Quench jet arrangement for annular rich-quench-lean gas turbine combustors

An outer liner of a combustor of a gas turbine engine, comprising:

• a plurality of liner regions arranged adjacent one another and separated by boundary lines;
• a plurality of combustion air admission holes formed in the liner regions, the air admission holes within each liner region forming a V-pattern of at least seven combustion air admission holes, wherein the plurality of air admission holes includes a first air admission hole axially aligned with a respective fuel injector and a second air admission hole approximately on a first boundary line between a respective liner region and a first adjacent outer liner region, the first air admission hole being downstream of the second air admission hole;
• a third air admission hole approximately on a second boundary line between the respective outer liner region and a second adjacent outer liner region;
• wherein the plurality of air admission holes includes fourth and fifth air admission holes on a line between the first and second air admission holes and sixth and seventh air admission holes on a line between the first and third air admission holes;
• and
• wherein each of the air admission holes is a combustion air admission hole configured to admit a quench jet into the combustion chamber such that the quench jet penetrates radially inward at least 25% of a width of the combustion chamber.

A combustor for a turbine engine, comprising:

• an outer liner having a first group of air admission holes and defining a plurality of outer liner regions, each outer liner region being separated from an adjacent outer liner by an outer boundary line;
• an inner liner circumscribed by the outer liner and forming a combustion chamber therebetween, the inner liner having a second group of air admission holes and defining a plurality of inner liner regions, each inner liner region being separated from an adjacent inner liner region by an inner boundary line;
• a plurality of fuel injectors extending into the combustion chamber and configured to deliver an air-fuel mixture to the combustion chamber, each of the plurality of fuel injectors being associated with one of the outer liner regions and one of the inner liner regions, and wherein each of the first group of air admission holes is a combustion air admission hole configured to admit a major or minor jet into the combustion chamber such that each major or minor jet penetrates radially inward at least 25% of a width of the combustion chamber,
• wherein the first group of air admission holes within a respective outer liner region includes a first air admission hole axially aligned with the respective fuel injector, a second air admission hole approximately on the outer boundary line between the respective outer liner region and a first adjacent outer liner region, the first air admission hole being downstream of the second air admission hole;
• a third air admission hole approximately on the outer boundary line between the respective outer liner region and a second adjacent outer liner region, the third air admission hole being circumferentially aligned with the second air admission hole;
• fourth and fifth air admission holes on a line between the first and second air admission holes;
• and
• sixth and seventh air admission holes on a line between the first and third air admission holes.