Abstract: This invention discloses systems and methods for control of a gas turbine or a gas turbine generator, where the gas turbine is connected to a dryer vessel in which gas turbine exhaust gases are used to heat treat a material in the dryer vessel. The control system comprises one or more sensors for temperature, moisture and/or flow rate in the dryer vessel and/or of the material inside, entering and/or exiting the dryer vessel and a controller responsive to the sensor for controlling the fuel and/or air flow into the gas turbine. This control system and method enables providing the appropriate heat output from the gas turbine to meet the process heat required for the desired material treatment. Optionally, the gas turbine can be a liquid fuel turbine engine, or a reciprocating engine can be substituted for the turbine engine.

Abstract: This invention discloses systems and methods for control of a gas turbine or a gas turbine generator, where the gas turbine is connected to a dryer vessel in which gas turbine exhaust gases are used to heat treat a material in the dryer vessel. The control system comprises one or more sensors for temperature, moisture and/or flow rate in the dryer vessel and/or of the material inside, entering and/or exiting the dryer vessel and a controller responsive to the sensor for controlling the fuel and/or air flow into the gas turbine. This control system and method enables providing the appropriate heat output from the gas turbine to meet the process heat required for the desired material treatment. Optionally, the gas turbine can be a liquid fuel turbine engine, or a reciprocating engine can be substituted for the turbine engine.

Abstract: A combustion control device for a gas turbine is capable of controlling fuel ratios such as a pilot ratio and controlling an aperture of a combustor bypass valve in response to a combustion gas temperature at an inlet of the gas turbine in accordance with the original concept by computing a combustion load command value which is proportional to the combustion gas temperature. The combustion control device is configured to calculate a 700° C. MW value and a 1500° C.

Abstract: A method is described for controlling load variations in a gas turbine. The method comprises reducing the flow of gaseous fuel entering the combustor to a predefined minimum value, if an increase is observed in the rotation regime of said turbine above a predefined maximum value and a total reduction in the load, activating a selective feeding sequence of the burners if the turbine is operating in normal functioning or premixed flame mode, modifying the angulation of the adjustable stator vanes, in order to reduce the speed rate of the compressor, and opening one or more anti-surge valves and one or more overboard bleeds, in order to reduce the air flow at the inlet of the combustor.

Abstract: Propellant management systems and methods are provided for controlling the delivery of liquid propellants in a space launch vehicle utilizing multiple rockets. The propellant management systems and methods may be configured to enable substantial simultaneous depletion of liquid propellants in each of a plurality of active rockets during operation of various booster stages of the launch vehicle.

Abstract: Hydromechanical regulator for controlling the flow of fuel injected into a turbomachine by means of a fuel feed unit (10), comprising a tachometric balance (20) having a beam consisting of two arms (24, 26), which beam can move about a pivot pin (22) under the action of at least a first force F1 applied by a drive rod (18) of the fuel feed unit via a first elastic member (28), and a rod (36) associated with a drive piston (38) for applying, via a second elastic member (40), a force F4 opposing the first force F1 to the beam of the balance so as to cause the fuel feed unit to open further during the transition from a first engine acceleration law to a second engine acceleration law.

Abstract: A method for predicting lean blow-outs (LBOs) in a gas turbine engine includes extracting a plurality of tones in pressure signals representative of pressure within monitored combustor cans, tracking a frequency of a hot tone in each monitored can, and utilizing the extracted tones and the tracked frequency to determine a probability of an LBO.

Abstract: An electric power supply system capable of maintaining stable power generation or the like regardless of variation in the amount of fuel gas being supplied and variation in the gas calorie, comprises a gas engine, a gas turbine, a suction device configured to collect the generating gas, a gas separating device configured to classify the gas collected according to the calorie, a gas calorie adjusting device configured to mix gases having different calories which are supplied from the gas separating device to adjust gas calorie before supplying to the gas engine and the gas turbine, a gas amount balance monitor device configured to monitor balance between the amount of gas being consumed by the gas turbine and the gas engine in operation and the amount of gas being supplied from the gas calorie adjusting device, and a system control device configured to control operation of the gas engine, operation of the gas turbine, and operation of the gas calorie adjusting device.

