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Using MERLOT Learning Objects in Mechanical Engineering

Using MERLOT Learning Objects in Mechanical Engineering. Dr. Edward H. Perry Department of Mechanical Engineering The University of Memphis. Using MERLOT Learning Objects in Mechanical Engineering. Engineering Thermodynamics Gas Dynamics. Steam Tables vs Online Steam Calculator.

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Using MERLOT Learning Objects in Mechanical Engineering

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  1. Using MERLOT Learning Objects in Mechanical Engineering Dr. Edward H. Perry Department of Mechanical Engineering The University of Memphis The University of Memphis

  2. Using MERLOT Learning Objects in Mechanical Engineering • Engineering Thermodynamics • Gas Dynamics The University of Memphis

  3. Steam Tables vs Online Steam Calculator The University of Memphis

  4. Steam Turbine • Typical Problem: Determine the enthalpy for steam leaving an idealsteam turbine at 1 psia if the steam enters at a pressure of 1500 psia and a temperature of 1000 oF. The University of Memphis

  5. Steam Table Approach - Step 1 • Using conventional superheated steam tables, we find that at 1500 psia and 1000 oF, the entropy s of the steam at the turbine inlet is: s1 = 1.6001 Btu/lbm-R The University of Memphis

  6. Steam Tables - Step 2Ideal Steam Turbine => Entropy remains constant (i.e., s2 = s1) Using the Saturation Tables, we find the quality of the steam at the turbine exit (p2 = 1 psia , s2 = s1 = 1.6001 Btu/lbm-R) is: x2 = (s2 - sf)/sfg = (1.6001 - 0.13266)/1.8453 = 0.795Thus, the enthalpy at the exit is: h2 = hf + xhfg = 69.74 + (0.795)(1036.0) = 893.4 Btu/lbm The University of Memphis

  7. Online Calculator Approachwww.mathpad.com “Ideal” Turbine => Entropy remains constant (s2=s1) Inlet Conditionsp1 = 1500 psiaT1 = 1000 oFThus, s1 = 1.60037… Btu/lbm-R Exit Conditionsp2 = 1 psias2 =s1 = 1.60037...Thus, h2 = 893.7 Btu/lbm The University of Memphis

  8. Determining Exit Conditions in a Rocket Nozzle Typical Problem: Determine the Mach number and speed of the combustion products leaving a converging-diverging nozzle with an area ratio of 50:1. Assume a specific heats ratio g of 1.20 for the gases. The University of Memphis

  9. Traditional Approach - Calculations This non-linear equation is not only messy. It cannot be solved directly. A trial-and-error root-finding approach must be used. The University of Memphis

  10. Traditional Approach The results of one such iterative method are shown below and indicate that the correct answer is approximatelyM = 4.3958 The University of Memphis

  11. Online Calculator Approachhttp://www.aoe.vt.edu/~devenpor/aoe3114/calc.html Using the calculator, we immediately find the Mach number to be 4.3958 The University of Memphis

  12. Nozzle Simulatorhttp://www.grc.nasa.gov/WWW/K-12/airplane/ienzl.html The University of Memphis

  13. Thanks Merlot! The University of Memphis

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