Conjugate heat transfer analysis of a radially cooled nozzle guide vane in an aero gas turbine engine-Reference-Cited by-同舟云学术

Conjugate heat transfer analysis of a radially cooled nozzle guide vane in an aero gas turbine engine

Published:2020-10-08 Issue:0 Volume:0 Page:
ISSN:0334-0082
Container-title:International Journal of Turbo & Jet-Engines
language:en
Short-container-title:

Author:

Arunkumar G. L.¹,Shetty Balachandra P.¹,Mishra R. K.²

Affiliation:

1. Department of Mechanical Engineering , Nitte Meenakshi Institute of Technology , Bangalore , India

2. Regional Centre for Military Airworthiness , Bangalore , India

Abstract

Abstract This paper presents a computational method to investigate cooling performance of NASA-C3X cascade vane coated with thermal barrier coating (TBC), for which experimental data are available. The vane was cooled internally by air flows through radially oriented 10 channels. A three-dimensional conjugate heat transfer simulation has been performed which allows the conduction-convection on metal vane by eliminating need of multiple boundary solutions. The predicted aerodynamic and thermal loads with the effect of turbulent intensity is found to be good agreement with experimental data and inclusion of TBC leads to quantitative reduction in vane metal temperature.

Publisher

Walter de Gruyter GmbH

Subject

Aerospace Engineering

Link

https://www.degruyter.com/document/doi/10.1515/tjj-2020-0031/pdf

Reference33 articles.

1. Beniaiche, A, Ghenaiet, A, Carcasci, C, Facchini, B. Heat transfer investigation in new cooling schemes of a stationary blade trailing edge. Appl Therm Eng 2015;87:816–25. https://doi.org/10.1016/j.applthermaleng.2015.05.001.

2. Han, J-C, Dutta, S, Srinath, E. Gas turbine heat transfer and cooling technology Boca Raton, Florida, USA: CRC Press; 2012.

3. Sankar, V, Ramkumar, PB, Sebastian, D, Joseph, D, Jose, J, Kurian, A. Optimized thermal barrier coating for gas turbine blades. Mater Today Proc 2019;11:912–9. https://doi.org/10.1016/j.matpr.2018.12.018.

4. Reghu, VR, Shankar, V, Ramaswamy, P. Assessment of thermal barrier effects across 8% Y2O3-ZrO2 coatings on Al-Si substrates via electrical heating source. In: AIP conference proceedings. AIP Publishing LLC, Maryland, USA; 2019, vol 2166, 020016 p.

5. Hour, J, Wicks, BJ, Antoniou, RA. An investigation of fatigue failures of turbine blades in a gas turbine engine by mechanical analysis. J Eng Fail Anal 2002;9:201–11. https://doi.org/10.1016/s1350-6307(01)00005-x.

Cited by 1 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Assessment of performance degradation of a mixed flow low bypass turbofan engine through GasTurb simulation;International Journal of Turbo & Jet-Engines;2023-08-03