EP1206634A4 - Systeme de suralimentation pour turbines a gaz - Google Patents

Systeme de suralimentation pour turbines a gaz

Info

Publication number
EP1206634A4
EP1206634A4 EP00968293A EP00968293A EP1206634A4 EP 1206634 A4 EP1206634 A4 EP 1206634A4 EP 00968293 A EP00968293 A EP 00968293A EP 00968293 A EP00968293 A EP 00968293A EP 1206634 A4 EP1206634 A4 EP 1206634A4
Authority
EP
European Patent Office
Prior art keywords
supercharging
gas turbine
turbine
subsystem
power
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP00968293A
Other languages
German (de)
English (en)
Other versions
EP1206634A1 (fr
Inventor
William L Kopko
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Enhanced Turbine Output Holding LLC
Original Assignee
Enhanced Turbine Output Holding LLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US09/388,927 external-priority patent/US6308512B1/en
Priority claimed from US09/475,154 external-priority patent/US6442942B1/en
Application filed by Enhanced Turbine Output Holding LLC filed Critical Enhanced Turbine Output Holding LLC
Publication of EP1206634A1 publication Critical patent/EP1206634A1/fr
Publication of EP1206634A4 publication Critical patent/EP1206634A4/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/36—Open cycles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates generally to gas turbine power generation systems and more
  • the system uses a supercharging
  • the supercharging fan is preferably combined with an inlet air
  • This low rating temperature means that the
  • capacity reduction at summer-peaking conditions can amount to approximately 20 to 40%
  • cooling can reduce inlet air temperatures by 10 to 20 °F, depending on the local climate.
  • Another method for controlling turbine capacity involves a variable-speed
  • intercooling effect is roughly a 5% increase in capacity for a water mass flow equal to 1%
  • fogging is the amount of water mist that compressor may
  • At least one turbine manufacturer has
  • the invention may be added to an existing gas turbine or designed for a new,
  • Figure 1 is a graph illustrating the relationship between turbine capacity and
  • FIGS. 2A-2C are schematic diagrams of one preferred embodiment of the present invention.
  • FIG. 3 shows another preferred embodiment of the invention that uses an
  • Figure 4 shows an alternate embodiment of the invention that uses an axial-flow
  • FIG. 5 shows another alternate embodiment of the invention that uses series
  • Figure 6 is a graph comparing the temperature- variant turbine capacity of several
  • Figures 7 A and 7B are schematic compressor maps that show the principles of
  • Figures 8A and 8B are fan curves that show how multiple fans can be used to vary
  • Figure 9 is a graph of maximum supercharging pressure as a function of turbine
  • FIG 10 shows an alternate embodiment of the invention in which heated
  • compressor output air is fed back into the compressor inlet air stream to regulate gas turbine performance
  • FIG 11 shows an alternate embodiment of the invention in which turbine output
  • FIG 12 shows an alternate embodiment of the invention in which turbine output
  • Figure 13 illustrates an embodiment of the invention employed in a combined-
  • Figure 14 illustrates a preferred embodiment of the invention which uses a
  • Figure 15 is a perspective view illustrating the preferred construction
  • Figures 16A and 16B are an end view and a section view, respectively, illustrating
  • Figures 17A and 17B are perspective views illustrating application of the
  • Figure 18 is a schematic diagram of another preferred embodiment of the
  • a supercharger for a gas turbine contains a fan and a fogger located in
  • FIG. 2A shows a preferred embodiment of the invention.
  • a gas turbine power plant 11 contains a gas turbine system 10 and a generator 28.
  • Gas turbine system 10
  • the turbine 16 includes a compressor 12, a burner 14, and a turbine 16.
  • the turbine 16 shares a common
  • the compressor 12 receives
  • Burner 14 heats the air from
  • Turbine 16 rotates in response to the received heated inlet air stream 22, thereby rotating
  • Figure 2A depicts a simple turbine arrangement for the purpose of
  • the gas turbine will normally include filters,
  • the inlet air stream 18 is provided to the compressor 12 as follows. A first
  • supercharging fan 30 and a second supercharging fan 32 draw ambient air 40 and supply
  • the air cooler 34 is preferably a direct evaporative cooler that cools and humidifies the air
  • cold water can be provided by a vapor-compression chiller, an absorption chiller, or from
  • the air cooler is preferably located in
  • the supercharging fans is that it can remove any heat added by the supercharging fans.
