112
P. L. Rupesh and Arulprakasajothi
depicted in Fig. 13. The results shown in Fig. 13 also show that the temperature has
been increased from root to tip of the blade.
6 Conclusion
The above results shown in the present work shows that the thermal paint is a powerful
technique for thermal mapping in geometry of a gas turbine blade. The experimental
results obtained in the above study reveal that the temperature contour of a blade
surface can be obtained experimentally. These results help in health monitoring of
the blade and the selection of material for blade. The creep of the blade can be
decreased based on the observation of peak temperature occurred due to irreversible
change of colour in temperature indicating paint. The experimental results also hold
in relation with the computational results.
References
1. Ganesan V (2003) Gas turbines, 2nd edn. Tata McGraw Hill Publication, New York
2. Nau P, Yin Z, Lammel O, Meier W (2018) Wall temperature measurements in gas turbine
combustors with thermographic phosphors. J Eng Gas Turbines Power 141(4)
3. Saravanamuttoo HIH, Cohen H, Rogers GFC (2001) Gas turbine theory, 5th edn. Pearson
Education Ltd, UK
4. Boyce MP (2002) Gas turbine engineering handbook, 2nd edn. Gulf Professional Publishing
Company, Houston
5. Mark CP, Selwyn A (2016) Design and analysis of annular combustion chamber of a low bypass
turbofan engine in a jet trainer aircraft. Propul Power Res 5(2):97–107
6. Rupesh PL, Prakasajothi MA, Chandrasekhar U, Mycherla R, Teja MB (2019) Study on temperature indicating paint for surface temperature measurement—a review. In: Innovative design,
analysis and development practices in aerospace and automotive engineering (I-DAD 2018),
Lecture notes in mechanical engineering
7. Cameron HE. Calibration for thermal paint chemistry. ZEIT 4500 aeronautical engineering
project, thesis and practical experience. School of Engineering & Information Technology
8. Mandavkar PS, Sawane SM, Dongre DG (2008) Study of thermal mapping for health
monitoring of gas turbine blade. Int J Res Sci Eng 1(2)
9. Lempereur C, Andral R, Prudhomme JY (2008) Surface temperature measurement on engine
components by means of irreversible thermal coatings. Meas Sci Technol 19(10):105501
10. Yang L, Zhi-Min L (2015) The research of temperature indicating paints and its application in
aero-engine temperature measurement. In: Asia-Pacific International Symposium on Aerospace
Technology (APISAT2014). Procedia Eng 99:1152–1157
11. Girish Prasad M, Ravitej M, Shanmuga Priya (2016) Thermal analysis of aero gas turbine
blade. Int J Mech Prod Eng 4(7). ISSN: 2320-2092
12. Gallardo JM, Rodriguez JA, Herrera EJ (2002) Failure of gas turbine blades. Wear 252(3–
4):264–268
13. Naeem MT, Jazayeri SA, Rezamahdi N (2008) Failure analysis of gas turbine blades. In:
Proceedings of the IAJC-IJME international conference
14. Munktell M (2008) Cooling of combustion chamber. Letebvre AH (1983) Gas turbine
combustion. Chapter 8: heat transfer
P. L. Rupesh and Arulprakasajothi
depicted in Fig. 13. The results shown in Fig. 13 also show that the temperature has
been increased from root to tip of the blade.
6 Conclusion
The above results shown in the present work shows that the thermal paint is a powerful
technique for thermal mapping in geometry of a gas turbine blade. The experimental
results obtained in the above study reveal that the temperature contour of a blade
surface can be obtained experimentally. These results help in health monitoring of
the blade and the selection of material for blade. The creep of the blade can be
decreased based on the observation of peak temperature occurred due to irreversible
change of colour in temperature indicating paint. The experimental results also hold
in relation with the computational results.
References
1. Ganesan V (2003) Gas turbines, 2nd edn. Tata McGraw Hill Publication, New York
2. Nau P, Yin Z, Lammel O, Meier W (2018) Wall temperature measurements in gas turbine
combustors with thermographic phosphors. J Eng Gas Turbines Power 141(4)
3. Saravanamuttoo HIH, Cohen H, Rogers GFC (2001) Gas turbine theory, 5th edn. Pearson
Education Ltd, UK
4. Boyce MP (2002) Gas turbine engineering handbook, 2nd edn. Gulf Professional Publishing
Company, Houston
5. Mark CP, Selwyn A (2016) Design and analysis of annular combustion chamber of a low bypass
turbofan engine in a jet trainer aircraft. Propul Power Res 5(2):97–107
6. Rupesh PL, Prakasajothi MA, Chandrasekhar U, Mycherla R, Teja MB (2019) Study on temperature indicating paint for surface temperature measurement—a review. In: Innovative design,
analysis and development practices in aerospace and automotive engineering (I-DAD 2018),
Lecture notes in mechanical engineering
7. Cameron HE. Calibration for thermal paint chemistry. ZEIT 4500 aeronautical engineering
project, thesis and practical experience. School of Engineering & Information Technology
8. Mandavkar PS, Sawane SM, Dongre DG (2008) Study of thermal mapping for health
monitoring of gas turbine blade. Int J Res Sci Eng 1(2)
9. Lempereur C, Andral R, Prudhomme JY (2008) Surface temperature measurement on engine
components by means of irreversible thermal coatings. Meas Sci Technol 19(10):105501
10. Yang L, Zhi-Min L (2015) The research of temperature indicating paints and its application in
aero-engine temperature measurement. In: Asia-Pacific International Symposium on Aerospace
Technology (APISAT2014). Procedia Eng 99:1152–1157
11. Girish Prasad M, Ravitej M, Shanmuga Priya (2016) Thermal analysis of aero gas turbine
blade. Int J Mech Prod Eng 4(7). ISSN: 2320-2092
12. Gallardo JM, Rodriguez JA, Herrera EJ (2002) Failure of gas turbine blades. Wear 252(3–
4):264–268
13. Naeem MT, Jazayeri SA, Rezamahdi N (2008) Failure analysis of gas turbine blades. In:
Proceedings of the IAJC-IJME international conference
14. Munktell M (2008) Cooling of combustion chamber. Letebvre AH (1983) Gas turbine
combustion. Chapter 8: heat transfer