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An air intake system of a propeller-turbine engine with a propeller gearbox 1 in in-line arrangement, includes one or more intake units 3 arranged essentially below a nacelle fairing 2 of the propeller-turbine engine with each intake unit 3 being related to a elbow diffuser 19 , a shock diffuser 4 ,

An air intake system of a propeller-turbine engine with a propeller gearbox 1 in in-line arrangement, includes one or more intake units 3 arranged essentially below a nacelle fairing 2 of the propeller-turbine engine with each intake unit 3 being related to a elbow diffuser 19 , a shock diffuser 4 , and a rotationally symmetric attenuation chamber 5 into which the respective shock diffuser 4 issues and which is connected to the compressor inlet 6 of the propeller-turbine engine.

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1. An air intake system of a propeller-turbine engine having a propeller gearbox in in-line arrangement, comprising:at least one intake unit arranged essentially below a nacelle fairing of the propeller-turbine engine,a diffuser flowingly connected to each intake unit, anda rotationally symmetric at

1. An air intake system of a propeller-turbine engine having a propeller gearbox in in-line arrangement, comprising:at least one intake unit arranged essentially below a nacelle fairing of the propeller-turbine engine,a diffuser flowingly connected to each intake unit, anda rotationally symmetric attenuation chamber that is rotationally symmetric with the engine and into which each respective diffuser issues and which is flowingly connected to a compressor inlet of the propeller-turbine engine. 2. An air intake system in accordance with claim 1, wherein the intake unit includes a device for deflecting and diverting a propeller hub boundary layer. 3. An air intake system in accordance with claim 2, wherein the intake unit is oriented to a nacelle-related speed vector of the propeller flow. 4. An air intake system in accordance with claim 3, wherein the diffuser is an elbow-type diffuser. 5. An air intake system in accordance with claim 4, wherein the intake unit includes a branch to an inertia-type particle separator. 6. An air intake system in accordance with claim 5, wherein the attenuation chamber includes at least one secondary outlet. 7. An air intake system in accordance with claim 6, wherein the intake unit is designed in the form of a NACA air intake. 8. An air intake system in accordance with claim 7, and further comprising a plurality of intake units distributed around a circumference of the nacelle. 9. An air intake system in accordance with claim 3, wherein the diffuser is a shock diffuser. 10. An air intake system in accordance with claim 9, wherein the intake unit includes a branch to an inertia-type particle separator. 11. An air intake system in accordance with claim 10, wherein the attenuation chamber includes at least one secondary outlet. 12. An air intake system in accordance with claim 11, wherein the intake unit is designed in the form of a NACA air intake. 13. An air intake system in accordance with claim 12, and further comprising a plurality of intake units distributed around a circumference of the nacelle. 14. An air intake system in accordance with claim 1, wherein the intake unit is oriented to a nacelle-related speed vector of the propeller flow. 15. An air intake system in accordance with claim 1, wherein the diffuser is an elbow-type diffuser. 16. An air intake system in accordance with claim 1, wherein the diffuser is a shock diffuser. 17. An air intake system in accordance with claim 1, wherein the intake unit includes a branch to an inertia-type particle separator. 18. An air intake system in accordance with claim 1, wherein the attenuation chamber includes at least one secondary outlet. 19. An air intake system in accordance with claim 1, wherein the intake unit is designed in the form of a NACA air intake. 20. An air intake system in accordance with claim 1, and further comprising a plurality of intake units distributed around a circumference of the nacelle.