Patent ID: 8220249
Filing Date: 2012-07-17
Classification: F02K,F05D

Abstract:
1. A rocket nozzle comprising: a dual-bell nozzle; and a gas introducing section configured to introduce gas into a space surrounded by said dual-bell nozzle, wherein combustion gas flows in said space, said dual-bell nozzle includes: a first stage nozzle bell-shaped and surrounding an upstream portion of said space; and a second stage nozzle bell-shaped and surrounding a downstream portion of said space, said dual-bell nozzle has an inflection point between said first stage nozzle and said second stage nozzle, said gas introducing section includes a first gas inlet provided to a first inner wall surface of said first stage nozzle, said gas is introduced into said space from said first gas inlet, turbine exhaust gas after driving a turbo pump is used as said gas, said first gas inlet injects said gas parallel to said first inner wall surface adjacent said inflection point, said gas introducing section includes: a second gas inlet provided to a second inner wall surface of said second stage nozzle; and a three-way valve, each of said first gas inlet, said second gas inlet and said turbo pump is connected to said three-way valve, and said second gas inlet injects said turbine exhaust gas as a film-like flow along said second inner wall surface adjacent said inflection point, wherein said three-way valve switches between said first gas inlet and said second gas inlet to connect one of said first gas inlet and said second gas inlet to said turbo pump.