Honeywell International Inc.

Adrian R Allan

Mark C Morris

Bjoern Schenk

Vincent Chung

Donald L Palmer

Raymond Gage

James Lolnell Hadder

Arun Kumar

William J Howe

George E Zurmehly

Louis D Cruse

Mario Alejandro Hidalgo

Peter L Morgan

An improved type of cooled component is disclosed. The cooled components, such as turbine airfoils and combustors, have a base metal structural member, including a metal sheet or blank, with a featured surface. The features, such as fins, pins, and other protrusions, as well as divots, indentions, slots, channels, and holes, are formed by lithographic processes. The protrusions can be formed from a different material than the metal sheet or blank, preferably one with superior heat-conductive or oxidation properties. A related method of manufacturing is also disclosed.

Cooled component with a featured surface and related manufacturing method

The mounting of low expansion full ring shrouds in a turbine engine requires radial compliance to limit the stresses experienced by the shroud due to thermal growth differences between the shroud and its support. A method provides radial compliance with no looseness in a mounting system. The mounting system also allows for axial motion of the shroud, should such motion be needed or desired. The lack of looseness in the mounting system results in an ability to achieve smaller tip clearances and thus better engine performance.

Compliant mounting system for turbine shrouds

Cooling air to the blades and disks of a gas turbine may be modulated to provide a variable turbine cooling flow. A bellows may be extended by providing a high pressure compressor discharge flow to an interior of the bellows. The bellows may be compressed when the interior of the bellows communicates with ambient pressure air. The extension/compression of the bellows moves an arm over orifices in a cooling air flow path. The pressure inside of the bellows is metered to move the arm over at least one orifice, thereby restricting cooling air flow when the engine is running at low power. The pressure inside of the bellows is metered to move the arm to uncover all of the slots to provide maximum cooling flow when the engine is running at high power. The resulting variable cooling flow system results in less need for cooling air at low powers, thus reducing engine fuel consumption.

Variable turbine cooling flow system

A variable geometry vane for use in a turbine engine. The vane can be radially mounted in a shroud ring while outside the turbine engine. The shroud and vane assembly can then be mounted to an engine hub without disassembly of the shroud, eliminating the need for a split ring shroud. Once located surrounding the hub, vanes are slid radially inward until a radially inward vane button engages a hole within the hub. Vanes are locked in place using clips slid into slots within the shroud. The clips are retained in place using an adjacent engine part bolted to the face of the shroud. Once in place within the engine, vanes are attached to a control arm for airflow adjustment.

Vane radial mounting apparatus

A ceramic finger seal for use between a housing and a combustor liner to inhibit air passage therebetween and for use in fluid sealing between a rotating shaft and a housing circumscribing the rotating shaft. The ceramic finger seal has at least two annular diaphragm members constructed of two or more diaphragm segments bonded end to end by ceramic cement or other high temperature joining compounds. The diaphragm members may be partitioned into a generally continuous inner diameter portion and a segmented outer diameter portion or the reverse thereof. The segmented portion includes finger elements spaced uniformly apart forming gaps therebetween and extend radially outward or inward terminating in a foot portion. The rolled edge on the finger is formed by laser cutting to prevent gouging of the combustor liner surface.

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Chandler, AZ, United States of America

Adrian R Allan