Abstract: An embodiment of the present invention may provide a variable speed booster, which receives air from a compressor of a gas turbine through an intercooler, to supply air at a relatively constant pressure to an air processing unit. An embodiment of the present invention may provide an external power source to energize the variable speed booster; which provides air at a relatively constant pressure to an air processing unit.

Abstract: The present invention relates to a flow discharge device (30) for discharging a flow of gas (F) from a first gaseous fluid (A) into a second gaseous fluid (B) which is of a lower pressure than the first gaseous fluid. The discharge device comprises a valve (34) disposed between the first and second gaseous fluids and arranged to regulate the discharge flow (F) and a swirler means (50) disposed between the valve (34) and the second gaseous fluid. The swirler means (50) comprises a plurality of radially extending circumferentially spaced vanes (61, 63, 65). In use the swirler means (50) swirls the discharge flow (F). This acts to reduce the energy, and therefore the pressure of the discharge flow. This results in quieter operation.

Abstract: A method and system for operating a gas turbine engine power system are provided. The system includes a gas turbine engine system that includes a gas turbine engine coupled to an electrical generator through a first shaft wherein the gas turbine engine includes a compressor, a combustion chamber, and a turbine drivingly coupled to the compressor and the electrical generator. The system also includes a variable speed electrical motor coupled to a load through a second shaft and a variable speed drive selectably couplable to the electrical generator during a starting sequence of the gas turbine engine system in a first configuration of the gas turbine engine power system and to the variable speed motor in a second configuration of the gas turbine engine power system.

Abstract: A method of starting up a turbine with a compressor have an inlet guide vane, a number of bleed valves, and a number of blades so as to limit the duration in a rotating stall window. The method may include starting rotation of the blades, increasing the speed of the rotation of the blades, closing one or more bleed valves so as to shift the rotating stall window to a higher rotational speed, partially opening the inlet guide vane to a position outside the rotating stall window, and opening the bleed valves while partially closing the inlet guide vane such that the number of blades pass through the rotating stall window.

Abstract: An apparatus and method for suppressing dynamic instability in a bleed duct of a gas turbine engine includes a fan bypass duct configured to permit a flow of air through the gas turbine engine. The fan bypass duct defines a fan duct surface, and the bleed duct has an inlet in fluid communication with the fan bypass duct and a flow control valve having an opened position and a closed position. A flow diverter is positioned on the fan duct surface proximate the inlet of the bleed duct and diverts the flow of air from the inlet when the flow control valve is closed, while permitting a portion of the flow of air to enter the inlet when the flow control valve is opened.

Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. A first interstage bleed circuit is joined in flow communication between a first preultimate stage of the compressor and hollow blades in the turbine to provide thereto pressurized primary air. A second interstage bleed circuit is joined in flow communication between a second preultimate stage of the compressor and the turbine blades to provide thereto pressurized secondary air at a lower pressure than the primary air.

Abstract: A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compressor and a forward cooling channel in vanes of the nozzle for feeding first cooling holes therein with pressurized primary air at a first pressure. A second bleed circuit is joined in flow communication between an intermediate stage of the compressor and aft cooling channels in the nozzle vanes to feed second cooling holes with pressurized secondary air at a second pressure less than the first pressure.

Abstract: An inlet bleed heat and power augmentation system utilizing a bi-directional and common piping arrangement is disclosed. The piping arrangement includes a plurality of feed tubes arranged to communicate either steam to a compressor discharge plenum or compressed air from the compressor discharge plenum. Various embodiments of the invention are discussed including operation methods.

Abstract: A system is provided for directing air from plural compressor ports to provide cooling and/or sealing air to an associated turbine site. A first flow from a pressure stage of the compressor has a first pressure and temperature. A second flow from another pressure stage of the compressor has a second pressure and temperature. The first and second pressures/temperatures are different. An ejector has two inlets for receiving the first and second flows, and output for combining the first and second flows into a third flow. The pressure and temperature of the third flow are different from the first and second pressures and temperatures. A bypass line is connected between the first flow and the third flow, and provides a bypass flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the pressure and temperature of the bypass flow and the third flow. The mixer comprises inner and outer sections.

Abstract: A technique is provided for operating a gas turbine engine that has a combustor with a primary stage and one or more other stages and a first compressor providing an air flow to the combustor. This technique includes driving a variable load device with the rotating shaft of the gas turbine engine and sensing pressure of the air flow and an engine speed. In response to a decrease in loading of the engine by the variable load device: selectively bleeding the air flow as a function of the engine speed and regulating temperature in the primary stage of the combustor as a function of a ratio between fuel flow provided to primary stage and the pressure to prevent engine flame out. In one form, the combustor is arranged as a dry load emissions type and the variable load device includes an electric power generator.

