United Technologies Corporation

James J Nolan

Stanley J Markowski

Edmund E Striebel

George W Austin, Jr

Robert A Breton

This invention relates to an improvement of the cooling air flow distribution in proximity to the combustion and dilution air holes of a combustor liner fabricated from Finwall.RTM. material for a turbine type power plant.

Combustor liner for gas turbine engine

A low emission combustion chamber in which vitiated products of combustion from a pilot burner are caused to swirl about the combustion chamber axis before fuel droplets are introduced into the vitiated, swirling combustion products for flash vaporization therein to produce a vaporized, swirling, vitiated fuel-air mixture so as to effect ignition lag until swirling combustion air can be mixed with the swirling mixture to molecularly premix the fuel and air and increase its oxygen content to reduce the ignition lag to effect autoignition at an equivalence ratio less than 1 so as to effect high-rate, lean burning in the primary combustion chamber.

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Glastonbury, CT, United States of America

James J Nolan