Jun LIU, Xueju QIU, Huacheng YUAN
DOI Number: 10.60853/7x0z-1×39
Conference number: HiSST-2024-0095
To satisfied the thrust requirement of aero-engine operating within Ma 0-5 and altitude 0-30 km, a variable geometry inlet was designed. The corrected mass flow requirement of this wide range aero-engine is almost 125 kg/s with the design point at Ma2.35 and altitude 20 km, corresponding to the throttle ratio equals to 1.50. The total pressure requirement of inlet is shown in Fig 1 which is higher than MIL-E-5008B specification and lower than AIA standard. To satisfied the mass flow requirement of aero-engine, the inlet capture area is designed at 2.0 m2, with height-to-wide 1.39. The design point of this two-dimensional inlet is Ma 3.6. To meet this inlet total pressure recovery requirement, the throat Mach number of inlet should be lower than Ma 1.5. The geometry of two-dimensional inlet and its variable-geometry scheme is shown in Fig. 2. It consists of two external ramps. The first ramp is 10 deg curve wall. The second ramp angle is designed according to inflow Mach number and increased from 0 deg to 10deg. The inlet throat Mach number is between 1.3 and 1.5 to meet the criteria of total pressure requirement. Therefore, the throat height along with the diffuser of the inlet is adjustable. Then the performance of this inlet was investigated through numerical simulation. Reynolds-Average Navier-Stroke(RANS) equations were solved to acquire the flow field of this wide range operation inlet. The performance of this inlet at different inflow Mach number and back-pressure are shown in Fig. 3. Finally, the performance of inlet at match point is shown in Fig. 4. As shown in this figure, mass flow ratio and total pressure recovery within Ma 3.6 can meet the requirement of aero-engine.