Abstract: Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine having a compressor section, a combustor section and a turbine section. The combustor section has a lower T_PZ limit and the turbine engine has a design load. The assembly further includes at least one air bleed line from the compressor and at least one valve for controlling air flow through the bleed line. Control structure is provided for opening the valve to allow bleed air to flow through the bleed line when an operating load is less than the design load. The flow rate through the bleed line is increased as the operating load is decreased, reducing the power delivered by the turbine assembly while maintaining the T_PZ above a lower T_PZ limit. A method for operating a turbine engine assembly is also disclosed.

Abstract: A bleed valve assembly for discharging bleed air into a gas turbine engine bypass plenum includes a bleed flow duct, a bleed valve, and a flow deflector. The bleed flow duct is contoured such that it delivers uniformly flowing bleed air to the flow deflector when the bleed valve is in the open position. The flow deflector has a plurality of openings formed therein. Each opening fluidly communicates the bleed air flow passage with the bypass plenum. A portion of the openings are oriented at a discharge angle such that bleed air is discharged from each opening in a direction that does not have a vector component in the direction in which air is flowing in the bypass plenum, and another portion of the openings are oriented to provide stress relief to the deflector.

Abstract: A control apparatus of an extracted air booster system of an integrated gasification combined cycle power plant can additionally serve a sufficient pressure control function and a sufficient antisurge control function. For example, when an inlet guide vane is fully closed or has a small opening degree equal to or smaller than a predetermined opening degree, a second control section of the control apparatus performs pressure control based on a pressure deviation, instead of or as well as antisurge control. In the pressure control, the degree of opening of an antisurge valve is controlled so that a booster outlet pressure detection value can become equal to a set pressure value. In a case where a pressure ratio is larger than a set pressure ratio value, it is also effective that the second control section performs the antisurge control even when the inlet guide vane is fully closed.

Abstract: A method of protecting a turbine compressor of a gas turbine engine that is part of an integrated gasification combined-cycle power generation system that includes an air separation unit that may include the steps of: (1) extracting an amount of compressed air that is compressed by the turbine compressor; (2) supplying the extracted amount of compressed air to the air separation unit; and (3) varying the amount of compressed air extracted from the turbine compressor based upon a desired compressor pressure ratio across the turbine compressor. The method further may include the step of supplying the air separation unit with a supply of compressed air from a main air compressor. The amount of compressed air supplied to the air separation unit by the main air compressor may be varied based upon the amount of compressed air extracted from the turbine compressor.

Abstract: An embodiment of the present invention may provide a variable speed booster, which receives air from a compressor of a gas turbine through an intercooler, to supply air at a relatively constant pressure to an air processing unit. An embodiment of the present invention may provide an external power source to energize the variable speed booster; which provides air at a relatively constant pressure to an air processing unit.

Abstract: A method for performing maintenance on a gas turbine engine assembly includes unplugging a first connector from a first socket, the first connector electrically coupled to the engine control unit, the first socket electrically coupled to the hydromechanical unit, plugging a second connector into the first socket, the second connector electrically coupled to a driver simulator, cranking the engine core to a low speed value, and operating the driver simulator to reposition at least one of the variable stator vane assembly and the variable bypass valve from a first operational position to a second operational position that is different than the first operational position.

Abstract: A bi-modal bleed valve assembly is provided. In one embodiment, the bi-modal bleed valve assembly includes a housing assembly having a bleed inlet, a bleed outlet, a control servo port, and a control chamber therein. A main flow control valve is fluidly coupled to the control chamber and configured to move between an open position and a closed position to regulate fluid flow from the bleed inlet to the bleed outlet. The main flow control valve is configured to move from an open position to a closed position when the pressure within the control chamber surpasses a predetermined threshold. A switching valve is fluidly coupled between the bleed inlet, the servo control port, and the control chamber. The switching valve is configured to route fluid flow into the control chamber from: (i) the bleed inlet in an autonomous mode, and (ii) the servo control port in a servo-controlled mode.

Abstract: An exhaust-side bearing rotatably supports a rotor of a turbine. A seal air-pipe and a first air-supply pipe supply compressed air extracted from a compressor of the turbine to the exhaust-side bearing. A second air-supply pipe supplies compressed air from a supplementary air-source to the exhaust-side bearing. A control apparatus switches between the first air-supply pipe and the second air-supply pipe based on the operation state of the gas turbine.

