公开(公告)号：KR101317443B1

公开(公告)日：2013-10-10

申请号：KR1020120112364

申请日：2012-10-10

Applicant: 한국항공대학교산학협력단

Inventor： 곽재수 ,  최은영 ,  박정신

IPC: F01D5/18 ,  F02C7/12 ,  F01D25/12

CPC classification number: F01D5/187 ,  F01D5/147 ,  F01D25/12 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/20

Abstract: PURPOSE: A cooling blade of a gas turbine is provided to increase a heat transfer efficient by strengthening secondary flow by a lib because cold air flows into the inside by leaning to one side, by slantly installing multiple libs in an inner flow path and installing a structure on an inlet of the inner flow path. CONSTITUTION: A cooling blade of a gas turbine includes an airfoil (20) and an inner flow path (30). In the inner flow path of the airfoil, multiple libs (31) are slantly installed. On an inlet of the inner flow path, a structure (32) is installed to disturb the flow of cold air which flows into through an inlet port (11a). The structure is formed as multiple pins which are installed to make one side of the inlet of the inner flow path have higher density than the other side, or as a rectangular block shape which is installed to lean to one side of the inlet of the inner flow path, in order to make the inlet flow lean to one side. The inlet flow which leans to one side strengthens secondary flow by the libs in order to increase a heat transfer coefficient.

Abstract translation: 目的：提供一种燃气轮机的冷却叶片，通过加强二次流动来提高传热效率，因为冷空气通过倾斜到一侧而流入内部，通过在内部流动路径中倾斜地安装多个库，并安装 在内部流路的入口处的结构。 构成：燃气轮机的冷却叶片包括翼型件（20）和内部流动路径（30）。 在翼型件的内部流动路径中，多个库（31）倾斜地安装。 在内部流路的入口处，安装有结构（32），以扰乱通过入口（11a）流入的冷空气流。 该结构形成为多个销，其安装成使得内部流路的入口的一侧具有比另一侧更高的密度，或者形成矩形块状，该矩形块形状安装成倾斜到内侧流入口的一侧 流动路径，以使入口流动倾斜到一侧。 倾斜到一侧的入口流增强了二次流动，以增加传热系数。

公开(公告)号：KR102086260B1

公开(公告)日：2020-03-06

申请号：KR1020180146274

申请日：2018-11-23

Applicant: 한국항공대학교산학협력단

Inventor： 곽재수 ,  정진영

IPC: F01D21/00 ,  F01D5/18 ,  G01M9/06 ,  G01M9/04

公开(公告)号：KR1020170125491A

公开(公告)日：2017-11-15

申请号：KR1020160055190

申请日：2016-05-04

Applicant: 한국항공대학교산학협력단

Inventor： 곽재수 ,  장한나 ,  박정신 ,  강영준

IPC: F01D5/18 ,  F01D5/08 ,  F02C7/12

Abstract: 본발명에따른블레이드는, 냉각공기가유입되는유입구가형성된루트부; 상기루트부의상측에형성되며, 고온고압의연소가스와충돌하며, 상기유입구로유입된냉각공기가흘러가는유로가내부에형성되며, 상기유로를흘러가는공기가토출되는분사홀들이형성된에어포일; 상기유로의내벽에동일간격으로경사지게형성된복수개의립들; 및상기유로의중심부를향해돌출되도록, 상기유로의내벽에적어도하나이상설치된교란구조물;을포함하는것을특징으로한다.

Abstract translation: 根据本发明的叶片包括：具有冷却空气流过的入口的根部; 形成在根部，具有高温高压的燃烧气体的碰撞，和空气箔，其中所述入口冷却空气流动通道的所述入口端口内形成，形成的上侧是在通过流动通道的空气喷射流喷射孔; 在流路的内壁上等间隔地形成多个唇; 并且，在流路的至少一个以上的内壁上设置有向流路的中央部突出的干扰结构。

公开(公告)号：KR1020120048439A

公开(公告)日：2012-05-15

申请号：KR1020100110066

申请日：2010-11-05

Applicant: 한국항공대학교산학협력단

Inventor： 곽재수 ,  노영철

IPC: F01D5/20 ,  F01D5/14 ,  F01D11/08

CPC classification number: F01D5/20 ,  F01D5/141 ,  F01D11/08 ,  F02C7/18 ,  F05D2220/32

Abstract: PURPOSE: A gas turbine blade having a squealer tip is provided to improve the durability and the energy efficiency by forming a floor of the squealer tip into an inclined plane so that leakage flows are reduced. CONSTITUTION: A gas turbine blade having a squealer tip comprises a rim. The rim is formed on a front end edge portion of the tip. The squealer tip comprises a cavity inside the rim. A floor of the cavity is formed into an inclined plane. The inclined plane of the floor of the cavity is formed between a sidewall of a pressure surface and the sidewall of a suction surface towards a center. A width of the rim is 1.5 ~ 5% of a length of blade code. The depth from an upper end of the rim to a bottom of the cavity is 1 ~ 6% of a length of a blade span.

Abstract translation: 目的：提供一种具有尖叫尖端的燃气轮机叶片，以通过将尖叫尖端的底板形成倾斜平面来提高耐久性和能量效率，使得泄漏流量减小。 构成：具有尖叫尖端的燃气轮机叶片包括轮辋。 边缘形成在尖端的前端边缘部分上。 尖叫尖端包括边缘内的空腔。 空腔的地板形成倾斜平面。 空腔的底板的倾斜平面形成在压力表面的侧壁和抽吸表面的侧壁之间朝向中心。 边缘的宽度为刀片代码长度的1.5〜5％。 从边缘上端到空腔底部的深度是叶片跨度长度的1〜6％。