GAS TURBINE ENGINE COMBUSTOR WITH FLUIDIC CONTROL OF SWIRLERS

摘要

A system and method for controlling air flow through a combustor swirler assembly that includes an inner swirler and an outer swirler. A bistable fluidic amplifier that includes an air inlet, a first air outlet, a second air outlet, and a control port is disposed upstream of the combustor swirler assembly. A flow of compressed is directed into the air inlet of the bistable fluidic amplifier and, based on the control air pressure at the control port, the flow of compressed air supplied to the air inlet is selectively directed to either the first air outlet or the second air outlet.

主权项

1. A gas turbine engine combustor assembly, comprising:
an inner annular liner, outer annular liner spaced apart from the inner annular liner, and a dome assembly coupled between the inner and outer annular liners to define a combustion chamber; a plurality of fuel/air openings formed in an extending through the dome assembly; a plurality of swirler assemblies, each swirler assembly disposed within a different one of the fuel/air openings, each swirler assembly comprising an inner swirler and an outer swirler that surrounds the inner swirler; and a bistable fluidic amplifier comprising an air inlet, a first air outlet, a second air outlet, and a control port, the air inlet adapted to receive a flow of compressed air, the first air outlet in fluid communication with the air inlet and one of the outer swirlers, the second air outlet in fluid communication with the air inlet and one of the inner swirlers, the control port adapted to selectively receive a flow of control air, wherein the bistable fluidic amplifier is responsive to control air pressure at the control port to selectively direct the flow of compressed air supplied to the air inlet to either the first air outlet or the second air outlet.