Abstract: A method for forming a thermal barrier coating on a combustor panel or a fuel nozzle comprises the steps of: providing a component selected from the group consisting of a combustor panel, a bulkhead heat shield, and a fuel nozzle; optionally depositing a first layer of a metallic alloy onto the component; and depositing a ceramic composition layer using an electron beam physical vapor deposition technique. If the component is formed from a yttrium or other active element doped single crystal superalloy, the first layer may be omitted and the ceramic composition layer may be deposited directly onto a surface of the component.

Abstract: A burner including a pressure measurement device for pressure measurement in a combustion medium inside a gas turbine is provided. The burner supplies the combustion medium in an uncombusted state to a combustion chamber of the gas turbine. The pressure measurement device includes a measuring point defining the location of the pressure measurement, wherein the measuring point is located inside the burner of the gas turbine. In addition, a gas turbine including a burner and a method for controlling a fuel supply to a burner are provided.

Abstract: A device comprising a combustion toroid for receiving combustion-induced centrifugal forces therein to continuously combust fluids located therein and an outlet for exhaust from said combustion toroid.

Abstract: A sliding surface of a high-temperature portion is subjected to an electro-discharge surface treatment with one or both of a high-temperature hard material (4) and a material having a lubricating property at a high temperature (6). The high-temperature hard material (4) is any or a mixture of cBN, TiC, TiN, TiAlN, TiB2, WC, Cr3C2, SiC, ZrC, VC, B4C, Si3N4, ZrO2, and Al2O3. The material having the lubricating property at the high temperature (6) contains chromium and/or chromium oxide (Cr2O3) and/or hexaboron nitride (hBN). An electrode formed by compression molding of the high-temperature hard material, and the high-temperature lubricating material containing at least one of Cr and hBN and having the lubricating property at the high temperature is used as the electrode for the electro-discharge surface treatment.

Abstract: A method for operating a power plant (2), which includes at least one compressor (3), at least one turbine (4), and a burner arrangement (5), involves, to enhance the power plant (2), feeding a combustion exhaust gas from a pre-burner (8) of the burner arrangement (5) to an oxygen-removal device (11), which removes gas of the oxygen from the combustion exhaust gas in which it is contained.

Abstract: A system involving a two-step gasification of a carbonaceous source to produce bulk hydrogen that avoids the early formation of CO2 and obviates the traditional water gas shift (WGSR) step, carbochlorination of a metallic ore the production of metals found in the ore that utilizes carbon monoxide as an oxygen sink, rather than the traditional coke, and carbon oxides management that eliminates major impediments to emission-neutral power generation and the reduction of major metals. The gasification uses a rotary kiln reactor and gas-gas cyclonic separation process to separate synthesis gas into purified hydrogen and purified carbon monoxide. Purified bulk carbon monoxide issued in metallurgical reduction, and purified bulk hydrogen as fuel for an emission-neutral hydrogen combined cycle (HCC) turbine power generation station.

Abstract: A process of coating an article includes the steps of (1) applying a ceramic compound to at least one surface of an article to form a layer of ceramic compound; (2) applying at least one inert compound upon the ceramic compound layer to form a protective layer, wherein the at least one inert compound is composed of a first inert compound having a cubic crystalline structure of formula (I) A3B2X3O12, or a second inert compound comprising a hexagonal crystalline structure of formula (II) A4B6X6O26, or a mixture of the first inert compound and the second inert compound; (3) optionally drying the coated article; (4) optionally repeating steps (2) and (3); and (5) heat treating the coated article.

Abstract: A twin-shaft gas turbine 1, which has a gas generator 2 including a compressor 7, a combustor 8, and a high-pressure turbine 9, is configured to make a first control mode and a second control mode selectively usable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.

Abstract: Disclosed is a gas turbine for a thermal power plant, especially a gas turbine, comprising a rotatable rotor and a duct which can be penetrated by a gas and in which turbine blades for driving the rotor are disposed. The inventive gas turbine is characterized by a blocking device which at least partially prevents the gas from penetrating the duct in a closed position.

Abstract: A combustor arrangement for a gas turbine engine (31) has a split line (42) and a plurality of burners (20,37) arranged in an annular ring (40). The burners (46) of the combustor on either side of the split line (42) have a separation distance of at least two times the average separation distance between burners (48) distant from the split line (42).

