File(s) under permanent embargo
Reason: This item is currently closed access.
The response to incident acoustic waves of the flow field produced by a multi-passage lean-burn aero-engine fuel injector
conference contribution
posted on 2017-11-02, 10:46 authored by Nicholas C. W. Treleaven, Jialin SuJialin Su, Andrew GarmoryAndrew Garmory, Gary PageGary Page© 2017 ASME. Previous work has shown that compressible unsteady Reynolds-Averaged Navier-Stokes (URANS) simulations, with suitable acoustic boundary conditions, are capable of correctly predicting the acoustic impedance of simplified fuel injectors. In this work the method developed is applied to simulating the acoustically forced flow in and downstream of a realistic multi-passage fuel injector. The simulations are validated by compar-ing the impedance of the injector with data obtained experimen-tally by a multi-microphone technique. Such results can then be used in conjunction with a suitable low-order thermo-Acoustic network model to predict the stability of combustors. However the validated simulations can also be used to reveal further de-tails about the effect of acoustic forcing on the flow field. The velocity flow field produced by the injector with and without acoustic forcing is analysed using snapshot POD to de-termine the large scale energy containing structures within the flow. In the non-Acoustically forced simulations it was found that the first four POD modes correspond to two rotating spi-ral modes, designated as the m=1 and m=2 modes with a peak frequency content of 450 Hz for the first mode and 1000 Hz for the second mode corresponding to experimental Hot-Wire mea-surements made in a separate study. It is hypothesised that these spiral modes will affect the atomisation, evaporation and mixing of the fuel in subsequent planned two-phase simulations. POD analysis of the flow subjected to 300 Hz, 300 Pa acoustic excita-tion shows that the first four POD modes correspond to similarly shaped spiral modes. The acoustic excitation is responsible for the appearance of 4 POD modes within the injector body that correspond to two push-pull velocity modes with axes of symme-try perpendicular to each other. The acoustic forcing also pro-duces two additional POD modes that most likely represent the non-linear interaction between the push-pull and spiral modes. Further analysis of the fluctuations in pressure, mass flow rate, angular velocity and swirl number, within the passages and at the injector exit plane, show that the fluctuations in pressure and mass flow rate average across the passages while variations in angular velocity and swirl number sum across the passages. The relationship between mass flow rate, angular velocity and swirl number is discussed with reference to general observations of the sensitivity of flames to fluctuations in these quantities.
Funding
The authors acknowledge the assistance of Marco Zedda from Rolls-Royce plc and the support of EPSRC (Engineering and Physical Sciences Research Council) through their support of the Centre for Doctoral Training in Gas Turbine Aerodynamics, grant ref. EP/L015943/1, EPSRC grant ref EP/M023893/1 and Rolls-Royce plc. Calculations were performed on HPCMidlands funded by the EPSRC, Grant ref EP/K000063/1.
History
School
- Aeronautical, Automotive, Chemical and Materials Engineering
Department
- Aeronautical and Automotive Engineering
Published in
ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition Proceedings of the ASME Turbo ExpoVolume
Part F130041-4BCitation
TRELEAVEN, N.C.W. ...et al., 2017. The response to incident acoustic waves of the flow field produced by a multi-passage lean-burn aero-engine fuel injector. Presented at the ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition Charlotte, North Carolina, USA, Volume 4B: Combustion, Fuels and Emissions, pp. V04BT04A026.Publisher
© Rolls Royce. Published by American Society of Mechanical Engineers (ASME)Version
- AM (Accepted Manuscript)
Publisher statement
This work is made available according to the conditions of the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International (CC BY-NC-ND 4.0) licence. Full details of this licence are available at: https://creativecommons.org/licenses/by-nc-nd/4.0/Publication date
2017Notes
This paper is in closed access.ISBN
9780791850855Publisher version
Book series
ASME;GT2017-64527Language
- en