This document provides an overview of gas turbine fundamentals and components. It discusses the gas turbine course topics which include the lubrication oil system, hydraulic oil system, trip oil system and other key systems. It then summarizes the components and operation of a GE 9001E gas turbine, including descriptions of the compressor, combustion system, turbine, bearings and lubrication oil system.

1. GAS TURBINE COURSE
1. GAS TURBINE FUNDAMENTALS
2. GAS TURBINE COMPONENTS
3. LUBRICATION OIL SYSTEM
4. HYDRAULIC OIL SYSTEM
5. TRIP OIL SYSTEM
6. VARIABLE INLET GUIDE VANES, IGV
7. STARTING SYSTEM

2. GAS TURBINE COURSE
8. FUEL SYSTEM
9. COOLING & SEALING AIR SYSTEM
10. COOLING WATER SYSTEM
10. ATOMIZING AIR SYSTEM
11. FIRE PROTECTION SYSTEM
12. COMPRESSOR WATER WASHING
13. GAS TURBINE MAINTENANCE

3. STEAM TURBINE
STEAM
HP/IP LP MW
LOAD
STEAM
GENERATOR (BOILER)

4. GAS TURBINE (OPEN CYCLE)
FUEL
COMBUSTION
CHAMBER
HIGH TEMPERATURE/PRESSURE GAS
HIGH PRESSURE
AIR
MW
AIR INLET LOAD
TURB
COMPRESSOR

5. HEAT ENGINE
• A DEVICE THAT CONVERTS HEAT
INTO WORK IS KNOWN AS HEAT
ENGINE
EXAMPLE :
- Petrol Engine
- Diesel Engine
- Gas Turbine Engine
- Steam Engine

6. HEAT ENGINE
High Temperature Source
Output
Heat Engine W
Heat Sink

7. Otto Cycle
Pressure (P)
1 - 2 Compression
3 2 - 3 Combustion
3 - 4 Expansion
4 - 1 Exhaust
4
2
1
Volume (V)

8. DIESEL CYCLE
Pressure (P) 1 - 2 Compression
2 - 3 Combustion
3 - 4 Expansion
3 4 - 1 Exhaust
2
4
1
Volume (V)

9. BRAYTON CYCLE
(Constant Pressure Cycle)
Pressure (P)
1 - 2 Compression
3 2 - 3 Combustion
2
3 - 4 Expansion
4 - 1 Exhaust
4
1
Volume (V)

10. Fundamental of Gas Turbine
FUEL
4 c = compressor
b = burners
2 b t = turbine
c t GENERATOR
3
AIR
1
When the Brayton Cycle is worked out for a steady flow
process, we have a simple gas turbine cycle.
In a simple gas turbine cycle, combustion & exhaust occur
at constant pressure and compression & expansion occur
continuously.

11. General Description of GE 9001E
• The Model Series 9001E gas turbine is a 3000
rpm, single shaft with a 14 combustor, reverse-
flow combustion system, simple-cycle power
package that basically requires only fuel & fuel
connections, generator breaker and AC power
source for turbine start-up.
• The MS9001E is also available in a combined-
cycle configuration for application utilizing a Heat
Recovery Generator or similar device

12. Gas Turbine Unit
• The gas turbine unit consists of a 17-stage axial flow
compressor and a 3-stage power turbine.
• Each section, compressor rotor & turbine rotor is
assembled separately and joined together through bolt
construction.
• The assembled rotor is a three bearing design utilizing
pressure-feed elliptical & tilt-pad journal bearings. This
design assures that rotor-critical speed are above the
operating speed for optimum turbine bucket/turbine shell
clearances.

13. Gas turbine Components
• The MS9001E gas turbine assembly consists of
six major section or groups :
1. Air inlet
2. Compressor
3. Combustion system
4. Turbine
5. Exhaust
6. Support system

14. Gas Path Description
Starting system actuated - ambient air drawn in through inlet plenum -
compress in 17 stages axial compressor - compressed air flow into
annular space surrouding 14 combustion chambers - flows into liners
through metering holes.
Fuel from off-base source divide into 14 equal flows lines - fuel is
equally controlled into 14 nozzles - ignition by spark plugs - flame
propagate through crossfire tubes - combustion chamber pressure
causes spark plug retract from hot flame zone at operating speed.
Hot gas from combustion chamber expand into 14 separate transition
piece - flow through 3-stage turbine section (rows of fixed nozzles &
rotating buckets) - In fixed nozzles (kinetic energy increased &
pressure drop) - In moving buckets (kinetic energy turn to rotor
rotation to generate electrical power)

15. Gas Path Description - continue
After 3rd. Stage buckets - gases directed into exhaust hood
& diffuser (a series of turning vanes to turn the gases from
axial to radial direction, minimizing exhaust hood losses) -
Gases pass into exhaust plenum - introduced to atmosphere
through exhaust stack.