Abstract: It is known that power is normally extracted within a gas turbine engine from a shaft in order to drive auxiliary devices such as electrical power generators. With high extraction rates from such shafts there is mismatching in rotational speeds between the shafts which must be adjusted through leakage taken from valves 8, 9. By measuring parameters and in particular pressure at a number of positions or parts within an engine arrangement 1 and comparing those parameters either through ratios or directly with reference values a controller can be configured in order to choose the correct sequence and scheduling of the valves 8, 9 opening to balance shaft speed. In such circumstances more efficient operation of the engine arrangement can be achieved over a wider range of engine speeds including idling.

Abstract: A method of controlling a load of a gas turbine engine that is part of an integrated gasification combined-cycle power generation system, which includes an air separation unit, that includes the steps of: (1) extracting an amount of compressed air that is compressed by a turbine compressor; (2) supplying the extracted amount of compressed air to the air separation unit; and (3) varying the amount of compressed air extracted from the turbine compressor based upon a desired load for the gas turbine engine.

Abstract: A bleed duct is configured for bleeding fan air from the fan bypass duct in a turbofan aircraft engine. The bleed duct includes a tubular conduit having an inlet and outlet at opposite ends. The conduit is configured in flow area for recovering pressure from speeding fan air bled therethrough. A shroud extends forwardly from the duct inlet for suppressing dynamic pressure oscillations inside the conduit without degrading the pressure recovery.

Abstract: A simplified air bleed balancing control system for a pair of aircraft gas turbine engines reduces the number of pressure transducers and differential pressure transducers. Advantages include lower weight, less expensive system, better total system MTBF (mean time before failure), acceptable differential pressure transducer drift identification and compensation by the digital controller, and fewer maintenance tasks.

Abstract: A bleed air balancing system includes a plurality of bleed air flow paths (12) each carrying bleed air from one of a plurality of gas turbine engines (10), each bleed air flow path (12) including a flow rate sensor (19), and a circuit (52, 200) outputting at least one flow rate setpoint based on flow rates measured by each of the flow rate sensors (19), wherein each of the plurality of bleed air flow paths (12) includes: a pressure regulating valve (16), a pressure sensor (18), and a controller (20) for controlling the position of the pressure regulating valve (16), the controller (20) including an output (26) connected to the pressure regulating valve (16), a pressure control loop (60) generating a pressure correction signal, and a flow control loop (62) generating a flow correction signal, wherein the controller (20) outputs a control signal (28) on the output (26) based on the pressure correction signal and the flow correction signal. A method of operating the system is also disclosed.

Abstract: A bleed valve assembly for discharging bleed air into a gas turbine engine bypass plenum includes a bleed flow duct, a bleed valve, and a flow deflector. The bleed flow duct is contoured such that it delivers uniformly flowing bleed air to the flow deflector when the bleed valve is in the open position. The flow deflector has a plurality of openings formed therein. Each opening fluidly communicates the bleed air flow passage with the bypass plenum and is oriented at a discharge angle such that bleed air is discharged from each opening in a direction that does not have a vector component in the direction in which air is flowing in the bypass plenum.

Abstract: A bleed valve (30) for a gas turbine engine (10) comprises a diffuser (50), through which heated compressor bleed air flows (54) into a bypass duct (22) air stream (B), has a plurality of small holes (40). The plurality of holes (40) is divided into two or more arrays of holes (52p,q,r), each array of holes (52p,q,r) is angled (?) away from one another so that their respective bleed flows (54p,q,r) do not coalesce. This separation improves mixing with the air stream (B) and helps prevent hot bleed air damaging nacelle and other engine components.

Abstract: A gas turbine includes a compressor, a combustor, a turbine, and a flow path diverting an excess portion of the compressed air produced by the compressor around the turbine. The flow path conducts the excess portion into a turbine exhaust gas flow producing a cooled exhaust gas. A method of operating the gas turbine includes opening an inlet guide vane of the compressor to allow the compressor to produce an increased volume of compressed air. The increased volume exceeds a volume of compressed air needed to support combustion. An excess portion of the compressed air is directed into the exhaust gas to produce a cooled exhaust. In a combined cycle power plant, the cooled exhaust from the gas turbine may be used to warm a steam turbine portion to a desired temperature while allowing operation of the gas turbine at a power level that produces exhaust gas at a temperature higher than the desired temperature.

