Analytical Model for the Performance Estimation of Pre-Cooled Pulse Detonation Turbofan Engines

Xisto, Carlos; Ali, Fakhre; Petit, Olivier; Grönstedt, Tomas; Rolt, Andrew; Lundbladh, Anders

doi:10.1115/gt2017-63776

Cited by 11 publications

(16 citation statements)

References 27 publications

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“…Furthermore, these models were investigated in a gas turbine engine from a thermodynamic perspective such as in (Snyder & Nalim, 2012). Studies on the integration into a gas turbine using realistic side conditions have been performed by (Grönstedt, et al, 2014), (Xisto, et al, 2017), (Sousa, et al, 2017) and (Stathopoulos, 2018). Still, complete gas turbine optimisations regarding thermal efficiency for various combustor models and their comparison using realistic constraints are not yet available.…”

Section: Introductionmentioning

confidence: 99%

A Comparison of Steady-State Models for Pressure Gain Combustion in Gas Turbine Performance Simulation

Neumann¹,

Woelki²,

Peitsch³

2019

Proceedings of Global Power &Amp; Propulsion Society

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Pressure gain combustion (PGC) is widely considered to improve gas turbine thermal efficiency substantially. However, there is no consensus on the modelling in gas turbine performance simulation. Even though it remains the main tool for design studies, the steady-state 0D representation has difficulties in modelling the inherently intermittent behaviour of pressure gain combustion. Selecting the optimal gas turbine design is therefore difficult as common PGC models tend to under-or overestimate performance. In this paper, an algebraic combustor model is inferred from published CFD data and varied to have an optimistic and pessimistic representation. These models among others will be used in an optimisation to identify the best gas turbine design with respect to thermal efficiency. The consideration of the secondary air system and blade metal temperatures ensure a realistic case study. At the end of this paper, sensitivity studies shed light on cycle design at uncertain combustor performance. The selected PGC models achieve an improvement in thermal efficiency between 3.8-6.6 percentage points compared to conventional isobaric combustion. However, this is less than half the 13.3 percentage points gain promised by ideal isochoric combustion.

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Section: Introductionmentioning

confidence: 99%

A Comparison of Steady-State Models for Pressure Gain Combustion in Gas Turbine Performance Simulation

Neumann¹,

Woelki²,

Peitsch³

2019

Proceedings of Global Power &Amp; Propulsion Society

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show abstract

“…Individual combustor models were investigated in a gas turbine engine from a thermodynamic perspective such as in [20]. Studies on the integration into a gas turbine using realistic side conditions were performed by [1,[21][22][23]. Complete gas turbine optimizations regarding thermal efficiency for various combustor models and their comparison under realistic constraints were published by this author in [19].…”

Section: Introductionmentioning

confidence: 99%

Potentials for Pressure Gain Combustion in Advanced Gas Turbine Cycles

Neumann

Peitsch

2019

Applied Sciences

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Pressure gain combustion evokes great interest as it promises to increase significantly gas turbine efficiency and reduce emissions. This also applies to advanced thermodynamic cycles with heat exchangers for intercooling and recuperation. These cycles are superior to the classic Brayton cycle and deliver higher specific work and/or thermal efficiency. The combination of this revolutionary type of combustion in an intercooled or recuperated gas turbine cycle can, however, lead to even higher efficiency or specific work. The research of these potentials is the topic of the presented paper. For that purpose, different gas turbine setups for intercooling, recuperation, and combined intercooling and recuperation are modeled in a gas turbine performance code. A secondary air system for turbine cooling is incorporated, as well as a blade temperature evaluation. The pressure gain combustion is represented by analytical-algebraic and empirical models from the literature. Key gas turbine specifications are then subject to a comprehensive optimization study, in order to identify the design with the highest thermal efficiency. The results indicate that the combination of intercooling and pressure gain combustion creates synergies. The thermal efficiency is increased by 10 percentage points compared to a conventional gas turbine with isobaric combustion.

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“…Since viscosity was ignored in this study, a laminar finite rate model is acceptable for combustion with relatively small turbulence-chemistry interactions (such as detonation) according to the author's experience. Additionally, the numerical results of Wang [30], Xisto et al [31], and Liu et al [32] indicate that a laminar finite rate model can effectively describe many fundamental combustion and detonation phenomena. Therefore, a laminar finite rate model was selected as the chemical reaction model in this study.…”

mentioning

confidence: 99%

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

Zheng

Zhao

et al. 2018

Applied Sciences

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Considering the potential applications of continuously rotating detonation (CRD) combustors in gas turbines, this paper performed a numerical investigation into the pressure gain performance of CRD combustors, using methane-air as a reactive mixture and under the operating conditions of a micro gas turbine. To analyze the formation process of CRD waves, the variation characteristics of several typical thermodynamic parameters involving thermal efficiency, pressure ratio, and available energy loss were discussed in terms of time and space scales. Numerical results showed that the pressure gain characteristics of the CRD combustors was associated with the corresponding change in Gibbs free energy. Compared to approximate constant pressure-based combustors, usually used in the gas turbines studied, CRD combustors with lower Gibbs free energy loss could offer a significant advantage in terms of pressure ratio. It was found that detonation waves played an important role in increasing pressure ratios but that oblique shock waves caused the loss of extra Gibbs free energy. Due to the changing oblique shock wave height, the effects of CRD combustor axial length on pressure ratios and Gibbs free energy loss were more significant than the effects on detonation wave propagating characteristics and combustion thermal efficiency. When the axial length was changed from 200 mm to 100 mm, the pressure ratio increased by approximately 15.8%.

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Analytical Model for the Performance Estimation of Pre-Cooled Pulse Detonation Turbofan Engines

Abstract: This paper proposes a pulse detonation combustion (PDC) model integrated within Chalmers University's gas turbine simulation tool GESTPAN (GEneral Stationary and Transient Propulsion ANalsysis

Cited by 11 publications

References 27 publications

A Comparison of Steady-State Models for Pressure Gain Combustion in Gas Turbine Performance Simulation

A Comparison of Steady-State Models for Pressure Gain Combustion in Gas Turbine Performance Simulation

Potentials for Pressure Gain Combustion in Advanced Gas Turbine Cycles

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

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