-
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.
-
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.
-
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.
-
公开(公告)号：US11572801B2
公开(公告)日：2023-02-07
申请号：US16568821
申请日：2019-09-12
Applicant: General Electric Company
Inventor： Daniel Endicott Osgood , Gregory Terrence Garay , Daniel Lee Durstock , Steven Robert Brassfield , Tingfan Pang
Abstract: The disclosure relates to a component for a turbine engine with a heated airflow and a cooling airflow. The component includes a wall separating the heated airflow from the cooling airflow. The wall can have a heated surface confronting the heated airflow and a cooled surface confronting the cooling airflow. The component can also include a baffle with a set of cooling holes.
-
公开(公告)号：US11352889B2
公开(公告)日：2022-06-07
申请号：US16223308
申请日：2018-12-18
Applicant: GENERAL ELECTRIC COMPANY
Abstract: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.
-
Patent Agency Ranking
公开(公告)号：US20210349439A1
公开(公告)日：2021-11-11
申请号：US16871186
申请日：2020-05-11
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Tingfan Pang , Gregory Terrence Garay , Xi Yang , Daniel Lee Durstock , Steven Robert Brassfield , William Charles Herman
IPC: G05B19/4099 , B29C64/393 , G06F30/10
Abstract: A method of using additive manufacturing to form or print a component based on an original model of a component, where the geometry of the original model is compensated to form a compensated model. The compensated model can be used to form or print the component. The printed component as a final model can then be compared to the original model.
-
公开(公告)号：US11053809B2
公开(公告)日：2021-07-06
申请号：US16513226
申请日：2019-07-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , David Alan Frey , Kirk D. Gallier , Steven Robert Brassfield
Abstract: A component, such as for a turbine engine, can include an airfoil with an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. The component can also include at least one cooling passage within the interior.
-
公开(公告)号：US10968750B2
公开(公告)日：2021-04-06
申请号：US16120758
申请日：2018-09-04
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Zachary Daniel Webster , Gregory Terrence Garay , Xi Yang , Tingfan Pang , Steven Robert Brassfield
IPC: F01D5/18
Abstract: An apparatus and method for cooling a component for a turbine engine which generates a hot gas flow and provides a cooling fluid flow, the component comprising a body having an outer surface, at least a portion of which is exposed to the hot gas flow to define a hot surface, a cooling cavity located within the body and fluidly coupled to the cooling fluid flow and a pin located within the cooling cavity and defining a cooling hole.
-
公开(公告)号：US20210040858A1
公开(公告)日：2021-02-11
申请号：US17082288
申请日：2020-10-28
Applicant: General Electric Company
Inventor： Tingfan Pang , Helen Ogbazion Gabregiorgish , Zachary Daniel Webster , Gregory Terrence Garay , Steven Robert Brassfield , Daniel Endecott Osgood
IPC: F01D5/18
Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. A plurality of outlets and a plurality of scalloped portions can extend along the outer wall.
-
公开(公告)号：US10443398B2
公开(公告)日：2019-10-15
申请号：US14884100
申请日：2015-10-15
Applicant: General Electric Company
Abstract: An airfoil for a gas turbine engine comprises a cooling circuit defined within the airfoil providing a flow of cooling fluid within the airfoil. The cooling circuit exhausts the flow of cooling fluid out a slot opening comprising an airfoil element. The slot opening further defines an acceleration zone and a deceleration zone to meter the flow of cooling fluid within the airfoil.
-
-
-
-
-
-
-
-
-
Search Results
66
records
(took 0.029 seconds)
