子叶片的放大示意图。
附图标记
10 转子轮盘
20 转子叶片
21 叶片前缘
22 叶片尾缘
GD 转子轮盘重心
GB 转子叶片重心
D 重心连线方向
Db 偏置后的重心连线方向
Δ1 前缘变形量
Δ2 尾缘变形量
w 偏移量。
具体实施方式
下面结合附图说明根据本发明的转子叶尖间隙控制方法的各步骤、以及利用该方法制造的转子叶片的结构及其效果,其中,相同的部件由相同的附图标记进行标示。
图1示出了在重心未经偏移的转子轮盘10,该转子轮盘10上安装有若干个转子叶片20,为了便于示意,该图中仅示出了一个转子叶片20。
众所周知,在高速旋转过程中由轴承支撑的旋转体被称为转子,转子是诸如电动机、发电机、燃气轮机、透平压缩机和压气机等动力机械领域中的主要旋转部件。转子能够围绕其轴线转动,该轴线的延伸方向被称为转子的轴向,从该轴线垂直向外呈辐射状延伸的方向被称为转子的径向。在压气机中,转子的转子轮盘支承有多个转子叶片,这些转子叶片沿转子轮盘的周向均匀分布。转子叶片通常被分为叶根、叶身和叶尖三部分,其中,叶根固定或一体形成在转子轮盘上,叶身沿转子的径向以一定的空间曲面形式伸展,而叶尖位于转子叶片的径向最外侧。
在转子工作时,转子叶片20跟随转子及转子轮盘10一起围绕轴线作圆周转动。虽然图中没有示出,但本领域的普通技术人员应当了解的是,机匣作为包围在转子外部的壳体部件,主要用于形成气流通道。机匣通常由金属或金属合金铸造或锻造而成,并且在叶尖与机匣的内壁之间留有一定的径向间隙,即转子叶尖间隙。
根据本发明的转子叶尖间隙控制方法包括如下步骤:
(i)在热态设计时,使转子叶片20的重心GB与转子轮盘10的重心GD在航空发动机的轴向方向上重合。如图1所示,连接转子叶片20的重心GB与转子轮盘10的重心GD的虚线即为发动机的轴向方向D。
(ii)当转子叶片20与转子轮盘10完成转冷后,在转子轮盘10连同其上的转子叶片20高速旋转期间,由于离心力的作用,转子叶片20的前缘21和尾缘22会产生不同的径向位移。此时,测量转子叶片20的前缘21的前缘变形量Δ1以及转子叶片20的后缘22的后缘变形量Δ2。
如图2所示,可以看到安装在图1所示的转子轮盘10上的转子叶片20,其中虚线示出了转子叶片20在静止状态下所处的位置,而实线则示出了转子叶片20在旋转状态下所处的位置。可以利用本领域公知的变形量检测装置、例如市场上可购买到的变形模量测试仪等检测前缘21的前缘变形量Δ1以及后缘22的后缘变形量Δ2。
(iii)当检测到的前缘变形量Δ1和后缘变形量Δ2之间的差异大于规定范围时,将前缘变形量Δ1和后缘变形量Δ2进行比较,并判断前缘21和后缘22中哪个具有较小的变形量。
需要说明的是,上述“规定范围”具体规定如下:
对于叶高小于20mm的叶片,该规定范围为叶高的0.5%-1.5%;
对于叶高为20mm至40mm的叶片,该规定范围为叶高的0.25%-2%;
对于叶高为40mm至100mm的叶片,该规定范围为叶高的0.2%-1%;
对于叶高大于100mm的叶片,该规定范围为叶高的0.2%-0.6%。
(iv)根据比较后的结果调整转子轮盘10的重心GD,直至前缘变形量Δ1与后缘变形量Δ2趋于大致相同。与图2类似,图4中的虚线示出了转子叶片20在静止状态下所处的位置,而实线则示出了转子叶片20在旋转状态下所处的位置。此时,转子叶尖间隙的变化量达到设计目标。
更具体地说,经模拟实验后发现,转子轮盘10的重心GD相对于转子叶片10的重心GB偏置于靠近转子叶尖的前缘21侧时,转子叶尖的前缘21的前缘变形量Δ1大于转子叶尖的尾缘22的后缘变形量Δ2。反之,转子轮盘10的重心GD相对于转子叶片10的重心GB偏置于靠近转子叶尖的尾缘22侧时,转子叶尖的前缘21的前缘变形量Δ1小于转子叶尖的尾缘22的后缘变形量Δ2。为此,在上述第(iv)步骤中,可以采用将转子轮盘10的重心GD朝向前缘21和后缘22中具有较小变形量的一者偏置预定的偏移量w的方法,对转子轮盘10的重心GD进行调整。
如图3所示,其中示出了重心GD经偏移的转子轮盘10。可以看到,转子轮盘10的重心GD原先位于发动机的轴向方向D上。通过对重心GD进行偏移,该重心GD已经偏移到偏置后的重心连线方向Db上,其偏移量为图3中箭头所示的尺寸w。通过上述偏置调整,能够改善甚至解决转子叶尖在工作时前缘21和尾缘22的径向位移不一致的问题。
