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Master Thesis Report Literature Review 2.2 Cycle Analysis of the Influence of BLI In this section, the influence of boundary layer ingestion on the size of the propulsion system, ther- modynamic as well as propulsive efficiency will be discussed. It should be pointed out that the exact inflow condition is dependent on the aircraft geometry, placement of the propulsor as well as the flight condition. The concept of inlet recovery ratio will be introduced as it is an indicator of the amount of boundary layer ingested. Figure 2.8: Control Volume Analysis of a Engine with Boundary Layer Ingestion [4] = PT1 (2.12) loss PT0 A greater ingestion of the boundary layer implies a lower inlet recovery ratio. In order to understand the influence of boundary layer ingestion on engine design and cycle performance, the following math- ematical relations between inlet recovery ratio and related design parameters were derived below. The thrust produced by an engine is given by the following expression: T = m ̇ (Vexit − Vinlet) = m ̇ (V2 − V0) (2.13) Assuming incompressible flow, the bernouli equation can be used to calculate the exit velocity as follows: Defining the fan pressure ratio as: The exit velocity can be expressed as: V2 = ρV22 PT2 = Ps,2 + 2 2 V2 = ρPT2 −Ps,2 FPR = PT2 PT1 2 ρFPR∗PT1 −Ps,2 (2.14) (2.15) (2.16) (2.17) 9PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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