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

2021 ◽  
Author(s):  
PEREDDY NAGESWARA REDDY
Keyword(s):  
Gas Turbine ◽  
Performance Enhancement ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Pulse Detonation ◽  
Wave Rotors

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.

Air-Argon-Steam or Organic Fluid Combined Power Cycle With Pulse Detonation Combustion for Electric Power Plants

2021 ◽  
Author(s):  
Pereddy Nageswara Reddy
Keyword(s):  
Gas Turbine ◽  
Combined Cycle ◽  
Working Fluid ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Specific Work ◽  
Gas Turbine Engines ◽  
Detonation Products ◽  
Pulse Detonation ◽  
Detonation Combustion

Abstract Gas turbine engines with pulse detonation combustion show the superior performance in terms of specific work output and thermal efficiency when compared to the conventional gas turbine engines with isobaric combustion. But, a quasi-steady expansion of detonation products through the gas turbine results in an unsteady operation. Moreover, as the detonation products during quasi-steady expansion are initially at a very high temperature (over 2500 K), they cannot be expanded in the turbine as it is. To overcome the above difficulties associated with pulse detonation combustion in gas turbine engines, Air-Argon-Steam or organic fluid Combined Cycle (AASCC) is proposed in the present work. AASCC comprises two gas turbine cycles, viz. the Humphrey cycle with the air as the working fluid and the Brayton cycle with the argon as the working fluid and a steam turbine cycle, viz. the Rankine or organic Rankine cycle with the steam or organic substance as the working fluid. The temperature of the hot detonation products is reduced to Turbine Inlet Temperature (TIT) by exchanging heat energy between detonation products and compressed argon in a Detonation Products to Argon Heat Exchanger (DPAHE) and in turn, raising the temperature of the compressed argon to Argon Turbine Inlet Temperature (ATIT). The residual energy of both detonation products and argon after the expansion in the respective turbines is utilized to generate the steam or organic fluid vapor in the Heat Recovery Generators (HRGs) to operate a steam or organic fluid turbine. AASCC with pulse detonation combustion is analyzed based on quasi-steady state one dimensional formulation, and a computer code is developed in MATLAB to simulate the cycle performance at different compressor pressure ratios and TITs. C2H4/air is taken as the fuel-oxidizer. The performance of AASCC with pulse detonation combustion is compared with that of a conventional Air-Steam Combined Cycle (ASCC) with constant pressure combustion. It is found that the thermal efficiency of AASCC with pulse detonation combustion can go up to 44.5%–46.5% depending on the working fluid used in the bottoming Rankine cycle as against 37.8%–41.0% of ASCC at a TIT of 1400 K. The maximum specific work output of AASCC at a TIT of 1400 K is found to vary from 1143.0 to 1202.0 kJ/kg air as against to 335.0 to 364.0 kJ/kg air of ASCC.

Performance enhancement of a trapped-vortex combustor for gas turbine engines using a novel hybrid-atomizer

2018 ◽  
Vol 216 ◽  
pp. 286-295 ◽  
Author(s):  
Mingyu Li ◽  
Xiaomin He ◽  
Yuling Zhao ◽  
Yi Jin ◽  
Kanghong Yao ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Performance Enhancement ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Trapped Vortex

Gas Screen in Components of Gas Turbine Engines

1997 ◽  
Vol 28 (7-8) ◽  
pp. 536-542
Author(s):  
A. A. Khalatov ◽  
I. S. Varganov
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Gas Screen

Potential Application of Composite Materials to Future Gas Turbine Engines

1988 ◽  
Author(s):  
James C. Birdsall ◽  
William J. Davies ◽  
Richard Dixon ◽  
Matthew J. Ivary ◽  
Gary A. Wigell
Keyword(s):  
Composite Materials ◽  
Gas Turbine ◽  
Potential Application ◽  
Turbine Engines ◽  
Gas Turbine Engines
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