A review of active control approaches in stabilizing combustion systems in aerospace industry

Zhao, Dan; Lu, Zhengli; Zhao, He; Li, X.Y.; Wang, Bing; Liu, Peijin

doi:10.1016/j.paerosci.2018.01.002

Cited by 179 publications

(63 citation statements)

References 144 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…1989; McManus, Poinsot & Candel 1993; Annaswamy & Ghoniem 1995; Dowling & Morgans 2005; Zhao et al. 2018).…”

Section: Introductionmentioning

confidence: 99%

“…In practice, hydrodynamics (Renard et al 2000) and entropy (Marble & Candel 1977;Candel et al 2009) mechanisms may also play a role in the feedback mechanism. Based on this description, it follows that interrupting the flame-acoustic coupling would weaken or suppress thermoacoustic instabilities, and indeed this approach is pursued by passive control devices (Putnam 1971;Richards, Straub & Robey 2003) and by active control strategies (Poinsot et al 1989;McManus, Poinsot & Candel 1993;Annaswamy & Ghoniem 1995;Dowling & Morgans 2005;Zhao et al 2018).…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Thermoacoustic interplay between intrinsic thermoacoustic and acoustic modes: non-normality and high sensitivities

2019

View full text Add to dashboard Cite

This study analyses the interplay between classical acoustic modes and intrinsic thermoacoustic (ITA) modes in a simple thermoacoustic system. The analysis is performed using a frequency-domain low-order network model as well as a time-domain spatially discretised model. Anti-correlated modal sensitivities are found to arise due to a pairwise interplay between acoustic and ITA modes. The magnitude of the sensitivities increases as the interplay between the modes grows stronger. The results show a global behaviour of the modes linked to the presence of exceptional points in the spectrum. The time-domain analysis results in a delay-differential equation and allows the investigation of non-normal behaviour and its consequences. Pseudospectral analysis reveals that energy amplification is crucially linked to an interplay between acoustic and ITA modes. While higher non-orthogonality between two modes is correlated with peaks in modal sensitivity, transient energy growth does not necessarily involve the most sensitive modes. In particular, growth estimates based on the Kreiss constant demonstrate that transient amplification relies critically on the proximity of the non-normal modes to the imaginary axis. The time scale for transient amplification is identified as the flame time delay, which is further corroborated by determining the optimal initial conditions responsible for the bulk of the non-modal energy growth. The flame is identified as an active and dominant contributor to energy gain. The frequency of the optimal perturbation matches the acoustic time scale, once more confirming an interplay between acoustic and ITA structures. Flame-based amplification factors of two to five are found, which are significant when feeding into the acoustic dynamics and eventually triggering nonlinear limit-cycle behaviour.

show abstract

“…1989; McManus, Poinsot & Candel 1993; Annaswamy & Ghoniem 1995; Dowling & Morgans 2005; Zhao et al. 2018).…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Thermoacoustic interplay between intrinsic thermoacoustic and acoustic modes: non-normality and high sensitivities

2019

View full text Add to dashboard Cite

show abstract

“…However, with a few exceptions (see e.g., [3,4]), most of these devices can only dampen a narrow band of frequencies. The addition of active control has also proven to be effective in laboratory combustors and full scale rigs [5][6][7]. It adapts to changing operating conditions but depends critically on the effectiveness and durability of the sensors and actuators, and is not sufficiently safe for commercial use, particularly in aircraft.…”

Section: Introductionmentioning

confidence: 99%

Thermoacoustic stabilization of a longitudinal combustor using adjoint methods

Aguilar

Juniper

2020

Phys. Rev. Fluids

View full text Add to dashboard Cite

We construct a low order thermoacoustic network model that contains the most influential physical mechanisms of a thermoacoustic system. We apply it to a laboratory-scale longitudinal combustor that has been found to be thermoacoustically unstable in experiments. We model the flame, which is behind a bluff body, by a geometric level set method. We obtain the thermoacoustic eigenvalues of this configuration and examine a configuration in which six eigenmodes are unstable. We then derive the adjoint equations of this model and use the corresponding adjoint eigenmodes to obtain the sensitivities of the unstable eigenvalues to modifications of the model geometry. These sensitivities contain contributions from changes to the steady base flow and changes to the fluctuating flow. We find that these two contributions have similar magnitudes, showing that both contributions need to be considered. We then wrap these sensitivities within a gradient-based optimization algorithm and stabilize all six eigenvalues by changing the geometry. The required geometry changes are well approximated by the first step in the optimization process, showing that this sensitivity information is useful even before it is embedded within an optimization algorithm. We examine the acoustic energy balance during the optimization process and identify the physical mechanisms through which the algorithm is stabilizing the combustor. The algorithm works by, for each mode, reducing the work done by the flame, while simultaneously increasing the work done by the system on the outlet boundary. We find that only small geometry changes are required in order to stabilize every mode. The network model used in this study deliberately has the same structure as one used in the gas turbine industry in order to ease its implementation in practice. * Now at Norges teknisk-naturvitenskapelige universitet (NTNU);

show abstract

“…This robust control methodology has been applied to a wide variety of practical systems, such as general industrial applications, e.g., electric power systems including permanent magnet synchronous motors which are favorable in transportation [31], electromechanical [32] and electro-hydraulic systems [33], and robotics including multitude of medical usages like robotic scalpel position control [34] or control for lower limb rehabilitation as well [35]. Furthermore, aerospace controls are also involved, like space manipulators [36], thrust-vector control for spacecraft landing [37] active suppression for combustion instabilities [38], or limit protection control for gas turbine engines [39] as well as setpoint tracking control with output constraints for turbofans [40].…”

Section: Introductionmentioning

confidence: 99%

Sliding Mode Control for Micro Turbojet Engine Using Turbofan Power Ratio as Control Law

Derbel

Beneda

2020

Energies

View full text Add to dashboard Cite

The interest in turbojet engines was emerging in the past years due to their simplicity. The purpose of this article is to investigate sliding mode control (SMC) for a micro turbojet engine based on an unconventional compound thermodynamic parameter called Turbofan Power Ratio (TPR) and prove its advantage over traditional linear methods and thrust parameters. Based on previous research by the authors, TPR can be applied to single stream turbojet engines as it varies proportionally to thrust, thus it is suitable as control law. The turbojet is modeled by a linear, parameter-varying structure, and variable structure sliding mode control has been selected to control the system, as it offers excellent disturbance rejection and provides robustness against discrepancies between mathematical model and real plant as well. Both model and control system have been created in MATLAB® Simulink®, data from real measurement have been taken to evaluate control system performance. The same assessment is conducted with conventional Proportional-Integral-Derivative (PID) controllers and showed the superiority of SMC, furthermore TPR computation using turbine discharge temperature was proven. Based on the results of the simulation, a controller layout is proposed and its feasibility is investigated. The utilization of TPR results in more accurate thrust output, meanwhile it allows better insight into the thermodynamic process of the engine, hence it carries an additional diagnostic possibility.

show abstract

A review of active control approaches in stabilizing combustion systems in aerospace industry

Cited by 179 publications

References 144 publications

Thermoacoustic interplay between intrinsic thermoacoustic and acoustic modes: non-normality and high sensitivities

Thermoacoustic interplay between intrinsic thermoacoustic and acoustic modes: non-normality and high sensitivities

Thermoacoustic stabilization of a longitudinal combustor using adjoint methods

Sliding Mode Control for Micro Turbojet Engine Using Turbofan Power Ratio as Control Law

Contact Info

Product

Resources

About