Abstract: A mixing chamber with a wall and at least one vortex generating element arranged on the wall is provided. The vortex generating element has at least three surfaces, at least one of the surfaces forming a top surface and the other surfaces forming at least first and second side surfaces, the first and second side surfaces arranged not in parallel, the top surface being in contact with the wall via a front edge of the top surface, the front edge extending traverse to a flow direction, the top surface further abutting the first and second side faces forming first and second edges, the first side surface extending in parallel to the flow direction so that the first edge does not contribute to generating a vortex, and the second side surface extending not in parallel to the flow direction so that the second edge contributes to generating the vortex.

Abstract: A compact, single shaft gas turbine gas generator uses a high pressure ratio dual-entry single stage centrifugal compressor, can combustors, and a radial inflow turbine with the compressor configured to achieve an overall pressure ratio of about 12:1 or greater and Mach Numbers less than or equal to about 1.4. The radial inflow turbine is configured to provide an expansion ratio of about 4:1 to about 5:1, to provide partially expanded combustion gases to a free-power turbine or an expansion nozzle, in a work-producing engine configuration. A ball bearing assembly in front of the compressor is used in conjunction with a thrust piston assembly to take up turbine thrust load, while a radial tilt pad bearing assembly is used in front of the turbine. A collector with scroll-shaped sector portions collects compressed air from an annular vaned diffuser, and respective crossover ducts channel the collected diffused compressed air from each sector portion to a plenum feeding can combustors.

Abstract: There is described a gas turbine with a channel wall that limits a flow, said channel wall comprising first and second wall sections, one of the wall sections being part of a combustion chamber of the gas turbine and the other wall section being part of an annular hot gas channel of a turbine unit, and the two adjacent wall sections facing each other with a gap there between. In order to reduce the leakage quantities of blocking gas that protect the gap from the entry of hot gas, it is proposed that blocking element projects from the side of the first wall section into the gap and can be displaced transversely thereto, said blocking element comprising a piston face disposed in the first wall section and a sealing structure lying opposite the piston face, it being possible to press said sealing means against an end sealing section of the second wall section by means of a pressure medium that acts on the piston face.

Abstract: A building having an energy conversion apparatus and method for distributed energy systems using recovered energy of stationary structure wind resistance and solar radiation in conjunction with normal and off-peak operation of a gas turbine engine. The energy sources are combined, as available, for electric generation and to drive an air liquefier. Liquid air compression and pre-compression cooling of an atmospheric air portion of engine working fluid reduces compression work while increasing engine efficiency. The liquefied air is stored and transferred between buildings and between buildings and vehicles, as required.

Abstract: Apparatus for protecting a feed injector and methods of assembly are provided. In one aspect, a method of assembling a feed injector cooling apparatus includes coupling a coolant source in flow communication with a mounting flange, coupling the mounting flange to a first end of a sheath, wherein the sheath circumscribes a feed injector barrel, and coupling a cap to a second end of the sheath, wherein the cap includes a center port through which a feed injector tip projects into a gasifier.

Abstract: An auxiliary electrical power supply includes a fuel combustor passively sourced with fuel for combusting fuel and a thermoelectric generator close-coupled to the combustor for converting the heat from the combustor to electric power.

Abstract: The present invention relates to a baffle (10) for the bottom of a combustion chamber of a gas turbine engine, comprising a flat portion of wall (10a) with an opening for an injector of the combustion chamber to pass through, two longitudinal edges (10c, 10d) for the assembly to two adjacent baffles and two transverse edges (10e, 10f), wherein at least one of the edges comprises a joint cover (10d1) arranging a housing (10d10) along said edge for an edge (10?c) of an adjacent baffle (10?) so as to seal the junction between the two edges. The invention also relates to a combustion chamber incorporating said baffles.

Abstract: An energy recovery system for a process means (100) comprises a compressor (1), a turbine (2) and a generator (4) being arranged to be driven by a main shaft (3). It also comprises a heat exchanger (5) on a first side being fluidly arranged between the compressor (1) and the turbine (2) and on a second side being fluidly arranged downstream of a process means (100). Heat emanating from exhausts of said process means (100) is transferred to an airflow of the compressor turbine (1, 2) assembly, which airflow is expanded in the turbine (2) which then powers the compressor (1) and the generator (4). Energy is thus recovered from the process, which energy is transformed into electricity so that the overall efficiency of the process is increased.

