General Electric Company

Eric Richard Bonini

Ronald Scott Bunker

Christopher Edward LaMaster

Jeremy Peter Latimer

John Duong

Michael James Dutka

Marc Edward Blohm

Matthew John McKeever

Thomas Robbins Tipton

Paul Griffin Delvernois

Ya-Tien Chiu

Kelvin Rono Aaron

Govindarajan Rengarajan

Venkata Siva Prasad Chaluvadi

Alexander David Shrum

San-Dar Gau

Jamie Dean Lumpkin

Franco Monteleone

Gregory Thomas Foster

Gary Charles Liotta

Bruce Clark Busbey

John Herbert Dimmick

Patrick Shawn Reilly

John Robert Sech

Kiran Sreeram

John Herbert Iii Dimmick

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.

Components with cooling channels and methods of manufacture

A rotor wheel for an engine includes a plurality of impeller vanes and a plurality of fluid passages defined by adjacent impeller vanes. The fluid passages are radially disposed across at least a portion of the rotor wheel. One or more impeller inserts may be disposed within one or more of the plurality of fluid passages, respectively. The impeller inserts define an impeller passage with a passage shape that controls a flow of fluid through the one or more of the plurality of fluid passages.

Rotor wheel and impeller inserts

The present application and the resultant patent provide an axial compressor for a gas turbine engine. The compressor may include a rotor disk positioned along an axis of the compressor. The rotor disk may include a slot defined about a radially outer surface of the rotor disk, and the slot may include a slot planar surface facing away from the rotor disk. The compressor also may include a compressor blade coupled to the rotor disk via the slot. The compressor blade may include a platform positioned over the radially outer surface of the rotor disk, and the platform may include a platform sealing edge facing toward the rotor disk. The compressor further may include a gap defined between the platform sealing edge and the slot planar surface, wherein the gap is configured to control a flow of leakage air from a high-pressure side of the compressor blade to a low-pressure side of the compressor blade. The present application and the resultant patent further provide a related method of controlling stage-to-stage leakage in an axial compressor of a gas turbine engine.

Axial compressor and method for controlling stage-to-stage leakage therein

A method of machining a component is provided. The component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one interior space. A core is disposed within each interior space. The method includes forming at least one hole in the substrate while the core is disposed within the respective interior space. Each hole extends through the substrate to provide fluid communication with the respective interior space. The method further includes removing the core from the respective interior space. The core may be a casting core or a subsequently formed core.

Backstrike protection during machining of cooling features

A method of forming cooling channels in a component is provided. The component has a substrate having outer and inner surfaces. The inner surface defines at least one interior space, and a core is disposed within each interior space. The method includes forming at least one access hole in the substrate, while the core is disposed within the respective interior space, removing the core from the respective interior space, and forming at least one groove in the outer substrate surface (before or after the core is removed). Each access hole connects the groove in fluid communication with the respective interior space. The method further includes disposing a coating over at least a portion of the outer substrate surface, where the coating includes at least a structural coating that extends over the groove(s), such that the groove(s) and the structural coating together define one or more channels configured to convey a coolant from the respective interior space(s) for cooling the component.

Methods of forming cooling channels using backstrike protection

An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Airfoil shape for a compressor

An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Article of manufacture

Methods of forming a ceramic component and a high temperature mold for use therewith are provided. The method includes providing a fixture having a receiving surface configured to receive an unfired ceramic component. The method includes applying a continuous high temperature membrane to a surface of the unfired ceramic component. The method includes covering the continuous high temperature membrane and unfired ceramic component with a high temperature loose media. The method includes heating the unfired ceramic component to a firing temperature. The high temperature mold includes the fixture and a support structure forming a compartment surrounding the fixture. The mold allows the high temperature loose media to be contained within the compartment and to cover the continuous high temperature membrane. The continuous high temperature membrane and high temperature loose media are evenly distributed over the uncured ceramic component and operable to provide constant pressure during processing using the mold.

Methods of forming a ceramic component and a high temperature mold component for use therewith

An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

Airfoil shape for a compressor blade

An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

Growing community of inventors

Greer, SC, United States of America

Eric Richard Bonini