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Academic literature on the topic 'Acoustic igniter'

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Published: 14 March 2023

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Journal articles on the topic "Acoustic igniter"

1

Pearson, Nicholas, and William E. Anderson. "Acoustic Response of a Resonant Igniter with Confuser Inlet." AIAA Journal 46, no. 4 (April 2008): 1013–15. http://dx.doi.org/10.2514/1.22340.

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Ahmed, Umair, Fakhre Ali, and Ian Jennions. "Signal Processing of Acoustic Data for Condition Monitoring of an Aircraft Ignition System." Machines 10, no. 9 (September 19, 2022): 822. http://dx.doi.org/10.3390/machines10090822.

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Degradation of the ignition system can result in startup failure in an aircraft’s auxiliary power unit. In this paper, a novel acoustics-based solution that can enable condition monitoring of an APU ignition system was proposed. In order to support the implementation of this research study, the experimental data set from Cranfield University’s Boeing 737-400 aircraft was utilized. The overall execution of the approach comprised background noise suppression, estimation of the spark repetition frequency and its fluctuation, spark event segmentation, and feature extraction, in order to monitor the state of the ignition system. The methodology successfully demonstrated the usefulness of the approach in terms of detecting inconsistencies in the behavior of the ignition exciter, as well as detecting trends in the degradation of spark acoustic characteristics. The identified features proved to be robust against non-stationary background noise, and were also found to be independent of the acoustic path between the igniter and microphone locations, qualifying an acoustics-based approach to be practically viable.
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PONCE, M., A. LÓPEZ, J. CORREA, J. ARAU, and J. M. ALONSO. "ELECTRONIC BALLAST FOR HID LAMPS WITH HIGH FREQUENCY SQUARE WAVEFORM TO AVOID ACOUSTIC RESONANCES." Journal of Circuits, Systems and Computers 13, no. 03 (June 2004): 651–63. http://dx.doi.org/10.1142/s0218126604001623.

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This paper presents a driver for a HID lamp based on the application of a high frequency current square waveform through the lamp with the goal of avoiding acoustic resonances. The proposed ballast is fed from a 12-V dc input voltage and is intended to be used in systems supplied from nonconventional sources, such as back-up batteries, photovoltaic generators and automotive applications. In order to initiate the discharge in the lamp, a specially-designed igniter supplied from the 12-V dc voltage is used to apply high voltage ignition peaks to the lamp. Experimental results obtained from a laboratory prototype for a 70-W Metal Halide lamp supplied at 30 kHz are also shown to evaluate the possibilities of the proposed topology.
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4

Dixon, S., C. Edwards, S. B. Palmer, and J. Reed. "Ultrasonic generation using a plasma igniter." Journal of Physics D: Applied Physics 34, no. 7 (March 20, 2001): 1075–82. http://dx.doi.org/10.1088/0022-3727/34/7/309.

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Ma, Xiaochi, Yifei Zhu, Yun Wu, Xiancong Chen, and Bingxuan Lin. "Multi-physics modeling of a spark plasma jet igniter." Journal of Physics D: Applied Physics 55, no. 3 (October 18, 2021): 035201. http://dx.doi.org/10.1088/1361-6463/ac2b65.

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Torregrosa, A. J., A. Broatch, A. Gil, and J. Gomez-Soriano. "Numerical approach for assessing combustion noise in compression-ignited Diesel engines." Applied Acoustics 135 (June 2018): 91–100. http://dx.doi.org/10.1016/j.apacoust.2018.02.006.

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Tokharski, J., C. West, and P. R. Smy. "Use of a plasma jet igniter as a gas pump." Journal of Physics D: Applied Physics 21, no. 12 (December 14, 1988): 1830–32. http://dx.doi.org/10.1088/0022-3727/21/12/029.

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Barkhudarov, E. M., N. K. Berezhetskaya, V. A. Kop'ev, I. A. Kossyi, N. A. Popov, M. I. Taktakishvili, and S. M. Temchin. "Ring-shaped electric discharge as an igniter of gas mixtures." Journal of Physics D: Applied Physics 43, no. 36 (August 25, 2010): 365203. http://dx.doi.org/10.1088/0022-3727/43/36/365203.

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Broatch, A., R. Novella, J. García-Tíscar, and J. Gomez-Soriano. "On the shift of acoustic characteristics of compression-ignited engines when operating with gasoline partially premixed combustion." Applied Thermal Engineering 146 (January 2019): 223–31. http://dx.doi.org/10.1016/j.applthermaleng.2018.09.089.

