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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：US20150152734A1
公开(公告)日：2015-06-04
申请号：US14396062
申请日：2013-04-23
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Christopher Michael Ceglio , Randall Charles Bauer , Stephen Mark Molter , Mark Edward Stegemiller
IPC: F01D5/18
CPC classification number: F01D5/186 , F01D5/187 , F05D2250/292 , F05D2260/202
Abstract: A turbine airfoil for a gas turbine engine including an outer peripheral wall having an external surface, the outer peripheral wall enclosing an interior space and including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; wherein the outer peripheral wall has a varying wall thickness which incorporates a locally-thickened wall portion; and a film cooling hole having a shaped diffuser exit passing through the outer peripheral wall within the locally-thickened wall portion.
Abstract translation: 一种用于燃气涡轮发动机的涡轮机翼片，其包括具有外表面的外周壁，所述外周壁包围内部空间，并且包括在前缘和后缘处连接在一起的凹形压力侧壁和凸形抽吸侧壁; 其中所述外周壁具有变化的壁厚，其包含局部增厚的壁部分; 以及膜冷却孔，其具有穿过局部加厚的壁部分中的外周壁的成形扩散器出口。
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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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Patent Agency Ranking
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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公开(公告)号：US10100647B2
公开(公告)日：2018-10-16
申请号：US14406018
申请日：2013-06-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Stephen Mark Molter , Mark Edward Stegemiller , Shawn Michael Pearson , Steven Robert Brassfield
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 a trailing edge; an endwall projecting 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 having a throat disposed at its upstream end; and at least one film cooling hole passing through the outer surface and communicating with the plenum.
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公开(公告)号：US09995148B2
公开(公告)日：2018-06-12
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
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.
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公开(公告)号：US09850762B2
公开(公告)日：2017-12-26
申请号：US13800647
申请日：2013-03-13
Applicant: General Electric Company
Inventor： Stephen Mark Molter , Timothy Deryck Stone
CPC classification number: F01D5/187 , F01D5/18 , F01D5/186 , F01D5/188 , F01D5/20 , F05D2240/307 , F05D2250/185 , F05D2260/20 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F05D2260/2212 , F05D2260/607 , Y02T50/676
Abstract: A dust mitigation system for airfoils includes a plurality of contoured tip turns which curve about at least two axes. This inhibits recirculation areas common within airfoils and further inhibits dust build up within the cooling flow path of the airfoil.
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公开(公告)号：US20150159871A1
公开(公告)日：2015-06-11
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
CPC classification number: F23R3/04 , F01D5/186 , F01D9/023 , F01D9/065 , F02K1/822 , F05D2240/11 , F05D2240/81 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/03042 , Y02T50/676
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.
Abstract translation: 提供燃气涡轮发动机壁。 壁包括内表面和相对的外表面，其中限定有至少一个膜冷却孔。 所述至少一个膜冷却孔包括从内表面延伸的倾斜入口孔和从倾斜入口孔的出口端横向分开的一对通道。 一对通道具有基本上恒定的宽度并且由脊分开以形成回旋形横截面形状。
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