Abstract: A combined-cycle power plant, a steam thermal power plant, and a method for operating the power plant, which are capable of effectively utilizing raw fuel produced from medium- or small-scaled gas fields and oil fields. Raw fuel produced from a gas field is separated into a gas component and a liquid component by a separator. The gas component is burnt in a combustor of a gas turbine, and resulting motive power is converted to electricity by a power generator. The liquid component separated by the separator is burnt in a steam generator to generate steam that is supplied to a steam turbine. Resulting motive power of the steam turbine is converted to electricity by a power generator. Since the electricity generated by the power generators is AC power, the AC power is converted by a converter to DC power that is transferred from the vicinity of the gas field to a consuming area via a cable.

Abstract: By using a plug to charge a medium-sized battery of the most up-to-date technology, the Rabbat PLUG-IN ENGINE benefits from the most up-to-date and most economical available grid supply at any point in time, to start the engine. The Direct Current from the battery sequentially activates an Ultrasound Transducer. The ultrasound waves break down physically electrolyte water into H and OH. The electrolyte carrying H or OH according to whether it is the cathode or the anode, is absorbed into a microfiber substance. The microfiber contains a wire-grid electrode, either anode or cathode. The electrolytic process finally breaks down chemically the partially ionized electrolyte into Hydrogen and Oxygen making use of the H and OH produced by sonic waves The Oxygen produced is passed through an Ionizer. Ionized ambient air, ionized Oxygen, and Hydrogen are injected into and piezzoelectrically sparked in the combustion chamber of a special cored type of gas turbine.

Abstract: The invention relates to an arrangement for a turbomachine combustion chamber, the arrangement comprising a chamber end wall pierced by at least one opening, an injector system, and a deflector mounted on the downstream side of the chamber end wall in the opening by means of an annulus, said injector system including a pinch ring mounted on the upstream side and fastened against the annulus with the pinch ring and the annulus together defining a groove, and a bowl mounted in the opening, the bowl being made up of at least two distinct parts, at least a first part forming an end plate suitable for sliding radially in the groove, and a second part forming a bowl collar that is provided with a collar extending parallel to the chamber end wall on its downstream side, said first and second bowl parts being fastened together by means of a twist-lock coupling.

Abstract: A process is disclosed that uses fired heater having two types of burners. The first burner is located in a duct which provides oxygen-containing gas to the heater to be combusted with the fuel provided by the burner. The second burner is located in the heater and provides both air and fuel for combustion. The heater may be located downstream of a gas turbine engine that cogenerates electricity and provides the oxygen-containing gas. The second burners are operated at a low flow rate until the flow rate of oxygen-containing gas through the duct is diminished, in which case the flow rate to the second burners is increased.

Abstract: The combustion chamber (10) comprises a chamber endwall (16) which takes the form of a substantially frustoconical component consisting of a succession of adjacent planar portions (166). The invention can be applied to a combustion chamber (10) of a turbine engine (2).

Abstract: A power generation system (10) and method of operating a power generation system (10). An exemplary power generation system (10) shown in FIG. 1 includes a gasification system (2) for generating a supply (33) of a first gas comprising hydrogen and a supply (39) of a second gas comprising carbon monoxide based on a chemical breakdown of hydrocarbons in a melt (17). A component system (3) produces a supply of steam (99) by reacting one of the streams of gas and a steam turbine (120) generates mechanical power by expanding the steam (99). In an associated method, a melt (17) is created in a gasifier (12) which then receives a hydrocarbon source (22) to generate a continuous supply (33) of a first gas comprising hydrogen while increasing concentration of dissolved carbon in the melt (17). Hydrogen present in the first gas is supplied to a first combustor (90). A continuous supply (39) of a second gas comprising carbon monoxide is generated with carbon present in the melt (17).

Abstract: A system to utilize exhaust generated by a fuel consuming device including a plenum situated to receive the exhaust from the fuel consuming device and a stack in fluid communication with the plenum. The stack is adapted to allow the exhaust to exit the plenum in one instance and ambient air to enter the plenum in another instance. The system also includes a thermal device adapted to draw a fluid flow from the plenum for operation of the thermal device. The fluid flow includes at least one of the exhaust from the fuel consuming device and the ambient air.

Abstract: The invention is about a submerged combustion method and the device; in details, it is a submerged combustion method and the device utilizing turbine heat engine principle. In the invention, turbine power combustion means is used and substituted conventional submerged combustion system that must equip air blowing means. The high temperature gases generated from the combustion within the turbine power combustion means will do works on turbine, which will drive the air compressor means of the turbine power combustion means to induce air for combustion, and will drive the second-time complete combustion of high temperature gases and the complement fuel, and then the gases will come out from water bottom against tank water pressure and carry out heat interchange with tank water. The turbine submerged combustion boiler device of the invention need not equip air blowing means additionally which would consume energy. So it has high energy efficiency and a simple system structure.