Abstract: A mapping device maps each burner mode at various bleed settings to generate control schedules for a combustion controller that ensure combustion dynamic (acoustic) pressures, and emissions limits and ring flame temperatures are within operational limits. In general, a method of combustor mapping involves adjusting the bulk ring flame temperature to meet emissions and acoustic requirements. The dome (ring) ring flame temperature is then adjusted to determine maximum and minimum ring flame temperature boundary limits. At both the maximum and minimum ring flame temperatures, the emissions levels and acoustic pressures are checked to see that they are within specification limits. If they are not, the bulk ring flame temperature is adjusted, and the entire process is repeated for that bleed setting and burner mode. If the emissions levels and acoustic pressures are within specification limits, then the power is increased to a different mode and bleed setting combination, and the process is again repeated.

Abstract: A method of monitoring a physical parameter comprises receiving a sensor signal representative of an actual value from each of a plurality of sensors. The method further comprises calculating confidence value for each sensed value and a weighted average of actual values of the sensor signal by weighting each sensed value by the respective confidence value. The weighted average is used to determine a corresponding value of the sensed parameter.

Abstract: In a method for operating a gas turbine centre in the vicinity of the group nominal full-load conditions, the cooling of the working fluid before and/or during the compression is set in such a way that the respectively attainable full-load power is above the current power. Rapid power demands can therefore be rapidly satisfied by an increase in the turbine inlet temperature or by opening an adjustable inlet guide vane row, whereas the control of the cooling effect, which has a tendency to be more sluggish, is employed to adjust the full-load operating point.

Abstract: The present application relates to fuel flow limit calculator (12) for use with a fuel control system (30) of an engine (10) comprising a fuel delivery means (28) and a compressor (16). The fuel control system (12) seeks to control the fuel/air ratio (FAR) near the weak extinction limit of the engine (10) as calculated by the fuel flow limit calculator (12). Both the static (PS3) and total (P3) pressure are measured at the exit of compressor (16). This enables a flow reference value (Q3) to be determined so that the air mass flow (W3) can be calculated and the limiting fuel/air ratio calculated. An advantage of the present invention is that it does not require stable combustion for satisfactory operation and allows the occurrence of preferential extinction within an annular combustor (22) to be beneficially utilised.

Abstract: A low-emission method for producing power using a gas turbine includes premixing a plurality of fuel and air mixtures, injecting the fuel and air mixtures into a combustion chamber using a plurality of fuel nozzles, and adjusting a ratio of fuel and air injected by at least one of the nozzles to control a fuel/air concentration distribution within the combustion chamber.

Abstract: A method of monitoring and controlling the combustion dynamics of a gas turbine engine system is provided. The system includes at least one gas turbine that includes at least one combustor can. The method includes receiving a signal from a gas turbine engine sensor that is indicative of combustion dynamics in at least one of the combustor cans, processing the received signal to determine a probability of lean blowout for at least one combustor can, and controlling the gas turbine engine system to facilitate reducing a probability of a lean blowout (LBO) event using the determined probability of lean blowout.

Abstract: A method of controlling a gas turbine system (10) may include controlling an inlet guide vane position (98) to maintain a turbine (24) exhaust temperature at a corrected value that is a function of a compressor (12) inlet temperature and a turbine (24) normalized load. The method may include selecting the minimum value (138) of a part load tunable value, a part load maximum value and a fixed maximum value of a turbine (24) exhaust temperature for the corrected value. A corrected value setpoint may be determined (94) for the gas turbine system (10) operating at a part load condition where at least one of a fuel flow rate and the inlet guide vane position is controlled (98) so the corrected value does not exceed the corrected value setpoint. The corrected value may prevent a turbine (24) engine from exceeding its firing temperature during operation and ensure the engine operates within combustor dynamics and emissions limits.

