Computer method for design of acoustic liners for turbofan engines by Gene L. Minner

Cover of: Computer method for design of acoustic liners for turbofan engines | Gene L. Minner

Published by National Aeronautics and Space Administration, for sale by the National Technical Information Service in Washington, Springfield, Va .

Written in English

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  • Airplanes -- Turbojet engines -- Noise.,
  • Acoustical materials -- Design.,
  • Noise control -- Mathematical models.

Edition Notes

Book details

StatementGene L. Minner and Edward J. Rice; Lewis Research Center, Cleveland, Ohio.
SeriesNASA technical memorandum ; NASA TM X-3317, NASA technical memorandum -- X-3317.
ContributionsRice, Edward J., Lewis Research Center., United States. National Aeronautics and Space Administration.
The Physical Object
Pagination[1], 91 p. :
Number of Pages91
ID Numbers
Open LibraryOL17516515M

Download Computer method for design of acoustic liners for turbofan engines

Acoustic liner A successful method of further reducing noise, even in ultra-high bypass ratio engines, is to absorb the sound created within the engine.

Acoustically absorbent material or acoustic liners can be placed on the interior surfaces of the engines.

Probably the most common passive method of noise control is the use of acoustic Size: KB. A Two-Level Approach for Design Optimization of Acoustic Liners liner panels that are commonly used to damp engine noise in turbofan engines.

The method design optimization studies to determine liner parameters. If the number of design parameters in these 1. fan noise radiated to the far field is using acoustic liners. Liners are applied on the internal walls of engine intakes and bypass ducts, in order to attenuate the fan noise while it propagates through the ducts before it is radiated to the exterior.

Typical liners used for this purpose in turbofan engines File Size: KB. Simulation-based optimization of acoustic liner design in a turbofan engine nacelle for noise reduction purposes can dramatically reduce the cost and time needed for experimental designs.

Acoustic liners are applied on the internal walls to attenuate the fan noise while it propagates through the engine ducts. Typical engine duct liners are either so-called single degree of freedom (SDOF) or double degree of freedom (DDOF) liners.

SDOF liners consists of a porous facing sheet backed by. Passive Techniques for Fan Noise Reduction in New Turbofan Engines: Review turbofan engine, fan and exhaust noise [1] are among the Acoustic liner Probably the most common passive method of noise control is the use of acoustic liners.

The liners absorb the radiated. of low-noise aircraft engines. The optimization of liners for the intake and the bypass ducts is crucial for reducing fan noise from modern high-bypass ratio engines.

Several numerical and analytical methods have been developed for the prediction of sound attenuation in lined ducts with flow. For analytical analysis, a method of choice is to use a modal decomposition of the.

CFD techniques are required to inform liner acoustic impedance prediction models, in particular the resistance of facing sheets in grazing flow CAA techniques are required for impedance models of novel liners and for design features that result in liners being non-locally reacting (e.g.

drainage slots) d ' p RUcu Facing sheet resistanceFile Size: 1MB. Aircraft engines, typically turbofans, use acoustic liners to damp engine noise. Liners are applied on the internal walls of the engine nacelle, both in the intake and by-pass ducts, and use Helmholtz resonance principle for the dissipation of incident acoustic energy.

The performance of an intercooled turbofan engine is analyzed by multidisciplinary optimization. A model for making preliminary simplified analysis of the mechanical design of the engine is. Noise Suppression Methods for Turbofan Engines Jayson Bulaon University of Illinois Champaign, IL.

Using acoustic liners, a scarfed inlet, stator vane sweep and lean, and active-passive Methods for Jet Noise Suppression of Turbofan Engines File Size: KB. International Journal for Numerical Methods in Engineering (12), pp. Reflection of an acoustic line source by an impedance surface with uniform flow.

Brambley E.J., Gabard G. Journal of Sound and Vibration (21), pp.A full discrete dispersion analysis of time-domain simulations of acoustic liners with flow.

liner optimization methods, and relevant results. Introduction: An axisymmetric mixer-ejector exhaust nozzle, schematically shown in Figure 1, is planned for the ESPR turbofan engine. Acoustic treatment of the ejector surface becomes a viable means to reduce farfield noise. GEAE is designing appropriate liners for this application.

