公开(公告)号：US20210222565A1

公开(公告)日：2021-07-22

申请号：US16749143

申请日：2020-01-22

Applicant: General Electric Company

Inventor： Zachary John Snider ,  Brad Wilson VanTassel ,  Jeffrey Clarence Jones

IPC: F01D5/18

Abstract: A turbine rotor blade is additively manufactured and includes an airfoil body with a radially extending chamber for receiving a coolant flow, a tip end at a radial outer end of the airfoil body, and a shank at a radial inner end of the airfoil body. The radially extending chamber extends at least partially into the shank to define a shank inner surface. An integral impingement cooling structure is within the radially extending chamber. The integral impingement cooling structure allows an exterior surface of a hollow body thereof to be uniformly spaced from the airfoil inner surface despite the curvature of the chamber. The turbine rotor blade has impingement cooling throughout the blade.

公开(公告)号：US20210222560A1

公开(公告)日：2021-07-22

申请号：US16749178

申请日：2020-01-22

Applicant: General Electric Company

Inventor： Zachary John Snider

IPC: F01D5/08 ,  F01D5/18

Abstract: A turbine rotor blade root is additively manufactured and includes a shank having a radially extending chamber defined therein. A blade mount is at a radial inner end of the shank. The blade mount has a hollow interior defined therein with the hollow interior in fluid communication with the radially extending chamber. A lattice support structure is disposed within the hollow interior of the blade mount.

公开(公告)号：US10927693B2

公开(公告)日：2021-02-23

申请号：US16263596

申请日：2019-01-31

Applicant: General Electric Company

Inventor： Sathyanarayanan Raghavan ,  Gautam Suresh Naik ,  Prabhjot Singh ,  Zachary John Snider ,  Changjie Sun

IPC: F01D11/08 ,  F01D25/14 ,  F01D5/14 ,  F01D5/20

Abstract: A turbine shroud for turbine systems may include a unitary body including a support portion coupled directly to a turbine casing of the turbine system, and forward hook(s) and aft hook(s) formed integral with the support portion. The unitary body may also include an intermediate portion formed integral with and extending from the support portion. The intermediate portion may include a non-linear segment extending from the support portion, and a forward segment formed integral with the non-linear segment. The forward segment of the intermediate portion may be positioned axially upstream of the forward hook(s). Additionally the unitary body may include a seal portion formed integral with the intermediate portion, opposite the support portion. The seal portion may include a forward end formed integral with the intermediate portion. The forward end may be positioned axially upstream of the forward hook(s).

公开(公告)号：US20210010423A1

公开(公告)日：2021-01-14

申请号：US16504865

申请日：2019-07-08

Applicant: General Electric Company

Inventor： Zachary John Snider ,  Matthew Troy Hafner ,  Lyndsay Marie Kibler

IPC: F02C7/16 ,  F02C9/16 ,  F23R3/26

Abstract: A flow regulating system for increasing a flow of cooling fluid supplied to a cooling system of a component of a gas turbine system is provided. The flow regulating system includes: a pneumatic circuit embedded within a section of the component, the pneumatic circuit including a set of interconnected pneumatic passages; and a pressure-actuated switch fluidly coupled to the pneumatic circuit. The pressure-actuated switch is activated in response to a formation of a breach in the section of the component and an exposure of at least one of the pneumatic passages of the pneumatic circuit embedded in the section of the component. The activation of the pressure-actuated switch increases the flow of cooling fluid supplied to the cooling system of the component.

公开(公告)号：US20200248557A1

公开(公告)日：2020-08-06

申请号：US16263430

申请日：2019-01-31

Applicant: General Electric Company

Inventor： Zachary John Snider

IPC: F01D5/14 ,  F01D25/14 ,  F01D5/20 ,  F01D11/08

Abstract: Turbine shrouds including structural breakdown and collapsible features are disclosed. The shrouds may include a unitary body including a support portion coupled directly to a turbine casing of the turbine system, an intermediate portion integral with and extending away from the support portion, and a seal portion integral with the intermediate portion. The unitary body of the shroud may also include two opposing slash faces extending adjacent to and between the support portion and the seal portion, and a plenum extending through the support portion, the intermediate portion, and at least a portion of the seal portion, between the two opposing slash faces. Additionally, the unitary body may include a bridge member(s) formed integral with the intermediate portion, and extending partially through the plenum, and an aperture(s) formed within a portion of the plenum extending through the intermediate portion.

