Propulsion Lab Guide - Department of Aerospace Engineering

AEROSPACE ENGINEERING
AE547
EXPERIMENTAL AERODYNAMICS
Instructor:
LABWORK
GT100 TURBOJET TRAINER
FINAL REPORT
Assoc. Prof. Dr. Dilek Funda Kurtuluş
Prepared by:
Ezgi Anık
Ebru Sema Koşaroğlu

Abstract
The main purpose of the lab work is to prepare a user manual for undergraduate students of
Aerospace Engineering Department about new equipment provided by Lockheed Martin as a part of
our graduate course “Experimental Aerodynamics”. According to this purpose, “GT100 Turbojet
Trainer “is introduced for the propulsion experiments. Firstly, general information about trainer is
given. This report also includes technical specifications, working procedure and important notes for
“GT100 Turbojet Trainer”. The working procedure is explained to provide better understanding for
students.

Content List
Abstract ................................................................................................................................................... 1
Introduction ............................................................................................................................................. 3
GT100 Turbojet Trainer ........................................................................................................................... 4
Technical Specifications....................................................................................................................... 5
Specifications ................................................................................................................................... 5
Important Services .......................................................................................................................... 5
Operating Conditions ...................................................................................................................... 5
Capabilities ...................................................................................................................................... 5
Fuel Specifications ........................................................................................................................... 6
Working Principle ................................................................................................................................ 6
Working Procedure ............................................................................................................................. 7
GT100 Turbojet Software .................................................................................................................. 11
Sample Experiment ........................................................................................................................... 12
Conclusion ............................................................................................................................................. 12
Acknowledgement ................................................................................................................................. 13
References ............................................................................................................................................. 13

Introduction
The best way of teaching is associating the theory and practice with each other. This
can be provided with laboratory work in engineering and science. In order to obtain practical
knowledge, a demonstration was performed in Aerospace Engineering Hangar Building. The
experimental procedure was repeated four times with the help of TecQuipment personnel for a
better understanding. Therefore, this report mostly includes the experimental procedure of
GT100 Turbojet Trainer. However, technical specifications are also mentioned in this final
report. Especially, working procedure part will be beneficial for students who want to learn
how to use “GT100 Turbojet Trainer”. In this part, some photographs are given as figures to
provide better information about working steps.

GT100 Turbojet Trainer
Turbojet Trainer is a laboratory device that helps us to understand the mechanism and
performance of a kerosene powered single-shaft gas turbojet. GT100 Turbojet Trainer
includes an Automatic Data Acquisition (ADA) system, "Gas Turbine Theory" textbook and a
fully schematic instrumentation panel diagram to make procedure more comprehensible.
Turbojet Trainer should be connected to a computer with data acquisition software
which allows display, graph, analyze and save the data collected from the Automatic Data
Acquisition (ADA) system. The data acquisition system includes adaptors and leads, and the
software is supplied on CD-ROM.
Trainer works simply by air transfer from an air box through a compressor and a
combustion chamber at the mean time a fuel pump transfer fuel from a fuel tank and spray
into the combustion chamber. Then, a spark ignites the air and fuel mixture while the mixture
flows through a radial turbine then a variable area propelling nozzle and finally mixture
exhausts from the exhaust system.
Figure 1: GT100 Turbojet Trainer [1].

