Effect of radial location of nozzles on performance of preswirl systems: A computational and theoretical study

Abstract

Abstract

This article investigates the effect of the radial location of the inlet nozzles on the performance of a direct-transfer preswirl system in a rotor—stator wheel-space. A commercial code is used to solve the Reynolds averaged Navier—Stokes equations using a high-Reynolds-number k-ε/k-ω turbulence model with wall functions. The three-dimensional steady-state model has previously been validated against experimental results from a scale model of a gas turbine rotor—stator system. Computations are performed for three inlet-to-outlet radius ratios, r_p/r_b=0.8, 0.9, and 1.0, a range of preswirl ratios, 0.5<β _b <2.0, and varying turbulent flow parameters, 0.12<λ _T <0.36. The rotational Reynolds number for each case is 10⁶.

The flow structure in the wheel-space and in the region around the receiver holes for each inlet radius is related to the swirl ratio. The performance of the system is quantified by two parameters: the discharge coefficient for the receiver holes (C_{d, b}) and the adiabatic effectiveness for the system (θ_{b, ad}).

As in previous work, the discharge coefficient is found to reach a maximum when the rotating core of fluid is in synchronous rotation with the receiver holes. As the radius ratio is increased, this condition can be achieved with a smaller value for preswirl ratio β_b. A simple model is presented to estimate the discharge coefficient based on the flowrate and swirl ratio in the system.

The adiabatic effectiveness of the system increases linearly with preswirl ratio but is independent of flowrate. For a given preswirl ratio, the effectiveness increases as the radius ratio increases. Computed values show good agreement with analytical results. Both performance parameters show improvement with increasing inlet radius ratio, suggesting that for an optimum preswirl configuration an engine designer would place the preswirl nozzles at a high radius.