Infrared radiation suppressor for a gas turbine engine

摘要

An infrared radiation suppressor secured to the discharge end of a gas turbine engine has a series of movable vanes maintained in an open trailing edge configuration in which they form converging flow passages for the gases emanating from the gas turbine engine and passing between the vanes, thereby decreasing the gas static pressure at the vane trailing edges below ambient levels. Flow passages in heat exchange relationship with the duct walls of the suppressor carry ambient air through the passages to a point downstream of the vanes. The lowered static pressure at this point causes ambient air to flow through the passages and into the gas stream, thereby cooling the duct walls and the gas stream. The hollow center of the movable vanes are also open to ambient air at the outer ends. The lowered static pressure at the vane trailing edges also causes large quantities of ambient air to enter into the hollow vanes and out the trailing edges into the gas stream further cooling the gases. The movable vanes may be pivoted to a closed or near closed trailing edge configuration in which they form diverging flow passages to the gases which increase the static pressure of the gases discharged from the engine. This enables the suppressor to function as a highly efficient diffuser when infrared radiation suppression is not needed.