Computer method for design of acoustic liners for turbofan engines. Washington: National Aeronautics and Space Administration ; Springfield, Va.: For sale by the National Technical Information Service, (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors.

The acoustic liners that are built into the engine nacelle are fundamental in controlling fan noise. Acoustic liners present a major design challenge because they must address a large number of conflicting design requirements.

Liners must provide high levels of noise reduction over a wide range of engine operating conditions and frequencies. Liners. Engineering models predicting how sound radiates from jet exhausts has been developed and used extensively for the acoustic design of liners on turbofan engines.

Mode-matching for duct acoustics We have developed a method to predict how sound is attenuated in ducts and waveguides with complex distribution of acoustic treatments.

New Method for Jet Noise Reduction in Turbofan Engines Dimitri Papamoschou∗ University of California, Irvine, Irvine, California ncipleisreduction of the convective Mach number of turbulent eddies that produce intense downward sound radiation.

In a jetFile Size: KB. Technologies for Turbofan Noise Reduction Dennis Huff NASA Glenn Research Center Cleveland, Ohio U.S.A. Special thanks to Edmane Envia, James Bridges and Mike Jones presented at 10th AIAA/CEAS Aeroacoustics Conference Manchester, United Kingdom Computer-aided liner optimization for fan noise propagation and radiation.

By Lorenzo Lafronza. Abstract. The main object of this thesis is to investigate acoustic lining in turbofan ducts which have optimal attenuation for a tonal and broadband noise sources.

Liner attenuation is necessary in modern turbofan : Lorenzo Lafronza. Abstract. The research presented in this thesis explores the prediction of noise propagation and radiation in turbofan engine intakes and bypass ducts, and the optimisation of noiAuthor: Iansteel Mukum Achunche.

Acoustic scattering by an axially-segmented turbofan inlet duct liner at supersonic fan speeds By A. McALPINE, R.J. ASTLEY, V.J.T.

HII, N.J. BAKER, and A.J. KEMPTON. Journal of Sound and Vibration,Response surface method optimization of uniform and axially segmented duct acoustic liners. An innovative technique is presented to reduce noise from turbofan aircraft engines by incorporating the acoustic treatment with liners in engine ducts.

The tonal noise source and the near field sound propagation in the nacelle duct are simultaneously predicted with a single CFD analysis based on an efficient Nonlinear Harmonic (NLH) Size: 2MB. • Design of shrouded fan blades with a high length-to-chord aspect ratio or of large-chord fan blades with honeycomb core.

• Knowledge of the dynamics of rotors stiffened by high gyroscopic couples and submitted to large out of balance forces (e.g.

fan blade failure). • Fan blade-off and containment analysis methods (e.g. blade loss).File Size: 1MB. Conceptual Development of Quiet Turbofan Engines for Supersonic Aircraft Dimitri Papamoschou¤ University of California, Irvine, Irvine, California and Marco Debiasi† The Ohio State University, Columbus, Ohio This is a jointthermodynamicand acousticstudy of engines fornext-generation supersonicaircraft.

It explores. Blades on fans in current-generation turbofan engines can experience centrifugal loadings of around tons—equivalent to the weight of a diesel locomotive hanging on each blade.

Centrifugal loading increases with radius, with rotational speed, and with blade mass. Reduction in. method which neglects backwards reflected waves. The derivation of the parabolic approximation is presented.

Several code validation cases are given. An acoustic lining design process for an example aft fan duct is discussed. It is noted that the method can efficiently model realistic three-dimension effects, acoustic lining, and flow within theCited by: The performance of acoustic treatments installed on aircraft engines is strongly influenced by the boundary layer of the grazing flow on the surface of the liner.

The parametric study presented in this paper illustrates the extent of this effect and identifies when it is significant. The acoustic modes of a circular duct with flow are calculated using a finite difference method. I currently doing by final project about designing fan for turbofan discussing with my lecturer,I decided to do it based on axial compressor preliminary design method in Gas Turbine Theory: G.

Rogers, H. Saravanamuttoo, Henry Cohen after following the design method,I'm stucked at determining the pitch to chord ratio for five points from hub to ing. A mode-merging design method (MMDM) for bulk liners with porous materials is proposed to maximize transmission losses in flow ducts.