  • a bypass damper 36 allows air to enter the plenum 38 without going through the
  • supercharging fan 32 has a second damper 44 on its discharge end.
  • the controller 50
  • the controller can be as simple as a thermostat; alternatively, it may include
  • Dampers 42 and 44 and bypass damper 36 act as check valves to prevent reverse
  • the dampers preferably open in response to a pressure
  • FIGS. 2B and 2C show how the dampers operate in response to
  • the first and second supercharging fans 30 and 32 preferably are belt-driven
  • centrifugal fans or direct-drive axial fans.
  • the preferred design uses
  • Fans of this type can supply a
  • Electric motors preferably three-phase
  • induction motors ⁇ normally would provide the power to drive the supercharging fans
  • fans can be used, or even a single supercharging fan may be used.
  • supercharging fans allow for staging of fans to adjust turbine inlet pressure in increments
  • the two supercharging fans have approximately equal pressure
  • the lead supercharging fan has a larger flow
  • variable-speed drives or, in the case of axial fans, variable-pitch blades are
  • Inlet vanes are another alternative, but not preferred because of their relatively poor efficiency.
  • Figure 3 shows an alternate embodiment that uses an indirect evaporative cooler
  • the configuration is similar to that
  • turbine system 10 and generator 28 form a gas turbine power plant 11. Likewise, the gas
  • turbine system 10 includes a compressor 12, a burner 14, and a turbine 16.
  • evaporative cooler 60 uses a secondary air stream 62, which is taken from a portion of the
  • a turbine inlet air stream 66 is formed by the remaining
  • stream 62 is indirectly heated and humidified by the air flow from plenum 38 inside the
  • indirect evaporative cooler 60 exits as exhaust air stream 65.
  • Figure 4 shows another alternate embodiment that uses a motor-driven axial-flow
  • Supercharging fan 116 includes a motor 100 that drives impeller 102,
  • the motor 100 is preferably a three-phase
  • induction motor and is connected to a utility power line by conductors 110, 112, and 114
  • the contactor 104 may be a simple, manually operated device, in which case an
  • the preferred arrangement includes a thermostat 109
  • Thermostat 109 thus functions to limit turbine
  • the supercharging fan can be any kind of sophisticated controls.
  • the supercharging fan can be any kind of power.
  • variable-pitch blades which are adjusted by a controller that senses pressure
  • Additional mechanical hardware can be added to improve performance. For example, a
  • bypass damper can reduce the pressure drop through the supercharging fan when it is not
  • a direct evaporative cooler or other cooling means could be added to reduce
  • An eddy current clutch or mechanical clutch could be
  • FIG. 5 shows another alternate embodiment, this one having two supercharging
  • a first supercharging fan 216 includes a first impeller 202 and a
  • the first motor 200 in a first housing 206.
  • the first fan is located in an inlet air stream 208
  • Conductors 210, 212, and 214 connect the first motor 200
  • a second fan 236 is located upstream of the
  • the second fan comprises a second impeller 222 and a second motor 220 in
  • the second motor 220 is connected through switch 224 and
  • First and second damper 42 and 44 are
  • FIG. 2B shows operation with the first supercharging fan 30 off and the second
  • damper 36 is open to allow air to go around the supercharging fans 30 and 32.
  • Figure 6 illustrates the benefits of such a system. This figure is based on
  • the present invention is essentially flat, while the capacity for conventional systems drops
  • the base system is a simple-cycle turbine that
  • the present invention also has the same 100 MW capacity
  • the bigger base and bigger base with evaporative cooler are simple-cycle turbines
  • cooler takes advantage of the lower inlet temperatures available with evaporative cooling to reduce the size requirements of the turbine for a given capacity at high ambient
  • the present invention limits turbine output to allow the benefits of supercharging
  • Table 1 shows a cost comparison (adapted from Kolp et al.) for the supercharger
  • the new supercharger is less than half of the cost of adding peaking turbine capacity.
