Detailed measurements using pneumatic probe traverses, blade static pressure tappings, and laser anemometry are made in the third stage of a large-scale, low-speed, four-stage, axial flow, research compressor. Inlet conditions show well-ordered “two-dimensional” flow from approximately 40 to 85 percent annulus span. Outside of this region, reduced total pressure due to upstream leakage losses and endwall effects results in high incidence to the following blade row. As a result, peak suction surface static pressure moves forward along the blade chord for both the hub and tip of stators and rotors. At the blade tip, however, the peak suction pressure is maintained with chord due to radial flow on the suction surface being entrained into the tip leakage jet. The extent of rotor chord for which this “entrainment” occurs increases with increasing rotor tip clearance gap. The leakage jet from both stators and rotors is seen to “roll up” into a vortex downstream of their respective blade rows.
The assessment of Student Outcomes is an import component for program evaluation and improvement. Though not proposed as the only tool a program should employ to measure the achievement of outcomes, the capstone design course can be a valuable mechanism to measure performance with regards to Student Outcomes. Because of the expansive reach of the engineering design process, capstone design projects present a natural environment to structure assessment activities that directly map to Student Outcomes. This paper presents versions of the Mechanical Engineering capstone design course that have been specifically structured to assess achievement of Student Outcomes commonly included in engineering accreditation criteria. Typically the outcomes are assessed by assignments that guide the engineering design process.
The paper proposes a straightforward technique to quantify the performance of a gas turbine secondary air system. By recognising the air system as a component in its own right and performing the calculations suggested the systems engineer should be better able to develop and optimise a given air system. The effect of any requested compromise can also be better quantified to other component groups.
Detailed measurements using pneumatic probe traverses, blade static pressure tappings and laser anemometry are made in the third stage of a large scale, low speed, four stage, axial flow, research compressor.
Inlet conditions show well ordered ‘two dimensional’ flow from approximately 40 to 85% annulus span. Outside of this region, reduced total pressure due to upstream leakage losses aod endwall effects results in high incidence to the following blade row. As a result, peak suction surface static pressure moves forward along the blade chord for both the huh and tip of stators and rotors. At the blade tip however, the peak suction pressure is maintained with chord due to radial flow on the suction surface being entrained into the tip leakage jet. The extent of rotor chord for which this ‘entrainment’ occurs increases with increasing rotor tip clearance gap. The leakage jet from both stators and rotors is seen to ‘roll up’ into a vortex downstream of their respective blade rows.
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