Abstract: A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication with the fan section including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft and interdigitated with the stationary compressor blade row; a core system positioned downstream of the compressor, where the core system further includes an intermediate compressor positioned downstream of and in flow communication with the booster compressor, the intermediate compressor being connected to a second drive shaft, and a combustion system for producing pulses of gas having increased pressure and temperature from a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet; and, a low pressure turbine

Abstract: A supercharging system for gas turbine power plants (11). The system includes a supercharging fan (30, 32) and controller (50) for limiting turbine power output to prevent overload of the generator (28) at lower ambient temperatures. The controller can limit power output by burner control, inlet temperature control, control of supercharging fan pressure and other options. The system can be retrofit on an existing turbine without replacing the generator and associated parts.

Abstract: A rotor for use in turbine applications has a radial compressor/pump having radially disposed spaced apart fins forming passages and a radial turbine having hollow turbine blades interleaved with the fins and through which fluid from the radial compressor/pump flows. The rotor can, in some applications, be used to produce electrical power.

Abstract: In a gas-turbine installation according to the invention there is provided, in order to increase the compressor mass flow, a separate turbo-compressor which is connected in parallel to the compressor of the gas turbine and which is preferably operated by means of an electric motor. By this means, the gas turbine is, at a current ambient temperature, operated with increased power output appropriate to a lower ambient temperature.

Abstract: An energy storage gas-turbine electric power generating system includes a liquid air storage tank for storing liquid air, a vaporizing facility for vaporizing the liquid air stored in the liquid air storage tank, a combustor for generating a combusted gas by combusting the air vaporized by the vaporizing facility and a fuel, a gas turbine driven by the combusted gas generated in the combustor, and a gas-turbine generator connected to the gas turbine for generating electric power. The system further includes a pressurizing unit for pressurizing the liquid air stored in the liquid air storage tank up to a pressure higher than a pressure of air supplied to the combustor to supply the liquid air to the vaporizing facility, an expansion turbine driven by expanding the air vaporized by the vaporizing facility and an expansion-turbine generator connected to the expansion turbine for generating electric power.

Abstract: A gas-turbine supercharging system with improved control. A gas-turbine supercharger that preferably comprises a variable-pitch axial flow fan and a logger supplies, cooled, pressurized air to a gas-turbine power plant. The gas-power plant is preferably a part of combined-cycle power plant that comprises a steam cycle and a duct burner. A controller modulates the output of the fogger and the supercharging fan to maximize the total plant output and provide optimum efficiency without exceeding plant operating limits. The fogger and fan are preferably selected to maximize the allowable output from gas turbine at summer peaking conditions. For the case of a combined-cycle power plant, the preferred mode of operation is to reduce fog output while maintaining a maximum fan pressure as ambient temperature drops below the maximum design value.

Abstract: A gas turbine engine (10) comprises a first compressor (16), a combustor (22) and a first turbine (24) arranged in flow series. The first turbine (24) is arranged to drive the first compressor (16). The first compressor (16) has variable inlet guide vanes (38) and the first turbine (24) has variable inlet guide vanes (42). A second compressor (48) is arranged upstream of the first compressor (16). An auxiliary intake (12) is arranged upstream of the first compressor (16) and downstream of the second compressor (48). A valve (54) is arranged upstream of the first compressor (16) and downstream of the second compressor (48). The valve (54) is movable between a first position in which the second compressor (48) supplies air to the first compressor (16) and a second position in which the second compressor (48) does not supply fluid to the second compressor (16) and the auxiliary intake (12) supplies fluid to the first compressor (16).

Abstract: A gas turbine (1), in particular for model aircraft, model helicopters and other small propulsion units, comprising a drive shaft (3) rotatably mounted by means of two main bearings (13, 13′) and extending through an annular combustion chamber (2) and to which a compressor impeller (4) and a turbine wheel (11) are non-rotationally connected, and a driven shaft (14) driven by said drive shaft (3), wherein a device comprised of front toothed wheels is provided for transmitting the torque from the drive shaft (3) to the driven shaft (14) between the two main bearings (13, 13′).

Abstract: A flow machine is shown with a compressor and at least one turbine, and in which an air intake booster is arranged in an intake duct of the compressor, and an exhaust gas booster is arranged in an exhaust gas duct of the at least one turbine. In operation of the flow machine, the individual booster stages are operated, singly or in combination, in dependence on the specific operating conditions. The flow machine and the associated operating process make possible an economical mode of operation of the flow machine.

