초록 ▼

A vortex-generating device is presented to reduce a thermal exposure of an aircraft to hot exhaust gases discharged from an aircraft engine. The engine also discharges cold air from a fan of the engine. The aircraft engine may be coupled to the aircraft via a support mast located on a main wing. A p

A vortex-generating device is presented to reduce a thermal exposure of an aircraft to hot exhaust gases discharged from an aircraft engine. The engine also discharges cold air from a fan of the engine. The aircraft engine may be coupled to the aircraft via a support mast located on a main wing. A portion of the support mast of an aircraft engine is located near a hot gas flow being discharged from the engine. The vortex-generating device is positioned on a surface of the support mast. The device generates a vortex which crosses the hot gases and prevents the hot gas flow from reaching a heat sensitive portion of the support mast. This device is adaptable to the operating conditions of an already-built aircraft without any notable increased weight.

대표청구항 ▼

The invention claimed is: 1. An aircraft having a wing, the wing comprising:an airfoil to provide lift;at least one engine assembly to provide propulsion for the aircraft, the at least one engine assembly including:an aircraft engine to provide propulsion to the aircraft by creating a flow of hot ga

The invention claimed is: 1. An aircraft having a wing, the wing comprising:an airfoil to provide lift;at least one engine assembly to provide propulsion for the aircraft, the at least one engine assembly including:an aircraft engine to provide propulsion to the aircraft by creating a flow of hot gases and a jet of cold air,an engine support structure to couple the aircraft engine to the wing, the engine support structure including a downstream zone located laterally and downstream of an exhaust output of a nacelle and of an engine cowl,the engine cowl to discharge the flow of hot gases in a cylindrical shape in a direction coaxial with the engine cowl, andthe nacelle surrounding the engine cowl to discharge the jet of cold air; anda plurality of vortex-generating devices attached to and extending out of the engine support structure downstream of the engine cowl and the nacelle, each of the vortex-generating devices disturbing the flow of hot gases, deviating a hot boundary layer of the flow of hot gases and absorbing the hot boundary layer by mixing the hot gases with the cold air, whereinthe plurality of vortex-generating devices are spaced apart from each other and disposed along a direction in which the flow of hot gases is discharged from the engine cowl,wherein each of the vortex generating devices is substantially aft of an output of the engine cowl from which the hot gases are discharged.