![Engine Design Choices
BPR (x:1) 9.1
π 40.21
πFan 1.55
πIPC 1.52
πHPC 17.07
ζs 0.04
ηM 0.96
M@ SLS 1660 kg/s
QR [J/kg] 4.30E+07](https://image.slidesharecdn.com/finalpresentation-12811076045889-phpapp01/85/Design-Project-3-320.jpg)
![Ambient: INLET:
Position:
a 1 Inlet
Po 33,223 33,174
P 20,715 24,974 1.90
To 248 248 1.80
T 217 229 1.70
ρ 0.33 0.38
1.60
ho 248,802 248,802
h 217,390 229,417 1.50
Vax 251 197 1.40
M 0.85 0.65 1.30
R 287 287 1.20
γ 1.40 1.40
1.10
Radial (m)
Cp 1003 1003
Area (m2) 7.82 1.00
Diameter [ft] - 10.35 0.90
0.80
0.70
Inlet Area Distribution 0.60
9.5 0.50
9.0 0.40
8.5
Area [m^2]
8.0 0.30
7.5
7.0 0.20
6.5
6.0 0.10
5.5
5.0 0.00
4.5
0.00
0.10
0.20
0.30
0.40
0.50
0.60
0.70
0.80
0.90
1.00
1.10
1.20
1.30
1.40
1.50
1.60
1.70
1.80
4.0
0 0.5 1 1.5 2 Axial (m)
x [m]](https://image.slidesharecdn.com/finalpresentation-12811076045889-phpapp01/85/Design-Project-9-320.jpg)
![Annulus Area Distribution Number of Blades
0.660
0.650 150
Area [m2] 0.640 130
0.630
110 Rotors
0.620
90 Stators
0.610
70 IGV
0.600
0.590 50
Stator
Stator
Stator
IGV
Rotor
Rotor
Rotor
1 2 3
2
1
3
2
1
3
IPC Annulus
0.90
0.85
0.80
Radial [m]
0.75
0.70
IGV R1 S1 R2 S2 R3 S3 0.65
0.60
0.55
Cascade Blade View 0.50
2.05
2.30
2.50
2.45
2.00
2.15
2.20
2.35
2.40
2.10
2.25
Axial [m]](https://image.slidesharecdn.com/finalpresentation-12811076045889-phpapp01/85/Design-Project-17-320.jpg)
![Stage Pressure Ratio
Thermodynamics Distribution Stage Efficiency
In Out 0.920
1.25
P [kPa] 37,922 70,188 1.20
1.15 0.910
50,881 76,443
Etta
Po [kPa]
Pi
1.10
T [K] 262 317 1.05 0.900
To [K] 285 325 1.00
1 2 3 0.890
ρ [kg/m3] 0.505 0.772
1 2 3
V [m/s] 215 125 Rotor Stage
Rotor Stage
M 0.662 0.351
h0 [J/kg] 285,678 325,900
γ 1.4
R [J/kg·K] 287
Cp [J/kg·K] 1003
Stator Loss Coefficient
0.050
0.040
0.030
0.020
IGV Stator 1 Stator 2 Stator 3
Stage](https://image.slidesharecdn.com/finalpresentation-12811076045889-phpapp01/85/Design-Project-18-320.jpg)
![HPC Overall
Thermodynamics 1.9
Stage Pressure Ratio
1.8
Inlet Exit
Stage Pressure Ratio
1.7
Po [KPa] 76.4 1292.6 1.6
1.5
P [KPa] 68.4 1229.3
1.4
T [k] 314.7 763.0 1.3
To [k] 324.8 773.6 1.2
1.1
ρ [kg/m3] 0.758 5.620 1
V [m/s] 142.5 148.7 1 2 3 4 5 6 7 8 9
Stage
M 0.40 0.27
γ 1.38 1.38
R [J/kg·K] 286.7 286.7 0.920
Stage Efficiency
Cp [J/kg·K] 1041 1041 0.910
0.900
0.890
0.880
0.870
1 2 3 4 5 6 7 8 9](https://image.slidesharecdn.com/finalpresentation-12811076045889-phpapp01/85/Design-Project-25-320.jpg)
