General Electric LM6000PC

SCOPE OF SUPPLY

For a detailed description of the basic and optional scope of supply please refer to the accompanying Product Specification manual.

BASIC SCOPE OF SUPPLY

THE FOLLOWING EQUIPMENT AND SERVICES ARE INCLUDED IN THE BASIC SCOPE OF SUPPLY:

- LM6000PC gas turbine engine equipped with bellmouth and screen.

- Natural gas fuel, water injected combustion system, complete and self –contained on the unit, with connection on the baseplate for customers filtered, regulated fuel supply at 675 psig +/- 20 psig.

- Generator, 13,800 Volt, 60 Hz, 3600RPM, 71.176 MVA @ 0.85 pf, 59 Deg F cooling air. Low maintenance brushless excitation system suitable for Class I, Group D, Div 2 areas. Neutral and line cubicles with CTs, surge protectors and lightning arrestors.

- I-beam baseplates for turbine, generator and unit mounted accessories.

- Acoustic enclosure for gas turbine, generator and unit mounted accessories.

- Multi stage air inlet filtration system for both gas turbine and generator, including weather hoods, inlet screen, pre-filter, final barrier filter, intake silencer, and standard ducting to plenum chamber. Filter house ladders and platforms are included.

- Electro-hydraulic starting system

- Separate oil systems for gas turbine and generator, including duplex filters, shell and tube coolers, stainless steel piping and stainless steel reservoirs.

- Axial-exhaust system with discharge flange for customer connection.

- Unit control panel for indoor mounting in a controlled environment, including microprocessor fuel management and sequencing system, generator metering.

- Bently Nevada vibration monitoring, CRT annunciation of alarms and shutdowns,

- RS232, LAN or Modbus ports for data output to customers control systems.

- I/O cubicle mounted on gas turbine enclosure.

- 24VDC Control system. Battery with dual battery chargers.

- Fire and gas detection and extinguishing system, serving both turbine and generator compartments, complete with 24VDC battery and charger.

- “On-line” water wash system and “soak wash” system

- Generator factory testing to IEEE or IEC standards. Gas turbine performance test by GE.; full load string test and performance verification of turbine.

- Six sets of drawings and data packages, O&M manuals.

- Training course for up to 10 customer personnel.

1.2 Equipment and Services by Seller

1.2.1 Transport to the job site (all logistics)

1.2.2 Complete Engineering, Procurement and Construction Services (the EPC)

1.2.3 Simple cycle exhaust stack with EPA ports, platforms and ladders

1.2.4 35’ X 14’ Modular Control Room

1.2.5 Inlet air chilling module

1.2.6 Fired, fuel gas, heating module

1.2.7 Unit 480 V Motor Control Center

1.2.8 NEMA 3R 15 kV Switchgear

1.2.9 Dual Fuel Option (transfer fuels at reduced load, non-cooled CDP)

1.2.10 O&M Manuals on CD ROM

1.2.11 Low ambient temperature anti-icing system

1.2.12 Generator inlet air cooling system

1.3 Equipment and Services by Purchaser

The Purchaser will provide the following equipment, materials, and services unless otherwise noted:

1.3.1 Unloading, indoor and outdoor storage (as required) and installation labor.

1.3.2 Foundations, anchor bolt hardware, grouting forms, and grouting.

1.3.3 Fuel and water forwarding systems including piping to flange connections at Vendor's baseplate.

1.3.4 Lubricants and fluids (Operating and Commissioning)

1.3.5 High voltage cables and/or bus duct from the generator terminals.

1.3.6 Electric utility interconnect including the required circuit breakers and protective devices.

1.3.7 Interconnection piping, conduit, and wiring between the unit control panel, main unit termination boxes, auxiliary system modules, and motor control center.

1.3.8 Bolts, nuts, washers, and gaskets required at terminal points.

2.0 REFERENCED DOCUMENTS

The applicable sections of the following US and ISO Codes and Standards will be considered as relevant Standards for gas turbine equipment. The designs and procedures will be compliant with applicable sections of the following:

AGMA 421 Standard Practice for High Speed Helical and Herringbone Gear Units (Used for the accessory gear except for service factor.)