Abstract: A gas turbine engine. The engine is based on the use of a gas turbine driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. The supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdyanamic flow path formed between the rim of the rotor, the strakes, and a stationary external housing. Part load efficiency is enhanced by use of a lean pre-mix system, a pre-swirl compressor, and a bypass stream to bleed a portion of the gas after passing through the pre-swirl compressor to the combustion gas outlet. Use of a stationary low NOx combustor provides excellent emissions results.

Abstract: A method in which an air mass flow supplied to a compressor in a power plant is divided in a flow divider into a small partial flow and into a larger partial flow. The smaller partial flow is supplied to an ejector via an air cooler and a booster. The larger partial flow is supplied to the suction line of said ejector. Both partial flows are combined in the ejector. The mass flow which is combined at the outlet of the ejector can be used as pressurized air in various components of a power plant.

Abstract: A multistage compressor assembly containing at least two guided rotor compressor stages, each of which contains an eccentric mounted on a shaft located within a housing, a rotor mounted on the eccentric shaft which contains at least three intersecting faces, a partial bore located at the intersection of adjacent faces, and at least three rollers rotatably mounted within the partial bores of the rotor.

Abstract: A compressor in a multi-stage axial form of construction, with a rotor which is mounted overhung and includes a plurality of moving-blade rings on blade carriers connected to one another, and with a blade arrangement, in which the moving-blade ring of the first stage forms the blade cascade arranged furthest upstream. At least one of the rotating blade carriers is produced in an MMC form of construction, that is to say as a metal component fiber-reinforced at least in regions, and the rotary bearing absorbing the large part of the radial loads occurring on the rotor has a predetermined breaking point which, when a defined radial load is exceeded, allows a radial shift of the rotor, with the result that the latter brushes against the stator.

Abstract: A turbocharger for an internal combustion engine comprises an air intake, a compressor, a compressor housing (2), a plurality of bypass channels (1) formed in the compressor housing (2) providing a short cut to air from the air intake into the turbine, and elements for controlling the extent to which the bypass channels are open, for example by a slidable or rotatable sleeve (5) having a pattern of slots (6) corresponding to the pattern of channels. This results in increased stability and overall efficiency.

Abstract: For supporting the cooling of an air-cooled gas turbine set, it is proposed to arrange, in the cooling air ducts of the cooling system, means for increasing the pressure of the flowing cooling air. In an embodiment, the cooling system (17) is supplied with high pressure compressor air from the end stages of the compressor (1) of a gas turbine set (1, 2, 3, 4). This cooling system branches into a first branch (18), by means of which the combustor (2) and the first stages, particularly the first guide blade row of the turbine (3), are cooled. A second branch (19) conducts cooling air to the further turbine stages. An ejector (20) is provided for increasing, as needed, the pressure drop available by means of the first branch (18) of the cooling system. Its ejector nozzle (22) is supplied with live steam (9) taken from a waste heat steam generator (51), the live steam supply being adjustable by means of an adjusting member (21).

Abstract: A land based gas turbine apparatus includes an integral compressor; a turbine component having a combustor to which air from the integral compressor and fuel are supplied; and a generator operatively connected to the turbine for generating electricity; wherein hot gas path component parts in the turbine component are cooled entirely or at least partially by cooling air or other cooling media supplied by an external compressor. A method is also provided which includes the steps of supplying compressed air to the combustor from the integral compressor; and supplying at least a portion of the cooling air or other cooling media to the hot gas path parts in the turbine component from an external compressor.

Abstract: A gas turbine has a cooling air system supplying air for cooling a high temperature part of the gas turbine and a spray air system supplying air for spraying fuel into a combustor and is formed so that a part of high-pressure air compressed by a gas turbine compressor is used as air of the cooling air system and spray air system, wherein a heat exchanger and a boost compressor are arranged downstream of the outlet of compressed air of the gas turbine compressor, and the boost compressor is composed of a parallel connection of a compressor driven by the turbine shaft and ae compressor driven by a driven source other than the turbine shaft, and pressurized air from the boost compressor is used as air for the cooling air system and the spray air system.

