Gas Turbine:: A Gas Turbine Also Called A Combustion Turbine, Is A Type of Continuous and

Gas turbine:
A gas turbine is a combustion engine at heart of a power plant that

can convert natural gas or other liquid fuels to mechanical energy. This energy
then drives a generator that produces the electrical energy that moves along
power lines to homes and business.
A gas turbine also called a combustion turbine, is a type of continuous and
internal combustion engine. The main elements common to all gas turbine
engines are an upstream rotating gas compressor a combustor a downstream
turbine on the same shaft as the compressor.
 A gas line of dia 8 inch which a gas is passing in these lines and carried to a
gas filter which a gas is filtrated and dust particles in a gas and corrosion
particles is stuck in a gas filter.
 A filtrated gas is passed through in these lines.
 A motor is attached to a compressor.

Powerplant support:
The turbine engine is cantilevered aft from the forward flange of the air inlet
housing, which is bolted to the reduction gear unit. Additional rear support is
provided by a steel pedestal, attached to the combustor housing aft flange.
The pedestal base rests on a vibration isolated pad, located on the package
base below the combustor housing, and provided for axial thermal growth.
The vibration pad is provided with load springs, adjustment bolts and spacers,
and in addition to serving as a resilient rear mount, also permit vertical and
horizontals adjustments of the engine for purpose of alignment.
Technical Data:
Data application to 100 percent engine speed and rated full load sea level
150°C with zero inlet, exhaust bearing and generator losses. All values given
are nominal, burning natural gas fuel unless otherwise specified.
Identity : Solar type Centaur
Engine speed : 14950RPM
Air compressor : 11 stage-axial flow
Compressor ratio : 1: 10.2
Combustion chamber : single, annular with 12 fuel injectors
Engine assembly : 3 stages-axial flow
Bearing (sleeve) : 3 tild-paid radial, 1 fixed thrust
Fuel : Natural gas
Output power : 4136 KW (gas)
 Compressor:
Gas turbine are comprised of three primary section
mounted on the same shaft are.
 Compressor
 Combustion chamber
 turbine
The compressor can be either axial flow or centrifugal flow. Axial flow compressor
is more common in power generation because they have higher flow rates and
efficiencies. Axial flow compressors are comprised of multiple stages of rotating
and stationary blades through which air is drawn in parallel to the axis of rotation
and incrementally compressed as it passes through each stage. The acceleration
of the air through the rotating blades and diffusion by the stators increase the
pressure and reduce the volume of the air. Although no heat is added, the
compression of the air also causes the temperature to increase. The compressor
must be smoothly accelerated and reach firing speed before fuel can be
introduced and ignition can occur.
Behind the compressor the motor is working with a power of
400KW & Speed 2900 rpm. And compressor is attached to oil tank. The
function of oil tank is to separate oil and gas. And this gas is passed to a gas
cooler to cool gas and then passed to a collective filter because some moisture
of oil in a gas is collected in a collective filter.
In this process an Actuator meter valve is used this pipe line because valve
actuator is the mechanism for opening and closing a valve. Manually operated
valve require someone in attendance to adjust them using a direct or geared
mechanism attached to the valve stem.
 Combustion Chamber:
Air leaving the compressor must first be slowed down and then
split into two streams. The smaller stream is fed centrally into a region where
atomized fuel is injected and burned with a flame held in place by a turbulence-
generating obstruction. The larger, cooler stream is then fed into the chamber
through holes along a “combustion liner” (a sort of shell) to reduce the overall
temperature to a level suitable for the turbine inlet. Combustion can be carried
out in a series of nearly cylindrical elements spaced around the circumference of
the engine called cans, or in a single annular passage with fuel-injection nozzles at
various circumferential positions. The difficulty of achieving nearly uniform exit-
temperature distributions in a short aircraft combustion chamber can
be alleviated in stationary applications by longer chambers with partial internal
reversed flow.
 In a gas-turbine engine driving an electric generator, the speed must be

kept constant regardless of the electrical load. A decrease in load from the
design maximum can be matched by burning less fuel while keeping the
engine speed constant. Fuel flow reduction will lower the exit temperature
of the combustion chamber and, with it, the enthalpy drop available to the
turbine. Although this reduces the turbine efficiency slightly, it does not
affect the compressor, which still handles the same amount of air. The
foregoing method of control is substantially different from that of a steam
turbine, where the mass flow rate has to be changed to match varying
loads.
 An aircraft gas-turbine engine is more difficult to control. The required

