General Electric Company

Tariq Kay Harris

Steven Clayton Vise

Gilbert Farmer

John Robert Staker

Marwan Al-Roub

George Eric Moertle

Ella Christine Kutter

Bruce Ernest Mills

James Patrick Holmes

Michael Burke Briski

A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.

Method and apparatus for cooling gas turbine engine igniter tubes

Cooling film effectiveness is increased in multi-hole film cooled combustor liners having dilution holes by altering the orientation of the film cooling holes in the vicinity of the dilution holes. The cooling holes include a first group of cooling holes angled in a first circumferential direction and a second group of cooling holes angled in a second circumferential direction, opposite to the first circumferential direction. The cooling holes in the second group of cooling holes are located between adjacent ones of the dilution holes so as to direct cooling air to the regions immediately downstream of the dilution holes. Groups of oppositely directed cooling holes can be used with other hot spot regions on the liner, such as those caused by borescope holes, igniter ports and swirling combustor gases.

Combustor liner having preferentially angled cooling holes

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Cincinnati, OH, United States of America

Tariq Kay Harris