ANSI/AFBMA

Std 9 Loading Ratings and Fatigue Life for Ball Bearings.

Std 11 Load Ratings and Fatigue Life for Roller Bearings.

ASCE-7 Minimum Design Loads for Buildings and Other Structures

(Used for Snow Loads)

ANSI B1.1 Unified Inch Screw Threads (S&S Energy Products complies at the customer's connection)

ANSI B1.20.1 Pipe Threads

ANSI B16.5 Steel Pipe Flanges and Flanged Fittings

ANSI B16.9 Factory - Made Wrought Steel Butt Welding Fittings

ANSI B16.21 Non-metallic Flat Gaskets for Pipe Flanges. (Spiral-wound gaskets per API 601 may be used, particularly in turbine compartment piping.)

ANSI B31.1 Pressure Piping and gas turbine piping systems comply.

ANSI B133.2 Basic Gas Turbine. Complies, with the exception of paragraph:

8.5 Loose items such as jackscrews and eyebolts are not furnished. Provisions for use of such items are not included in the design.

ANSI B133.3 Gas Turbine Auxiliary Equipment. Auxiliary equipment will fully comply with design portions only. The Seller’s recommended lube oil flushing procedure will be implemented. Atomizing air receiver is not applicable.

ANSI B133.4 Gas Turbine Controls and Protection Systems

ANSI B133.5 Gas Turbine Electrical Equipment

ANSI B133.8 Gas Turbine Installation Sound Emissions

ANSI C37.90 Relays Associated with Electric Power Apparatus

ANSI C37.90.1 Guide for Surge Withstand Capability (SWS) Tests

ANSI C50.10 General Requirements for Synchronous Machines

ANSI C50.13 Requirements for Cylindrical Rotor Synchronous Generators

ANSI C50.14 Requirements for Combustion Gas Turbine Driven Cylindrical Rotor Synchronous Generators (The GTG does not provide a peak reserve rating. Not all of the prototype tests indicated in Table 2 have necessarily been conducted.)

ANSI C57.94 American Standard, Guide for Installation and Maintenance of Dry Type Transformers

ANSI C83.16 Relays

ANSI S1.2 Method for the Physical Measurement of Sound

ANSI S1.4 Specification for Sound Level Meters

ANSI S1.13 Method for the Measurement of Sound Pressure Levels

ANSI/ASHRAE 52.1-1992 Gravimetric and Dust Spot Procedures for Testing Air-cleaning Devices Used in General Ventilation for Removing Particulate Matter

ANSI/IEEE C37.2 Electrical Power System Device Function Numbers (The Unit complies with respect to device designations except that in a few cases device numbers had to be modified or added for this application.)

ANSI/IEEE 100 IEEE Standard Dictionary of Electrical and Electronics Terms

ANSI/NEMA MG1 Motors and Generators

ANSI/NEMA MG2 Safety Standard for Construction and Guide for Selection, Installation and Use of Electric Motor and Generators

ANSI/NFPA 12 Carbon Dioxide Extinguishing Systems

ANSI/NFPA 70 National Electrical Code (Electrical components will be designed to meet the intent of this Code for Class 1, Group D, Div. 2, Hazardous area classification where appropriate.).

API 614 Lubrication, Shaft-Sealing, and Control - Oil Systems for Special - Purpose Applications

API 616 Gas Turbine for Refinery Services

API 650 Storage Tanks

API 670 Vibration Monitoring Systems

API 678 Accelerometer - Based Vibration Monitoring System

API RP11PGT Packaged Combustion Gas Turbines

ASME PTC22 Gas Turbine Power Plants - Performance Test Codes

ASME Section VIII ASME Boiler and Pressure Vessel Code

ASME Section IX ASME Boiler and Pressure Vessel Code

AWS D1.1 American Welding Specification

EIA RS-232 Interface between Data Terminal Equipment and Data Communication Equipment Employing Serial Binary Interchange

IEC 34.1 Rotating Electrical Machines - Rating and Performance

IEC 34.3 Rotating Electrical Machines - Turbine Type Synchronous Machines

IEEE Std. 421 IEEE Standard Criteria and Definitions for Excitation Systems for Synchronous Machines

JIC Hydraulic Standards for Industrial Equipment

UBC Uniform Building Code (Used for wind loads and seismic design)

3.0 TECHNICAL REQUIREMENTS

3.1 Operation

The Unit shall be capable of satisfactory operation from 0% load to 100% load at the Site Design Conditions. During startup, the turbine shall be capable of idling unsynchronized for up to 60 minutes. The UNIT shall be capable of starting, synchronizing and loading within 10 minutes of dispatch from a ready to start condition.