The eigenequation and its partial derivative equation governing the coupled acoustic fields in the duct and backchamber are derived, from which the merging double eigenvalue is obtained at a target frequency for a single incident circumferential : Xianghai Qiu, Xiaodong Jing, Lin Du, Xiaofeng Sun, Mats Åbom, Hans Bodén.

A prediction method for sound attenuation in acoustically lined circular ducts of uniform cross section containing radially sheared fluid flow is developed. The flow is regarded as consisting of a core of uniform flow surrounded by a thin layer near the duct wall in which the flow is sheared.

The method is based on the solutions (acoustic modes) of an eigenfunction derived from the governing Cited by: 1. An iterative finite element-integral technique is used to predict the sound field radiated from the JT15D turbofan inlet.

The sound field is divided into two regions: the sound field within and near the inlet which is computed using the finite element method, and the radiation field beyond the inlet which is calculated using an integral solution by: temperature of resin-based composites, so that the resin matrix composite acoustic liners are mainly used in the cold side of the engine.

For resin matrix composite acoustic liners, the acoustic liners of current generation of high- bypass ratio turbofan engines (such as GE's CFM turbofan engines) are made of advanced composite materials.

This is through the aerodynamic design and the various features built into the subassemblies such as Acoustic Liners used extensively througout the nacelle which convert acoustic energy into small amounts of heat.

This is a major source of noise-reduction in modern aircraft engines. C.2, England* (Received 15 Apriland in revised form 15 June ) The development of a method is described for reducing the approach-landing noise of commercial jet transports by means of acoustic linings for attenuating the noise generated by the fan-compressor in turbofan engines and radiated from the intake and fan-exit by: 7.

Despite many advances in aviation noise control over the past 50 years, the industry is continually striving to reduce noise emissions. Turbofan engine acoustic liners are efficient attenuators of engine noise.

Plasma actuators have been used as flow control devices in other settings and will now be studied as an enhancement for acoustic by: 1.

Methods of rotor-stator interaction noise prediction and suppression which can be applied to the UL ducted fan propulsion unit were first used in turbofan engine fan design and development.

Therefore, the rotor-stator configuration is only taken into account in the studies referred to. DuringFile Size: 1MB. DESIGN, AND MODIFICATION OF TURBOFAN/JET ENGINE TEST CELLS Date: 12/26/02 Initiated by: AFS AC No: Change: 1.

PURPOSE. This advisory circular (AC) provides guidance regarding test cell correlation procedures for test cells used for in-service acceptance testing of turbofan and turbojet engines. This AC discussesFile Size: KB.

Bypass ratio. The bypass ratio (BPR) of a turbofan engine is the ratio between the mass flow rate of the bypass stream to the mass flow rate entering the core.

A bypass ratio, for example, means that 10 kg of air passes through the bypass duct for every 1 kg of air passing through the core. Jet engines make noise for the same reason why thunder, whistles and flutes make sound - High speed air meets low speed air.

Jet engines (which includes turbofans) operate by moving massive amount of air at high speed. In pure turbojets (which are. Prediction of Supersonic Fan Noise Generated by Turbofan Aircraft Engines was focussed on improving the capability of predicting supersonic fan noise from modern high-bypass-ratio turbofan aero-engines.

The shift from single core jet engines to highbypass-ratio turbofan engines brought about a reduction in the overall aircraft engine noise principally by reducing the jet-broadband : Oluwaseun Emmanuel Adetifa. and the soft vane showing 2 dB reduction in aft acoustic power levels.

As a follow on, it was decided to test both concepts in a higher bypass ratio model with a pressure ratio more indicative of actual turbofan engines. The motivation for the use of the OTR is that placing treatment over the rotor should allow for attenuation of rotor self noise.

The method of suppressing with an acoustic liner around the fan blades of a jet engine noise over a relatively narrow frequency range, said fan having a first operating condition of one fan speed and a second operating condition of another fan speed, wherein said fan generates a noise of a first frequency range under said first operating.Pratt & Whitney is a large gas turbine engine design company, and has been in the engine business since it's inception in InP&W designed, built and flew a large "Geared Turbofan" engine which was a demonstrator for a new product architecture being developed, the first of the new product family being the PWl G.

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