scholarly journals A review of pollutants emissions in various pressure gain combustors

2019 ◽  
Vol 11 ◽  
pp. 175682771987072 ◽  
Author(s):  
Vijay Anand ◽  
Ephraim Gutmark
Keyword(s):  
Fluid Dynamic ◽  
Pollutant Emission ◽  
Turbine Engines ◽  
Thermodynamic Efficiency ◽  
Gas Turbine Engines ◽  
Wave Rotor ◽  
Pulse Detonation ◽  
Global View ◽  
Pressure Gain Combustion ◽  
Rotating Detonation

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.

scholarly journals Wave rotor-enhanced gas turbine engines

1995 ◽  
Author(s):  
Gerard Welch ◽  
Scott Jones ◽  
Daniel Paxson
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Wave Rotor

scholarly journals A Numerical Investigation of Premixed Combustion in Wave Rotors

1996 ◽  
Author(s):  
M. Razi Nalim ◽  
Daniel E. Paxson
Keyword(s):  
Premixed Combustion ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Wave Rotor ◽  
Governing Equations ◽  
Simulation Methodology ◽  
Advantages And Disadvantages ◽  
Wave Rotors ◽  
Rotor Wall ◽  
Combustion Processes

Wave rotor cycles which utilize premixed combustion processes within the passages are examined numerically using a one-dimensional CFD-based simulation. Internal-combustion wave rotors are envisioned for use as pressure-gain combustors in gas turbine engines. The simulation methodology is described, including a presentation of the assumed governing equations for the flow and reaction in the channels, the numerical integration method used, and the modeling of external components such as recirculation ducts. A number of cycle simulations are then presented which illustrate both turbulent-deflagration and detonation modes of combustion. Estimates of performance and rotor wall temperatures for the various cycles are made, and the advantages and disadvantages of each are discussed.

scholarly journals A Numerical Investigation of Premixed Combustion in Wave Rotors

1997 ◽  
Vol 119 (3) ◽  
pp. 668-675 ◽  
Author(s):  
M. R. Nalim ◽  
D. E. Paxson
Keyword(s):  
Premixed Combustion ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Wave Rotor ◽  
Governing Equations ◽  
Simulation Methodology ◽  
Advantages And Disadvantages ◽  
Wave Rotors ◽  
Rotor Wall ◽  
Combustion Processes

Wave rotor cycles that utilize premixed combustion processes within the passages are examined numerically using a one-dimensional CFD-based simulation. Internal-combustion wave rotors are envisioned for use as pressure-gain combustors in gas turbine engines. The simulation methodology is described, including a presentation of the assumed governing equations for the flow and reaction in the channels, the numerical integration method used, and the modeling of external components such as recirculation ducts. A number of cycle simulations are then presented that illustrate both turbulent-deflagration and detonation modes of combustion. Estimates of performance and rotor wall temperatures for the various cycles are made, and the advantages and disadvantages of each are discussed.

scholarly journals The Advanced Low-Emissions Catalytic-Combustor Program: Phase I — Description and Status

1979 ◽  
Author(s):  
A. J. Szaniszlo
Keyword(s):  
Phase I ◽  
Gas Turbine ◽  
Primary Objective ◽  
Pollutant Emission ◽  
Turbine Engines ◽  
Variable Geometry ◽  
Gas Turbine Engines ◽  
Analytical Evaluation ◽  
Three Phase ◽  
Catalytic Combustor

The Advanced Low-Emissions Catalytic-Combustor Program ia an ongoing three-phase contract contract effort with the primary objective of evolving the technology required for incorporating catalytic combustors into advanced aircraft gas-turbine engines. Phase I is corrently in progress. At the present time, analytical evaluation is being conducted on advanced catalytic combustor concepts — including variable geometry — with their known inherent potential advantages of low level pollutant emission, widened combustion at ability limits, and reduced pattern factor for longer turbine life. Phases II and III will consist of experimental evaluation of the most promising concepts.

Mapping Efficiency of a Pulsing Flow-Driven Turbine

2020 ◽  
Vol 142 (6) ◽  
Author(s):  
Mark H. Fernelius ◽  
Steven E. Gorrell
Keyword(s):  
Pressure Pulse ◽  
Pressure Ratio ◽  
Pulse Amplitude ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Efficiency ◽  
Pressure Gain Combustion ◽  
Pulsing Flow ◽  
Cycle Efficiency ◽  
Flow Experiences

Abstract Pressure gain combustion (PGC) shows potential to increase the cycle efficiency of conventional gas turbine engines (GTEs) if used in place of the steady combustor. However, a turbine driven by pulsing flow experiences a decrease in efficiency. An experimental rig was built to compare a steady flow-driven turbine with a pulsing flow-driven turbine. The pressure pulse was a full annular, sinusoidal pressure pulse. The experimental data showed a decrease in turbine efficiency and pressure ratio. The pressure pulse amplitude and not the frequency was discovered to be the cause for the decrease in turbine efficiency for the current experimental setup. The decrease in turbine efficiency was mapped with turbine pressure ratio and corrected amplitude to demonstrate how the efficiency of a turbine under pulsing flow conditions could be mapped.

