公开(公告)号：US20210131291A1

公开(公告)日：2021-05-06

申请号：US16674059

申请日：2019-11-05

Applicant: General Electric Company

Inventor： Melbourne James Myers ,  Michael Anthony Wondrasek ,  Mary Virginia Holloway ,  Luke C. Sponseller ,  Brandon Joseph Kerins

IPC: F01D5/18

Abstract: A turbine blade includes a root for fixing the turbine blade to a turbine rotor; and an airfoil coupled to the root, the airfoil including a suction side and a pressure side, and at least one internal wall defining a coolant chamber in the airfoil for delivering a coolant through the airfoil. A tip shroud is coupled to a radially outer end of the airfoil by a suction side fillet and a pressure side fillet. The tip shroud includes a shroud body defining a substantially trident-shaped shroud cooling passage including: a trunk cooling passage, a center cooling passage in fluid communication with the trunk cooling passage, a suction side cooling passage in fluid communication with the trunk cooling passage, and a pressure side cooling passage in fluid communication with the trunk cooling passage. The center cooling passage is fluidly coupled to the coolant chamber to receive a coolant.

公开(公告)号：US11225872B2

公开(公告)日：2022-01-18

申请号：US16674059

申请日：2019-11-05

Applicant: General Electric Company

Inventor： Melbourne James Myers ,  Michael Anthony Wondrasek ,  Mary Virginia Holloway ,  Luke C. Sponseller ,  Brandon Joseph Kerins

IPC: F01D5/18

Abstract: A turbine blade includes a root for fixing the turbine blade to a turbine rotor; and an airfoil coupled to the root, the airfoil including a suction side and a pressure side, and at least one internal wall defining a coolant chamber in the airfoil for delivering a coolant through the airfoil. A tip shroud is coupled to a radially outer end of the airfoil by a suction side fillet and a pressure side fillet. The tip shroud includes a shroud body defining a substantially trident-shaped shroud cooling passage including: a trunk cooling passage, a center cooling passage in fluid communication with the trunk cooling passage, a suction side cooling passage in fluid communication with the trunk cooling passage, and a pressure side cooling passage in fluid communication with the trunk cooling passage. The center cooling passage is fluidly coupled to the coolant chamber to receive a coolant.

公开(公告)号：US10954797B1

公开(公告)日：2021-03-23

申请号：US16824916

申请日：2020-03-20

Applicant: General Electric Company

Inventor： John Franklin Ryman ,  Brandon Joseph Kerins ,  Mary Virginia Holloway

IPC: F01D5/14

Abstract: The present application provides a turbine rotor blade including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z 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 expressed in a unit of distance (e.g., inches) by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values may be joined smoothly with one another to form a complete airfoil shape.