Sunday, April 9, 2023

1.8 GT Fuel Gas System-9HA Gas Turbine Combine Cycle Power Plant - Operation

 1.0 SYSTEM DESCRIPTION

    1.1 General

  • The main functions of the system are:
  • To regulate the flow of gas fuel to the gas turbine
  • To regulate the fuel fraction between the gas fuel line 
  • To measure the gas fuel mass flow rate for performance perspective
  • To isolate the turbine from the gas fie] supply in case of a safety event 
  • To securely evacuate all the remaining gas fuel in the turbine and the Heat Recovery steam
  • Generator to decrease the start-up time by skipping the purging phase

The gas fuel system is an assembly of valves, heat exchangers, piping and instrumentation where:

  • A safety isolation valve, located outside of main turbine hall separates the gas turbine from the gas fuel supply in case of a safety event,
  • A flow meter measures the mass flow rate of gas fuel to the turbine.
  • Four gas control valves, operating in choked condition, regulate the flow of gas fuel and the split
  • among the four premix circuits.

Page 2/9 of the P&ID 119T7367 shows the gas fuel flow meter with the Safety Shut-Off valve and the
safety vent valve. Page 3/9 shows the instrumentation at the inlet of the skid. Page 4/8 shows the
instrumentation and vent valve for the cavity upstream of the gas control valves. Pages 5/9, 6/9 and
7/9 show the gas control valves and manifold with the associated instrumentation. Page 8/9 shows the
temperature transmitters connected to the various thermocouples installed on the skid, as well as the
I DVP cabinet containing the digital positioners of gas control valves. Page 9/9 shows the purge credit
shut off air valves with the purge credit coriolis flow meter and the purge credit vent valve.





2.0 SYSTEN DEVICES FUNCTIONS

GE Code: Function
MG2-1: Coriolis mass flow meter measuring the gas fuel mass flow
96FM-1 Gas mass flow transmitter
VGI-1: Safely shuts off the gas fuel supply to the skid in case of safety trip
65VGI-1: Servo valve controlling the VGI-1 valve opening
VGV-1: Safely vents the cavity between the SSOV and the gas skid
VGS-1:Isolation valve cutting off the gas flow for shut down sequence
VGV-3:Vents the cavity between VGS and VGM
20VGM-10:Shuts off the gas fuel for shut down sequence
90VGM-10:Gas monitored valve (VGM-10) positioner
4VGM-10: TRIP relay for VGM-10 closing
VGV-4: Vents the cavity between VGM and gas control valves VGC
20VGC-1: Controls the gas fuel flow in PM1 circuit 
20VGC-2: Controls the gas fuel flow in PM2 circuit
20VGC-3: Controls the gas fuel flow in PM23circuit
20VGC-4: Controls the gas fuel flow in Quaternary circuit

3.0 SYSTEM COMPONENT DESCRIPTION
Before going into the gas fuel heating and conditioning system, the gas flows through the flow meter (MG2-1), used to validate the performance of the power plant, then it reaches the safety shut-off valve(VG1-I). This valve located outside of the main turbine hall is closed during a safety event to shut-off the gas supply to the turbine. In the meantime, the safety vent(VGV-I) opens to vent the gas between the safety shut-off valve and the gas fuel skid to prevent any potential hazard.

The gas stop valve(VGS-I) is the first isolation valve on the skid, installed within the gas turbine compartment. Upstream of it is installed pressure and temperature measurements. The gas modulation valve(VGM-I) is a pressure reduction valve used to decrease the pressure upstream of the gas control valves in order to increase their strokes within the allowable operating range of the hardware. The gas modulation valve controls its downstream pressure during acceleration of the turbine and remains fully opened in the loaded region.
Typically, VGC-I and 2 flow gas from light-off to 30% load while VGC-3 and 4 remain closed. The four gas control valves are opened above 3-% and  the gas fuel mass flow rate increase with load, while the repartition of gas between the lines is adapted based upon the load of the turbine and the control philosophy required by the combustion system.

4.0 SYSTEM OPERATION

4.1 General

The gas turbine software controls and monitors automatically all the devices of this system. 

4.2 Start-up

Initial state before start up is as follow:

· All the gas stop valves except VGI-1 and control valves are in closed position and vent valves in open position (except VGV-1).

