Abstract: A gas turbine engine includes a primary combustor, a secondary combustor, a high pressure (HP) turbine, and a mixing duct. The HP turbine is downstream of the primary combustor and fluidly connected to a rear end of the primary combustor via a first exhaust duct. The mixing duct is disposed downstream of the HP turbine and the secondary combustor. The mixing duct has a first inlet fluidly connected to the HP turbine via a turbine exit duct, a second inlet fluidly connected to a rear end of the secondary combustor via a second exhaust duct, and an outlet. The turbine exit duct directs a primary exhaust stream, which is emitted from the primary combustor and expanded through the HP turbine, into the mixing duct. The second exhaust duct directs a secondary exhaust stream emitted from the secondary combustor into the mixing duct.

Abstract: In one embodiment, a pulse detonation system includes a pulse detonation tube and an air valve disposed at an upstream end of the pulse detonation tube. The air valve is configured to provide an air flow into the pulse detonation tube. The pulse detonation system also includes a fuel injector configured to inject fuel into the air flow to establish a fuel-air mixture configured to support detonation, and to establish a region in the fuel-air mixture having a fuel to air ratio insufficient to support a detonation wave. The pulse detonation system further includes an ignition source configured to detonate the fuel-air mixture when the region is disposed adjacent to the air valve.