Patent ID: 8302377
Filing Date: 2012-11-06
Classification: F02C,F02K,F05D,F23R

Abstract:
1. An engine, comprising: a compressor stage through which a compressed flow passes; a compressor plenum which is coupled to and downstream of the compressor stage and receives said compressed flow; a pulse detonation combustor stage having a plurality of pulse detonation combustors, where said pulse detonation combustor stage receives said compressed flow from said compressor plenum and uses at least a portion of said compressed flow in operation of at least one of said pulse detonation combustors; an exit nozzle stage coupled to said pulse detonation combustor stage which comprises at least one exit nozzle having a converging-diverging geometry, wherein an exhaust from said at least one pulse detonation combustor is directed to at least one exit nozzle and said at least one exit nozzle directs said received exhaust out of said exit nozzle stage; and at least one turbine stage downstream of said exit nozzle stage, wherein said at least one turbine stage receives said received exhaust directed out of said exit nozzle stage.