GENERATORS, A.C., GAS TURBINE DRIVEN
1350 KW Kawasaki /Stamford, 4160V., enclosure, Series M1A-03 gas turbine engines (2 available)
Individual Gas Turbine Engine Data:
Designed and built by Kawasaki Heavy Industries (KHI), Series MIA, Model 03, s/ns: KHI 52631 & KHI 52632. The Gas-Turbine Engines are suitable for operation utilizing either diesel fuel or kerosene, grades 1 and 2, with an LHV around 10300kcal/kg. Maximum allowable viscosity is 12 CST.
Individual Generator Data:
Mfgr. Stamford model 734D, Rating 1,500 kW, 1,875 kVa at 105o temperature rise over 40oC., 3 ph, 4 wire grounded neutral, s/ns: J55991 & J55992
The sets are housed in sound proof indoor type enclosures and are designed for standby duty with continuous ratings and provision for paralleling with each other and with a local utility company.
(I.) Description of each system
The Kawasaki MIA-03 Industrial Gas Turbine engine is a single-shaft, open cycle turbine with a virtually constant output shaft rotational speed. This engine has originally been developed by KAWASAKI HEAVY INDUSTRIES, LTD. For driving an electric generator. Major subassemblies are (1) turbine power section, (2) gearbox and accessory drive section and (3) controls.
1. Turbine power section
The power section consists of: 1. Compressor (impellers and diffusers) 2. Turbine (rotor and turbine nozzle) 3. Combustion system (combustion liner, ignitor and fuel nozzle)
A. Compressor This unit is a two-stage centrifugal flow design made up of two single-suction radial flow impellers with shrouds and diffusers. B. Turbine Three-stage axial flow type, each stage comprised of a turbine nozzle and a rotor. C. Combustion System This is the unit, which contains the combustion liner. On the MIA-03, fuel, compressed air and ignition come together in a 'single can' combustor. The main component is the combustion liner, whose top end is fixed by the bolts to the combustion casing, and the other a slip fit into a 'scroll' assembly, which surrounds the turbine section. The scroll is a doughnut-shaped duct, which guides the combustion gases to the turbine nozzles.
2. Gearbox & Accessory Drive Section
The main gearbox assembly provides support for the power section of the MIA-03 engine. It contains the reduction gearing that enables the power section to drive accessories and output shaft at appropriate speed. The lubricating oil sump is installed at the bottom of the main gearbox. The accessory gearbox on the main gearbox provides pads for mounting the starter, main and starting fuel pump. Output shaft speed is determined by gear ratio combination. Shaft speed of either 1,500 rpm or 1,800 rpm will be available as requested.
Operation of the MIA-03 Gas Turbine engine being fully automatic, required only a command into the control panel to initiate the start and run sequence. This command, which can either be a manual Start button, and signal from a remote source or from commercial power failure, will initiate start, accelerating and governor control at rated speed.
The engine will automatically be shut down in the event of:
a.) High exhaust gas temperature
b.) Over speed
c.) Low oil pressure
d.) Start failure
(II.) Mechanical Features - General
The Kawasaki MIA-03 gas turbine engine power section is made up of three (3) major components:
The compressor draws in air, discharging it through the combustor and turbine.
Heat energy generated by burning injected fuel is added to air in the combustor, and converted into shaft power by the turbine to drive the compressor and the generator. Two-thirds of the turbine power is consumed to drive the compressor, and the remaining is used for generator driving. The gas turbine power section connected to the gearbox drives components required for the engine operation at rated speed.
1. Compressor section
The compressor casing contains two stages of centrifugal compressors consisting of impellers and diffusers.
The impeller is fitted on a shaft, which is initially turned by an electric starter through drive gearing.
The rotating impeller draws in large quantities of air and accelerates it radially outwards to an extremely high speed. The air passes through the space between the blades and an impeller shroud and leaves at the tips of the impeller blades. The impeller shroud fits over the contoured face of the impeller while keeping a clearance. The shroud is attached to the compressor casing. After receiving kinematic energy from the impeller, the air flows through the diffuser.
The diffuser is a divergent-shaped duct, which surrounds the impeller. As air passes through the diffuser, its speed is reduced due to the increasing area (divergence). A reduction in dynamic pressure increases static pressure.
Thus, the diffuser converts high-speed give to the air by the impeller to a lower speed, high static pressure. Due to compression, the air temperature increases, causing further rise in pressure. Consequently, the compressor transforms mechanical energy into pneumatic energy.
The turbine supplies power to the compressor for pressurizing the intake air. Density of the intake air varies with ambient temperature. Therefore, power required to operate the compressor at normal speed varies with ambient temperature and pressure.
2. Combustion section
Air-fuel mixture burns in a combustion liner. The combustion liner used on the MIA-03 model engine is of the 'single can type'. This single can type has the advantage of easy removal for maintenance and inspection. An integrated fuel nozzle, primary and main, is provided making a simple, dependable fuel system.
The combustion liner is inserted in the scroll, which acts to guide the hot gases of combustion to the turbine nozzles. Top end of this liner is fixed by the nut, which is fastened to the combustor casing; the other end is a slip-fit into the scroll assembly, which surrounds the turbine section.
All the pressurized air passes through the holes and slots in the combustion liner on its way to the turbine section. The required heat energy is supplied by the fuel injected through the fuel nozzle located in the top end of the combustion liner, and the fuel-air mixture is ignited by the ignition system. Ignition is required only at the time of the starting, as the heat of combustion keeps up burning as long as the fuel is supplied. Much of the air discharged by the compressor is used to cool the high temperature combustion gases to the point where the turbine can be operated without melting blades. Therefore, only a small portion of the pressurized air (approximately 25%) supplies the oxygen used in combustion. This is called primary air. The remaining air (secondary air) introduced downstream of the combustion zone, dilutes the product of combustion, bringing the temperature down to a value which the turbine and nozzle can tolerate. Secondary air flows along the inside of the combustion liner walls preventing contact from flame. Proper proportions of primary and secondary air are controlled by the spacing and sizes of the openings in the combustor liner. If fuel flow through the fuel nozzle is high, energy of the gas stream to the turbine will be high and temperature at the turbine inlet will also be high. Therefore, turbine inlet temperature influences the power that can be developed by the turbine.
3. Turbine section
The turbine section is comprised of a turbine wheel and turbine nozzle. The turbine nozzle consists of numerous stator vanes. In the nozzle, air is forced to flow from a large to a small area due to the convergent shaft of the vanes, resulting in an increase in gas speed and a decrease in gas pressure. This is quite opposite in function from the diffuser. The stator vanes are angled to direct combustion gases against the turbine blades. The turbine stator converts combustion gases into low pressure and high speed.
The turbine wheel consists of blades attached to a disc and placed in the flow path of the combustion gases. As gases resist being turned, they exert a force on what attempts to change its direction. When high-speed gases from the stator are forced against the turbine, the blades change direction with the blades being subjected to a force, and the resulting torque rotates the turbine wheel. The turbine changes pneumatic energy, supplied from the compressor, into mechanical energy. The power generated by the turbine is returned thought the coupled main shaft to rotate the compressor. The amount of force given to the turbine wheel is proportional to the mass flow of gases across the turbine wheel blades. The combustion gases, having passed across the turbine wheel, are discharged into the atmosphere.
Included are component and system manuals, a full set of drawings, Switchgear, an individual control panel and a battery charger for each Gas Turbine Generator Set.
Location: Our Millbury, Massachusetts USA Warehouse