Combustor hole arrangement for gas turbine engine
A combustor liner for a gas turbine is provided. The combustor liner comprises a wall and a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole.
1. A combustor liner for a gas turbine comprising:
a wall; and
a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole, each circular first airflow injection hole having a first area equal to a second area of each non-circular second airflow injection hole;
wherein the plurality of airflow injection holes is an alternating arrangement of first airflow injection holes and second airflow injection holes, such that a first airflow injection hole is adjacent to a second airflow injection hole in each circumferential direction along the circumferentially-extending row and a second airflow injection hole is adjacent to a first airflow injection hole in each circumferential direction along the circumferentially-extending row.
2. The combustor liner of claim 1 , wherein the second airflow injection hole has an axial length greater than a circumferential width of the second airflow injection hole.
3. The combustor liner of claim 2 , wherein an aspect ratio of the axial length to the circumferential width is between two and six.
4. The combustor liner of claim 1 , wherein the second airflow injection hole is one of elliptically-shaped, diamond-shaped or oval-shaped.
5. The combustor liner of claim 1 wherein a ratio of first airflow injection hole diameter and second airflow injection hole circumferential width is between 3 and 12.
6. A combustor for a gas turbine engine comprising:
a combustor case; and
a combustor liner disposed in the combustor case, radially offset from the combustor case to define an airflow pathway between the combustor case and the combustor liner, the combustor liner including:
a wall; and
a plurality of airflow injection holes in the wall arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole, the plurality of airflow injection holes configured to reduce a temperature of combustion gases exiting the combustor, each circular first airflow injection hole having a first area equal to a second area of each non-circular second airflow injection hole;
wherein the plurality of airflow injection holes is an alternating arrangement of first airflow injection holes and second airflow injection holes, such that a first airflow injection hole is adjacent to a second airflow injection hole in each circumferential direction along the circumferentially-extending row and a second airflow injection hole is adjacent to a first airflow injection hole in each circumferential direction along the circumferentially-extending row.
7. The combustor of claim 6 , further comprising one or more fuel injectors extending through the combustor liner and into the combustion zone, providing a flow of fuel for combustion in the combustion zone.
8. The combustor of claim 6 , wherein the second airflow injection hole has an aspect ratio of axial length to circumferential width of between two and six.
9. The combustor of claim 6 , wherein the second airflow injection hole is one of elliptically-shaped, diamond-shaped or oval-shaped.
10. The combustor of claim 6 wherein a ratio of first airflow injection hole diameter and second airflow injection hole circumferential width is between 3 and 12.
11. A gas turbine engine comprising:
a turbine; and
a combustor operably connected to the turbine, the combustor driving the turbine via combustion products of the combustor, the combustor including:
a combustor case; and
a combustor liner disposed in the combustor case, radially offset from the combustor case to define an airflow pathway between the combustor case and the combustor liner, the combustor liner including:
a wall; and
the wall including a plurality of airflow injection holes arranged in a circumferentially-extending row, the plurality of airflow injection holes including a plurality of circular first airflow injection holes and at least one non-circular second airflow injection hole, the plurality of airflow injection holes configured to reduce a temperature of combustion gases exiting the combustor, each circular first airflow injection hole having a first area equal to a second area of each non-circular second airflow injection hole;
wherein the plurality of airflow injection holes is an alternating arrangement of first airflow injection holes and second airflow injection holes, such that a first airflow injection hole is adjacent to a second airflow injection hole in each circumferential direction along the circumferentially-extending row and a second airflow injection hole is adjacent to a first airflow injection hole in each circumferential direction along the circumferentially-extending row.
12. The gas turbine engine of claim 11 , further comprising one or more fuel injectors extending through the combustor liner and into the combustion zone, providing a flow of fuel for combustion in the combustion zone.
13. The gas turbine engine of claim 11 , wherein the second airflow injection hole has an aspect ratio of axial length to circumferential width of between two and six.