Technical Specifications
Specifications
Net dimensions and weight: 1350 mm x 1700 mm x 750 mm and 350 kg (with no fuel or oil)
Packed dimensions and weight: 3.6 m3 and 525 kg
Fuel (Kerosene-Jet A1) specification:
o Specific gravity (or relative density): 0.78
o Net calorific value: 43.6 x 106 J/kg
o Flash point: 38 to 66°C
o Freezing point: -38 to 46°C
o Viscosity: 1.4 to 2.5 x 10-6 m2.s-1
o Boiling-point (final): 260°C
Speed range: 50 000 to 90 000 rpm
Important Services
Floor space needed: 2000 mm x 2000 mm of solid, level floor
Electrical supply: 230 VAC, 50 Hz single-phase (other ratings available - specify on order)
Water supply: At least 18 liters/minute
Exhaust: At least 200 mm diameter, direct to atmosphere
Vent: For oil breather pipe - 19 mm
Operating Conditions
Operating environment: Dry and well-ventilated engine test laboratories
Storage temperature range: –25ºC to +55ºC (when packed for transport)
Operating temperature range: +5ºC to +40ºC
Operating relative humidity range: 30% to 95% (non-condensing)
Capabilities
The software is capable to calculate the following performance characteristics by changing
mass fuel rate and nozzle area:
Thrust generation
Isentropic, polytropic and mechanical efficiencies of compressor, combustion chamber and
turbine
Pressure ratios of turbine, compressor and non-dimensional characteristics
Combustion chamber pressure losses and combustion efficiencies
Specific fuel consumption, thermal efficiency, air standard cycle, work ratio and heat balance

Fuel Specifications
Specific gravity 0.78
Net calorific value 43.6x10 6 J/kg
Flash point 3866˚C
Freezing point -3846˚C
Boiling Point 260˚C
Working Principle
Trainer works simply by air transfer from an air box through a compressor and a combustion
chamber at the mean time a fuel pump transfer fuel from a fuel tank and spray into the combustion
chamber. Then, a spark ignites the air and fuel mixture while the mixture flows through a radial
turbine then a variable area propelling nozzle and finally mixture exhausts from the exhaust system.
Figure 1: Turbojet Layout

Working Procedure
1. Water Supply Connection should be checked (Figure 5).
2. Oil pipe should be away from exhaust as much as possible.
3. Exhaust pipe should be checked whether it is open to atmosphere or not (Figure 2).
4. Fuel valve at the lower part of the Trainer frame should be checked (Figure 3). It should be
open before Trainer starts to work. This valve should not be closed.
5. Computer and Trainer connection should be checked to provide the data collection.
Moreover, computer program should be opened.
6. The power button which is on the right hand side of the Turbojet Trainer should be switched
“on” (Figure 4).
7. The Purge/Shutdown (Figure 6) button should be checked whether it is in outward position or
not. It should be in outward position while Trainer is working.
8. Fans button (Figure 6) should be pressed in order to start fans and oil pumps for cooling.
When the fans are activated, the oil pumps become active automatically. If this does not
occur, oil pumps should be activated manually.
9. After all these steps are performed, the led lights (Figure 6, N1 speed-oil pressure-water
supply-T3 temperature-jet pipe temperature) on the Trainer should be checked whether they
are green or not. If all of them are green, then Trainer is ready to operate.
10. While Turbojet Trainer is being started, nozzle area indicator should show its maximum value
(100 %).
11. Fuel flow valve should be turned three times to the left while the fuel pump button is being
pressed simultaneously. It is very important to do both of them at the same time. If not fuel
is wasted. Just after this procedure, the ignition button should be pressed immediately (Figure
6) .If the ignition button is not pressed at the right time, then fuel flow valve should be closed
to the right immediately. Now, Turbojet Trainer is ready for experiment. The data collection

is provided according to needed time interval using the start time capture link in the
program.
12. Nozzle area and fuel flow rate can be changed according to the experimental requirement.
13. N1 (rpm) should be checked during the experiment. It should not exceed 90000 rpm value.
14. After experiment is done, N1 (rpm) value is decreased to 50 rpm while turning the fuel flow
valve to the right. After it is decreased to 50 rpm, Purge/Shutdown button is pressed. (N1-
rpm indicator can be seen from Figure 6.)
15. After that, fans and oil pumps starts and stops automatically. This automatic start and stop
should be waited for cooling of the system sufficiently before Turbojet Trainer is switched off
entirely.
Figure 2: Exhaust
Figure 3: Fuel Valve

Figure 4: Power Button
Figure 5: Water Inlet and Outlet Pipes

Figure 6: Front Panel
Some of the abridgments such as T3a, P4 in the figure are explained in the following table:
Table 1: Nomenclature
Important Note: If Turbojet Trainer is needed to shut down immediately, Purge/ Shutdown (Figure
6) button is pressed and instantly the fuel flow valve should be closed (turning to the right).

