Abstract: A combustor liner has an annular shell which includes a first portion and a second portion. The first portion is provided with slot film cooling and the second portion is provided with multi-hole film cooling. The multi-hole cooling portion can be located either forward or aft of the slot film cooling portion, depending on the nature of the combustor that the liner is to be used in. In one possible embodiment, the liner includes a first annular panel, a second annular panel section joined at its forward end to the aft end of the first panel section, and a third annular panel section being joined at its forward end to the aft end of the second panel section. At least one of the panel sections has multi-hole film cooling and at least one other of the panel sections has slot film cooling.

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 liner for use in a gas turbine engine includes a first annular panel section having a forward end, an aft end and a first cooling nugget located at the forward end thereof, and a second annular panel section having a forward end, an aft end and a second cooling nugget located at the forward end thereof. The second panel section is joined at its forward end to the aft end of the first panel section. A first row of cooling holes is located in the first cooling nugget, and a second row of cooling holes is located in the second cooling nugget. A group of dilution holes is located in the first panel section. The dilution holes are located at the aft end of the first panel section, immediately upstream of the second cooling nugget. Furthermore, each one of the dilution holes defines an aftmost edge, and all of the aftmost edges are axially aligned, even if the dilution holes have different hole diameters.

Abstract: A combustor liner has an annular shell which includes a first portion and a second portion. The first portion is provided with slot film cooling and the second portion is provided with multi-hole film cooling. The multi-hole cooling portion can be located either forward or aft of the slot film cooling portion, depending on the nature of the combustor that the liner is to be used in. In one possible embodiment, the liner includes a first annular panel, a second annular panel section joined at its forward end to the aft end of the first panel section, and a third annular panel section being joined at its forward end to the aft end of the second panel section. At least one of the panel sections has multi-hole film cooling and at least one other of the panel sections has slot film cooling.

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 liner for use in a gas turbine engine includes a first annular panel section having a forward end, an aft end and a first cooling nugget located at the forward end thereof, and a second annular panel section having a forward end, an aft end and a second cooling nugget located at the forward end thereof. The second panel section is joined at its forward end to the aft end of the first panel section. A first row of cooling holes is located in the first cooling nugget, and a second row of cooling holes is located in the second cooling nugget. A group of dilution holes is located in the first panel section. The dilution holes are located at the aft end of the first panel section, immediately upstream of the second cooling nugget. Furthermore, each one of the dilution holes defines an aftmost edge, and all of the aftmost edges are axially aligned, even if the dilution holes have different hole diameters.