가스터빈 연소기 출구 열·유동장 분포가 터빈에 미치는 효과의 수치해석 연구

Abstract

Effects of temperature and flow fields at a combustor outlet on a high pressure gas turbine stage are investigated by using numerical methods. Numerical simulations of the annular type combustor are carried out by using large eddy simulation (LES) and unsteady Reynolds-averaged Navier-Stokes equations (URANS) techniques. The temperature distribution is found to be significantly affected by vortical structures at the primary zone and dilution jets. Numerical simulations of high pressure turbine stage are also conducted by using the Reynolds-averaged Navier-Stokes equations (RANS). Temperature distributions and aerodynamic loads at blade and end wall surfaces are drastically altered by changes in temperature, momentum, turbulent kinetic energy and turbulence dissipation rate at the exit of the combustor which are imposed as turbine inlet boundary conditions.