초록 ▼

A one piece cold combustor wall for lining the reverse flow hot combustor wall of a gas turbine engine, disposed at a distance from the outer surface of the hot combustor wall. Improved cooling of the hot combustor wall results from the addition of impingement cooling air injected through orifices i

A one piece cold combustor wall for lining the reverse flow hot combustor wall of a gas turbine engine, disposed at a distance from the outer surface of the hot combustor wall. Improved cooling of the hot combustor wall results from the addition of impingement cooling air injected through orifices in the cold combustion wall directed at the hot combustion wall together with film cooling by air conducted between the hot and cold combustor walls. The cold combustor wall is perforated with a pattern of air impingement inlet orifices through the cold combustor wall conducting compressed air from the outer surface of the cold combustor wall in compressed air jets directed at the outer surface of the hot combustor wall. The provision of a cold combustor wall also improves conventional air film cooling by adding impingement cooling and reusing the air after impingement to form a contained air film between the hot and cold walls. An air cooled thermal expansion joint joins the hot and cold walls at a downstream end with interlocking flanges, with sliding seal surfaces disposed on parallel adjacent sides.

대표청구항 ▼

[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:] [1.] A reverse flow gas turbine engine combustor comprising:a one piece hot combustor wall connected downstream to a turbine stage, the hot combustor wall having an inner surface in com

[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:] [1.] A reverse flow gas turbine engine combustor comprising:a one piece hot combustor wall connected downstream to a turbine stage, the hot combustor wall having an inner surface in communication with hot combustion gas flowing in a direction toward the turbine stage and an outer surface in contact with cool compressed air, the hot combustor wall including air film cooling means, comprising a plurality of air film inlet orifices through the hot combustor wall, the inlet orifices being disposed in a series of circular peripheral rings spaced apart along the length of the hot combustor wall, for conducting compressed air from the outer surface of the hot combustor wall in a cooling air film along the inner surface of the hot combustor wall in the hot gas flow direction;a one piece cold combustor wall fixed to the hot combustor wall at an upstream end in a sealed continuous joint, the cold combustor wall being disposed at a distance from the outer surface of the hot combustor wall defining a partial annular toroid-shaped external air chamber between an inner surface of the cold combustor wall and the outer surface of the hot combustor wall, the cold combustor wall having an outer surface in contact with cool compressed air and including air impingement cooling means, comprising a plurality of air impingement inlet orifices through the cold combustor wall, for conducting compressed air from the outer surface of the cold combustor wall in a plurality of impinging compressed air jets directed at the outer surface of the hot combustor wall, the impinging air jets being disposed in a series of discrete peripheral bands spaced apart along the length of the cold combustor wall between the rings of inlet orifices of the hot combustor wall; anda continuous circumferential thermal expansion joint connected to the hot combustor wall at a downstream end, the thermal expansion joint comprising sliding seal surfaces engaging the downstream ends of the cold and hot combustor walls, wherein the downstream ends of the cold and hot combustor walls have interlocking tongues and grooves, the sliding seal surfaces disposed on parallel adjacent sides of each tongue.