  • Table 2 shows how adding a supercharging fan can improve power plant
  • supercharging fan can significantly improve peak power output for gas turbines.
  • Table 2 shows that a significant improvement is possible with a supercharging fan
  • supercharging pressure may exceed 60 inches of static pressure.
  • Figures 7A and 7B are compressor maps illustrating the improvement in turbine
  • the vertical axis is turbine
  • the horizontal axis is the mass flow parameter, which is given by the equation:
  • m is the turbine mass flow rate
  • ⁇ is the compressor inlet pressure divided by the standard atmospheric pressure
  • ⁇ is the compressor inlet absolute temperature divided by design absolute
  • the pressure ratio is the compressor discharge pressure divided by the atmospheric pressure.
  • Compressor curve 300 shows the performance of the compressor at design
  • compressor curve 301 shows the performance at peak inlet temperature.
  • Turbine line 302 shows the performance of the turbine at design conditions
  • line 303 represents the turbine performance at peak inlet temperature.
  • compressor curve 300 and turbine line 302 defines the design operating point 304.
  • intersection of the compressor curve 301 and turbine line 303 is operating point 305 at the
  • the operating line 306 shows possible turbine operating points at
  • Surge line 307 is the limit of stable operation for the
  • the air can restore the turbine capacity.
  • Figure 7B illustrates how the new system can improve turbine capacity at peak
  • turbine line 312 reflects the slightly higher temperature. The intersection of the turbine
  • Operating line 318 shows possible operating conditions with different operating parameters
  • Another compressor curve 316 and a turbine line 320 correspond to a lower
  • the turbine capacity are the operating pressures and power output that are acceptable for
  • Figure 8A plots fan curves showing how parallel supercharging fans can work
  • a lead fan curve 350 is for
  • the gas turbine line 356 is nearly vertical since the flow through the turbine
  • the operating point 358 is at the intersection of the lead fan curve 350 and the turbine line 356. This operating point 358 corresponds to
  • a first lag fan curve 352 corresponds to the performance of the lag fan at full
  • Fan curve 364 corresponds to running both fans together. The intersection of the
  • a second lag fan curve 354 represents fan performance at low speed
  • fan curve 360 represents the corresponding two fan operation.
  • An operating point 362 is the corresponding two fan operation.
  • FIG. 8B illustrates operation with two similar fans in series. Fan curve 372
  • turbine line 370 represents operation point 378 for one fan.
  • Fan curve 374 corresponds to
  • Operating point 376 represents turbine operation with both fans
  • the controller can use the
  • the gas turbine power plant comprises a gas turbine system 432
  • the gas turbine system 432 includes burner 422, compressor 420,
  • stream 440 enters the compressor 420 and is compressed to form burner inlet air stream
  • the burner 422 heats the air stream 442 to form burner outlet air stream/ turbine
  • inlet air stream 444 that enters turbine 424.
  • the turbine 424 extracts power from the air
  • the gas turbine power plant also includes structure,
  • the gas turbine power plant also may include a bottoming steam cycle system or
  • the turbine 424 drives the compressor 420 and generator 426, which also shares
  • the generator supplies electric power to the utility grid through conductors
  • Supercharging fan 423 pressurizes fan inlet air stream 453 to form a pressurized
  • the first evaporative cooler 425 The first evaporative cooler 425
  • the first evaporative cooler 425 cools
  • the supercharging fan supplies a static pressure on the order of 60 inches of water
  • the pressurized air stream 455 may be a centrifugal fan or an axial fan.
  • a second evaporative cooler 470 is provided upstream of the supercharging fan
  • the evaporative cooler includes an evaporative pad 434 and a pump 436, which
  • the evaporative coolers each also may include a sump with a float valve to
  • evaporative coolers are illustrated, indirect evaporative coolers or indirect-direct
  • evaporative coolers also may be employed.