Performance Enhancement of Gas Turbine Engines Topped With Wave Rotors and Pulse Detonation Combustors

2020 ◽  
Author(s):  
Pereddy Nageswara Reddy
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Compressed Air ◽  
Turbine Engines ◽  
Specific Work ◽  
Wave Rotor ◽  
Detonation Products ◽  
Turbine Engine ◽  
Pulse Detonation ◽  
C 30

Abstract In the present research work, a novel method of integrating the conventional gas turbine engine with a Wave Rotor (WR) and a Pulse Detonation Combustor (PDC) is proposed to increase the specific work and thermal efficiency of the engine. Two gas turbine engine configurations, viz. (i) Baseline engine topped with a wave rotor and a steady flow combustor (BWRSFC), and (ii) Baseline engine topped with a wave rotor and a pulse detonation combustor (BWRPDC), have been analyzed with and without recuperative systems. In the case of BWRPDC, the principle of quasi-steady expansion of detonation products through a nozzle into the ejector to entrain and eject the bypassed compressed air along with detonation products exhausted from WR, and a steady expansion of remained detonation products of PDC through the WR to provide the required energy transfer to further compress and supply the un-bypassed compressed air to PDC, has been considered. The pressure of the ejected gases from the ejector will be 25% to 35% higher than the air pressure delivered by the compressor of baseline engine and can develop more specific work with enhanced thermal efficiency when expanded in the turbine. A computer code is developed in MATLAB to simulate the engine performance with and without recuperation / regeneration. For thermodynamic calculations, two un-recuperated micro-turbine engines called C-30 and C-60 made by Capstone Turbine Corporation are considered. C2H4/air is taken as the fuel-oxidizer. The variation in specific work, and thermal efficiency with wave rotor pressure ratio has been investigated for C-30 and C-60 engines. Further, a sensitivity analysis of the performance of BWRPDC with a change in the Entrainment Coefficient (EC) of ejector has also been made.

Wave Cycle Design for Wave Rotor Gas Turbine Engines With Low NOx Emissions

1995 ◽  
Author(s):  
M. Razi Nalim ◽  
Edwin L. Resler
Keyword(s):  
Gas Turbine ◽  
Performance Enhancement ◽  
Design Method ◽  
Thermodynamic Cycle ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Wave Rotor ◽  
Nox Formation ◽  
Wave Cycle

The wave rotor is a promising means of pressure-gain for gas turbine engines. This paper examines novel wave rotor topping cycles which incorporate low-NOx combustion strategies. This approach combines two-stage ‘rich-quench-lean’ (RQL) combustion with intermediate expansion in the wave rotor to extract energy and reduce the peak stoichiometric temperature substantially. The thermodynamic cycle is a type of reheat cycle, with the rich-zone air undergoing a high pressure stage. Rich-stage combustion could occur external to or within the wave rotor. An approximate analytical design method and CFD/combustion codes are used to develop and simulate wave rotor flow cycles. Engine cycles designed with a bypass turbine and external combustion demonstrate a performance enhancement equivalent to a 200–400°R (110–220°K) increase in turbine inlet temperature. The stoichiometric combustion temperature is reduced by 300–450°R (170–250°K) relative to an equivalent simple cycle, implying substantially reduced NOx formation.

scholarly journals Wave Cycle Design for Wave Rotor Gas Turbine Engines With Low NOx Emissions

1996 ◽  
Vol 118 (3) ◽  
pp. 474-480 ◽  
Author(s):  
M. R. Nalim ◽  
E. L. Resler
Keyword(s):  
Gas Turbine ◽  
Performance Enhancement ◽  
Design Method ◽  
Thermodynamic Cycle ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Gas Turbine Engines ◽  
Wave Rotor ◽  
Nox Formation ◽  
Wave Cycle

The wave rotor is a promising means of pressure-gain for gas turbine engines. This paper examines novel wave rotor topping cycles that incorporate low-NOx combustion strategies. This approach combines two-stage “rich-quench-lean” (RQL) combustion with intermediate expansion in the wave rotor to extract energy and reduce the peak stoichiometric temperature substantially. The thermodynamic cycle is a type of reheat cycle, with the rich-zone air undergoing a high-pressure stage. Rich-stage combustion could occur external to or within the wave rotor. An approximate analytical design method and CFD/combustion codes are used to develop and simulate wave rotor flow cycles. Engine cycles designed with a bypass turbine and external combustion demonstrate a performance enhancement equivalent to a 200–400 R (110–220 K) increase in turbine inlet temperature. The stoichiometric combustion temperature is reduced by 300–450 R (170–250 K) relative to an equivalent simple cycle, implying substantially reduced NOx formation.

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