Development of Approach to Detecting Cracks in the Aviation Ggas Turbine Engine Blades in the Operation Modes

Abstract

The paper proposes an approach to detecting cracks that appear in the gas turbine blades during the aircraft engine operation. According to the research hypothesis, the proposed system consists of capsules with a substance exhibiting the ionizing properties at high temperatures, which are positioned in the blade body during its design. During the crack development and opening in the capsule area, the ionizing substance is released due to the pressure difference outside and inside the capsule into the turbine flow part, where it is registered because of a current jump with the substance hitting the sensors. Part of this study was devoted to considering and solving the model problems to assess possibilities of implementing the proposed approach using the example of a cylindrical shell with the precreated rectangular cutout, where a thin-walled capsule was positioned. A bench was created to conduct the experimental research; it was equipped with a signal monitoring system to detect the active substance operating at temperatures corresponding to the gas turbine engines. Alkaline solutions of different concentrations were experimentally studied to identify those most promising ones and use them as the ionizing substance. Possibilities were found to create pressure inside a thin-walled capsule sufficient to destroy its shell following acceptable restrictions on its thickness. Based on a series of numerical and full-scale experiments, influence of the width of the created cutout in a thick-walled shell and the thickness of the shell of a thin-walled capsule on the pressure level in it required for its destruction was studied

The work was supported by the Russian Science Foundation Grant no. 22-79-10114 "Development of a system for diagnosing damage to turbine blades and a method for optimizing heat removal under thermal fatigue conditions"

Please cite this article in English as:

Andrianov I.K., Grinkrug M.S., Kara Balli M. Development of approach to detecting cracks in the aviation gas turbine engine blades in the operation modes. Herald of the Bauman Moscow State Technical University, Series Mechanical Engineering, 2024, no. 1 (148), pp. 4--20 (in Russ.). EDN: AOJTEO

References

[1] Komov A.A. Aircraft landing gear scheme and engine protection. Vestnik MAI [Aerospace MAI Journal], 2022, vol. 29, no. 1, pp. 7--18 (in Russ.).DOI: https://doi.org/10.34759/vst-2022-1-7-18

[2] Grinkrug M.S., Kara Balli M., Tkacheva J.I., et al. Experimental study for choosing an active substance in a microcracks detection system in the turbine blade. IOP Conf. Ser.: Mater. Sc. Eng., 2021, vol. 1111, art. 012020. DOI: http://dx.doi.org/10.1088/1757-899X/1111/1/012020

[3] Ignatovich S.R., Menou A., Karuskevich M.V., et al. Fatigue damage and sensor development for aircraft structural health monitoring. Theor. Appl. Fract. Mech., 2013, vol. 65, pp. 23--27. DOI: https://doi.org/10.1016/j.tafmec.2013.05.004

[4] Sirotin N.N., Nguen T.Sh. Numerical simulation technique for working blades operational damages of turbojet low-pressure compressor rotor. Vestnik MAI [Aerospace MAI Journal], 2021, vol. 28, no. 4, pp. 131--150 (in Russ.). DOI: https://doi.org/10.34759/vst-2021-4-131-150

[5] Szczepankowski A., Szymczak J. Initiation of damage to the hot part of aircraft turbine engines. Research Works of AFIT, 2016, vol. 38, no. 1, pp. 61--74.

[6] Zhang Z., Yang G., Hu K. Prediction of fatigue crack growth in gas turbine engine blades using acoustic emission. Sensors, 2018, vol. 18, no. 5, art. 1321. DOI: https://doi.org/10.3390/s18051321

[7] Nguen Ngok T., Kolenko G.S. Analysis of the fracture mechanics and workability of a gas turbine blade in the presence of a crack. Materialovedenie. Energetika [Materials Science. Power Engineering], 2020, vol. 26, no. 3, pp. 56--69 (in Russ.). DOI: https://doi.org/10.18721/JEST.26304

[8] Feng J., Geng R., Wu G., et al. AE characteristic analysis in aircraft fatigue test under flight loading condition. J. Mech. Eng., 2010, vol. 46, no. 8, pp. 6--11.

