Correction: Design of a Thermal Wind Tunnel for Impingement and Film Cooling Research

2018 ◽  
Author(s):  
Sean C. Underwood ◽  
Ray Taghavi ◽  
Saeed Farokhi
Keyword(s):  
Wind Tunnel ◽  
Film Cooling ◽  
Thermal Wind

scholarly journals Comparison of turbine blade film cooling efficiency between PSP and TLC techniques in a stationary wind tunnel

AIP Advances ◽  
2021 ◽  
Vol 11 (1) ◽  
pp. 015333
Author(s):  
Xiaojian He ◽  
Haiwang Li ◽  
Guoqin Zhao ◽  
Ruquan You
Keyword(s):  
Wind Tunnel ◽  
Turbine Blade ◽  
Film Cooling ◽  
Cooling Efficiency ◽  
Film Cooling Efficiency

Film cooling experimental technique using a Ludwieg tube wind tunnel

1993 ◽  
Vol 6 (2) ◽  
pp. 186-195
Author(s):  
Ming-Yuan Zhang ◽  
Fu-Kang Tsou ◽  
Xue-Jun Chen ◽  
Shih-Jiun Chen
Keyword(s):  
Wind Tunnel ◽  
Experimental Technique ◽  
Film Cooling ◽  
Ludwieg Tube

Design, Characterization, and Verification of a Closed Loop Wind Tunnel With Linear Cascade and Upstream Wake Generator

2015 ◽  
Author(s):  
Carlos R. Gonzalez ◽  
Guillaume F. Bidan ◽  
Jason W. Bitting ◽  
Christopher M. Foreman ◽  
Jean-Philippe Junca-Laplace ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Test Section ◽  
Film Cooling ◽  
Spectral Characteristics ◽  
Test Facility ◽  
Flat Plates ◽  
Freestream Velocity ◽  
Linear Cascade ◽  
Wide Range ◽  
Stationary Frame

A new cascade wind tunnel has been designed and constructed at the LSU Wind Tunnel Laboratory. The objective was to develop a versatile test facility, suitable for a wide range of experimental studies and measurements on turbine airfoils, especially with regards to film-cooling incorporating realistic unsteady effects due to passing wakes. The test section consists of a four passage linear cascade composed of three full blades and two shaped wall blades. The 2D blade shape profile of the cascade is a high-lift, low-pressure turbine L1A profile provided by the US Air Force Research Laboratories (AFRL), with a 152-mm axial chord. The Reynolds number based on the axial chord length at the nominal freestream velocity of 50 ms−1 is 500,000. A conveyor-based system was designed and fabricated to simulate the passing wakes of the upstream vanes (or blades) on the test blades (or vanes) depending on which airfoil types are put on the stationary frame and the moving frame of the conveyor. The original implementation uses blade profiles on the stationary frame and thick plate wake generators on the translating frame. Results are presented from hot-wire surveys conducted to characterize and qualify the velocity and turbulence intensity distributions and associated spectral characteristics at the cascade test section inlet, in the wake of the vanes and in the wake of the test blade. A blade instrumented with 123 pressure taps was used to acquire static pressure profiles of the cascade central blade, which were compared to the ones from the nominal airfoil design as well as to those obtained from a CFD simulation of the cascade flow. Incoming velocity and temperature profiles were found to be uniform to within a few percentage points, and the pressure coefficient distribution was found to be in good agreement with design values. The passage periodicity of the conveyor-belt-driven, flat-plates was verified and their wake was characterized. These results verified that the cascade wind tunnel operates according to design, thus proving to be a reliable test-bed for film cooling studies with and without unsteady wake effects. The design also incorporates an in-house-designed, miniature periscopic and adjustable laser sheet generating system integrated within the “dummy” blades to enable Particle Image Velocimetry measurements in the intra-blade domain.

An Experimental Investigation on Cooling Performance of a Laminated Configuration Using Infrared Thermal Image Technique

2009 ◽  
Author(s):  
Jianhua Wang ◽  
Xijia Lv ◽  
Qingdong Liu ◽  
Xiangyu Wu
Keyword(s):  
Wind Tunnel ◽  
Film Cooling ◽  
Imaging System ◽  
Temperature Drop ◽  
Cooling Effectiveness ◽  
Infrared Thermal Imaging ◽  
Digital Control Systems ◽  
Image Technique ◽  
Thermal Imaging System ◽  
Hot Surface

The performance of double-wall laminated film cooling configurations was studied by the experiments carried out in the hot gas wind tunnel of UTSC. Three devices with the true size of gas turbine components were employed as specimens. The specimens have different angles of film hole with mainstream direction and rib designs. The temperature distributions at the hot surface of the specimens were measured by an infrared thermal imaging system. An algorithm of digital imaging signal was used, and two-dimensional temperature drop from initial wall to cooled wall was directly obtained. By comparison of the temperature drop of the three devices, the influences of the columnar ribs and angle of film holes on cooling effectiveness were discussed. The experimental parameters of the wind tunnel were accurately dominated by two digital control systems for mainstream temperature and mass flow rate, average cooling effectiveness of the three specimens were measured. The correlations between the mainstream Reynolds number with the Nusselt number and the average effectiveness were quantitatively compared for the three specimens. The investigation indicates that the effect of the film holes’ angle on the overall cooling effectiveness is much marked than the rib effect.