  • a key feature of the present invention is the relative sizing of the supercharged
  • the supercharged turbine are sized so that the generator operates at nearly full capacity at
  • auxiliaries would be sized based on full supercharged output at winter conditions
  • invention includes means for controlling turbine capacity at low ambient temperatures so
  • a controller 460 receives a current signal 468 from a current sensor
  • the controller 460 preferably includes the normal capacity and safety functions of the gas turbine power plant, but it may alternately be a
  • the current sensor is preferably a current transformer, in which case the
  • the controller 460 provides a damper control signal 464 to damper 450 to control
  • the controller 460 also identifies the damper 450 and circulates through the damper 450 to the compressor inlet.
  • the controller 460 also specifies the controller 460 to control the damper 450 and circulates through the damper 450 to the compressor inlet.
  • the controller 460 also specifies the controller 460 to control the damper 450 and circulates through the damper 450 to the compressor inlet.
  • embodiment may be as simple as on/off control, although variable control with variable-
  • variable-pitched blades also might be employed.
  • the current sensor 462 senses a
  • controller 460 responds first by turning off the pump 436, thereby
  • the preferred control response is to start to open the damper 450 to allow heated air 452 to
  • the controller 460 sends a fan
  • the controller 460 may then send a damper control signal 464 to
  • controller 474 receives a current signal 468 from a current sensor 462 that senses
  • controller 474 provides a pump control signal 466 to pump 436
  • controller 474 also provides a burner
  • control signal 472 to the burner 422, which regulates the burner output and hence turbine
  • controller 474 the controller 474
  • the controller also can be a stand-alone
  • controller 474 responds by
  • controller 474 responds by
  • FIG 12 shows another alternate embodiment of the invention in which turbine
  • output is controlled by regulating compressor inlet temperature using a heater.
  • Controller 484 receives a temperature signal 490 from a temperature sensor 488 that is
  • the controller 484 provides a heater
  • control signal 482 to a heater 480 located upstream of the compressor inlet, and the heater
  • the heater is upstream of the evaporative cooler, the heater alternatively may be located
  • a second option is to use a boiler with a separate liquid-to-air heat
  • a third option is to use a heat exchanger that recovers heat from the turbine
  • Electric heaters are a fourth option, although they are not
  • the heater should be capable of modulating its output so as to maintain the
  • the controller 484 responds by turning
  • controller 484 provides a heater control signal 482 to turn on heater 480
  • Figure 13 shows another, similar alternate embodiment that is especially suitable
  • a combined-cycle gas turbine power plant for use with a combined-cycle power plant.
  • a combined-cycle gas turbine power plant for use with a combined-cycle power plant.
  • 506 includes an additional steam cycle system 498 that utilizes exhaust heat from the
  • the steam cycle 498 includes a boiler 504, a
  • a liquid-to-air heat exchanger 491 is provided in a fluid loop with
  • the pump 492 circulates heat transfer
  • the pump receives a signal 494 from controller 484, which regulates
  • the controller also can turn off the second evaporative cooler 470 as a first step in
  • Direct contact liquid-to-gas heat exchange is also an
  • the liquid would contain a suitable neutralizing agent (such as sodium bicarbonate), sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium bicarbonate, sodium
  • heat from the condenser 502 could be used to warm the inlet air stream.
  • compressor inlet temperature as feedback control parameters, other parameters may be
  • control inputs may include generator
  • Figures 10 through 13 show a second evaporative cooler
  • this feature is optional and can be eliminated
  • the second evaporative cooler does enhance the first evaporative cooler
  • the use of the first evaporative cooler is also optional to some extent, but
  • control is the preferred method of control for the supercharging fan. More sophisticated
  • variable-speed drives or variable-pitch fan blades are examples of variable-speed drives or variable-pitch fan blades.
  • Figure 14 illustrates a preferred embodiment that incorporates an indirect
  • variable-speed drive 550 receives electrical power from the
  • variable-frequency AC power to an induction motor 522.
  • induction motor 552 drives a shaft 554 that drives a supercharging fan 556.