· The vent valves are closed and VGS-1 is opened to pressurize the piping up to the upstream° VGM-1

During the startup sequence:

· The VGM-1 opens to bring gas fuel upstream of the gas control valves and controls i downstream pressure as an increasing function of gas turbine speed.

· At a typical 14% speed, the gas control valves (20VGC-1 and 20VGC-2) open and the gas turbine is ignited.

· After ignition, 20VGC-1 is closed while all the flow of gas fuel is transferred on 20VGC-2. flow of gas increases as the gas turbine accelerates.

· At a typical 60% speed, 20VGC-1 opens in addition to 20VGC-2.

· The gas turbine keeps accelerating up to Full Speed No Load and then reaches loaded operation.


4.3 NORMAL OPERATION

During normal operation:

· Starting from Full Speed No Load, the load increases with gas fuel through 20VGC-1 and 20VGC - 2..

· At a typical 20% load, 20VGC-3 and 20VGC-4 open to fuel the last two circuits, so the load can keep increasing.

· At a typical 30% load, the behavior of the gas turbine varies depending on the gas temperature.

· When the load decreases, the gas turbine follows the same load path in the reverse direction.


 

4.4 SHUTDOWN
During the shutdown sequence:

· When the gas turbine is at Full Speed No Load, the speed starts decreasing with gas flowing through 20VGC-1 and 20VGC-2. At a typical 60% speed, 20VGC-2 is fully closed so all the gas flows through 20VGC-1.

· The gas fuel flow and the speed keep decreasing until flameout, occurring at a typical 40% speed The gas fuel stop valves are closed and the vent valves are opened after flameout.


4.5  GAS LEAK TESTS

During the gas leak tests sequence when the gas turbine is shut down, the philosophy is to successively open and close the stop valves of the gas fuel line and monitor pressure decay or build-up in the cavities of known volume, allowing quantifying the leakage rate of the valves. For example, with gas pressurized at the beginning of the gas fuel line, the tightness class of VGS-1 is checked by closing VGS-1 and the two valves of the cavity downstream (20VGM-10 and VGV-3). Since the valve are closed, the pressure in the cavity increases due to the leakage through VGS-1. After a determined amount of time, the pressure in the cavity has to be below the maximum allowable limit so the tightness class of the valve is not compromised.

4.6 GAS TURBINE TRIP

In the event of a gas turbine trip:

· The two stop valves VGS-1 and VGM-1 are closed and the cavities of the module filled with gas fuel are vented to the atmosphere.

· If the trip is a safety trip, the VGI-1 is closed as well and the gas fuel from VGI-1 to the gas turbine is vented to the atmosphere.

4.7 LOAD REJECTION

When the circuit breakers open at load rejection:

· The gas turbine is brought back to its Full Speed No Load condition, with gas flowing through 20VGC-1 and 20VGC-2 and 20VGC-3 and 4 being closed.

Saturday, April 8, 2023

1.7.3 AIR INLET SYSTEM OPERATION - 9HA GAS TURBINE -COMBINE CYCLE POWER PLANT OPERATION

1. SYSTEM OPERATION

1.0 General

The gas turbine software controls automatically all the devices of this system.

1.2 Start-up

Initial state before start up is as follow:
· Air filter clean air path, inlet duct and inlet plenum clean, free of water, dust, and FOD
· Filter elements of each stage correctly installed to avoid any air by-pass
Housing and duct correctly assembled with gaskets to avoid air bypass
Access doors and hatches closed
· Filter Housing implosion doors closed
· Anti-icing/Bleed-Heating system operational, correctly installed to allow free expansion
· Electrical supply ON
· Sensors and transmitters functional
· Speedtronic operational

Start-up procedure:

  • All access doors should be fully closed
  • The by-pass doors should be closed.
  • Heating cables should be ON
  • Speedtronic should be operational and at initial state
  • Control panels should be powered on

The filter housing is a static system with no need of start-up instruction. As soon as the GT is ON, inlet air is going through the filtration system, what makes it operational. The filtration system start with the GT.


1.3 Normal Operation

Continuous measurement of inlet pressure drop which increases with fouling of filters. For each filtration stage, an alarm signal will be initiated when final pressure drop level recommended for filters replacement will be reached.

