Abstract

The scope of this work was to develop a technique based on the regression method and apply it on a real cooled geometry for measuring its internal heat transfer distribution. The proposed methodology is based upon an already available literature approach. For implementation of the methodology, the geometry is initially heated to a known steady temperature, followed by thermal transient, induced by injection of ambient air to its internal cooling system. During the thermal transient, external surface temperature of the geometry is recorded with the help of infrared camera. Then, a numerical procedure based upon a series of transient finite element analyses of the geometry is applied by using the obtained experimental data. The total test duration is divided into time steps, during which the heat flux on the internal surface is iteratively updated to target the measured external surface temperature. The final procured heat flux and internal surface temperature data of each time step is used to find the convective heat transfer coefficient via linear regression. This methodology is successfully implemented on three geometries: a circular duct, a blade with U-bend internal channel, and a cooled high pressure vane of real engine, with the help of a test rig developed at the University of Florence, Italy. The results are compared with the ones retrieved with similar approach available in the open literature, and the pros and cons of both methodologies are discussed in detail for each geometry.

Highlights

  • Gas turbine efficiency and power output is limited by the extreme temperature encountered in the high-pressure turbine

  • IR technique is recommended for studying a complex 3D geometry operating in high temperature environments because of its ability to handle larger temperature range and low sensitivity to the viewing angle [17], given that the geometry measuring surface is properly treated

  • In the central part of the leading edge (LE) region, both methods provide similar results with local difference not exceeding 15%, while larger discrepancies are observed towards the TE, with local difference continuously increasing up to value of 100%

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Summary

Background

Gas turbine efficiency and power output is limited by the extreme temperature encountered in the high-pressure turbine. At the Oxford turbine research facility, a combustor swirl simulator (at engine scale) was designed for studying the influence of the swirl on the higher pressure turbine stage [7] This approach has strong limitations faced by many authors, in terms of smaller size of the component, difficulty in accessing the inner surface of the geometry, and higher conductivity of the material, which smooths the temperature patterns related to the internal heat transfer distributions. The authors considered a constant coolant temperature in this case but suggested to use a proper fluid model to evaluate local time-varying flow temperature for more complex geometries This technique was further used for assessing the flow feature of film holes by comparing the obtained results with a standard [13]. This work fits with this research trend, since it presents the development and implementation of a procedure to measure heat transfer distribution of real geometries

Proposed Methodology
Experimental Part
Test Rig
Experimental Procedure Steps
Data Postprocessing
Finite Element Analysis Part
Circular Duct
Mockup of Gas Turbine Blade
High Pressure Vane
Findings
Conclusions
Full Text
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