An Experimental Study on Frequency Characteristics of the Microphone Array Covered with Kevlar in Closed Test Section Wind Tunnel

Experimental study of the influence of flow pulsation in settling chamber on the supersonic free stream disturbances was carried out. Data on the pulsations in the settling chamber and the efficiency of deturbulization system as well as the correlation of pulsations of the flow of settling chamber and flow pulsations in test section of T-325 supersonic wind tunnel of ITAM SB RAS were obtained.

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Turbulent Reduction in a Wind Tunnel Using Trip Strip

Volume 1 ◽

10.1115/ht-fed2004-56876 ◽

2004 ◽

Cited By ~ 1

Author(s):

Mohammad Reza Soltani ◽

Mojtaba Dehghan Manshadi ◽

Mohammad Javad Mirabdollahi

Keyword(s):

Experimental Study ◽

Wind Tunnel ◽

Test Section ◽

Velocity Profiles ◽

Turbulent Intensity ◽

Tunnel Wall ◽

Low Speed ◽

Flow Quality

In this investigation an intensive experimental study was conducted to study the flow quality in a test section of a low speed, V∞ = 10–100, closed return wind tunnel. An interesting result was obtained when a trip strip, a guitar wire with D = 1.14mm, was installed near the end of the contraction region. Addition of this trip wire resulted in a turbulent reduction almost at all speed ranges along the entire test section. Further, it smoothness the variation of turbulent intensity along the test section too. Velocity profiles along the tunnel wall at various speeds using a rake were measured with and without the trip wire. In addition, pressure contours at different location of the test section was measured too.

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Experimental Study on Hot Lubricating Oil Anti-Icing System of Aero-Engine Strut

Volume 5B: Heat Transfer ◽

10.1115/gt2014-26502 ◽

2014 ◽

Author(s):

Wei Dong ◽

Jianjun Zhu ◽

Yong Chen ◽

Zhixiang Zhou

Keyword(s):

Experimental Study ◽

Wind Tunnel ◽

Temperature Variation ◽

Mass Flow ◽

Test Section ◽

Liquid Water Content ◽

Lubricating Oil ◽

Electric Heater ◽

Transient Temperature ◽

Aero Engine

This paper presents an experimental study on the performance of hot oil anti-icing system of aero-engine strut in icing wind tunnel. The experiments are performed in YBF-02 icing wind tunnel. The YBF-02 icing wind tunnel has a test section of 0.28m width and 0.18m height. With the limitation of model blocking, airspeed up to 200m/s can be achieved. A refrigeration system can provide the test-section with temperature from −25°C to 0°C. The experimental model is a full-scale inlet strut of a turboshaft engine. The hot lubricating oil flows through the internal passage of the strut and heats the strut to prevent the strut from ice accretion on its surface. In experiments, the hot oil was heated by an electric heater. The temperature and mass flow of the oil are controlled by Programmable logic controller (PLC) system. The temperature distributions on the strut surface are measured by T type thermocouples. The icing environment parameters in icing wind tunnel for engine strut are: the air total temperature is −10°C,-5°C; the airspeed is 40m/s; the liquid water content ranges from 0.5g/m3 to 2.0g/ m3; the median volume diameter (MVD) of the super-cooled droplet is 20μ m. The surface temperatures of the strut and the ice shape accreted on the strut are measured and photographed. The transient temperature variation of the strut surface is recorded in hot oil anti-icing tests. The characteristics of ice shape and temperature variation on the strut surface with a hot oil anti-icing system are analyzed. The effects of temperature and mass flow of hot oil on the performance of the anti-icing system under different icing conditions are studied.

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