GT100 Turbojet Software
Figure 7: Turbojet Software
As it can be seen from Figure 7 , all of the required parameters are listed in different subtitles
in Turbojet Software. Fuel properties, all temperature values, all pressure values, work done and
efficiencies can be seen from this software. Moreover, according to different time intervals the data
acquisition is possible. Start time capture link in the tool bar provides to change this time interval
(seconds). In addition to this, data can be saved as html or data file (see Appendix B). If the saved file
is not deleted, for the same data series, new data are added to the previous data without changing
the old ones. This allows to see the previous experiments and to make comparison between different
experiments.

Sample Experiment
An experiment was performed to understand better how Turbojet Trainer and Software
work. As it can be seen from Figure 8 , the nozzle area was started to change at 54th second and time
interval is determined as 9 seconds. Therefore, data is recorded in every 9 seconds. Speed (as rpm)
was controlled during experiment not to exceed 90000 rpm. Temperatures, pressures, fuel
properties, nozzle area and thrust values were recorded as it was mentioned in previous subtitle.
Time
Time
T1 - T2 -
Ta -
Ambien
Compre Compre
T3a
t air
ssor ssor
inlet outlet
T3b
T3 -
Pa -
Turbine T4 - Jet
ΔP1 -
Ambien
inlet pipe
t air
Airbox
average
P2 -
P3 -
Compre
P4 - Jet N1 x
Turbine
ssor
pipe 1000
inlet
outlet
mf -
Fuel
Mass
Flow
F -
Thrust
Na - %
Area
Work
done
Isentrop
Compre
ic
Work
ssion
Efficien
done
Ratio
cy
Isentrop Mechani Isentrop
Fuel
Air /
ic cal
ic
Calorific Fuel
Efficien Efficien
Efficien
Value
Ratio
cy cy
cy
(s) (°C) (°C) (°C) (°C) (°C) (°C) (°C) (mbar) (mbar) (bar) (bar) (mbar) (rpm) (g/s) (N) (%) (W) (%) (W) (%) (%) (kJ.kg -1 Temperatures Pressures
Data Series 1
Miscellaneous Parameters Compressor Turbine Burner
) (%)
0 18 21 37 128 124 126 144 917 2.8 0.09 -0.01 1 18.8 -0.01 -14.6 100 1315 50 1.098 -1693 1505 -78 43600 -1678 0
9 18 22 37 95 89 92 113 917 2.8 0.09 -0.01 1 18.5 0 -16.7 100 1233 53 1.098 -1975 1920 -62 43600 -- 0
18 18 22 36 77 71 74 93 917 2.8 0.08 -0.01 1 18.3 0 -18.6 100 1151 51 1.087 -1787 1827 -64 43600 -- 0
27 18 22 39 241 257 249 217 917 7.5 0.41 -0.01 10 60.6 1.8 -0.6 100 2286 193 1.447 4990 -1129 46 43600 36 0.013
36 18 22 46 400 421 410 338 917 7.9 0.44 -0.01 10 62.3 1.8 11.7 100 3314 146 1.48 11526 -1942 29 43600 64 0.013
45 18 21 50 466 473 470 393 917 8 0.44 -0.01 11 62.7 1.8 25.7 100 4028 120 1.48 12397 -1819 32 43600 74 0.013
54 18 19 50 488 486 487 415 917 8.7 0.47 -0.01 14 64.4 1.78 33.6 91 4489 118 1.513 12079 -1457 37 43600 82 0.012