  • supercharging fan draws ambient air and supplies a pressurized air stream 558 to a
  • the cooling coil is a water-to-air heat exchanger that cools the air
  • a cooled air stream 570 exits the coil and enters an evaporative cooler 425, which is configured as described above.
  • the cooling coil 560 is connected, by means of piping 562, to a pump 564 and a
  • cooling tower 566 to form a circuit, which circuit acts as an indirect evaporative cooler.
  • the cooling tower is preferably a forced-draft wet tower which can cool water to
  • cooling tower and cooling coil could be replaced with an air-to-air heat located
  • a direct evaporative cooler could be placed upstream of the heat exchanger, on
  • controller 568 prevents overload of the gas turbine at lower
  • the controller 568 receives a temperature signal 572 from a
  • the controller also receives a pressure signal 574 from a pressure sensor 575
  • the pressure sensor 575 can be located in the pressurized air stream 558.
  • the pressure sensor 575 can be located in the pressurized air stream 558.
  • the controller 568 provides a speed control signal 578 to the variable-speed drive
  • This signal modulates the speed of the supercharging fan to maintain the optimum
  • the controller also provides an output signal 576 to pump 564 in
  • cooling tower is unaffected by the energy input from the supercharging fan. Therefore, the cooling coil can cool the airstream 558 to temperatures approaching the ambient wet-
  • the evaporative cooler 425 can then
  • desiccant, or absorption cooling systems may replace the direct evaporative cooler.
  • Cooling systems using ground water or cold lake or ocean water are another option.
  • An interior duct 610 is disposed
  • the fluid would be air, but the ductwork assembly may be
  • the space 615 is filled with fluid or
  • porous material such as fiberglass, open-cell foam, etc.
  • porous fill material such as fiberglass, open-cell foam, etc.
  • the flow passage 612 for equalizing pressure across the interior duct may be
  • the flow passage may also be provided by cracks or other small openings that are
  • passage 612 is that it must be able to permit sufficient fluid flow rates through it to ensure
  • path may include a pressure relief valve to reduce the risk of damage to the interior duct if
  • Figure 15 shows a rectangular interior duct
  • the interior duct may have
  • the interior duct need only handle
  • the outer duct preferably has a circular cross-section to minimize material
  • ducts may include corrugations or other reinforcements to improve rigidity and reduce
  • Typical materials for constructing the ducts include metals such as steel or
  • Figure 16A and 16B show a front and a cross-sectional view, respectively, of a
  • transition duct which may be used to connect two different sized ducts.
  • conical outer duct 620 encloses a tetrahedral or pyramidoidal interior duct 621.
  • passage 622 is provided in the wall of the interior duct 621 to equalize fluid pressure
  • This transitional duct assembly can be used either as a diffuser or a flow
  • 16 A, and 16B illustrate basic configurations of the high pressure duct according to the
  • this invention can be applied to practically any particular duct geometry
  • FIGS 17A and 17B illustrate such ductwork employed specifically with a gas
  • Figure 17A shows the cooler, without a supercharger, with a direct
  • evaporative cooler 630 at the end of a rectangular duct 631 that supplies air to the inlet of
  • the rectangular duct 631 is designed to carry a pressure difference (as
  • FIG 17B shows the corresponding supercharged configuration.
  • the fan 635 is connected to an end piece 639 of a diffuser duct 636.
  • the diffuser duct is
  • Each of these ducts includes a round duct on the exterior that encloses a rectangular interior duct.
  • the new duct that requires huge amounts of material for reinforcement.
  • the new duct that requires huge amounts of material for reinforcement.
  • Fig. 18 illustrates an alternate preferred embodiment of the invention, using a
  • a gas-turbine power plant 121 comprises
  • a compressor 120 and an expander 124 that are rigidly attached to a shaft 130 that drives
  • An air stream 191 enters the compressor, which pressurizes the air and supplies it to a combustor 122.
  • the combustor heats the air and supplies it to the
  • the expander extracts work from the expanding gas to drive the
  • a supercharger 190 is located upstream of the gas-turbine power plant.
