Wing-propulsion unit combination, airplane and wing section of an airplane comprising a propulsion unit tap air channel arrangement

Abstract

Wing-propulsion unit combination comprising a wing (W) with a main wing (W1) and a propulsion unit (E) with a pre-mix chamber (E1), a combustion chamber and a hot air chamber (E2), further comprising: a) a propulsion unit tap air channel (2) running along the span direction (SW) and along the front edge of the main wing, said tap air channel comprising a propulsion unit tap air inlet apparatus (2-1) that is coupled to a propulsion unit hot air chamber (E2), and comprising a propulsion unit tap air outlet apparatus (2-2) that is made up of a mouth at the main wing (W1) or a connecting part for coupling the propulsion unit tap air channel to a user of the propulsion unit tap air, b) a surrounding air channel (10) running along the propulsion unit tap air channel (2) comprising a surrounding air inlet apparatus (10-1) that is located at a component of the airplane (AC) facing the proper flow direction (S) of the airplane (AC) and that comprises an opening (10-3) for letting in surrounding air into the surrounding air channel (10), and comprising a surrounding air outlet apparatus (10-2) with a passage between the surrounding air channel (10) and a pre-mix chamber (E1) of the propulsion unit (E), so that the arrangement (1) of propulsion unit tap air channel (2) and surrounding air channel (10) forms a heat exchange apparatus for cooling of the air flowing in the propulsion unit tap air channel (2) and so that the surrounding air passing through the surrounding air channel (10) is fed to the combustion chamber in the propulsion unit.

Description

technical field [0001] The invention relates to a wing-engine combination unit with a wing and an engine, an aircraft with a wing and a wing part of the aircraft with an engine bleed air channel structure. Background technique [0002] The use of engine bleed air is applied to different systems of the aircraft. Additionally, engine bleed air is used for thermal regulation and pressurization of the aircraft airframe. Fuel, hydraulic and water tanks are also kept pressurized by means of bleed air in order, for example, to prevent pump failure. The bleed air discharge is a simple and proven system which is constructed from technically simple components. [0003] The disadvantage of the use of bleed air is that it leads to an increase in fuel consumption and a decrease in engine power. For this reason, for example in the case of high take-off power, the bleed discharge is switched off in order to prevent overheating of the turbine. Therefore, branching bleed air from the eng...

AI Technical Summary

Problems solved by technology

[0003] The disadvantage of the use of bleed air is that it leads to an increase in fuel consumption and a decrease in engine power

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