Abstract: A system and method for adding superheat to the hot process gas at the discharge of a compressor drive turbine of a high compression ratio gas turbine or aviation gas turbine. The superheat brings the temperature ratio (T2/T1) of the power output turbine into equality with the pressure ratio (P2/P1)(K?1)/K to effect a highly efficient and adiabatic isentropic expansion across the power output turbine. The added superheat contributes to the output power of the engine less any inefficiency of the output power turbine. All of the variables are brought together to develop the proper superheat levels for obtaining the greatest power output possible at minimum fuel consumption levels.

Abstract: A turbine engine includes a turbine section having a first turbine portion and a second turbine portion arranged along a central axis. A re-heat combustor is arranged between the first and second turbine portions. The re-heat combustor includes a combustion duct having a curvilinear flow portion. The curvilinear flow portion provides an increased residence time of combustion products passing through the re-heat combustor.

Abstract: A method for operating a gas turbine set comprises the compression of an air mass flow in a compressor, feeding the compressed air mass flow into a first combustion chamber, burning the first mass fuel flow in the first combustion chamber in the compressed mass air flow, expanding the resulting hot gas in the first turbine, feeding the partially expanded hot gas into a second combustion chamber, and burning a second mass fuel flow in the second combustion chamber in the partially expanded hot gas. The method furthermore comprises supplying to the gas turbine set the first mass fuel flow and the second mass fuel flow preferably in a common supply line with a fuel supply pressure, and stipulating division of the total mass flow into a first and second mass fuel flow according to a normal operation concept. When the boundary value of the fuel supply pressure for example in the preferably common supply line is not reached, there is a deviation from the division according to the normal operating concept.

Abstract: In a method for operating a gas turbine (11) in a combined cycle power plant (40), air, which is used to burn a syngas that is recovered from coal, is drawn in and compressed by the gas turbine (11), the compressed air is fed into a combustor (18, 19) and such that a portion of the compressed air is separated into oxygen and nitrogen. An improved degree of efficiency is achieved by this method by virtue of the fact that a gas turbine (11) with reheating and two combustors (18, 19) and two turbines (16,17) is used. In the first combustor (18), syngas is burned using the compressed air, and the resultant hot gases are expanded in the first turbine (16). In the second combustor, syngas is burned using the gases coming from the first turbine (16) and the resultant gases are expanded in the second turbine (17) such that the nitrogen that occurs in the separation of the air is led to the gas turbine (11) to be compressed.

Abstract: In a method for operating a gas turbine (11) in a combined cycle power plant (40), air, which is used to burn a syngas that is recovered from coal is drawn in by the gas turbine (11) and compressed, is led to a combustor (18, 19), and a portion of the compressed air is separated into oxygen and nitrogen. An improved degree of efficiency is achieved by virtue of the fact that a gas turbine (11) with reheating is used, which includes two combustors (18,19) and two turbines (16, 17), in which, in the first combustor (18) syngas is burned using compressed air, and the resultant hot gases are expanded and in which, in the second combustor, syngas is burned using the gases coming from the first turbine (16) and the resultant hot gases are expanded in the second turbine (17), and that the nitrogen that occurs in the separation of the air is used to cool the gas turbine (11).

Abstract: In a method for operating a gas turbine (11) in a combined cycle power plant (40), air is drawn in and compressed though the gas turbine (11), the compressed air is led to a combustor (18, 19) to burn a syngas recovered from a fossil fuel, especially coal, and the gases that result in the course of the combustion are expanded in a downstream turbine (16, 17). In such a method, an improved degree of efficiency is achieved by virtue of the fact that a gas turbine (11) with reheating is used, which includes two combustors (18, 19) and two turbines (16, 17); in the first combustor (18), syngas is burned with the compressed air, and the resultant hot gases, e.g., flue gases, are expanded in the first turbine (16), and in the second combustor syngas is burned by the gases coming from the first turbine (16), and the resultant hot gases are expanded in the second turbine (17).