由于转子轮盘10的重心GD与转子叶片20的重心GB的相对偏移量w和/或转子转速综合地影响了航空发动机工作时转子叶片20的前缘21与尾缘22的径向位移差,根据转子转速范围可以优选合适的转子轮盘10的重心GD与转子叶片20的重心GB的相对偏移量w,并获得期望的转子叶片20的前缘21与尾缘22的径向位移差,进而在转子叶片工作时使其前缘21和尾缘22的径向变形量Δ1和Δ2趋于大致相同。
应当注意的是,此处所用的术语“大致相同”并非是指严格意义上的数值相等,而是在可以容许的误差范围内达到数值在同一数量级基本上接近即可。换句话说,只要是在可以容许的误差范围内达到数值基本类似,就能够认为变形量Δ1和Δ2趋于大致相同。
利用上述控制方法,可以制造出多个用于航空发动机的转子叶片20。这些转子叶片20沿转子的周向布置在带重心偏置特征的转子轮盘10上。
上述重心偏置特征以如下方式中的至少一种实现:
(i)转子叶片20的重心GB与转子轮盘10的重心GD在航空发动机的轴向方向D上存在预定的偏移量w;
(ii)转子轮盘10的对称中心线基本上垂直于所述航空发动机的轴向方向D,也就是说,转子轮盘10的对称中心线不严格垂直于发动机的轴向方向,而是呈现接近90°的锐角或钝角;
(iii)转子轮盘10的非对称特征。
虽然以上结合了较佳实施例对本发明的转子叶尖间隙控制方法以及利用该方法制造的转子叶片进行了说明,但是本技术领域中的普通技术人员应当认识到,上述示例仅是用来说明的,而不能作为对本发明的限制。因此,可以在权利要求书的实质精神范围内对本发明进行修改和变型,这些修改和变型都将落在本发明的权利要求书所要求的范围之内。
Claims (9)
1.一种转子叶尖间隙控制方法,所述控制方法用于航空发动机,包括以下步骤:
使转子叶片(20)的重心(GB)与支承所述转子叶片(20)的转子轮盘(10)的重心(GD)在所述航空发动机的轴向方向(D)上重合;
使所述转子轮盘(10)转动,
其特征在于,还包括:
测量所述转子叶片(20)的前缘(21)的前缘变形量(Δ1);
测量所述转子叶片(20)的后缘(22)的后缘变形量(Δ2);
当所述前缘变形量(Δ1)和所述后缘变形量(Δ2)之间的差异大于规定范围时,比较所述前缘变形量(Δ1)和所述后缘变形量(Δ2);以及
根据比较后的结果调整所述转子轮盘(10)的重心(GD),直至所述前缘变形量(Δ1)与所述后缘变形量(Δ2)趋于大致相同,其中,
通过将所述转子轮盘(10)的重心(GD)朝向所述前缘(21)和所述后缘(22)中具有较小变形量的一者偏置预定的偏移量(w)来调整所述转子轮盘(10)的重心(GD)。
2.如权利要求1所述的控制方法,其特征在于,根据所述转子轮盘的转速确定所述预定的偏移量(w)。
3.如权利要求1所述的控制方法,其特征在于,所述规定范围被规定如下:
对于叶高小于20mm的叶片,所述规定范围为叶高的0.5%-1.5%;
对于叶高为20mm至40mm的叶片,所述规定范围为叶高的0.25%-2%;
对于叶高为40mm至100mm的叶片,所述规定范围为叶高的0.2%-1%;
对于叶高大于100mm的叶片,所述规定范围为叶高的0.2%-0.6%。
4.如权利要求1所述的控制方法,其特征在于,所述航空发动机为增压级压气机。
5.如权利要求1所述的控制方法,其特征在于,利用变形模量测试仪测量所述转子叶片(20)的前缘(21)的前缘变形量(Δ1)以及所述转子叶片(20)的后缘(22)的后缘变形量(Δ2)。
6.一种利用如权利要求1所述的控制方法制造的转子叶片(20),其特征在于,所述转子叶片(20)支承在带重心偏置特征的转子轮盘(10)上。
7.如权利要求6所述的转子叶片(20),其特征在于,所述重心偏置特征实现为所述转子叶片(20)的重心(GB)与所述转子轮盘(10)的重心(GD)在所述航空发动机的轴向方向(D)上存在预定的偏移量(w)。
8.如权利要求6所述的转子叶片(20),其特征在于,所述重心偏置特征实现为所述转子轮盘(10)的对称中心线基本上垂直于所述航空发动机的轴向方向(D)。
9.如权利要求6所述的转子叶片(20),其特征在于,所述重心偏置特征实现为所述转子轮盘(10)的非对称特征。
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EP4242466A1 (en) | 2023-09-13 |
CN112032105A (zh) | 2020-12-04 |
WO2022095720A1 (zh) | 2022-05-12 |
US20240011409A1 (en) | 2024-01-11 |
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