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公开(公告)号：US10822986B2
公开(公告)日：2020-11-03
申请号：US16263548
申请日：2019-01-31
Applicant: General Electric Company
Inventor： Zachary John Snider , David Wayne Weber
Abstract: Turbine shrouds including internal cooling passages are disclosed. The shrouds may include a unitary body including a support portion, an intermediate portion formed integral with and extending from the support portion, and a seal portion formed integral with the intermediate portion, opposite the support portion. The unitary body may also include two opposing slash faces extending between the support portion and the seal portion, a HGP seal slot formed on each of the two opposing slash faces, and at least one plenum and cooling passage extending through the support portion, intermediate portion, and/or the seal portion. The unitary body may also include an exhaust channel and slash face exhaust holes formed in each of the two opposing slash faces. The exhaust channel may be in fluid communication with the cooling passage(s), and the slash face exhaust holes may be in fluid communication with the exhaust channel.
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公开(公告)号：US10746057B2
公开(公告)日：2020-08-18
申请号：US16116165
申请日：2018-08-29
Applicant: General Electric Company
Inventor： Zachary John Snider , Gary Charles Liotta
Abstract: A method for constructing a variable nozzle assembly within a turbine engine that includes: constructing a variable nozzle sub-assembly; attaching the variable nozzle sub-assembly to a casing; and linking segments of a segmented shaft via an opening. Constructing the variable nozzle sub-assembly may include: attaching a downstream inner platform to a upstream inner platform; inserting an outer stem of a first segment through an outer stem opening formed through the downstream outer platform; connecting the first segment to the downstream outer platform by loading a first bearing about a protruding spherical shaped section of the outer stem; inserting the inner stem through an opening formed through the downstream inner platform while aligning sidewalls of the downstream and upstream outer platforms; mechanically securing the aligned sidewalls; and connecting the first segment to the downstream inner platform by loading a second bearing about a protruding spherical shaped section of the inner stem.
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公开(公告)号：US20200248558A1
公开(公告)日：2020-08-06
申请号：US16263548
申请日：2019-01-31
Applicant: General Electric Company
Inventor： Zachary John Snider , David Wayne Weber
Abstract: Turbine shrouds including internal cooling passages are disclosed. The shrouds may include a unitary body including a support portion, an intermediate portion formed integral with and extending from the support portion, and a seal portion formed integral with the intermediate portion, opposite the support portion. The unitary body may also include two opposing slash faces extending between the support portion and the seal portion, a HGP seal slot formed on each of the two opposing slash faces, and at least one plenum and cooling passage extending through the support portion, intermediate portion, and/or the seal portion. The unitary body may also include an exhaust channel and slash face exhaust holes formed in each of the two opposing slash faces. The exhaust channel may be in fluid communication with the cooling passage(s), and the slash face exhaust holes may be in fluid communication with the exhaust channel.
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公开(公告)号：US10711632B2
公开(公告)日：2020-07-14
申请号：US16116153
申请日：2018-08-29
Applicant: General Electric Company
Inventor： Zachary John Snider , Gary Charles Liotta
Abstract: A turbine engine having a variable nozzle assembly that includes: a variable nozzle having an airfoil that extends radially across an annulus formed between inner and outer platforms; and a segmented shaft that translates a torque between segments included therewithin. The segmented shaft may include a first and second segment. The first segment of the segmented shaft may include: the airfoil of the variable nozzle; an outer stem extending from the outer end of the airfoil; and an inner stem extending from the inner end of the airfoil. A first and second connector may connect the first segment to the inner platform and outer platform, respectively. A third connector may connect the first segment to the second segment. The first and second connector may include a first and second spherical bearing, respectively. The third connector may include a first universal joint.
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公开(公告)号：US20200072073A1
公开(公告)日：2020-03-05
申请号：US16116153
申请日：2018-08-29
Applicant: General Electric Company
Inventor： Zachary John Snider , Gary Charles Liotta
Abstract: A turbine engine having a variable nozzle assembly that includes: a variable nozzle having an airfoil that extends radially across an annulus formed between inner and outer platforms; and a segmented shaft that translates a torque between segments included therewithin. The segmented shaft may include a first and second segment. The first segment of the segmented shaft may include: the airfoil of the variable nozzle; an outer stem extending from the outer end of the airfoil; and an inner stem extending from the inner end of the airfoil. A first and second connector may connect the first segment to the inner platform and outer platform, respectively. A third connector may connect the first segment to the second segment. The first and second connector may include a first and second spherical bearing, respectively. The third connector may include a first universal joint.
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Patent Agency Ranking
公开(公告)号：US20200025026A1
公开(公告)日：2020-01-23
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
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.
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公开(公告)号：US10465521B2
公开(公告)日：2019-11-05
申请号：US15334483
申请日：2016-10-26
Applicant: General Electric Company
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.
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公开(公告)号：US10233761B2
公开(公告)日：2019-03-19
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
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.
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公开(公告)号：US09863269B2
公开(公告)日：2018-01-09
申请号：US15347879
申请日：2016-11-10
Applicant: General Electric Company
Inventor： Donald W. Shaw , Kurt Kramer Schleif , Zachary John Snider
CPC classification number: F01D21/003 , F03D7/042 , F03D80/82 , F05D2220/31 , F05D2220/32 , F05D2240/60 , F05D2260/80 , Y02E10/72
Abstract: A system for packaging electronic components in a rotatable shaft includes an annular carrier shaft having a first end that is axially spaced from a second end and an inner surface that is radially spaced from an outer surface, and a plurality of transmitter assemblies annularly arranged within the carrier shaft. Each transmitter assembly includes a transmitter housing radially supported within the carrier shaft via a pair of circumferentially spaced rail members. Each transmitter assembly comprises a daughter board that extends laterally and longitudinally across a bottom portion of the transmitter housing and at least one electronic component electrically coupled to the daughter board. The electronic component extends substantially perpendicular to the daughter board within the transmitter housing.
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公开(公告)号：US09777589B2
公开(公告)日：2017-10-03
申请号：US14522622
申请日：2014-10-24
Applicant: General Electric Company
Inventor： Kurt Kramer Schleif , Donald W. Shaw , Zachary John Snider , Mario Joseph Arceneaux
CPC classification number: F01D21/003 , F01D17/06 , F01D17/08 , F01D17/085 , F03D17/00 , F03D80/00 , F03D80/85 , F05D2220/30 , F05D2240/60 , F05D2260/83 , H02G1/08
Abstract: A system for routing rotatable wire bundles which extend from a rotor shaft of a turbomachine includes a plurality of wire bundles which extend outwardly from an inner passage of the rotor shaft of the turbomachine. An annular wire barrel is coupled to an end of the rotor shaft. A plurality of thru-holes is defined within and/or by the wire barrel. The plurality of thru-holes is annularly arranged therein. Each thru-hole extends through an aft wall of the wire barrel and is circumferentially spaced from adjacent thru-holes. Each wire bundle extends individually through a corresponding thru-hole of the plurality of thru-holes.
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