![Inlet Exit LPT Annulus
0.90
Po [KPa] 469 113
0.85
P [KPa] 436 106
0.80
T [k] 1320 905
0.75
Y Direction (Radial)
To [k] 1332 919
0.70
ρ [kg/m3] 1.272 .452 0.65
V [m/s] 163 171 0.60
M 0.24 0.30 0.55
γ 1.36 1.36 0.50
R [J/kg·K] 260 260 0.45
0.40
Cp [J/kg·K] 1013 1013
4.65
4.75
4.80
4.95
5.05
4.60
4.70
4.90
5.00
4.85
5.10
X direction (Axial)](https://image.slidesharecdn.com/finalpresentation-12811076045889-phpapp01/85/Design-Project-40-320.jpg)
![Fan STATOR: BP Nozzle
Bypass Nozzle 13 (Choked)
14
1.8
Po [Pa] 50,490 49,032
1.8
1.7 P [Pa] 42,658 25,903
1.7 To [K] 285 285
1.6
T [K] 271 237
1.6
1.5 ρ [kg/m3] 0.55 0.38
1.5 ho [J/kg] 285,678 285,678
1.4
Vax [m/s] 164 309
Y Direction (meters)
1.4
1.3 M 0.50 1.00
1.3 A [m2] 5.88 4.50
1.2
ηss 0.96
1.2
1.1
1.1
1.0
1.0
0.9
0.9
0.8
0.8
0.7
0.7
0.6
2.6
2.7
2.7
2.8
2.8
2.9
2.9
3.0
3.0
3.1
3.1
3.2
3.2
3.3
3.3
3.4
3.4
3.5
3.5
3.6
3.6
3.7
X direction (meters)](https://image.slidesharecdn.com/finalpresentation-12811076045889-phpapp01/85/Design-Project-48-320.jpg)
Design Project
- 1. J.L. Wilson
- 2. Section 1 Engine Specifications Section 2 Inlet Fan Design Fan Stator Section 3 Intermediate Pressure Compressor Section 4 High Pressure Compressor Section 5 Combustion Chamber Section 6 High Pressure Turbine Section 7 Low Pressure Turbine Section 8 Nozzles Ducts Design
- 3. Engine Design Choices BPR (x:1) 9.1 π 40.21 πFan 1.55 πIPC 1.52 πHPC 17.07 ζs 0.04 ηM 0.96 M@ SLS 1660 kg/s QR [J/kg] 4.30E+07
- 4. Overall h-s Diagram 1,800,000 1,600,000 HPT Combustion Chamber 1,400,000 1,200,000 Enthalpy (J/kg) 1,000,000 Duct 800,000 LPT 600,000 Nozzle HPC 400,000 IPC 200,000 Fan 0 0 50 100 150 200 250 300 350 400 450 500 550 600 650 700 750 800 850 900 950 Entropy (J/kg∙K)
- 5. Thrust Output SLS T.O. Cruise Units 25.2% of T.O. TOTAL 116,188 82,866 20,850 lbs Bypass 91,050 64,929 12,132 lbs Core 26,038 17,938 8,718 lbs Thrust Split 78 78 58 % T.I.T. 1900 1800 1760 K mfuel 4.86 4.34 1.67 kg/s f .0295 0.0264 0.0288 - SFC 0.3317 .4155 0.6358 lb/lbf·h
- 6. 5.90 5.80 5.70 5.60 5.50 5.40 5.30 5.20 5.10 5.00 4.90 4.80 4.70 4.60 4.50 4.40 4.30 4.20 4.10 4.00 3.90 3.80 3.70 3.60 3.50 Engine SideView 3.40 3.30 Axial (m) 3.20 3.10 3.00 2.90 2.80 2.70 2.60 2.50 2.40 2.30 2.20 2.10 2.00 1.90 1.80 1.70 1.60 1.50 1.40 1.30 1.20 1.10 1.00 0.90 0.80 0.70 0.60 0.50 0.40 0.30 0.20 0.10 0.00 1.50 0.70 1.90 1.80 1.70 1.60 1.40 1.30 1.20 1.10 1.00 0.90 0.80 0.60 0.50 0.40 0.30 0.20 0.10 0.00 Radial (m)
