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Research Article

Combustion Instability Analysis of a Gas Turbine Combustor with Varying Hydrogen Blending Ratios and Nozzle Geometry
Jaewoo Janga
,
Juhwan Leea
,
Jaehong Choib
,
Youngbin Yoonb
,
Jungmin Seokc
,
Daesik Kima*
aDepartment of Mechanical Engineering, Gangneung Wonju National University, Wonju 26403, Korea
bDepartment of Aerospace Engineering, Seoul National University, Seoul 08826, Korea
cGT Combustor Development Team, Doosan Enerbility, Changwon 51711, Korea
*Corresponding Author
30 November 2025. pp. 52-66
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Abstract

This study investigates the characteristics of combustion instability in a lab-scale single-nozzle combustion test rig, focusing on variations in hydrogen blending ratio and nozzle geometry. Steady-state 3D CFD simulations were performed to extract the time delay and its distribution key parameters of the flame transfer function which were then applied to a 1D network model for combustion instability analysis. The CFD results showed that changes in hydrogen blending ratio and nozzle geometry altered the flame structure, thereby affecting the time delay characteristics. These variations were found to directly influence the growth rate, helping to identify the causes of combustion instability observed in the experiments.

Keywords
Combustion instability
Gas turbine combustor
1D network model
CFD
Hydrogen blending ratio
Nozzle geometry
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Information
  • Publisher :The Korean Society of Propulsion Engineers
  • Publisher(Ko) :한국추진공학회
  • Journal Title :Journal of Propulsion and Energy
  • Journal Title(Ko) :Free Open Access International Journal on Propulsion and Energy Science and Technology
  • Volume : 5
  • No :2
  • Pages :52-66
  • Received Date : 2025-08-27
  • Revised Date : 2025-10-29
  • Accepted Date : 2025-11-05
  • DOI :https://doi.org/10.6108/JPNE.2025.5.2.052
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