AD_433GasTurb_Project

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Nov 24, 2024

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GasTurb Project Report Alberto Delgado ad30 November 29, 2023 1 Homework 1: Gas Turbine Cycle 1.1 Thrust Specific Fuel Consumption TSFC = 2 . 0307 × 10 − 5 kg/N − s 1.2 Fuel-to-Air Ratio W f = . 03304 kg/s W 3 = 1 . 50778 kg/s f = ˙ m fuel ˙ m fuel = . 021913 (1) Comparing the fuel-to-air ratio that was computed ( f = . 021913 ) with the one that was calculated from homework nine ( f = 0 . 0276 ), it is slightly less than the result, as the homework had more assumptions that simplified the calculation - the homework assumed ideal isentropic turbines and compressors. 1.3 Nozzle Exit Conditions Core Nozzle: P exit = 15 . 00 kPa, M exit = . 73 , u exit = 370 . 98 m/s Fan Nozzle: P exit = 20 . 50 kPa, M exit = 1 , u exit = 323 . 29 m/s 1.4 Specific Thrust F N / ˙ m totalair = 116 . 25 N-s/kg (m/s) F N / ˙ m coreair = 1043 . 50 N-s/kg (m/s) 1

1.5 Calculation Results for Ideal Isentropic Efficiencies Core Nozzle: P exit = 32 . 50 kPa, M exit = 1 , u exit = 523 . 96 m/s Fan Nozzle: P exit = 20 . 50 kPa, M exit = 1 , u exit = 318 . 18 m/s F N / ˙ m totalair = 155 . 1 N-s/kg (m/s) F N / ˙ m coreair = 1374 . 5 N-s/kg (m/s) The values computed from GasTurb 14 for both isentropic turbines and compressors are lower than the values from homework nine. The FN/m˙ totalair is = 155.1 m/s and FN/m˙coreair is = 1374.5 m/s. The FN /m˙ totalair is = 158 m/s and FN/m coreair is = 1423 m/s from homework nine. These values are nearer to the homework values than the values computed above because more ideal assumptions have been used, but they are not the exact same as the homework nine values because GasTurb 14 has other real assumptions that were not changed to ideal assumptions/values. 2

2 Homework 2: Parametric Studies 2.1 One Variable Parametric Study Graph 2 4 6 8 10 12 14 *10 3 Altitude [m] 19 19.5 20 20.5 21 21.5 22 22.5 23 23.5 Sp. Fuel Consumption [g/(kN*s)] 2.5 3 3.5 4 4.5 5 5.5 6 6.5 7 Net Thrust [kN] .75 .76 .77 .78 .79 .8 .81 .82 .83 .84 Propulsive Efficiency 236 240 244 248 252 256 260 264 268 272 Flight Velocity V0 [m/s] Altitude = 3000 ... 12000 [m] Figure 1: Flight velocity, propulsive efficiency, net thrust, and specific fuel consumption variance with altitude. 3

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2.2 Two Variable Parametric Study Graph 4 5 6 7 8 9 10 HP Compressor Pressure Ratio 18 18.5 19 19.5 20 20.5 21 21.5 22 22.5 Sp. Fuel Consumption [g/(kN*s)] HP Compressor Pressure Ratio = 5 ... 9 Design Bypass Ratio = 4 ... 8 Fuel Flow [kg/s] = 0.0425...0.09 0.045 0.0475 0.05 0.0525 0.055 0.0575 0.06 0.0625 0.065 0.0675 0.07 0.0725 0.075 0.0775 0.08 0.0825 0.085 0.0875 Fuel Flow > 0.07[kg/s] 0.07 4 5 6 7 8 6 7 8 9 1% Figure 2: The effects of HP compressor pressure ratio and specific fuel consumption on the fuel flow rate 2.2.1 Details for BPR=7 and P3/P2 = 6 TSFC = 19 . 2536 g/ ( kNs ) = 19 . 253 × 10 − 6 kg/ ( Ns ) (2) P t 3 P t 1 = P t 3 P t 2 P t 2 P t 1 = 507 . 334 34 . 1639 × . 99 = 14 . 7 (3) 2.3 Iteration Result The thrust-specific fuel consumption of the engine is 19.3 g/kN-s at an altitude of 11,404 meters . 4

3 Homework 3: Off Design Analysis 3.1 Compressor Map Operating Line 4 8 12 16 20 24 28 32 36 Mass Flow W 2RStd [kg/s] 0 2 4 6 8 10 12 14 16 Pressure Ratio P 3 /P 2 Compr Map is valid for RNI=1 and no modifiers applied 0.5 0.6 0. 7 0 . 7 5 0 . 8 0 .8 5 0.9 0.95 1 N =1.05 0.85 0.84 0.83 0.82 0.80 0.75 0.70 Figure 3: Operating line on the compressor map. 5

3.2 Handling Bleed vs. Relative Corr. Spool Speed .4 .5 .6 .7 .8 .9 1 1.1 Rel. Corr. Spool Speed 0 .04 .08 .12 .16 .2 .24 .28 .32 .36 Handling Bleed WB_hdl/W2 Reference Bleed Figure 4: The effects of bleed air on handling bleed vs relative corrected spool speed 6

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3.3 TSFC vs. Relative Corr Spool Speed .4 .5 .6 .7 .8 .9 1 1.1 Rel. Corr. Spool Speed 10 20 30 40 50 60 70 80 90 Sp. Fuel Consumption [g/(kN*s)] Reference Bleed Figure 5: The effects of bleed air on Specific fuel consumption vs relative corrected spool speed The handling bleed INCREASES the specific fuel consumption. 7

3.4 Surge Margin vs. Spool Speed 5 6 7 8 9 10 11 12 13 14 *10 3 Spool Speed [RPM] -30 -20 -10 0 10 20 30 40 50 60 Surge Margin Reference Bleed Figure 6: The effects of bleed air on surge margin vs the spool speed [RPM] The lowest spool speed with a positive surge margin for the reference case is 7156 RPM . 8