16. Accessory Compartment
• Several system involved in turbine operation located in
this section :
1. Starting Mean
2. Fuel System
3. Lubrication & Seal Oil System
4. Hydraulic System
5. Cooling Water System
6. Atomizing Air System
Major components - starting motor, torque converter &
accessory drive gear.

17. Turbine Base & Support
• Turbine base - supports the gas turbine & is a structural steel
fabrication of welded steel beam & plates.
• Turbine supports - gas turbine is mounted to its base by vertical
supports at three locations :
1. Forward support
2. Two Aft supports (with cooling jacket) - on either side of
exhaust frame
• Gib key & Guide Block - Gib key is machined on lower half of turbine
shell & fit into the guide block which is welded to the aft cross beam
of turbine base (prevent lateral & rotational movement & permitting
axial & radial movement for thermal expansion)

18. Compressor Section
• The Axial flow Compressor section consists of :
1. Compressor Rotor
2. Enclosing Casing
Within the compressor casing are Inlet guide Vanes (IGV), 17 stages
of rotor & stator airfoil-shaped blades and exit guide vanes.
The stator (casing) for compressor composed of four major sections :
1. Inlet casing
2. Forward Compressor casing
3. Aft Compressor casing
4. Compressor discharge casing

19. Combustion System
• The combustion system is a reverse-flow type with 14
combustion chambers arranged around the periphery of the
compressor discharge casing.
• The major components consists of :
1. Fuel nozzles
2. Spark plug ignition system
3. Ultraviolet flame detector
4. Combustion wrapper
5. Combustion chamber - comb. liners & transition piece
6. Crossfire tubes

20. Turbine Section
• The three-stage turbine section is the area where energy, in
the form of high temperature pressurized gas produced by
the compressor & combustion sections, is converted to
mechanical energy.
• Major components in the turbine section are :
1. Turbine rotor - consists of two wheel shafts, the 1st., 2nd. & 3rd.
Stage turbine wheel with buckets & two turbine spacers.
2. Turbine stator - consists of turbine shell and exhaust frame.
Turbine stationary nozzles, diaphragm, shroud, bearing no. 3 &
exhaust diffuser are internally supported from these components.

21. Bearings
• The MS9000 gas turbine unit contain three main journal
bearings used to support the gas turbine rotor & thrust
bearing to maintain rotor to stator axial position & support
thrust load developed on the rotor.
No. Class Type
1 Loaded Tilting pad -thrust equalizing
1 Unloaded Tilting pad - non thrust equalizing
1 Journal Elliptical
2 Journal elliptical
3 Journal Tilting pad.

32. Lubrication Oil System
• The lubricating requirements for the gas turbine
are furnished by a common forced-feed lubrication
system. Lubricating fluid is circulated to the three
main turbine bearings, generator bearings,
reducing gear, accessory gear, as hydraulic oil in
torque converter and also as control, trip oil, high
pressure hydraulic oil & generator seal oil.

33. Lub. Oil System - continue
• Such a system must supply cool, clean and pressurized oil to bearing.
This lub. system includes the following :
1. Lub. oil reservoir in the accessory base (12,490 liter)
2. Main lub. oil pump (shaft driven from accessory gear).
3. Auxiliary lub. oil pump
4. Emergency lub. oil pump
5. Auxiliary & emergency seal oil pump
6. Lub. oil heat exchangers
7. Lub. oil filters.
8. Pressure relief valve VR1 in main pump discharge header (6.9)
9. Bearing header pressure regulator VPR2-1 (1.7 bars)
10. Mist Eliminator

34. Lub. oil system - control components
• Some important operating parameters monitored by Speedtronic Mark
V control system :
1. Oil Level Detection
71 QH = Level detector switch, Alarm when level is high (254 mm)
71 QL = Level detector switch, alarm when level is low ( 432 mm)
2. Pressure & Temperature Protective Devices
63QT-2A & 2B = Pressure switch in lub. oil feed piping to generator
bearings. Trip turbine when < 0.55 bar
63QT-1A & 1B = Temperature switch in lub. oil header.
Trip the turbine if temperature > 79.4o C
63 QQ-1 = Differential pressure switch
alarm when pressure across oil filters of 1.03 bar (15 psi)

35. Lubricating oil Pumps
• Main Oil Pump - positive displacement pump mounted on & driven by
the accessory gear, rated 2725 lpm & 7 bar.
• Auxiliary Oil Pump - submerged centrifugal pump driven by AC
motor (88QA-1), rated 2460 lpm & 7.5 bar.
Higher pressure for torque converter during slow roll & start-up.
Starts when speed drop below 14HS (90% rated speed) stop when
turbine attains 95% rated speed.
Also when 63QA-1 sense a drop below 4.83 bar.
• Emergency Lub. Oil Pump - submerged centrifugal pump driven by a
DC motor (88QE-1).
Rated at 1590 lpm & 1.4 bar. Back-up for AOP when 63QT-2A & 2B
below 0.55 bar.