3.2 Performance Data and Guarantees

The Seller guarantees the kW output, heat rate, NOx, CO, PM10 and UHC emissions, and noise emissions of the Unit according to the Contract.

Seller shall provide additional performance data to show how changes in ambient temperature and inlet/exhaust losses affect heat rate, power output, exhaust mass flow, and exhaust gas temperature.

3.3 Site Design Conditions

3.3.1 Climatic Conditions

The Unit and related equipment furnished by the Seller shall be designed for proper operation with the following climatic conditions:

- Maximum wind velocity of 100 mph

- Ambient temperature range of 44 to +105°F*

- Relative humidity of 15% to 100%

*Lower-operating temperatures can be realized with the addition of an anti-ice system

3.3.2 Seismic Conditions

The gas turbine structure and attachments shall be designed in accordance with UBC 1997, Seismic Zone 4.

3.4 Surface Temperatures

Surface temperature of components that can be readily accessed during normal operation shall not exceed 140°F without a barrier to protect personnel. The engine compartment interior and roof are excluded from this requirement.

4.0 LM6000PC Uprated GAS TURBINE GENERATOR SET

4.1 Gas Turbine

Major Components of the LM6000 turbine are:

- 5-stage low pressure compressor (LPC)

- 14-stage variable geometry high pressure compressor (HPC)

- Annular combustor

- 2-stage air cooled high pressure turbine (HPT)

- 5-stage low pressure turbine (LPT)

- Accessory Drive Gear Box

The LPC will be driven through a concentric drive shaft by the 5-stage LPT, forming the low-pressure rotor. The high-pressure rotor will be formed by the 14-stage HPC, driven by the 2-stage HPT. The high pressure "core" will be formed by the HPC, combustor and HPT section.

The Unit uses the Low-Pressure Turbine (LPT) powers the output shaft. Driving with the LPT improves fuel efficiency and allows the turbine to be directly coupled to the electrical generator rotating at 3600 RPM. The gas turbine drives the generator through a flexible dry type coupling connected to the front, or "cold", end of the LPC shaft.

4.2 Turbine Cycle

The gas turbine cycle begins with air entering the inlet plenum, where it is directed through inlet guide vanes into the LPC. The LPC compresses the air by a ratio of approximately 2.4:1. Air leaving the LPC is directed into the HPC. Variable bleed valves (VBV) in the flow passage between the two compressors regulate the airflow entering the HPC during idle, low power operation, and transient load conditions. To further control the airflow, the HPC will be also equipped with variable pitch inlet guide vanes and stator vanes.

The HPC compresses the air by a ratio of approximately 12:1. The HPC discharge will then be directed into the annular combustor section where it mixes with the fuel from the 30 fuel nozzles. One igniter initially ignites the fuel/air mixture. When combustion is self-sustaining, the igniter will then be turned off. The hot combustion gases will then be directed into the HPT, which consequently drives the HPC. The gas then expands further through the LPT, which drives the LPC. The flanged LPC shaft drives the electric generator.

4.3 Inlet Section

The air intake section of the gas turbine consists of an annular flow section to direct the air stream into the low-pressure compressor.

4.4 Low Pressure Compressor

The low-pressure compressor (LPC) will be a 5-stage axial flow compressor with 2.4:1 pressure ratio. At low power settings and during large power reduction transients modulating bleed ports control LPC bypass flow to assure adequate LPC stall margins.

