公开(公告)号：US10746029B2

公开(公告)日：2020-08-18

申请号：US15426159

申请日：2017-02-07

Applicant: General Electric Company

Inventor： Jeffrey Clarence Jones ,  Robert Alan Brittingham

IPC: F01D5/20 ,  F01D5/18 ,  F01D5/22 ,  F02C3/04

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a leading edge and a trailing edge and defines a chord extending from the leading edge to the trailing edge. A tip shroud couples to the airfoil and includes a leading edge wall and a trailing edge wall and defines a tip shroud cavity. The tip shroud cavity includes a leading edge portion at least partially defined by the leading edge wall and positioned largely upstream of fifty percent of the chord. The tip shroud cavity also includes a trailing edge portion at least partially defined by the trailing edge wall and positioned largely downstream of fifty percent of the chord. An intermediate portion of the tip shroud cavity fluidly couples the leading edge portion of the tip shroud cavity and the trailing edge portion of the tip shroud cavity.

公开(公告)号：US10519777B2

公开(公告)日：2019-12-31

申请号：US15978932

申请日：2018-05-14

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Travis J Packer ,  Jeffrey Clarence Jones ,  Nicholas William Rathay ,  Ian Darnall Reeves

IPC: F01D5/14 ,  B22F5/04 ,  B22F3/105 ,  F01D5/00 ,  B23P6/00 ,  B23K1/00 ,  B33Y80/00 ,  F01D5/18 ,  B33Y10/00 ,  B23K101/00

Abstract: The disclosure relates to a tip member configured to be coupled to a blade structure for a turbomachine. A body of the tip member includes: a first surface configured to engage a radially outboard end of the blade structure, a second surface positioned opposite the first surface, and at least one perimeter sidewall positioned between the first and second surfaces, wherein the at least one perimeter sidewall has an airfoil cross-section; and an opening passing through the body from the first surface to the second surface, and having a single directional orientation therebetween, wherein the opening is sized to receive a post positioned on the radially outboard end of the blade structure.

公开(公告)号：US10465525B2

公开(公告)日：2019-11-05

申请号：US15217041

申请日：2016-07-22

Applicant: General Electric Company

Inventor： Jeffrey Clarence Jones ,  Adam John Fredmonski

IPC: F01D5/18 ,  B33Y10/00 ,  B33Y50/02 ,  B33Y80/00 ,  B23K26/342 ,  B23K26/70 ,  F01D5/14 ,  F01D9/04 ,  F01D25/12 ,  B23K15/00 ,  B29C64/106 ,  B29C64/153 ,  B29C64/386 ,  B23K101/00 ,  B23K103/18

Abstract: A blade includes an airfoil body defined by a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant, the airfoil body having an outer surface and an inner surface facing the radially extending chamber. A first corrugated surface is on at least a portion of the outer surface of the airfoil body; and a first rib partitions the radially extending chamber, the first rib including a first side and an opposing second side. A second corrugated surface is on at least a portion of at least one of the first and second sides of the first rib.

公开(公告)号：US20190105822A1

公开(公告)日：2019-04-11

申请号：US15728890

申请日：2017-10-10

Applicant: General Electric Company

Inventor： Jose Troitino Lopez ,  Eric Lee Bell ,  Jeffrey Clarence Jones

IPC: B29C45/26 ,  B22C7/02 ,  B22C9/10 ,  B33Y80/00 ,  B29C45/14 ,  B29C45/78

Abstract: A mold system and method for forming a casting article for investment casting is disclosed. The mold system includes a mold for receiving therein a selected core chosen from a plurality of varied cores. The mold includes a plurality of separable mold portions that are coupleable together to create the mold and configured to form a sacrificial material from a sacrificial material fluid about the selected core. At least one selected separable mold portion of the plurality of separable mold portions includes a set of varied interchangeable versions of the at least one selected separable mold portion. Each varied interchangeable version of the selected separable mold portion is configured to accommodate a different core of the plurality of varied cores. A number of systems for controlling a temperature of the mold are also disclosed.

公开(公告)号：US20180328193A1

公开(公告)日：2018-11-15

申请号：US15426159

申请日：2017-02-07

Applicant: General Electric Company

Inventor： Jeffrey Clarence Jones ,  Robert Alan Brittingham

IPC: F01D5/20 ,  F01D5/18 ,  F02C3/04

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a leading edge and a trailing edge and defines a chord extending from the leading edge to the trailing edge. A tip shroud couples to the airfoil and includes a leading edge wall and a trailing edge wall and defines a tip shroud cavity. The tip shroud cavity includes a leading edge portion at least partially defined by the leading edge wall and positioned largely upstream of fifty percent of the chord. The tip shroud cavity also includes a trailing edge portion at least partially defined by the trailing edge wall and positioned largely downstream of fifty percent of the chord. An intermediate portion of the tip shroud cavity fluidly couples the leading edge portion of the tip shroud cavity and the trailing edge portion of the tip shroud cavity.

公开(公告)号：US20180023403A1

公开(公告)日：2018-01-25

申请号：US15217062

申请日：2016-07-22

Applicant: General Electric Company

Inventor： Jeffrey Clarence Jones ,  Adam John Fredmonski

IPC: F01D9/02 ,  F01D5/18 ,  F01D25/12 ,  F01D5/14

CPC classification number: F01D5/187 ,  F01D5/141 ,  F01D5/145 ,  F01D5/147 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/184 ,  F05D2250/61 ,  F05D2260/204 ,  F05D2260/22141 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine vane includes an airfoil body having a leading edge, a trailing edge and a smooth outer surface. A cutout is included within at least one of the leading edge and the trailing edge, the cutout removing a predetermined area of the airfoil body. A coupon is coupled in the cutout to replace the predetermined area of the airfoil body. The coupon includes a first corrugated surface on at least a portion of an outer surface thereof. The coupon allows for the addition of advantageous wake mixing and cooling efficiencies to preexisting vanes.