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Cover picture by J.T. Genter April 27th, 2018
Amsterdam, October 26, 2018 AV2E15
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Executive Summary
The Antonov An-225 Mriya is currently used for large transport which are operations for long
haul as well as short haul. The Antonov airplane also has another function than what it was
designed for, namely it was used for transporting the Buran for military operations. Due to high
fuel prices and high current operating costs the Antonov design office and the department
Aviation Studies of Amsterdam University of Applied Science asked our group to reduce the
engines of the Antonov from six to four, and increase the range to 3200 nautical miles, carrying
a payload of 200 Tons.
Our advice is to use the GE90-85B engine and modify the following components by:
Increasing the bypass
Increasing the total inlet temperature
Expanding the compressor area by adding a compressor stage
Increasing the fan efficiency
Increasing the turbine efficiency
Increasing the nozzle efficiency
After these modification, the Antonov can reach the range of 3200 nautical miles, carrying a
budget. Another option we recommend is that Antonov uses the GE90-85B engine without any
the preferred payload. The Antonov will reach an distance of 2880 nautical miles while carrying
200 Tons.
The main question was:
What are the minimum performance requirements to replace the six jet engines with four
alternative (modified) jet engines, with which we can extend the range to 3200 NM with 8%
reserve fuel, with a payload of 200 Tons?
We did calculation on the five crucial flight phases to answer the main question. These flight
phases are cruise, holding, descent, enroute climb and second segment climb. Out of the
calculations, performance tables are produced. We retrieved the specific fuel consumption and
the minimum thrust based on these tables. The specific fuel consumption and the minimum
thrust determined the selection of engines. According to our calculations and assumptions, we
determined that the GE90-85B is the most suitable engine for the Antonov An-225 Mriya.
Amsterdam, October 26, 2018 AV2E15
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Contents
Executive Summary ................................................................................................................... 2
List of Symbols .......................................................................................................................... 4
List of Abbreviations .................................................................................................................. 6
1. Introduction ........................................................................................................................ 7
2. Theory & Methods ............................................................................................................. 8
2.1. Theory: Performance ................................................................................................... 8
2.1.1. Flight Phase 1: Cruise .......................................................................................... 8
2.1.2. Flight Phase 2: Holding ...................................................................................... 11
2.1.3. Flight Phase 3: Descent ...................................................................................... 12
2.1.4. Flight Phase 4: Enroute Climb ........................................................................... 13
2.1.5. Flight Phase 5: Second Segment Climb ............................................................. 16
2.2. Theory: Gas Turbine .................................................................................................. 18
2.3. Methods: Performance ............................................................................................... 26
2.3.1. Flight Phase 1: Cruise ........................................................................................ 26
2.3.2. Flight Phase 2: Holding ...................................................................................... 28
2.3.3. Flight Phase 3: Descent ...................................................................................... 30
2.3.4. Flight Phase 4: Enroute Climb ........................................................................... 32
2.3.5. Flight Phase 5: Second Segment Climb ............................................................. 34
3. Gas turbine: Results & Analysis ...................................................................................... 38
3.1. Recommended Values ............................................................................................... 38
3.2. The Selection of the Engines ..................................................................................... 38
3.3. Modification .............................................................................................................. 38
4. Conclusion and Recommendation .................................................................................... 43
4.1. Conclusion ................................................................................................................. 43
4.2. Recommendation ....................................................................................................... 43
References ................................................................................................................................ 44
List of Appendices ................................................................................................................... 46
Amsterdam, October 26, 2018 AV2E15
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List of Symbols
ah Speed of sound at altitude h in m/s
ch Vertical speed at altitude h in m/s
cx Speed at stage x in m/s
CD Drag coefficient
CD0 Parasitic drag coefficient
CL Lift coefficient
CT Specific fuel consumption in N/(N*s)
air Heat capacity ratio of air
e Oswald factor
g Earth-surface gravitational acceleration in
m/s2
p0 Pressure on sea level in Pa
ph Pressure at altitude h in Pa
px Pressure at stage x in Pa
px Ideal pressure at stage x in Pa
p0x Total pressure at stage x in Pa
p0x Total ideal pressure at stage x in Pa
average Average density between two selected
altitudes in kg/m3
0 Density on sea level in kg/m3
h Density at altitude h in kg/m3
The difference between current and next
altitude
,0.03 Maximum thrust with 0.03 thrust in N
h Altitude in m
k The fraction of 1 divided by the
multiplication of S, A.R. and
L Temperature lapse rat in K/m
Mh Mach number at altitude h
mfuel Mass of the fuel in kg
mfuel-1 Mass of the fuel of the previous altitude in kg
RS,air Specific gas constant for dry air in J/(kg*K)
RS,gas Specific gas constant for gas in J/(kg*K)
S Wing surface in m2
sy Vertical distance in m (meters)
sx Horizontal distance in m (meters)
sx-1 Horizontal distance of the previous altitude
in m (meters)
The difference of time between current and
next altitude
th Time at altitude h in min
th-1 Time from current to next altitude in min
TASh True airspeed at altitude h in m
TAS0 True airspeed on sea level in m
IASh Indicated airspeed at altitude h in m/s
T0 Temperature on sea level in K
Tx Temperature at stage x in K
Tx Ideal temperature at stage x in K
< Less than
Amsterdam, October 26, 2018 AV2E15
[This page is intentionally left blank]
Cover picture by J.T. Genter April 27th, 2018
Amsterdam, October 26, 2018 AV2E15
, 2
Executive Summary
The Antonov An-225 Mriya is currently used for large transport which are operations for long
haul as well as short haul. The Antonov airplane also has another function than what it was
designed for, namely it was used for transporting the Buran for military operations. Due to high
fuel prices and high current operating costs the Antonov design office and the department
Aviation Studies of Amsterdam University of Applied Science asked our group to reduce the
engines of the Antonov from six to four, and increase the range to 3200 nautical miles, carrying
a payload of 200 Tons.