1.4 Shut-Down

No specific instruction is needed for filtration system normal shutdown. It occurs when the GT is turned OFF.

1.5 Manual Operation

  1. Before GT Start-Up

To be checked :

· Filter housing : airtightness of door seals, by-pass doors and between all modules

· Electrical equipment : lights and warnings

· Control of sensors : calibration of sensors and transmitters

· Filter assembly : correct assembly of coalescers, prefilters and final filters, no final filters by-pass

· General checks : no risk of foreign object damage

     2. During  Normal  Operation

The pressure drop increase due to filter fouling should be controlled. If the pressure drop is too high an alarm signal is initiated and the filters should be replaced.

Insect screen, AI coils system, BH manifold, by-pass doors and especially filter elements should be checked to detect any potential damage.

During normal operation, pressure transmitters and dew point transmitters calibration shall also checked.

1.6  FILL  UP  AND  DRAINAGE

The inlet system use only water with anti-freeze as heating fluid in the AI/Heater coils system. Fill up or drainage of coils will be part of the complete AI loop commissioning and maintenance operation.

A draining system of modules floors is provided. Water retention (if any) inside the filter hoes should be identified during filter inspection. Draining system shall be then improve to resolve the water retention issues.

1.7.4 SYSTEM TECHNICAL DATA/ALLOWABLE LIMITS

1.0 PRESSURE DROP

Differential pressure drop measurement is performed at the outlet of the filter housing by two pressure drop transmitters (96 TF-1/2). Global air inlet filter pressure drop value is indicated through a numerical signal to the GT control panel. In case of very high pressure drop:

An alarm is generated after a time delay of 2 sec when the pressure drop reaches 1500 pa.

A GT Fast Run back followed by a GT Shutdown if necessary is performed after a time delay of 2 Sec  at 2100Pa. At 2300Pa, the implosion doors will open as electromagnets will be unpowered.






Friday, October 18, 2019

1.7.2 System Components Description-9HA GT Inlet Air System

2.0 System Component Description


2.1 Filtration

Insect screen : made of steel/steel panels which have to be removed for winter season, avoid mosquitos to reach filtration stages ad to quickly clogged them.

Weather Hoods: Six hoods protect the filter housing intake. Each hood is made of a painted carbonn steel sub structure covered by cladding sheets. Lifting lugs and water draining gutter and pipes are fitted with each hood.

Coalescer Stage: Composed of an arrangement of support holding frames. AISI type 304L, fitted with water draining gutters and pipes. This frames support the 576 coalescer panels made of fiberglass fiber packaged in a plastic frame used for water droplet removal.

Pre Filter and High Efficiency Filter (HEF) Stage: Composed of a V shape support holding frame arrangement, made of AISI 304L. Each horizontal row of holding frames is inclined of 10 degree to evacuate water captured in the filter elements. Gutters and drain pipes enable water draining outside of the filter housing. Holding frame arrangement is designed to support 512 pocket type pre filters and 512 HEF cells. Pre filters are reverse installed against the front face of HEF cells and maintained by a stainless steel wires basket. Pre Filters efficiency class G4 (EN779) are made of synthetic fibers, a plastic header fitted with a gasket for sealing when installed against HEF. HEF efficiency class F9 are of made of fiber glass media, a plastic frame fitted with a gasket for sealing when installed in the support frame.


2.2 Closing Flap

Enable to close and to isolate the inlet air path from the cold ambient conditions during GT stop periods.

2.3 Anti Icing / Heater


Water/Air heat exchanger is used to prevent frost or ice forming on the filtration stages and other stiffeners, silencer baffles are located int he air path during icing events. Exchanger system is also used to heat ambient air, to follow the minimum air temperature(-29 degree Celsius) admissible at compressor intake (heater function).

2.4 Bleed Heating


Hot air extracted from the GT compressor when required by the bleed heating function (guarantee of NOx emission, protect IGV against icing) is dispatched in the filter housing by the bleed heating(IBH) manifold. The IBH manifold is composed stainless steel acoustical nozzlws through the filter housing air path.

2.5 Implosion Doors


Implosion door equipped with electro magnetsm limit swictches, heating gaskets open (2300 Pa) to prevent from inlet system implosion in case of high high pressure drop level reached during shutdown period.