- 7. 1% increase in SLS Thrust 23% decrease in length Eliminates a stage in IPC, HPT, and LPT Perfect radius balance between HPC and HPT
- 9. Ambient: INLET: Position: a 1 Inlet Po 33,223 33,174 P 20,715 24,974 1.90 To 248 248 1.80 T 217 229 1.70 ρ 0.33 0.38 1.60 ho 248,802 248,802 h 217,390 229,417 1.50 Vax 251 197 1.40 M 0.85 0.65 1.30 R 287 287 1.20 γ 1.40 1.40 1.10 Radial (m) Cp 1003 1003 Area (m2) 7.82 1.00 Diameter [ft] - 10.35 0.90 0.80 0.70 Inlet Area Distribution 0.60 9.5 0.50 9.0 0.40 8.5 Area [m^2] 8.0 0.30 7.5 7.0 0.20 6.5 6.0 0.10 5.5 5.0 0.00 4.5 0.00 0.10 0.20 0.30 0.40 0.50 0.60 0.70 0.80 0.90 1.00 1.10 1.20 1.30 1.40 1.50 1.60 1.70 1.80 4.0 0 0.5 1 1.5 2 Axial (m) x [m]
- 11. Fan Annulus 1.850 RPM= 2720 1.800 1.750 1.700 π Fan=1.55 1.650 1.600 1.550 1.500 Mass Flow Cruise=587 kg/s 1.450 1.400 1.350 1.300 22 Blades 1.250 1.200 Y Direction (Meters) 1.150 Δh0=36,876 J/kg 1.100 1.050 1.000 0.950 0.900 H/T Avg=0.341 0.850 0.800 0.750 Diffusion Factor Avg=0.32 0.700 0.650 0.600 0.550 Tip Hade= -7º 0.500 0.450 0.400 0.350 Hub Hade=35º 0.300 0.250 0.200 0.150 Flow Coeff.=0.469 0.100 0.050 0.000 Work Coeff.=0.32 0.000 0.050 0.100 0.150 0.200 0.250 0.300 0.350 0.400 0.450 0.500 0.550 0.600 0.650 0.700 0.750 0.800 0.850 0.900 X direction (Meters)
- 12. Hub VAX=168 m/s Camber=45 Stagger=25 MRel=0.808 Mid VAX=168 m/s Camber=7 Stagger=59 MRel=1.17 Tip VAX=168 m/s Camber=1 Stagger=69 MRel=1.57
- 14. Thermodynamics Po 50881 50490 Fan Stator Annulus P 40210 42658 1.800 MRel=0.59 T 266 271 1.750 To 285 285 1.700 ρ 0.527 0.548 1.650 Camber=34 ° V 193 164 1.600 1.550 Vax 159 164 1.500 γ 1.4 1.4 1.450 Stagger=17 ° Y Direction (Meters) 1.400 R 287 287 1.350 Cp 1003 1003 1.300 1.250 ξ13 0.04 1.200 1.150 1.100 1.050 1.000 0.950 0.900 0.850 0.800 0.750 0.700 0.650 0.600 1.90 1.95 2.00 2.05 2.10 2.15 2.20 2.25 2.30 2.35 2.40 2.45 2.50 2.55 2.60 2.65 2.70 2.75 2.80 X direction (Meters)
- 15. Fan Operating Conditions Fan Composition Max Temperature 325 K Carbon Fiber Reinforced Polymer Min Temperature 216 K Density 1.79 g/cc Max Service Temperature 460 K Min Service Temperature 200 K Protected by polyurethane coating Leading Edge Titanium guards and Blade Protection Stator Composition Polyurethane Coating Ti- 3Al- 5Mo Max Service Temperature 378 K Density 4.35 g/cc Max Service Temperature 680 K Min Service Temperature 208 K Min Service Temperature 55 K Excellent durability vs. water Excellent durability vs. Acceptable durability vs. water, salt water, solvents, and oils, fuels, and salt water sunlight
