Simulations of hot-gas flow in internally cooled cascade of turbine vanes

• Autorzy: Sznajder Janusz

Identyfikatory

DOI

10.2478/kones-2019-0044

• Języki publikacji: EN

Abstrakty

EN

An experiment in cooling of gas turbine nozzle guide vanes was modelled numerically with a conjugate viscousflow and solid-material heat conduction solver. The nozzle vanes were arranged in a cascade and operated in highpressure, hot-temperature conditions, typical for first turbine stage in a flow of controlled-intensity, artificiallygenerated turbulence. The vane cooling was internal, accomplished by 10 channels in each vane with cooling-air flow. Numerical simulations of the experiment were conducted applying two turbulence models of the k-omega family: k-omega-SST and Transition SST implemented in the ANSYS Fluent solver. Boundary conditions for the simulations were set based on conditions of experiment: total pressures and total temperature on inlet to cascade, static pressure on the outlet of the cascade and heat flux on the surface of cooling channels. The values of heat flux on the surface of cooling channels were evaluated based on Nusselt numbers obtained from experiment and varied in time until steadystate conditions were obtained. Two test cases, one with subcritical outlet flow, and another one, with supercritical outlet flow were simulated. The result of experiment – distributions of pressure, surface temperature, and heat transfer coefficients on the vane external surface were compared to results of numerical simulations. Sensitivity of the vane surface temperatures and heat transfer coefficients to turbulence models and to boundary-condition values of parameters of turbulence models: turbulence energy and specific dissipation of turbulence energy was also studied.

Słowa kluczowe

EN

aircraft engines; mechanical engineering; engine parts; simulation and modelling

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2019
• Tom: Vol. 26, No. 2
• Strony: 151--158
• Opis fizyczny: Bibliogr. 4 poz., rys.

Twórcy

autor

Sznajder Janusz

• Łukasiewicz Research Network – Institute of Aviation, Department of Aerodynamics Krakowska Av. 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 492, fax: [phone]

Bibliografia

• [1] Hylton, L., Mihelc, M. S., Turner, E. R., Nealy, D. A., York, R. E., Analytical and Experimental Evaluation of the Heat Transfer Distribution over the Surfaces of Turbine Vanes, Detroit Diesel Allison, Division of General Motors Corporation, Contract NAS 3-22761, May 1983.
• [2] Craig, H. R, Cox, H. J. A., Performance Estimation of Axial Flow Turbines, Proc. Instn. Mech. Engrs., Vol. 185, 32/71, pp. 407-424, 1970-71.
• [3] Back da Trinidade, D., Bugała, P., Simone, D., Review of Loss Models for High Pressure Turbines, Journal of KONES Powertrain and Transport, Vol. 25, No. 2, pp. 38-44 2018.
• [4] ANSYS Documentation, available at https://ansyshelp.ansys.com.

Uwagi

Opracowanie rekordu w ramach umowy 509/P-DUN/2018 ze środków MNiSW przeznaczonych na działalność upowszechniającą naukę (2019).