Verification of mathematical model of transonic axial compressor stage

The research presents the results of verification and validation of the mathematical model of the flow path transonic model NASA Stage 37 axial compressor using the data of the experiment conducted by NASA in the 1970s. The work presents the sequence of constructing a mathematical model of the flow path, as well as geometric models of the blade units. The mathematical model of the impeller blades is constructed based on the geometry of the blade airfoil obtained from the results of calculating the stress-strain state using the finite element method. When calculating the stress-strain state of the blade, the effect of gas-dynamic loads and centrifugal forces is considered. For gas-dynamic calculations, a study is conducted on grid independence with a description of the calculation method for the first near-wall layer and a justification for the choice of the turbulence model. A numerical study of the viscous gas flow in the flow path of the model stage is carried out considering the distribution of flow parameters and the position of the measurement control points according to the NASA report. As a result of numerical studies, gas-dynamic characteristics of the stage are constructed, and the distribution of flow parameters in the calculated sections along the height of the flow part is investigated. The obtained gas-dynamic characteristics based on the developed mathematical model quantitatively and qualitatively correspond to the results of NASA gas-dynamic tests. The obtained model can be used for further optimization or other calculations using the finite element method.

1. Inozemtsev A. A., Sandratskiy V. L. Gazoturbinnyye dvigateli [Gas turbine engines]. Perm, 2006. 1202 p. (In Russ.).

2. Tsanev S. V., Burov V. D., Remezov A. N. Gazoturbinnyye i parogazovyye ustanovki teplovykh elektrostantsiy [Gas turbine and combined cycle plants of thermal power plants] / Ed. by S. V. Tsanev. Moscow, 2002. 584 p. (In Russ.).

3. Zysin L. V. Parogazovyye i gazoturbinnyye teplovyye elektrostantsii [Combined-cycle and gas turbine thermal power plants]. Saint Petersburg, 2010. 368 p. (In Russ.).

4. Reid L., Moore R. D. Design and overall performance of four highly loaded, high speed inlet stages for an advanced highpressure-ratio core compressor. NASA Technical. Paper 1337. 1978. 132 p.

5. Reid L., Moore R. D. Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.,26, respectively, and with design pressure ratio of 1.82. NASA Technical. Paper 1338. 1978. 105 p.

6. Reid L., Moore R. D. Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.78, respectively, and with design pressure ratio of 1.82. NASA Technical. Paper 1974. 1982. 115 p.

7. Reid L., Moore R. D. Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ratio of 2.05. NASA Technical. Paper 1659. 1980. 105 p.

8. Reid L., Moore R. D. Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.77, respectively, and with design pressure ratio of 2.05. NASA Technical. Paper 2001. 1982. 117 p.

9. Dunham J. CFD validation for propulsion system components (la validation CFD des organes des propulseurs), Tech. rep., Advisory Group for Aerospace Research and Development (AGARD), Neuilly-sur-Seine (France). AGARD Advisory. Repot 355. 1998. 100 p.

10. Xiang J., Schlüter J., Duan F. CFD Validation and analysis of a single-stage axial compressor. Applied Mechanics and Materials. 2014. Vol. 629. P. 109–118. DOI: 10.4028/www.scientific.net/AMM.629.109.

11. Blinov V. L., Zubkov I. S. Verifikatsiya raschлtnoy modeli transzvukovoy stupeni dlya resheniya zadach ucheta vliyaniya erozionnogo iznosa na rabotu osevogo kompressora [Verification of a transonic stage cfd model for assessing the erosion wear influence on the operation of the axial compressor]. Vestnik Samarskogo universiteta. Aerokosmicheskaya tekhnika, tekhnologii i mashinostroyeniye. Vestnik of Samara University. Aerospace and Mechanical Engineering. 2023. Vol. 22, no. 1. P. 51–62. DOI: 10.18287/2541-7533-2023-22-1-51-62. EDN: BMAYGI. (In Russ.).

12. Vani A., Dr. Manjunath S. V., Dr. Basawaraj [et al.]. Aerodynamic design, analysis and optimization of transonic axial compressor blade with the combination of NACA 65, Double Circular Arc (DCA) and Multiple Circular Arc Airfoil (MCA). Tuijin Jishu/Journal of Propulsion Technology. 2023. Vol. 44, no. 4. DOI: 10.52783/tjjpt.v44.i4.4328.

13. Morris A. L., Halle J. E., Kennedy E. High-loading, 1800 ft/sec tip speed transonic compressor fan stage I. Aerodynamic and mechanical design. NASA CR-120907. 1972. 104 p.

14. Nagai K., Ikesawa K., Sugimoto T. [et al.]. Design and development of a two stage transonic axial flow compressor. ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. Paper 96-GT-059, V001T01A015. 8 p. DOI: 10.1115/96-GT-059.

15. Crouse J. E., Janetzke D. C., Schwirian R. E. A computer program for composing compressor blading from simulated circular-arc elements on conical surfaces. NASA TN D-5437. 1969. 85 p.

16. Piollet E., Nyssen F., Batailly A. Blade/casing rubbing interactions in aircraft engines: Numerical benchmark and design guidelines based on NASA rotor 37. Journal of Sound and Vibration. 2019. Vol. 460. P. 114878. DOI: 10.1016/j.jsv.2019.114878.

17. Langley Research Center, Design study of advanced model support systems for the national transonic facility, Tech. rep. NASA. Document ID 19870010864. 1987.

18. Hall А. M., Slunder C. The metallurgy, behavior, and application of the 18-percent nickel maraging steels. Tech. rep. Battelle Memorial Inst. Columbus OH Columbus Labs. Document ID 19690004861. 1968.

19. Wagner J. A. Correlation of mechanical properties with metallurgical structure for 18Ni 200 grade maraging steel at room and cryogenic temperatures. Cryogenics. 1991. Vol. 31, Issue 9. P. 780–785. DOI: 10.1016/0011-2275(91)90134-i.

20. Zolotukhin A. S., Marenina L. N. Verifikatsiya metodiki postanovki CFD-issledovaniy osevoy kompressornoy stupeni na primere NASA Stage 37 v programmnom komplekse ANSYS CFX [Verification of the methodology of CFD studies of axial compressor stage on the example of NASA Stage 37 in the ANSYS CFX software package]. Energoeffektivnyye Inzhenernyye Sistemy, Tekhnologii SPG, Vodorodnaya Energetika. Saint Petersburg, 2023. P. 114–115. EDN: GOXMAG. (In Russ.).

21. David C. Wilcox turbulence modeling for CFD. California, DCW Industries, Inc., 2006. 536 p.

22. Spalart P. R., Allmares S. R. A one-equation turbulence model for aerodynamic flows. AIAA. 1992. Vol. 439. DOI: 10.2514/6.1992-439.

23. Menter F. R. Zonal two equation k-ω turbulence models for aerodynamic flows. AIAA. 1993. URL: https://core.ac.uk/download/pdf/42776707.pdf (accessed: 14.11.2024).

24. Menter F. R., Kuntz M., Langtry R. Ten years of industrial experience with the SST turbulence model. Heat and Mass Transfer 4 / Eds.: K. Hajalic, Y. Nogano, M. Tummers. Begell House, Inc. 2003, 8 p.