Abstract: Sliding-Action Magneto-Mechanical Injector Throttling Device (SLAMMIT) provides on-demand, yet accurate, throttling of the mass flow of the fuel and/or oxidizer into the combustion chamber of a vortex injector. At least two SLAMMIT sub-assemblies comprise the SLAMMIT Device and each sub-assembly is integrated into a manifold and is driven to slide in a given direction by a drive block that is internal to the sub-assembly. The drive block is, in turn, actuated by an electromagnet that is external to the SLAMMIT sub-assembly. As the SLAMMIT sub-assemblies slide, flappers inside the sub-assemblies achieve the effective opening size of the injection orifices anywhere between fully open and fully closed.

Abstract: A method for controlling a combustor of an engine, the combustor having a fuel to oxidant ratio, the fuel to oxidant ratio being defined as a ratio of an amount of fuel supplied to the combustor divided by an amount of oxygen in an oxidant stream supplied to the combustor includes controlling the fuel to oxidant ratio of the combustor as a function of the amount of oxygen in the oxidant stream.

Abstract: Apparatus and method for detecting incipient lean blowoff conditions in a lean premixed combustion nozzle of a gas turbine. A sensor near the flame detects the concentration of hydrocarbon ions and/or electrons produced by combustion and the concentration monitored as a function of time are used to indicate incipient lean blowoff conditions.

Abstract: A turbine inlet temperature operating section (15) determines the turbine inlet temperature T4 based on the flow rate Gf and temperature Tf of fuel being supplied to a combustor (3) and the flow rate G3 and temperature T3 of air. Based on the turbine inlet temperature T4, a pilot ratio operating section (16) sets a pilot ratio, and a bypass valve operating section (17) and an IGV opening operating section (18) generate a bypass valve control signal and an IGV control signal, respectively.

Abstract: A gas turbine engine with a single stage combustor includes an external premixer to provide premixed fuel/compressed air to the combustor as well as compressed air for dilution; and an automatic controller to provide feedback control of the compressed air flow and fuel flow to the premixer in accordance with actual power versus power demand. The fuel/compressed air mixture is combusted in a combustor and the combustion gases and dilution air are expanded in a turbine. The engine further includes a bleed valve under control of the controller for diverting sufficient compressed dilution air past the turbine to induce increased fuel flow and compressed air flow to the premixer for delivery to, and combustion of, the combustor to compensate for the power deficit due to the bled air, to provide selected minimum premixer exit velocities during engine operation.

Abstract: A gas turbine control system is disclosed which operates to stabilize the system frequency in a case of transitional variations of the system frequency without making the strength of hot gas path parts of the gas turbine below a maximum stress value of the hot gas path parts. When a system frequency abnormality is detected, the output of the gas turbine is adjusted to recover the system frequency by making a gas turbine combustion gas temperature control inoperative. For this purpose, there are provided a logical circuit operative to make the gas turbine combustion gas temperature control disabled or inoperative in response to an abnormal system frequency detection signal, and a recovery circuit that operates to cancel the inoperative state of the gas turbine combustion gas temperature control. The detection of an abnormal system frequency may be carried out by an outside signal. An abnormality detection unit may be provided in a combined cycle plant.

Abstract: The present invention relates to a premixed fuel injector for low NOx emission and high heating load combustion. The premixed fuel injector of the present invention comprises a center nozzle and a plurality of outer nozzles arranged around the center nozzle, wherein a distance between the adjacent outer nozzles is 15 to 25 times as large as the diameter of the outer nozzle. Further, an air/fuel mixture is supplied to the outer nozzles and fuel is supplied to the center nozzle at a level of 0.1 to 10% of the total amount of fuel supplied to the outer nozzles. According to the premixed fuel injector for high heating load combustion in which nozzles are arranged as described above, there are various advantages in that it's simple, without additional devices, stable flames can be obtained, and NOx emissions are greatly reduced during combustion.