2.6 Inlet Duct and Silencer


Inlet duct and silencer system is composed of one Elbow, one silencer section, one extraction joint and one support structure.
The elbow and the silencer duct structure are made of stiffened carbon steel sheets protected against corrosion by a painting system.
Noise reduction is achieved by an arrangement of parabllel baffles, Baffles are made of stainless steel type AISI 304L structure and perforated sheets which protect the acoustic cushions made of mineral wool and fiber glass fabric.
As additional acoustic treatment, inlet duct walls are externally insulated with mineral wool and cladding.


2.7 Inlet Plenum

Inlet plenum is composed of a casing structure in several parts; a cone, a support structure. Casing structure and cone are made of stiffened carbon steel protected against corrosion by a painting system.
The plenum is fitted with pressure, temperature and dew point measurement connections. A drain connection located in the plenum floor enables washing water evacuation.



Wednesday, October 16, 2019

1.7.1 Gas Turbine 9HA Air Inlet System


1.0   System Description

1.1    Main Function

The main function of the system are:
·         To remove water and dust particles from the atmosphere air sucked by the gas turbine compressor(air filter housing)
·         To covey filtered air towards the inlet plenum and to reduce gas turbine compressor noise(inlet duct and silencer).
·         To collect and distribute filtered air to the GT compressor intake.
 The inlet & exhaust system is an open loop where:
·         The air filter housing function is the removal of contaminants from the ambient air sucked by the FT compressor. Clean air is required by the combustion, the hot parts s cooling air system and to avoid corrosion, erosion and fouling of mechanical components such as compressor sand turbine blades.
·         Insects screen enables to catch big amount of insect which could clogged very quickly the pre filters stages, and so avoid frequent maintenance of pre filtration stages.
·         Inlet weather hoods and coalesce stage are used to remove water droplets. Dust Particles are removed by pre filter and high efficiency filtration cells.
·         A closing flab enables inlet system closing in case of long FT stop period to avoid very cold air circulation through compressor and Gas turbine.
·         Anti-icing protection of the inlet system components is ensured by a water/air heat exchanger. Exchanger also enables to guarantee the minimum ambient air temperature (-29 C) required at the compressor.
·         A bleeding heating manifold with acoustical nozzles dispatches air extracted from compressor in GT part load, to protect IGV stages from icing and to respect Nox level.
·         The mechanical security of the inlet system ducting and housing is insured by pressure drop monitoring which controls a GT Run Back in case of high pressure drop level reached and by implosion doors’ opening.
·         The air inlet duct system including the inlet silencer is used to convey atmospheric filtered air towards the inlet plenum. Inlet silencer enables to attenuate noise generated by the GT compressor.
·         The inlet plenum collects the atmospheric air and allow the inlet compressor feeding with a homogeneous distribution.

1.2    Components of Air intake System.


GE Code
Function
Weather Hoods
Protect filter housing against rain water from entering into the intake system.
Closing Flap
Close inlet system to avoid cold air circulation during GT stop period.
Water/Air Heat Exchanger
Operates as Anti icing system to protect filters against frost and as heater to guarantee min. required Temp. At compressor inlet.
AIBH manifold
Dispatch air extracted from GT compressor in the inlet system to cover the BH functions.
Pre filter and high efficiency stage
Remove dust particles from ambient air sucked by GT compressor.
Inlet silencer
Drive filtered ambient air towards the inlet plenum. Reduce noise coming from GT compressor.
Inlet plenum
Collect and distribute air to the GT compressor intake (IGV).

 



Monday, October 7, 2019

1.6.0 GT 9HA Bearings


General


The 9HA.01 gas turbine unit has two double tilting pad journal bearings which support the gas turbine rotor and two self-equalizing tilting pad thrust bearings to maintain the rotor-to-stator axial position. These bearings are incorporated in the inlet casing and exhaust frame which are supplied oil from the main lubricating oil system.

Lubrication

The main turbine bearings are pressure-lubricated with oil supplied, from the oil reservoir. Oil feed piping where practical, is run within the lube oil drain lines, or drain channels, as a protective measure. In the event of a supply line leak, oil will not be sprayed on nearby equipment, thus eliminating a potential safety hazard.
The oil flows through branch lines to an inlet in each bearing housing. When the oil enters the housing inlet, flows into an annulus around the bearing. From the annulus, the oil flows through machined holes or slots to the bearing rotor interface.