Abstract: In a gas turbogroup, which comprises a compressor, a first combustion chamber, a first turbine, a second combustion chamber, and a second turbine, the first combustion chamber is arranged downstream of the compressor, the first turbine is arranged downstream of the first combustion chamber, the second combustion chamber is arranged downstream of the first turbine, and the second turbine is arranged downstream of the second combustion chamber, wherein the second combustion chamber has a convectively cooled wall. A cooling air feed line for the second combustion chamber branches from the main flow path of the gas turbogroup downstream of the compressor and upstream of the first combustion chamber. A return line for heated cooling air leads from the second combustion chamber upstream of the first turbine to the main flow path.

Abstract: A bypass channel for use in an inter-turbine transition duct assembly of a turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and at least two injection openings disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference across the high-pressure turbine. The flow out of the at least two injection openings is used to energize the boundary layer flow downstream of the high-pressure turbine in order to allow for the use of a more aggressively expanded inter-turbine duct without boundary layer separation. Methods for optimizing the flow through the turbine engine are also disclosed.

Abstract: A thermal power plant with sequential combustion and reduced CO2 emissions is disclosed, which includes the following components, which are connected in series via in each case at least one flow passage (S): a combustion feed air compressor unit, a first combustion chamber, a high-pressure turbine stage, a second combustion chamber and a low-pressure turbine stage. The second combustion chamber and/or the low-pressure turbine stage can be supplied with a cooling gas stream for cooling purposes. A method for operating a thermal power plant of this type is also disclosed.

Abstract: A turbine engine includes a compressor, a combustor fluidly connected to the compressor and a first turbine operated by a combustion product formed in the first combustor. The turbine engine also includes a reheat chamber in which air, fuel, and exhaust gases from the first turbine are ignited to form a combustion product used to drive a second turbine. The engine further includes a controller that regulates at least one of an amount of fuel and compressed air delivered to the combustor and an amount of fuel, compressed air and exhaust gases delivered to the reheat chamber based on at least one turbine engine parameter measured by a sensor.

Abstract: A flexible method and arrangement provides an effective conversion of energy from any kind of energy sources and/or fuels by combustion and/or gasification, during long-term sustainable economy and environment, by energy conversion in stages. With an open partially circulated condensate system and/or a closed circulation feed water system, stages include first stage of conversion by gasification/combustion, pressurized and/or atmospheric with or without steam- and/or gas-turbines and/or pressurized fuel cell, followed by a second stage of conversion, which second stage utilizing condensation cooling including direct and/or indirect heat transmissions by the first stage produced pressurized mass flow of primary/secondary/residual heat comprising sensible and latent heat, by means of arrangement of expander turbines including counter current fed feed water/condensate fractions during preheating of condensate and feed water respectively before the return to the first stage of conversion.

Abstract: A two-stage power generation system having a compressed air source with two compressed air outlets, one of which provides compressed air to the first stage of power generation and the other of which provides compressed air to the second stage of power generation. All of the fuel for the two-stage power generation system is introduced into the first stage. Exhaust gases from the first stage are introduced into a fuel inlet of the second stage of power generation. The first stage preferably includes a gas turbine operated in partial oxidation mode. The exhaust gases from the partial oxidation gas turbine contain thermal and chemical energy, both of which are used in the second stage.

Abstract: A high energy system comprising a high energy electrical device powered by an electrical generator both of which are cooled by a cryogenic liquid oxidant stored in a storage tank. A power turbine powered by a combustor using fuel and the oxidant drives the electrical generator. A turbopump powered by a portion of exhaust flow from the power turbine pumps the cryogenic liquid oxidant from the storage tank to the generator and the device. In an exemplary embodiment of the system, the electrical device is a directed energy weapon, uses liquid air as the liquid oxidant, and uses a variable geometry turbine nozzle in the power turbine. A reheater may be used between a high pressure turbine and a lower pressure turbine of the power turbine. Compressor bleed from a gas turbine engine may provide air augmentation to the power turbine.

Abstract: The invention relates to an inventive steam power plant comprising at least one steam turbine and a steam generator. According to the invention, a firing device is located downstream of the steam generator and upstream of the steam turbine and/or downstream of a first turbine phase and upstream of a second turbine phase of the stream turbine in the direction of the stream flow and the steam flow can be heated in a combustion chamber of the firing device by being mixed with a heating gas that can be generated in the combustion chamber.

