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Master Thesis Report Literature Review Where the negative sign in T ds disappears since the relative stagnation pressure is decreasing through the rotor. It should be pointed out that since the rotation speed is constant, a constant relative stagnation enthalpy implies a constant rothalpy across the rotor. Substituting equation 2.45 and using the ideal gas law relation, the entropy change across the rotor can be expressed as follows: ∆srotor = p01,rel − p02,rel = R(p01,rel − p02,rel) = Rδloss(P01,rel − P1) ρ01,relT01,rel P01,rel P01,rel ∆srotor = Rδloss(1 − P1 ) P01,rel Inlet Distortion Inlet total pressure distortion can be classified as either circumferential or radial with respect to the machine axis. Circumferential distortions are considered to be more critical than radial distortions as it produces a disturbance normal to the airfoil motion, resulting in a change in the angle of attack and stall margin. An illustration of both type of distortion is shown in figure 2.23. Figure 2.23: Type of Inlet Distortion In order to assess the circumferential type inlet distortion, the distortion analysis methodology de- scribed by the Society of Automative Engineers document ARP 142019 was used. The concept of the circumferential distortion intensity as well as the circumferential distortion extent are being being introduced. The circumferential distortion extend for a given ring, (θi) ̄, is the angular distance in degrees for which the local total pressure falls below the ring average total pressure, where i refers to a single ring along the contour of the circle (See figure 2.24). (θi) ̄ = θ2i − θ1i (2.52) The circumferential distortion intensity, (∆pc )i, which quantifies the amount of total pressure variation (2.50) (2.51) around the ring is computed as follows: p ( ∆pc )i = ( Pav − Pav,low )i p Pav (2.53) Where: 22PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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