公开(公告)号：US11248479B2

公开(公告)日：2022-02-15

申请号：US16985369

申请日：2020-08-05

Applicant: General Electric Company

Inventor： Stephen Walter Newman ,  Bryan David Lewis ,  Debdulal Das

IPC: F01D9/04 ,  F01D5/18

Abstract: A cast turbine nozzle includes an airfoil having a body including a suction side, a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, and a cooling cavity defined by an inner surface of the body. The nozzle also includes at least one endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, and a plurality of heat transfer protrusions extending inwardly from the inner surface within the body, the plurality of heat transfer protrusions extending from the leading edge along the suction side and along the pressure side in a radially staggered columnar pattern. The inner surface includes a planar surface extending between adjacent heat transfer protrusions.

公开(公告)号：US20200157956A1

公开(公告)日：2020-05-21

申请号：US16191614

申请日：2018-11-15

Applicant: General Electric Company

Inventor： Sylvain Pierre ,  Bryan David Lewis ,  Debdulal Das ,  Stephen Walter Newman

IPC: F01D9/04 ,  F01D5/14

Abstract: A turbine nozzle having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.

公开(公告)号：US20150252673A1

公开(公告)日：2015-09-10

申请号：US14198659

申请日：2014-03-06

Applicant: General Electric Company

Inventor： Brad Wilson VanTassel ,  James Ryan Connor ,  Bryan David Lewis ,  Adebukola Oluwaseun Benson

IPC: F01D5/08 ,  B23P15/02

CPC classification number: F01D5/082 ,  B23P15/02 ,  F01D5/187 ,  F01D11/24 ,  F05D2240/11 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/676 ,  Y10T29/49341

Abstract: Platform cooling arrangements in a turbine rotor blade include a feedhole that extends from the suction side slash face to the interior cooling passage, and, one or more branch holes that each extends from the feedhole to the suction side slash face such that coolant flows from the interior cooling passage, through the feedhole to the one or more branch holes and exits the platform along the suction side slash face.

Abstract translation: 涡轮转子叶片中的平台冷却装置包括从吸入侧斜面向内部冷却通道延伸的进料孔，以及一个或多个分支孔，每个分支孔从进料孔延伸到吸入侧斜面，使得冷却剂从 内部冷却通道，通过进料孔到达一个或多个分支孔，并沿吸力侧斜面离开平台。