Download Acoustic Control of Turbulent Jets by A.S. Ginevsky, Y.V. Vlasov, R.K. Karavosov PDF

By A.S. Ginevsky, Y.V. Vlasov, R.K. Karavosov

Results of experimental study on aerodynamic and acoustic regulate of subsonic turbulent jets by means of acoustic excitation are awarded. It used to be tested that those regulate tools, originated by way of authors, not just can accentuate blending (by acoustic irradiation at low frequency), but in addition particularly ease it (at high-frequency irradiation). This learn monograph provides the up to date result of the authors supplemented via different investigations performed in united states, Germany and nice Britain. The equipment for the numerical simulation of subsonic turbulent jets less than acoustic excitation are defined intimately, and examples are reviewed of useful purposes, together with relief of turbojet engine noise and acoustic regulate of self-sustained oscillations in wind tunnels.

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Extra info for Acoustic Control of Turbulent Jets

Example text

70] for the case of transverse acoustical excitation of a turbulent jet. Fig. 5 for different levels of the sound pressure, L, for two issue speeds U o = 10 and 20 mls. Here the following facts engage our attention. First, these functions are defined for strict1y fixed levels of the sound pressure near the nozzle edge and for v; I U o respectively. Thus the curves ulu_ = 1)7\ (St,) and u' lu~ = 1)72 (St s ) are smooth unlike the similar curves in the previous paragraph. : 10). The action sign change in Fig.

15) at the section xl Bo = 200 where the suppression tumed out to be maximum. 2. 017 corresponding to the maximum spatial increase of disturbances in complete agreement with the linear theory of stability. 022. 025 the values u' / u~ > 1 can be achieved. 4 .. 8 Fig. 13. l) L = 105 dE, 2) L = 135 dB, 3) L = 135 dE. 46 CHAPTER 2. 1 ,----------------------------------, • 1 .. L-_ _ _ _----' 1 2 4 6 8 x/d Fig. 14. Change of u / u_ a10ng the jet axis for Uo = 10 mls, St s =9 1) L = 105 dB, 2) L = 135 dB.

54]. 1. 1 y/ro Fig. 6. 89. 5) is attended (Fig. 25]. As follows from Fig. 53]. 23]. g. s0o / U o for x / d = 4 where 0 is the momentum loss thickness at the initial section of a laminar boundary layer (Fig. 10 for a jet under longitudinal acoustical excitation. 022 . ° 40 CHAPTER 2. 5 2 5 St Fig. 7. 4. 1 x/d Fig. 8. 5. 1. 5 O 500 1000 t. ls Fig. 9. Change in the Euler time correlation of the longitudinal velocity pulsations at the points x! d = 3, Y / d = O and x! 75 , 3) a radiation-free jet. 017 .

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