36. Seal Oil Pump
• The seal oil to the generator bearings is normally supplied
by the main lub. system through a separate line directly to
the seal oil control unit of the generator. This line is
plumbed into the system upstream of VPR2-1. The seal oil
control unit will regulate the seal oil pressure to maintain it
a nominal 0.32 bar above hydrogen gas pressure.
• The seal oil pump is driven by two motors :
AC motor - 88QS-1
DC motor - 88ES-1

37. GE Gas Turbine Device Code - 1st. letter
Q - Lub. oil
H - Hydraulic/heater
A - Air
F - Fuel/flow/fire
D - diesel/divider
C - Clutch/Compressor/Co2
T - Trip/turbine
P - Purge
W - Water/warm
S - Stop/speed/start
G - Gas

38. GE Gas Turbine Device Code - 2nd letter
A - Alarm/accessory/air/atomization
B - booster/bleed R - Release/ratio/rachet
C - Cooling/control S - Start
D - Divider/differential T - Turbine/trip/tank
E - Emergency V - Valve/Vane
F - Fuel
G - Gas
H - Heater/high
L - Low level/liquid
M - Middle/medium/minimum
N - Normal
P - Pressure/Pump
Q - Lub. oil

39. Code designation by figures
12 - Overspeed mechanism 77 - Speed senser
20 - Solenoid valve 88 - Electric motor
23 - Heating device 90 - Modulating valve
26 - Temperature switch 96 - Pressure transmitter
33 - Limit switch
39 - Vibration detector
43 - Manual switch
45 - Fire detector
49 - Overload protection
63 - Pressure switch
65 - Servo. Valve
71 - Level detecting system

40. Hydraulic Supply System
• Hydraulic supply system provides fluid power required for
operating the control components of the gas turbine fuel
system. The fluid furnished the means for opening or
resetting the fuel stop valves, in addition to the variable
turbine inlet guide vanes and the hydraulic control & trip
devices of the gas turbine.
• Major system components includes the main hydraulic
pump, an auxiliary supply pump, the system filters, an
accumulator assembly and the hydraulic supply manifold
assemblies.

41. Trip Oil System
• The hydraulic trip oil system is the primary interface
between the turbine protection system circuits of the
Speedtronic Mark V Control System and the the
components on the turbine which open the IGVs and allow
fuel flow to turbine.
• The trip oil system contains devices which are eletrically
operated by Speedtronic control signals as well as
completely mechanical devices that operate directly on trip
oil system independent of the turbine control panel.
• The trip oil system ensures that fuel flow is halted & the
IGVs close at a unit trip.

42. Variable Inlet Guide Vanes (IGVs)
• IGVs are used to control the airflow through the
compressor, in turn controlling the airflow through the
entire machine.
• The IGVs modulate during the start-up and acceleration of
the gas turbine to rated speed, loading & unloading of the
generator and deceleration of the gas turbine during
shutdown.
• This modulation maintains proper flows & pressure, and
thus stresses in the compressor during part-speed
operation, maintains a minimum pressure drop across fuel
nozzles while operating at 100% speed & also maintains
high exhaust temperatures at low generator load level.

43. Starting System
• Like other internal combustion engines, a gas turbine
cannot produce torque at zero speed.
• The starting mean system is used to start the gas turbine
rolling, crank it to firing speed and assist the fired turbine
to self-sustaining speed.
• This is accomplished by an induction motor starting device
operating through a torque converter coupled to the
accessory gear.
• This arrangement provides the cranking torque for turbine
start-up. For shutdown, this continues to rotate the turbine
rotor at slow speed for cool down purposes.

44. Dual Fuel System
• This gas turbine has duel fuel capability. It supplied with
both a natural gas & a liquid fuel (distillate) system.
• While operating on gas fuel, if the gas fuel pressure should
drop below a pre-set value, the control system will
automatically transfer to liquid fuel operation.
• There is no automatic transfer from liquid to gas, that
transfer must be initiated by operator.
• Mechanical fuel handling & electrical control components
are incorporated in the design of capable of burning either
two fuel individually or both fuels simultaneously.

