Honeywell International Inc.

Hiroshi Kawamura

Morris G Anderson

David G Walhood

Albert K Wong

Mark A Kuper

Mark Lai

Luis M Flamand

A gas turbine engine assembly includes a combustor configured to combust an air-fuel mixture to produce combustion gases in a first direction; a transition liner coupled to the combustor and adapted to receive the combustion gases from the combustor and to redirect the combustion gases in a second direction; and a turbine coupled to the transition liner and adapted to receive the combustion gases from the transition liner. The transition liner has a plurality of effusion holes that include a first group that extend at least partially in a tangential direction.

Systems and methods for cooling gas turbine engine transition liners

A combustor liner for shielding an engine from heat generated in a combustion zone includes a sheet with a cool surface for intercepting a cooling air stream and a hot surface enclosing the combustion zone, the combustor liner further including an array of effusion holes extending from the cool surface to the hot surface to allow a portion of the cooling air stream to pass through the effusion holes into the combustion zone, where a portion of the array includes a plurality of upstream-pointed effusion holes oriented such that each upstream-pointed effusion hole has an orientation obtuse to a direction of main flow in the combustion zone so as to control the momentum of cooling air passing into the combustion zone.

Effusion momentum control

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Glendale, AZ, United States of America

Hiroshi Kawamura