The invention relates to an aviation propeller (10) having a longitudinal axis (X), comprising a hub (12), an annular row of ductless upstream rotor blades (14) and an annular row of ductless downstream stator blades (16), each downstream stator blade (16) having a variable pitch, and wherein at least one of the downstream stator blades (16) is in a closed pitch configuration with respect to another of the downstream stator blades (16) because the at least one of the downstream stator blades (16) has a pitch angle (gamma) less than the pitch angle (gamma) of the another downstream stator blade (16).

    本发明涉及一种具有纵向轴线(X)的航空推进器(10),其包括轮毂(12)、环形行的无导管上游转子叶片(14)和环形行的无导管下游定子叶片(16),每一下游定子叶片(16)具有可变俯仰,且其中所述下游定子叶片(16)中的至少一个相对于所述下游定子叶片(16)中的另一个处于闭合俯仰配置,因为所述下游定子叶片(16)中的所述至少一个具有的俯仰角(γ)小于所述另一个下游定子叶片(16)的所述俯仰角(γ)。


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    Title :

    Aviation propeller


    Additional title:

    航空推进器



    Publication date :

    2024-11-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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