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公开(公告)号：US10563514B2
公开(公告)日：2020-02-18
申请号：US15314618
申请日：2015-05-29
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Robert David Briggs , Shawn Michael Pearson
Abstract: A structure for disrupting the flow of a fluid is provided, the structure comprising: a first lateral wall and a second lateral wall spaced apart from one another a distance across an X-axis; and a turbulator extending between the first lateral wall and the second lateral wall, the turbulator extending away from the floor. The turbulator includes a first front surface extending between the first lateral wall and the second lateral wall, a second front surface extending between the first lateral wall and the second lateral wall, a first rear surface extending between the first lateral wall and the second lateral wall, the first rear surface extending between the first front surface and the floor, and a second rear surface adjoining the first rear surface and extending between the first lateral wall and the second lateral wall, the second rear surface extending between the second front surface and the floor.
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公开(公告)号：US10393381B2
公开(公告)日：2019-08-27
申请号：US15417399
申请日：2017-01-27
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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公开(公告)号：US10386069B2
公开(公告)日：2019-08-20
申请号：US14407076
申请日：2013-06-13
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Robert Frederick Bergholz , Douglas Ray Smith , Frederick Alan Buck , Stephen Mark Molter , Kevin Robert Feldmann
Abstract: A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.
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公开(公告)号：US09869185B2
公开(公告)日：2018-01-16
申请号：US14418626
申请日：2013-07-30
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Steven Robert Brassfield , Stephen Mark Molter , Mark Edward Stegemiller , Nicholas Ertel , Vanessa Camarillo
CPC classification number: F01D5/185 , B23P15/04 , F01D5/147 , F01D5/187 , F05D2250/14 , Y10T29/49316 , Y10T29/49321
Abstract: A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. The orientation of the crossover holes minimizes stress concentration caused by the presence of the crossover holes.
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公开(公告)号：US20170362943A1
公开(公告)日：2017-12-21
申请号：US15182651
申请日：2016-06-15
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Kirk Douglas Gallier , Ronald Scott Bunker
CPC classification number: F01D5/282 , F01D5/187 , F05D2260/941 , F05D2300/5024 , F05D2300/522 , F05D2300/6033 , Y02T50/672 , Y02T50/676
Abstract: A component for a gas turbine engine includes a first region formed substantially of a first CMC material, wherein first region defines a first thermal conductivity. The component further includes a second region formed substantially of a second CMC material, wherein the second region defines a second thermal conductivity. Further, the component defines a thickness and the first region is positioned adjacent to the second region along the thickness, wherein the first thermal conductivity is different than the second thermal conductivity to alert a thermal profile of the component.
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Patent Agency Ranking
公开(公告)号：US20140322008A1
公开(公告)日：2014-10-30
申请号：US13800426
申请日：2013-03-13
Applicant: General Electric Company
Inventor： Stephen Mark Molter , Steven Robert Brassfield , Shawn Michael Pearson , Mark Edward Stegemiller
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D5/186 , F01D5/188 , F05D2250/185 , F05D2260/20 , F05D2260/202 , F05D2260/203 , F05D2260/2212 , Y02T50/67 , Y02T50/676
Abstract: Apparatuses and methods are taught for cooling a turbine blade wherein at least one circuit is isolated along a cool suction side of the blade and the circuit turns aft toward a trailing edge.
Abstract translation: 教导了用于冷却涡轮机叶片的装置和方法，其中至少一个电路沿着叶片的冷抽吸侧被隔离，并且该回路朝后缘向后转。
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公开(公告)号：US11143402B2
公开(公告)日：2021-10-12
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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公开(公告)号：US10577949B2
公开(公告)日：2020-03-03
申请号：US15182651
申请日：2016-06-15
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Kirk Douglas Gallier , Ronald Scott Bunker
IPC: F01D5/28
Abstract: A component for a gas turbine engine includes a first region formed substantially of a first CMC material, wherein first region defines a first thermal conductivity. The component further includes a second region formed substantially of a second CMC material, wherein the second region defines a second thermal conductivity. Further, the component defines a thickness and the first region is positioned adjacent to the second region along the thickness, wherein the first thermal conductivity is different than the second thermal conductivity to alert a thermal profile of the component.
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公开(公告)号：US10443407B2
公开(公告)日：2019-10-15
申请号：US15043900
申请日：2016-02-15
Applicant: General Electric Company
Abstract: An apparatus for a gas turbine engine can include an airfoil having an interior. The interior can be separated into one or more cooling air channels extending in a span-wise direction. An accelerator insert can be placed in one or more cooling air channels to define a reduced cross-sectional area within the cooling air channel to accelerate an airflow passing through the cooling air channel.
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公开(公告)号：US20180363467A1
公开(公告)日：2018-12-20
申请号：US16059212
申请日：2018-08-09
Applicant: General Electric Company
Inventor： Stephen Mark Molter , Mark Edward Stegmiller , Shawn Michael Pearson , Steven Robert Brassfield
CPC classification number: F01D5/186 , B23P15/02 , F01D5/187 , F01D5/20 , F01D5/225 , F01D9/041 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2240/81 , F05D2260/202 , Y10T29/49341
Abstract: A turbine airfoil apparatus includes: an airfoil including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; an endwall that projects laterally outwardly from the airfoil at one spanwise end thereof, the endwall having an outer surface facing the airfoil and an opposing inner surface; a plenum defined within the endwall between the inner and outer surfaces wherein the plenum is forked in plan view, with at least two branches, each branch terminating at a closed end, each branch having a throat disposed at its upstream end, wherein each throat has a relatively constricted flow area for increasing flow velocity; and at least one film cooling hole passing through the outer surface and communicating with the plenum.
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