United Engine Corporation (UEC) Inter RAO Group General Electric

6F.03 (6FA) gas turbine unit

Gas turbine unit 6F.03 (6FA)

Specifications of power units based on gas turbine units 6F.03 (6FA)

GT MODEL Simple cycle
output power
Combined cycle
output power
Combined cycle
output power
Efficiency in the combined cycle
6F.03 (6FA) 82 MW 124 MW 250 MW >55%


Russian Gas Turbines LLC provides for a full range of maintenance services, including the services of installation/adjustment supervision, efficiency tests, personnel training, as well as services of long-term maintenance.

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International operation experience

The 6F.03 (6FA) gas turbine is well-suited for both base load and cyclic duty in a variety of configurations, including combined cycle, district heating, oil and gas or industrial cogeneration.

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Main technical parameters and key components

The gas turbine unit 6F.03 (6FA) is based on the advanced technologies used in GT 7FA design. The configuration is a single shaft, bolted rotor with the generator connected to the gas turbine through a reduction gear coupling on the compressor side or on the "cold" end. Such feature allows for axial exhaust and arrangement optimization in the combined cycle.

Gas turbine 6F.03 (6FA) parameters

Number of compressor stages 18
Compression ratio 16.4:1
Number of turbine stages 3
Combustion chamber type, number of combustion chambers cannular, 6 combustion chambers
Fuel combustion temperature > 1260 °C
Fuel types Natural gas, associated petroleum gas, synthetic gas, diesel fuel
Starter Electric motor
Exhaust system Axial

6F.03 (6FA) gas turbine generator parameters

Power (delay) coefficient


Output voltage, kV 11.5 kV
Rated power, MW 82 MW


Compressor is axial and has 18 stages with the first row of modulating inlet guide vanes and a compression ratio of 16.4:1 under ISO conditions. Compressor consists of rotor and casing (stator). The first two stages are realized with supersonic technologies. Compressor is designed with interstage air extraction for cooling and sealing of the turbine nozzles and the wheel space, as well as for surge control during GT start-up. Compressor wheels are tightened with 15 bolts, thus making a rigid structure, and are centered with rabbets.

Combustion system

The gas turbine has a reverse-flow system with six low-emission combustion chambers of the 2nd generation (DLN-2.6), with six nozzles per chamber. Standard combustion system equipment includes two retractable spark plugs and four flame detectors. Crossfire tubes connect each combustion chamber to adjacent chambers on two sides. Heat-resistant insulation is applied to the internal surface of liners and transition pieces. Each combustion chamber, flame tube or adapter can be replaced separately to facilitate maintenance.

Casings and exhaust diffusor

The gas turbine has five casings that are horizontally split for maintenance and repair. Boroscopic holes are located on compressor casing, combustion chambers and turbine casing for visual inspections. Fire-resistant bearing can be accessed by removing the upper half of the compressor inlet casing. The other bearing is readily accessible for maintenance and repair without dismantling the turbine casing.

Exhaust diffusor consists of two cylinders. After the third turbine stage, exhaust gases flow to the diffusor, where they slow down and restore pressure to improve efficiency. The exhaust diffusor is equipped with 21 thermocouples to control gas temperature.


Turbine section has three stages with air cooling of all three nozzle stages and of the first two bucket stages. The first-stage bucket has an advanced cooling system to bear high combustion temperatures. The cooling system uses turbulated inner passages with cooling air discharging through the blade tip, front and back edges. Blades have elongated shanks to isolate turbine wheel rim from hot gas flow, and integral shrouds are incorporated on the 2nd and 3rd stages to eliminate fatigue stresses and to improve efficiency. The first stage has a two-piece shroud that allows reducing tip clearances.

The design of a single-shaft rotor with two bearings ensure high torque moment, and has internal air-cooling for the turbine section. Shaft rotates counterclockwise when facing the gas turbine output flange, and the load gear changes the direction of rotation as it drives the rotor. For on-site replacement, turbine rotor is handled and taken off the casing as a single unit, and the turbine buckets can be replaced in sets or individually without any field rotor balancing.

Standard specifications of gas turbine unit 6F.03 (6FA) under ISO conditions

Electric power at generator's terminals 82 MW
Efficiency at generator's terminals 36%
Specific heat consumption 9991 kJ/kWh
Exhaust gas temperature 613 °C
Exhaust gas flow 213.1 kg/sec
NOx content in emissions 15 ppm
CO content in emissions 9 ppm

Standard supply set of gas turbine unit 6F.03 (6FA)

Load gear
DLN 2.6 module
Electric and electronics control room (Mark VIe)
Startup device - static frequency converter (SFC)
Lube oil and gas fuel system module.
Air atomizing and water injection system module
Exhaust silencer
Gas turbine enclosure
Acoustic enclosure
Air inlet
Auxiliary transformer


Supply of eight GTU 6F.03 (6FA) for Kaliningrad region

In December 2015, Russian Gus Turbines LLS signed an agreement with LLC "Kaliningrad Generation" for the supply of eight...

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Two GT 6F.03 (6FA) for power supply of Rosneft oil fields

The fact that 6FA gas turbines with highly robust and reliable construction can tolerate harsh conditions explains the choice...

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