United Technologies Corporation

Raytheon Technologies Corporation

David R Wiley

Jonathan Jeffery Eastwood

Monica Pacheco-Tougas

Craig F Smith

Jeffrey D Melman

Claude I Barnett

Hannes A Alholm

Dennis John Duhamel

David A Burns

Randy J Danburg

Reed A Kakuska

A method for manufacturing an apparatus with a flow passage includes providing a preform apparatus with a preform flow passage. Flow area of the preform flow passage is determined to provide determined flow area data. The determined flow area data is compared to reference flow area data to provide flow area comparison data. The preform apparatus is chemical milled based on the flow area comparison data.

Method for chemical milling an apparatus with a flow passage

A combustor liner cap assembly is provided for use in a multiple fuel nozzle combustor of a gas turbine. The combustor liner cap assembly includes a tube plate having a plurality of fuel nozzle openings and a plurality of open ended premix tubes extending aft from the tube plate. Each premix tube has a forward end having a forward edge, the forward end being received in a corresponding one of the fuel nozzle openings. Each premix tube is secured to the tube plate aft of the forward edge of the forward end of the premix tube, for example, metallurgically bonded, such as by welding or brazing, to the tube plate or threaded into the tube plate.

Gas turbine combustor liner cap assembly

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Jupiter, FL, United States of America

David R Wiley