Abstract: A system and method for adding superheat to the hot process gas at the discharge of a compressor drive turbine of a high compression ratio gas turbine or aviation gas turbine. The superheat brings the temperature ratio (T2/T1) of the power output turbine into equality with the pressure ratio (P2/P1)(K?1)/K to effect a highly efficient and adiabatic isentropic expansion across the power output turbine. The added superheat contributes to the output power of the engine less any inefficiency of the output power turbine. All of the variables are brought together to develop the proper superheat levels for obtaining the greatest power output possible at minimum fuel consumption levels.

Abstract: The present invention comprises a highly supercharged, regenerative gas-turbine system. The gas turbine comprises a compressor, a regenerator, a combustor, and an expander. A pre-compressor pressurizes air going into the compressor section of the gas turbine. A cooler lowers the temperature of the air going into the compressor. The compressor pressurizes air, which then flows through the regenerator, which heats the air before it enters the combustor. The combustor further heats the air which then flows through the expander and then the regenerator. A post-expander is preferably located downstream of the regenerator. The post-expander is a second expander that receives high-pressure gas exiting the regenerator. The post-expander preferably drives the pre-compressor. The preferred pre-compressor and post-expander are toroidal intersecting vane machines (TIVMs), which are positive-displacement rotary devices. Numerous alternated embodiments of this basic system are described.

Abstract: An oxygen fired power generation system is disclosed. The power generation system has a high pressure combustor having a water recycle temperature control subassembly, and an intermediate pressure combustor having a CO2 recycle temperature control subassembly. Thus, a first energy cycle utilizes a first energy source operatively associated with a corresponding first heat sink, and a first inert agent to provide energy transfer therebetween and temperature control during operation of the first energy source. In like fashion, a second energy cycle utilizes a second energy source operatively associated with a corresponding second heat sink, and a second inert agent to provide energy transfer therebetween and temperature control during operation of the second energy source. The first and second energy sources are not identical, the first and second heat sinks are not identical and the first and second inert agents are not identical.

Abstract: A reheat heat exchanger is provided particularly for use in Rankine cycle power generation systems. The reheat heat exchanger includes a high pressure path between a high pressure inlet and a high pressure outlet. The reheat heat exchanger also includes a low pressure path between a low pressure inlet and a low pressure outlet. The two paths are in heat transfer relationship. In a typical power generation system utilizing the reheat heat exchanger, the high pressure inlet is located downstream from a source of high temperature high pressure working fluid. An expander is located downstream from the high pressure outlet and upstream from the low pressure inlet. A second expander is typically provided downstream from the low pressure outlet. The reheat heat exchanger beneficially enhances the efficiency of power generation systems, particularly those which utilize expanders having inlet temperatures limited to below that produced by the source of working fluid.

Abstract: A reheat combustion system for a gas turbine comprises a mixing tube adapted to be fed by products of a primary combustion zone of the gas turbine and by fuel injected by a lance; a combustion chamber fed by the said mixing tube; and at least one perforated acoustic screen. The or each said acoustic screen is provided inside the mixing tube or the combustion chamber, at a position where it faces, but is spaced from, a perforated wall thereof. In use, the perforated wall experiences impingement cooling as it admits air into the combustion system for onward passage through the perforations of the said acoustic screen, and the acoustic screen damps acoustic pulsations in the mixing tube and combustion chamber.

Abstract: The invention relates to a method for decreasing the level of carbon dioxide present in the fumes discharged by a power generator burning a mixture of a combustive agent and of a fuel containing hydrocarbons, wherein a gaseous mixture comprising at least part of said combustive agent and at least part of said fumes is compressed, all or part of the carbon dioxide present in the compressed gaseous mixture is eliminated by absorption, a fuel is mixed with the gaseous mixture, the resulting mixture of fuel and gaseous mixture is burnt and the fumes from the combustion process are expanded. The invention also relates to a power generator for implementing said method.

