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公开(公告)号：US11092029B2
公开(公告)日：2021-08-17
申请号：US16531775
申请日：2019-08-05
Applicant: General Electric Company
Inventor： Jason David Shapiro , Jonathan David Baldiga
Abstract: A shroud hanger assembly or shroud assembly is provided for a gas turbine engine wherein a hanger includes a radially depending and axially extending arm. The arm or retainer engages a pocket formed in a shroud so as to retain the shroud in a desired position relative to the hanger. An aft retaining structure is provided on the hanger and provides a seat for a seal structure which biases the retainer so that the arm of the hanger maintains engagement in the shroud pocket. A baffle may be utilized at the hanger to cool at least some portion of the shroud.
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公开(公告)号：US10731509B2
公开(公告)日：2020-08-04
申请号：US16513033
申请日：2019-07-16
Applicant: General Electric Company
Inventor： Victor Hugo Silva Correia , Jonathan David Baldiga
Abstract: A compliant seal component, a turbomachine including such compliant seal component, and an associated method for cooling the compliant seal component disposed in the turbomachine are disclosed. The compliant seal component includes a convoluted portion and a plurality of end portions spaced apart from each other. The plurality of end portions is joined to the convoluted portion. An end portion of the plurality of end portions includes a first section and a second section, the second section defining a plenum. The end portion further includes a plurality of inlet holes and a plurality of outlet holes. The plurality of inlet holes is configured to direct a portion of a cooling fluid to the plenum. The portion of the cooling fluid in the plenum is configured to cool the end portion. The plurality of outlet holes is configured to discharge the portion of the cooling fluid from the plenum.
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公开(公告)号：US20200025377A1
公开(公告)日：2020-01-23
申请号：US16398439
申请日：2019-04-30
Applicant: General Electric Company
Inventor： Mark Eugene Noe , Shawn Michael Pearson , Joshua Tyler Mook , Brandon ALlanson Reynolds , Jonathan David Baldiga
Abstract: Gas turbine engines, as well as outer walls and flow path assemblies of gas turbine engines, are provided. For example, an outer wall of a flow path comprises a combustor portion extending through a combustion section, and a turbine portion extending through at least a first turbine stage of a turbine section. The combustor and turbine portions are integrally formed as a single unitary structure that defines an outer boundary of the flow path. As another example, a flow path assembly comprises a combustor dome positioned a forward end of a combustor; an outer wall extending from the combustor dome through at least a first turbine stage; and an inner wall extending from the combustor dome through at least a combustion section. The combustor dome extends radially from the outer wall to the inner wall and is integrally formed with the outer and inner walls as a single unitary structure.
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Patent Agency Ranking
公开(公告)号：US10378770B2
公开(公告)日：2019-08-13
申请号：US15417437
申请日：2017-01-27
Applicant: General Electric Company
Inventor： Brandon ALlanson Reynolds , Jonathan David Baldiga , Andrew Scott Bilse , Mark Eugene Noe , Brett Joseph Geiser
Abstract: Flow path assemblies and gas turbine engines are provided. In one exemplary embodiment, a flow path assembly comprises an inner wall and a unitary outer wall including a combustor portion extending through a combustion section and a turbine portion extending through at least a first turbine stage of a turbine section. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The inner wall and the unitary outer wall define a combustor of the combustion section. In another exemplary embodiment, a flow path assembly comprises a unitary inner wall defining an inner boundary of a flow path and extending from a forward end of a combustor through a nozzle portion of a first turbine stage, and a unitary outer wall defining an outer boundary of the flow path and extending from the forward end of the combustor through at least the first turbine stage.
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公开(公告)号：US20190145275A1
公开(公告)日：2019-05-16
申请号：US15810448
申请日：2017-11-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Victor Hugo Silva Correia , Jonathan David Baldiga
CPC classification number: F01D25/12 , F01D11/005 , F05D2240/11 , F05D2240/24 , F05D2260/201 , F16J15/022
Abstract: A compliant seal component, a turbomachine including such compliant seal component, and an associated method for cooling the compliant seal component disposed in the turbomachine are disclosed. The compliant seal component includes a convoluted portion and a plurality of end portions spaced apart from each other. The plurality of end portions is joined to the convoluted portion. An end portion of the plurality of end portions includes a first section and a second section, the second section defining a plenum. The end portion further includes a plurality of inlet holes and a plurality of outlet holes. The plurality of inlet holes is configured to direct a portion of a cooling fluid to the plenum. The portion of the cooling fluid in the plenum is configured to cool the end portion. The plurality of outlet holes is configured to discharge the portion of the cooling fluid from the plenum.
