As the axial fan blades move within the fan case pressure transients are developed, which can be measured and qualified by a fixed point monitor. The nature of the pressure transient pattern observed close to the fan blade varies with the location on the fan performance curve. Measurement of the pressure fluctuation around the fan blade ring reveals the minute variation in pressure associated with the movement of the air within the fan. Such observations could be the basis for an on-line fan monitoring system based on the acoustic emissions from the fan blade. This paper describes a preliminary study that was conducted to evaluate the nature of the pressure transient profiles close to the blade of a laboratory axial flow fan. A comparison i...
An experimental rotor has been expressly realized to study the trailing edge noise generated by axia...
The relation between the noise level of an axial flow fan and the flow around the fan rotor was inve...
Flutter testing is an integral part of aircraft gas turbine engine development. In typical flutter t...
A major source of the noise generated by high bypass ratio aircraft fan engines is the unsteady pres...
This paper presents an experimental study on the fully developed rotating stall of an axial flow fan...
ABSTRACT This paper describes a technique for the investigation of noise sources correlated to tip c...
This two-part study describes the development of a novel stall-detection methodology for low-speed a...
This paper presents an experimental technique developed to assess the performance of a family of axi...
The aim of this work is to study the correlation mechanisms underlying the aerodynamic field generat...
This study describes the assessment of a novel methodology that the authors recently proposed for th...
We describe a mechanical/acoustic study of a short-ducted axial flow fan. The purpose is to compare ...
Abstract An experimental investigation of the aerodynamic response of the rotor blading of a single ...
This paper dealswith the experimental validation of an analytical trailing-edge noisemodel dedicated...
Stall induced vibrations place fundamental limitations on a fan stage performance and remains a pers...
An investigation was conducted to compare the steady-state and dynamic flow characteristics of an ax...
An experimental rotor has been expressly realized to study the trailing edge noise generated by axia...
The relation between the noise level of an axial flow fan and the flow around the fan rotor was inve...
Flutter testing is an integral part of aircraft gas turbine engine development. In typical flutter t...
A major source of the noise generated by high bypass ratio aircraft fan engines is the unsteady pres...
This paper presents an experimental study on the fully developed rotating stall of an axial flow fan...
ABSTRACT This paper describes a technique for the investigation of noise sources correlated to tip c...
This two-part study describes the development of a novel stall-detection methodology for low-speed a...
This paper presents an experimental technique developed to assess the performance of a family of axi...
The aim of this work is to study the correlation mechanisms underlying the aerodynamic field generat...
This study describes the assessment of a novel methodology that the authors recently proposed for th...
We describe a mechanical/acoustic study of a short-ducted axial flow fan. The purpose is to compare ...
Abstract An experimental investigation of the aerodynamic response of the rotor blading of a single ...
This paper dealswith the experimental validation of an analytical trailing-edge noisemodel dedicated...
Stall induced vibrations place fundamental limitations on a fan stage performance and remains a pers...
An investigation was conducted to compare the steady-state and dynamic flow characteristics of an ax...
An experimental rotor has been expressly realized to study the trailing edge noise generated by axia...
The relation between the noise level of an axial flow fan and the flow around the fan rotor was inve...
Flutter testing is an integral part of aircraft gas turbine engine development. In typical flutter t...