Abstract: A low or no pollution power generation system is provided. The system has an air separator to collect oxygen. A gas generator is provided with inputs for the oxygen and a hydrocarbon fuel. The fuel and oxygen are combusted within the gas generator, forming water and carbon dioxide. Water or other diluents are also delivered into the gas generator to control temperature of the combustion products. The combustion products are then expanded through at least one turbine or other expander to deliver output power. The combustion products are then passed through a separator where the steam is condensed. A portion of the water is discharged and the remainder is routed back to the gas generator as diluent. The carbon dioxide can be conditioned for sequestration. The system can be optimized by adding multiple expanders, reheaters and water diluent preheaters, and by preheating air for an ion transfer membrane oxygen separation.

Abstract: An improved turbine engine topology, wherein the improvement comprises a repositioning, with respect to a conventional intercooled regenerative turbine engine topology, of exhaust gas output from a low pressure turbine stage to a regenerator, to an exhaust gas output from a high pressure turbine stage to the regenerator. The engine topology may additionally employ, as an intermediate stage between the high pressure turbine and the low pressure turbine, a feedback control system, whereby the exhaust gas output from the high pressure turbine stage to the regenerator flows through the feedback control. The engine topology may advantageously also employ an additional cooler and an additional exhaust gas output in the feedback control, whereby exhaust gas flows from the feedback control through the additional cooler to a high pressure compressor stage, or the exhaust gas can flow from the feedback control through a bottoming cycle to the high pressure compressor stage.

Abstract: In a reheat gas turbine engine for power generation, fuel is burnt with compressed air from a compressor in a first or primary combustor, the combustion products are passed through a high pressure turbine, the exhaust of the high pressure turbine is then burnt together with further fuel in a reheat combustor to consume the excess air, and the exhaust of the second combustor is passed through a lower pressure turbine. Excess air is supplied to the first combustor, thereby enabling so-called “lean burn” combustion for production of low levels of pollutants in the exhaust of the engine. Some turbine components of the turbines, e.g., blades or vanes, are cooled by cooling air supplies tapped off from the compressor.

Abstract: A turbo shaft engine for amplifying an air stream flow rate includes a turbine fan assembly and gas generator. The gas generator includes a primary air duct defining intake and outlet ports. 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 primary air duct over a Coanda-profiled guide member 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 fan assembly for amplifying incoming intake flow. The remaining motive flow is again combusted and used to rotate turbine blades. A resonance chamber with volume adjustment is included for tuning a pulse of intake flow into the primary combustion chamber.

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: An oxygen fired power generation system is disclosed. The power generation system has a high pressure combustor having a water recycle temperature control subassembly, and an intermediate pressure combustor having a CO2 recycle temperature control subassembly. Thus, a first energy cycle utilizes a first energy source operatively associated with a corresponding first heat sink, and a first inert agent to provide energy transfer therebetween and temperature control during operation of the first energy source. In like fashion, a second energy cycle utilizes a second energy source operatively associated with a corresponding second heat sink, and a second inert agent to provide energy transfer therebetween and temperature control during operation of the second energy source. The first and second energy sources are not identical, the first and second heat sinks are not identical and the first and second inert agents are not identical.

Abstract: Turbojet powerplant with at least one compressor (1), at least one combustion chamber (2), a high-pressure turbine (3) and a low-pressure turbine (4), characterised in that a heat exchanger (5) is arranged between the compressor (1) and the combustion chamber (2), in that at least one hot-gas line (6) branches off from an area downstream of the high-pressure turbine (3) and is connected to the heat exchanger (5), and in that at least one cold-gas line (7) connects the heat exchanger (5) with an area upstream of the low-pressure turbine (4).

Abstract: The invention relates to a method for starting a power plant (1), in particular a gas storage power plant, with the following steps: S1: ignition of an auxiliary combustion chamber (19), S2: operation of the auxiliary combustion chamber (19) in such a way that the consequently heated gas introduced into a first flow path (13) has a temperature which is below a self-ignition temperature of a fuel/oxidizer/gas mixture delivered to the main combustion chamber (5) for starting the latter, S3: operation of the auxiliary combustion chamber (19) according to step S2, until a recuperator (12) has a predetermined preheating temperature, S4: Starting of a turbine (3) and ignition of the main combustion chamber (5).