Abstract: A cycle for producing pressurized gas turbine inlet conditions by capturing gas turbine exhaust waste heat, converting the heat into steam energy and applying the steam energy to drive a variable speed, supercharging fan located at the gas turbine inlet. The supercharging fan is used to increase the air mass flow rate into the gas turbine so that the gas turbine shaft horsepower can be augmented. For a simple cycle gas turbine that is not equipped with an exhaust waste heat recovery system, the invention improves the overall cycle efficiency. For combined cycle peaking applications, the variable speed, supercharging fan provides peaking output with an overall peaking efficiency that is better than the combined efficiency of a base load combined cycle plant and a peaking simple cycle plant. The invention can also improve a gas turbine power output response rate.

Abstract: A land based gas turbine plant includes a turbine compressor, a turbine section, and a combustor between the compressor and the turbine section. A heat recovery boiler incorporating at least one heat exchange section is arranged to receive exhaust gas from the turbine section, the heat recovery boiler receiving water passed in heat exchange relationship with the exhaust gas to produce steam. An external compressor supplies augmenting combustion air that is mixed with the steam produced in the heat recovery boiler to produce a mixture of steam and air that is injected into the combustor.

Abstract: A method for equalizing fluid pressure in a primary fluid flow region, comprised of providing a modulating fluid flow region adjacent to the primary flow region and separating the two regions with a perforated wall. By controlling the fluid pressure in the modulating fluid flow region, and permitting fluid to flow between the perforated wall, the fluid pressure in the primary fluid flow region is equalized. The perforations may be formed either in at least one ring about the perimeter of the plenum or at least one row along the longitudinal direction of the plenum. Furthermore, at least one of the perforations may be canted in either the longitudinal or radial directions. This method is important in equalizing the air pressure in a turbine engine air inlet and thereby avoiding aerodynamic distortions in said inlet. Additionally, an apparatus is provided for equalizing the pressure in a primary fluid flow region.

Abstract: An external rotor gas turbine engine to provide direct high speed thrust or to provide rotational shaft work to power electrical generators or aircraft engine fans. To supply compressed air to the rotating inlet of the turbine or combustor, the dynamic compressor has an external rotor journaled onto an internal stator. The entire outside of the engine rotates allowing for a sealless high pressure rotating air source to the exoskeletal turbine. For the prime mover embodiment, the residual kinetic energy from the rotating nozzles may be recovered by an impulse turbine. For the high speed propulsion engine, the impulse turbine is replaces with stator vanes to redirect the momentum in an axial direction.

Abstract: A rotary valve for pulse detonation engines includes a rotor rotatively mounted in the forward end of the pulse detonation tube and a plurality of transfer plenums for receiving fuel and air arranged around the rotor and partially disposed over the forward end of the tube. The rotor has a plurality of internal flow passages formed therein which periodically align with a plurality of inlet ports formed near the forward end of the tube as the rotor rotates. Each one of the transfer plenums is aligned with a corresponding one of the inlet ports so that the flow passages will establish fluid communication between the tube and the transfer plenums when aligned with the inlet ports. Additional features include axial injection of the fuel-air mixture into the pulse detonation tube, pre-compression of the inlet flow and a drive system located outside of the primary gas path.

Abstract: An electric generating system comprised of a micro turbine and a rotary device containing a housing having a curved inner surface with a profile equidistant from a trochoidal curve, an eccentric mounted on a shaft disposed within the housing, a rotor mounted on the eccentric shaft which contains at least three intersecting faces and a partial bore located at the intersection of adjacent faces, and at least three rollers rotatably mounted within the partial bores of the rotor. Heat from the micro turbine is passed to a boiler, wherein it is used to generate heated liquid and/or heated fluid.

Abstract: A process for generating electricity in which a gas/liquid mixture is compressed in a compressor, partially purified in an accumulator/separator, partially purified in a coalescent filter, subjected to pressure regulation, and then fed to a microturbine.

Abstract: A centrifuge compression combustion turbine employing curved radial downward sloping impeller blade compressor fan units, which densify in two stages the air entering the turbine before entering the combustor section, or alternatively when placed within the turbine exhaust air stream, converts the energy in the air exhaust stream leaving into rotational energy.

Abstract: A system for generating electricity containing a power generating device and, operatively connected thereto, a fluid lubricated rotary positive displacement system. The rotary positive displacement system has a feed means for supplying gas at a pressure of from about 0.2 p.s.i.g. to about 400 p.s.i.g. to a rotary positive displacement compressor. The rotary positive displacement compressor has a discharge pressure of from about 20 to about 950 p.s.i.g., a pressure ratio per stage of from about 1.1 to about 6.0, and a flow capacity of from about 5 to about 3,000 standard cubic feet per minute. The system also contains a receiving tank connected to the rotary positive displacement compressor, a device for feeding liquid to the receiving tank, a device for cooling a mixture of gas and liquid, a device for separating a mixture of gas and liquid, and a device for feeding liquid to the rotary positive displacement compressor.

