An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown.
Immersed core flow inlet between rotor blade and stator vane for an unducted fan gas turbine
2019-09-03
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS |
IMMERSED CORE FLOW INLET BETWEEN ROTOR BLADE AND STATOR VANE FOR UNDUCTED FAN GAS TURBINE
European Patent Office | 2016
|IMMERSED CORE FLOW INLET BETWEEN ROTOR BLADE AND STATOR VANE FOR AN UNDUCTED FAN GAS TURBINE
European Patent Office | 2016
|IMMERSED CORE FLOW INLET BETWEEN ROTOR BLADE AND STATOR VANE FOR AN UNDUCTED FAN GAS TURBINE
European Patent Office | 2016
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