General Electric Company

Robert Barry Solda

Robert Francis Manning

Mohammad Esmaail Taslim

Stephen K Tung

David Gellman

Lalit K Parekh

A turbine nozzle includes a seal pad mounted to a seal support from an inner band thereof. The seal pad is provided for cooperating with seal teeth in an interstage seal. A bypass aperture extends through the seal support to bypass cooling air around the seal pad for providing relatively cool air aft of the seal teeth for improving cooling of the interstage seal in this region.

Interstage seal cooling

A turbine nozzle includes inner and outer bands having respective air inlets. A plurality of hollow vanes are integrally joined to the bands in flow communication with the inlets. Each vane includes first and second cooling channels extending between the bands which are separated by an inclined septum which converges the two channels away from the corresponding inlets for reducing pressure drop as the cooling air is discharged.

Pressure compensated turbine nozzle

A turbine engine airfoil includes a three-pass serpentine shaped cooling cavity including a leading edge chamber, an oversized intermediate chamber, and a trailing edge chamber in flow communication. The cavity further includes a combination of a plurality of ribs and a plurality of pins, a purge air swirler, a turning vane, and a metering partition which mixes the high pressure air and provides increased air cooling and uniform flow control in the airfoil. The metering partition provides a decrease of the air pressure in the trailing edge chamber allowing for an increase in the number of trailing edge slots.

Growing community of inventors

Peabody, MA, United States of America

Robert Barry Solda