公开(公告)号：US10443403B2

公开(公告)日：2019-10-15

申请号：US15412387

申请日：2017-01-23

Applicant: General Electric Company

Inventor： Weston Nolan Dooley ,  James Michael Hoffman ,  Steven Robert Brassfield

IPC: F01D5/18 ,  B22C9/10 ,  B22C9/24 ,  B22C9/04 ,  B22C7/02 ,  B22D25/06 ,  B22D29/00

Abstract: An apparatus relating to engineering the geometry for a ball-chute support feature in an investment casting core. The investment casting core is for an airfoil region having at least one serpentine feature and at least one inlet feature coupled to the at least one serpentine feature by a ball-chute support feature. The investment casting core is leached out to form cooling passages in the airfoil.

公开(公告)号：US10208605B2

公开(公告)日：2019-02-19

申请号：US14884009

申请日：2015-10-15

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Steven Robert Brassfield ,  Robert Frederick Bergholz ,  Aaron Ezekiel Smith ,  Weston Nolan Dooley

IPC: F01D5/18 ,  F01D25/12 ,  F01D5/14 ,  F01D9/04 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58

Abstract: A turbine engine comprises an airfoil having one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

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

IPC: F01D5/14 ,  F01D5/18 ,  B23P15/04

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.

公开(公告)号：US20170107829A1

公开(公告)日：2017-04-20

申请号：US14884114

申请日：2015-10-15

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Steven Robert Brassfield ,  Robert Frederick Bergholz ,  Aaron Ezekiel Smith ,  Weston Nolan Dooley

IPC: F01D5/18 ,  F01D25/12 ,  F01D5/30 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D5/3007 ,  F01D9/041 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/303 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/676

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

公开(公告)号：US20170107827A1

公开(公告)日：2017-04-20

申请号：US14884088

申请日：2015-10-15

Applicant: General Electric Company

Inventor： Matthew Lee Krumanaker ,  Weston Nolan Dooley ,  Steven Robert Brassfield

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2220/323 ,  F05D2240/303 ,  F05D2250/71 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/221 ,  Y02T50/676

Abstract: An airfoil for a gas turbine engine can receive a flow of cooling fluid through a cooling circuit. The cooling circuit is defined within the airfoil comprising a supply passage and a leading edge cooling passage, the two passages being in fluid communication through a plurality of impingement orifices disposed within a cross-over rib disposed between and at least partially defining the passages. The cross-over rib can further comprise a cross-section to provide thermal stress-relief for the cross-over rib.

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。