A swirler stabilized combustion chamber for a micro-gas turbine fuelled with natural gas

Krieger, G.; Campos, André P. V. de; Filho, Fernando Luiz Sacomano; Souza, Rafael Cavalcanti de

doi:10.1590/s1678-58782012000400004

Cited by 17 publications

(9 citation statements)

References 8 publications

(9 reference statements)

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“…Design and manufacturing of combustion chamber for use with T/C has already been demonstrated, achieving a turbine inlet temperature of about 800 • C [26,27].…”

Section: Design and Operation Aspectsmentioning

confidence: 99%

“…For the design specifications of Table 1, power and thermal efficiency are evaluated and depicted in Figure 2. Power increases with TIT, while thermal efficiency achieves a maximum for TIT of 850 • C. Here, three cases of turbine inlet temperature are studied: (a) 400 • C, because it is the nominal inlet turbine temperature of the T/C; (b) 800 • C, because it is the maximum one experimentally demonstrated [26,27] (while we are not sure if it is in within the limits of the specific T/C used in this work); and (c) 600 • C, the intermediate of the two in order to establish a performance trend.…”

Section: Design and Operation Aspectsmentioning

confidence: 99%

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Solar Hybrid Micro Gas Turbine Based on Turbocharger

Kalathakis

Aretakis

Mathioudakis

2018

ASI

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The performance of solar hybrid Brayton cycle materialized by a micro-gas turbine based on a turbocharger is studied. The use of a turbocharger is aimed at investment cost reduction and construction simplification. Two configurations are investigated, namely hybrid and solar-only. Design aspects are discussed, in view of the requirement for minimizing the cost of electricity produced. A key parameter is the turbine inlet temperature and its effect on performance is investigated. The effect of heliostat field size is also investigated. Augmentation of the maximum temperature leads to better performance, as a result of higher cycle efficiency. Solar-only configuration features are compared with hybrid ones and the contribution of different cost components to the final electricity cost is discussed.

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“…Design and manufacturing of combustion chamber for use with T/C has already been demonstrated, achieving a turbine inlet temperature of about 800 • C [26,27].…”

Section: Design and Operation Aspectsmentioning

confidence: 99%

Section: Design and Operation Aspectsmentioning

confidence: 99%

Solar Hybrid Micro Gas Turbine Based on Turbocharger

Kalathakis

Aretakis

Mathioudakis

2018

ASI

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“…The air incoming through is slower, due to the wider space it occupies and due to the losses in entering the chamber through small, 1 cm-diameter holes; consequently, holes' ANSYS Fluent software has been used to simulate each swirler alone and, subsequently, a wider portion of the chamber. Since this problem is strongly related to turbulent stress generations [22], second moment closure is an appropriate [17,23,24] way of treating it: its higher computational cost with respect to a standard k-model, however, limited the size of the simulation domain, limiting it to one (two in the final simulation) swirler at a time. In Fluent, this is called the Reynolds stress model (RSM), and it solves each stress generation component (uu, vv, ww, uv, uw, vw).…”

Section: Fuel Injection Modellingmentioning

confidence: 99%

Design and Optimization of Fuel Injection of a 50 kW Micro Turbogas

Capata

Achille

2018

Designs

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Abstract:The present article deals with the design of a micro turbogas turbine suitable for on board applications, e.g., as a power generator on hybrid transit bus, characterized by a simple constructive approach. Deriving the machine layout from an existing KJ-66 aircraft model engine, the authors propose a theoretical design of a compact, lightweight turbogas turbine, by investigating the technical possibility and limits of the proposed design. In particular, a different combustion chamber layout has been proposed, and fuel adduction channels for different swirler designs have been simulated via ANSYS Fluent in order to identify a satisfactory fuel spreading. As a result, the complete characterization of the design parameters and geometries has been performed, and a series of RANS simulations has been used in order to identify an optimal swirler configuration.

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“…However, the large-scale combustors cannot be scaled down as it is due to unscalable parameters, such as characteristic combustion time (Van den Braembussche 2005). Hence, modification in the combustor design is required for making the combustor compact e.g., reverse flow combustor (Krieger et al 2012). On the other hand, the volume of combustor is a scalable parameter.…”

Section: Introductionmentioning

confidence: 99%

Study of Flow Field Inside a Can Combustor for Micro Gas Turbine Engine Under Nonreacting Flow Conditions

Vijayakumar

Bhatt

2021

J. Aerosp. Technol. Manag.

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Generally, micro gas turbines are in the range of 15 to 300 kW. However, recent applications in unmanned aerial vehicles (UAVs) and polygeneration require a small micro gas turbine. So, here a small swirl combustor designed for micro gas turbine engine of capacity less than 1 kW is analyzed under nonreacting flow conditions. Simulations have been carried out to study the flow field inside the can combustor. Flow field characteristics, like velocity, path lines, turbulent intensity and total pressure loss are studied. The total pressure loss across the combustor is also measured experimentally and compared with that of simulation results. Good agreement is achieved between experimental and numerical results. The combustor total pressure drop was found to be negligible in the range of 0.002 to 0.06% at an inlet velocity ranges from 1.7 to 10.19 m/s. Flow pattern indicates a strong swirling pattern and strong interaction between the secondary air entrainment inside the flame tube.

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A swirler stabilized combustion chamber for a micro-gas turbine fuelled with natural gas

Abstract: Micro

Cited by 17 publications

References 8 publications

Solar Hybrid Micro Gas Turbine Based on Turbocharger

Solar Hybrid Micro Gas Turbine Based on Turbocharger

Design and Optimization of Fuel Injection of a 50 kW Micro Turbogas

Study of Flow Field Inside a Can Combustor for Micro Gas Turbine Engine Under Nonreacting Flow Conditions

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