A turbine engine assembly including an air flow guide assembly, including at least one guide vane and at least one structural arm, the vane and arm extending radially about an axis. The arm includes an upstream end portion having a guide vane profile and including a leading edge aligned with that of the vane; a downstream portion; and an intermediate portion including an upper surface extending between an upstream end point and a downstream end point. The upstream end point is separated from the leading edge of the arm by an axial distance of between 0.2c and 0.5c, c being the length of the axial chord of the vane, and the angle of the tangent to the upper surface at the upstream end point is equal to that at the downstream end point ±1 degree.
Turbine engine air guide assembly with improved aerodynamic performance
19.10.2021
Patent
Elektronische Ressource
Englisch
IPC: | F02K JET-PROPULSION PLANTS , Strahltriebwerke / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS |
TURBINE ENGINE AIR GUIDE ASSEMBLY WITH IMPROVED AERODYNAMIC PERFORMANCE
Europäisches Patentamt | 2018
|GAS TURBINE ENGINE AIR FLOW STRAIGHTENING UNIT WITH IMPROVED AERODYNAMIC CHARACTERISTICS
Europäisches Patentamt | 2020
|Analysis of Gas Turbine Engine Operability with the Aerodynamic Turbine Engine Code
British Library Conference Proceedings | 1997
|