elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Indirect combustion noise: Experimental investigation of the vortex sound generation in nozzle flows

Kings, Nancy (2015) Indirect combustion noise: Experimental investigation of the vortex sound generation in nozzle flows. Dissertation. DLR-Forschungsbericht. DLR-FB 2015-21, 219 S.

Full text not available from this repository.

Abstract

In recent years combustion noise of aero-engines has gained in importance. The latter consists of direct noise, related to the unsteady combustion process itself, and indirect noise. As known, entropy noise, contributing to indirect noise, is produced when entropy fluctuations originating from the combustor are accelerated through the turbine. According to the characterisation of a flow by pressure, entropy and vorticity perturbations, accelerated vorticity fluctuations are likewise expected to generate an indirect noise component. Within this work, the vortex sound generation mechanism was studied in a model experiment simplifying the combustor-turbine combination of aero-engines. Vorticity fluctuations were generated artificially by air-injection into swirl free as well as swirling tube flows and the proof of the emission of vortex sound during their acceleration in a convergent-divergent nozzle could be provided. The spatial and temporal change of the velocity field was determined with Hot-Wire Anemometry measurements upstream of the nozzle and the produced acoustic waves were detected downstream of it. For various flow fields imposed with perturbations the identification and separation of direct and vortex sound was achieved. Beside the dependency on the vorticity fluctuation amplitude, increasing the air-injection into the mean flow augments the vortex sound in case of a choked nozzle, the swirl intensity of the mean flow was figured out as a further parameter for this indirect sound generation process. In addition to the sound generation caused by the acceleration of a predominant, artificially produced vortex structure, the broadband noise emission of an accelerated tube flow was studied. With a linear theory approach, the alterations of the fluctuating velocity components through the acceleration were estimated. The coupled influence of the flow field upstream of the nozzle and of its occurring changes due to the imposed mean flow gradient revealed a significant effect on the vortex sound and therewith on the indirect noise generation mechanism.

Item URL in elib:https://elib.dlr.de/98236/
Document Type:Monograph (DLR-Forschungsbericht, Dissertation)
Additional Information:Zugl.: Berlin, Technische Universität, Diss., 2015(urn:nbn:de:kobv:83-opus4-67598)
Title:Indirect combustion noise: Experimental investigation of the vortex sound generation in nozzle flows
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Kings, NancyDLR, AT-TRAUNSPECIFIED
Date:2015
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Number of Pages:219
ISSN:1434-8454
Status:Published
Keywords:aeroacoustics; idirect combustion noise; nozzle flow; vortex sound; vorticity wave generator Liner
Institution:Technische Universität Berlin
Department:Fakultät V - Verkehrs- und Maschinensysteme
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:propulsion systems
DLR - Research area:Aeronautics
DLR - Program:L ER - Engine Research
DLR - Research theme (Project):L - Combusion Chamber Technologies (old), E - Gas Turbine (old)
Location: Berlin-Charlottenburg
Institutes and Institutions:Institute of Propulsion Technology > Engine Acoustic
Deposited By: Bake, Dr.-Ing. Friedrich
Deposited On:12 Oct 2015 10:35
Last Modified:12 Oct 2015 10:35

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.