Customer presentation for high bypass turbofan design in competition with the GE 90-115B

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)