Question

5.34 Cooling method for gas turbines. Refer to the Journal of Engineering for Gas Turbines and Power (January 2005) study of a high-pressure inlet fogging method for a gas turbine engine, Exercise 5.19 (p. 281). Recall that you analyzed a model for heat rate (kilojoules per kilowatt per hour) of a gas turbine as a function of cycle speed (revolutions per minute) and cycle pressure ratio. Now consider a qualitative predictor, engine type, at three levels (traditional, advanced, and aeroderivative).

(a) Write a complete second-order model for heat rate (y) as a function of cycle speed, cycle pressure ratio, and engine type.

(b) Demonstrate that the model graphs out as three second-order response surfaces, one for each level of engine type.

(c) Fit the model to the data in the GASTUR- BINE file and give the least squares prediction equation.

(d) Conduct a global F -test for overall model adequacy.

(e) Conduct a test to determine whether the second-order response surface is identical for each level of engine type.

Answer 1

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