Combustor liner for a gas turbine engine and an associated method thereof

A gas turbine engine comprising:

• a compressor;
• and
• a combustor operatively coupled to the compressor, wherein the combustor comprises a casing and a combustor liner disposed within the casing to define a passageway therebetween the casing and the combustor liner, wherein the combustor liner comprises:
• a panel configured to define an annular combustion zone;
• at least one first through-hole disposed on a section of the panel in a first row extending along a circumferential direction;
• and
• a plurality of second through-holes disposed on the section of the panel, spaced apart from each other along an axial direction and the circumferential direction, and arranged adjacent to the at least one first through-hole,
• wherein the plurality of second through-holes comprises a first set of through-holes and a second set of through-holes,
• wherein the first set of through-holes is arranged in a second row and the second set of through-holes is arranged in a third row different from the second row,
• wherein the second and third rows extend along the circumferential direction, and
• wherein the at least one first through-hole and the plurality of second through-holes collectively cover a circumferential plane of the section of the panel along the first, second, and third rows.

A method for regulating jet wakes in a combustor, comprising:

• directing a portion of a compressed fluid from a compressor into a passageway defined between a casing and a combustor liner of the combustor;
• directing a combustion gas along an annular combustion zone defined by a panel of the combustor liner;
• discharging a first sub-portion of the portion of the compressed fluid from the passageway into the annular combustion zone via at least one first through-hole to aid in further combustion of an unburned portion of the combustion gas,
• wherein the at least one first through-hole is disposed on at least a section of the panel in a first row extending along a circumferential direction;
• and
• discharging a second sub-portion of the portion of the compressed fluid from the passageway into the annular combustion zone via a plurality of second through-holes to distribute the second sub-portion around a circumferential plane of the section of the panel collectively covered by the at least one first through-hole and the plurality of second through-holes, and purging out the jet wakes,
• wherein the plurality of second through-holes is disposed on the section of the panel, spaced apart from each other along an axial direction and the circumferential direction, and arranged adjacent to the at least one first through-hole, wherein the plurality of second through-holes comprises a first set of through-holes and a second set of through-holes, wherein the first set of through-holes is arranged in a second row and the second set of through-holes is arranged in a third row different from the second row, and wherein the second and third rows extend along the circumferential direction.