Investigation of pulse detonation combustors — Axial turbine system

Anand, Vijay; George, Andrew St.; Knight, Ethan; Gutmark, Ephraim

doi:10.1016/j.ast.2019.105350

Cited by 28 publications

(5 citation statements)

References 19 publications

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“…Another experiment was carried out by Anand [54] as a circular array of six detonation combustors is attached to an axial turbine. PDCs were operated at 5, and 10Hz under serval fill and purge fractions.…”

Section: Cooperating Workmentioning

confidence: 99%

Pulse Detonation Engine Performance Analysis

Xiao

Zheng

et al. 2023

J. Phys.: Conf. Ser.

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A brief retroversion is conducted on the developments of pulse detonation engines over these decades. Attempts are made to cover performance analysis, nozzle effects, partial filling, and cooperating work. Researchers have spared no effort to establish accurate models to describe the unsteady nature of pulse detonation engines while the accuracy is relatively just as it comes at the price of more or less simplification. Nozzle design would make a great difference to the ultimate performance as numerical simulations have proved nozzle shape, as well as expansion ratio, needs precisely devised. The partial filling has an impact on specific impulses by altering the pressure relaxation process which is testified by numerical simulations and experiments. Component matching brings a challenge to engineering practice due to the comprehensive and complicated co-reaction between every part of the engine. How to reconcile different components remains a fatal issue as many institutes have done amounts of work to demonstrate the feasibility of such a novel propulsion option.

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Section: Cooperating Workmentioning

confidence: 99%

Pulse Detonation Engine Performance Analysis

Xiao

Zheng

et al. 2023

J. Phys.: Conf. Ser.

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“…The performance of turbines in unsteady flow is the subject of long-term research. Very active in turbocharging, it is currently also stimulated by the prospect of breakthroughs in aeronautical propulsion [1][2][3][4]. Engine cycles with constant volume combustion (CVC) should improve the thermal efficiency of such devices, at least on the theoretical ground.…”

Section: Introductionmentioning

confidence: 99%

Physics of the Unsteady Response of Turbine Cascade to Pulsed Flow Conditions

Bertojo,

Binder,

Gressier

2024

IJTPP

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The present contribution is in direct continuation of previous work which aimed at demonstrating the possible benefit of the unsteady feeding of turbines. Some numerical analyses of the flow inside a skeletal cascade revealed that instantaneous overloading occurs on the blades. However, such an academic case is far from a realistic configuration. The present paper investigates the influence of a simplified thickness distribution to check whether the instantaneous benefit is still observed. Based on numerical simulations, an analysis of the physical origin of the overloading is proposed on a single blade. It results in the choice of a triangular thickness distribution, which should promote the physical phenomena responsible for the overloading. A parametric study of such a distribution demonstrates that it is possible to obtain instantaneous performance very close to the optimum of the flat plate. Conclusions drawn from the single-blade analysis are extended to cascades and stator–rotor configurations and show an increase in the complexity of physical phenomena. Ultimately, the aim is to optimize the geometric shape to obtain maximum overloading. Consequently, the same type of study was carried out for the expansion phase, and similar results were obtained.

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“…The advantages of pressure gain and higher thermodynamic efficiency of detonation combustion demonstrate its great potential for application in propulsion systems [1,2]. There are three representative realization forms of detonation engine according to the stabilization method of detonation wave: rotating detonation engine (RDE) [3], pulse detonation engine (PDE) [4] and oblique detonation engine (ODE) [5]. RDE is considered as a feasible application due to the steady thrust performance.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of ethylene-fueled ramjet rotating detonation engine with an annular combustor

Feng

Zheng

Xiao

et al. 2023

J. Phys.: Conf. Ser.

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A ramjet-mode rotating detonation engine fueled by ethylene is designed to demonstrate the feasibility of rotating detonation organization in annular combustor under high-speed incoming flow condition. The incoming flow with the design total temperature of 860 K and Mach number of 2 at the isolator inlet is provided by an air-heater, and the total mass flow is about 1.0 kg/s. The results show that the ramjet rotating detonation engine can operate in detonation mode when the equivalence ratio (ER) is no less than 0.54. By high-frequency pressure analysis and optical observation, two propagation modes of detonation wave are observed: rotating detonation in the ER range of 0.54-0.71 and longitudinally pulsating detonation in the ER range of 0.82-0.97. In rotating detonation mode, the wave velocity increases as ER increases, and the detonation velocities are about 60% of the CJ value. In longitudinally pulsating detonation mode, the propagation frequencies of the detonation wave are in the range of 1010 Hz-1017 Hz, which is much lower than that in rotating detonation mode, and the upstream propagation velocity of the detonation wave is estimated as 964 m/s. In addition, the maximum static pressure in the combustor increases with the ER from 0.54 to 0.97, and reaches 0.24 MPa when ER is 0.97. When ER is no more than 0.58, the isolator can effectively suppress the back pressure in the combustor, while ER is no less than 0.71, the back pressure in the combustor affects the flow at the isolator inlet, which implies that the isolator design needs to be optimized.

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Investigation of pulse detonation combustors — Axial turbine system

Cited by 28 publications

References 19 publications

Pulse Detonation Engine Performance Analysis

Pulse Detonation Engine Performance Analysis

Physics of the Unsteady Response of Turbine Cascade to Pulsed Flow Conditions

Experimental investigation of ethylene-fueled ramjet rotating detonation engine with an annular combustor

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