4.5 High Pressure Compressor

The high-pressure compressor (HPC) will be a 14-stage design. Variable stators in stages 1 through 5 provide stall-free operation and high efficiency throughout the starting and operating range. The stator geometry of stages 6-14 will be fixed.

The HP compressor casing will be split horizontally to allow ready access to the stator vanes and rotor blades for inspection or replacement.

4.6 Combustion System

The gas generator will be furnished with 30 externally mounted fuel nozzles for the natural gas fuel system requirements. For NOx reduction, water will also be injected into the fuel nozzles through a separate manifold.

The Unit uses a high performance annular combustor with low exit temperature pattern, low-pressure loss and high combustion efficiency at all operating conditions.

4.7 High Pressure Turbine

The high-pressure turbine (HPT) will be an air cooled, 2-stage design with demonstrated high efficiency.

The HPT will be designed to be easily maintainable in service. Significant maintainability features include:

- Stage 1 nozzle assembly will be removable as a unit.

- Stage 2 nozzle assembly will be removable as a unit.

- Turbine blades will be individually replaceable.

- Stage 1 and 2 shrouds will be segmented and designed for removal and replacement in the stator assembly.

The 2-stage high-pressure turbine will be assembled on the same shaft as the 14-stage high-pressure compressor.

Compressor discharge air will be used to cool the rotor structure and both blade stages. The cooling air flows through the shaft and the bore of the stage 1 disk, where it separates to supply stage 1 and 2 blades. Compressor discharge air and bleed air will be used to cool the HPT stator.

4.8 Low Pressure Turbine

A 5-stage low-pressure turbine receives the outlet flow from the HP turbine. The LP turbine will be mounted on a common shaft with the 5-stage LP compressor. This shaft will be concentric to the HP rotor.

4.9 Gas Turbine Support Structures

Three frames provide support for the LP and HP rotors.

- Front Frame

The front frame will be a major engine structure that provides support for the LPC rotor and the forward end of the HPC rotor. The frame also forms an airflow path between the outlet of the LPC and the inlet of the HPC. Engine front mount provisions will be made off the front frame.

The front frame contains the engine "A" sump that includes a thrust and a radial bearing for support of the LPC rotor and a radial bearing which supports the forward end of the HPC rotor. Lubrication oil, supply and scavenge, lines for the "A" sump will be routed inside the frame struts. The engine inlet gearbox will be located in the "A" sump, with the radial drive shaft extending out through the strut located at the six o'clock position.

- Compressor Rear Frame

The compressor rear frame consists of an outer case, 10 struts and the "B-C" sump housing. The outer case supports the combustor and 30 fuel nozzles. The hub provides support for both a thrust bearing and a radial bearing to support the mid section of the HP rotor system.

- Turbine Rear Frame

The turbine rear frame provides the aft connection of the gas turbine to the base through the rear engine mounts and is the structure supporting the "D-E" sump, and the LPT stator case.

4.10 Accessory Drive System

The hydraulic starter, lube and scavenge pump, variable geometry hydraulic pump, and other accessories will be mounted and driven from the accessory gearbox. The accessory gearbox, located below the front HPC casing at the six o'clock position on the air collector, will be driven from the transfer gearbox through a short horizontal shaft. The transfer gearbox will be driven by the high-pressure rotor system.

4.11 Variable Geometry (VG) Control System

The variable geometry system consists of a positive displacement hydraulic pump, with torque motor positioned hydraulic servos for porting fluid at regulated pressure, two HPC variable stator vane actuators and six LPC bleed valve actuators. Electrical inputs from the SSEP controls operate three separate servo valves mounted on the gas turbine. The variable output pressures from these servos position the low-pressure compressor variables bleed valves (VBV) and the high-pressure compressor variable stator vanes (VSV). Position feedback of the moving elements will be provided by linear variable differential transformers (LVDT) integral with the actuators.

4.12 Gas Generator Overall Features

Included are modular LPC assembly, fabricated compressor front frame and air collector, modular HPC and HPT, fabricated compressor rear frame and turbine mid-frame and modular LPT. Each rotating mass will be supported by roller bearings, and rotor axial thrust loads are carried by ball bearings. Labyrinth type, long-life seals will be used in the bearing sumps. Each sump will be individually scavenged. A common line to an air/oil separator vents the “A”, “B-C” and “D-E” sumps.

