The high demands placed on aircraft turbine engines necessitate the use of the latest engine compressors which must be increasingly efficient and more robust due to the increased loads. The key safety issue in this context is to ensure compressor stability over all engine speed ranges and...

This study investigates the aerodynamic performance of a fourth-generation normal shockwave inlet system, with a primary focus on minimizing pressure losses and ensuring uniform airflow distribution. A computational model was developed, incorporating a section of the fuselage along with the complete inlet duct. The model was discretized using a hybrid mesh approach to enhance numerical accuracy. The analysis was conducted at a flight altitude of 8000 m, encompassing 370 distinct cases defined by varying angles of attack and Mach numbers. This comprehensive parametric study yielded a dataset of 10,800 total pressure measurements across predefined sampling locations. Based on the obtained results, flow distortion coefficients in both circumferential (CDI) and radial directions (RDI) were systematically determined for each test case. The interdependencies between CDI, RDI, Mach number, and angle of attack (α) were analyzed and presented in a consolidated manner. In the second phase of the study, an artificial neural network (ANN) utilizing a Feed-Forward architecture was implemented to predict pressure distributions for intermediate flight conditions. The ANN was trained using the CFG algorithm, and the predictive accuracy was assessed through the determination coefficients computed by comparing ANN-based estimates with numerical simulation results. The findings demonstrate the efficacy of ANN-based modeling in enhancing the predictive capabilities of inlet flow dynamics, offering valuable insights for optimizing next-generation supersonic air intake systems.

This article outlines the methodology and results of measuring gaseous and particulate emissions from a miniature aircraft turbine engine tested on a test bench. An atmosFIR analyzer, manufactured by Protea, was utilized to analyze gaseous components such as carbon monoxide (CO), carbon dioxide (CO₂), and nitrogen oxides (NOₓ). Particulate matter measurements were conducted using a Dekati ELPI+ device, which operated in conjunction with a heated path and an eDiluter dilution tunnel. The emission results for individual exhaust components were compared to the engine's rotor speed and existing literature on exhaust emissions for this type of engine. Additionally, a fractional analysis of the particulate matter emitted in the exhaust gas was performed. The distribution of particulate matter as a function of aerodynamic diameter over the entire test cycle was presented. The paper also addresses the limitations and measurement errors associated with these measurements and the interpretation of the data.