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Aerodynamic and heat transfer performances of a highly loaded transonic turbine rotor with upstream generic rim seal cavity

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Propulsion and Power Research 2021年第4期10卷 317-331页

作者： Zakaria Mansouri Faculty of Engineering The University of NottinghamNottinghamUnited Kingdom abylsen sciences&technologies rhône-alpes Grenoble38000France

In turbine disk cavity,rim seals are fitted between the stator and its adjacent rotor disk.A coolant air injected through the turbine disk cavity to prevent the ingress of mainstream hot *** purpose of this paper is to investigate numerically the effect of the upstream purge flow on the aero and thermal performances of a high pressure turbine *** investigations are conducted on a generic rim seal cavity inspired from a realistic turbofan *** purge fractions(PF)equal to 0.2%,0.5%,1.0%and 1.5%of the mainstream are *** simulations are done by solving the three-dimensional Reynolds averaged Navier-Stokes and energy transport *** results include the effect of the PF on the cooling effectiveness,the sealing effectiveness,the secondary flows with losses and the heat transfer behavior,within the cavity and across the rotor *** low PF of 0.2%provided a low cooling effectiveness,a moderate sealing effectiveness and minimum *** high PF of 1.5%gave a high cooling effectiveness,a best sealing effectiveness and maximum *** medium PF of 1.0%supplied a compromise between the aerodynamic and thermal design needs with good cooling and sealing efficiencies and a tolerable level of losses.

关键词： Axial turbine Thermal characteristics Aerodynamic losses Generic cavity Purge flow Rim seal Numerical simulation

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The influence of inlet swirl intensity and hot-streak on aerodynamics and thermal characteristics of a high pressure turbine vane

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Chinese Journal of Aeronautics 2021年第11期34卷 66-78页

作者： Zakaria MANSOURI Riyadh BELAMADI abylsen Science&Technology rhone alpes Grenoble 38000France Ecole Superieure de technologies Industrielles(ESTI) Annaba 23000Algeria

In modern gas turbines,the High Pressure Turbine(HPT)is exposed to an extreme thermal environment due to the burned gases leaving the *** burned gases are characterized by flow and temperature distortions that effect the aerodynamics and heat transfer of the *** purpose of this paper is to investigate numerically the effect of the intensity of the swirling flow combined with the temperature non-uniformity‘‘Hot-Streak"(H-S)on the aerothermal performances of a HPT Nozzle Guide Vane(NGV).The investigations are conducted on the solid untwisted NGV annular cascade developed in NASA Lewis Research *** swirl intensities(|S_(n)|=0,0.1,0.25 and 0.5),two swirl orientations(positive and negative)and two hot-streaks(rounded and radial)at the NGV inlet are *** simulations are done by solving the Reynolds Averaged Navier-Stokes(RANS)equations using ANSYS-CFX *** results show that the H-S with swirl undergoes twisting following the orientation of the *** H-S twist is aggressive under positive swirl compared to the negative swirl *** inlet swirl generates a new secondary flow structure,so called Swirl Vortex(SV),which induces more aerodynamic *** aerodynamic efficiency under negative swirl found to be higher than that under positive *** maximum temperature on the vane surface is controlled by the radial transport of the SV towards the endwalls.

关键词： Aerodynamics Heat transfer Hot-Streak HP turbine NGV Swirl intensity

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