Technical Briefs

Air-Standard Aerothermodynamic Analysis of Gas Turbine Engines With Wave Rotor Combustion

[+] Author and Article Information
M. R. Nalim1

Department of Mechanical Engineering, Indiana University-Purdue University Indianapolis, Indianapolis, IN 46202-5132

H. Li

Department of Mechanical Engineering, Purdue University, West Lafayette, IN 47907

P. Akbari

Department of Mechanical Engineering, Indiana University-Purdue University Indianapolis, Indianapolis, IN 46202-5132


Corresponding author.

J. Eng. Gas Turbines Power 131(5), 054506 (Jun 09, 2009) (6 pages) doi:10.1115/1.3078790 History: Received August 28, 2008; Revised November 22, 2008; Published June 09, 2009

The wave rotor combustor can significantly improve gas turbine engine performance by implementing constant-volume combustion. The periodically open and closed combustor complicates thermodynamic analysis. Key cycle parameters depend on complex gas dynamics. In this study, a consistent air-standard aerothermodynamic model with variable specific heat is established. An algebraic model of the dominant gas dynamics estimates fill fraction and internal wave compression for typical port designs, using a relevant flow Mach number to represent wave amplitudes. Nonlinear equations for thermodynamic state variables are solved numerically by Newton–Raphson iteration. Performance measures and key operating conditions are predicted, and a quasi-one-dimensional computational model is used to evaluate the usefulness of the algebraic model.

Copyright © 2009 by American Society of Mechanical Engineers
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Figure 1

Wave pattern in a developed view of the wave rotor combustor

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Figure 2

Efficiency, η, and specific work, w, as functions of wave rotor combustor exit Mach number for different wave rotor internal efficiencies

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Figure 3

Cycle efficiency, specific work, and pressure gain as functions of temperature ratio with M3=0.6, ηWE=ηWC=0.8

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Figure 4

CFD simulation of wave rotor combustor cycle with burned residual gas (μ=0.76) and forward propagating deflagration in stratified fuel-air mixture

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Figure 5

Pressure-gain comparison of CFD and linear approximation to algebraic model




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