Abstract: An installation for generating energy comprises a compressor assembly for compressing air, having a low-pressure compressor, which is connected to a high-pressure compressor via a primary air path. Furthermore, a compressor turbine assembly is provided for the purpose of driving the low-pressure compressor and/or the high-pressure compressor. The installation also has a combustion device for burning a suitable mixture of compressed air and a fuel, and a power turbine with a rotatable shaft for releasing mechanical energy. An exhaust-gas pipe system is connected to the exhaust-gas outlet of the power turbine.

Abstract: There is provided a low-emission, staged-combustion power generation system and associated method for generating power. The power generation system and method combust a carbonaceous fuel with an oxidizing fluid, both of which are substantially free of nitrogen and sulfur, to generate power, for example, in the form of electricity, without the formation of nitrous oxides (NOx) and sulfur oxides (SOx). Efficiency is enhanced using a multi-staged combustion, in which the carbonaceous fuel is partially combusted before passing through a first power take-off device and subsequently reheated and passed through one or more additional power take-off devices. Additionally, exhaust gases from one or more of the power take-off devices can be extracted and processed to provide quantities of useful products such as hydrogen and methanol.

Abstract: A variable cycle gas turbine engine (10) includes first and second compressors (18,16), combustion apparatus (20) and first and second turbines (22,24) operable to drive the first and second compressors (18,16) respectively via interconnecting shafts. The capacity of one of the turbines (24) may be varied, for example by means of guide vanes (32) which can be adjusted to reduce or increase a throat area (40) through which air leaves the guide vanes to impact the turbine. The capacity of the turbine may be increased at low engine speeds, to reduce the pressure ratio across the turbine and across the compressor (16) which it drives, thereby improving the surge margin of the compressor.

Abstract: A gas turbine (5) according to the invention, which comprises a main combustion chamber (10), a cooling system for air cooling of at least the guide vanes (26, 29) and guide rings (28, 38) of various stages (25, 27) of the gas turbine (5), and a main gas passage, also includes a further combustion chamber (34), which is arranged downstream of the main combustion chamber (10) as seen in the hot-gas main direction (H). The cooling air (15) used to cool a stage (25) of the gas turbine which is arranged upstream of the further combustion chamber (34) is fed into this further combustion chamber (34). In this context, it is particularly advantageous for the cooling air (15) used to cool the various stages (25, 27) of the gas turbine (5) to be fed for combustion. This makes it possible, inter alia, to increase the output of the gas turbine (5) without having to increase the supply of fuel.

Abstract: A combustion chamber includes a mixing zone and a combustion zone within which self-ignition of a fuel and air mixture can occur. Fuel and support air are injected laterally at the sidewall of the mixing zone into hot gases passing through the mixing zone. The operating range of the combustion chamber can be increased while noxious substances are reduced by injecting differently controlled fuel/support air mixture jets into different target spaces within the mixing zone.

Abstract: A combustion chamber in a combustion turbine is operated in a fuel rich mode, so that combustion is incomplete in the combustion chamber. Additional air can be added either in the expansion turbine or in additional combustion chambers, with additional combustion taking place either in the expansion turbine or in the additional combustion chambers. The process is better able to maintain a steady temperature throughout the expansion turbines, achieving higher efficiencies and more nearly approximately the more efficient infinite reheat cycle than the simple Brayton cycle. The atmosphere at the exit to the combustion chamber is reducing, rather than the normal oxidizing atmosphere, so oxidation of nitrogen to produce NOx is lessened, and the ability to use other alloys is enhanced. Emissions of CO2, a greenhouse gas, are reduced per unit of power produced.

Abstract: An improved turbine engine topology, wherein the improvement comprises a repositioning, with respect to a conventional intercooled regenerative turbine engine topology, of exhaust gas output from a low pressure turbine stage to a regenerator, to an exhaust gas output from a high pressure turbine stage to the regenerator. The engine topology may additionally employ, as an intermediate stage between the high pressure turbine and the low pressure turbine, a feedback control system, whereby the exhaust gas output from the high pressure turbine stage to the regenerator flows through the feedback control. The engine topology may advantageously also employ an additional cooler and an additional exhaust gas output in the feedback control, whereby exhaust gas flows from the feedback control through the additional cooler to a high pressure compressor stage, or the exhaust gas can flow from the feedback control through a bottoming cycle to the high pressure compressor stage.

