A detailed study of the air flow through the fan stage of a high bypass turbofan in engine-out conditions is proposed, to address the key performance issues of this severe case of off-design operation. Experiments are conducted in the new turbofan test rig of ISAE, specially suited to reproduce windmilling operation in an ambient ground setup. The engine is equipped with conventional measurements to characterize the cycle performance and directional five-hole probes are used to characterize the flow across the fan stage. These first results confirm the findings of the literature that the fan outlet guide vane operates under severe off-design angle-of-attack. Massive flow separation is expected in the stator vanes, generating an important p...
The paper focuses on the holistic assessment of the integrated fan stage of DLRs Advanced Technology...
The rotor sub-assembly of the high-pressure turbine of a modern turbofan engine is typically free to...
Experimental testing of aircraft configurations requires the use of representative engine units to s...
A detailed study of the air flow through the fan stage of a high bypass turbofan in engine-out condi...
A detailed study of the air flow through the fan stage of a high-bypass, geared turbofan in windmill...
In the present study, the flow through the fan stage of a high bypass ratio turbofan at windmill is ...
A detailed study of the unsteady airflow through the fan stage of a bypass turbofan is pro- posed. E...
The flow in the windmilling regime of a high-bypass-ratio geared turbofan is studied. The nu- merica...
It is apparent that all fluid flows behave in a transient manner, particularly with fluid flows acro...
For an unpowered turbofan in flight the airflow through the engine causes the fan to freewheel. This...
This paper aims for the analysis of experimental and numerical results of windmilling flow topologie...
The exit flow field of the fan root of large turbofan engines defines the inlet conditions to the co...
The determination of the rotational speed and massflow of a windmilling fan is critical in the desig...
Due to the large disturbance created by the sonic boom, supersonic flight is strictly controlled by ...
Ultra high-bypass ratio aircraft engines adopt slim fan cowl profiles which are sensitive to separat...
The paper focuses on the holistic assessment of the integrated fan stage of DLRs Advanced Technology...
The rotor sub-assembly of the high-pressure turbine of a modern turbofan engine is typically free to...
Experimental testing of aircraft configurations requires the use of representative engine units to s...
A detailed study of the air flow through the fan stage of a high bypass turbofan in engine-out condi...
A detailed study of the air flow through the fan stage of a high-bypass, geared turbofan in windmill...
In the present study, the flow through the fan stage of a high bypass ratio turbofan at windmill is ...
A detailed study of the unsteady airflow through the fan stage of a bypass turbofan is pro- posed. E...
The flow in the windmilling regime of a high-bypass-ratio geared turbofan is studied. The nu- merica...
It is apparent that all fluid flows behave in a transient manner, particularly with fluid flows acro...
For an unpowered turbofan in flight the airflow through the engine causes the fan to freewheel. This...
This paper aims for the analysis of experimental and numerical results of windmilling flow topologie...
The exit flow field of the fan root of large turbofan engines defines the inlet conditions to the co...
The determination of the rotational speed and massflow of a windmilling fan is critical in the desig...
Due to the large disturbance created by the sonic boom, supersonic flight is strictly controlled by ...
Ultra high-bypass ratio aircraft engines adopt slim fan cowl profiles which are sensitive to separat...
The paper focuses on the holistic assessment of the integrated fan stage of DLRs Advanced Technology...
The rotor sub-assembly of the high-pressure turbine of a modern turbofan engine is typically free to...
Experimental testing of aircraft configurations requires the use of representative engine units to s...