Abstract: A catalytic gas turbine includes a compressor, a catalytic combustor, a turbine, and a flow path conducting a bypass portion of the compressed air around the combustor and turbine. A method of operating the catalytic gas turbine to activate a catalyst in the catalytic combustor includes opening an inlet guide vane upstream of the compressor to a position to produce an increased volume of compressed air. The increased volume exceeds a volume of compressed air needed to support combustion. A bypass portion of the compressed air is extracted and directed around the combustor and turbine. The method may also include extracting a recirculation portion of the compressed air and directing the recirculation portion into the inlet of the compressor.

Abstract: A multi-position pressurized fluid actuator is mounted for movement in a casing. The actuator includes at least one selectively openable opening at a location corresponding to an intermediate position through which pressurized fluid can be selectively bled from the actuator to permit the actuator to remain in the intermediate position.

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: A system and method for an engine bleed flow-sharing control system is disclosed. For a multi-engine bleed system, one (10) of the engines is selected as the master channel (15) such that the bleed air supply pressure of the control system receiving the bleed air is controlled (11, 12, 13) to achieve a desirable supply pressure range. To slave the other engine airflow control channels (25, 35, 45), the airflow rate (14) is also measured in the master channel (15) and the measured airflow rate is used as the airflow setpoint for other channels (25, 35, 45). The difference between the airflow setpoint and the airflow rate in the other channel is applied to control (21, 31, 41) the pressure or the valve/actuator opening area at the inlet of that channel (25, 35, 45).

Abstract: A method of operating a combustor in a gas turbine that receives combustion air from a compressor includes a) controlling combustion temperature as a function of compressor discharge air bled from the compressor by determining a minimum amount of compressor discharge air required for maintaining a predetermined minimum combustion temperature; and b) bleeding compressor discharge air in excess of the minimum amount from the compressor via a control valve.

Abstract: A pneumatically operated compressor bleed valve communicating between a compressor housing and a bypass duct of a gas turbine engine. The valve has an annular piston slidably mounted within an annular chamber concentric the longitudinal engine axis. An annular valve plug on the piston and an annular valve seat on the compressor housing defining a valve seal interface. A control air pressure conduit communicates between a portion of the annular chamber bounded by the piston and a source of control air pressure. Guide bearings mounted to the periphery of the piston and the housing have a helical guide surface concentric the engine axis.

Abstract: A method for operating a turbine is provided. The method includes supplying working fluid to a first flow path input and routing the fluid through a heating unit coupled in flow communication to the flow path between first flow path input and the turbine. The method also includes extracting a portion of the working fluid from first flow path at a point intermediate the heating unit and an inlet of the turbine. The method further includes re-circulating the extracted fluid through a second flow path such that the extracted fluid is discharged upstream from the heating unit.

Abstract: A bleed valve 60 for regulating a fluid flow through a bleed hole 88 defined by a casing 49 of a gas turbine engine 10 compressor 22, the bleed valve 60 comprises a central axis 92, a piston 62 and a static structure 70, the static structure 70 generally surrounds the piston 62, and is arranged to define in axial sequence from the bleed hole 88 first, second and third chambers 82, 84, 86 respectively, the piston 62 comprises a spindle 66, a first end plate 90 slidably sealed against the static structure 70 and a valve face end plate 64 from which walls 68 axially extend, the walls 68 being slidably sealed to the static structure 70, the static structure 70 comprises a radially inwardly extending flange 74, the flange 74 defining an aperture 76 through which the spindle 66 axially extends and is slidably sealed against, the first chamber 82 is in fluid communication with the compressor 22 via pressure balancing apertures 108 defined in the valve face end plate 64, the third chamber 86 is also in fluid communic

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: An air bleed assembly for extracting air from a flowpath in a gas turbine engine includes a casing for surrounding a row of circumferentially spaced apart rotor blades and defining at least in part the flowpath for receiving air compressed by the rotor blades. The casing includes a bleed port disposed downstream of a row of the blades for receiving a portion of the compressed air as bleed airflow and a bleed duct extending away from the bleed port. The bleed duct has an annular slot in the casing. The annular slot has annular slot leading and trailing edges and an annular bifurcated splitter disposed along at least a portion of the annular slot trailing edge. The bifurcated splitter has an annular leading edge forebody located upstream of and separated from an annular splitter wall by an annular return channel. In one embodiment of the invention, the rotor blades are fan blades and the annular bleed space is in the flowpath in a fan section of the engine.