Abstract: A multi-spool turbofan engine has a plurality of circumferentially spaced poppet valves with diverters secured thereto for precisely controlling bleed of combustion gas aft of the high pressure turbine whereby the high pressure spool operates at high idle RPM so as to power accessories and the low pressure spool operates at low RPM so as to minimize noise and fuel consumption.

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: A combustion turbine with a secondary combustor is provided. The secondary combustor is disposed within the turbine assembly of the combustion turbine. The secondary combustor assembly is structured to maintain the working gas at a working temperature within the turbine assembly. The secondary combustor assembly re-heats the working gas by injecting a combustible gas into the working gas. The secondary combustor assembly includes a plurality of openings disposed among the vanes and/or blades in the turbine assembly which are coupled to a combustible gas source. As the combustible gas is injected into the working gas, the combustible gas will auto-ignite. That is, the combustible gas will combust without the need for an igniter or pre-existing flame. Combustion of the combustible gas in the turbine assembly re-heats the working gas.

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 the flow of the bleed airflow is imparted with 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 thermal power plant comprises: an air compressor which compresses a sucked air to generate a high pressure air; a gas turbine combustor adapted to supply a fuel to the high pressure air from the air compressor to generate a combustion gas; a high pressure gas turbine adapted to perform an expansion working of the combustion gas from the gas turbine combustor and generate an exhaust gas; a low pressure gas turbine and adapted to perform an expansion working of the exhaust gas from the high pressure gas turbine and generate an exhaust gas containing carbon dioxide; and a carbon dioxide absorbing and discharging equipment located on an outlet side of the low pressure gas turbine, the carbon dioxide absorbing and discharging equipment being provided with a carbon dioxide absorbing and discharging agent having a property of absorbing the carbon dioxide contained in the exhaust gas supplied from the low pressure gas turbine and decomposing the absorbed carbonate by the exhaust gas supplied from the high pressure

Abstract: The aim of the invention is to further improve the closed cycle for generating electric power in such a way that efficiency is enhanced and general pressure and temperature requirements regarding the working fluid used are substantially reduced. The invention also seeks to provide an improved technical solution that meets the requirements of continuos operation at rated output despite fluctuations in load requirements. This is achieved through a multistep steam power operating method for generating electric power in a cycle by using an additional gaseous energy carrier to increase the pressure, the temperature and the volume of the working fluid in the cycle and by recirculating the working fluid in the cycle in such a way that continuously overheated steam is used as a working fluid. The invention can be used in the generation of electric power in a cycle.

Abstract: A combustion turbine with a secondary combustor is provided. The secondary combustor is disposed within the turbine assembly of the combustion turbine. The secondary combustor assembly is structured to maintain the working gas at a working temperature within the turbine assembly. The secondary combustor assembly re-heats the working gas by injecting a combustible gas into the working gas. The secondary combustor assembly includes a plurality of openings disposed among the vanes and/or blades in the turbine assembly which are coupled to a combustible gas source. As the combustible gas is injected into the working gas, the combustible gas will auto-ignite. That is, the combustible gas will combust without the need for an igniter or pre-existing flame. Combustion of the combustible gas in the turbine assembly re-heats the working gas.

Abstract: A gas turbine (5) according to the invention, which comprises a main combustion chamber (10), a cooling system for air cooling of at least the guide vanes (26, 29) and guide rings (28, 38) of various stages (25, 27) of the gas turbine (5), and a main gas passage, also includes a further combustion chamber (34), which is arranged downstream of the main combustion chamber (10) as seen in the hot-gas main direction (H). The cooling air (15) used to cool a stage (25) of the gas turbine which is arranged upstream of the further combustion chamber (34) is fed into this further combustion chamber (34). In this context, it is particularly advantageous for the cooling air (15) used to cool the various stages (25, 27) of the gas turbine (5) to be fed for combustion. This makes it possible, inter alia, to increase the output of the gas turbine (5) without having to increase the supply of fuel.

