Thermodynamic analysis of recuperative gas turbines and aero engines

Salpingidou, Christina; Vlahostergios, Zinon; Misirlis, Dimitrios; Donnerhack, Stefan; Flouros, Michael; Goulas, A.; Yakinthos, K.

doi:10.1016/j.applthermaleng.2017.05.169

Cited by 25 publications

(9 citation statements)

References 14 publications

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“…This situation presents an enormous opportunity for gas turbines of stationary power applications because it means that major performance improvements can be made with relatively modest R&D efforts . For this reason, many scientists are still working on gas turbine cycle improvements …”

Section: Introductionmentioning

confidence: 99%

“…1 For this reason, many scientists are still working on gas turbine cycle improvements. [2][3][4][5][6][7][8] Among the proven "low-technology" modifications mentioned earlier, steam injection is found to be the most effective in boosting the output capacity and thermal efficiency while reducing NO x emissions of gas turbines. 9 At the same time, steam injected gas turbine (STIG) plants have several advantages over combined cycle units although CC units would be more efficient because of the expansion of the steam content into vacuum.…”

Section: Introductionmentioning

confidence: 99%

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Thermoenvironomic evaluation of simple, intercooled, STIG, and ISTIG cycles

Kayadelen

Üst

2018

Int J Energy Res

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Summary Low‐technology cycle modifications available for improving gas turbine performance are still largely unexploited. Among those proven modifications, steam injection is found to be the most effective in boosting both the output capacity and thermal efficiency while reducing NOx emissions. It further improves part load performance under varying ambient conditions. Intercooling is another low‐technology modification which can improve performance of simple and steam injected gas turbine cycles. Because of the uncertainties relating to an efficiency comparison of steam injected and simple cycle designs, the decision as to whether it is worthwhile to give more emphasis to steam injected cycles should be made on grounds other than efficiency alone. Therefore, this study comparatively evaluates simple, intercooled, steam injected (STIG), and intercooled steam injected (ISTIG) gas turbine cycles from the points of efficiency, network output, economics, and pollutant emissions using an advanced validated thermoenvironomic model. Optimum cycle parameters are investigated. Economic feasibility of steam injection and intercooling on simple and intercooled cycles are evaluated using an updated plant cost data. Total and environmental costs as well as profit of the plant owner are estimated for varying fuel costs and varying cycle parameters such as pressure, steam injection, and equivalence ratio. Results of our analysis based on the characteristic cycle parameters show that network output increases up to 22.2% and 14% respectively, when steam injection is implemented on simple and intercooled gas turbine cycles which correspond to up to 6.7% and 4.4% decrease in specific fuel consumption. Steam injection decreases NOx emissions of simple and intercooled cycles up to 67.2% and 65.2% respectively, and provides up to approximately 126.3% increase in net profit of intercooled cycle at the expense of an increase in total cost by 3.3%.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Thermoenvironomic evaluation of simple, intercooled, STIG, and ISTIG cycles

Kayadelen

Üst

2018

Int J Energy Res

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“…Another possibility for improvement is given by the management of heat flow, in order to decrease the amount of waste heat of engines that is lost to the environment. For this reason, focus is put on the recuperation of engine waste heat [16,17]. Conducted works on TE high power applications in the hot gas environment have been restricted over the years to basic assessments from estimated temperature differentials and approximated heat flux conditions [18][19][20].…”

Section: Introductionmentioning

confidence: 99%

TEG Design for Waste Heat Recovery at an Aviation Jet Engine Nozzle

2018

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Finite element model (FEM)-based simulations are conducted for the application of a thermoelectric generator (TEG) between the hot core stream and the cool bypass flow at the nozzle of an aviation turbofan engine. This work reports the resulting requirements on the TEG design with respect to applied thermoelectric (TE) element lengths and filling factors (F) of the TE modules in order to achieve a positive effect on the specific fuel consumption. Assuming a virtual optimized TE material and varying the convective heat transfer coefficients (HTC) between the nozzle surfaces and the gas flows, this work reports the achievable power output. System-level requirement on the gravimetric power density (>100 Wkg −1 ) can only be met for F ≤ 21%. When extrapolating TEG coverage to the full nozzle surface, the power output reaches 1.65 kW per engine. The assessment of further potential for power generation is demonstrated by a parametric study on F, convective HTC, and materials performance. This study confirms a feasible design range for TEG installation on the aircraft nozzle with a positive impact on the fuel consumption. This application translates into a reduction of operational costs, allowing for an economically efficient TEG-installation with respect to the cost-specific power output of modern thermoelectric materials.

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“…Since the performance of aero-engines is already exploited to a high extent and further improvement by means of known concepts seems increasingly difficult, new technologies have to be considered in order to reduce the fuel consumption and environmental pollution of future aircrafts and to move closer to the specified goals by ACARE [14] and Flightpath 2050 [15]. For this reason more attention is payed recently to the recuperation of engine waste heat [16,17]. Conducted works on TE high power applications in the hot gas environment have been restricted over the years to basic assessments from estimated temperature differentials and approximated heat flux conditions [18][19][20].…”

Section: Introductionmentioning

confidence: 99%

TEG Design for Waste Heat Recovery at an Aviation Jet Engine Nozzle

Ziółkowski¹,

Zabrocki²,

Müller³

2018

Preprint

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The application of thermoelectric generators (TEG) on the nozzle of an aviation jet engine was studied by finite element TEG-simulations. Against the background of system-level requirements of the reference aircraft this work reports the resulting requirements on the TEG design with respect to applied thermoelectric (TE) element lengths and fill factors (F) within the TE modules in order to maintain a positive effect on the specific fuel consumption. Assuming a virtual optimized TE material and varying the convective heat transfer coefficients at the nozzle surfaces this work reports the achievable power output. System-level requirement on the gravimetric power density (> 100 Wkg-1) can only be met for F ≤ 21%. Extrapolating TEG coverage to the full nozzle surface, the power output reaches 1.65 kW per engine. Assessment of further potential is demonstrated by a parametric study on the fill factor, convective heat transfer coefficients, and materials performance. This study confirms a feasible design range for TEG installation on the aircraft nozzle with a positive impact on the fuel consumption. This application translates into a reduction of operational costs, allowing for an economically efficient installation of TEG in consideration of the cost-specific power output of modern thermoelectric materials.

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Thermodynamic analysis of recuperative gas turbines and aero engines

Cited by 25 publications

References 14 publications

Thermoenvironomic evaluation of simple, intercooled, STIG, and ISTIG cycles

Thermoenvironomic evaluation of simple, intercooled, STIG, and ISTIG cycles

TEG Design for Waste Heat Recovery at an Aviation Jet Engine Nozzle

TEG Design for Waste Heat Recovery at an Aviation Jet Engine Nozzle

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