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Jafari, S. M., H. Mehdigholi, and M. Behzad. "Valve Fault Diagnosis in Internal Combustion Engines Using Acoustic Emission and Artificial Neural Network." Shock and Vibration 2014 (2014): 1–9. http://dx.doi.org/10.1155/2014/823514.

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This paper presents the potential of acoustic emission (AE) technique to detect valve damage in internal combustion engines. The cylinder head of a spark-ignited engine was used as the experimental setup. The effect of three types of valve damage (clearance, semicrack, and notch) on valve leakage was investigated. The experimental results showed that AE is an effective method to detect damage and the type of damage in valves in both of the time and frequency domains. An artificial neural network was trained based on time domain analysis using AE parametric features (AErms, count, absolute AE energy, maximum signal amplitude, and average signal level). The network consisted of five, six, and five nodes in the input, hidden, and output layers, respectively. The results of the trained system showed that the AE technique could be used to identify the type of damage and its location.
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Conference papers on the topic "Acoustic igniter"

1

Scholl, David, Craig Davis, Stephen Russ, and Terry Barash. "The Volume Acoustic Modes of Spark-Ignited Internal Combustion Chambers." In International Congress & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1998. http://dx.doi.org/10.4271/980893.

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Pancharia, Pankaj, Vikram Ramanan, Baladandayuthapani Nagarajan, and S. R. Chakravarthy. "Simultaneous TR-PIV and CH* Chemiluminescence During Combustion-Instability Triggered Flame-Flashback in a Backward Facing Step Combustor." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91252.

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Abstract The present study is an experimental investigation of the nature of acoustically induced flashback in a lab-scale dump combustor. The control parameters varied include the inlet Reynolds number (Re) and the inlet turbulence intensity. The primary bifurcation plots of the combustor from stable to the unstable condition are seen to be significantly altered by the inlet turbulence intensity, with the latter delaying the onset of combustion instability to higher Re. The analysis of multivariate high-speed data acquisition and processing (viz. unsteady pressure, flame imaging and velocity field by means of PIV) reveals the role of low-frequency high amplitude acoustics in modulating the flame. It is seen that high amplitude oscillations are sustained by two mechanisms 1. Modulation of the flame by coherent structures shedding at the step and 2. The bulk flame motion in-and-out at the edge of the step. It is seen that flow reversal at sufficiently low frequencies provide enough duration for the hot products to ignite fresh reactants upstream of the duct, which in-turn reinforces the coherent unsteadiness in the system, thereby increasing the propensity of the mixture to be ignited more upstream with every cycle. This ultimately leads to the flame flashing back till the point of premixing. This work thus addresses and reforms the occurrence of flashback being an example of loss of static stability, whereby the overriding presence of dynamic combustion instability results in a flashback to behave in a dynamic manner.
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An, Rong, Yanhong Tian, and Chunqing Wang. "Effect of modulation structure on the laser-ignited self-propagating behavior of Ti/Al multilayer films." In 2014 Joint IEEE International Symposium on the Applications of Ferroelectrics, International Workshop on Acoustic Transduction Materials and Devices & Workshop on Piezoresponse Force Microscopy (ISAF/IWATMD/PFM). IEEE, 2014. http://dx.doi.org/10.1109/isaf.2014.6918154.

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Prieur, Kevin, Daniel Durox, Guillaume Vignat, Thierry Schuller, and Sébastien Candel. "Flame and Spray Dynamics During the Light-Round Process in an Annular System Equipped With Multiple Swirl Spray Injectors." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76840.