The Advanced Cooling Technology for the 1500°C Class Gas Turbines: Steam-Cooled Vanes and Air-Cooled Blades

1997 ◽  
Vol 119 (3) ◽  
pp. 624-632 ◽  
Author(s):  
H. Nomoto ◽  
A. Koga ◽  
S. Ito ◽  
Y. Fukuyama ◽  
F. Otomo ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Electric Power ◽  
Gas Turbine ◽  
Film Cooling ◽  
Gas Turbines ◽  
Combined Cycle ◽  
Cooling Effectiveness ◽  
Impingement Cooling ◽  
Cycle Systems ◽  
Cooling Technology

It is very essential to raise the thermal efficiency of combined cycle plants from the viewpoint of energy saving and environmental protection. Tohoku Electric Power Co., Inc., and Toshiba Corporation in Japan have jointly studied the next generation of combined cycle systems using 1500°C class gas turbine. A promising cooling technology for the vanes using steam was developed. The blades are cooled by air, adopting the impingement cooling, film cooling, and so on. The cooling effectiveness was confirmed both for the vanes and the blades using a hot wind tunnel. This paper describes the design features of the vanes and the blades, and the results of the verification tests using the hot wind tunnel.

scholarly journals Experimental Study Of Short Hole Film-Cooling

2021 ◽  
Author(s):  
Mohammed A. Gandhi
Keyword(s):  
Experimental Study ◽  
Wind Tunnel ◽  
Film Cooling ◽  
Double Row ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness ◽  
Single Row ◽  
Blowing Ratio ◽  
Lift Off ◽  
Low Speed Wind Tunnel

An experimental study was conducted to investigate the film cooling effectiveness of a few configurations of short injection holes: single row, double row and both of the preceding cases with an upstream ramp placed at two different locations. In order to perform the above study, a wind-tunnel facility was assembled to facilitate in the successful culmination of the experiments. The focus of the study was to determine the cooling provided by the short injection holes at a variety of blowing ratios and whether adding an extra row of holes, upstream of the first row would make a difference. For the second part, a ramp was placed upstream of the single and double row configuration to help improve cooling . All of the experiments were performed in a low speed wind-tunnel with a mainstream velocity of 8 m/s and a turbulence insity of 3.3%. Higher blowing ratios were ineffective in improving film-cooling effectiveness due to jet lift-off. Two rows of holes increased the cooling effectiveness by 200%, when compared to single row configurations at the same blowing ratio without ramps. Upstream ramps provided significant improvement in the near hole region of the injection holes.

scholarly journals Experimental Study Of Short Hole Film-Cooling

2021 ◽  
Author(s):  
Mohammed A. Gandhi
Keyword(s):  
Experimental Study ◽  
Wind Tunnel ◽  
Film Cooling ◽  
Double Row ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness ◽  
Single Row ◽  
Blowing Ratio ◽  
Lift Off ◽  
Low Speed Wind Tunnel

An experimental study was conducted to investigate the film cooling effectiveness of a few configurations of short injection holes: single row, double row and both of the preceding cases with an upstream ramp placed at two different locations. In order to perform the above study, a wind-tunnel facility was assembled to facilitate in the successful culmination of the experiments. The focus of the study was to determine the cooling provided by the short injection holes at a variety of blowing ratios and whether adding an extra row of holes, upstream of the first row would make a difference. For the second part, a ramp was placed upstream of the single and double row configuration to help improve cooling . All of the experiments were performed in a low speed wind-tunnel with a mainstream velocity of 8 m/s and a turbulence insity of 3.3%. Higher blowing ratios were ineffective in improving film-cooling effectiveness due to jet lift-off. Two rows of holes increased the cooling effectiveness by 200%, when compared to single row configurations at the same blowing ratio without ramps. Upstream ramps provided significant improvement in the near hole region of the injection holes.

A Novel Single-Passage Transonic Wind Tunnel for Turbine-Vane Film Cooling

2020 ◽  
Vol 142 (7) ◽  
Author(s):  
Mohamed Qenawy ◽  
Lin Yuan ◽  
Yingzheng Liu ◽  
Di Peng ◽  
Xin Wen ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Film Cooling ◽  
Three Dimensional ◽  
Fast Response ◽  
Low Flow ◽  
Wind Tunnels ◽  
Single Passage ◽  
Turbine Vane ◽  
Response Pressure ◽  
Transonic Wind Tunnel

Abstract Wind-tunnel testing of turbines cascade is an important technique for quantifying the realistic conditions of turbine-vane film cooling. However, the complex and expensive facilities needed for the multipassage design of such wind tunnels have prompted the introduction of the single-passage design strategy. In this contribution, detailed procedures for building a novel single-passage transonic wind-tunnel using additive manufacturing are presented. In addition, the detailed flow structure caused by the passage was investigated. The proposed design was evaluated step-by-step using an integrated model that successively comprised two-dimensional (2D) periodic passage simulation, 2D single-passage simulation, three-dimensional (3D) single-passage simulation, construction, and testing. The proposed design was found to achieve flow periodicity at transonic flow conditions with relatively low-flow consumption. The results were validated by comparison to the available literature data. In addition, an endwall-cooling configuration was successfully deployed using fast-response pressure-sensitive paint (fast-PSP). This study, combined with the help of commercial software and 3D printing, shed light upon strategies for time- and cost-reduction in linear cascade design, which could benefit the turbomachinery community.

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