Abstract: A method for suppressing infrared radiation from an engine of an aircraft operating in an environment includes directing hot exhaust from the aircraft engine into a lobed mixer of a single baffle infrared suppressor having a collapsible, translatable baffle to generate alternating flows of hot exhaust gas and cold air. The method further includes directing the alternating flows of hot exhaust gas and cold air towards the single baffle assembly to mix the hot exhaust gas with the cold air.

Abstract: A method enables a gas turbine engine to be assembled. The method includes providing a combustor including a liner that defines a combustion chamber therein, and coupling a casing within the gas turbine engine to extend circumferentially around the combustor liner, wherein the casing includes an inlet and a scroll duct that is coupled in flow communication to the inlet and extends at least partially circumferentially around the liner. The method also includes coupling the inlet in flow communication with a feed air source.

Abstract: A method facilitates assembling a gas turbine engine. The method comprises coupling a combustor including a dome assembly and a combustor liner that extends downstream from the dome assembly to a combustor casing that is positioned radially outwardly from the combustor, coupling a fuel injector including a fuel inlet and an air inlet to the combustor casing such that the fuel injector extends axially through the dome assembly such that fuel may be discharged from the primer nozzle into the combustor, and coupling the air inlet to an air source such that cooling air received therethrough is circulated through the fuel injector to facilitate cooling the fuel injector.