CN112780353A - 借助于冲击冷却来冷却燃气涡轮/涡轮机的构件的装置 - Google Patents

借助于冲击冷却来冷却燃气涡轮/涡轮机的构件的装置 Download PDF

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CN112780353A
CN112780353A CN202011230796.1A CN202011230796A CN112780353A CN 112780353 A CN112780353 A CN 112780353A CN 202011230796 A CN202011230796 A CN 202011230796A CN 112780353 A CN112780353 A CN 112780353A
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component
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C·B·多姆尼克
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MAN Energy Solutions SE
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    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
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    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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Abstract

本发明涉及一种用于冷却燃气涡轮/涡轮机的构件(1)的装置，该构件带有热气体冲击的外表面(2)和集成冷却通道(3)，其中在冷却通道(3)内布置有带有至少一个冲击冷却孔(5)的冲击冷却元件(4)，其中冲击冷却元件(4)与待冷却构件(1)的目标表面(6)隔开，并且为了冷却构件(1)，作为冲击冷却射流的冷却流体可引导到目标表面(6)上，其中表面结构(8)形成在目标表面(6)上，冲击冷却射流冲击在表面结构上。

Description

借助于冲击冷却来冷却燃气涡轮/涡轮机的构件的装置
技术领域
本发明涉及一种用于冷却燃气涡轮/涡轮机的构件的装置，构件带有热气体冲击的外表面和集成冷却通道，其中布置有带有至少一个冲击冷却孔的冲击冷却元件。
背景技术
燃气涡轮的多种构件(例如，诸如叶片)暴露于燃烧室的燃烧气体的高温。此外，可通过增加在燃烧室中实现的燃烧温度来进一步改善燃气涡轮的效率。然而，由于暴露于热气体的构件的热容量，这样的温度增加具有限制。这特别适用于位于还承受主要机械应力的燃烧室下游的涡轮级的引导叶片和动叶片。
出于此原因，需要特别的冷却方法以便抵消构件失效并且不超过基于材料的温度限制。相关构件并且特别是其承受高热负荷的区域以已知方式用从压缩机分出来的冷却空气冷却。在现有技术中，这些叶片的叶配备有供有冷却空气的冷却装置。通过从压缩机引出部分压缩空气且将该空气传送到涡轮部分实现叶片冷却。在将冷却空气引入到涡轮部分之后，该冷却空气流过形成在叶片的叶片叶部分中的通道。
DE 102008003412A1公开了借助于局部直接冲击冷却来更有效地冷却叶片末梢帽以便降低在承受主要应力的末梢帽的区域中的金属温度。
除此之外，例如在从EP 1001135A2已知的用于涡轮叶片的冲击冷却中，沿纵向延伸的分隔壁布置在例如由两个侧壁定界的中空叶片的内部中，这两个侧壁在每种情况下与侧壁部分一起形成伸长的冷却空气供给和冷却空气分配室以及邻接这些的多个冲击空气冷却室。通过冲击空气通道，引入到冷却空气室中的冷却空气到达邻近的冲击空气冷却室，以便由此冷却从内侧承受高热应力的涡轮叶片的外壁的区域的内表面，并且因此能够在高效率和没有材料损坏的情况下以优选的高燃烧温度操作燃气涡轮。在分隔壁中，冲击空气通道线性但倾斜地定向，以便确保冲击在外壁的内表面上的冲击冷却空气的有利角度。从冲击空气冷却室经由涡轮叶片的侧壁中的空气通道离开的空气另外在叶片材料和热气体之间产生隔离层，该隔离层进一步降低涡轮叶片上的热应力。
发明内容
本发明的目的在于提供一种用于冷却燃气涡轮/涡轮机的构件的装置，该装置进一步改善冷却的效率。
通过根据专利权利要求1的特征组合来解决该目的。
根据本发明，提出了一种用于冷却燃气涡轮/涡轮机的构件的装置，该构件带有热气体冲击的外表面和集成冷却通道。在冷却通道内，布置有带有至少一个冲击冷却孔的冲击冷却元件。该冲击冷却元件与待冷却构件的目标表面隔开，并且为了冷却构件，作为冲击冷却射流的冷却流体可通过冲击冷却孔引导到目标表面上。此外，表面结构(冲击冷却射流冲击该表面结构)形成在目标表面上。