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公开(公告)号：US20180238183A1
公开(公告)日：2018-08-23
申请号：US15440320
申请日：2017-02-23
Applicant: General Electric Company
Inventor： Brandon ALlanson Reynolds , Jonathan David Baldiga
CPC classification number: F01D9/042 , F01D9/023 , F01D25/005 , F01D25/24 , F05D2220/32 , F05D2230/53 , F05D2240/35 , F05D2260/30 , F05D2300/6033 , F23R3/002 , F23R3/007 , F23R3/10 , F23R3/60 , F23R2900/00017 , F23R2900/00018 , Y02T50/672
Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall and an outer wall defining an opening therethrough, as well as a nozzle airfoil having an inner end radially opposite an outer end that is positioned within the opening defined in the outer wall such that the outer end projects radially outwardly from the outer wall. The flow path assembly also comprises a pin and a first support member. The pin extends from the first support member to the outer end of the nozzle airfoil to support the nozzle airfoil. In some embodiments, the outer end of the nozzle airfoil defines a flange configured to receive the pin and a radial stop configured to press against a radially outward external support, and the pin is configured to transfer a load on the nozzle airfoil to an external structure.
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37.发明申请公开(公告)号：US20180238182A1
公开(公告)日：2018-08-23
申请号：US15440235
申请日：2017-02-23
Applicant: General Electric Company
CPC classification number: F01D9/042 , F01D9/023 , F01D11/02 , F02C3/14 , F05D2230/53 , F05D2230/60 , F05D2240/35 , F05D2300/6033 , Y02T50/672 , Y02T50/673
Abstract: Flow path assemblies and methods for assembling a flow path assembly of a gas turbine engine are provided. For example, a flow path assembly comprises a unitary outer wall including combustor and turbine portions that are integrally formed as a single unitary structure; a single piece, generally annular inner band; and a plurality of nozzle airfoils extending from the unitary outer wall to the inner band. Each nozzle airfoil interfaces with the inner band to position the inner band within the assembly. An exemplary assembly method comprises inserting an inner band into a flow path having a unitary outer wall as its outer boundary; inserting a plurality of nozzle airfoils into the flow path; and securing the nozzle airfoils with respect to the unitary outer wall. The inner band interfaces with an inner end of each nozzle airfoil to radially locate the inner band within the flow path.
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公开(公告)号：US20180216824A1
公开(公告)日：2018-08-02
申请号：US15417602
申请日：2017-01-27
Applicant: General Electric Company
Inventor： Brandon ALlanson Reynolds , Jonathan David Baldiga , Andrew Scott Bilse , Michael Todd Radwanski , Ernesto Andres Vallejo Ruiz , Aaron Michael Dziech , Mark Eugene Noe
CPC classification number: F23R3/002 , F01D5/06 , F01D5/225 , F01D9/023 , F01D9/04 , F02C3/14 , F05D2220/32 , F05D2230/53 , F05D2240/35 , F05D2300/6033 , F23R3/10 , F23R2900/00018 , Y02T50/672
Abstract: Flow path assemblies and gas turbine engines are provided. A flow path assembly may comprise a combustor dome positioned at a forward end of a combustor of a combustion section of a gas turbine engine, and a unitary outer wall including a combustor portion extending through the combustion section and a turbine portion extending through at least a first turbine stage of a turbine section of the gas turbine engine. The combustor portion and the turbine portion are integrally formed as a single unitary structure. The flow path assembly also comprises an inner wall extending from the forward end of the combustor through at least the combustion section. The combustor dome extends radially from the unitary outer wall to the inner wall and is configured to move axially with respect to the inner wall and the unitary outer wall. Other flow path assemblies and gas turbine engine configurations are provided.
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