Honeywell International Inc.

Michael J Durden

John R Barrett

Brian D Koch

Robert A Kime

Howard M Becker

Larry W Aycock

Robert Sandoval

A secondary flow, turbine cooling air system for the uniform cooling of high pressure turbine module components such as the turbine shroud, turbine blade tips, turbine nozzle, transion liner, and turbine bearing support housing in a recuperated gas turbine engine is provided. The secondary flow turbine cooling system provides uniform cooling air having a similar pressure and temperature in a recuperated gas turbine engine as the compressor discharge air of a non-recuperated gas turbine engine. A method for uniform cooling of high pressure turbine module components using the secondary flow turbine cooling air system is also provided.

Secondary flow, high pressure turbine module cooling air system for recuperated gas turbine engines

A recuperator and turbine support adapter for securing a recuperator to a combustor case is provided. The recuperator and turbine support adapter comprises an outer strutted body, an inner strutted body and a thermal spring. The thermal spring allows for thermal expansion of the recuperator and turbine support adapter while alleviating any stress or fatigue damage to the adapter. Each of the outer strutted bodies further comprises an outer ring and an inner ring connected by a plurality of struts. The recuperator and turbine support adapter also provides a means of directing the flow of cold compressed air to the recuperator and the return of the recuperator heated air to the combustor/turbine module.

Recuperator and turbine support adapter for recuperated gas turbine engines

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Chandler, AZ, United States of America

Michael J Durden