Thermodynamic Evaluation of Pulse Detonation Combustion for Gas Turbine Power Cycles

Abstract

Constant-volume (pressure-gain) combustion cycles show much promise for further increasing the efficiency of modern gas turbines, which in the last decades have begun to reach the boundaries of modern technology in terms of pressure and temperature, as well as the ever more stringent demands on reducing exhaust gas emissions. The thermodynamic model of the gas turbine consists of a compressor with a polytropic efficiency of 90%, a combustor modeled as either a pulse detonation combustor (PDC) or as an isobaric homogeneous reactor, and a turbine, the efficiency of which is calculated using suitable turbine operational maps. A simulation is conducted using the one-dimensional reacting Euler equations to obtain the unsteady PDC outlet parameters for use as turbine inlet conditions. The efficiencies for the Fickett–Jacobs and Joule cycles are then compared. The Fickett–Jacobs cycle shows promise at relatively low compressor pressure ratios, whereas the importance of the harvesting of exhaust gas kinetic energy for the cycle performance is highlighted.

Enhancement of the transition to detonation of a turbulent hydrogen–air flame by nanosecond repetitively pulsed plasma discharges

“…The need for more efficient cycles for combustion-based energy production has led to much attention being paid to pressure-gain combustion cycles in recent years (e.g., [1][2][3][4][5][6]). These cycles are inherently more efficient and will allow not only for an easier transition to but also, when utilizing hydrogen as a fuel, an efficient coupling with renewable energy sources in the future [7][8][9].…”

A Thermodynamic Analysis of the Pressure Gain of Continuously Rotating Detonation Combustor for Gas Turbine

“…For example, researchers from a U.S. naval research laboratory reported that CRD-based engines had the potential to meet 10% increased power requirements, as well as reduce future fuel use by 25%, which could save approximately 300 to 400 million dollars a year [11]. Gray et al [12] and Sousa et al [13] quantitatively evaluated the thermodynamic benefits of gas turbines equipped with CRD combustors versus conventional technology using constant pressure combustion, under different operating conditions. Their analyses consistently demonstrated the significant promise of CRD combustors at relatively low compressor pressure ratios.…”

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

“…Some other concepts are the piston topping (Kaiser et al, 2015) and the nutating disk (Meitner et al, 2006). All these setups are theoretically supported by substantial thermodynamic gains, described in detail, e.g., by (Heiser and Pratt, 2002;Gray et al, 2016).…”