公开(公告)号：US11136890B1

公开(公告)日：2021-10-05

申请号：US16829087

申请日：2020-03-25

Applicant: General Electric Company

Inventor： Jan Emeric Agudo ,  Martin James Jasper

IPC: F01D5/18 ,  F02C3/04

Abstract: The rotor blade includes a platform and a shank extending radially inward from the platform. The rotor blade further includes an airfoil extending radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit includes a plurality of pins. The plurality of pins includes a first pin group positioned radially inward of the platform and a second pin group positioned within the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge. The plurality of exit channels is downstream from the plurality of pins. The cooling circuit also includes at least one bypass conduit extending from an inlet disposed in the cooling circuit to an outlet positioned on the trailing platform face. The at least one bypass conduit is positioned radially inward of the platform surface.

公开(公告)号：US20210301670A1

公开(公告)日：2021-09-30

申请号：US16835492

申请日：2020-03-31

Applicant: General Electric Company

Inventor： Martin James Jasper ,  Jan Agudo ,  Melbourne James Myers ,  Richard Ryan Pilson ,  Christopher W. Kester

IPC: F01D5/28

Abstract: An airfoil includes a root and a tip, which define a span of the airfoil therebetween. The airfoil also includes a leading edge and a trailing edge downstream of the leading edge along a flow direction. The leading edge and the trailing edge each extend across the span of the airfoil from the root to the tip. The airfoil further includes a pressure side surface and a suction side surface. The airfoil also includes a thermal barrier coating on the pressure side surface and the suction side surface. The thermal barrier coating includes a base layer and a top coat. A thickness of the base layer varies across each of the pressure side surface and the suction side surface with a maximum thickness of the base layer at the leading edge.

公开(公告)号：US20210301669A1

公开(公告)日：2021-09-30

申请号：US16829059

申请日：2020-03-25

Applicant: General Electric Company

Inventor： Martin James Jasper ,  Charles Wesley Wells

IPC: F01D5/26 ,  F02C3/04

Abstract: Rotor blades and turbomachines are provided. The rotor blade includes a main body having a shank, an airfoil extending radially outwardly from the shank, and a platform. The main body further includes a pressure-side slash face and a suction-side slash face. Each of the pressure-side slash face and the suction-side slash face includes a damper land and defines a slot. The damper land is disposed radially inward from the slot.

公开(公告)号：US11118460B1

公开(公告)日：2021-09-14

申请号：US16824936

申请日：2020-03-20

Applicant: General Electric Company

Inventor： Craig Allen Bielek ,  Martin James Jasper ,  Jan Emeric Agudo

IPC: F01D5/14 ,  F04D29/38

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