公开(公告)号：JP2013096411A

公开(公告)日：2013-05-20

申请号：JP2012236241

申请日：2012-10-26

Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

Inventor： GREEN BRIAN ,  NOLAN SEAN

IPC: F01D5/14 ,  F04D29/54

CPC classification number: F01D5/143 ,  F05D2250/73 ,  F05D2250/74 ,  Y02T50/673

Abstract: PROBLEM TO BE SOLVED: To provide a stator vane airfoil formed with non-axisymmetrical inner diameter and outer diameter endwall contour.SOLUTION: An airfoil comprises a pressure surface and a suction surface extending axially from a leading edge to a trailing edge and radially from a base section to a tip section, and the base section and the tip section define a mean span therebetween. An inner endwall defines an inner endwall contour, by extending axially and circumferentially from the base section, and an outer endwall defines an outer endwall contour, by extending axially and circumferentially from the tip section. The inner and outer endwall contours are defined by varying radial deviations from circumferentially uniform nominal inner and outer radii, where one of the radial deviations varies axially and circumferentially by at least 3% of the mean span of the airfoil.

Abstract translation: 要解决的问题：提供一种形成有非轴对称内径和外径端壁轮廓的定子叶片翼型件。 解决方案：翼型件包括压力表面和从前缘到后缘轴向延伸并且从基部到末端部分的径向延伸的吸力表面，并且基部和末端部分在其间限定了平均间距。 内端壁通过从基部轴向和周向延伸而限定内端壁轮廓，并且外端壁通过从尖端部分轴向和周向延伸而限定外端壁轮廓。 内外壁轮廓通过从周向均匀的标称内径和外半径变化的径向偏差来限定，其中径向偏差之一轴向和周向变化至少为翼型平均跨度的3％。 版权所有（C）2013，JPO＆INPIT

公开(公告)号：CA2789467C

公开(公告)日：2019-05-07

申请号：CA2789467

申请日：2012-09-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GREEN BRIAN ,  NOLAN SEAN

IPC: F01D9/02 ,  F04D29/30

Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, defining a mean span therebetween. An inner endwall defines an inner endwall contour extending axially and circumferentially from the root section, and an outer endwall defines an outer endwall contour extending axially and circumferentially from the tip section. The inner and outer endwall contours are defined by varying radial deviations from circumferentially uniform nominal inner and outer radii, where one of the radial deviations varies axially and circumferentially by at least three percent of a mean span of the airfoil.

公开(公告)号：EP2885506A4

公开(公告)日：2016-04-13

申请号：EP13829595

申请日：2013-03-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TURNER MATTHEW A ,  ALARCON ANDREW G ,  GLASPEY JAMES ,  GREEN BRIAN ,  FORD BARRY M ,  JUREK RENEE J

IPC: F01D5/30 ,  F01D5/02 ,  F01D5/12 ,  F01D5/14 ,  F02C7/00

CPC classification number: F01D5/30 ,  F01D5/02 ,  F01D5/143 ,  F01D5/145 ,  F01D11/008 ,  F05D2220/32 ,  F05D2240/55 ,  Y02T50/673

公开(公告)号：SG11201407843UA

公开(公告)日：2015-03-30

申请号：SG11201407843U

申请日：2013-03-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TURNER MATTHEW A ,  ALARCON ANDREW G ,  GLASPEY JAMES ,  GREEN BRIAN ,  FORD BARRY M ,  JUREK RENEE J

IPC: F01D5/30 ,  F01D5/12 ,  F02C7/00

Abstract: A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge. The first depression is formed along the flowpath surface adjoining the suction side edge, and the second depression is formed along the flowpath surface adjoining the pressure side edge.

公开(公告)号：CA2789467A1

公开(公告)日：2013-05-01

申请号：CA2789467

申请日：2012-09-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GREEN BRIAN ,  NOLAN SEAN

IPC: F01D9/02 ,  F04D29/30

Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, defining a mean span therebetween. An inner endwall defines an inner endwall contour extending axially and circumferentially from the root section, and an outer endwall defines an outer endwall contour extending axially and circumferentially from the tip section. The inner and outer endwall contours are defined by varying radial deviations from circumferentially uniform nominal inner and outer radii, where one of the radial deviations varies axially and circumferentially by at least three percent of a mean span of the airfoil.