Abstract: A gas turbine engine comprising a compressor, a power turbine, a counter-rotating compressor turbine for powering the compressor and a heat exchanger interconnected among them, uses a mixer to mix waste fluid heated by the heat exchanger with combustion air and feed the mixture to a combustor.

Abstract: A supercharging system for gas turbine power plants. The system includes a supercharging fan and means for limiting turbine power output to prevent overload of the generator at lower ambient temperatures. Possible means for limiting power output include burner control, inlet temperature control, control of supercharging fan pressure, and other options. Supercharging fan pressure can be controlled by staging fans, variable-speed drives, variable-pitch blades, and other options. The invention permits the supercharging system to be retrofit on existing turbines without replacing the generator and associated auxiliary equipment. A novel high-pressure duct design (particularly for use between the supercharging fan and the gas turbine) is also disclosed.

Abstract: A method is provided for equalizing fluid pressure in a primary fluid flow region, comprised of providing a modulating fluid flow region adjacent to the primary flow region and separating the two regions with a perforated wall. By controlling the fluid pressure in the modulating fluid flow region, and permitting fluid to flow between the perforated wall, the fluid pressure in the primary fluid flow region is equalized. The perforations may be formed either in at least one ring about the perimeter of the plenum or at least one row along the longitudinal direction of the plenum. Furthermore, at least one of the perforations may be canted in either the longitudinal or radial directions. This method is important in equalizing the air pressure in a turbine engine air inlet and thereby avoiding aerodynamic distortions in said inlet. Additionally, an apparatus is provided for equalizing the pressure in a primary fluid flow region.

Abstract: According to this process, here is supplied with air, with a variable flow rate, the air distillation unit both by a compression apparatus and by a branch of the output of a compressor that supplies air to the gas turbine unit, and the supply flow rate of the distillation unit is varied by varying the flow rate through this branch.

Abstract: A turbo shaft engine for amplifying an air stream flow rate includes a plurality of blades positioned within a turbine housing for rotation by an intake air flow. A gas generator having a primary air duct defines intake and outlet ports, the intake port receiving the intake flow from the housing. A combustion chamber is connected to the primary air duct for igniting an admixture of fuel and a portion of the intake flow to form an energized motive flow. The motive flow is discharged from the combustion chamber back into the air intake of the primary air duct so as to amplify the flow rate of incoming intake flow by momentum transfer. A portion of the motive flow is returned directly to the housing inlet port for amplifying incoming intake flow. The remaining motive flow is again combusted and used to rotate the turbine blades.

Abstract: In an integrated method of air separation, a plant comprises at least one first air separation unit (1, 101), a first air compressor (13), a first combustion chamber (17), a first expansion turbine (19), a second air compressor (15), a second combustion chamber (23) and a second expansion turbine (25) and a third air compressor (21) in which compressed air is sent from the first air compressor to the first combustion chamber and to the first air separation unit, compressed air is sent from the second air compressor to the second combustion chamber and to the first air separation unit.

Abstract: The present invention relates to a flow machine with a compressor (2) and at least one turbine (5), and in which an air intake booster (3) is arranged in an intake duct (1) of the compressor (2), and an exhaust gas booster (9) is arranged in an exhaust gas duct (8) of the at least one turbine (4) [sic]. In operation of the flow machine, the individual booster stages are operated, singly or in combination, in dependence on the specific operating conditions.

Abstract: Integrated air-separation process and plant, comprising at least two air separation units (1, 101), an air compressor (13), which feeds a combustion chamber and at least one of the air separation units with compressed air, and at least one dedicated air compressor (21, 121) feeding one or both of the air separation units, so that, if both air separation units receive air from the compressor (13), the proportions of air coming from the air compressor are different in the case of the two air separation units.

