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Apr 1980

Volume 67, Issue S1, pp. S1-S103

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back to top Session R. Noise IV: Test Cells and Hush Houses
Invited Papers
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Control of jet engine noise (A)

M. I. Schiff

J. Acoust. Soc. Am. Volume 67, Issue S1, pp. S41-S41 (1980); (1 page)

Online Publication Date: 11 Aug 2005

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A review covering the more than two decades of Industrial Acoustics Company's experience in the design and manufacture of jet engine noise suppression equipment. The development of this equipment for aircraft and test stand applications is traced. Some of the more significant noise control sytems are illustrated. Examples of how the interaction of acoustics, aerodynamics, and mechanical performance impacts the operation and service life of jet engine noise suppression equipment are included.
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A review of the acoustical aspects of hush house design (A)

I. L. Vér

J. Acoust. Soc. Am. Volume 67, Issue S1, pp. S41-S41 (1980); (1 page)

Online Publication Date: 11 Aug 2005

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This paper reviews the acoustic requirements, the acoustic performance of hush houses, and the present state of available design information. Emphasis will be placed on dry‐cooled‐type facilities. Experience gained, through model studies and through performance evaluation of recently completed facilities, will be cited. The conflict between acoustical aerodynamical, aerothermal, and structural design requirements, and cost limitations will be discussed and the need for close cooperation between acoustical aerodynamical, aerothermal, and structural designer and the close consultation with future user, as a prerequisite for a balanced design, pointed out.
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Test cell and hush house noise suppression developments (A)

M. Lepor

J. Acoust. Soc. Am. Volume 67, Issue S1, pp. S41-S42 (1980); (2 pages)

Online Publication Date: 11 Aug 2005

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The Navy has a number of technical approaches under development to diminish the noise impact of ground run‐up testing. Since resources are scarce, it is important that all reasonable designs for satisfying noise abatement objectives be considered to ensure proper committments to these resources. The initial thrust of the development effort where the engine is in the aircraft (e.g., “in‐frame”) is the acoustical enclosure or hush house program. A series of these facilities have been designed for a variety of air station requirements. An alternate air‐cooled noise suppression system under consideration for out‐of‐frame testing is the design of a test cell exhaust section based on the application of the Coanda/Refraction concept. Current methods for design of water‐cooled jet engine test cells for out‐of‐frame testing are largely empirical. By developing working internal thermo/aerodynamic models prior to preliminary design, the design of new test cells and/or required modifications of existing water‐cooled facilities would be greatly enhanced. The need for the development of models and for advances in material technology for optimization of test cell and hush house designs are discussed.
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Acoustic test facilities (A)

N. D. Taylor

J. Acoust. Soc. Am. Volume 67, Issue S1, pp. S42-S42 (1980); (1 page)

Online Publication Date: 11 Aug 2005

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Two unique acoustic test facilities at the Evendale Plant of the Aircraft Engine Group are used for developing and testing aircraft engines and their derivatives. The large (80 000 cu ft) anechoic chamber at the AEG plant in Evendale, Ohio was built for the purpose of studying and reducing jet noise. One‐sixth scale models of two‐flow engine nozzles can be tested under simulated in‐flight conditions provided by a wind tunnel around the nozzle simulating approach or takeoff. Frequencies to 80 000 Hz are scaled to full engine size. This chamber has the unique capability of making noise measurements in the forward quadrant as well as aft over an extensive range of temperatures and pressures in all three flows. The laser velocimeter has also proved to be a valuable tool in the study of noise source generation. Nozzles tested over the past four years include baseline conic configurations, mixers, suppressors, ejectors, and coannular nozzles with plugs. For supersonic engines, nozzles with inverted flow (fan/core) were examined. The large reverberant test chamber at the AEG plant in Evendale, Ohio was built for the purpose of measuring sound power levels around the LM2500 Gas Turbine Engine Module (derivative of the TF39/CF6‐6 aircraft engines). Levels must be measured to insure compliance of 30 000 shaft hp modules which are eventually mounted in power plants or on shipboard where noise environment is critical. Sound levels are measured at the same time that performance measurements are made.
Contributed Papers
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Noise level measurements around F‐16 noise suppresser system (A)

Richard P. Hentz and Rollin O. Boe

J. Acoust. Soc. Am. Volume 67, Issue S1, pp. S42-S42 (1980); (1 page)

Online Publication Date: 11 Aug 2005

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Several interesting results were noted while taking a complete series of acoustical measurements around an F‐16 noise suppressor system. We designed this system for the USAF and were required to demonstrate its conformance with acoustical specifications. Measurements were taken using the same aircraft during a two‐day period of stable weather. Although consistant measurements would be the most agreeable, large fluctuations were observed that could not be explained by wind, atmospheric absorption, or background noise. These results lend credence to similar published results [R. N. Foss, J. Acoust. Sec. Am. 66, 1088–1092 (1979)]. These results emphasize the need for a better method of acoustically certifying test cells and hush houses.
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An exploratory survey of noise levels associated with a 100‐kW wind turbine (A)

J. R. Balombin

J. Acoust. Soc. Am. Volume 67, Issue S1, pp. S42-S42 (1980); (1 page)

Online Publication Date: 11 Aug 2005

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During the past few years, NASA's Lewis Research Center has managed a wind turbine project for the Department of Energy. This effort has included the design, construction, and operation of a 125‐ft‐diam, 100‐kW wind turbine at the NASA Plum Brook Station near Sandusky, Ohio. During some of the performance tests, the opportunity arose to make exploratory noise measurements and results of those surveys are presented. The data include measurements as functions of distance from the turbine, and directivity angle, and cover a frequency range from 1 Hz to several kHz. Potential community impact is discussed in terms of A‐weighted noise levels relative to background levels, and the infrasonic spectral content. Finally, the change in the sound power spectrum associated with a change in the rotor speed is described.
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