Investigation on turbine inter-vane combustion performance based on fuel cooled vane

被引：0

作者：

Qing L. ^{[1
,2
]}

Zhu J. ^{[1
,2
]}

Cheng Z. ^{[1
,2
]}

机构：

[1] School of Energy and Power Engineering, Beihang University, Beijing

[2] National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, Beihang University, Beijing

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2024年 / 39卷 / 06期

关键词：

combustion performance; fuel cooled vane; high-temperature fuel; radial vane cavity; turbine inter-vane burner; ultra-compact combustion;

D O I：

10.13224/j.cnki.jasp.20220388

中图分类号：

学科分类号：

摘要：

To expand the performance of aero-gas turbine engine， a structure of high-pressure turbine inter-vane combustion was proposed. The high-temperature fuel was injected into the inter-vane channel after cooling the vane. And the flame was stabilized by radial vane cavity (RVC). The C3X turbine guide vane was used as the inter-vane combustion model and the effects of radial vane cavity (depth length ratio 0.4− 0.6)，fuel-air ratio (0.007− 0.010 5) and fuel temperature (300− 500 K) on inter-vane combustion performance were numerically studied. It was observed that the optimization combustion effect was obtained with depth length ratio 0.5. The thermal resistance loss caused by combustion was about 7%，which can realize the approximately isothermal combustion between the vanes. The inter-vane combustion performance decreased with the increase of fuel-air ratio， and the combustion efficiency reached 98.86% at 20 mm away from the blade outlet when the fuel-air ratio was 0.007. The combustion performance of high-temperature fuel in the inter-vane channel was better than that of low-temperature fuel，and the combustion efficiency at the outlet of the blade increased about 13%. The conclusions can provide a reference for the development of inter-vane burner technology. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

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