公开(公告)号：US10260363B2

公开(公告)日：2019-04-16

申请号：US15372642

申请日：2016-12-08

Applicant: General Electric Company

Inventor： Zachary John Snider ,  Sandip Dutta ,  Kassy Moy Hart

IPC: F01D11/00 ,  F16J15/08 ,  F01D25/12 ,  F01D9/02 ,  F01D5/18 ,  B22F3/105

Abstract: Aspects of the disclosure include a sealing insert, turbine component, and code for manufacturing a sealing insert. A sealing insert includes at least one insert wall for insertion proximate a component wall to define a space between the at least one insert wall and the component wall. At least one compressible seal is provided between the at least one insert wall and the component wall. The compressible seal or seals divide the space into a plurality of compartments.

公开(公告)号：US20180371920A1

公开(公告)日：2018-12-27

申请号：US15632656

申请日：2017-06-26

Applicant: General Electric Company

Inventor： Travis J Packer ,  Elisabeth Kraus Black ,  Robert William Davidoff ,  Zachary John Snider

IPC: F01D5/14 ,  F01D5/18

Abstract: A hollowed body component made by additive manufacturing is disclosed. The hollow body has a longitudinal extent, an exterior surface and an interior surface, the interior surface having a first side and an opposing, second side. A first set of curved supports are curved along lengths thereof and extend between the first side and the opposing, second side to support the hollow body at least during the additive manufacturing thereof. Some embodiments include cooling passages open to the interior surface. Here, the curved supports extend between opposing pairs of passage-free spaces on the interior surface to support the hollow body at least during the additive manufacturing thereof. In one example, the component is an impingement insert for a hot gas path component.

公开(公告)号：US20180112547A1

公开(公告)日：2018-04-26

申请号：US15334450

申请日：2016-10-26

Applicant: General Electric Company

Inventor： Zachary John Snider ,  Gregory Thomas Foster ,  Joseph Anthony Weber ,  James Fredric Wiedenhoefer

IPC: F01D9/06 ,  F01D5/18 ,  F01D25/08

CPC classification number: F01D9/065 ,  F01D5/147 ,  F01D5/186 ,  F01D5/187 ,  F01D9/041 ,  F01D9/06 ,  F01D25/08 ,  F05D2220/32 ,  F05D2240/122 ,  F05D2240/123 ,  F05D2240/124 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2260/202 ,  F05D2260/204

Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.

公开(公告)号：US20180112534A1

公开(公告)日：2018-04-26

申请号：US15334483

申请日：2016-10-26

Applicant: General Electric Company

Inventor： Zachary John Snider ,  Gregory Thomas Foster ,  Srikanth Chandrudu Kottilingam

IPC: F01D5/18 ,  F01D9/06

CPC classification number: F01D5/147 ,  F01D5/187 ,  F01D5/286 ,  F05D2240/304

Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body and a coolant return passage extends within the airfoil body, with each passage having respective a supply and return connection passage to an exterior surface of the airfoil body. A seat in the exterior surface of the airfoil body receives a cover that includes a trench on an interior surface thereof to fluidly connect the return connection passage and the supply connection passage and form a coolant passage for the airfoil body. Various arrangements of cooling circuits may be created with the cover that allow for reuse of the coolant.

公开(公告)号：US20170342910A1

公开(公告)日：2017-11-30

申请号：US15163747

申请日：2016-05-25

Applicant: General Electric Company

Inventor： Zachary John Snider ,  Joshua Lee Margolies ,  Kurt Kramer Schleif

IPC: F02C7/32 ,  F01D21/00 ,  F02C3/04

CPC classification number: F02C7/32 ,  F01D17/02 ,  F01D21/003 ,  F01D25/00 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2240/90 ,  F05D2260/30 ,  F05D2270/80 ,  F05D2300/20 ,  F05D2300/6033 ,  Y02T50/672

Abstract: The present disclosure is directed to a system for attaching an instrument lead to a gas turbine engine component. The system includes a gas turbine engine component that includes a surface. A first sleeve couples to the surface of the gas turbine engine component. The first sleeve defines a first sleeve passageway extending therethrough. An instrument lead extends through the first sleeve passageway. A first potting material couples the instrument lead to the first sleeve to prevent the instrument lead from moving longitudinally relative to the first sleeve.