Patent ID: 8683780
Filing Date: 2014-04-01
Classification: F02C,F05D,F23C,F23R,Y02E

Abstract:
1. A pulse detonation combustion system, comprising: an inlet section in communication with a fuel supply and an oxidizer supply; a detonation chamber in fluid communication with the inlet section; an igniter in fluid communication with the inlet section and the detonation chamber; and a plurality of first flame accelerators disposed on an upstream side of the igniter and a plurality of second flame accelerators disposed on a downstream side of the igniter, wherein at least one first flame accelerator of the plurality of first flame accelerators and at least one second flame accelerator of the plurality of second flame accelerators are geometrically structured to have directionally-dependent drag coefficients, wherein the at least one first flame accelerator and the at least one second flame accelerator have a greater drag coefficient for precursor and combustion shockwaves propagating in a direction away from the igniter than for waves propagating in a direction toward the igniter.