Honeywell International Inc.

Brian D Koch

John R Barrett

Robert A Kime

Larry W Aycock

Howard M Becker

Michael J Durden

Gregory O Woodcock

Timothy Ertz

Robert Sandoval

Jeff Guymon

Brian Jardine

Craig White

A combustor for an engine assembly includes a cylindrical wall forming a combustion chamber in which an air and fuel mixture is combusted; and a plurality of effusion cooling holes formed in the cylindrical wall, the plurality of effusion cooling holes oriented such that cooling air flowing therethrough cools the cylindrical wall with effusion cooling, convection cooling, and impingement cooling.

Effusion cooling techniques for combustors in engine assemblies

A retention structure includes a center body including an outer surface, an enclosed end, an open end, and a contact section, the outer surface adapted to define a first portion of a flowpath, and the contact section extending radially outwardly from a centerline and located on the enclosed end and configured to reduce a radial and a torsional component of a first load that exceeds a first threshold applied to the contact section, when the turbine rotates and applies the first load to the contact section and an energy absorber coupled to the center body, disposed adjacent to the contact section, and having an outer surface adapted to define a second portion of the flowpath, the energy absorber further adapted to collapse, when the turbine rotates and contacts the energy absorber and applies a second load that exceeds a second threshold to the energy absorber.

Retention structures and exit guide vane assemblies

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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Gilbert, AZ, United States of America

Brian D Koch