Abstract: A pneumatic/mechanical actuator described herein consists of a variation of a Brayton-cycle machine for generating actuation force. The system avoids the continues heat problem of a Brayton-cycle by using compressed gas to drive a reversible turbine. The turbine only is driven when a change of actuation position. The system includes an internal-combustion engine-air compressor, a pneumatic energy storage and transfer system, a fuel/air mixing means, two electric pilot valves, two lean-ratio high-pressure catalytic-bed burners, a small-diameter and reversible turbine, a ratio speed-reducing transmission, an optical-encoder feedback position and speed sensor and a ball-screw push-rod mechanism. An alternative embodiment uses a free piston engine compressor hybrid to provide the compressed air. Manual or computer control may be used to monitor and direct desired changes in actuator position.

Abstract: A gas turbine engine comprising a turbine mounted downstream of a compressor and a heat exchanger interconnected between the turbine and compressor and to a heated fluid source, which is connected to a fuel source, has a compressor flow duct having a plurality of flow duct areas, each providing a different compression ratio, and a plurality of outlet taps, each communicating with a respective area of the plurality of flow duct areas, that supplies combustion air to the gas turbine engine flow duct and also controls an outlet tap switch having a plurality of positions for selectively opening to the atmosphere one outlet tap and disconnecting the rest of the outlet taps from the atmosphere in each switch position.

Abstract: A gas turbine has a cooling air system supplying air for cooling a high temperature part of the gas turbine and a spray air system supplying air for spraying fuel into a combustor and is formed so that a part of high-pressure air compressed by a gas turbine compressor is used as air of the cooling air system and spray air system, wherein a heat exchanger and a boost compressor are arranged downstream of the outlet of compressed air of the gas turbine compressor, and the boost compressor is composed of a parallel connection of a compressor driven by the turbine shaft and ae compressor driven by a driven source other than the turbine shaft, and pressurized air from the boost compressor is used as air for the cooling air system and the spray air system.

Abstract: In a system for reusing a thermal energy of an air discharged from a heated air source to heat a combustion air to be supplied into a combustion device so that the combustion air is mixed with a fuel to be combusted in the combustion device, an air feeder sucks the combustion air and feeds the combustion air toward the combustion device, an inlet passage at an upstream side of the air feeder passes the combustion air toward the air feeder, and the inlet passage includes a first inlet port for taking the air from the heated air source through the first inlet port into the inlet passage to incorporate the air to the combustion air and a second inlet port for taking an atmospheric air through the second inlet port into the inlet passage to incorporate the atmospheric air to the combustion air.

Abstract: This invention relates to a bleed valve of a compressor, in particular a compressor of a bypass aero-engine, with a guiding device provided downstream of a valve body in the bleed duct, said guiding device directing the bleed airflow from a compressor duct to a bypass duct in such a manner that the direction of flow of the bleed airflow is imparted a component which is unidirectional with the airflow carried in the bypass duct. The present invention provides a dissipation screen in the bleed duct between the valve body and the guiding device to reduce the energy contained in the bleed airflow, thereby decreasing the loading of the bypass duct. Moreover, the present invention provides for an attenuation chamber downstream of the dissipation screen as viewed in the direction of the bleed airflow.

Abstract: A supercharger for improving performance of a gas-turbine power plant at high ambient temperatures. The supercharger comprises an auxiliary fan that can pressurize air before it enters the gas turbine and means for limiting turbine power output at lower ambient temperatures. The means for limiting turbine power may include control over supercharging pressure, gas-turbine inlet air temperature, or burner exit temperature. The supercharger preferably also comprises cooling means located in the air stream between the auxiliary fan and the inlet to the turbine. The air cooler is preferably a direct evaporative cooler, but could also be an indirect evaporative cooler, a cooling coil with associated mechanical or absorption refrigeration system, etc. The supercharger may also include a bypass damper that allows air to move freely around the auxiliary fan when the fan is not operating. This supercharger is especially suitable for retrofit on existing gas-turbine power plants.

Abstract: A method of operating a combustion turbine power generation system and derivatives thereof. The method provides at least one combustion turbine assembly including a compressor, an expansion turbine operatively associated with the compressor, a generator coupled with the expansion turbine; a combustor feeding the expansion turbine; flow path structure fluidly connecting an outlet of the compressor to an inlet of the combustor; a supplemental compressor structure; connection structure fluidly connecting an outlet of the supplemental compressor structure to a point upstream of the combustor, and valve structure associated with the connection structure to control flow through the connection structure.

Abstract: A centrifuge compression combustion turbine employing curved radial downward sloping impeller blade compressor fan units, which densify in two stages the air entering the turbine before entering the combustor section, or alternatively when placed within the turbine exhaust air stream, converts the energy in the air exhaust stream leaving into rotational energy.