Abstract: A gas turbo group has a combustion chamber comprising a catalytic burner stage (2), a preburner stage (1) located upstream from the catalytic burner stage, as well as a non-catalytic burner stage (11, 5, 6) located downstream from the catalytic burner stage. The preburner stage serves to always maintain a temperature (T1) at the inlet into the catalytic stage that corresponds at least to a minimum temperature (TMIN) necessary for operating the catalytic burner stage. According to the invention, the gas turbo group is operated so that the burner stage located downstream from the catalytic combustion chamber is taken into operation only when the temperature (T2) at the outlet from the catalytic stage has reached an upper limit in the presence of a maximum combustion air mass flow.

Abstract: A recuperated gas turbine engine system and associated method employing catalytic combustion, wherein the combustor inlet temperature can be controlled to remain above the minimum required catalyst operating temperature at a wide range of operating conditions from full-load to part-load and from hot-day to cold-day conditions. The fuel is passed through the compressor along with the air and a portion of the exhaust gases from the turbine. The recirculated exhaust gas flow rate is controlled to control combustor inlet temperature.

Abstract: A gas turbine apparatus is provided wherein a turbine is driven or rotated by burning a mixture of a fuel and compressed air and supplying a combustion gas generated by the combustion. A flameout determination unit is provided in the apparatus which is adapted to calculate the air/fuel ratio in the air/fuel mixture, correct the calculated air/fuel ratio to calculate a corrected air/fuel ratio which is substantially constant, compare the calculated corrected air/fuel ratio with a predetermined reference air/fuel ratio, and generate a signal indicative of occurrence of a flameout when the corrected air/fuel ratio is smaller than the reference air/fuel ratio.

Abstract: In a gas turbine control apparatus, a frequency analyzing section frequency-analyzes at least one of pressure oscillation in combustors of a gas turbine and acceleration oscillation of each of the combustors and outputs a first frequency analysis result as the result of frequency analysis for a plurality of predetermined frequency bands. A control unit controls at least one of a first fuel flow rate of fuel and a first air flow rate of air based on the first frequency analysis result for the plurality of frequency bands. The fuel and the air are supplied to the gas turbine.

Abstract: A gas turbine control system is disclosed which operates to stabilize the system frequency in a case of transitional variations of the system frequency without making the strength of hot gas path parts of the gas turbine below a maximum stress value of the hot gas path parts. When a system frequency abnormality is detected, the output of the gas turbine is adjusted to recover the system frequency by making a gas turbine combustion gas temperature control inoperative. For this purpose, there are provided a logical circuit operative to make the gas turbine combustion gas temperature control disabled or inoperative in response to an abnormal system frequency detection signal, and a recovery circuit that operates to cancel the inoperative state of the gas turbine combustion gas temperature control. The detection of an abnormal system frequency may be carried out by an outside signal. An abnormality detection unit may be provided in a combined cycle plant.

Abstract: The present invention provides a supercharged open cycle gas turbine engine comprising a core engine for generating shaft power output, a supercharger for increasing the pressure of intake air of the core engine, said supercharger includes a rotary ram-in compressor and a turbine driven by gases discharged from the core engine and having variable-area nozzle assembly; operator controlled means for elective bleeding of variable part of the exhaust gases discharged from the core engine and supplied to the supercharger turbine; at least one pressure sensor for detecting the degree of rise in the pressure of air supplied by the supercharger's compressor; and means for adjusting both the area of the nozzles of the supercharger's turbine and the rate of fuel supply to the core engine according to the detected degree of rise in the pressure of supplied air.

Abstract: The method and apparatus of the present invention discloses a power plant operating at low inlet pressure and temperature using a combination of conventional internal combustion engine techniques and jet engine techniques. The combination of a unique combustion chamber design, a novel variable impedance blade set turbine and a closed loop control system allows a variable resonant frequency for combusted gases. As the resonant frequency is approached a control mechanism uses sensor data to maintain the operating point such that maximum power output is achieved for a given throttle setting. The combination of the unique combustion chamber design, multiple fuel injector/sparking device pairs, finely atomized fuel, excess oxygen and the closed loop control system further provides a very linear power curve with low exit hydrocarbon pollution levels and high fuel efficiency.