Lubricant Sealing

Oil on the surface of the turbine shaft is prevented from being spun along the shaft by oil seals in each of the bearing housings. These labyrinth seals are assembled at the extremities of the bearing assemblies where oil control is required. A smooth surface is machined on the shaft and the seals are assembled so that only a small clearance exists between the oil seals and the shaft. The oil seals are designed with tandem rows of teeth and an annular space between them. Pressurized sealing air is admitted into this space to prevent lubrication oil reservoir is vented to atmosphere after passing through an oil vapor extractor.

Load Coupling

A rigid, hollow coupling connects the forward compressor rotor shaft to the generator. A bolted flange connection forms the joint at each end of the coupling.





Sunday, September 22, 2019

1.5.0 Turbine Section (GE 9HA Details)


Turbine

5.1 Turbine Section

The turbine section is the area in which energy in the form of high temperature pressurized gas, produced by the compressor and combustion sections, is converted to mechanical energy. The 4th stage axial flow turbine consist of the rotor, casing, exhaust frame, exhaust diffuser, buckets, nozzles and shrouds.

5.2 Turbine Rotor


A) Structure
The turbine rotor assembly consists of the aft turbine shaft, the first-, second-, third-, and fourth-stage turbine wheel assemblies with spacers and turbine buckets.
Concentricity control is achieved with mating rabbets on the turbine wheels, wheel shaft, and spacers. The wheels, spacers and aft shaft are held together with 5 sets of bolts that pass through each of the wheels and mating up with bolting flanges on the shafts and spacers. Selective positioning of rotor members is performed to improve balance the assembly.
B) Wheel Shafts
The aft shaft of the turbine rotor includes the NO.2 bearing journal.
C) Wheel assemblies
Spacers between the first and second, the second and third and between the third and fourth-stage turbine wheels determine the axial position of the individual wheels. These spacers carry the flow path seals. Near flow path seals are attached to the spacers using circumferential dovetails and serve to protect the rotor surface from hot gas path temperatures. The 1-2 spacers forward and aft faces include radial slots for cooling air passages.
Turbine buckets are assembled in the wheels with fir-tree-shaped dovetails that fit into matching cut-outs in the turbine wheel rims. All three turbine stage buckets are precision investment-cast. The shank on these buckets effectively shields the wheel rims and bucket dovetails from the hot gas path temperatures while mechanically damping bucket vibrations. Stage three and four buckets are further aided in damping vibration with interlocking shrouds at the buckets tips. These shrouds increase the turbine efficiency by minimizing tip leakage. Radial teeth located on the bucket shrouds mate with stepped surfaces on the stator hardware create labyrinth seals against gas path leakage around the bucket tips.
The increase in size of the buckets from the first to the fourth stage is necessitated by the pressure reduction resulting from energy conversion in each stage, requiring an increased annulus area to accommodate the gas flow.
D) Cooling
The turbine rotor is cooled to maintain reasonable operating temperatures and, therefore, assure a longer turbine service life. Cooling is accomplished by means of a positive flow of cool air extracted from the compressor and discharged radially outward through a space between turbine wheel and the stator, into the main gas stream. This area is called wheelspace.
E) Wheel space
Each turbine wheel has a forward and aft wheelspace that needs to be purged to prevent the hot gas air path from permeating these cavities. By maintaining these cavities purged, the integrity of the turbine structure will be maintained.
The first-stage forward wheelspace is cooled by compressor discharge air. An inducer at the inner flowpath efficiently pre-swirls the extraction air, which is then passed through holes in the midshaft and 0-stage spacer. Inducer air then flows through the first-stage forward wheelspace and is routed through the first stage bucket, is discharged into the main gas stream aft of the first-stage nozzle.
All other wheelspaces are purges with 10th stage compressor extraction air (taken form the inner diameter flowpath at stage10), which flows through the rotor bore, up through passages in the turbine wheels, and into the turbine flow path.

