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• W2321306952 abstract "Intermediate casing (1C) duct is an axi-symmetric annular duct with contoured walls that connect the low pressure and the high-pressure compressors. It plays a vital role in the bifurcation of the fan flow that enters a typical turbofan engine. It divides the flow into three, viz.; the by-pass, the core and the cooling flow. The cooling flow passage is formed by eight holes that are plunged on the inner casing of 1C duct. The flow in the complex geometry of the 1C duct is analysed in a 180° sector using the general-purpose CFD code PHOENICS. The results are compared with the experimental data obtained from the engine. The flow features are depicted by Mach number distribution, total pressure losses and mass flows distribution is estimated from the CFD results. INTRODUCTION Intercasing duct plays an important role to divide the flow into by-pass and core flow by the help of splitter in a typical turbo fan engine where the fan and the gas generator compressors are aerodynamically coupled. The two compressors are held in position via few struts. The core flow enters into the engine core compressor and the bypass flow enters the outer annular duct formed by the casing of the core engine and the outer casing of the turbo-fan engine. Many investigators have studied the flow analysis of the 1C duct. O'Brien has developed a methodology to calculate the flow field varying in circumference in an axial flow fan with downstream stater guide-vanes and casing support struts* A time marcMug solution for the rotor is coupied to a potential flow solution for down stream flow in the vane and strut regions*. Ng 2 has studied tjte effect of the strut on the unsteady pressure fields on the rotor Wades. The unsteady effect exceeds due to the stMor/rotor/stnit spacing bet falls off rapidly as struts are moved downstream. CMang et al developed a response prediction system to model the rotor Made response due to the pressure distribution from the down stream stator vanes and struts. Qingliang has modeled part-span steeud and engine splitter by a 3-D viscous auineiical scheme. The * Scientists, CFD groisp Copy right © 2001 The American Institute of Aeronautics and Astronautics Inc. All rights reserved. numerical results are compared with the experimental data obtained from the three-stage compressor rig. It is concluded that such analysis is required to obtain a favourable inlet condition to the compressor. In the present paper, the flow in the 1C duct alone has been studied using a general-purpose code PHOENICS. The analysis shows that the general flow phenomena have been captured well. INTERMEDIATE CASING DUCT A typical inter casing duct has a s-shape configuration where eight symmetric struts are located in the circumference at 36° apart. The splitter ring is located at a distance of 40% from the inlet plane of the 1C duct. The cooling holes are plunged on the hub casing of the core duct and are located at 45% from the splitter inlet plane. The circumferential view of the 1C duct shows the strut position along with the core and the bypass duct annulus in Figure 1. The 1C duct is a complex geometry with one inlet and three outlets. In the present paper, the flow has been modeled for a 180° sector to study the effect of splitter and the struts along with the cooling holes. The sectors AOB, BOC, COD and DOE consist of one, two, one and no cooling holes on the inner casing of the core duct. 1 American Institute of Aeronautics and Astronautics c)2001 American Institute of Aeronautics & Astronautics or Published with Permission of Author(s) and/or Author(s)' Sponsoring Organization. INSTRUMENTATION The 1C duct of the turbo-fan is instrumented by two total pressure and two total temperature rakes at inlet and outlet plane. The wall static pressures are measured at three different locations. NUMERICAL METHOD The steady, 3-Dimensional Navier-Stokes equations with K.-Z turbulence model of PHOENICS computer code is used for the analysis of the 1C duct. Governing Equations The governing equations for the mass, momentum, energy, turbulent kinetic energy and its dissipation are written in the conservative form as Div(pu(/> -Fjgrad ) = Sj .. (1) dt where, any conserved property T^ exchange coefficient of 84, source term The expressions for ((>, 1 and 84, are shown in Table 1: Table 1. * 1 U V w H" @default.
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• W2321306952 date "2001-07-08" @default.
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• W2321306952 title "Flow prediction in the intermediate casing of compressors" @default.
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• W2321306952 doi "https://doi.org/10.2514/6.2001-3619" @default.
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