Abstract: In a reheat gas turbine engine for power generation, fuel is burnt with compressed air from a compressor in a first or primary combustor, the combustion products are passed through a high pressure turbine, the exhaust of the high pressure turbine is then burnt together with further fuel in a reheat combustor to consume the excess air, and the exhaust of the second combustor is passed through a lower pressure turbine. Excess air is supplied to the first combustor, thereby enabling so-called “lean burn” combustion for production of low levels of pollutants in the exhaust of the engine. Some turbine components of the turbines, e.g., blades or vanes, are cooled by cooling air supplies tapped off from the compressor.

Abstract: A thermal power plant comprises: an air compressor which compresses a sucked air to generate a high pressure air; a gas turbine combustor adapted to supply a fuel to the high pressure air from the air compressor to generate a combustion gas; a high pressure gas turbine adapted to perform an expansion working of the combustion gas from the gas turbine combustor and generate an exhaust gas; a low pressure gas turbine and adapted to perform an expansion working of the exhaust gas from the high pressure gas turbine and generate an exhaust gas containing carbon dioxide; and a carbon dioxide absorbing and discharging equipment located on an outlet side of the low pressure gas turbine, the carbon dioxide absorbing and discharging equipment being provided with a carbon dioxide absorbing and discharging agent having a property of absorbing the carbon dioxide contained in the exhaust gas supplied from the low pressure gas turbine and decomposing the absorbed carbonate by the exhaust gas supplied from the high pressure

Abstract: A gas turbo-machine and method of designing and constructing such machine includes preselecting specific operating conditions for the gas turbo-machine, and constructing a master stage as a model to have a given design and geometric shape which results in substantially the optimum efficiency during operation of the master stage at the preselected operating conditions. At least one additional stage is then added to the master stage which is substantially identical to the master stage in geometric shape and design, but in which the linear dimensions of the additional stage differ from those of the master stage in accordance with the formula LT={square root over (DT+L )} where L is the ratio of the linear dimensions of the additional stage to the master stage and D is the gas density ratio of the master stage.

Abstract: An oxygen separator and method for separating oxygen from a heated oxygen containing gas that employs oxygen-selective ceramic membranes of elongated, tubular configuration within a duct for separation of oxygen from a heated gas. The duct can be attached between the exhaust of a gas turbine and a power generator driven by the exhaust or can be connected to one or more burners of a gas turbine. Supplementary compressed feed air may be added at a flow rate at least equal to that of the permeated oxygen for cooling and flow balancing purposes. A purge stream can also be introduced. Additionally, combustor tubes fabricated from an oxygen-selective ceramic membrane material may also be provided to produce combustion products that in turn can be used as a purge for downstream oxygen-selective ceramic membranes.

Abstract: A combustor system for a gas turbine is disclosed in which fuel is mixed with an air stream entering the combustor and is then burned, and the resulting combustion air stream is fed downstream from the combustor to a turbine. A quick and efficient mixing of the air stream and fuel is achieved in that the combustor has an annular diffuser into which the air stream enters. Downstream from the diffuser and communicating with it, at least one essentially annular, toroidal chamber is provided. Mixing pipes extend downstream from the annular, toroidal chamber and are distributed over the periphery of the toroidal chamber. Downstream from the mixing pipes, an annular combustion chamber is provided into which the mixing pipes merge.

Abstract: A system for power generation comprising a turbine system and a power generating system connected to said turbine system, wherein said turbine system comprises: a compressor and inlet means for supplying fluid to said compressor for cooling said oxygen-containing gas; a combustion means; a gas turbine; a recuperator connected with outlet of said compressor means, and the outlet for exhaust gases of said gas turbine means, for mutual heat exchange; means for at least partially condensing water from the exhaust gases from said gas turbine means, said condensing means being connected with said outlet for exhaust gases of said gas turbine and further provided with an outlet for condensate and an outlet for discharging the remaining gas.

Abstract: A gas turbo-machine and method of designing and constructing such machine includes preselecting specific operating conditions for the gas turbo-machine, and constructing a master stage as a model to have a given design and geometric shape which results in substantially the optimum efficiency during operation of the master stage at the preselected operating conditions. At least one additional stage is then added to the master stage which is substantially identical to the master stage in geometric shape and design, but in which the linear dimensions of the additional stage differ from those of the master stage in accordance with the formula L={square root over (D)} where L is the ratio of the linear dimensions of the additional stage to the master stage and D is the gas density ratio of the master stage.