United Technologies Corporation

Raytheon Technologies Corporation

Christos Adamopoulos

Frank J Cunha

Timothy S Snyder

James B Hoke

Albert K Cheung

Stanislav Kostka, Jr

Hoyt Y Chang

Christopher B Lyons

Jr Stanislav Kostka

A combustor liner for a gas turbine is provided. The combustor liner comprises a wall and a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole.

Combustor hole arrangement for gas turbine engine

A cooled wall for lining a combustor of a gas turbine engine includes an annular outer wall defining a radial passage extending therethrough, an inner wall spaced radially from the outer wall to define an axial channel in fluid communication with the radial passage, and a connecting wall joining the inner wall to the outer wall. A method of making the cooled wall includes providing a three-dimensional computer model of the cooled wall, depositing a uniform thickness layer of material on a substrate, using a laser or electron beam to melt or sinter the material to form a cross section, repeating the depositing and cross section steps to form the cooled wall, and heat treating the cooled wall.

Combustor wall cooling channel formed by additive manufacturing

An air extraction port at a combustor of a gas turbine engine includes a port inlet at a combustor case of the combustor having an inlet area, a port outlet having a final area, and a fluid passage extending from the port inlet to the port outlet to convey an airflow, the port inlet sized and configured to extract the airflow from the combustor case at the same nominal upstream Mach number with a tolerance of +/&#x2212;0.05.

Apparatus and method for air extraction at a gas turbine engine combustor

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Colchester, CT, United States of America

Christos Adamopoulos