Abstract: A combustion chamber 10 for a gas turbine operates in a highly diluted mode of combustion has a substantially toroidal plenum 30. At least one combustion fluid injector is located at the periphery of the plenum. The shape of the plenum and the disposition of the combustion fuel injectors are such that a vortex flow 2 is established in the combustion chamber in use. Gasses are entrained in the vortex which provides high enough levels of the gas re-circulation to allow for the onset of highly diluted combustion.

Abstract: An improved chemical mixing micro-device with features on the micro- and nano-scale. The micro-device is comprised of at least one chemical inlet port and one chemical outlet port, a micro-evaporator, a micro-chamber and a micro-initiator. Also, a method of mixing at least one chemical in an evaporative mixing and/or reacting chamber is disclosed.

Abstract: The invention pertains to a seal element for sealing a gap, in particular within a turbo-machinery, between a first component and a second components spaced apart from each other, said first component having a first surface and said second component having an opposing second surfaces. The seal element comprises a support structure and a sealing structure covering at least partially said support structure. The support structure comprises at least two contacting members, each contacting member serves for putting a portion of the sealing structure in contact with one of the surfaces and being capable of following a deformation of said surface. The invention further pertains to a combustion turbine, wherein a gap is formed between a first surface and a second surface, which gap is sealed off by said seal element.

Abstract: The present invention provides an apparatus and method for reducing the pressure loss of air prior to entering a combustion system, such that, for a known combustion system having a predetermined pressure loss, the resulting fluid entering the turbine has a higher supply pressure that will result in more efficient turbine and increased engine output. Significant enhancements include the addition of a plurality of deflector assemblies to direct the air from a compressor outlet towards an exposed single-wall transition duct to provide direct cooling to a first panel of the transition duct.

Abstract: A method enables a gas turbine engine to be assembled. The method includes providing a combustor including a liner that defines a combustion chamber therein, and coupling a casing within the gas turbine engine to extend circumferentially around the combustor liner, wherein the casing includes an inlet and a scroll duct that is coupled in flow communication to the inlet and extends at least partially circumferentially around the liner. The method also includes coupling the inlet in flow communication with a feed air source.

Abstract: A conical helical design for a turbine combustor scroll utilizes as much cavity of the combustor housing as possible by adding an axial shift and an irregular cross sectional shape in the scroll without adversely effecting aerodynamic performance. The axial shift region of the combustor scroll extends the cross-sectional area centroid of the scroll beyond the scroll's discharge area B-width. The resulting scroll design allows for the use of a high performance engine with a larger combustor while reducing the weight of the system by making the combustor housing as small as possible. Furthermore, the scroll design increases the air velocity for convection cooling by reducing the gap between the scroll and the housing. The turbine scroll of the present invention is useful in engines for which high performance is required, such as certain high performance aircraft.

Abstract: A turbine engine combustor member, for example a deflector including an inner surface at a combustor interior and an outer surface away from such interior includes a body of a high temperature alloy having properties combining resistance to hot corrosion in March=1 flows and oxidation to avoid coating the outer surface. In one embodiment, the inner surface includes an environmental resistant coating comprising a ceramic-base thermal barrier coating. In some forms such coating includes an inner coating including Al under the ceramic-base coating. In another embodiment, the member includes air cooling passages and is substantially uncoated. Provision of such a member enables complete combustor assembly including a plurality of members and then coating all inner surfaces concurrently rather than individually before assembly.

Abstract: A gas turbine engine combustor (26) including a primary combustion chamber (28), a mixer element (34), a mixing chamber (46) and a secondary combustion chamber (48). The primary combustion chamber receives a fuel oxidizer mixture flow (22) and discharges a partially oxidized mixture flow (32). The mixer element includes a plurality of flow channels (36, 38) for separating the partially oxidized mixture from a flow of an oxidizer (24) and producing a plurality of partially oxidized mixture flows interspersed with a plurality of oxidizer fluid flows. The mixer element may include a plurality of tubes (62) retained by an upstream tubesheet (70) and a downstream tubesheet (76). The mixer element may function as a heat exchanger to heat the oxidizer fluid flow and to cool the partially oxidized mixture flow upstream of the post-mixing chamber.