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The ignition process of an annular combustor can be divided in several steps that end with the light-round. This corresponds to the sequence from the ignition of the first injector to the merging of the two flame fronts spreading in the annular system. The present article focuses on this important step, where two arch-like flame branches propagate in the chamber. These two turbulent travelling flames, nearly perpendicular to the combustor backplane, successively ignite the injection units and finally collide head-on and merge. In the present study, light-round of spray flames fed by liquid n-heptane is investigated. A high-speed camera operating at a frame rate of 6000 Hz and equipped with a filter centered on CH* emission is positioned on the side of the annular combustor, at the chamber backplane level and records images of one half of the chamber annulus. Acoustic pressure fluctuations are recorded through waveguide microphones plugged on the chamber backplane and microphones flush mounted in the annular plenum. The behavior of one injector ignited by the passing flame front is examined. One finds that the swirling flame structure formed by each injection unit evolves in time and that the anchoring location changes just after the passage of the travelling flame and during a period of a few milliseconds. This behavior can eventually lead to a flashback of the flame in the injector with possible severe damages. This dynamical phenomenon is described in detail. The propagation of the arch-like flame branch is then investigated. Flame images are used to determine the direction and velocity of the flame front by making use of a PIV like processing. One may distinguish two regions for the flame propagation. One is near the backplane, moving in a purely azimuthal direction, while the other corresponds to the remaining flame motion in the azimuthal and axial directions due to the volumetric expansion of the burnt gases. Filtered light images give some indications on the complex flame structures and on the typical length scales characterizing the moving front. Information is also obtained on the dynamics of the spray by shining a continuous laser sheet passing through one injector central axis and recording the light scattered by the n-heptane spray of droplets. These images are used to determine the influence of the incoming flame front on the evaporating n-heptane liquid droplets. A major result is that the flame modifies the spray much before its leading point reaches the injector unit and that its passage through the spray drastically changes the local droplet concentration and thus the local mixture composition.
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Khaira, Sukhbir Singh, Amandeep Singh, and Marcis Jansons. "Effect of Injection Parameters and Strategy on the Noise From a Single Cylinder Direct Injection Diesel Engine." In ASME 2011 Internal Combustion Engine Division Fall Technical Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/icef2011-60148.

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Acoustic noise emitted by a diesel engine generally exceeds that produced by its spark-ignited equivalent and may hinder the acceptance of this more efficient engine type in the passenger car market (1). This work characterizes the combustion noise from a single-cylinder direct-injection diesel engine and examines the degree to which it may be minimized by optimal choice of injection parameters. The relative contribution of motoring, combustion and resonance components to overall engine noise are determined by decomposition of in-cylinder pressure traces over a range of load, injection pressure and start of injection. The frequency spectra of microphone signals recorded external to the engine are correlated with those of in-cylinder pressure traces. Short Time Fourier Transformation (STFT) is applied to cylinder pressure traces to reveal the occurrence of motoring, combustion noise and resonance in the frequency domain over the course of the engine cycle. Loudness is found to increase with enhanced resonance, in proportion to the rate of cylinder pressure rise and under conditions of high injection pressure, load and advanced injection timing.
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Bothien, Mirko, Demian Lauper, Yang Yang, and Alessandro Scarpato. "Reconstruction and Analysis of the Acoustic Transfer Matrix of a Reheat Flame From Large-Eddy Simulations." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64188.

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Lean premix technology is widely spread in gas turbine combustion systems, allowing modern power plants to fulfill very stringent emission targets. These systems are, however, also prone to thermoacoustic instabilities, which can limit the engine operating window. The thermoacoustic analysis of a combustor is thus a key element in its development process. An important ingredient of this analysis is the characterization of the flame response to acoustic fluctuations, which is straightforward for lean-premixed flames that are propagation stabilized, since it can be measured atmospherically. Ansaldo Energia’s GT26 and GT36 reheat combustion systems feature a unique technology where fuel is injected into a hot gas stream from a first combustor, which is propagation stabilized, and auto-ignites in a sequential combustion chamber. The present study deals with the flame response of mainly auto-ignition stabilized flames to acoustic and temperature fluctuations for which a CFD system identification approach is chosen. The current paper builds on recent works, which detail and validate a methodology to analyze the dynamic response of an auto-ignition flame to extract the Flame Transfer Function (FTF) using unsteady Large-Eddy Simulations (LES). In these studies, the flame is assumed to behave as a Single-Input Single-Output (SISO) or Multi-Input Single-Output (MISO) system. The analysis conducted in GT2015-42622 qualitatively highlights the important role of temperature and equivalence ratio fluctuations, but these effects are not separated from velocity fluctuations. Hence, this topic is addressed in GT2016-57699, where the flame is treated as a multi-parameter system and compressible LES are conducted to extract the frequency-dependent FTF to describe the effects of axial velocity, temperature, equivalence ratio and pressure fluctuations on the flame response. For lean-premixed flames, a common approach followed in the literature assumes that the acoustic pressure is constant across the flame and that the flame dynamics are governed by the response to velocity perturbations only, i.e., the FTF. However this is not necessarily the case for reheat flames that are mainly auto-ignition stabilized. Therefore, in this paper we present the full 2 × 2 transfer matrix of a predominantly auto-ignition stabilized flame and hence describe the flame as a Multi-Input Multi-Output (MIMO) system. In addition to this, it is highlighted that in presence of temperature fluctuations the 2 × 2 matrix can be extended to a 3 × 3 matrix relating the primitive acoustic variables as well as the temperature fluctuations across the flame. It is shown that only taking the FTF is insufficient to fully describe the dynamic behavior of reheat flames.
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Arghode, Vaibhav, and Ashwani K. Gupta. "Non-Premixed and Premixed Colorless Distributed Combustion for Gas Turbine Application." In ASME 2010 International Mechanical Engineering Congress and Exposition. ASMEDC, 2010. http://dx.doi.org/10.1115/imece2010-38209.

