公开(公告)号：US20240110484A1

公开(公告)日：2024-04-04

申请号：US17937851

申请日：2022-10-04

Applicant: General Electric Company

Inventor： James Zhang ,  John McConnell Delvaux ,  Zachary John Snider

IPC: F01D5/16 ,  F01D9/04 ,  F01D25/06

CPC classification number: F01D5/16 ,  F01D9/041 ,  F01D25/06 ,  F05D2220/30 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/96

Abstract: A vibration damping system includes a vibration damping element for a turbomachine nozzle or blade. A body opening extends through the turbomachine nozzle or blade between the tip end and the base end thereof. A vibration damping element includes a volute spring vibration damping element configured to be installed within the body opening in the turbomachine nozzle or blade. The volute spring vibration damping element includes a spiral coil of a metal sheet strip with a surface of the metal sheet strip contacting itself in a direction of an axis of the coil. The body opening has an inner dimension, and the volute spring vibration damping element has an outer dimension sized to frictionally engage the inner dimension of the body opening to dampen vibration. In certain embodiments, the body opening and the volute spring vibration damping element each have a conical perspective shape.

公开(公告)号：US20240035384A1

公开(公告)日：2024-02-01

申请号：US17815372

申请日：2022-07-27

Applicant: General Electric Company

Inventor： Zachary John Snider ,  Brad Wilson VanTassel ,  Brian Denver Potter ,  John McConnell Delvaux

IPC: F01D25/04 ,  F01D25/06

CPC classification number: F01D25/04 ,  F01D25/06 ,  F05D2220/32 ,  F05D2260/96

Abstract: A vibration dampening system includes a vibration dampening element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration dampening element includes a plurality of stacked damper pins within the body opening. The damper pins include an outer body having an inner opening, a first end surface and an opposing second end surface; and an inner body nested and movable within the inner opening of the outer body. The end surfaces frictionally engage to dampen vibration. The inner body has a first central opening including a first portion configured to engage an elongated body therein and an outer surface configured to frictionally engage a portion of the inner opening of the outer body to dampen vibration.

公开(公告)号：US11248471B2

公开(公告)日：2022-02-15

申请号：US16749167

申请日：2020-01-22

Applicant: General Electric Company

Inventor： Zachary John Snider

IPC: F01D5/18

Abstract: A turbine rotor blade is additively manufactured and includes an airfoil body including a concave pressure side outer wall and a convex suction side outer wall that connect along leading and trailing edges. A shank is at a radial inner end of the airfoil body, and at least one angel wing extends laterally from at least one side of the shank. A coolant transfer passage is defined through the at least one angel wing. The coolant transfer passage fluidly couples a first wheel space portion defined between the shank and a first adjacent shank of a first adjacent turbine rotor blade and a second wheel space portion defined between the shank and a second adjacent shank of a second adjacent turbine rotor blade. The coolant transfer passage allows coolant to pass between wheel space portions of adjacent turbine rotor blades.

公开(公告)号：US11220916B2

公开(公告)日：2022-01-11

申请号：US16749158

申请日：2020-01-22

Applicant: General Electric Company

Inventor： Zachary John Snider

IPC: F01D5/18 ,  F01D25/12

Abstract: A turbine rotor blade is additively manufactured and includes an airfoil body with a radially extending chamber for receiving a coolant flow. A platform extends laterally outward relative to the airfoil body and terminates at at least one slash face. A cooling circuit is within the platform and is in fluid communication with a source of the coolant flow. Cooling passage(s) are in the platform and in fluid communication with the cooling circuit. The cooling passage(s) extend in a non-linear configuration from the cooling circuit to exit through the at least one slash face of the platform, providing improved cooling compared to linear cooling passages.