  • supercharger comprises a fan 140, a first fogger 149, and a second fogger 169 that are
  • the first fogger is located upstream of the fan, while the
  • second fogger is located between the fan and the turbine.
  • the fan 140 comprises a hub 141 and fan blades 142.
  • the fan is rigidly attached
  • a motor 146 drives the motor shaft 144 and thereby drives the fan
  • the fan is preferably a variable-pitch axial flow fan.
  • the hub 141 includes a
  • the motor is preferably a three-phase induction motor or other electric motor.
  • the output of the fan is on the order of 60 inches of water static pressure.
  • optimum pressure depends on the availability of a suitable fan, generator capacity, turbine
  • a multistage, axial- flow fan as shown in Figure 18, can achieve this static pressure. Centrifugal fans or single-stage axial fans are also an option. If centrifugal fan
  • variable-pitch blades are not normally an option so a variable-speed drive is the
  • variable inlet vanes are preferred means for controlling fan capacity.
  • Other options include variable inlet vanes
  • Variable-speed is also an alternative for axial fans.
  • the first fogger 149 comprises a first manifold 156, second manifold 158, and a
  • Each manifold has spray nozzles that create mist 162. The first
  • manifold receives pressurized water from a first pump 150. Likewise a second pump 152
  • the pump outlet pressure is preferably roughly 1000 to 3000 psi.
  • the stream of water 164 feeds the pump inlets.
  • the water is preferably filtered,
  • An air stream 148 is drawn into the duct 147 through the first
  • the second fogger 169 is located downstream of the fan. Like the first fogger,
  • the second fogger is comprised of multiple manifolds and pumps.
  • sixth manifolds, 176, 178, and 180 are connected to fourth, fifth, and sixth pumps 170,
  • the first fogger is preferably sized to ensure
  • water added to the air stream would preferably be the amount for saturation at the inlet to
  • a controller 161 controls the operation of the supercharger 190.
  • the fan inlet temperature provides a signal to the controller to reduce fan capacity by
  • temperatures mean that less water is required to saturate the air, so the controller 160 can
  • the pumps for the first fogger can be turned
  • the second fogger may still operate at this condition, if the
  • foggers may be turned off and the fan may be allowed to free rotate in the air stream.
  • bypass damper around the fan may be provided to reduce pressure drop to the turbine
  • the second fogger may be eliminated in cases where the turbine compressor is especially sensitive to
  • the controller could modulate the amount of fog from
  • the first fogger to ensure complete evaporation of the water droplet before they reach the
  • Multiple fans can provide redundancy to improve
  • turbine capacity control such as modulation of the combustor output or means for
  • heating the inlet air stream can prevent overload of the generator and other components.
  • a silencer is preferably located upstream of the fan
  • a large increase in capacity The system can achieve a capacity increase
  • the controls allow the system to match the maximum capacity of the gas-turbine power plant at a wide range of ambient temperature
  • gas-turbine power plant can continue to operate without the supercharger in

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

L'invention concerne un système de suralimentation destiné à des centrales à turbines à gaz (11). Le système comprend un ventilateur de suralimentation (30, 32) et un contrôleur (50) permettant de limiter la sortie d'énergie des turbines, afin d'empêcher une surcharge du générateur (28) à une température ambiante basse. Le contrôleur peut limiter la sortie d'énergie en contrôlant, entre autres, les brûleurs, la température d'entrée ou la suralimentation de la pression du ventilateur. L'invention permet au système de suralimentation d'être installé de façon rétroactive sur des turbines existantes, sans qu'il soit nécessaire de remplacer le générateur et les parties associées.
