Combustor primary zone cooling flow scheme
AssigneePratt & Whitney Canada Corp.
InventorsHAYLEY OZEM, SI-MAN AMY LAO, SRI SREEKANTH, JEFFREY VERHIEL
Life of this patent
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Abstract
A gas turbine engine combustor has a shell defining a combustion chamber having a primary zone and a dilution zone downstream of the primary zone. The shell has an outer skin and an inner skin defining an air gap therebetween. The inner skin in the upstream portion of the primary zone is free from effusion holes and has heat transfer augmenters projecting from a back side thereof into the air gap. Effusion holes in the inner skin are only disposed downstream towards the tail end of the primary zone in order to delay the injection of any disruptive cooling air that could potentially interfere with the combustion process.
Claims18
A combustor for a gas turbine engine, the combustor comprising:
- a shell defining a combustion chamber having a primary zone and a dilution zone downstream of the primary zone, the shell having an outer skin and an inner skin, the inner and outer skins defining an air gap therebetween, heat transfer augmenters projecting from the inner skin into the air gap, effusion holes extending through the inner skin downstream of the heat transfer augmenters, the inner skin being free from effusion holes over a portion surrounding an upstream half of the primary zone.
A combustor for a gas turbine engine, the combustor comprising:
- a shell defining a combustion chamber having a primary zone and a dilution zone downstream of the primary zone, the shell having an outer skin and an inner skin, the inner and outer skins defining an air gap therebetween, the primary zone having an upstream portion corresponding generally to the first 40% to 60% of the primary zone and a remaining downstream portion;
- in the upstream portion of the primary zone, the inner skin being free from effusion holes and having heat transfer augmenters projecting from a back side thereof into the air gap;
- and in the remaining downstream portion of the primary zone, the inner skin having effusion holes extending therethrough.
A method of providing cooling to a gas turbine engine combustor having a combustor shell defining a combustion chamber, the combustion chamber having a primary zone where combustion occurs and a dilution zone downstream of the primary zone, the method comprising:
- cooling down an inner skin of the combustor shell by using a combination of impingement and convection cooling over an upstream half of the primary zone and a combination of impingement and effusion cooling over a remaining downstream half of the primary zone.
Dependencies are inferred from the claim text.