- 16. Overall Pressure Ratio: 1.52 3 Stages with an IGV Work Done: 40,085 J/kg Power: 2,328,149 W (3,122 hp) Core Mass Flow: 58.08 kg/s RPM: 2720
- 17. Annulus Area Distribution Number of Blades 0.660 0.650 150 Area [m2] 0.640 130 0.630 110 Rotors 0.620 90 Stators 0.610 70 IGV 0.600 0.590 50 Stator Stator Stator IGV Rotor Rotor Rotor 1 2 3 2 1 3 2 1 3 IPC Annulus 0.90 0.85 0.80 Radial [m] 0.75 0.70 IGV R1 S1 R2 S2 R3 S3 0.65 0.60 0.55 Cascade Blade View 0.50 2.05 2.30 2.50 2.45 2.00 2.15 2.20 2.35 2.40 2.10 2.25 Axial [m]
- 18. Stage Pressure Ratio Thermodynamics Distribution Stage Efficiency In Out 0.920 1.25 P [kPa] 37,922 70,188 1.20 1.15 0.910 50,881 76,443 Etta Po [kPa] Pi 1.10 T [K] 262 317 1.05 0.900 To [K] 285 325 1.00 1 2 3 0.890 ρ [kg/m3] 0.505 0.772 1 2 3 V [m/s] 215 125 Rotor Stage Rotor Stage M 0.662 0.351 h0 [J/kg] 285,678 325,900 γ 1.4 R [J/kg·K] 287 Cp [J/kg·K] 1003 Stator Loss Coefficient 0.050 0.040 0.030 0.020 IGV Stator 1 Stator 2 Stator 3 Stage
- 19. Diffusion Factor on Stators Diffusion Factor on Rotors 0.500 0.500 0.400 0.400 0.300 0.300 DF Hub DF Hub 0.200 0.200 Mid Mid 0.100 0.100 Tip Tip 0.000 0.000 1 2 3 IGV 1 2 3 Rotor Stator Mrel Tip Flow and Work Coeff. 0.900 0.800 1.000 0.700 0.800 0.600 0.500 Mrel 0.600 Flow Coeff. 0.400 Rotors 0.400 Work Coeff. 0.300 0.200 Stators 0.200 0.100 0.000 0.000 1 2 3 1 2 3 4 5 6 7 8 Rotor Station
- 20. Titanium Ti-8Al-1Mo-1V Service Temp: 720 K Max IPC Temp: 317 K Ni-Cd Electroplated Coating Corrosion resistant
- 22. • 9 Stages with IGV and OGV • Overall Pressure Ratio – 17.04 • Mass Flow Rate – 58.08 kg/s • RPM -11100 • Power Required – 25.77 MW
- 23. 0.500 0.450 OGV 0.400 IGV 0.350 Y Direction (Radial) 0.300 HPC Diffuser 0.250 0.200 Stage 1 Stage 2 Stage 3 Stage 4 Stage 5 Stage 6 Stage 8 Pi = 1.85 Pi = 1.6 Pi = 1.44 Pi = 1.36 Pi = 1.32 Pi = 1.28 Pi = 1.21 0.150 Stage 7 Stage 9 Pi = 1.25 Pi = 1.15 0.100 0.050 0.000 3.60 3.70 3.05 3.30 3.50 3.15 3.20 3.45 3.00 3.35 3.65 3.75 3.10 3.40 3.55 2.95 3.25 X direction (Axial)