公开(公告)号：US11215074B2

公开(公告)日：2022-01-04

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: F01D25/12 ,  F01D25/14 ,  F01D21/14 ,  B33Y80/00

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：US11179917B2

公开(公告)日：2021-11-23

申请号：US15401575

申请日：2017-01-09

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Matthew Troy Hafner ,  John McConnell Delvaux ,  Glenn Curtis Taxacher ,  Zachary John Snider

IPC: B32B18/00 ,  C04B35/573 ,  C04B35/80 ,  C04B37/00 ,  F01D25/00 ,  F01D5/28 ,  F01D9/02

Abstract: A CMC ply assembly is disclosed including at least one matrix ply interspersed amongst a plurality of CMC plies. Each of the plurality of CMC plies includes a first matrix and a plurality of ceramic fibers. The at least one matrix ply includes a second matrix and is essentially free of ceramic fibers. The plurality of CMC plies and the at least one matrix ply are arranged in an undensified ply stack having an article conformation. A CMC article is disclosed including a plurality of densified CMC plies and at least one densified matrix ply interspersed amongst the plurality of densified CMC plies. A method for forming the CMC article is disclosed including forming, carburizing, infusing a melt infiltration agent into, and densifying the CMC ply assembly. The melt infiltration agent infuses more completely through the at least one matrix ply than through the plurality of CMC plies.

公开(公告)号：US11098596B2

公开(公告)日：2021-08-24

申请号：US15624252

申请日：2017-06-15

Applicant: General Electric Company

Inventor： Zachary John Snider ,  Daniel Burnos ,  Lana Maria Osusky ,  Brian Gene Brzek ,  Gregory Thomas Foster

IPC: F01D5/18

Abstract: A turbine airfoil includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a cooling air supply cavity disposed within the turbine airfoil, and a near wall cooling cavity disposed within the turbine airfoil and fluidly coupled to the cooling air supply cavity to receive cooling air. In addition, the near wall cooling cavity partially extends along the suction side wall from adjacent the leading edge to a location more proximal the trailing edge. Moreover, the near wall cooling cavity provides near wall cooling to a high heat load region along the suction side wall.

公开(公告)号：US10989068B2

公开(公告)日：2021-04-27

申请号：US16040062

申请日：2018-07-19

Applicant: General Electric Company

Inventor： Travis J Packer ,  Benjamin Paul Lacy ,  Ibrahim Sezer ,  Zachary John Snider ,  Brad Wilson VanTassel

IPC: F01D25/12 ,  F01D11/08

Abstract: Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a unitary body including a forward and aft end, an outer surface facing a cooling chamber formed between the unitary body and a turbine casing of the turbine system, and an inner surface facing a hot gas flow path. The shrouds may also include a first cooling passage extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the first cooling passage to the cooling chamber. Additionally, the shrouds may include a second cooling passage and/or a third cooling passage. The second cooling passage may extend adjacent the forward end and may be in fluid communication with the first cooling passage. The third cooling passage may extend adjacent the aft end, and may be in fluid communication with the first cooling passage.

公开(公告)号：US20200248559A1

公开(公告)日：2020-08-06

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

Abstract: A turbine shroud for turbine systems are disclosed. The shrouds 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：US20180017466A1

公开(公告)日：2018-01-18

申请号：US15716797

申请日：2017-09-27

Applicant: General Electric Company

Inventor： Andrea Booher Kretschmar ,  Zachary John Snider ,  Nathan Lee Brown ,  Kurt Kramer Schleif ,  Michael Allen Ball

IPC: G01M15/14 ,  G01D11/30 ,  F01D17/02

CPC classification number: G01M15/14 ,  F01D17/02 ,  G01D11/30

Abstract: A system for attaching a probe to a casing of a gas turbine engine is disclosed. The system may include a probe receptacle attachable to the casing. The probe receptacle may include an internal bore, a bayonet slot, a spring disposed within the internal bore adjacent to the bayonet slot, and a sealing surface within the internal bore. The system also may include a probe attachment assembly disposed about the probe and configured to engage the probe receptacle. The probe attachment assembly may include at least one bayonet positionable within the bayonet slot and a seal positionable adjacent to the sealing surface within the internal bore.