5.3 Buckets

Air is introduced into each first-stage and second-stage bucket through a plenum at the base of the bucket dovetail. it flow through precision cast serpentine passages and is introduced into the flow path through a series of cooling holes on the airfoil surface, tip and trailing edge.
Unlike the first-stage buckets, the third-stage buckets are cooled with machined internal air passages that travel the entire length of the foil. This cooling air enters cavity in tip shroud before exiting into the main gas stream. Air is introduced, like the first and second-stage, with a plenum at the base of the bucket dovetail.
The holes in the first, second, and third stage buckets are spaced and sized to obtain optimum bucket cooling while minimizing the compressor extraction air.
The Fourth-stage buckets are not internally air cooled. The tips of these buckets, like third stage buckets, are enclosed with interlocking by tip shrouds that are designed to minimize tip leakage and dampen the mechanical vibration of these long arifoils.

5.4 Near Flow path seals

a. Near flow path seals are installed using dovetail mounting in the 1-2, 2-3, and 3-4 spacer. These replaceable seals provide protect the turbine rotor wheelspaces from hot gas path temperature. Sealing teeth on this part mate with honeycomb attached to the power nozzles to isolate turbine stages.

5.5 Structure

The casing area of the turbine section is composed of six major elements. These are the:
a.       Inner turbine shell
b.      Outer turbine shell
c.       Nozzles
d.      Diaphragms
e.      Shrouds
f.        Exhaust Frame
The Inner turbine shell makes up a portion of the gas path annulus and supports the power nozzle assemblies and shrouds. The inner turbine shell is encased and supported by the outer turbine shell. The outer turbine shell also provides a pressure barrier structural strength to the gas turbine. Cooling air extracted from the compressor flows to static hot gas path components though the outer turbine shell. The inner turbine shell is allowed to ‘float ‘slightly within outer turbine shell for improved performance from bucket tip clearance control. The inner and outer turbine shells are split horizontally to provide access for servicing internal components
The exhaust frame supports the rotor at the aft bearing, makes up the outer wall of the gas-path annulus, and supports the exhaust diffuser. It is split horizontally to facilitate servicing.
           
      Inner Turbine Shell

The inner turbine shell controls the axial and radial positions of the shrouds and nozzles. It determines turbine clearances and the relative positions of the nozzles to the turbine buckets. This positioning is critical to gas turbine performance.
The inner turbine shell is cooled during operation by air flowing from the 8th and 11th stage compressor extraction air. After cooling the inner turbine shell, 8th and 11th stage air is directed to the third and second-stage nozzles respectively for cooling.
The center-line of the inner turbine shell is aligned to the rotor center-line during assembly and is supported by ledges in the outer turbine shell.
   
       Outer Turbine Shell

The outer turbine shell is bolted to and aft end of the compressor discharge casing. It supports the inner turbine shell, provides structural strength to the gas turbine, makes up the outer pressure boundary, and provides a connection point for compressor extraction piping.

 Nozzles

In the turbine section there are four stages of stationary nozzles which direct the high-velocity flow of the expanded hot combustion gas against the turbine buckets causing the turbine rotor to rotate. Because of the high pressure drop across these nozzles, there are seals at both the inside and the outside diameters to prevent loss of system energy by leakages. Since these nozzles operate in the hot combustion gas flow, they are subjected to thermal stresses in addition to gas pressure loading.


       First-Stage Nozzle


    The first-nozzle receives the hot combustion gases from the combustion system via the transition pieces. The transition pieces are sealed to both the outer and inner sidewalls on the entrance side of the nozzle.
      The 9HA.01 gas turbine first-stage nozzle contains a forward and aft cavity in the vane and is cooled by a combination of film, impingement and convection techinques in both the vane and sidewall regions.
      The nozzle segments, each with a single airfoil, are supported at the inner diameter by a horizontally split retaining ring which is supported by the aft end of the compressor discharge casing. They are supported at the outer diameter by the first stage shroud.


    Second-Stage Nozzle


    Air exiting from the first stage buckets is again expanded and redirected against the second-stage turbine buckets by the second-stage nozzle. This nozzle is made of cast segments, each with two airfoil. The male hooks on the entrance and exit sides of the outer sidewall fit into female grooves on the aft side of the first-stage shrouds and on the forward side of the second-stage shrouds to maintain the nozzle concentric with the turbine shell and rotor. This close fitting tongue-and-groove fit between nozzle and shrouds acts as an outside diameter air seal. The second-stage nozzle is cooled with 11th stage extraction air.