EP00968293A 1999-06-10 2000-06-09 Systeme de suralimentation pour turbines a gaz Withdrawn EP1206634A4 (fr)

Applications Claiming Priority (15)

Application Number Priority Date Filing Date Title
US475154 1983-03-14
US13884899P 1999-06-10 1999-06-10
US138848P 1999-06-10
US13989499P 1999-06-22 1999-06-22
US139894P 1999-06-22
US388927 1999-09-02
US09/388,927 US6308512B1 (en) 1999-06-10 1999-09-02 Supercharging system for gas turbines
US15227799P 1999-09-03 1999-09-03
US152277P 1999-09-03
US15920799P 1999-10-13 1999-10-13
US159207P 1999-10-13
US09/475,154 US6442942B1 (en) 1999-06-10 1999-12-30 Supercharging system for gas turbines
US19530200P 2000-04-10 2000-04-10
US195302P 2000-04-10
PCT/US2000/015821 WO2001000975A1 (fr) 1999-06-10 2000-06-09 Systeme de suralimentation pour turbines a gaz

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Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8584464B2 (en) 2005-12-20 2013-11-19 General Electric Company Gas turbine engine assembly and method of assembling same
JP4929004B2 (ja) * 2007-03-23 2012-05-09 三菱重工業株式会社 ガスタービン発電システム
BRPI0823073A2 (pt) * 2008-09-08 2015-09-22 Volvo Lastvagnar Ab metodo para diagnosticos embarcados e sistema para diagnosticos embarcados
KR101011335B1 (ko) * 2009-01-15 2011-01-28 김한기 스팀 발생장치
KR101503294B1 (ko) * 2011-01-21 2015-03-18 미츠비시 히타치 파워 시스템즈 가부시키가이샤 발전 플랜트
TWI563164B (en) * 2011-03-22 2016-12-21 Exxonmobil Upstream Res Co Integrated systems incorporating inlet compressor oxidant control apparatus and related methods of generating power
EP2809905A1 (fr) * 2012-01-30 2014-12-10 PowerPHASE LLC Systèmes de stockage d'énergie et de complément d'énergie de turbine à gaz et leurs procédés de fabrication et d'utilisation
US9239007B2 (en) * 2012-05-31 2016-01-19 General Electric Company Gas turbine compressor inlet pressurization having a torque converter system
US20130318941A1 (en) * 2012-05-31 2013-12-05 General Electric Company Supercharged Combined Cycle System With Air Flow Bypass
US9771864B2 (en) * 2012-05-31 2017-09-26 General Electric Company Gas turbine compressor inlet pressurization and flow control system
CN102797833A (zh) * 2012-08-31 2012-11-28 长城汽车股份有限公司 车辆生热构件用冷却节能装置
JP6291245B2 (ja) * 2012-12-20 2018-03-14 ゼネラル・エレクトリック・カンパニイ Ｈｒｓｇおよびファンへの空気流バイパスを備えた過給結合サイクルシステム
US9567913B2 (en) * 2013-01-28 2017-02-14 General Electric Company Systems and methods to extend gas turbine hot gas path parts with supercharged air flow bypass
US9581089B2 (en) * 2013-05-10 2017-02-28 General Electric Company Gas dosage control for gas engine
EP2910742A1 (fr) * 2014-02-20 2015-08-26 Siemens Aktiengesellschaft Procédé de couplage d'une turbine à vapeur et d'une turbine à gaz avec un angle différentiel
US10030558B2 (en) * 2015-06-29 2018-07-24 General Electric Company Power generation system exhaust cooling
RU2621448C2 (ru) * 2015-10-06 2017-06-06 федеральное государственное автономное образовательное учреждение высшего образования "Самарский государственный аэрокосмический университет имени академика С.П. Королева (национальный исследовательский университет)" (СГАУ) Способ работы комбинированной газопаровой установки
RU2628851C1 (ru) * 2016-10-25 2017-08-22 федеральное государственное бюджетное образовательное учреждение высшего образования "Национальный исследовательский университет "МЭИ" (ФГБОУ ВО "НИУ "МЭИ") Газотурбинная установка
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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1029635A (fr) * 1950-11-14 1953-06-04 Snecma Perfectionnement aux turbo-réacteurs à deux flux
