Next Article in Journal
A POD-Based Procedure for the Split of Unsteady Losses of an LPT Cascade
Previous Article in Journal
The Effect of Hot Streaks on a High Pressure Turbine Vane Cascade with Showerhead Film Cooling
Article Menu

Export Article

Open AccessArticle
Int. J. Turbomach. Propuls. Power 2017, 2(3), 16; doi:10.3390/ijtpp2030016

Effect of Distortion on Turbofan Tonal Noise at Cutback with Hybrid Methods

1
Aerodynamics and Acoustics Department, Safran Aircraft Engines, 77550 Moissy-Cramayel, France
2
CFD Team, CERFACS, 31100 Toulouse, France
3
Department of Mechanical Engineering, Université de Sherbrooke, Sherbrooke, QC J1K2R1, Canada
4
Department of Aerodynamics, Energetics and Propulsion, ISAE, 31400 Toulouse, France
This paper is an extended version of our paper published in 22nd AIAA/CEAS Aeroacoustics Conference, 2016, Paper No. 2016-2818.
*
Author to whom correspondence should be addressed.
Academic Editor: Marcello Manna
Received: 30 March 2017 / Revised: 31 August 2017 / Accepted: 4 September 2017 / Published: 20 September 2017

Abstract

New ultra high bypass ratio architectures may significantly affect the fan tonal noise of future aircraft engines. Indeed, such a noise source is supposed to be dominated by the interaction of fan-blade wakes with outlet guide vanes. However, shorter nacelles in these engines are expected to trigger an important air-inlet distortion that can be responsible for new acoustic sources on the fan blades. Full annulus simulations based on the unsteady Reynolds-averaged Navier–Stokes equations are presently used to study this effect. Simulation results show that the air-inlet distortion has a main effect in the fan-tip region, leading to a strong variation of the fan-blade unsteady loading. It also significantly modifies the shape of the fan-blade wakes and, consequently, the unsteady loading of the outlet guide vanes. Acoustic predictions based on the extension of Goldstein’s analogy to an annular duct in a uniform axial flow are presented and show that the fan sources notably contribute to the fan tonal noise. The air-inlet distortion is responsible for an increase of the noise radiated by both the fan and the outlet guide vane sources, leading to a global noise penalty of up to three decibels. View Full-Text
Keywords: fan tonal noise; inlet distortion; hybrid methods fan tonal noise; inlet distortion; hybrid methods
Figures

Figure 1

This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).

Scifeed alert for new publications

Never miss any articles matching your research from any publisher
  • Get alerts for new papers matching your research
  • Find out the new papers from selected authors
  • Updated daily for 49'000+ journals and 6000+ publishers
  • Define your Scifeed now

SciFeed Share & Cite This Article

MDPI and ACS Style

Daroukh, M.; Moreau, S.; Gourdain, N.; Boussuge, J.-F.; Sensiau, C. Effect of Distortion on Turbofan Tonal Noise at Cutback with Hybrid Methods. Int. J. Turbomach. Propuls. Power 2017, 2, 16.

Show more citation formats Show less citations formats

Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Article Metrics

Article Access Statistics

1

Comments

[Return to top]
Int. J. Turbomach. Propuls. Power EISSN 2504-186X Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top