Abstract: An expansion turbine stage for compressed gases has a housing and a turbine rotor. The housing has flow guide channels for feeding the compressed gas to the turbine rotor. The turbine rotor, which is over-mounted and has centripetal flow through it, is followed by an out-flow diffuser enclosed by the housing, to delay the cold expanded gas. The out-flow diffuser is arranged in a holder bore in the housing, as a separate component. For thermal insulation of the housing relative to the cold expanded gas stream, the out-flow diffuser is made of a non-metallic material having a low heat conductivity.

Abstract: In order to develop a combustion chamber with a closed cooling system for a turbine with an inner wall and an outer wall (1) bounding the combustion area, wherein there is an intermediate space between the inner wall and the outer wall (1) through which cooling fluid can flow, and which comprises a cooling fluid feed system opening out into the intermediate space and a cooling fluid discharge system for discharging the cooling fluid from the intermediate space, so that it has a reduced extension in the radial direction, it is proposed with the invention that the cooling fluid discharge system should comprise channel-type drainage structures (8) running essentially along the axial orientation of the combustion chamber, which are interrupted by inlet structures (4) of the cooling fluid feed system arranged between the drainage structures (8).

Abstract: An apparatus for vaporizing liquefied natural gas (LNG) is disclosed. The apparatus comprises an LNG side with a plurality of heat transfer circuits and a heating medium side with a plurality of passages within a trough like containment. The vaporizer is designed for high heat transfer rates and reduced thermal stresses. The vaporizer can be brought on line quickly, and can utilize sea water and other fluids as the heating medium.

Abstract: A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and relative to the turbine scroll. The pivoting liner has the ability to control and minimize air leakage from part to part, for example, from the liner to the turbine scroll and liner to the surrounding structures, during various operating conditions. Additionally, the liner provides for easy assembly with no flow path steps. Finally, the pivoting liner tolerates thermal and mechanical stresses and minimizes thermal wear.

Abstract: A premixer for a combustor to entrain a selected volume of fuel in an oxidizer to be combusted to heat the oxidizer. The combustor is for a gas powered turbine which employs the hypergolic or high energy air stream which will allow a fuel to be combusted in the absence of an additional ignition source. A heat exchanger and a catalyst combusts a first portion of fuel in air without the production of undesired chemical species. The catalyst is employed to lower the combustion temperature of the fuel to substantially eliminate selected chemical species. The fuel premixed in the air then encounters the catalyst and the fuel is combusted to increase the temperature of the air to an auto-ignition temperature so that no other ignition source is needed to combust additional fuel added later.

Abstract: A counter-flow system for use in a turbine for selecting various mixtures of fluids for use with the system. The system may be used for a combustor for a gas powered turbine which employs a heat exchanger to combust a fuel without the emission of undesired chemical species. A gas powered turbine requires expanding gases to power the turbine blades. Fuel is combusted to produce the required gases. An oxidizer is introduced into the counter-flow system in a first direction before a first portion of fuel is introduced into the oxidizer. The fuel and oxidizer mixture is then flowed through a second pathway wherein the fuel and oxidizer mixture obtains a selected amount of thermal energy. Moreover, in a second pathway an equivalence ratio of the fuel and oxidizer mixture may be altered from the original fuel and oxidizer mixture.

Abstract: A flow control device for a combustor is provided in which the flow control device comprises a shroud having a first end and a second end wherein the second end is coupled to the combustor. The shroud is disposed to receive a primary fluid and disposed to direct the primary fluid into the combustor. In addition, the shroud further comprises a plurality of ports disposed therein wherein the ports are oriented to extract a portion of a flow from a flow path of the primary fluid so as to control a flow rate of the primary fluid through the shroud.

Abstract: A combustion chamber 10 for a gas turbine operates in a highly diluted mode of combustion has a substantially toroidal plenum 30. At least one combustion fluid injector is located at the periphery of the plenum. The shape of the plenum and the disposition of the combustion fuel injectors are such that a vortex flow 2 is established in the combustion chamber in use. Gasses are entrained in the vortex which provides high enough levels of the gas re-circulation to allow for the onset of highly diluted combustion.

Abstract: A method comprising providing a combustion apparatus, introducing a fuel into the combustion apparatus, and introducing feed air into the combustion apparatus. The method further comprises using the combustion apparatus to cause at least some of the fuel and at least some of the feed air to swirl within the combustion region and about a longitudinal axis of the combustion apparatus, and causing an initial combustion reaction of some of the swirling fuel and feed air in the combustion region to form combustion reaction products. Some of the swirling fuel at least temporarily remains unburned. The swirling is sufficient to cause the unburned fuel to move radially away from the longitudinal axis and to cause the combustion reaction products to move radially toward the longitudinal axis.

