초록 ▼

Successful flight of high altitude military aircraft is dependent, in part, upon the ability of the aircraft to remain undetected during flight. Against the highly sophisticated infrared sensors developed during recent years, particularly for miliary use, an aircraft powered by a gas turbine engine

Successful flight of high altitude military aircraft is dependent, in part, upon the ability of the aircraft to remain undetected during flight. Against the highly sophisticated infrared sensors developed during recent years, particularly for miliary use, an aircraft powered by a gas turbine engine is at a particular disadvantage. Hence infrared emissions from gas turbine engines have been reduced by use of a variety of infrared radiation (IR) suppressor designs. But in these designs aerodynamic problems are difficult to analyze and geometrical parameters are very critical, and nearly impossible to maintain. The IR suppressor herein provides the best blend of simple aerodynamics, heat transfer, and geometry.

대표청구항 ▼

In an infrared radiation suppressor for aircraft gas turbine engine outlets wherein hot exhaust gases discharged therefrom are blocked from view by metal surfaces, and mixed with ambient air drawn into said suppressor to cool the gases and radiation-emitting hot metal surfaces, the improvement compr

In an infrared radiation suppressor for aircraft gas turbine engine outlets wherein hot exhaust gases discharged therefrom are blocked from view by metal surfaces, and mixed with ambient air drawn into said suppressor to cool the gases and radiation-emitting hot metal surfaces, the improvement comprising: exhaust gas transition means including a gas inlet duct having a circular inlet adapted to fit the engine outlet, and having flat converging surfaces forming a rectangular outlet, a concentric flow separator geometrically similar to the gas inlet duct so that it has a round end, and two flat converging surfaces, but dissimilar in that a plate covers its round end, the flow separator being disposed within the gas inlet duct with its plate end in the circular gas inlet end, forming an annular duct for inflowing engine exhaust gases, and rectangular ducts downstream therefrom in the direction of gas flow, partition means formed by merging the two flat converging surfaces of the flow separator into a single dividing plane to form two adjacent rectangular outlet ducts, the transition duct thus transforming engine exhaust gases from annular flow to two rectangularly confined gas streams; air mixing means including a rectangular mixing duct larger than the rectangular transition duct outlet adapted to be attached thereto but to overlap the rectangular outlet or the transition duct to form a perimetrical ambient air inlet slot therebetween, the mixing duct having divergent walls and parallel sides forming a housing with an outlet larger than its inlet, flow divider means within the mixing duct having a plane surface joining the transition outlet partition means and having diverging walls in the housing as extensions of the plane surface, the diverging walls extending across the housing between its sides to form two diverging gas ducts separated from each other within the housing, to effect more even heating of divider surfaces, the cross sectional area of the housing being larger than that of the transition section outlet to create a mixing plane aspirating air through the perimetrical air inlet slot to cool gas stream in the two ducts, a shielding plate within the housing between the diverging flow divider walls to block a rear view of the divergent flow divider, and spaced from the flow divider surfaces; means cooling the flow divider and shielding plate including portholes in the sides of the mixer housing and slots between the shielding plate and flow divider which cooperate to draw ambient air across shielding plate and flow divider surfaces.