Shockless Explosion Combustion: An Innovative Way of Efficient Constant Volume Combustion in Gas Turbines

Bobusch, Bernhard C.; Berndt, Phillip; Paschereit, Christian Oliver; Klein, Rupert

doi:10.1080/00102202.2014.935624

Cited by 52 publications

(29 citation statements)

References 13 publications

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“…1.0xe 5 1.0xe 8 1.0xe 11 1.0xe 14 dp/dt, (Pa This phenomenon is due to the extremely fast interaction between the energy released and the corresponding temperature rise from the combustion reaction which in turn feeds back to produce constantly increasing reaction rates because of the dependence of temperature on the reaction rate, that is, (-E a /RT), where E a is the activation energy. Figures 5 and 6 show the variation of heat of combustion at the top dead center position versus compression ratio and adiabatic flame temperature for compression ratios in the range 9.5 ≤ r c ≤ 11.5 respectively.…”

Section: Resultsmentioning

confidence: 99%

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Combustion dynamics at the top dead center position of a spark ignition engine

Anetor¹,

Osakue²,

Odetunde³

2017

FME Transaction

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A zero-dimensional spark ignition engine model was used to conduct a systematic study of combustion dynamics at the top dead center (TDC) position of a 5.734 liter, V8 spark-ignition engine. The model captures all the experimentally observed essential features concerning combustion at the TDC. The combustion dynamics at compression ratios, r c = 9.5, 10.5, 11.5 and 15.5 and fuel-air equivalence ratio, ϕ = 1.0 were investigated with the numerical model. The results show that for r c = 15.5, the fueloxidizer charge was consumed almost instantaneously. Furthermore, the data shows that it took about 153.0, 52.6, 21.0 and 1.43 ms at compression ratios, r c of 9.5, 10.5, 11.5 and 15.5 respectively for the in-cylinder combustion dynamics to reach a value T * = 1.0. In the last 0.01 ms, for all compression ratios, the rate of change of pressure, dp/dt lies in the range 10 8 < dp/dt < 10 14 Pa/s while the corresponding temperature varies from 2230 ≤ T ≤ 2700 K. The study also shows that as the compression ratio increases both the adiabatic flame temperature and heat of combustion at the top dead center increases monotonically as well.

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Section: Resultsmentioning

confidence: 99%

“…However, ∆t was gradually reduced as T * = (T-T i )/(T ad -T i ) → 1.0, in order to preserve accuracy. Simulations are terminated when 8 18 0 C H ω ≤ and the flame is extinguished, that is, the fuel (C 8 H 18 ) has been totally consumed.…”

Section: Numerical Solutionmentioning

confidence: 99%

Combustion dynamics at the top dead center position of a spark ignition engine

Anetor¹,

Osakue²,

Odetunde³

2017

FME Transaction

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“…However, it is quite difficult to improve the cycle efficiency in conventional gas turbines due to the high entropy change during the combustion process [1,2]. In order to break through the bottleneck of efficiency improvement, various advanced combustion technologies, including detonation [3][4][5], wave rotors [6], and shockless explosion [7,8] were studied in the past few decades.…”

Section: Introductionmentioning

confidence: 99%

Investigation of the Pressure Gain Characteristics and Cycle Performance in Gas Turbines Based on Interstage Bleeding Rotating Detonation Combustion

Wang

Zhao

et al. 2019

Entropy

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To further improve the cycle performance of gas turbines, a gas turbine cycle model based on interstage bleeding rotating detonation combustion was established using methane as fuel. Combined with a series of two-dimensional numerical simulations of a rotating detonation combustor (RDC) and calculations of cycle parameters, the pressure gain characteristics and cycle performance were investigated at different compressor pressure ratios in the study. The results showed that pressure gain characteristic of interstage bleeding RDC contributed to an obvious performance improvement in the rotating detonation gas turbine cycle compared with the conventional gas turbine cycle. The decrease of compressor pressure ratio had a positive influence on the performance improvement in the rotating detonation gas turbine cycle. With the decrease of compressor pressure ratio, the pressurization ratio of the RDC increased and finally made the power generation and cycle efficiency enhancement rates display uptrends. Under the calculated conditions, the pressurization ratios of RDC were all higher than 1.77, the decreases of turbine inlet total temperature were all more than 19 K, the power generation enhancements were all beyond 400 kW and the cycle efficiency enhancement rates were all greater than 6.72%.

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“…This so-called pressure gain combustion (PGC) can be accomplished by different means. The leading paths are pulse detonation (Roy et al, 2004;Pandey and Debnath, 2016), rotating detonation (Zhou et al, 2016;Kailasanath, 2017;Paxson and Naples, 2017), wave rotors (Akbari and Nalim, 2009;McClearn et al, 2016) and shockless explosion (Bobusch et al, 2014;Reichel et al, 2016) combustion. Some other concepts are the piston topping (Kaiser et al, 2015) and the nutating disk (Meitner et al, 2006).…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic assessment of a highly loaded high pressure compressor exposed to pressure gain combustion disturbances

Almeida

Peitsch

2018

J. Glob. Power Propuls. Soc.

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A numerical aeroelastic assessment of a highly loaded high pressure compressor exposed to flow disturbances is presented in this paper. The disturbances originate from novel, inherently unsteady, pressure gain combustion processes, such as pulse detonation, shockless explosion, wave rotor or piston topping composite cycles. All these arrangements promise to reduce substantially the specific fuel consumption of present-day aeronautical engines and stationary gas turbines. However, their unsteady behavior must be further investigated to ensure the thermodynamic efficiency gain is not hindered by stage performance losses. Furthermore, blade excessive vibration (leading to high cycle fatigue) must be avoided, especially under the additional excitations frequencies from waves traveling upstream of the combustor. Two main numerical analyses are presented, contrasting undisturbed with disturbed operation of a typical industrial core compressor. The first part of the paper evaluates performance parameters for a representative blisk stage with high-accuracy 3D unsteady Reynolds-averaged Navier-Stokes computations. Isentropic efficiency as well as pressure and temperature unsteady damping are determined for a broad range of disturbances. The nonlinear harmonic balance method is used to determine the aerodynamic damping. The second part provides the aeroelastic harmonic forced response of the rotor blades, with aerodynamic damping and forcing obtained from the unsteady calculations in the first part. The influence of blade mode shapes, nodal diameters and forcing frequency matching is also examined.

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Shockless Explosion Combustion: An Innovative Way of Efficient Constant Volume Combustion in Gas Turbines

Cited by 52 publications

References 13 publications

Combustion dynamics at the top dead center position of a spark ignition engine

Combustion dynamics at the top dead center position of a spark ignition engine

Investigation of the Pressure Gain Characteristics and Cycle Performance in Gas Turbines Based on Interstage Bleeding Rotating Detonation Combustion

Aeroelastic assessment of a highly loaded high pressure compressor exposed to pressure gain combustion disturbances

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