        Third-Stage Nozzle


     The third-stage nozzle receives the hot gases as it leaves the second-stage buckets, increase its velocity by pressure drop, and directs this flow against the third-stage buckets. The nozzle consists of cast segments, each with one airfoil. It is held at the outer sidewall forward and aft sides in grooves in the turbine shrouds in a manner similar to that used on the second-stage nozzle. The third stage nozzle is cooled by 8th stage compressor extraction air.

       Fourth-Stage Nozzle


      The fourth-stage nozzle receives the hot gas as it leaves the third-stage buckets, increases its velocity by pressure drop, direct this flow against the fourth-stage buckets. The nozzle consists of cast segments, each with three airfoils. It is held at the outer sidewall forward and aft sides in grooves in the turbine shrouds in a manner similar to that used on the second-stage nozzle. The fourth-stage nozzle is uncooled.




    Diaphragm


Attached to the inside diameter of the second third, and fourth –stage nozzle segments are the nozzle diaphragms. These diaphragms deter air leakage past the inner sideall of the nozzles and the turbine rotor The high/low, labyrinth seal teeth are machined into the inside diameter of the diaphragm. They mate with opposing sealing lands on the turbine rotor. Minimal radial clearances between stationary parts (diaphragms and nozzles) and the moving rotor are essential for maintaining low inter-stage leakage, this result in higher turbine efficiency.

   Shrouds


Unlike the compressor blading, the turbine buckets tips do not run directly against an integral machined surface of the casing but against thin walled segments mounted female grooves located in the turbine shell. The shrouds primary function is to provide a cylindrical surface to minimize bucket tip clearance leakage.
The turbine shrouds’ secondary function is to provide a high thermal resistance between the hot gases and the comparatively cool turbine casing. By accomplishing this function, the turbine casing cooling load is drastically reduced, the turbine casing diameter is controlled, the turbine casing roundness is maintained, and important turbine clearances are assured.
The first stage stationary shroud segments are in low pieces. The gas-side inner shrouds is separated from the supporting outer shroud to allow for expansion and contraction and thereby improve low-cycle fatigue life. The inner shroud is cooled b impingement, film, and convection.
He shroud segment are maintained in the circumferential position by radial pins from the inner turbine shell. Joints between shroud segments are sealed by fixable metal seals.

  Exhaust Frame


Gases exhausted from the fourth turbine stage enter the diffuser where velocity is reduced by diffusion and pressure is recovered. The exhaust frame is bolted to the aft end of the turbine casing. Structurally, the frame consists of an outer cylinder and an inner cylinder interconnected by the radial struts. The No. 2 bearing is supported from the inner cylinder.
Exhaust frame radial struts cross the exhaust gas stream. These Struts position the inner cylinder and No. 2 bearing in relation to the outer casing of the gas turbine. The struts must be maintained at a constant temperature in order to control the center position of the rotor in relation to the stator. This temperature stabilization is accomplished by protecting the struts from exhaust gas with an airfoil shaped metal firing that forms an air space around each strut. Off-base blowers provide cooling air flow through the No. 2 bearing tunnel and then to the fourth-stage aft wheelspace and air space of the struts.
Removable trunnions on the sides of the exhaust frame are used with similar trunnions on the inlet casing to lift the gas turbine when it is separated from its base.
The exhaust diffuser located at the aft end of the turbine is bolted to the exhaust frame. At the exit of the diffuser, the gases are directed into the exhaust plenum.

 .

Wednesday, April 24, 2019

1.4.0 DLN-2.6 + Combustion System

4.0 DLN-2.6 + Combustion System

The combustion system is a reverse-flow design with 16 combustion chambers arranged around the periphery of the compressor discharge casing. Combustion chambers are numbered counter-clockwise starting with the chamber just left of the chamber at top dead center when looking aft end. This system also includes the fuel nozzles, a spark plug ignition system, flame detectors, and crossfire tubes.
High pressure air from the compressor discharge is directed around the aft end of the transition piece. Most of the compressor discharge air enters the holes in the aft end of the transition piece to cool the transition piece and for annulus between the flow sleeve and liner, through holes in the aft end of the flow sleeve. This air passes through the quaternary fuel ring and then enters the combustion zone through the cap assembly for proper fuel combustion. Fuel is supplied to each combustion chamber through six nozzles designed to disperse and mix the fuel with the proper amount of combustion air (and to the quaternary ring at during baseload operation). Hot gases, generated from burning fuel in the combustion chambers, flow through the impingement cooled flow sleeve and transition piece to the turbine.

