United Technologies Corporation

Nicholas Mule

Alexander W Williams

James P Bangerter

Frank J Cunha

Timothy S Snyder

Monica Pacheco-Tougas

Nurhak Erbas-Sen

A liner for a combustor of a turbine engine includes a cooling feature which projects from a backside and one or more effusion holes that communicate(s) through the liner. The effusion hole(s) surround an opening through said liner. The cooling feature may include a trip strip or a pyramid pin fin (e.g., a three-side pyramid pin fin, a conical pyramid pin fin). The effusion hole(s) may penetrate said cooling feature. The effusion hole(s) may define an angle less than or equal to ninety (90) degrees with respect to a face of said liner. The effusion hole(s) may be proximate an opening through said liner.

Gas turbine engine combustor liner

A combustor liner which reduces cooling flow to a combustion chamber and augments pressure drop split between impingement holes and effusion holes is disclosed. The combustor liner may further include accelerating channels, trip strips, pedestals, and cone-shaped effusion holes to provide further cooling of the liner. The combustor liner may reduce NOx production and the temperature of the combustion chamber of a gas turbine engine or the like.

Cooling for combustor liners with accelerating channels

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Thousand Oaks, CA, United States of America

Nicholas Mule