UNSTEADY TWO-PHASE GAS-PARTICLE FLOWS IN BLADE CASCADES
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eady Two-Phase Gas-Particle Flows in Blade Cascades D. A. Romanyuka,* and Yu. M. Tsirkunova,** a
Ustinov Baltic State Technical University “Voenmech”, St. Petersburg, Russia *e-mail: [email protected] **e-mail: [email protected] Received January 16, 2020; revised February 8, 2020; accepted March 12, 2020
Abstract—Unsteady flows of a gas with solid particles in a system of two plane “rotor–stator” cascades are investigated. The carrier-gas flow is modeled using the Navier–Stokes equations (pseudo DNS approach) and, for comparison, the Reynolds equations (URANS approach) with the Menter SST k–ω model of turbulence. In both cases, the equations are solved using a second-order finitevolume method. In the absence of particle collisions, the admixture motion is modeled using a Lagrangian approach and the colliding particles are modeled by the Monte Carlo method. The feedback effect of the particles on the carrier gas flow is taken into account. The influence of different factors of random nature (particle distribution over sizes, particle scattering after collisions with the blades, particle–particle collisions) on the admixture flow pattern and particle concentration profiles at the outlet of the stator cascade is analyzed. Key words: two-phase gas-particle flow, Lagrangian method, Monte Carlo method, particle distribution over sizes, scattering of rebounding particles, numerical modeling DOI: 10.1134/S0015462820050122
1. INTRODUCTION In the flight of an aircraft with a gas-turbine engine through a dusty atmosphere, the dispersed particles can be ingested in the intake and result in erosion of the compressor blades and other elements of the duct. In the recent literature [1–5], a large attention has been paid to modeling the admixture flow, particle interactions with compressor blades, and predicting the reduction in the engine life due to the erosion. Of a significant danger is the aircraft flight through volcanic ash clouds [6]. Predicting the behavior of particles in the flow over the aircraft, in the compressor, and in the subsequent elements of the gas-turbine engine duct requires the development of adequate mathematical models of two-phase flows. The main difficulties are associated with modeling the effects of random nature, such as particle-particle collisions, scattering of non-spherical particles rebounded from the solid surfaces, particle distribution over sizes, random positions of the particles in the free stream, etc. These effects were discussed only in a few publications. In [7], a kinetic model was proposed for describing the dynamics of colliding particles in the known flow field of the carrier gas. Later, a continual-kinetic model of gas-particle mixture was developed [8], in which the carrier gas was described as a continuum and the particles were treated as a discrete medium. This model took into account the particle-particle collisions and the feedback effect of the particles on the carrier-gas flow. Particle-wall collisions of non-spherical particles were considered in [9–11]. An important
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