公开(公告)号：US20140219778A1

公开(公告)日：2014-08-07

申请号：US13630419

申请日：2012-09-28

Applicant: United Technologies Corporation

Inventor： Mark A. Boeke ,  Shawn J. Gregg ,  Sarah Riley ,  Jeffrey J. DeGray ,  Richard M. Salzillo

IPC: F01D5/18 ,  F01D9/02

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D9/02 ,  F01D25/12 ,  F01D25/246 ,  F05D2240/12 ,  F05D2240/81 ,  F05D2260/204 ,  Y02T50/672 ,  Y02T50/676

Abstract: A stator vane for a gas turbine engine includes an airfoil extending in a radial direction and supported by a platform having a gas flowpath surface. A cooling passage is arranged in the platform and includes a circumferential passage that is fluidly connected to an inlet passage extending through and edge of the platform, and film cooling holes extending from the gas flowpath surface to the circumferential passage, radial extending passage through the edge of the platform. A void is interconnected to at least one of the radially extending passage and the inlet passage.

Abstract translation: 用于燃气涡轮发动机的定子叶片包括沿径向延伸并由具有气体流路表面的平台支撑的翼型件。 冷却通道布置在平台中，并且包括流体连接到延伸通过平台的边缘的入口通道的圆周通道，以及从气体流路表面延伸到周向通道的膜冷却孔，通过边缘的径向延伸通道 的平台。 空隙与径向延伸通道和入口通道中的至少一个相互连接。

公开(公告)号：US09803488B2

公开(公告)日：2017-10-31

申请号：US14590317

申请日：2015-01-06

Applicant: United Technologies Corporation

Inventor： Sarah Riley ,  Kristopher K. Anderson

IPC: F01D9/04 ,  F01D5/18 ,  F01D25/12

CPC classification number: F01D9/041 ,  F01D5/186 ,  F01D25/12 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

公开(公告)号：US09334755B2

公开(公告)日：2016-05-10

申请号：US13630107

申请日：2012-09-28

Applicant: United Technologies Corporation

Inventor： Sarah Riley ,  Mark A. Boeke ,  Jeffrey J. DeGray ,  Shawn J. Gregg

IPC: F01D5/18 ,  F01D25/12 ,  F01D9/02

CPC classification number: F01D25/12 ,  F01D5/187 ,  F01D9/02 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2240/127 ,  F05D2240/81 ,  F05D2250/183 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/672 ,  Y02T50/676

Abstract: An airfoil component for a gas turbine engine includes an airfoil extending from a platform. At least one of the airfoil and the platform includes a cooling passage defined by a surface. A chevron-shaped trip strip extends from the surface into the cooling passage at a trip strip height along a length. The trip strip height varies along the length. A turbine vane for a gas turbine engine includes inner and outer platforms. A cooling passage is provided in the inner platform. The cooling passage is provided by first and second radially extending legs spaced circumferentially apart from one another and joined to one another by a circumferential passage. A pair of airfoils extend radially from the same inner platform. A trip strip extends from the surface into the circumferential passage at a trip strip height along a length. The trip strip height varying along the length.

Abstract translation: 用于燃气涡轮发动机的翼型件包括从平台延伸的翼型件。 翼型件和平台中的至少一个包括由表面限定的冷却通道。 一个V形形状的跳闸条从一个长度的跳闸带高度从表面延伸到冷却通道中。 跳闸条高度沿长度变化。 用于燃气涡轮发动机的涡轮叶片包括内平台和外平台。 在内平台上设有冷却通道。 冷却通道由第一和第二径向延伸的腿部彼此周向间隔开并且通过周向通道彼此连接而设置。 一对翼型件从相同的内平台径向延伸。 跳闸条沿着一段长度以一个跳闸带高度从表面延伸到圆周通道中。 行程长度沿长度变化。

公开(公告)号：US20150211376A1

公开(公告)日：2015-07-30

申请号：US14590317

申请日：2015-01-06

Applicant: United Technologies Corporation

Inventor： Sarah Riley ,  Kristopher K. Anderson

IPC: F01D9/02

CPC classification number: F01D9/041 ,  F01D5/186 ,  F01D25/12 ,  F05D2250/74 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

Abstract translation: 叶片包括具有延伸穿过翼型件的外表面的多个薄膜冷却孔的一对翼型件。 每个多个薄膜冷却孔根据表1所示的X，Y和Z的笛卡尔坐标值以几何坐标突破外表面。每个几何坐标是从平台的前缘导轨上的参考点测量的 的叶片。