Thermodynamic analysis of a gas turbine engine with a rotating detonation combustor

Sousa, Jorge; Paniagua, Guillermo; Morata, Elena Collado

doi:10.1016/j.apenergy.2017.03.045

Cited by 204 publications

(52 citation statements)

References 25 publications

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“…9 Significant impetus has been directed in recent years oriented toward practical application of detonation combustion through two devices-PDCs 38 and RDCs. 39 The first of these practical combustors, the PDC, was developed in the 1940s. 40 The PDC is a device which periodically consumes reactants using a detonation.…”

Section: Pulse Detonation Combustorsmentioning

confidence: 99%

“…11 This effect has been proposed to produce a significant increase in thermodynamic efficiency, thereby producing a step-change increment in the efficiency of gas-turbine engines. For instance, rotating detonation combustors (RDCs) have been proposed to cause: an increase of up to 9% in fuel efficiency, 11 an increase of up to 15% in the total pressure in the combustor due to detonation, 12 an increase of 5% in thermal efficiency, 13 and finally up to 14% increase in power plant efficiency over conventional J class turbines. 14 While these forecasts are highly promising, the associated emissions characteristics of these devices are to be given equal importance to use them in any practical applications.…”

Section: Introductionmentioning

confidence: 99%

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A review of pollutants emissions in various pressure gain combustors

Anand

Gutmark

2019

International Journal of Spray and Combustion Dynamics

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Recent years have witnessed a significant growth in the advancement and study of various unsteady combustors because of the prospective stagnation pressure gain offered by them. The pressure gain combustion produced by this class of combustors is poised to produce a step-change increase in the thermodynamic efficiency of gas-turbine engines. The current manuscript is oriented toward presenting a review on the pollutant emission characteristics of these devices; specifically, studies done so far on wave rotor combustors, pulsejet combustors, pulse detonation combustors, and rotating detonation combustors are evaluated. Because of the inherent fluid dynamic unsteadiness peculiar to pressure gain combustion devices, their emissions behavior is not well understood, and is notably different from the more conventional, steady combustors. The global view provided herein is expected to further the understanding of pressure gain combustion systems and ascertain the practicality of implementing them in real-world applications.Â Time in mode hr ð ÞOf the above terms, the time of operation cannot be altered since it is mission specific. This implies that

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Section: Pulse Detonation Combustorsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A review of pollutants emissions in various pressure gain combustors

Anand

Gutmark

2019

International Journal of Spray and Combustion Dynamics

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“…Sci. 2019, 9,x FOR PEER REVIEW 19 of 24 in the increasing of the Mach number. Since the outlet of RDC with θ = 0° has flowed at supersonic speed, the supersonic flow of the outlet due to the diverging nozzle is reasonable and acceptable.…”

Section: Effect Of Different Diverging Nozzles On Temperature Parametersmentioning

confidence: 99%

“…Outlet parameters of RDC, mainly including temperature, pressure, and Mach number, directly determine the thrust [7,8], thermal efficiency [9][10][11], and combustor-turbine integration [12][13][14] of RDC-based engines. Therefore, the unsteady outlet flow field control of the RDC with different nozzles is one focus of current research.…”

Section: Introductionmentioning

confidence: 99%

Effects of Diverging Nozzle Downstream on Flow Field Parameters of Rotating Detonation Combustor

Sun

Zheng

et al. 2019

Applied Sciences

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Featured Application: Provide basis for rotating detonation combustor applications on gas turbine.Abstract: In this study, three-dimensional numerical studies have been performed to investigate the performance of a rotating detonation combustor with a diverging nozzle downstream. The effects of a diverging nozzle on the formation and propagation process of a detonation wave and typical flow field parameters in a rotating detonation combustor are mainly discussed. The results indicate that the diverging nozzle downstream is an important factor affecting the performance and design of a rotating detonation combustor. The diverging nozzle does not affect the formation and propagation process of the rotating detonation wave, while the time of two key wave collisions are delayed during the formation process of the detonation wave. With increases of the diverging angle, the rotating detonation combustor with the diverging nozzle can still maintain a certain pressure gain performance. Both the diverging nozzle and diverging angle have great influence on the flow field parameters of the rotating detonation combustor, including reducing the high pressure and temperature load, making the distribution of the outlet parameters uniform, and changing the local supersonic flow at the outlet. Among them, the outlet static pressure is reduced by up to 88.32%, and the outlet static temperature is reduced by up to 32.12%. This evidently improves the working environment of the combustor while reducing the thermodynamic and aerodynamic loads at the outlet. In particular, the diverging nozzle does not affect the supersonic characteristics of the outlet airflow, and on this basis, the Mach number becomes coincident and enhanced.

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“…This turning (and consequent power extraction) is constrained by the Kantrowitz limit that sets the maximum flow angle. Through an engine analysis, it was proven that for supersonic flights, a low-pressure ratio turbojet equipped with a supersonic turbine could be up to 5% more fuel efficient than conventional turbojet engines [10].…”

Section: Introductionmentioning

confidence: 99%

Design and Experimental Assessment of Bladeless Turbines for Axial Inlet Supersonic Flows

Braun

Paniagua

Falempin

et al. 2020

Journal of Engineering for Gas Turbines and Power

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Supersonic inlet flow is usually considered to be detrimental to the performance of turbine systems. A new class of bladeless turbines was developed, which allows for power extraction from supersonic axial inflows without swirl with minimal maintenance cost. This is achieved through a wavy hub surface that promotes shocks and expansion fans and hence generates torque. In a first step, a baseline bladeless turbine is designed and the power extraction is analyzed. The bladeless turbine surface is parametrized in matlab and subsequently imported into Hexpress (Numeca) to mesh an unstructured grid. The first layer thickness is kept below one for all the simulations. The unstructured mesh is loaded into cfd++ (Metacomp) to solve the three dimensional steady Reynolds-averaged Navier–Stokes (RANS) equations. Second, the work extraction principle is broken down from a three-dimensional unsteady problem into a two-dimensional steady phenomenon. An experimental campaign is outlined and test details are discussed. Finally, after the experimental characterization, the operational envelope and scaling of the bladeless turbine are described for several reduced mass flows, reduced speeds, and geometrical features of the turbine (amplitude of the wavy surface, helix angle, hub radius, and length of the axial turbine).

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Thermodynamic analysis of a gas turbine engine with a rotating detonation combustor

Cited by 204 publications

References 25 publications

A review of pollutants emissions in various pressure gain combustors

A review of pollutants emissions in various pressure gain combustors

Effects of Diverging Nozzle Downstream on Flow Field Parameters of Rotating Detonation Combustor

Design and Experimental Assessment of Bladeless Turbines for Axial Inlet Supersonic Flows

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