초록 ▼

A shield is disposed in spaced relationship to the exterior surface of the combustor liner of a gas turbine engine and extends over a plurality of very small holes formed in the combustor liner so as to block flow of air to these holes. Further, the shield provides a space between the shield and the

A shield is disposed in spaced relationship to the exterior surface of the combustor liner of a gas turbine engine and extends over a plurality of very small holes formed in the combustor liner so as to block flow of air to these holes. Further, the shield provides a space between the shield and the combustor liner for receiving reverse flow of air. A portion of the air flowing along the exterior surface of the combustor liner is diverted for reverse flow in the path provided between the shield and the combustor liner. A lesser plurality of substantially larger holes are provided in the combustor liner at the point of reversal of the air so that the dirt particles in the air, because of the centrifugal force acting thereon, tend to flow through these larger holes. A second group of larger holes are provided in the combustor liner approximately at the forward end of the space between the shield and the combustor liner. In flowing to the very small holes in the combustor liner the air must make a second reversal and substantially all of any remaining dirt particles are caused to flow through this second group of larger holes during this second reversal of air flow. Accordingly, the air reaching the very small holes in the combustor liner and being directed to the interior surface of the combustor liner for cooling thereof is substantially devoid of dirt particles and the possibility of plugging any of these very small holes is minimized.

대표청구항 ▼

A gas turbine engine combustor aft of the gas turbine compressor section, said combustor comprising: (a) a liner disposed inwardly of a combustor outer wall and in the compressor discharge airflow, wherein the compressor discharge airflow is used for combustor cooling air and said liner is positione

A gas turbine engine combustor aft of the gas turbine compressor section, said combustor comprising: (a) a liner disposed inwardly of a combustor outer wall and in the compressor discharge airflow, wherein the compressor discharge airflow is used for combustor cooling air and said liner is positioned for flow of cooling air past the exterior of said liner; (b) a plurality of small film cooling holes in said liner, said film cooling holes being inclined toward the aft end of the combustor to direct cooling air along the interior surface of said liner; (c) first means on said liner for blocking direct flow of air to said small film cooling holes and providing a path for reverse flow of air between said first means and the exterior surface of said liner; (d) second means disposed aft of said first means for diverting a portion of said air and providing reverse flow of the diverted air into said path; and (e) a first plurality of larger holes in said liner at the point of reversal of flow of said air for passing dirt particles therethrough.