公开(公告)号：US20210301667A1

公开(公告)日：2021-09-30

申请号：US16835476

申请日：2020-03-31

Applicant: General Electric Company

Inventor： Mark Steven Honkomp ,  William Scott Zemitis ,  Melbourne James Myers ,  Jacob Charles Perry, II

IPC: F01D5/18

Abstract: A rotor blade for a turbomachine is provided. The rotor blade includes a platform, an airfoil extending from the platform, and a cooling circuit extending within the platform and the airfoil. The cooling circuit includes a plurality of cooling passages defined by a plurality of ribs. The plurality of ribs includes an offset rib.

公开(公告)号：US20200173291A1

公开(公告)日：2020-06-04

申请号：US16207995

申请日：2018-12-03

Applicant: General Electric Company

Inventor： Nicholas William Rathay ,  William Dwight Gerstler ,  Mark Steven Honkomp

IPC: F01D5/20 ,  F01D5/18

Abstract: A tip for a turbine component, turbine rotor blade or tip of a blade, is disclosed. The tip includes a tip plate configured to be coupled at a tip end of an airfoil chamber; and a tip rail extending radially from the tip plate, the tip rail disposed near or at a periphery of the tip plate. The trip rail includes a cooling structure constituting at least a portion of the tip rail. The cooling structure is in fluid communication with the airfoil chamber, and includes a plurality of repeating, three dimensional unit cells. Each unit cell defines a flow passage that is in fluid communication with the flow passage of at least one other unit cell. The flow passages of the 3D unit cells create a tortuous cooling passage in at least a portion of the tip rail.

公开(公告)号：US10156146B2

公开(公告)日：2018-12-18

申请号：US15137341

申请日：2016-04-25

Applicant: General Electric Company

Inventor： Jalindar Appa Walunj ,  Mark Steven Honkomp

IPC: F02C7/12 ,  F01D5/18 ,  F01D5/14

Abstract: The present disclosure is directed to an airfoil for a gas turbine rotor blade. The airfoil includes a pressure side wall and a suction side wall connected to the pressure side wall at a leading edge portion and a trailing edge portion. The pressure side wall and the suction side wall collectively define an internal cavity within the airfoil. A plurality of pins is disposed within the internal cavity. The trailing edge portion defines a first cooling passage having a first inlet spaced apart from a first outlet by a first length and a second cooling passage comprising a second inlet spaced apart from a second outlet by a second length. The first length is greater than the second length.

公开(公告)号：US10001014B2

公开(公告)日：2018-06-19

申请号：US15019516

申请日：2016-02-09

Applicant: General Electric Company

Inventor： Mark Steven Honkomp ,  Xiaoyong Fu ,  Paul Kendall Smith ,  Jalindar Appa Walunj

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F01D5/143 ,  F01D5/147 ,  F05D2220/30 ,  F05D2250/74 ,  Y02T50/673

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.