Abstract: The invention describes a premix burner, in which fuel and air can be mixed to form a fuel/air mixture, for forming at least one stable flame front within a downstream combustion chamber for driving a gas turbine which follows the combustion chamber, having a premix burner casing which is formed in the manner of a tube open at the upstream end, is connected in the downstream direction to the combustion chamber via a transition contour and through which air can flow, a burner lance, which is designed as an inner tube, projects into the interior of the premix burner casing on the upstream side, encloses a flow passage which is annular in cross section together with the premix burner casing, and has an inner tube wall which surrounds an inner flow passage and in which there is at least one fuel-addition unit for feeding fuel into the inner flow passage and at least one further fuel-addition unit for feeding fuel into the annular flow passage is provided in such a manner that downstream of the inner tube the fuel

Abstract: A combustor can simultaneously reduce the amount of NOx exhaust and combustion oscillation. The combustor has an internal cylinder which accommodates a premixing nozzle and an external cylinder which accommodates the internal cylinder, and includes an air flow passage which supplies air from a compressor to the premixing nozzle. The air flow passage is provided with a punched metal plate near the maximum velocity fluctuation position whereat the velocity fluctuation of the air flow increases to a maximum.

Abstract: A set amount of fluid can be constantly supplied to an actuator and a flow-back of fluid from the actuator can be prevented, even in case of developing variations of a load pressure of the actuator and a pressure of a hydraulic pump, and provided is a control valve for controlling the driving of the actuator connected to the hydraulic pump, a logic check valve mounted in a path between the hydraulic pump and the control valve to be opened and shut, and a logic control valve mounted between the hydraulic pump and the pressure chamber of the logic check valve and for controlling an amount of fluid passing through the upper side of the logic check valve from the hydraulic pump upon switching.

Abstract: An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a generally rectangular exit end with an increased first and second radius of curvature, a generally cylindrical inlet sleeve, and a generally rectangular end frame. Cooling of the transition duct is accomplished by a plurality of holes angled towards the end frame of the transition duct and drilled at an acute angle relative to the outer wall of the transition duct. Effusion cooling geometry, including coverage area, hole size, and surface angle will be optimized in the transition duct to tailor the temperature levels and gradients in order to minimize thermally induced stresses. The combination of the increase in radii of curvature of the panel assembly with the effusion cooling holes reduces component stresses and increases component life.

Abstract: An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a generally rectangular exit end with an increased first and second radius of curvature, a generally cylindrical inlet flange, and a generally rectangular end frame. Cooling of the transition duct is accomplished by a plurality of holes angled towards the end frame of the transition duct and drilled at an acute angle relative to the outer wall of the transition duct. The combination of the increase in radii of curvature of the panel assembly with the effusion cooling holes reduces component stresses and increases component life. An alternate embodiment of the present invention is shown which discloses shaped angled holes for improving the film cooling effectiveness of effusion holes on a transition duct while reducing film blow off.

Abstract: Hydrocarbonaceous fuel, such as coal, oil or gas, is gasified to produce syngas comprising H2 and CO, scrubbed free of particles, and saturated with water. The syngas is then treated in an acid gas removal unit as desired to remove any impurities in the syngas. After processing the syngas in the AGR, it is routed to a hydrocarbon synthesis reactor. In the hydrocarbon synthesis reactor, the bulk of the H2 and CO in the syngas is converted to synthetic hydrocarbons, the makeup of which is generally dependent on the type catalyst used in the reactor. The unreacted gas, or tailgas, exiting the reactor, is sent to the gas turbine as fuel. Optionally, N2 or natural gas can be added to the tailgas prior to the combustion turbine. N2 may also optionally be mixed with the hydrocarbon synthesis reactor feed to help control the reaction temperature. After being combusted in the combustor of a gas turbine, the combustion products are expanded to produce power.

Abstract: A combustor for a gas turbine engine comprising at least one combustor air intake chute wherein at least one of the air intake chutes is configured to enhance the heat transfer relationship between the chute material and the air flowing over it. The air intake chutes have at least one raised feature formed on their inner surface which extends into the airflow passing through the chute. The raised features may take the form of a circumferential rib, an axial rib or a pedestal, or any combination of the same.