63 18 18 53 506 499 502 428 917 11.2 0.59 -0.01 32 71.2 2.05 42.3 69 5755 127 1.643 14097 -845 41 43600 83 0.013
72 18 17 57 513 500 506 428 917 14.7 0.72 -0.01 28 78.3 2.27 49.1 100 7533 131 1.785 17013 -978 44 43600 85 0.012
81 18 16 65 531 500 516 421 917 20.6 0.96 -0.01 45 88.5 2.62 56.2 100 10923 134 2.047 24518 -818 45 43600 88 0.012
90 18 16 68 499 467 483 409 917 5.5 0.3 -0.01 5 52.3 1.27 58.6 100 5989 47 1.327 9861 -2400 61 43600 86 0.011
99 18 18 61 383 371 377 364 917 3 0.11 -0.01 2 24.2 0.04 44.5 100 3656 22 1.12 1265 -612 289 43600 1541 0
108 18 19 56 253 244 248 272 917 2.9 0.1 -0.01 2 21.9 -0.02 41.4 100 3094 24 1.109 -2296 1410 -135 43600 -1841 0
117 18 20 53 180 171 176 212 917 2.8 0.1 -0.01 2 21 -0.02 36.8 100 2713 27 1.109 -3386 2454 -80 43600 -1160 0
Time
Time
T1 - T2 -
Ta -
Compre Compre
Ambien
T3a
t air
ssor ssor
inlet outlet
T3b
T3 -
Pa -
Turbine T4 - Jet
ΔP1 -
Ambien
inlet pipe
t air
Airbox
average
P2 -
P3 -
Compre
P4 - Jet N1 x
Turbine
ssor
pipe 1000
inlet
outlet
mf -
Fuel
Mass
Flow
F -
Thrust
Na - %
Area
Work
done
Isentrop
Compre
ic
Work
ssion
Efficien
done
Ratio
cy
Isentrop Mechani Isentrop
Fuel
Air /
ic cal
ic
Calorific Fuel
Efficien Efficien
Efficien
Value
Ratio
cy cy
cy
(s) (°C) (°C) (°C) (°C) (°C) (°C) (°C) (mbar) (mbar) (bar) (bar) (mbar) (rpm) (g/s) (N) (%) (W) (%) (W) (%) (%) (kJ.kg -1 Temperatures Pressures
Data Series 1
Miscellaneous Parameters Compressor Turbine Burner
) (%)
-- 12 12 33 145 146 146 106 923 -0.2 -0.01 -0.02 -2 0 -0.03 15.5 68 469 -4 0.989 1020 -1944 46 43600 -193 -0.001
-- 12 13 33 145 145 145 106 923 -0.2 -0.01 -0.02 -2 0 -0.03 15.5 68 446 -4 0.989 994 -1900 45 43600 -191 -0.001
-- 12 13 33 145 146 146 106 923 -0.2 -0.01 -0.02 -2 0 -0.03 15.4 68 446 -4 0.989 1020 -1944 44 43600 -193 -0.001
Conclusion
Figure 8: Experimental Data (as html file)
According to the main purpose of this lab work, “GT100 Turbojet Trainer” was studied both
theoretically and experimentally. Therefore, general information was given briefly. Firstly, technical
specifications were mentioned such as specifications, operating conditions and capabilities. Then,
working principle, procedure and Turbojet Software were mentioned. Especially, the working
procedure of “GT100 Turbojet Trainer” was explained step by step to provide better understanding
for students. Finally, a sample experiment results were shown as a figure.

Acknowledgement
We are extremely grateful to Melika GÜL for her support and help in our lab work.
References
1. GT100 Turbojet Trainer Safety Guide
2. GT100 Turbojet Trainer User Guide
3. Retrieved, October 16,2012, from TecQuipment
http://www.tecquipment.com/Thermodynamics/Gas-Turbines/GT100.aspx
4. Laboratory Experiment