Our advice is to use the GE90-85B engine and modify the following components by:
Increasing the bypass
Increasing the total inlet temperature
Expanding the compressor area by adding a compressor stage
Increasing the fan efficiency
Increasing the turbine efficiency
Increasing the nozzle efficiency
After these modification, the Antonov can reach the range of 3200 nautical miles, carrying a
budget. Another option we recommend is that Antonov uses the GE90-85B engine without any
the preferred payload. The Antonov will reach an distance of 2880 nautical miles while carrying
200 Tons.
The main question was:
What are the minimum performance requirements to replace the six jet engines with four
alternative (modified) jet engines, with which we can extend the range to 3200 NM with 8%
reserve fuel, with a payload of 200 Tons?
We did calculation on the five crucial flight phases to answer the main question. These flight
phases are cruise, holding, descent, enroute climb and second segment climb. Out of the
calculations, performance tables are produced. We retrieved the specific fuel consumption and
the minimum thrust based on these tables. The specific fuel consumption and the minimum
thrust determined the selection of engines. According to our calculations and assumptions, we
determined that the GE90-85B is the most suitable engine for the Antonov An-225 Mriya.
Amsterdam, October 26, 2018 AV2E15
, 3
Contents
Executive Summary ................................................................................................................... 2
List of Symbols .......................................................................................................................... 4
List of Abbreviations .................................................................................................................. 6
1. Introduction ........................................................................................................................ 7
2. Theory & Methods ............................................................................................................. 8
2.1. Theory: Performance ................................................................................................... 8
2.1.1. Flight Phase 1: Cruise .......................................................................................... 8
2.1.2. Flight Phase 2: Holding ...................................................................................... 11
2.1.3. Flight Phase 3: Descent ...................................................................................... 12
2.1.4. Flight Phase 4: Enroute Climb ........................................................................... 13
2.1.5. Flight Phase 5: Second Segment Climb ............................................................. 16
2.2. Theory: Gas Turbine .................................................................................................. 18
2.3. Methods: Performance ............................................................................................... 26
2.3.1. Flight Phase 1: Cruise ........................................................................................ 26
2.3.2. Flight Phase 2: Holding ...................................................................................... 28
2.3.3. Flight Phase 3: Descent ...................................................................................... 30
2.3.4. Flight Phase 4: Enroute Climb ........................................................................... 32
2.3.5. Flight Phase 5: Second Segment Climb ............................................................. 34
3. Gas turbine: Results & Analysis ...................................................................................... 38
3.1. Recommended Values ............................................................................................... 38
3.2. The Selection of the Engines ..................................................................................... 38
3.3. Modification .............................................................................................................. 38
4. Conclusion and Recommendation .................................................................................... 43
4.1. Conclusion ................................................................................................................. 43
4.2. Recommendation ....................................................................................................... 43
References ................................................................................................................................ 44
List of Appendices ................................................................................................................... 46
Amsterdam, October 26, 2018 AV2E15
, 4
List of Symbols
ah Speed of sound at altitude h in m/s
ch Vertical speed at altitude h in m/s
cx Speed at stage x in m/s
CD Drag coefficient
CD0 Parasitic drag coefficient
CL Lift coefficient
CT Specific fuel consumption in N/(N*s)
air Heat capacity ratio of air
e Oswald factor
g Earth-surface gravitational acceleration in
m/s2
p0 Pressure on sea level in Pa
ph Pressure at altitude h in Pa
px Pressure at stage x in Pa
px Ideal pressure at stage x in Pa
p0x Total pressure at stage x in Pa
p0x Total ideal pressure at stage x in Pa
average Average density between two selected
altitudes in kg/m3
0 Density on sea level in kg/m3
h Density at altitude h in kg/m3
The difference between current and next
altitude
,0.03 Maximum thrust with 0.03 thrust in N
h Altitude in m
k The fraction of 1 divided by the
multiplication of S, A.R. and
L Temperature lapse rat in K/m
Mh Mach number at altitude h
mfuel Mass of the fuel in kg
mfuel-1 Mass of the fuel of the previous altitude in kg
RS,air Specific gas constant for dry air in J/(kg*K)
RS,gas Specific gas constant for gas in J/(kg*K)
S Wing surface in m2
sy Vertical distance in m (meters)
sx Horizontal distance in m (meters)
sx-1 Horizontal distance of the previous altitude
in m (meters)
The difference of time between current and
next altitude
th Time at altitude h in min
th-1 Time from current to next altitude in min
TASh True airspeed at altitude h in m
TAS0 True airspeed on sea level in m
IASh Indicated airspeed at altitude h in m/s
T0 Temperature on sea level in K
Tx Temperature at stage x in K
Tx Ideal temperature at stage x in K
< Less than
Amsterdam, October 26, 2018 AV2E15
