Siemens Aktiengesellschaft

Siemens Energy, Inc.

Mikro Systems, Inc.

Glenn E Brown

Ching-Pang Lee

Benjamin E Heneveld

Alexander Ralph Beeck

Jill Klinger

Shantanu P Mhetras

A gas turbine engine component, including: a pressure side () having an interior surface (); a suction side () having an interior surface (); a trailing edge portion (); and a plurality of suction side and pressure side impingement orifices () disposed in the trailing edge portion (). Each suction side impingement orifice is configured to direct an impingement jet () at an acute angle () onto a target area () that encompasses a tip () of a chevron () within a chevron arrangement () formed in the suction side interior surface. Each pressure side impingement orifice is configured to direct an impingement jet at an acute angle onto an elongated target area that encompasses a tip of a chevron within a chevron arrangement formed in the pressure side interior surface.

Trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements

A turbine blade () including an airfoil () having multiple interior wall portions () each separating at least one chamber from another one of multiple chambers (). In one embodiment a first wall portion (-) between first and second chambers () includes first and second pluralities of flow paths (P,S) extending through the first wall portion. The first wall portion includes a first region Rhaving a first thickness, t, measurable as a distance between the chambers. One of the paths extends a first path distance, d, as measured from an associated path opening () in the first chamber (), through the first region and to an exit opening () in the second chamber () which path distance is greater than the first thickness.

Turbine blade incorporating trailing edge cooling design

A turbine blade for a turbine engine having a tip with one or more vortex generators for reducing tip leakage during operation of the turbine engine. The vortex generators may extend radially outward from the radially outer surface of the tip wall. The vortex generator may be positioned between a rib extending radially outward from the radially outer surface of the tip wall and an intersection between the outer surface of the tip wall and an outer surface on the pressure side. The vortex generators may include a base and three sides forming a triangular point with a first side having a larger surface are than second and third sides. One or more film cooling holes may be formed in the tip wall to provide cooling air to the tip. In one embodiment, film cooling holes may be positioned in one or more vortex generators.

Turbine blade tip with vortex generators

A squealer tip formed from a pressure side rib and a suction side rib extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure and suction side ribs may include chamfered leading edges with film cooling holes having exhaust outlets positioned therein. The film cooling holes may be configured to be diffusion cooling holes with one or more tapered sections for reducing the velocity of cooling fluids and increasing the size of the convective surfaces.

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West Palm Beach, FL, United States of America

Glenn E Brown