- 24. 0.600 Annulus Area Distribution 0.500 Overall Length (m) 0.634 0.400 Constant mid-radius (m) 0.397 Area (m2) 0.300 H/T inlet 0.456 0.200 H/T exit 0.932 0.100 0.000 Area inlet (m2) 0.538 S2 S6 S9 R1 S5 S7 S3 R4 OGV S1 R2 R8 S8 S4 IGV R3 R5 R6 R7 R9 Area exit (m2) 0.070 Stage Number of Blades 140 120 100 Number of Blades 80 Rotors 60 Stators IGV 40 OGV 20 0 IGV 1 2 3 4 5 6 7 8 9 OGV
- 25. HPC Overall Thermodynamics 1.9 Stage Pressure Ratio 1.8 Inlet Exit Stage Pressure Ratio 1.7 Po [KPa] 76.4 1292.6 1.6 1.5 P [KPa] 68.4 1229.3 1.4 T [k] 314.7 763.0 1.3 To [k] 324.8 773.6 1.2 1.1 ρ [kg/m3] 0.758 5.620 1 V [m/s] 142.5 148.7 1 2 3 4 5 6 7 8 9 Stage M 0.40 0.27 γ 1.38 1.38 R [J/kg·K] 286.7 286.7 0.920 Stage Efficiency Cp [J/kg·K] 1041 1041 0.910 0.900 0.890 0.880 0.870 1 2 3 4 5 6 7 8 9
- 26. Relative Mach Number 1.800 Overview 1.600 1.400 Relative Mach 1.200 •Transonic Compressor 1.000 0.800 Rotors • Aggressive Design 0.600 0.400 Stators 0.200 • Designed in Conjunction with HPT 0.000 1 2 3 4 5 6 7 8 9 Stage Diffusion Factor Rotors 0.700 Work and Flow Coefficients 0.600 0.50 0.500 Diffusion Factor Work Coefficient 0.40 0.400 0.30 TIP 0.300 0.20 MID 0.200 0.10 HUB 0.100 0.00 0.000 1 2 3 4 5 6 7 8 9 1 2 3 4 5 6 7 8 9 Stage Rotor Number
- 27. Titanium Alloy Ti-6Al-2Sn-2Zr-2Mo, annealed • Maximum Useful Temp. – 900 K • HPC maximum Service Temp. – 800K Nickel-Cadmium electroplated coating •Corrosion resistance
- 29. C.C. Design Choices ∏c.c. .99 C.C. Annulus 0.430 ζc.c. .99 .4 m 0.420 rm .6 m 0.410 radial height m L Diff. Combustion Chamber .045 m 0.400 dI Hub 0.390 Tip .03 m de 0.380 AI .116 m 0.370 .079 m 3.500 3.600 3.700 3.800 3.900 4.000 4.100 4.200 4.300 4.400 Ae 13 Axial length m d/L)inlet 20 d/L)exit
- 30. Flight Condition Thermo T.O. Cruise Inlet exit Inlet exit Po 4.01 MPa 3.96 MPa 1.24 MPa 1.23 MPa To 942 K 1800 K 800 K 1760 K ho 945.4 kJ/kg 2.03 MJ/kg 801.8 kJ/kg 1.98 MJ/kg Mach .16 .4 .16 .4 ZP ZI ZD Qf (JP-A) 4.30*107 J/kg % Combustion Zones M dot fuel 4.34 kg/s 1.23 kg/s ZP .20 f .0264 .0288 ZI .40 SFC .4151 lb/lbf h .6358 lb/lbf h ZD .40
- 32. Nickel Chromium N06004 Material Content N06004 C .15 % density 8.36 x 103 g/m3 Cr 18 % max service temp. ≈ 1900K Fe 28.3 % Young's modulus 6894.7 MPa Mn 1% Ni 60% S >.01% Si 1.75% Advantages reduces heat corrosion high heat resistance service operation @ 20,000 hrs
- 33. Single Stage Work Extracted : 481,899 J/kg Work Coefficient : 2.23 Mass Flow : 59.75 kg/s RPM : 11100
