Broadband pulsed flow using piezoelectric microjets

Hogue, J.M.; Solomon, John T.; Hays, Michael; Alvi, Farrukh S.; Oates, William S.

doi:10.1117/12.847560

Cited by 4 publications

(5 citation statements)

References 12 publications

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“…Figure 18 shows the difference in the power spectral density between 100 and 1000 Hz. The power spectral density for other individual frequencies are illustrated in [24]. Attenuation around 10 dB is observed between the 100 Hz and 1.4 kHz tests.…”

Section: Pulsed Flow Characterizationmentioning

confidence: 97%

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Piezoelectric Pulsed Microjets

Oates¹,

Alvi²

2011

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information.Send comments regarding this burden estimate or any other aspect of this collection of information, including suggesstions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington VA, 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any oenalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS.a. REPORT Piezoelectric Pulsed Microjets Final Report 14. ABSTRACT SECURITY CLASSIFICATION OF:This reports summarizes an investigation of coupling broadband piezoelectric actuators with large force microjet actuators to achieve pulsed flow control over a broad frequency range. The development is relevant to a range of flow control problems for rotorcraft noise control and dynamic stall, jet inlet flow separation, cavity bay flow control, etc. The results have provided multi-physics modeling describing the actuator dynamics, high fidelity aero-acoustic computations, and smart structure and fluid dynamic experimental characterization. It is shown that ABSTRACTThis reports summarizes an investigation of coupling broadband piezoelectric actuators with large force microjet actuators to achieve pulsed flow control over a broad frequency range. The development is relevant to a range of flow control problems for rotorcraft noise control and dynamic stall, jet inlet flow separation, cavity bay flow control, etc. The results have provided multi-physics modeling describing the actuator dynamics, high fidelity aero-acoustic computations, and smart structure and fluid dynamic experimental characterization. It is shown that the piezoelectric actuator achieved pulsed flow actuation from quasi-static up to at least 1.6kHz. Pulsed supersonic microjet flow was confirmed using micro-schlieren imagery up to 800Hz. The first design was also extended to a highly compact microjet actuator capable of comparable pulsed actuation which is expected to facilitate technology transfer. (c) Presentations 0.00 Number of Presentations:1.00 Non Peer-Reviewed Conference Proceeding publications (other than abstracts):Number of Non Peer-Reviewed Conference Proceeding publications (other than abstracts): 0 Peer-Reviewed Conference Proceeding publications (other than abstracts):Hogue, J., Kumar, R., Alvi, F., Oates, W., "Experimental Characterization of Broad Bandwidth Piezohydraulic Microjets", to be submitted to J. Mater. Syst. Struct. (d) ManuscriptsNumber of Peer-Reviewed Conference Proceeding publications (other than abstracts): 0 The number of undergraduates funded by this agr...

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Section: Pulsed Flow Characterizationmentioning

confidence: 97%

“…This was found to be true as the frequency increased to approximately 400 Hz. Additional comparisons up to 1.6 kHz are given in [24].…”

Section: Pulsed Flow Characterizationmentioning

confidence: 99%

Piezoelectric Pulsed Microjets

Oates¹,

Alvi²

2011

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“…Various active control methods have been summarized in reviews by Lin [17], Lu et al [18], Panaras and Lu [26], and Verma and Abdellah [31] have summarized various active control methods, including air jets, pulsed microjets [32,33], steady microjets [30,34,35], plasma jets [36], and synthetic jets [37]. The control effect of pulsed resonance-enhanced microjets has been demonstrated successfully [38], while other pulsed microjets based on piezoelectric [33] and microelectromechanical systems have also shown the same control effect [39]. The plasma jet has also shown good control ability in studies [36,40,41].…”

Section: Introductionmentioning

confidence: 99%

Simulations of Compression Ramp Shock Wave/Turbulent Boundary Layer Interaction Controlled via Steady Jets at High Reynolds Number

Dai,

Zhang

2023

Aerospace

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Shock wave/turbulent boundary layer interaction (SBLI) is one of the most common physical phenomena in transonic wing and supersonic aircraft. In this study, the compression ramp SBLI (CR-SBLI) was simulated at a 24° corner at Mach 2.84 using the open-source OpenFOAM improved delayed detached eddy simulation (IDDES) turbulence model and the “Rescaling and Recycling” method at high Reynolds number 1.57×106. The results of the control effect of the jet vortex generator on CR-SBLI showed that the jet array can effectively reduce the length of the separation zone. The simulation results of different jet parameters are obtained. With the increasing jet angle, the reduction in the length of the separation zone first increased and then decreased. In this work, when the jet angle was 60°, the location of the separation point was x/δ=−1.48, which was smaller than other jet angles. The different distances of the jet array also had a great influence. When the distance between the jet and the corner djet=70 mm, the location of the separation point x/δ=−1.48 was smaller than that when djet=65/60 mm. A closer distance between the jet hole and the corner caused the vortex structures to squeeze each other, preventing the formation of a complete vortex structure. On the other hand, when the jet was farther away, the vortex structures could separate effectively before reaching the shock wave, resulting in a better inhibition of SBLI. The simulation primarily focused on exploring the effects of the jet angle and distance, and we obtained the jet parameters that provided the best control effect, effectively reducing the length of the CR-SBLI separation zone.

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“…Compared to steady MJs, the PMJs are a more effective alternative as these are more energy efficient and can be tuned to target different frequencies. Other variants of PMJs are the piezoelectric [30] and MEMS PMJs [31]. However, active flow control devices, as already mentioned before, can be complex, expensive and also difficult to implement and maintain [25].…”

Section: Introductionmentioning

confidence: 99%

“…However, active flow control devices, as already mentioned before, can be complex, expensive and also difficult to implement and maintain [25]. Various groups in USA [29][30][31][32][33], Europe [10,28,34,35], UK [26,27], India [36,37] and China [38] are looking at different methods of shock-induced control in various areas of research applications.…”

Section: Introductionmentioning

confidence: 99%