这其中有利的是，借助于适当地形成的表面结构，目标表面的微观结构改善热传导。通过这样，可在冷却效果保持相同的情况下减少冷却介质的消耗，或者在冷却介质的消耗保持相同的情况下改善冷却性能。因此，本发明用于节省冷却空气并且因此增加效率的主要目的。
在有利的实施例版本中，设置为借助于从目标表面突出的星形肋形成表面结构。根据本发明，目标表面的微观结构包括向冲击冷却射流径向地布置的肋。通过这些适当地形成的肋，利用多种物理效应增加了热传导。最初，以该方式增加了目标表面的表面面积，并且由于肋的对应布置，通过流的局部加速增加了热流密度。除此之外，隔离了有害于热传导的横向流的冷却空气流并且避免了流分离。
在进一步有利的实施例版本中，根据本发明设置为借助于各自呈不同形式交错的从目标表面突出的星形肋形成表面结构。在某些应用情形中，因为表面结构可最优地适合于待冷却构件的几何形状，在目标表面上布置成多排的肋可进一步改善流特性并且因此还可进一步改善冷却性能。
优选地，以这样的方式形成用于冷却构件的装置：表面结构的肋与位于冲击冷却孔对面的中心点隔开而径向地向外侧延伸。这对于冲击冷却射流的冷却性能是有利的，因为冲击冷却射流在冲击在目标表面上之后直接如此引导通过表面结构或肋。
在本发明的示例性实施例中，设置为肋具有朝外侧渐缩的滴形形状。由于特殊形成的几何形状，优化了冷却空气流的流特性或冷却性能。
此外，其中肋具有线性、杆状的形状的实施例是有利的。特别是在多排中形成的表面结构的情况下，肋的交错的几何形状有利于冷却空气流的最优冷却性能。
根据本发明的用于冷却燃气涡轮/涡轮机的构件的装置在实施例版本中形成，使得肋具有不同的长度和/或高度，肋以此在目标表面上延伸。这继而具有在冷却空气的流上的积极影响，因此增加了效率。
此外，当星形肋形成在与冲击冷却孔的对应排相对的排中的目标表面上时是有利的。通过这样，在每个区域的目标表面上布置有带有适当的肋的特殊表面结构，其中，冷却空气流通过冲击冷却孔并冲击在目标表面上。结果，在这些区域中的每一个上提高了燃气涡轮/涡轮机的构件的冷却性能。
此外，在本装置的备选实施例中，设置为每个肋的位于径向内侧的起点到中心点的距离对应于肋的长度的大约75%-150%。这里，有利的是，冷却空气流最初冲击冷却表面并且随后流过相关的肋以用于优化冷却性能。
在本发明的优选实施例中，肋的侧翼至少在到目标表面的接合处正交地延伸，并且优选地只在到护罩侧的过渡处倾斜地形成或倒圆。在进一步的有利实施例中，根据本发明设置为护罩侧形成为平坦的且平行于目标表面。通过这样，最大限度地增大了肋的表面，并且目标表面的表面结构具有用于冷却的最优或最大的表面面积。
此外，根据本发明提出了如上文所描述的具有用于冷却燃气涡轮/涡轮机的构件的装置的燃气涡轮/涡轮机。
附图说明
本发明的其他有利的进一步发展在从属权利要求中标出或者在下文中通过附图或结合本发明的优选实施例的描述更详细地示出。附图示出：
图1是带有在冲击冷却的目标表面上的表面结构的燃气涡轮构件的截面图，
图2是带有布置成一排的肋的目标表面的透视图，
图3是带有布置成多排的肋的目标表面的透视图。
具体实施方式
在图1中，示出了具有用于冲击冷却的装置的燃气涡轮构件1的截面图，该构件包括在冲击冷却布置的目标表面6上的表面结构8。
燃气涡轮构件1包括在操作期间由热气体冲击的外表面2以及用于冷却的集成冷却通道3。冲击冷却元件4在冷却通道3内延伸，冲击冷却元件将冷却通道3分成用于冷却剂供给的供给部分11和冷却部分12，冷却部分中布置有待冷却的目标表面6。冲击冷却元件4与构件1的冷却部分12中的待冷却的目标表面6隔开。此外，冲击冷却元件4在示出的区域中包括四个冲击冷却孔5，冷却流体可经由该冲击冷却孔引导作为到位于冲击冷却孔5对面的目标表面6的中心点Z上用于冷却构件1的冲击冷却射流。
在图2中示出了带有布置成多排的肋9的目标表面6的透视图。表面结构8对应于图1中示出并在下文中描述的图示。
表面结构8(冲击冷却射流冲击在其上)形成在目标表面6上。该表面结构8借助于各自呈不同形式交错的星形肋9形成，该星形肋从目标表面6突出。与位于冲击冷却孔5对面的中心点Z隔开，肋9径向地向外侧延伸。肋9在目标表面6上的径向布置形成且布置在与冲击冷却孔5的对应排相对的排中。肋9的侧翼在到目标表面6的接合处正交地延伸并且只在朝护罩侧10的过渡处倾斜地形成并且倒圆。除此之外，相应交错的肋9具有不同的长度和高度，肋以此在目标表面6上延伸。两个径向布置中的一个包括向外侧渐缩的滴形的肋9，并且每个肋9的位于径向内侧的起点到中心点Z的距离大约对应于该肋9长度的75%。相比之下，其他径向布置的肋9具有线性、杆形的形式，并且每个肋9的位于径向内侧的起点到中心点Z的距离大约对应于该肋9的长度的150%。肋9的护罩侧10形成为平坦的且平行于目标表面6。
图2示出了带有布置成一排的肋9的目标表面6的透视图。表面结构8借助于如之前所描述的从目标表面6突出的滴形的星形肋9形成。
参考标号列表：
1 燃气涡轮构件
2 外表面
3 冷却通道
4 冲击冷却元件
5 冲击冷却孔
6 目标表面
8 表面结构
9 肋
10 护罩侧
11 供给部分
12 冷却部分
Z 中心点。