- 34. Blade Number 120 0.5 100 80 Stator 1 60 Y Direction (Radial) Rotor 1 0.45 40 20 0 0.4 Stage 1 0.35 Area 0.3 0.1500 4.25 4.3 4.35 4.4 4.45 0.1000 X direction (Axial) 0.0500 0.0000 LE 1 TE 2 LE 2 TE 3 Stator 1 Rotor 1 Stage 1
- 35. Thermo HPT In HPT Out P (Pa) 1,110,199 325,676 Velocity Distribution Po (Pa) 1,230,365 469,212 1000 T (K) 1,719 1,224 800 To (K) 1,760 1,332 600 ρ (kg/m3) 2.49 1.02 400 200 V ho (J/kg) 1,935,062 1,378,058 h (J/kg) 1,981,503 1,499,605 0 Vax V (m/s) 305 417 LE 1 TE 2 LE 2 TE 3 Vax (m/s) 305 493 M 0.40 0.758 Stator 1 Rotor 1 Δho (J/kg) 481899 Rpm 11100.00 Mdot (kg/s) 59.75 Density Static Pressure 3.000 1500000 2.000 1000000 1.000 500000 0.000 0 LE 1 TE 2 LE 2 TE 3 LE 1 TE 2 LE 2 TE 3 Stator 1 Rotor 1 Stator 1 Rotor 1
- 36. Stator 1 Rotor 1 LE 1 TE 2 LE 2 TE 3 rm 0.397 0.397 0.397 0.400 Area 0.0786 0.1200 0.1250 0.1400 α 0 64.6 65 -32 Vax 305 370 355 417 DoR Hub 0.416 Mid 0.482 Tip 0.558 Mrel Hub 0.000 0.771 0.758 1.271 Mid 0.000 0.694 0.694 1.290 Tip 0.000 0.632 0.612 1.310 Rothalpy 1621919 1621919 Flow Coeff 0.897 λ 2.229
- 37. Nickel Aluminide Nickel Cadmium Coating Max Temp ≈ 2400K Max Temp 1943 K Max service temp 1300 K Max Service Temp 1072 K Advantages Advantages heat resistant Resists heat corrosion load bearing Resists High temperature oxidation Easy to Cast
- 39. Stages 5 Work Extracted 417.8 KJ/kg Overall Pressure 4.15 Ratio Mass Flow Rate 59.75 kg/s RPM 2720
- 40. Inlet Exit LPT Annulus 0.90 Po [KPa] 469 113 0.85 P [KPa] 436 106 0.80 T [k] 1320 905 0.75 Y Direction (Radial) To [k] 1332 919 0.70 ρ [kg/m3] 1.272 .452 0.65 V [m/s] 163 171 0.60 M 0.24 0.30 0.55 γ 1.36 1.36 0.50 R [J/kg·K] 260 260 0.45 0.40 Cp [J/kg·K] 1013 1013 4.65 4.75 4.80 4.95 5.05 4.60 4.70 4.90 5.00 4.85 5.10 X direction (Axial)
- 41. Δh0 Distribution Pressure Ratio Distribution 25 1.50 1.45 20 1.40 1.35 Pressure Ratio Percent of Δho 15 1.30 1.25 10 1.20 1.15 5 1.10 1.05 0 1.00 1 2 3 4 5 1 2 3 4 5 Stage Stage
- 42. Annulus Area Distribution 1.000 0.900 0.800 0.700 Area 0.600 R² = 0.990 0.500 0.400 0.300 0.200 0 1 2 3 4 5 6 7 8 9 10 11 Stage Overall Length (m) 0.387 H/T inlet 0.833 H/T exit 0.779 Area inlet (m2) 0.340 Area exit (m2) 0.680
- 43. 2.500 2.250 2.000 Work Coefficient 1.750 1.500 Flow Coeffient 1.250 1.000 Degree of Reaction (mid) 0.750 0.500 Degree of Reaction (hub) 0.250 0.000 1 2 3 4 5 Number of Blades 250 200 150 Rotors 100 Stators 50 0 1 2 3 4 5
