Abstract: A liner for a combustor of a gas turbine engine, including a shell having a first end adjacent to an upstream end of the combustor and a second end adjacent to a downstream end of the combustor, wherein at least one discrete region is subject to distress from impingement of hot gases, a plurality of cooling slots formed in the shell through which air flows for providing a cooling film along a hot side of the shell, and a group of cooling holes formed in the shell in the discrete region to augment the cooling film and provide convective bore cooling to the discrete region.

Abstract: 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.

Abstract: 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.

Abstract: 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.