45. Gas Fuel
• The gas fuel system is designed to deliver gas fuel to the turbine
combustion chambers at the proper pressures & flow rates to meet all
of the starting, accelerating, loading requirements of gas turbine
operation. Major components are :
1. Pneumatic block valve VA27-1
2. Y-type strainer
3. Gas stop/speed ratio (VSR) & control (VGC) valve
4. Fuel gas low pressure alarm switch 63FG
5. Gas pressure gauges & vent valves
6. Gas fuel hydraulic trip relay VH5
7. Valve control servo-valves
8. Valve control LVDTs
9. Gas manifolds to Comb. chambers.
10. Fuel metering system

46. Liquid Fuel
• The liquid fuel system pumps and distributes fuel supplied from off-
base fuel forwarding system to the fourteen fuel nozzles of the
combustion system.
• The fuel system filters the fuel & divides the fuel flow into 14 equal
parts for distribution to the combustion chamber at the required
pressure & flow rates.
• Fuel pump bypass VC3 regulates the amount of fuel input to the
turbine combustion chamber by varying amount of bypassed fuel. If
valve closes, less fuel is circulated around the pump and more fuel
goes to the combustors & vice versa.
• The position of the bypass valve is a linear function of the Fuel Stroke
Reference (FSR) generated by the Speedtronic Mark V Control.

47. Major Components for Fuel System
1. In-line low pressure fuel filter FF1-1
2. Fuel oil stop valve VS1
3. Liquid fuel pump PF1
4. Fuel pump discharge relief valve VR4
5. Fuel bypass Valve VC3
6. Flow divider FD1
7. Selector valve assembly
8. Fuel line check valves
9. Fuel Nozzle assemblies
10. False Start drain valves VA17-1, -2 & -5

48. Control Devices associated to Fuel System
1. Fuel differential pressure switch 63LF-1
2. Liquid fuel servo valve 65FP
3. Fuel pump clutch solenoid 20CF
4. Permissive limit switches 33FL-1 & -2
5. Hydraulic trip relay VH4
6. LVDTs 96FP-1 & -2
7. Magnetic pickups 77FD-1,-2 & -2

49. Cooling & Sealing Air system
• The cooling & sealing air system provides the necessary air flow from
the compressor to the other parts of the gas turbine rotor & stator to
prevent excessive temperature buildup in these parts during normal
operation and sealing of the turbine bearings. Atmospheric air from
external centrifugal blowers is also used cool the turbine exhaust
frame.
• Cooling & sealing function provided by the system are :
1. Sealing of turbine bearings
2. Cooling the internal turbine parts subjected to high temperature
3. Cooling of the turbine outer shell & exhaust frame
4. Providing an operating air supply for air operated valves
5. Compressor pulsation protection

50. Atomizing Air System
• The atomizing air system provides high pressure air to
atomize the liquid fuel as it enters the combustors.
Atomization is necessary to ensure complete and proper
combustion. The ration of atomizing air to compresor
discharge pressure approx. 1.2 or greater.
Major components :
1. Main atomizing air compressor (driven by accessory
gear)
2. Starting atomizing air compressor
3. Atomizing air heat exchanger

51. Cooling Water System
• The cooling water system is a closed system designed to
accommodate the heat-dissipation requirements of the
turbine & generator lub. oil system, the atomizing air
precooler, the water cooled flame detector and turbine
support legs.
• On-based components includes lub. oil heat exchanger in
accessory base, turbine aft support legs, atomizing air heat
exchanger& heat exchanger of generator’s air cooling
system.
• The hot water of the cooling water system is then cooled
by off-base industrial type water cooling module.

52. Fire Protection System
• The carbon dioxide fire protection system extinguished
fires by reducing the oxygen content of the air in the
compartment from an atmospheric normal of 21% to less
than 15%, an insufficient concentration to support
combustion.
• To reduce the oxygen content, a quantity of carbon dioxide
equal or > than 34% of the compartment volume is
discharge into the compartment in one minute and
recognizing the reflash potential of combustibles exposed
to high temperature metal, it provides an extended
discharge to maintain an extinguishing concentration for a
prolong period to minimize likelihood of reflash condition.

53. Compressor Water Wash System
• Gas turbine can experience a loss of performance during operation as
result of deposits of contaminants on internal components. The
deposits of atmospheric contaminants on the compressor parts occur
with the ingestion of air. This contaminants can be removed by
washing with water-detergent solution followed by a water rinse.
• Major components for Compressor Water Wash System :
1. On- base Equipment
2. Off-base Equipment
• Two type of water wash procedures :
1. Off-line Compressor Wash
2. On-line compressor Wash

54. Gas Turbine Maintenance
• Classification Gas Turbine Maintenance ;
1. Standby Inspection
2. Running Inspection
3. Dis-assembly Inspection
Dis-assembly Inspection can be classified into :
1. Combustion Inspection
2. Hot Gas Path Inspection
3. Major Inspection