4.1 Combustor Configurations for Fuel Type:


Dual Fuel
This configuration is capable of operation on either natural gas or liquid fuel. The fuel type can be changed gas to liquid to gas while the GT is operating.
Gas Fuel Only
The fuel nozzles feed only natural gas to the combustion system, with no provision for liquid fuel operation.
Liquid fuel only
The fuel nozzles feed only liquid fuel and water into the combustion system, with no provision for gas fuel.
·         On gas fuel, the combustor operates on 6 fuel nozzles per combustor, where the number of fuel nozzles fueled increases as the GT load increases. One nozzle is fueled from FSNL to low load; three nozzles are fueled from low load to intermediate load; and six nozzles are fueled plus the quaternary fuel circuit from intermediate load to baseload. Emissions complaint operation required all fuel circuit to be fueled and GT firing temperature to be above a threshold temperature.
·         On oil operation, this combustor operated in diffusion amide across the entire load range, with only the outer 5 fuel nozzles fueled. Water injection is also injected by the fuel nozzles into the combustor for NOx reduction.

4.3 Outer Combustion chambers and Flow Sleeves

The outer combustion chamber, or casing, acts as the pressure vessel for the combustor. They also provide flanges for the fuel nozzle-end cover assemblies, crossfire tube flanges, spark plugs, flame detectors and false start drains. The flow sleeve forms an annular space around the cap and transition piece assemblies that directs the combustion and cooling into the forward end of the combustor fuel nozzle jet.


4.4 Cap, Flow Sleeve, and Transition Piece Assemblies

The combustion flow sleeves and transition pieces are passively cooled on their outside with air directed by the impingement sleeve to the forward end of the combustor and fuel nozzle inlet. Ridges on the liner outer surface augment the cooling effectiveness. The inner surfaces of the transition piece and flow sleeve have thermal barrier coating to reduce metal temperatures and thermal gradients. The aft end of the transition piece transforms the combustor annular flow into  flow profile to be fed into the Stage 1 Turbine Nozzle. The Cap has six burner tubes that engages each of the six fuel nozzles. The cap is cooled by effusion cooling passages.

4.5 Fuel Nozzle End Covers

There are six fuel nozzles assemblies in each combustor. They arranged with 1 located in the center and five arranged around the outer edge. Each fuel nozzle premixes the inlet air and gas fuel, and then forwards this mixture to the combustor reaction zone for burning. The outer fuel nozzles contain a liquid fuel and water passage down the center of the fuel nozzle for operation on oil, where oil and water is injected directly into the combustor. Water is injected into the reaction zone when the combustor is to be operated within emissions compliance on oil fuel.

4.6 Quaternary Fuel Ring

Each combustion chamber contain a Quaternary fuel ring located between the combustion casing and the CDC. Fuel is instructed at intermediate load and above.

4.7 Crossfire Tubes

All combustion chambers are interconnected by crossfire tubes to provide means for ignition of the chambers without ignitors. The outer chambers are connected with an outer crossfire tube and the combustion liners are connected by the inner crossfire tubes.

4.8 Spark Plugs

The combustor is ignited with two spark plugs that are positioned within the combustor downstream of a fuel nozzle. Once the combustor is ignited, the pressure from the combustor forces the ignitor tip to retract from the combustor for continous operation. These spark plugs receive their energy from high energy-capacitor discharge power supplies. Once the combustor chamber is ignited with the spark plug, the remaining chambers are ignited by the flame passing through the crossfire tubes that interconnect the reaction zone of the remaining chambers.

4.3 Flame Detectors

A flame monitoring system is used consisting of 4 flame detectors. The signals from the flame detectors are sent to the control system which uses an internal logic system to confirm whether the combustors are ignited or extinguished.