公开(公告)号：US20160076383A1

公开(公告)日：2016-03-17

申请号：US14856512

申请日：2015-09-16

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  Jesse M. Carr ,  Bryan P. Dube ,  Yongxiang D. Xue

IPC: F01D5/18 ,  F01D25/12 ,  F23R3/00 ,  F02C7/24 ,  F23R3/06 ,  F01D11/08 ,  F02C7/18

CPC classification number: F01D5/186 ,  F01D9/065 ,  F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F02C7/24 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2250/14 ,  F05D2260/202 ,  F05D2300/16 ,  F05D2300/20 ,  F05D2300/6033 ,  F23R3/002 ,  F23R3/06 ,  Y02T50/672 ,  Y02T50/676

Abstract: A film cooled component includes multiple film cooling holes. At least one of the film cooling holes has an elliptical cross sectional opening along the exterior surface of the film cooled component.

Abstract translation: 膜冷却部件包括多个膜冷却孔。 薄膜冷却孔中的至少一个具有沿着薄膜冷却部件的外表面的椭圆形横截面开口。

公开(公告)号：US10570749B2

公开(公告)日：2020-02-25

申请号：US15004498

申请日：2016-01-22

Applicant: United Technologies Corporation

Inventor： Charles Thistle ,  Yongxiang D. Xue

IPC: F01D5/18 ,  F01D5/14 ,  F01D9/04 ,  F01D25/12

Abstract: A component for a gas turbine engine is provided. The component having: a platform; an airfoil secured to and extending radially from the platform, the airfoil having an exterior surface extending from a leading edge and a trailing edge; an internal cooling cavity located within the airfoil; and a first row of pedestals extending between opposite sides of the internal cavity and a second row of pedestals adjacent to the first row of pedestals and extending between opposite sides of the internal cavity, wherein the first row of pedestals are further from the trailing edge than the second row of pedestals and a lowermost pedestal of the first row of pedestals is further from the platform than a lowermost pedestal of the second row of pedestals.

公开(公告)号：US20170211394A1

公开(公告)日：2017-07-27

申请号：US15004498

申请日：2016-01-22

Applicant: United Technologies Corporation

Inventor： Charles Thistle ,  Yongxiang D. Xue

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D5/14

Abstract: A component for a gas turbine engine is provided. The component having: a platform; an airfoil secured to and extending radially from the platform, the airfoil having an exterior surface extending from a leading edge and a trailing edge; an internal cooling cavity located within the airfoil; and a first row of pedestals extending between opposite sides of the internal cavity and a second row of pedestals adjacent to the first row of pedestals and extending between opposite sides of the internal cavity, wherein the first row of pedestals are further from the trailing edge than the second row of pedestals and a lowermost pedestal of the first row of pedestals is further from the platform than a lowermost pedestal of the second row of pedestals.