US3500636A (en) * 1966-02-18 1970-03-17 Ass Elect Ind Gas turbine plants
DE3425115A1 (de) * 1984-07-04 1986-01-16 Nebojsa Prof Dr Ing Gasparovic Gasturbinenanlage mit aufgeladenem, teilgeschlossenem kreislauf mit unmittelbarer verbrennung im arbeitsgasstrom
JPS63208624A (ja) * 1987-02-26 1988-08-30 Mitsui Eng & Shipbuild Co Ltd ガスタ−ビンの出力制御装置
US5937633A (en) * 1996-05-31 1999-08-17 Wang; Lin-Shu High-pressure intercooled gas turbine
US6003298A (en) * 1997-10-22 1999-12-21 General Electric Company Steam driven variable speed booster compressor for gas turbine

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB676008A (en) * 1948-10-11 1952-07-23 Rateau Soc Improvements in or relating to gas turbine plants
US2705865A (en) * 1950-02-16 1955-04-12 Maschf Augsburg Nuernberg Ag Method of operating gas turbines
US3796045A (en) * 1971-07-15 1974-03-12 Turbo Dev Inc Method and apparatus for increasing power output and/or thermal efficiency of a gas turbine power plant
US4027407A (en) * 1975-11-24 1977-06-07 Kiss Sandor G Jet flow alternator
US4702074A (en) * 1985-07-30 1987-10-27 Michael Munk Internal combustion engine system with fog injection and heat exchange
JP2971082B2 (ja) * 1989-12-15 1999-11-02 三菱重工業株式会社 ガスタービン設備及びその運転方法
US5191767A (en) * 1990-11-07 1993-03-09 Mistop, Inc. Gas turbine air handling system
US5193352A (en) * 1991-05-03 1993-03-16 Amsted Industries, Inc. Air pre-cooler method and apparatus
JP2954456B2 (ja) * 1993-07-14 1999-09-27 株式会社日立製作所 排気再循環型コンバインドプラント
GB2280224A (en) * 1993-07-22 1995-01-25 Ormat Ind Ltd Method of and apparatus for augmenting power produced from gas turbines
JP3706424B2 (ja) * 1996-01-19 2005-10-12 三菱重工業株式会社 ガスタービン吸気の冷却装置
DE69836910T2 (de) * 1997-04-22 2007-06-21 Hitachi, Ltd. Vorrichtung für eine gasturbine
JP3794168B2 (ja) * 1997-06-27 2006-07-05 株式会社日立製作所 排気再循環型コンバインドプラント
JPH1172029A (ja) * 1997-06-30 1999-03-16 Hitachi Ltd 水噴霧による出力増加機構を備えたガスタービン

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1029635A (fr) * 1950-11-14 1953-06-04 Snecma Perfectionnement aux turbo-réacteurs à deux flux
US3500636A (en) * 1966-02-18 1970-03-17 Ass Elect Ind Gas turbine plants
DE3425115A1 (de) * 1984-07-04 1986-01-16 Nebojsa Prof Dr Ing Gasparovic Gasturbinenanlage mit aufgeladenem, teilgeschlossenem kreislauf mit unmittelbarer verbrennung im arbeitsgasstrom
JPS63208624A (ja) * 1987-02-26 1988-08-30 Mitsui Eng & Shipbuild Co Ltd ガスタ−ビンの出力制御装置
US5937633A (en) * 1996-05-31 1999-08-17 Wang; Lin-Shu High-pressure intercooled gas turbine
US6003298A (en) * 1997-10-22 1999-12-21 General Electric Company Steam driven variable speed booster compressor for gas turbine

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
KOLP D A ET AL: "ADVANTAGES OF AIR CONDITIONING AND SUPERCHARGING AN LM6000 GAS TURBINE INLET", JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER, ASME, NEW YORK, NY, US, vol. 11, July 1995 (1995-07-01), pages 513 - 527, XP002933891, ISSN: 0742-4795 *
PATENT ABSTRACTS OF JAPAN vol. 012, no. 487 (M - 778) 20 December 1988 (1988-12-20) *
See also references of WO0100975A1 *

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AU7823200A (en) 2001-01-31
BR0011468B1 (pt) 2010-08-24
KR20020038921A (ko) 2002-05-24
CN1355869A (zh) 2002-06-26
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EA200200007A1 (ru) 2002-06-27
CA2376788A1 (fr) 2001-01-04

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