Siemens Energy, Inc.

Caleb Myers

Ching-Pang Lee

Gm Salam Azad

Steven Koester

Erik Johnson

Daniel Joo

Alan A Thrift

Johan K Westin

An airfoil () is disclosed for a gas turbine engine in which the airfoil () includes an internal cooling system () with one or more converging-diverging exit slots () configured to increase the effectiveness of the cooling system () at the trailing edge () of the airfoil () by increasing the contact of cooling fluids with internal surfaces () of the pressure and suction sides () of the airfoil (). In at least one embodiment, the trailing edge cooling channel () may include one or more converging-diverging exit slots () to further pressurize the trailing edge cooling channel () and may be formed by a first and second ribs () extending between an outer walls () forming the pressure and suction sides (). The converging-diverging exit slot () may be formed from a first converging section () having an inlet () with a larger cross-sectional area than an outlet () and is formed from a second diverging section () having an inlet () with a smaller cross-sectional area than an outlet ().

Internal cooling system with converging-diverging exit slots in trailing edge cooling channel for an airfoil in a turbine engine

A cooling system () positioned within a turbine airfoil () and having film cooling channels () positioned within inner and outer endwalls () of the turbine airfoil (), with cooling fluids supplied to the cooling channels () other than from an aft cooling chamber () to prevent blockages from developing within the film cooling channels () from debris that typically collects with the aft cooling chamber () during steady state operation of the turbine engine is disclosed. The cooling system () may include one or more midchord cooling channels () extending from a midchord cooling chamber () and including an outlet () positioned closer to a downstream edge () of the inner endwall () than an upstream wall () forming the aft cooling chamber (). The midchord cooling channel, thus, may cool aspects of the inner endwall () radially outward of the aft cooling chamber () without receiving cooling fluid from aft cooling chamber (), thereby eliminating the possibility of blockages from debris in the aft cooling chamber ().

Cooled turbine vane platform comprising forward, midchord and aft cooling chambers in the platform

A rim seal arrangement for a gas turbine engine includes a first seal face on a rotor component, and a second seal face on a stationary annular rim centered about a rotation axis of the rotor component. The second seal face is spaced from the first seal face along an axial direction to define a seal gap. The seal gap is located between a radially outer hot gas path and a radially inner rotor cavity. The first seal face has a plurality of circumferentially spaced depressions, each having a depth in an axial direction and extending along a radial extent of the first seal face. The depressions influence flow in the seal gap such that during rotation of the rotor component, fluid in the seal gap is pumped in a radially outward direction to prevent ingestion of a gas path fluid from the hot gas path into the rotor cavity.

Rim seal arrangement having pumping feature

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Cincinnati, OH, United States of America

Caleb Myers