АННОТАЦИЯ Рассмотрены результаты расчётно-конструкторских разработок и численных исследований вход-ного патрубка с первой ступенью и отсека первых трёх ступеней с учётом отбора пара, протечек через диафраг-менные, надбандажные уплотнения и разгрузочные отверстия в дисках ЦНД турбины К-1250-6,9/25 ²TURBOATOM². Some methodological aspects and the results of improving of studied facilities by numerical experiment by MTFS® code are discussed. It is shown that the main total pressure loss in inlet pipe arises in collector and in place of its connection with tube. The improvement of inlet pipe annular collector due to the profiled sheets and input tube knee reduces the internal loss coefficient in 2 times. The axial length of the radial-axial outlet channel increase and the height of the splitter reduction almost no effect on the internal losses, but significantly (by 45%) reduce the coefficient of circumferential nonuniformity of static pressure at the stage inlet. Based on the item-evaluation of the effectiveness the final version of the inlet (M7) is developed. It is revealed that the inlet flow angles on the nozzle edges in the left

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UDK 621.43.056 MASOUD HAJIVAND, PhD student of Aircraft engines design Department, National aerospace university named after N.Y. Zhukovsky «KhAI», Kharkov CFD MODELING OF KEROSENE COMBUSTION WITH VARIOUS INITIAL CONDITIONS AND FUEL DROPLET DIAMETERS This paper presents the numerical models for the analysis of combustor fuel spray, characteristics, in various injection conditions in a can type of combustor with a double stage radial swirler. Spray consists of two fundamental and consecutive steps, means the primary breakup and the secondary breakup. The primary breakup is modeled by Linearized Instability Sheet Atomization (LISA) which are mostly used in a pressure swirl atomizers. Secondary breakup is modeled by Taylor analogy breakup model (TAB). The trajectory and velocity of generated fuel droplets is determined by Lagrangian Particle Tracking. Characteristics of jet breakup, depends on a variety of factors such as turbulence, injection pressure drop, velocity profiles, nozzle geometry, and the physical state of the liquid fuel. In this paper Jet-A aviation fuel (kerosene), modeled as a two-component surrogate fuel (by mass 60 % C10H22 and 40 % C9H12). The standard k-ε model with the enhanced wall treatment and the Euler-Lagrange method were employed for the simulation of the turbulence and spray. All results of the simulation in this paper are analyzing in 3 various injection conditions and one of these cases was chosen and implemented in a real annular combustion chamber of a gas turbine. A PDF Flamelet model was employed to simulate combustion process.

Построена численная модель и выполнено численное исследование аэродинамических и энергетических характеристик выхлопного отсека ЦНД мощной паровой турбины, включающего последнюю ступень с предвключенным межступенчатым зазором, выхлопной патрубок, камеру влагоудаления, переходной патрубок. В качестве рабочего тела использован влажный пар с табличными параметрами. Обсуждается влияние надбандажной протечки в последней ступени, инжекции влажного пара через щель обечайки диффузора Ключевые слова: последняя ступень ЦНД, система влагоудаления, осерадиальный диффузор, выхлопной патрубок, влажный пар, численное моделирование, аэродинамические, энергетические характеристики.