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Numerical investigation of the interaction between upstream cavity purge flow and main flow in low aspect ratio turbine cascade

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Chinese Journal of Aeronautics 2013年第1期26卷 85-93页

作者： Jia Wei Liu Huoxing National Key Laboratory of Science and Technology on Aero-Engines Aero-Thermodynamics School of Energy and Power Engineering Beihang University

In modern gas turbines, rim seal located between the stator-disc and rotor-disc is used to prevent hot-gas ingestion into the inner stage-gap of high pressure turbine. However, the purge flow supplied to the cavity through the rim seal interacts with the main flow, producing additional aerodynamic loss due to the mixing process which plays a significant role in the formation, development and evolution of downstream secondary flow. In this paper, a set of cascade representative of low aspect ratio turbine is selected to numerically investigate the influence of upstream cavity purge flow on the hub secondary flow structure and aerodynamic loss. Cascade with/without upstream cavity and four different purge mass flow rates are all taken into account in this simulation. Then, a deep insight into the loss mechanism of interaction between purge flow and main flow is gained. The results show that the presence of cavity and purge flow has a significant impact on the main flow which not only changes the vortex structure in both the passage and upstream cavity, but also alters the cascade exit flow angle distribution along the spanwise. Moreover, aerodynamic loss in the cascade rises with the increase of purge flow rate while the sealing effect is also enhanced. Therefore, the effect of upstream cavity purge flow must be considered in the process of turbine aerodynamic design. What is more, it is necessary to minimize the purge flow rate in order to reduce aerodynamic loss on the premise of satisfying cooling requirements.

关键词： Aerodynamic loss Low aspect ratio purge flow Turbine Upstream cavity

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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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