| Citation: | GUO Jiafan, LIU Chuankai, WANG Yaoze, et al. Influence of the turbine guide vane adjustment on the film holes outflow in whole engine environment[J]. Journal of Aerospace Power, 2026, 41（5）：20240436 doi: 10.13224/j.cnki.jasp.20240436
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To investigate the influence of low-pressure turbine guide vane adjustments on film hole flow distribution in variable cycle engines, a variable inter-stage bleed module for the compressor and a turbine mixing module with adjustable vane angles were developed. These modules enabled modular coupling and data exchange between the main flow and secondary air systems. Using a core-driven fan stage variable cycle engine (CDFS VCE) as the test case, the impact of guide vane adjustments on film hole outflow across the engine was analyzed. The research indicated that considering the variable inter-stage bleeding for the compressor and the mixing with adjustable guide vane angles did not significantly affect the proportion of cooling air from the guide vanes and rotor blades to the core engine inlet flow, but caused a significantly unbalanced response in the distribution of cooling air among film holes at different positions of the guide vanes and rotor blades. Within the adjustment range of the guide vane angle from −3° to 4°, the flow rate ratio of the film holes on the suction side of the guide vane decreased by up to 20%, while the flow rate ratio of the film holes on the pressure side of the rotor blade decreased by approximately 6%.
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