公开(公告)号：US20240159151A1

公开(公告)日：2024-05-16

申请号：US18337841

申请日：2023-06-20

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Douglas Gerard Konitzer ,  Ronald Scott Bunker ,  Robert David Briggs

IPC: F01D5/18 ,  F01D5/14 ,  F01D25/00

CPC classification number: F01D5/186 ,  F01D5/147 ,  F01D5/187 ,  F01D25/002 ,  F05D2220/323 ,  F05D2230/20 ,  F05D2240/30 ,  F05D2250/185 ,  F05D2250/232 ,  F05D2260/202 ,  F05D2260/22141 ,  Y02T50/60

Abstract: A method and apparatus for minimizing engine weight for a turbine engine by utilizing one or more discrete protuberances disposed on an engine component wall. The wall can have a nominal thickness to decrease engine weight while the protuberances can provide increased discrete thicknesses for providing one or more cooling holes. The increased thickness at the protuberances provides for an increased thickness to provide sufficient length to increase cooling hole effectiveness.

公开(公告)号：US11208901B2

公开(公告)日：2021-12-28

申请号：US16423313

申请日：2019-05-28

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Zachary Daniel Webster

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

Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.

公开(公告)号：US10822956B2

公开(公告)日：2020-11-03

申请号：US14858244

申请日：2015-09-18

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Eric Richard Bonini

IPC: F01D5/08 ,  F01D5/18 ,  B23K26/388 ,  B23K26/38 ,  B23K26/384 ,  B23K26/382 ,  F01D9/04 ,  F01D25/28 ,  F01D25/30

Abstract: A component is provided and includes a substrate comprising an outer and an inner surface, where the inner surface defines at least one hollow, interior space. The component defines one or more grooves, where each groove extends at least partially along the outer surface of the substrate and has a base and a top. The base is wider than the top, such that each groove comprises a re-entrant shaped groove. One or more access holes are formed through the base of a respective groove, to connect the groove in fluid communication with the respective hollow interior space. Each access hole has an exit diameter D that exceeds the opening width d of the top of the respective groove. The diameter D is an effective diameter based on the area enclosed. The component further includes at least one coating disposed over at least a portion of the surface of the substrate, wherein the groove(s) and the coating together define one or more re-entrant shaped channels for cooling the component. A method for manufacturing the component is also provided. A method for manufacturing a component is also provided, where the groove and the access hole(s) are machined as a single continuous process, such that the groove and the access hole(s) form a continuous cooling passage.

公开(公告)号：US10815789B2

公开(公告)日：2020-10-27

申请号：US15043512

申请日：2016-02-13

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Jason Randolph Allen

IPC: F01D5/18 ,  F01D9/06 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F23R3/00 ,  F23R3/42

Abstract: An apparatus for an impingement hole for an engine component of a gas turbine engine includes an impingement baffle. The impingement baffle is spaced from an impingement surface and includes a plurality of impingement holes for providing an impingement flow to the impingement surface. The impingement holes can have an angled upstream edge such that an inlet has a greater cross-sectional area than an outlet. The walls of the impingement holes can have a hood to provide a higher shear flow content to minimize dust accumulation on the impingement surface.

公开(公告)号：US10704395B2

公开(公告)日：2020-07-07

申请号：US15150659

申请日：2016-05-10

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/28 ,  F01D5/18

Abstract: An airfoil for a turbine engine having an engine component including an air supply circuit coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the air supply circuit to an outer surface of the engine component through the passages.

公开(公告)号：US10508551B2

公开(公告)日：2019-12-17

申请号：US15238150

申请日：2016-08-16

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/18 ,  F01D5/28 ,  F01D9/04 ,  F01D25/12 ,  F02K3/06 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58 ,  F01D9/06

Abstract: An apparatus and method for cooling an engine component, such as an airfoil, including a wall to separate a hot flow from a cooling fluid flow. The component can include at least one trench disposed in a hot surface. The trench can be fed with the cooling fluid flow to cool the engine component along the hot surface with the cooling fluid flow.

公开(公告)号：US10415396B2

公开(公告)日：2019-09-17

申请号：US15150634

申请日：2016-05-10

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/28

Abstract: An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.

公开(公告)号：US10400675B2

公开(公告)日：2019-09-03

申请号：US14957946

申请日：2015-12-03

Applicant: General Electric Company

Inventor： Mohammed El Hacin Sennoun ,  Ronald Scott Bunker

IPC: F02C7/18 ,  F02C3/04 ,  F02K3/06 ,  F01D5/18 ,  F02K3/115

Abstract: An apparatus and method of cooling a gas turbine engine including a core with a compressor section in which the compressor section includes a closed loop cooling circuit having a pump, at least one heat pipe extending from at least one of the stationary vanes, a heat exchanger located within the bypass air flow, and a coolant conduit passing fluidly coupled to the pump and heat exchanger and passing by the heat pipe. The pump pumps coolant through the coolant conduit to draw heat from the heat pipes into the coolant to form heated coolant, the heated coolant then passes through the heat exchanger, where the heat is rejected from the coolant to the bypass air to cool the coolant to form cooled coolant, which is then returned to the heat pipes.

公开(公告)号：US10352177B2

公开(公告)日：2019-07-16

申请号：US15044697

申请日：2016-02-16

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Robert David Briggs ,  Timothy Deryck Stone

IPC: F01D5/14 ,  F01D5/18

Abstract: An airfoil for a turbine engine having a perimeter wall bounding an interior and defining a pressure side and a suction side, a radially extending rib located within the interior and spaced from the leading edge to define a radially extending leading edge chamber, and at least one impingement opening in the rib defining a flow path aligned with the leading edge.

公开(公告)号：US10350684B2

公开(公告)日：2019-07-16

申请号：US14937325

申请日：2015-11-10

Applicant: General Electric Company

Inventor： Ronald Scott Bunker

IPC: B22F5/04 ,  B22F7/08 ,  F01D5/18 ,  B22F3/105 ,  B33Y80/00 ,  B22F5/00 ,  B33Y40/00 ,  B22F5/10

Abstract: A method of forming a cooling hole structure on a turbine component. The turbine component has a component wall with inner and outer surfaces. A bore passes through the component wall and fluidly connects the inner surface and the outer surface. The method includes the steps of: A) forming a recess communicating with the bore and the outer surface; and B) using an additive manufacturing process to form an exit region in the recess.