Abstract: An aerodynamically stabilized premixing burner includes a swirl generator for the production of a rotating combustion air flow, and a device for the introduction of at least one fuel into this combustion air flow. The burner is advantageously provided with a device for the introduction of an axial air flow into the center of the generated rotational flow. This axial air flow is controllable in order to affect the position and intensity of the flame-stabilizing recirculation zone at the burner mouth.

Abstract: The present invention relates to a system for detecting aerodynamic instabilities in a jet turbine engine having a pressure transducer mounted in the engine. The pressure transducer, welded to a circuit in signal communication with a controller, is adapted to send measured pressure readings from air in a combustion chamber to the controller. The controller, located in spaced apart relation from the engine, is adapted by software to detect pressure patterns from the pressure signals generated by the transducer that are indicative of a stall or surge. A series of fuel and air valves located with compression and combustion chambers of the engine are in signal communication with the controller. The controller in response to detecting pressure signals indicating a stall or surge is operative to signals in the valves to change the air flow, air angle, fuel flow or speed to reduce the possibility of a stall or surge.

Abstract: Disclosed is an engine surge avoidance system and method which adapts the acceleration schedules (i.e., P2.5 bleed valve and NDOT) to prevent engine surge events from occurring while minimizing reductions in engine response time. The surge avoidance system and method disclosed herein achieves this goal by adapting both the NDOT and the P2.5 bleed schedules in an optimum fashion.

Abstract: An operation control apparatus and an operation control method for a single-shaft combined plant are provided. A clutch is engaged and disengaged, whereby a gas turbine (power generator) is connected to and disconnected from a steam turbine. The opening of IGV is controlled by an opening command, the opening of a burner bypass valve is controlled by another opening command, and the openings of fuel flow control valves are controlled by other opening commands found based on a pilot ratio. The commands to the IGV and the burner bypass valve and the pilot ratio are found during an isolated operation in which only the gas turbine is operated, during a joint operation in which the gas turbine and the steam turbine are both operated, during a transition from the isolated operation to the joint operation, and during a transition from the joint operation to the isolated operation.

Abstract: A method of operating a turbine arranged in a compressed air energy storage power generation plant comprises an open-loop control of an air mass flow applied within a lower turbine speed range and a closed-loop control of the turbine speed within a higher turbine speed range. The open-loop control comprises the control of the air mass flow by means of air inlet valves and a free development of the turbine speed. The closed-loop control comprises the control of the turbine speed by means of a speed controller, which is acted upon by a speed limiting value determined according to the current air mass flow and a windage calculation. The speed controller activates a static frequency converter in the case that the turbine speed reaches values that are critical with respect to turbine windage or rotor dynamics.

Abstract: Methods for avoiding surge in a compressor are provided. A representative method includes detecting precursor information of the compressor and controlling the compressor based on the precursor information to avoid a surge condition in the compressor. The control scheme for the method uses a real time observer for on-line identification of magnitude and frequency of dominant precursor waves. The observer outputs feed into a fuzzy logic control scheme, and the identified frequency and amplitude of the precursors are used to actuate devices, such as a bleed valve and/or a fuel valve, for active control of compressor surge. Systems and other methods are provided.

Abstract: The present invention relates to a system for detecting aerodynamic instabilities in a jet turbine engine having a pressure transducer mounted in the engine. The pressure transducer, welded to a circuit in signal communication with a controller, is adapted to send measured pressure readings from air in a combustion chamber to the controller. The controller, located in spaced apart relation from the engine, is adapted by software to detect pressure patterns from the pressure signals generated by the transducer that are indicative of a stall or surge. A series of fuel and air valves located with compression and combustion chambers of the engine are in signal communication with the controller. The controller in response to detecting pressure signals indicating a stall or surge is operative to signals in the valves to change the air flow, air angle, fuel flow or speed to reduce the possibility of a stall or surge.

