Honeywell International Inc.

Jong Liu

Malak Fouad Malak

Luis A Tapia

Balamurugan Srinivasan

Daniel Cregg Crites

Rajiv Rana

Dhinagaran Ramachandran

Gopal Samy Muthiah

Jyothishkumar Venkataramanan

Vighneswara Rao Kollati

David Chou

Ramakumar Venkata Naga Bommisetty

Dhanvantri Joshi

Sridhar Murari

Luis Tapia

Sujatha Guntu

The present disclosure provides various embodiments of cooling circuits, turbine blades with cooling circuits, and methods of forming such turbine blades, having raised rib turbulator structures, which may be used in gas turbine engines. In one exemplary embodiment, a cooling circuit for directing a flow of fluid is disclosed, the cooling circuit includes a cooling circuit wall and a plurality of raised turbulator ribs, each turbulator rib of the plurality of raised turbulator ribs being spaced apart from the cooling circuit wall to allow the fluid to flow between the cooling circuit wall and the plurality of turbulator ribs.

Turbine blades and methods of forming turbine blades having lifted rib turbulator structures

An engine component includes a body; and a plurality of cooling holes formed in the body, at least one of the cooling holes having a multi-lobed shape with at least a first lobe, a second lobe, and a third lobe.

Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations

Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.

Turbine blade airfoils including film cooling systems, and methods for forming an improved film cooled airfoil of a turbine blade

Turbine blade airfoils, showerhead film cooling systems thereof, and methods for cooling the turbine blade airfoils using the same are provided. The airfoil has a leading edge and a trailing edge, a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges, and an internal cavity for supplying cooling air. A showerhead of film cooling holes is connected to the internal cavity. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto an external wall surface at the leading edge of the airfoil. A plurality of surface connectors is formed in the external wall surface. Each surface connector of the plurality of surface connectors interconnects the outlets of at least one selected pair of the film cooling holes.

Turbine blade airfoils including showerhead film cooling systems, and methods for forming an improved showerhead film cooled airfoil of a turbine blade

An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface to the exterior surface; and a concave trench extending from the cooling hole at the exterior surface of the body in a downstream direction.

Gas turbine engine components with cooling hole trenches

An engine component includes a body; and a plurality of cooling holes formed in the body. At least one of the cooling holes has cross-sectional shape with a first concave portion and a first convex portion.

Gas turbine engine components with improved film cooling

A turbine engine component includes a wall, a main opening, and two clusters of two or more auxiliary openings. The wall includes cool and hot air sides. The main opening extends between the cool air side and the hot air side and has an inlet and an outlet. The inlet is formed on the cool air side, and the outlet is formed on the hot air side. The first cluster of two or more auxiliary openings extends from the main opening to the hot air side. The second cluster of two or more auxiliary openings extends from the main opening to the hot air side. The main opening may be cylindrical or conical with a converging passage extending from the cool air side to the hot air side. The converging main opening may enhance flow through the auxiliary openings especially at high blowing ratios.

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Scottsdale, AZ, United States of America

Jong Liu