thrust, and with-it engine speed, may have to be changed as altitude and
aircraft speed are altered. Higher altitudes lead to lower air-inlet
temperatures and pressures and reduce the mass flow rate through the
engine. Aircraft now use complex computer-driven controls to adjust
engine speed and fuel flow while all critical conditions are monitored
continuously.
 Gear Box:
The reduction gear unit is bolted to the engine air inlet housing and
installed on a raised mounted surface over the oil tank on the base. The
unit is of a high speed, two stages, star compound epicyclic design,
available at “outside speed of 1500 rpm.”
The unit utilize single helical, hardened and ground gearing capable of
sustaining momentary overload of up to approximately eight times normal
operated rated torque.
The hydrodynamic thrust bearing on the sun shaft and sleeve bearing on
the countershaft are pressure fed and oil. Additional oil jet cool and
lubricate the accessory pinion gear mesh, the output ball bearing, and the
one way of clutch of a starter shaft. All other accessory gear meshes and
bearings are lubricated by air-oil mist generated in the housing by the high
speed meshes.
Lubricating oil for a bearing and gear train is supplied from the turbine
engine lube oil system. Bearing oil seals are pressurized with seal air from
the engine air system.
Technical Data:
Manufacturer : SOLAR TURBINE
Type : High speed, two-stages star-
compound,
Rated output speed : 1500rpm
Overall efficiency with Ancillaries and bearings : 98.00%
Function of Gear box:

A suitable gearbox, such as a reduction gearbox, links
the output of the gas turbine engine to the input of the propeller or motor.
More, particularly, the reduction gearbox will “lower the speed” of the output
of the gas turbine engine provided to the propeller or rotor. The accessory
drive is a gearbox that forms part of a gas turbine engine. Although not part of
the engine's core, it drives the accessories, fuel pumps, etc., that are otherwise
essential for the operation of the engine or the aircraft on which it is mounted.
Accessory drives on large engines handle between 400–500 hp.
 Generator:
Brushless Three-phase medium voltage salient pole Synchronous generator
Manufacturer : ABB
Type : AMG 710MM4
Mounting : B3
Protection : IP 21
Cooling : IC 01
Weight : Kg 11800
Rating:
Output at 40°C : 5600 KVA
Power factor : 0.80
Voltage/Frequency : 6300 V
Frequency : 50 Hz
Current : 513 A
Overspeed : 1800 R/min
Insulation : class F
Temp Rise : class F
Standard : IEC 34
Speed : 1500 R/min
Efficiency : Valid at rated voltage and frequency
Load in % 110 100 75 50 25
Power factor 0.80 96.95 96.98 96.90 96.37
Power factor 1.00 97.78 97.79 97.70 95.44
Construction: The stator frame, end shield and main terminal boxes are steel
made.
The generator is provided with two pressure lubricated sleeve bearing and
cylindrical shaft extension. The stator core plate is a high grade, low loss silicon
steel with organic insulation. The pole wheel consists of punched and stacked
plates. The rotor is provided with a complete damper winding. All windings are
vacuum impregnated and provided with very strong bracing which withstand
all expected mechanical and electrical shocks and vibrations.
Direction of rotations: CCW seen from A-end
Turbine Start:
The indication “ready to start” must be present. When the “START” command
is given the program continuous as follows:
Prevent illation (30 sec) Turbine room ventilation indication “Start

Sequence
Power connect (5 min) Turbo-generator set equipment power

supply
Analog input check, Digital input check
Prelubrication(5 min) pre oil pump on

Pre-lube oil pressure check (delayed 30 sec)
Start (30 sec) Starting motor on

Hydraulic oil pressure check
Hydraulic actuator control on
Hydraulic oil pressure increase up to 400 bar
Turbine speed check ( 15 %)
Valves control (25 sec) Exhaust gas ducting purge,

Gas valve control
Gas pressure check
Ending Purge (5 min) End of exhaust ducting purge
Ignition(15 sec) Ignition (sequence on gas fuel)

Primary and torch valve open,
Temperature regulator on,
ignition torch on,
Ignition gas pressure check,
Ignition Temperature check(T5≥176°C)
1st acceleration (max .2 min) Acceleration to 90% speed,

start counter increment,
Hour counter activated
2nd acceleration (15 sec) acceleration to 90 % speed

Start counter increment
Hour counter activated
Pre-lab pump off
Hydraulic starting actuator off
Generator excitation on
Compressor excitation valve on
90% speed check
3rd acceleration (10 sec) regulation nominal speed
T5 turbine temperature offset
Temperature regulator off
Speed governor on
Starting motor off
Generator min. voltage check activated
100 % speed check
Indication “READY TO LOAD” on
Ready to load connection of the undervoltage relay

Indication “START SEQUENCE” OFF
Connection of the oil cooler fans

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Gas turbine:

A gas turbine is a combustion engine at heart of a power plant that

 In a gas-turbine engine driving an electric generator, the speed must be

 An aircraft gas-turbine engine is more difficult to control. The required

Function of Gear box:

Power factor 1.00 97.78 97.79 97.70 95.44

Prevent illation (30 sec) Turbine room ventilation indication “Start

Power connect (5 min) Turbo-generator set equipment power

Prelubrication(5 min) pre oil pump on

Start (30 sec) Starting motor on

Valves control (25 sec) Exhaust gas ducting purge,

Ending Purge (5 min) End of exhaust ducting purge

Ignition(15 sec) Ignition (sequence on gas fuel)

1st acceleration (max .2 min) Acceleration to 90% speed,

2nd acceleration (15 sec) acceleration to 90 % speed

Ready to load connection of the undervoltage relay

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