Prediction of the Acoustic Losses of a Swirl Atomizer Nozzle Under Non-Reactive Conditions

Abstract

When predicting combustion instabilities in gas turbine combustion chambers, the complex geometry and three dimensional flow configurations are often neglected. However, these may have significant influence on the overall acoustic damping behavior of the system. An important element governing the flow inside a combustion chamber is the swirl atomizer nozzle. Therein, the flow is accelerated and a swirling fluid motion is imposed. At its exit considerable high flow velocities are reached and multiple shear layers are formed which discharge into the combustion chamber. To predict damping effects in these environments, acoustic-flow interaction processes need to be taken into account. These involve scattering and refraction of incident acoustic waves in shear layers, acoustic interaction with the unstable hydrodynamic shear layers as well as acoustic wall interaction processes. Their combined effect can be studied using acoustic scattering matrices. In this paper the acoustic scattering behavior of a lean injection system developed by Avio is predicted under non-reactive conditions and compared to experiments. The numerical method is very general and works as follows: First, the fluid dynamic field is computed using a Reynolds averaged Navier-Stokes turbulence model. Then, the linearized Navier-Stokes equations are solved in frequency space around the previously computed mean flow state. The complex three dimensionality of the nozzle configuration is taken into account as well as its corresponding flow field. Results are compared against experimental measurements of a swirl atomizer nozzle at atmospheric and elevated inlet temperatures. It is shown that the scattering behavior and therefore the acoustic-flow interactions are captured accurately.

Measurements and computational fluid dynamics predictions of the acoustic impedance of orifices

“…(9) and (13). The analytical models give reactances which are linear with frequency and are therefore not capable of reproducing the experimental trends seen here.…”

“…Linearised methods for calculating acoustic behaviour have been used, for example Gikadi et al [9] used this method to investigate a swirl burner. They used a technique whereby a RANS simulation was produced of the steady field before a method using Linearised Navier-Stokes Equations (LNSE) was used to find the magnitude and phase of reflected and transmitted waves through a swirler.…”

Direct Assessment of the Acoustic Scattering Matrix of a Turbulent Swirl Combustor by Combining System Identification, Large Eddy Simulation and Analytical Approaches

“…Indeed, several studies deduced matrix coefficients for acoustically passive combustor parts of varying complexity, e.g., a single orifice [3], a tandem orifice [4], multiperforated liner plates [5], or a premixed nozzle [6]. The acoustic transfer behavior of swirl generators, which are an unavoidable part in swirl stabilized combustion systems, was numerically determined by Gikadi et al [7] and Ni et al [8]. A system of algebraic equations may be constructed from the collection of transfer (or scattering) matrices of the combustor elements.…”

Eigenvalue Analysis for the Prediction of Initial Growth Rates of Thermoacoustic Instability in Rocket Motors

“…The capability of frequency based LEE to capture relevant aeroacoustic phenomena has been shown in many publications. 15,16,17 The frequency based LEE approach is validated on the HF-7 test case on four given load points. 18 The paper is organized as follows.…”