Next Article in Journal
A Parameter Self-Tuning Rule Based on Spatial–Temporal Scale for Active Disturbance Rejection Control and Its Application in Flight Test Chamber Systems
Previous Article in Journal
LLM-ACNC: Aerospace Requirement Texts Knowledge Graph Construction Utilizing Large Language Model
Previous Article in Special Issue
Flow and Flame Mechanisms for Swirl-Stabilized Combustors
 
 
Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
Journals
Aerospace
Volume 12
Issue 6
10.3390/aerospace12060464
aerospace-logo
Submit to this Journal Review for this Journal Propose a Special Issue
► Article Menu

Article Menu

share Share announcement Help format_quote Cite question_answer Discuss in SciProfiles
first_page
settings
Order Article Reprints
Font Type:
Arial Georgia Verdana
Font Size:
Aa Aa Aa
Line Spacing:
Column Width:
Background:
This is an early access version, the complete PDF, HTML, and XML versions will be available soon.
Article

Experimental Investigation of Pure Hydrogen Flame in a Matrix Micro-Mixing Combustor

by
Zhenzhen Feng
1,2,
Xiaojing Tian
1,2,*,
Liangliang Xu
3,*,
Xi Xia
3 and
Fei Qi
3
1
State Key Laboratory of Clean and Efficient Turbomachinery Power Equipment, Deyang 618000, China
2
Dongfang Electric Corporation Dongfang Turbine Co., Ltd., Deyang 618000, China
3
School of Mechanical Engineering, Shanghai Jiao Tong University, Shanghai 200240, China
*
Authors to whom correspondence should be addressed.
Aerospace 2025, 12(6), 464; https://doi.org/10.3390/aerospace12060464
Submission received: 17 April 2025 / Revised: 20 May 2025 / Accepted: 21 May 2025 / Published: 23 May 2025
(This article belongs to the Special Issue Scientific and Technological Advances in Hydrogen Combustion Aircraft)
Versions Notes

Abstract

Pure hydrogen combustion is a critical pathway to achieving zero-carbon emissions for the gas turbine industry. Micro-mixing combustion is one of the most widely attractive hydrogen combustion methods in gas turbines. This study investigates pure hydrogen flame in a 3 × 3 matrix micro-mix combustor. The setup includes nine micro-mix injectors, each equipped with a bluff body and a hydrogen injection tube. The OH* chemiluminescence imaging and PIV (Particle Image Velocimetry) techniques were employed to visualize the single- and triple-flame morphology and flow field under various operating conditions. The results show that equivalence ratio, flow rate, and air injector exit angle can influence the flame structure and combustion characteristics, providing an insightful understanding of micro-mix pure hydrogen combustion.
Keywords: pure hydrogen combustion; micro-mixing flame; flame–flame interaction; gas turbine combustor; optical diagnostics pure hydrogen combustion; micro-mixing flame; flame–flame interaction; gas turbine combustor; optical diagnostics

Share and Cite

MDPI and ACS Style

Feng, Z.; Tian, X.; Xu, L.; Xia, X.; Qi, F. Experimental Investigation of Pure Hydrogen Flame in a Matrix Micro-Mixing Combustor. Aerospace 2025, 12, 464. https://doi.org/10.3390/aerospace12060464

AMA Style

Feng Z, Tian X, Xu L, Xia X, Qi F. Experimental Investigation of Pure Hydrogen Flame in a Matrix Micro-Mixing Combustor. Aerospace. 2025; 12(6):464. https://doi.org/10.3390/aerospace12060464

Chicago/Turabian Style

Feng, Zhenzhen, Xiaojing Tian, Liangliang Xu, Xi Xia, and Fei Qi. 2025. "Experimental Investigation of Pure Hydrogen Flame in a Matrix Micro-Mixing Combustor" Aerospace 12, no. 6: 464. https://doi.org/10.3390/aerospace12060464

APA Style

Feng, Z., Tian, X., Xu, L., Xia, X., & Qi, F. (2025). Experimental Investigation of Pure Hydrogen Flame in a Matrix Micro-Mixing Combustor. Aerospace, 12(6), 464. https://doi.org/10.3390/aerospace12060464

Note that from the first issue of 2016, this journal uses article numbers instead of page numbers. See further details here.

Article Metrics

Back to TopTop