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Non-premixed and premixed modes of Colorless Distributed Combustion (CDC) are investigated for application to gas turbine combustors. The CDC provides significant improvement in pattern factor, reduced NOx emission uniform thermal field in the entire combustion zone for it to be called as a isothermal reactor, and lower sound levels. Basic requirement for CDC is mixture preparation through good mixing between the combustion air and product gases so that the reactants are at much higher temperature to result in hot and diluted oxidant stream at temperatures that are high enough to auto-ignite the fuel and oxidant mixture. With desirable conditions one can achieve spontaneous ignition of the fuel with distributed combustion reactions. Distributed reactions can also be achieved in premixed mode of operation with sufficient entrainment of burned gases and faster turbulent mixing between the reactants. In the present investigation two non-premixed combustion modes and one premixed combustion mode that provide potential for CDC is examined. In all the configurations the air injection port is positioned at the opposite end of the combustor exit, whereas the location of fuel injection ports is changed to give different configurations. The results are compared for global flame signatures, exhaust emissions, acoustic signatures, and radical emissions using experiments and flow field, gas recirculation and mixing using numerical simulations. Ultra low NOx emissions are observed for both the premixed and non-premixed combustion modes, and almost colorless flames (no visible flame color) have been observed for the premixed combustion mode. The non-premixed mode was also provided near colorless distributed combustion. The reaction zone is observed to be significantly different in the two non-premixed modes.
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Xavier, Pradip, Mickael Pires, Alexis Vandel, Bruno Renou, Gilles Cabot, Mourad A. Boukhalfa, and Michel Cazalens. "Determination of Criteria for Flame Stability in an Annular Trapped Vortex Combustor." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43214.

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Development of lean premixed (LP) combustion is still a challenge as it results in considerable constraints for the combustor design. Indeed, new combustors using LP combustion are more prone to flashback, blow-off, or even thermo-acoustic instabilities. A detailed understanding of mechanisms leading to such extreme conditions is then crucial to reduce pollutant emissions, widen the range of operating conditions, and reduce design time. This paper reports the experimental study of an innovative LP trapped vortex combustor (TVC). The TVC concept uses a recirculating rich flow trapped in a cavity to create a stable flame that continuously ignites a main lean mixture passing above the cavity. This concept gave promising performances but some workers highlighted the existence of combustion instabilities for some operating conditions. Detailed studies have therefore been carried out in order to understand the occurrence of these drastic operating conditions. Results showed that the cavity flow dynamics in conjunction with the location of the interfacial mixing zone (between the cavity and the mainstream) were the driving forces to obtain stable combustion regimes. The goal of this work has been to take advantage of these detailed recommendations to determine stability maps, trends, and dimensionless parameters which could be easily used as early-design rules. For this reason, the study introduced a simple and robust criterion, based on the global pressure fluctuation energy. The latter was used to distinguish stable and unstable modes. An aerodynamic momentum flux ratio and a chemical stratification ratio (taken between the cavity and the mainstream) were defined to scale all measurements. Results indicated that the mainstream velocity was critically important to confine the cavity and to prevent combustion instabilities. Remarkably, this trend was verified and even more pronounced for larger cavity powers. In addition, flame stabilization above the cavity resulted in the existence of specific stratification ratios, in order to obtain a soft gradient of gas composition between the rich and lean regions. Finally, a linear relation between the mainstream and cavity velocities became apparent, thereby making possible to simply predict the combustor stability.
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Taamallah, Soufien, Santosh J. Shanbhogue, Yinka S. Sanusi, Esmail M. A. Mokhiemer, and Ahmed F. Ghoniem. "Transition From a Single to a Double Flame Structure in Swirling Reacting Flows: Mechanism, Dynamics, and Effect of Thermal Boundary Conditions." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43998.