[9] Geng Н., Zhou X., Yang B., et al. Design and simulation of gas turbine blade fatigue testing rig driven by electric magnet. IEEE ICMA, 2017, pp. 2034--2038. DOI: https://doi.org/10.1109/ICMA.2017.8016131

[10] Semenov A.S., Grishchenko A.I., Kolotnikov M.E., et al. Finite-element analysis of thermal fatigue of gas turbineblades. Part 1. Material models, failure criteria, parameter identification. Vestnik USATU, 2019, vol. 23, no. 1, pp. 70--81 (in Russ.).

[11] Maskaykin V.A., Makhrov V.P. Thermal conductivity research of the aircraft heat-insulating skin under flight conditions. Vestnik MAI [Aerospace MAI Journal], 2021, vol. 28, no. 4, pp. 118--130 (in Russ.). DOI: https://doi.org/10.34759/vst-2021-4-118-130

[12] Beghinia M., Bertinia L., Santusa C., et al. High temperature fatigue testing of gas turbine blades. Procedia Struct. Integr., 2017, vol. 7, pp. 206--213. DOI: https://doi.org/10.1016/j.prostr.2017.11.079

[13] Kortikov N.N. Uncertainties in modeling the thermal state of cooled gas turbine blade. Nauchno-tekhnicheskie vedomosti SPbGPU. Estestvennye i inzhenernye nauki [St. Petersburg Polytechnical University. Journal of Engineering Sciences and Technology], 2019, vol. 25, no. 4, pp. 31--41 (in Russ.). DOI: https://doi.org/10.18721/JEST.25403

[14] Li B., Fan X., Li D., et al. Design of thermal barrier coatings thickness for gas turbine blade based on finite element analysis. Math. Probl. Eng., 2017, vol. 3, art. 147830. DOI: https://doi.org/10.1155/2017/2147830

[15] Andrianov I.K., Grinkrug M.S., Vakuluk A.A. Numerical calculation of the heat sink parameters of the shell turbine vanes at the modeling of the heat-protective coating with a different number of layers. Current problems and ways of industry development: equipment and technologies, 2021, vol. 200, pp. 37--46. DOI: https://doi.org/10.1007/978-3-030-69421-0_5

[16] Vikulin A.V., Yaroslavtsev N.L., Zemlyanaya V.A. Estimation of efficiency of the cooling channel of the nozzle blade of gas-turbine engines. Therm. Eng., 2018, vol. 65, no. 2, pp. 88--92. DOI: https://doi.org/10.1134/S0040601517120102

[17] Solovyev M.S. Review of engineering measures to improve efficiency of film cooling of high-temperature gas turbine blades of advanced aircraft GTE. Vestnik RGATA imeni P.A. Solovyeva [Vestnik of P.A. Solovyov Rybinsk State Aviation Technical University], 2021, no. 4 (59), pp. 30--36 (in Russ.).

[18] Kvasha Yu.A., Zinevych N.A., Petrushenko N.V. Features of blade shape variation in the aerodynamic improvement of aircraft gas-turbine engine compressors. Tech. Mech., 2022, vol. 2, no. 2, pp. 17--24. DOI: https://doi.org/10.15407/itm2022.02.017

[19] Lepeshkin A., Remchukov S., Yaroslavtsev N., et al. Test technique for turbine cooled blades of gas turbine engines. J. Phys.: Conf. Ser., 2021, vol. 1925, art. 012086. DOI: https://doi.org/10.1088/1742-6596/1925/1/012086

[20] Cheng J., Dong Z., Zhao S., et al. Research on aerodynamic optimization method of multistage axial compressor under multiple working conditions based on phased parameterization strategy. Math. Probl. Eng., 2021, vol. 1. DOI: https://doi.org/10.1155/2021/5518507

[21] Birger I.A., Shorr B.F., Iosilevich G.B. Raschet na prochnost detaley mashin [Strength analysis of machine parts]. Moscow, Mashinostroenie Publ., 1993.