Abstract: A turbine plant includes a steam turbine, a gas turbine connected to the steam turbine, a generator, and an analyzing apparatus. The steam turbine includes a high pressure steam turbine, an intermediate pressure steam turbine, and a low pressure steam turbine. The turbine plant is adapted to be driven on selected one of natural gas and oil. The analyzing apparatus collects estimates the steam turbine output based on the inlet steam pressure of the intermediate steam turbine with a correction value. The correction value is calculated including the influence of the difference between the gas fuel case and the oil fuel case. The analyzing apparatus estimates a gas turbine output by calculating the difference between the estimated steam turbine output and the total output of the turbine plant. The gas turbine is operated using the estimated gas turbine output.

Abstract: A gas turbine plant for limiting a sudden increase of load of the gas turbine, i.e., of the amount of fuel, and suppressing a stress of the turbine, or for maintaining a suitable fuel-air ratio is disclosed. The plant includes a controller comprising a section for calculating a governor signal for controlling the degree of opening of the fuel valve, based on a revolution speed of the gas turbine; and a section for calculating a load-limiting signal for following the governor signal, wherein when the governor signal decreases, the load-limiting signal is larger than it by a predetermined value, while when the governor signal increases, the increase rate of the load-limiting signal has a predetermined upper limit. The controller also comprises a limiting section, into which both signals are input, for limiting the upper value of the governor signal by using the load-limiting signal as an upper limit.

Abstract: A surge detection system for detecting a surge occurred at a compressor of a gas turbine aeroengine having a turbine connected to the compressor. In the system, the ratio between the compressor outlet pressure and its differential and the differential of the turbine inlet temperature (or the ratio between the turbine inlet temperature and its differential) are calculated. Then, the calculated value are multiplied together and the product is compared with a threshold value. When the product is less than the threshold value, it is determined that a surge occurred at the compressor. With this, a surge occurred at the compressor and a magnitude or degree of the surge occurred may be accurately detected.

Abstract: Methods for avoiding surge in a compressor are provided. A representative method includes detecting precursor information of the compressor and controlling the compressor based on the precursor information to avoid a surge condition in the compressor. The control scheme for the method uses a real time observer for on-line identification of magnitude and frequency of dominant precursor waves. The observer outputs feed into a fuzzy logic control scheme, and the identified frequency and amplitude of the precursors are used to actuate devices, such as a bleed valve and/or a fuel valve, for active control of compressor surge. Systems and other methods are provided.

Abstract: A control method of a gas turbine provided with a plurality of combustors each of which has a first stage combustion part effecting diffusion combustion and a second stage combustion part effecting premixed combustion, comprises: monitoring a quantity of state representative of the combustion condition of the combustor or gas turbine, and regarding the combustion condition as being abnormal combustion when the quantity of state exceeds an allowable value and lowering gas turbine load to a predetermined partial load, thereby to continue the operation.

Abstract: A system and method for modular control of a multi-fuel turbogenerator include separate controllers for controlling fuel supplied to the combustor and power output from the generator. The power controller generates a fuel command based on the required turbine exhaust temperature, where the fuel command is independent of the particular fuel being used. Fuels may include natural gas, diesel, propane, waste gas, or gasoline, for example. The power controller communicates the fuel command and the airflow or calculated air/fuel ratio to the fuel controller which selects an appropriate mode of operation for the injectors. Injector operating modes include one or more pilot modes where fuel is not mixed with air prior to combustion, and one or more premix modes where fuel is highly mixed with air prior to combustion.

Abstract: A system and method for modular control of a multi-fuel turbogenerator include separate controllers for controlling fuel supplied to the combustor and power output from the generator. The power controller generates a fuel command based on the required turbine exhaust temperature, where the fuel command is independent of the particular fuel being used. Fuels may include natural gas, diesel, propane, waste gas, or gasoline, for example. The power controller communicates the fuel command and the airflow or calculated air/fuel ratio to the fuel controller which selects an appropriate mode of operation for the injectors. Injector operating modes include one or more pilot modes where fuel is not mixed with air prior to combustion, and one or more premix modes where fuel is highly mixed with air prior to combustion.