- 44. Nickel-Co-Cr Alloy, MAR–M 432 • Maximum Service Temp. = 1372 K • LPT maximum Service Temp. = 1332K Nickel-Cadmium Coating (Stage 1) • Max Temp. ≈ 2400 K • Max Service Temp. ≈ 1400 K • Resists heat corrosion • Resist high temperature oxidation
- 45. Inlet Exit 0.90 IPC-HPC Annulus P (Pa) 70,188 68,358 0.85 Po (Pa) 76,444 76,363 0.80 T (K) 317 315 0.75 To (K) 325 325 0.70 ρ (kg/m3) 0.772 0.758 0.65 Vax (m/s) 125 142 0.60 V (m/s) 171 142 0.55 M 0.351 0.40 γ 1.4 1.4 Radial (m) 0.50 0.45 Cp (J/kg∙K) 1003 1003 0.40 R (J/kg∙K) 287 287 0.35 ηss 0.96 0.30 0.25 V Duct Vax Duct 0.20 0.15 Distribution Distribution 0.10 200 150 0.05 150 140 0.00 100 130 2.40 2.45 2.50 2.55 2.60 2.65 2.70 2.75 2.80 2.85 2.90 2.95 3.00 3.05 3.10 50 120 Axial (m) 0 110 1 2 3 4 5 6 7 8 9 1 2 3 4 5 6 7 8 9
- 46. 0.475 Inlet Exit Y Direction (Radial) P (Pa) 1,227,026 1,265,456 0.425 Po (Pa) 1,292,511 1,289,759 T (K) 787 795 To (K) 799 799 0.375 ρ (kg/m3) 5.436 5.548 V (m/s) 153.8 92.8 M 0.274 0.165 0.325 γ 1.4 1.4 3.60 3.65 3.70 3.75 Cp (J/kg∙K) 1003 1003 R (J/kg∙K) 287 287 X direction (Axial) ηss 0.93 Duct Mach Variation Duct Area Variation 0.300 0.140 0.250 0.120 Mach Number 0.100 0.200 0.080 Area 0.150 0.060 0.100 0.040 0.050 0.020 0.000 0.000 1 2 3 4 5 1 2 3 4 5 Duct Station Duct Station
- 47. Core Nozzle Annulus 0.900 0.800 0.700 0.600 Radial (meters) 0.500 THERMO 0.400 Po 106276.88 P 56144.14 0.300 To 919.44 T 766.20 0.200 ρ 0.26 ho 922580.39 0.100 h 768817.00 0.000 Vax 554.55 V 4.400 4.500 4.600 4.700 4.800 4.900 5.000 5.100 5.200 5.300 5.400 5.500 5.600 5.700 554.55 M 1.00 Axial (meters) A 0.41
- 48. Fan STATOR: BP Nozzle Bypass Nozzle 13 (Choked) 14 1.8 Po [Pa] 50,490 49,032 1.8 1.7 P [Pa] 42,658 25,903 1.7 To [K] 285 285 1.6 T [K] 271 237 1.6 1.5 ρ [kg/m3] 0.55 0.38 1.5 ho [J/kg] 285,678 285,678 1.4 Vax [m/s] 164 309 Y Direction (meters) 1.4 1.3 M 0.50 1.00 1.3 A [m2] 5.88 4.50 1.2 ηss 0.96 1.2 1.1 1.1 1.0 1.0 0.9 0.9 0.8 0.8 0.7 0.7 0.6 2.6 2.7 2.7 2.8 2.8 2.9 2.9 3.0 3.0 3.1 3.1 3.2 3.2 3.3 3.3 3.4 3.4 3.5 3.5 3.6 3.6 3.7 X direction (meters)
Editor's Notes
- #21: The plate is then chromate-dipped and heat-treated at 650 degrees F for an hour to even out the cadmium over the nickel and to promote a diffusion bond. This heat treatment also drives off any absorbed hydrogen. Although the chromate coating is responsible for the color of the coating it serves no role other than protection of the cadmium layer prior to heat treatment.