4.13 Starting Motor

A hydraulic motor will be installed on the accessory gearbox to provide starting torque to the gas turbine. A 200 HP (150 kW) electric motor and hydraulic pump mounted on the auxiliary equipment module provide pressured hydraulic oil to power the hydraulic starter motor. (See Section 9).

4.14 Fuel Systems

The Purchaser will supply fuel in accordance with GE M&IAD Spec MID-TD-0000-1 at the baseplate connection. The components downstream of the baseplate connection are supplied by the Seller.

4.15 Lubrication System

A complete lubrication system for the gas turbine will be furnished as described in Section 10. The lube oil system includes mechanical pump, duplex filters, pressure and temperature instrumentation, 304 stainless steel reservoir and a 304 stainless steel piping system. The gas turbine uses rolling element dry sump bearings. There will be no need for auxiliary lube oil pumps. Bearing sumps will be sealed with knife-edge seals and pressurized with compressor bleed air. Oil will be removed from the seal air by an air-oil coalescer mounted on the roof skid.

4.16 Ignition System

The ignition system includes one ignition unit, which converts the 115 V, 60 Hz power to high voltage, and includes a high tension lead and igniter. The ignition system will be used only during starting and will be turned off once the engine reaches idle speed.

4.17 Borescope Inspection Provisions

Ports and removable covers in the casing permit borescope inspection of the blades and vanes of the low pressure compressor, the high pressure compressor, the high pressure turbine, the low pressure turbine, combustor, frames, and accessory gearbox.

4.18 Turbine Mounted Instruments

These devices will be incorporated into an electronic control system furnished. Details of the control system are described in Section 13.

The gas turbine will be equipped with the following sensors:

Qty Sensor

2 Speed sensors (XN25) high-pressure rotor - magnetic pickup type - located on accessory gearbox.

Speed sensors (XNSD) LP turbine rotor - magnetic pickup type - located in the LP turbine rear frame.

1 Low-pressure turbine inlet temperature (T48) sensor system - chromel alumel thermocouples - located on LPT case.

2 Accelerometers - located on the gas turbine, compressor rear frame, and LPT rear frame.

7 Resistance Temperature Detectors (RTD) will be provided to measure and monitor the temperature of lube oil in the Transfer Gearbox, the B-C sump, D-E sump scavenge lines, the accessory gearbox and the lube supply line to the gas turbine.

1 Low-pressure turbine inlet pressure probe (P48) - total pressure - located on the low-pressure turbine case.

1 Low-pressure compressor inlet temperature and total pressure probe (T2, P2) - located on the IGV case. The probe is a dual element RTD (two separate RTDs in one probe). The probe also includes a P2 (total pressure) sensing port.

1 High-pressure compressor inlet temperature and total pressure probe (T25, P25) - located on front frame. The probe will be a dual element RTD (two separate RTDs in one probe). The probe also includes a P25 (total pressure) sensing port.

2 Variable stator vane (VSV) position sensors - linearly variable differential transformer (LVDT) - located on the actuators.

2 Variable bleed valve (VBV) position sensors - linearly variable differential transformer (LVDT) - located on the actuators.

1 High-pressure compressor discharge temperature (T3) sensor - A dual element chromel - alumel thermocouple mounted on the compressor rear frame.

3 Remote indicating chip detectors, located in scavenge oil return lines.

2 Liquid manifold temperature sensors will be provided. Type K thermocouples (furnished on dual-fuel or gas-fuel-with-water-injection units only).

4.20 Water Injection System

The water injection system consists of inlet strainer, valves, piping controls and a duplex or two simplex boost pump skid(s) to boost water pressure to the required pressure. Purchaser must supply demineralized water to the customer connection located on the water injection boost skid. A minimum supply pressure of 5 psig will be available during gas fuel operation at a maximum rate of 55 gpm. NOx water cleanliness will satisfy GE M&IAD Spec MID-TD-0000-3.

5.0 GENERATOR AND AUXILIARIES