The information contained herein is private and confidential and for the sole use by Arvtech Aero Inc. and its affiliates. All rights reserved PROBLEM 2 (7 Marks) FIGURE 2: Compressor Turbine Assy SITUATION: Consider the single stage compressor turbine vane and blade Assy. configuration is depicted in Figure 1. DETERMINE: How many hours of flight time will it take for the blade to creep and create a radial clearance of 0.010 in. NOTE: * Use the average stress across the mission stress plane for the mission profile shown in Figure 2. Use the creep curves and data depicted in Figure 3 Assume that creep accumulation progresses in a sequential manner from condition to condition. Assume that the shroud will remain in its original location with no creep or deformation. The shroud and blade radial clearance in the production state is 0.040 in. SHROUD BLADE RADIAL CLEARANCE Cr=0.040 in. VAN R=13.189 in. MISSION STRESS PLANE R=11.575 in. BLADE SPAN = 1.614 in Blade Stress ksi. FIGURE 2: BLADE MISSION STRESS PROFILE 30 0.165, 20 Creep Leg 1, TO & Climb t = 0.30 0.66, 16 20 5.61, 16 6.468, 11 0.462, 20 10 0.165, 11 Creep Leg 2, Cruise t = 5.0 hrs. 5.61, 11 0, 11 0 -10 -20 -30 -40 -50 50 3/7/2023 1 2 3 4 5 Mission Time (hrs.) Fatigue FIGURE 3 CREEP CURVES FOR TAKE-OFF/CLIMB AND CRUISE Time (hrs) Creep (in/in) T=1800 F, O=20 ksi., Ecrupture=.28 (in/in) 0 0 0.3 100 0.024 200 0.03 300 0.033 0.25 400 0.035 500 0.036 0.2 6.6, 20 600 0.038 700 0.04 800 0.042 900 0.046 Creep Stain (in) 0.15 1000 0.05 0.1 1100 0.055 6.6,0 1200 0.07 0.05 1300 0.09 1400 0.115 1500 0.18 200 400 600 800 1000 1200 1400 1800 Time (hrs) 1600 0.28 Time(hrs) Creep (in/in) 0 0 T=1675 F, =16 ksi., Ecrupture= .24 (in/in) 0.35 500 0.0175 1000 0.024 0.3 1500 0.028 2000 0.032 0.25 2500 0.0345 24 3000 0.037 02 6.468, -46.87 3500 0.039 4000 0.0415 0.15 4500 0.045 5000 0.048 0.1 5500 0.05 6000 0.0585 0.05 6500 0.0825 7000 0.14 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 7500 0.205 Time (hrs) 8000 0.28