Abstract: A hybrid propulsion system for vehicles having an electronic storage and drive system for driving a vehicle and a thermal engine for charging and energizing the electrical storage and drive system, the thermal engine having a thermal energy source with a compressor and turbine combination operating in a Brayton cycle with the compressor being driven by an electrical motor and the turbine driving a generator, the compressor compressing the motive gas which is thermally heated by the thermal energy source and the heated gas expanding in the turbine.

Abstract: A gas turbine engine includes a rotatable impeller having a plurality of vanes with inlet and outlet ends. A plurality of diffuser channels are spaced apart radially beyond the outlet ends. A movable source of gaseous fuel is positioned adjacent the inlet ends of the vanes. The movable source of gaseous fuel is movable as a function of the rotational speed of the impeller, whereby the flow of gaseous fuel injected from the movable source is ejected from the outlet ends of the vanes into a selected one of the plurality of diffuser channels to facilitate combustion.

Abstract: A method for the separation of a feed gas mixture comprising oxygen and nitrogen in which an oxidant gas and fuel are combusted in a combustion engine to generate shaft work and a hot exhaust gas, the feed gas mixture comprising oxygen and nitrogen is compressed, and the resulting compressed feed gas mixture is separated into two or more product gas streams with differing compositions. The shaft work of the combustion engine is utilized to provide at least a portion of the work required for compressing the feed gas mixture, one of the product gas streams by is heated by indirect heat exchange with the hot exhaust gas from the combustion engine, and the resulting heated product gas is work expanded to generate shaft work and yield an expanded product gas stream. The combustion engine may be a gas turbine combustion engine.

Abstract: A method of operating a combustion turbine power generation system and derivatives thereof. The method provides at least one combustion turbine assembly including a compressor, an expansion turbine operatively associated with the compressor, a generator coupled with the expansion turbine; a combustor feeding the expansion turbine; flow path structure fluidly connecting an outlet of the compressor to an inlet of the combustor; a supplemental compressor structure; connection structure fluidly connecting an outlet of the supplemental compressor structure to a point upstream of the combustor, and valve structure associated with the connection structure to control flow through the connection structure.

Abstract: A gas turbine engine includes a rotatable impeller having a plurality of vanes with inlet and outlet ends. A plurality of diffuser channels are spaced apart radially beyond the outlet ends. A movable source of gaseous fuel is positioned adjacent the inlet ends of the vanes. The movable source of gaseous fuel is movable as a function of the rotational speed of the impeller, whereby the flow of gaseous fuel injected from the movable source is ejected from the outlet ends of the vanes into a selected one of the plurality of diffuser channels to facilitate combustion.

Abstract: A method is provided to ensure that a combustion turbine power generation system may operate at maximum allowable power at elevated ambient temperature and/or at low air density. The method includes providing at least one combustion turbine assembly including a compressor, an expansion turbine operatively associated with the compressor, a generator coupled with the expansion turbine; a combustor feeding the expansion turbine; flow path structure fluidly connecting an outlet of the compressor to an inlet of the combustor.

Abstract: A gas turbine engine that includes a steam driven variable speed booster compressor is described. In one embodiment, the engine includes a low pressure turbine and a booster compressor rotatable on a low pressure shaft. The engine further includes a high pressure compressor, a high pressure combustor, and a high pressure turbine rotatable on a high pressure (HP) shaft and forming the core engine. The output of the low pressure compressor is supplied to an intercooler, and the output of the intercooler is supplied to the high pressure compressor. The engine further includes a power turbine downstream of the high pressure turbine, and the power turbine is coupled to a generator by a shaft. The output exhaust of the power turbine is supplied to an exhaust heat boiler, and steam output by the boiler is supplied to, and drives, the low pressure turbine. Steam from the boiler may also be supplied to the high pressure combustor and to the power turbine.

Abstract: A gas turbine and a method for combustion of a fuel in a gas turbine, conduct a flow of compressed air through the gas turbine from a compressor section to a turbine section. The fuel is fed to the flow in the compressor section and is burnt in the flow between the compressor section and the turbine section. The flow is subjected to a spin with a speed component at right angles to a movement direction of the flow when the flow emerges from the compressor section. The combustion of the fuel increases the speed component in the movement direction of the flow, causing the speed of the flow entering the turbine section to correspond to a value predetermined by the geometry of the turbine section.