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We examine experimentally the transition from a single flame stabilized along the inner shear layer (ISL) to a double flame stabilized along both the inner and the outer shear layers (OSL) and spreading over the outside recirculation zone (ORZ) in a fully premixed swirl-stabilized combustor. This work is mainly driven by previous studies demonstrating the link between this transition in the flame macrostructure and the onset of thermo-acoustic instabilities [1, 2]. Here, we examine the transition mechanism under thermo-acoustically stable conditions as well as the dominant flow and flame dynamics associated with it. In addition, we explore the role of changing the thermal boundary conditions around the ORZ and its effect on the presence or absence of the flame there. We start by analyzing the two flames bounding the transition, namely the single conical flame stabilized along the ISL (flame III) and the double conical flames with reactions taking place in the ORZ (flame IV). A dual chemiluminescence approach — using two cameras with a narrow field of view focused on the ORZ — is undertaken to track the progression of the flame as it reaches the ORZ. During the transition, the flame front, initially stabilized along the ISL, is entrained by OSL vortices close to where the turbulent jet impinges on the wall, leading to the ignition of the reactants in the ORZ and the ultimately the stabilization of the flame along the outer shear layer (OSL). This ORZ flame is also subject to extinction when the equivalence ratio (ϕ) is between values corresponding to flames III and IV. For ϕ lower than the critical transitional value, the flame kernel originating from the ISL-stabilized flame is shown to reach the ORZ but fails to grow and quickly disappears. For ϕ higher than the critical value, the flame kernel expands as it is advected by the ORZ flow and ultimately ignites the reactants recirculating in the ORZ. Sudden and extreme peak-to-peak values of the overall heat release rate are found to be concomitant with the ignition and extinction of the ORZ reactants. Finally, Different thermal boundary conditions are tested by modifying the heat flux through the combustion chamber boundary, particularly around the ORZ. We find that the transition is affected in different ways: while the transition from flame III to IV (i.e. as ϕ increases) is insensitive to these changes; flame IV persists at lower ϕ as its value is reduced when heat losses through the boundaries are diminished.
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Berndt, Phillip, Rupert Klein, and C. Oliver Paschereit. "A Kinetics Model for the Shockless Explosion Combustion." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57678.

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The shockless explosion combustion (SEC) is a novel approach to constant volume combustion in gas turbines. It promises an efficiency gain comparable to that of pulse detonation combustion (PDC), but without the drawbacks associated with detonations. It utilizes homogeneous combustion of a volume of fuel/air to avoid strong shock waves, similar to the RCCI process in internal combustion engines. Recharging is handled analogous to a pulse jet through the pressure waves in the combustion chamber. To achieve homogeneous auto ignition, the process involves setting up a stratified layer of fuel/air such that it homogeneously auto ignites in an approximately constant volume combustion (CVC). This becomes feasible by using fuels with small dependence of their auto ignition time on temperature, e.g. blends involving fuels with negative temperature coefficient (NTC) behaviour. The ignition process of such fuels is complex and often involves multi-stage ignition on time scales comparable to the acoustic time scale. It is hence expected that even though a SEC effectively is CVC, the ignition can not be modeled in 0D, but that it instead involves complex interaction between gas dynamics and chemical kinetics. The stratification process therefore has to be numerically optimized in CFD calculations. Optimization, especially if whole cycles are to be simulated, requires small kinetics models, even if restricted to one dimension, to be computationally feasible. On the other hand, the interaction of kinetics and gas dynamics at ignition rules out an easy to evaluate optimization goal for reduction of the chemical kinetics using offline methods like directed relation graphs and the techniques based on sensitivity analysis introduced by Williams/Peters. Even if sufficient computation power was invested, the accuracy constraints on the auto ignition times severely limit the usability of a conventional reduced mechanism. Online tools like CSP or ILDM would be an option for practical purposes, but do not provide insight into the ignition process and are therefore of little help for fundamental research. For a CFD simulation of a SEC, a new ansatz has therefore been developed. We exploit the constraint of a small temperature dependence of the auto ignition time on temperature to introduce a model specialized for SEC simulation that is sufficiently small to allow optimization of a fuel/air stratification, yet features correct auto ignition delay times for each ignition stage to the accuracy of experimental measurements. We then proceed to present simulation results which a posteriori justify our approach and demonstrate that shockless explosion combustion is feasible.
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