Abstract: A method of operating a gas turbine engine having a compressor, a combustor between a waste fluid compressor and a power turbine, a counter-rotating compressor turbine installed downstream of the power turbine, and a heat exchanger having two circuits, in which a heated fluid is prepared by burning fuel with combustion air in a mixture with a waste fluid obtained downstream of a compressor turbine that which is cooled, compressed and heated before mixing with combustion air while keeping the temperature of the waste fluid downstream of the compressor turbine constant and removing a partial flow of the waste fluid into the atmosphere before heating the waste fluid prior to supplying the waste fluid for mixing with the combustion air.

Abstract: A control method of a gas turbine provided with a plurality of combustors each of which has a first stage combustion part effecting diffusion combustion and a second stage combustion part effecting premixed combustion, includes monitoring a quantity of state representative of the combustion condition of the combustor or gas turbine, and regarding the combustion condition as being abnormal combustion when the quantity of state exceeds an allowable value and lowering gas turbine load to a predetermined partial load, thereby to continue the operation.

Abstract: A combustor for a gas turbine engine uses compressed air to cool a combustor liner and uses at least a portion of the same compressed air for combustion air. A flow diverting mechanism regulates compressed air flow entering a combustion air plenum feeding combustion air to a plurality of fuel nozzles. The flow diverting mechanism adjusts combustion air according to engine loading.

Abstract: A method of determining the concentration of an exhaust component in a gas turbine engine includes measuring the concentration of the selected component at a single location, and using the measured concentration in a simple equation which yields a calculation of concentration in the engine exhaust. Use of this method requires that a measurement be taken for only one of multiple combustors in an engine, but the result is valid for the entire engine. Thus, the method can reduce the cost of design and development of new combustors for gas turbine engines, since it does not require that multiple combustors be built before the engine is tested. The sampling of the component of interest is done at a point sufficiently downstream that the concentration of the component has become relatively stable. The invention also includes an engine having one or more combustors modified to include a probe, and its associate analyzer, at an optimum location.

Abstract: In a method for regulating the power of a turbo set (10) converting thermal power into electric power, said turbo set (10) comprising, on a common shaft (17), a turbine (11) driven by the thermal power and a generator (16) driven by the turbine (11) and delivering electric power (PG) to a network (18), the electric power (PG) delivered by the generator (16) is determined and the thermal power (PT) for the turbine (11) is regulated as a function of the measured electric power (PG). Destabilization of the network and overloading of the turbo set (10) are avoided by additionally determining the kinetic power (Pkin) consumed or delivered by the shaft (17) and by regulating the thermal power (PT) in accordance with the sum of the electric power (PG) and kinetic power (Pkin).

Abstract: A control system for a ducted fan gas turbine engine (10) comprises a control unit (29) that receives input signals from a pressure transducer (27) located within the engine's fan duct (11) downstream of the fan (13) and a rotational speed transducer (32) mounted adjacent the shaft (24) carrying the fan (13). In the event of the control unit (29) detecting a fall in the air pressure downstream of the fan (13) and an increase in fan speed, it commands a temporary reduction in the fuel flow to the engine (10). Such a decrease in the air pressure downstream of the fan (13) and increase in fan speed is indicative of the fan (13) entering a stall condition. The temporary reduction in fuel flow to the engine (10) enables the fan (13) to recover from that stall condition.

Abstract: A system for the destruction of volatile organic compounds while generating power. In a preferred embodiment the system comprises a combustor and a reaction chamber connected to an exit of the combustor. A primary inlet to the combustor supplies a primary fuel to the combustor. A secondary fuel, comprising air and an amount of one or more volatile organic compounds, is supplied to a compressor, which compresses the secondary fuel and directs the secondary fuel to the combustor and the reaction chamber. The system is suitably configured to enable the stoichiometric reaction of the two fuels in a manner sufficient to destroy the volatile organic compounds contained in the secondary fuel and power a turbine engine connected to an exit of the reaction chamber.