公开(公告)号：US11308249B2

公开(公告)日：2022-04-19

申请号：US16457147

申请日：2019-06-28

Applicant: General Electric Company

Inventor： Sathyanarayanan Raghavan ,  Ananda Barua ,  Evan Dozier ,  Joseph Block ,  Brendon Leary ,  Prabhjot Singh ,  Arvind Rangarajan ,  Changjie Sun ,  Dean Robinson

IPC: G06F30/20 ,  B29C64/393 ,  B29C64/40 ,  B33Y40/00 ,  B33Y50/02 ,  G06F119/08 ,  G06F119/18

Abstract: A method, medium, and system to receive a specification defining a model of a part to be produced by an additive manufacturing (AM) process; execute an AM simulation on the model of the part to determine a prediction of thermal distortions to the part; execute a topology optimization (TO) to create TO supports that counteract the predicted thermal distortions; generate at least one rule-based support based on a geometry of the part to interface with the part at one or more regions other than the TO supports; combining the TO supports and the at least one rule-based support to generate a set of hybrid supports; save a record of the set of hybrid supports; and transmit the record of the set of hybrid supports to an AM controller to control an AM system to generate a support structure for an AM production of the part.

公开(公告)号：US10247009B2

公开(公告)日：2019-04-02

申请号：US15163061

申请日：2016-05-24

Applicant: General Electric Company

Inventor： Melbourne James Myers ,  Xiuzhang James Zhang ,  Stuart Samuel Collins ,  Camilo Andres Sampayo ,  Joseph Block

IPC: F01D5/08 ,  F01D5/18 ,  F01D5/14

Abstract: The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.

公开(公告)号：US20170342841A1

公开(公告)日：2017-11-30

申请号：US15163061

申请日：2016-05-24

Applicant: General Electric Company

Inventor： Melbourne James Myers ,  Xiuzhang James Zhang ,  Stuart Samuel Collins ,  Camilo Andres Sampayo ,  Joseph Block

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/143 ,  F01D5/186 ,  F05D2220/32 ,  F05D2240/304 ,  F05D2240/306 ,  F05D2240/81 ,  F05D2260/20

Abstract: The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.