Claims (12)

1.一种用于冷却燃气涡轮/涡轮机的构件(1)的装置，所述构件带有热气体冲击的外表面(2)和集成冷却通道(3)，其中在所述冷却通道(3)内布置有带有至少一个冲击冷却孔(5)的冲击冷却元件(4)，其中所述冲击冷却元件(4)与待冷却的所述构件(1)的目标表面(6)隔开，并且为了冷却所述构件(1)，作为冲击冷却射流的冷却流体可引导到所述目标表面(6)上，其中表面结构(8)形成在所述目标表面(6)上，所述冲击冷却射流冲击在所述表面结构上。
2.根据权利要求1所述的用于冷却燃气涡轮/涡轮机的构件(1)的装置，其特征在于，所述表面结构(8)借助于从所述目标表面(6)突出的星形肋(9)形成。
3.根据权利要求1所述的用于冷却燃气涡轮/涡轮机的构件(1)的装置，其特征在于，所述表面结构(8)借助于各自至少呈不同形式交错的星形肋(9)形成，所述肋从所述目标表面(6)突出。
4.根据权利要求2或权利要求3中的任一项所述的用于冷却燃气涡轮/涡轮机的构件(1)的装置，其特征在于，所述表面结构(8)的所述肋(9)与位于所述冲击冷却孔(5)对面的中心点(Z)隔开而径向地向外侧延伸。
5.根据权利要求2到权利要求4中的任一项所述的用于冷却燃气涡轮/涡轮机的构件(1)的装置，其特征在于，所述肋(9)具有朝所述外侧渐缩的滴状的形状。
6.根据权利要求2到权利要求4中的任一项所述的用于冷却燃气涡轮/涡轮机的构件(1)的装置，其特征在于，所述肋(9)具有线性、杆状的形状。
7.根据权利要求2到权利要求6中的任一项所述的用于冷却燃气涡轮/涡轮机的构件(1)的装置，其特征在于，所述肋(9)具有不同的长度和/或高度，所述肋以此在所述目标表面(6)上延伸。
8.根据权利要求2到权利要求7中的任一项所述的用于冷却燃气涡轮/涡轮机的构件(1)的装置，其特征在于，所述肋(9)的星状布置在所述目标表面(6)上形成和布置在与冲击冷却孔(5)的对应排相对的排中。
9.根据权利要求2到权利要求8中的任一项所述的用于冷却燃气涡轮/涡轮机的构件(1)的装置，其特征在于，每个肋(9)的位于径向内侧的起点到所述中心点(Z)的距离对应于所述肋(9)的长度的大约75%-150%。
10.根据权利要求2到权利要求9中的任一项所述的用于冷却燃气涡轮/涡轮机的构件(1)的装置，其特征在于，所述肋(9)的侧翼至少在到所述目标表面(6)的连接处正交地延伸，并且优选地只在到护罩侧(10)的过渡处倾斜地形成或倒圆。
11.根据权利要求2到权利要求10中的任一项所述的用于冷却燃气涡轮/涡轮机的构件(1)的装置，其特征在于，所述护罩侧(10)形成为平坦的且平行于所述目标表面(6)。
12.一种燃气涡轮/涡轮机，其具有根据前述权利要求中的任一项所述的用于冷却燃气涡轮/涡轮机的构件(1)的装置。
CN202011230796.1A 2019-11-06 2020-11-06 借助于冲击冷却来冷却燃气涡轮/涡轮机的构件的装置 Pending CN112780353A (zh)

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