-
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.
-
公开(公告)号：US20150226069A1
公开(公告)日：2015-08-13
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.
Abstract translation: 涡轮机翼片包括：在前缘和后缘处连接在一起并且在根部和尖端之间延伸的凹形压力侧壁和凸形抽吸侧壁; 在所述压力侧壁和所述吸力侧壁之间延伸的内部肋; 以及形成在所述肋中的交叉孔，所述交叉孔具有非圆形横截面形状，所述横截面形状具有限定所述横截面形状的最大尺寸的长轴; 其中所述交叉孔的长轴位于与所述肋的平面中，并且不平行于限定位于所述压力和抽吸侧壁之间的中心位置的虚拟曲线横向中心线。 交叉孔的方向最小化由交叉孔的存在引起的应力集中。
-
公开(公告)号：US20150167480A1
公开(公告)日：2015-06-18
申请号：US14407867
申请日：2013-06-14
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Steven Robert Brassfield , Mark Edward Stegemiller , Jonathan Filipa , Daniel Lee Durstock
CPC classification number: F01D5/30 , F01D5/22 , F01D5/3015 , F01D11/00 , F01D11/006 , F05D2240/57 , Y10T29/49321
Abstract: A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces. A sealing member is configured to be inserted into each slot of a first rotor blade of the plurality of rotor blades such that at least a portion of each sealing member extends beyond one of the opposing side faces. A second rotor blade of the plurality of rotor blades is coupled adjacent the first rotor blade such that at least a portion of one sealing member is inserted into a corresponding second slot on the second rotor blade.
Abstract translation: 用于具有旋转轴线的燃气涡轮发动机中的转子组件包括多个转子叶片。 每个转子叶片包括在相对侧面之间延伸的平台，从平台径向向内延伸的杆，以及至少部分限定在每个相对侧面中的狭槽。 密封构件被配置为插入到多个转子叶片中的第一转子叶片的每个槽中，使得每个密封构件的至少一部分延伸超过相对侧面之一。 多个转子叶片中的第二转子叶片与第一转子叶片相邻地连接，使得一个密封构件的至少一部分插入到第二转子叶片上相应的第二槽中。
-
公开(公告)号：US20180216822A1
公开(公告)日：2018-08-02
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
CPC classification number: F23R3/002 , F01D5/06 , F01D5/225 , F01D9/023 , F01D9/04 , F01D25/246 , F02C3/14 , F02C7/22 , F05D2220/32 , F05D2230/53 , F05D2240/35 , F05D2300/6033 , F23R2900/00018 , Y02T50/672
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.
-
公开(公告)号：US20170234145A1
公开(公告)日：2017-08-17
申请号：US15043900
申请日：2016-02-15
Applicant: General Electric Company
CPC classification number: F01D5/188 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/128 , F05D2240/30 , F05D2260/20 , F05D2260/202 , F05D2260/203 , F05D2260/2212 , Y02T50/672 , Y02T50/676
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.
-
Patent Agency Ranking
6.发明申请PROCESS FOR SELECTIVELY PRODUCING THERMAL BARRIER COATINGS ON TURBINE HARDWARE 审中-公开在涡轮五金机上选择生产热障涂层的工艺公开(公告)号：US20140341750A1
公开(公告)日：2014-11-20
申请号：US13724324
申请日：2012-12-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Thomas Edward Mantkowski , John Maynard Crow , Shawn Michael Pearson , Stephen Mark Molter
Abstract: A process of depositing a ceramic coating on an airfoil component and the component formed thereby is provided. The process includes depositing a bond coat on an airfoil component including on a trailing edge region thereof that defines a trailing edge of the airfoil component, within holes located within the trailing edge region and spaced apart from the trailing edge, and on lands located within the trailing edge region and between the holes. A ceramic coating is then deposited on the bond coat including on the trailing edge region of the airfoil component, within the holes located within the trailing edge region, and on the lands between the holes. The ceramic coating within the holes is selectively removed without completely removing the ceramic coating on the trailing edge region and the lands between the holes.
Abstract translation: 提供了一种在翼型部件上沉积陶瓷涂层的方法和由此形成的部件。 该方法包括在翼型部件上沉积粘结涂层，所述翼型部件包括在其后缘区域上限定翼型部件的后缘，位于后缘区域内并位于后缘区域内的孔内， 后缘区域和孔之间。 然后将陶瓷涂层沉积在粘合涂层上，包括在翼型部件的后缘区域，位于后缘区域内的孔内，以及孔之间的焊盘上。 选择性地去除孔内的陶瓷涂层，而不会完全去除后缘区域上的陶瓷涂层和孔之间的焊盘。
-
公开(公告)号：US10738621B2
公开(公告)日：2020-08-11
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
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.
-
公开(公告)号：US10100650B2
公开(公告)日：2018-10-16
申请号：US13724324
申请日：2012-12-21
Applicant: General Electric Company
Inventor： Thomas Edward Mantkowski , John Maynard Crow , Shawn Michael Pearson , Stephen Mark Molter
Abstract: A process of depositing a ceramic coating on an airfoil component and the component formed thereby is provided. The process includes depositing a bond coat on an airfoil component including on a trailing edge region thereof that defines a trailing edge of the airfoil component, within holes located within the trailing edge region and spaced apart from the trailing edge, and on lands located within the trailing edge region and between the holes. A ceramic coating is then deposited on the bond coat including on the trailing edge region of the airfoil component, within the holes located within the trailing edge region, and on the lands between the holes. The ceramic coating within the holes is selectively removed without completely removing the ceramic coating on the trailing edge region and the lands between the holes.
-
公开(公告)号：US09840920B2
公开(公告)日：2017-12-12
申请号：US14407867
申请日：2013-06-14
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Steven Robert Brassfield , Mark Edward Stegemiller , Jonathan Filipa , Daniel Lee Durstock
CPC classification number: F01D5/30 , F01D5/22 , F01D5/3015 , F01D11/00 , F01D11/006 , F05D2240/57 , Y10T29/49321
Abstract: A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces. A sealing member is configured to be inserted into each slot of a first rotor blade of the plurality of rotor blades such that at least a portion of each sealing member extends beyond one of the opposing side faces. A second rotor blade of the plurality of rotor blades is coupled adjacent the first rotor blade such that at least a portion of one sealing member is inserted into a corresponding second slot on the second rotor blade.
-
公开(公告)号：US20150152735A1
公开(公告)日：2015-06-04
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
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 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.
Abstract translation: 涡轮机翼型装置包括：在前缘和后缘处连接在一起的包括凹压侧壁和凸吸吸侧壁的翼型件; 所述端壁在所述翼型件的一个翼展端处从所述翼型件横向向外突出，所述端壁具有面向所述翼型件的外表面和相对的内表面; 限定在内表面和外表面之间的端壁内的气室，其中气室在平面图中分叉，至少两个分支，每个分支具有设置在其上游端的喉部; 以及至少一个通过外表面并与气室连通的薄膜冷却孔。
-
-
-
-
-
-
-
-
-
Search Results
23
records
(took 0.015 seconds)
