\ ME 200 L34 Self Study Assignment 9.6 Todays Class 9.11 Material not picked up this week may be recycled! \ ME 200 L34 Gas Turbine Power Generation and Aircraft Propulsion Self Study Assignment 9.6 Todays Class 9.11 Kim Sees Office ME Gatewood Wing Room 2172 Examination 3 grades, Quiz 5 grades are available Blackboard and Examinations and Quizzes can be picked up all of this week from Gatewood Room 2172 Material not picked up this week may be recycled! ThermoMentor © Program Spring 2014 MWF AM J. P. Gore Gatewood Wing 3166, Office Hours: MWF TAs: Robert Kapaku Dong Han

2 Outline Brayton Cycle (with Improved Performance) –Brayton Cycle for land based power generation and for aircraft propulsion (9.6; 9.11) –Reheating- land based power generation: will mention but leave for you to explore (9.7) –Regeneration - will mention but leave for you to explore (9.8) –Combined Regeneration and Reheating, Cogeneration - will mention but leave for you to self-study (9.9, 9.10) –Aircraft Propulsion (9.11) Will cover today including using Quiz 6.

3 Inlet State Component aDiffuser 1Compressor 2Combustor 3Turbine 4Nozzle Aircraft Propulsion (9.11) : Quiz 6.

Air Standard Brayton Cycle Thermal Efficiency back work ratio

Compressor Pressure Ratio and Brayton Cycle Performance The Brayton cycle thermal efficiency increases as the compressor pressure ratio increases 60 th (%) Compressor Pressure Ratio See Figure 9.12

6 Gas Turbine Example Problem Given: Heat supplied by the boiler = 5.2x10 8 Btu/h, Pressure ratio = P2/P1=P3/P4=12, Tmin = T1 = 520 o R, Tmax = T3= 2800 o R Find: Thermal efficiency: Eta Th, m dot air (lb/hr), w dot cycle (Btu/hr) If the turbine and the compressor are not isentropic but operate with T, C find the impact on the work of the cycle, heat input and thermal efficiency C = 0.86 (Chosen in class based on student input); T =0.91 chosen to be higher than Compressor efficiency since turbine efficiency matters more and companies must improve it sooner. Steps: (1) Identify and number all states and start a table of properties for the states. (2) Recognize that compressor efficiency and turbine efficiency lead to additional state definitions (2s, 2a in place of 2 and 4s and 4a in place of 4).

Steps: (1) Identify and number all states and start a table of properties for the states. (2) Recognize that compressor efficiency and turbine efficiency lead to additional state definitions (2s, 2a in place of 2 and 4s and 4a in place of 4). (3) Table A 22 E is to be referenced with the known states and knowledge of process definitions to find all properties necessary to calculate the work of compressor, work of Turbine, heat added, heat rejected and resulting Eta Th, m dot air (lb/hr), w dot cycle (Btu/hr) StateT, o Rh, Btu/lbmPrP, atm s *12= or ~ a ~ Pr not relevant s /12=58.5 ~ a ~409.13Pr not relevant1

Answers

Gas Turbine Power Plants 3. Compressor, combustion chamber, and turbine are treated as control volumes and mass, energy, and entropy balances are applied to each. 4. The heat rejection process substitutes exhaust and fresh air admission. 1.Compression, heat addition and expansion are followed by exhaust of products and induction of fresh air. 2. The last two steps represent heat rejection

Gas Turbine Power Plants 1 23 c

Gas Turbine Power Plants Thermal Efficiency back work ratio

Compressor Pressure Ratio and Brayton Cycle Performance Consider compressor pressure ratios p 2 /p 1 and p 2 /p 1 yielding cycles: to T H greater in cycle , and both cycles have the same heat rejection, hence cycle has inherently greater thermal efficiency. The Brayton cycle thermal efficiency increases as the compressor pressure ratio increases 60 th (%) Compressor Pressure Ratio

13 Gas Turbine Example Problem Given: Heat supplied by the boiler = 5.2x10 8 Btu/h, Pressure ratio = P2/P1=P3/P4=12, Tmin = T1 = 520 o R, Tmax = T3= 2800 o R StateT, Rh, Btu/lbPr Pr2=Pr1*P2/P Pr4=Pr3/12 Find: Thermal efficiency: Eta Th, m dot air (lb/hr), w dot cycle (Btu/hr)

Solution