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

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.

scholarly journals Comparison of different droplet measurement techniques in the Braunschweig Icing Wind Tunnel

2021 ◽  
Vol 14 (2) ◽  
pp. 1761-1781
Author(s):  
Inken Knop ◽  
Stephan E. Bansmer ◽  
Valerian Hahn ◽  
Christiane Voigt
Keyword(s):  
Wind Tunnel ◽  
Mass Flow ◽  
Liquid Water ◽  
Measurement Techniques ◽  
Wind Tunnel Test ◽  
Cloud Droplet ◽  
Liquid Water Content ◽  
Liquid Droplets ◽  
Spray System ◽  
Phase Doppler Interferometry

Abstract. The generation, transport and characterization of supercooled droplets in multiphase wind tunnel test facilities is of great importance for conducting icing experiments and to better understand cloud microphysical processes such as coalescence, ice nucleation, accretion and riming. To this end, a spray system has been developed, tested and calibrated in the Braunschweig Icing Wind Tunnel. Liquid droplets in the size range of 1 to 150 µm produced by pneumatic atomizers were accelerated to velocities between 10 and 40 m s−1 and supercooled to temperatures between 0 and −20 ∘C. Thereby, liquid water contents between 0.07 and 2.5 g m−3 were obtained in the test section. The wind tunnel conditions were stable and reproducible within 3 % standard variation for median volumetric diameter (MVD) and 7 % standard deviation for liquid water content (LWC). Different instruments were integrated in the icing wind tunnel measuring the particle size distribution (PSD), MVD and LWC. Phase Doppler interferometry (PDI), laser spectroscopy with a fast cloud droplet probe (FCDP) and shadowgraphy were systematically compared for present wind tunnel conditions. MVDs measured with the three instruments agreed within 15 % in the range between 8 and 35 µm and showed high coefficients of determination (R2) of 0.985 for FCDP and 0.799 for shadowgraphy with respect to PDI data. Between 35 and 56 µm MVD, the shadowgraphy data exhibit a low bias with respect to PDI. The instruments' trends and biases for selected droplet conditions are discussed. LWCs determined from mass flow calculations in the range of 0.07–1.5 g m−3 are compared to measurements of the bulk phase rotating cylinder technique (RCT) and the above-mentioned single-particle instruments. For RCT, agreement with the mass flow calculations of approximately 20 % in LWC was achieved. For PDI 84 % of measurement points with LWC<0.5 g m−3 agree with mass flow calculations within a range of ±0.1 g m−3. Using the different techniques, a comprehensive wind tunnel calibration for supercooled droplets was achieved, which is a prerequisite for providing well-characterized liquid cloud conditions for icing tests for aerospace, wind turbines and power networks.

scholarly journals An Experimental Study of Test Section Velocity Calibration for Low-Speed Wind Tunnel

2012 ◽  
Vol 40 (3) ◽  
pp. 230-236 ◽  
Author(s):  
Se-Yoon Oh ◽  
Jong-Geon Lee ◽  
Sung-Cheol Kim ◽  
Sang-Ho Kim ◽  
Seung-Ki Ahn
Keyword(s):  
Experimental Study ◽  
Wind Tunnel ◽  
Test Section ◽  
Low Speed ◽  
Velocity Calibration ◽  
Low Speed Wind Tunnel

scholarly journals A Study of the Pulsations of Flow in the Settling Chamber and Their Relationship with the Pulsations of the Supersonic Flow

2019 ◽  
Vol 14 (2) ◽  
pp. 77-85
Author(s):  
L. V. Afanasev ◽  
A. A. Yatskih ◽  
A. D. Kosinov ◽  
Yu. G. Yermolaev ◽  
N. V. Semionov ◽  
...  
Keyword(s):  
Experimental Study ◽  
Supersonic Flow ◽  
Wind Tunnel ◽  
Test Section ◽  
Free Stream ◽  
Settling Chamber ◽  
Flow Pulsation ◽  
Supersonic Wind Tunnel ◽  
Flow Pulsations

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.

Turbulent Reduction in a Wind Tunnel Using Trip Strip

Volume 1 ◽  
2004 ◽  
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.

Performance analysis of domestic solar air heating system using V-shaped baffles – An experimental study

2021 ◽  
pp. 095440892110162
Author(s):  
Vijayakumar Rajendran ◽  
Harichandran Ramasubbu ◽  
Karthick Alagar ◽  
Vignesh Kumar Ramalingam
Keyword(s):  
Experimental Study ◽  
Performance Improvement ◽  
Mass Flow ◽  
Thermal Efficiency ◽  
Heating System ◽  
Solar Air Heater ◽  
Absorber Plate ◽  
Air Heating ◽  
Mass Flow Rates ◽  
Carbon Dioxide Mitigation

An experimental study has been carried out to enhance a solar air heater’s performance by integrating artificial roughness through baffles on the absorber plate. In this paper, the thermal and energy matrices analysis of a Solar Air Heater (SAH) roughened with V up perforated baffles have been investigated. The effect of various mass flow rates on the SAH was analyzed with and without baffles. Experimental outputs like outlet air temperature, useful energy (heat) gain and thermal efficiency were evaluated to confirm the performance improvement. The baffled absorber plate SAH was found to give the maximum thermal efficiency and useful energy gain of 89.3% and 1321.37 W at a mass flow rate of 0.0346 kg/s, 13% and 12% higher than SAH without baffle. This result showed that the V up-shaped ribs in flow arrangement provide better thermal performance than smooth plate SAH for the parameter investigated. Energy matrices analysis and carbon dioxide mitigation of the SAH system were also analyzed.

Experimental Study on the Mobility of Channelized Granular Mass Flow

2016 ◽  
Vol 90 (3) ◽  
pp. 988-998 ◽  
Author(s):  
ZHOU Gongdan ◽  
Nigel G. WRIGHT ◽  
SUN Qicheng ◽  
CAI Qipeng
Keyword(s):  
Experimental Study ◽  
Mass Flow ◽  
Granular Mass

Thermo-mechanical analysis of a FGM plate subjected to thermal shock – A new numerical approach considering real time temperature dependent material properties

2021 ◽  
Vol 63 (4) ◽  
pp. 341-349
Author(s):  
Mete Onur Kaman ◽  
Nevin Celik ◽  
Resul Das
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Transfer Coefficient ◽  
Thermal Shock ◽  
Temperature Variation ◽  
Material Properties ◽  
Ambient Air ◽  
Transient Temperature ◽  
Heated Plate ◽  
The Heat Transfer Coefficient

Abstract In present the study, sudden cooling, in other words thermal shock, is applied to a plate that is originally a functionally graded material (FGM). The flat plate is assumed to have an edge crack on it. Hence a numerical couple-field analysis is performed on the plate. The FGM is a combination of Ni and Al2O3. The thermal and mechanical properties of the FGM are assumed to depend on temperature variation. The mixing percentages of the Ni and Al2O3 throughout the plate are considered to vary (i) linearly, (ii) quadratically and (iii) in half-order. In order to solve the problem, a new subroutine depending on temperature is written using APDL (ANSYS Parametric Design Language) codes. Three values of the heat transfer coefficient are applied to the initially heated plate. As a result, the transient temperature variation and stress intensity factor are presented to show the thermo-mechanical relation of the plate. The material properties changing with temperature results in more reliable temperature values. Increasing the heat transfer coefficient results in better cooling and in a lesser amount of time to reach ambient air temperature.

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