Abstract: A gas turbine engine having a waste heat recovery system is provided. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath, the exhaust section including a primary exhaust flowpath and a waste heat recovery flowpath parallel to the primary exhaust flowpath; and the waste heat recovery system includes a heat source exchanger positioned in thermal communication with a first portion of the waste heat recovery flowpath.

Abstract: A gas turbine engine includes a core engine, including a compressor section, a combustor section and a turbine section positioned within a core flow path of the gas turbine engine; a bypass splitter positioned radially outward of the core engine and configured to house the compressor section, the combustor section and the turbine section; a bypass duct positioned radially outward of the bypass splitter; a fan section positioned axially upstream of the compressor section, the fan section including a fan and an inlet cone positioned upstream of the fan; an inlet duct configured to house the fan section; an inlet precooler disposed within the inlet duct; and a heat exchange system configured to provide a cooling fluid to the inlet precooler.

Abstract: A thermodynamic apparatus (10) comprising a compressor module (100), a turbine module (200), and a regenerative heat exchanger (300) centred on a central axis (12). The compressor module (100), turbine module (200) and regenerative heat exchanger (300) are arranged in series along the central axis (12) such that the regenerative heat exchanger (300) is provided between the compressor module (100) and the turbine module (200).

Abstract: A heat insulating material assembly is provided with: a heat insulating material covering an outer surface of a casing of a gas turbine; and a guard part disposed so as to protrude from the outer surface of the casing and face an end surface of the heat insulating material. The heat insulating material is disposed outside an arrangement area of a plurality of openings for air intake from an external space into the casing and on an opposite side to the arrangement area across the guard part.

Abstract: A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid flow.

Abstract: A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

Abstract: An apparatus for dehumidifying ambient atmospheric air includes a first air path and a second air path. A heat exchanger system transfers at least a portion of radiated thermal energy to air drawn along the first air path to heat the air in the first air path and transfers at least a portion of the thermal energy from exhaust gas to air drawn along the first air path to heat the air in the first air path. The first air path connects the ambient atmosphere to a reactivation air outlet through the heat exchanger system and a desiccant in a second moisturized state, and the second air path connects the ambient atmosphere to a dried air outlet through the desiccant in a first dried state.

Abstract: A gas turbine engine (1) has a centrifugal compressor (4) and a radial turbine (14) mounted to a turbine shaft (2) for rotation with the shaft about the shaft axis Z. A number of combustion chambers (10) in the air/gas flow path between the compressor and the turbine are spaced circumferentially about the shaft axis. The combustion chambers (10) are elongate in the direction of air/gas flow and the longitudinal axis of each combustion chamber is skewed transversely relative to the axis Z of the turbine shaft. The combustion chambers (10) may be curved longitudinally about the shaft axis and may be aligned concentric about the axis. The engine may have a recuperator (8) radially outboard the compressor, the recuperator having radially directed flow passages through which air from the compressor is directed.

Abstract: A method including: (i) receiving a first amount of electricity into a pumped-heat energy storage system (“PHES system”) from a power generation plant supplying a second amount of electricity to an electrical grid; (ii) operating the PHES system in a charge mode, converting at least a portion of the received first amount of electricity to stored thermal energy; and (iii) increasing a power level of the PHES system such that the first amount of electricity that the PHES system receives from the power generation plant is increased such that the second amount of electricity supplied to the electrical grid by the power generation plant is a reduced amount of electricity less than the second amount of electricity.

Abstract: An assembly is provided for a gas turbine engine. This assembly includes a combustor wall, a case and an inlet. The combustor wall is configured with a quench aperture. The case is displaced from the combustor wall such that a plenum is formed by and extends between the combustor wall and the case. The case includes a case wall, a deflector and a conduit. The deflector projects out from the case wall into the plenum towards the combustor wall. The deflector is arranged upstream of the quench aperture. The inlet to the conduit is arranged next to and downstream of the deflector.

Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.

Abstract: A system including: a pumped-heat energy storage system (“PHES system”), wherein the PHES system is operable in a charge mode to convert electricity into stored thermal energy, wherein the PHES system comprises a working fluid path circulating a working fluid through, in sequence, at least a compressor system, a hot-side heat exchanger system, a turbine system, a cold-side heat exchanger system, and back to the compressor system; and (ii) a fluid path directing a hot fluid from a heat source external to the PHES system through a reheater, wherein a portion of the working fluid path through the turbine system comprises circulating the working fluid through a first turbine, the reheater, and a second turbine, and wherein the working fluid thermally contacts the hot fluid in the reheater, thereby transferring heat from the hot fluid to the working fluid.

Abstract: A system includes a gas turbine system having a first compressor, a combustor, and a turbine, where the first compressor provides a first portion of a discharge air directly to the combustor. The system includes a fluid circuit which receives a fluid comprising a second portion of the discharge air from the first compressor or a combustible fluid and provides the second portion of the discharge air to fuel at a location upstream of the combustor to alter a chemical and physical characteristic of the fuel in an air-fuel mixture that is provided to the combustor.

Abstract: A method of operating a thermal management system for a gas turbine engine includes determining the gas turbine engine is in a first operating mode; transferring heat from a first heat source exchanger to a heat sink system in response to determining the gas turbine engine is in the first operation mode, the first heat source exchanger thermally coupled to a first system/component of the gas turbine engine; determining the gas turbine engine is in a second operating mode, the second operating mode being different than the first operating mode; and transferring heat from a second heat source exchanger to the heat sink system in response to determining the gas turbine engine is in the second operation mode, the second heat source exchanger thermally coupled to a second system/component of the gas turbine engine, the second system/component being different than the first system/component.

Abstract: A rotor blade for a gas turbine, in particular an aircraft gas turbine, having a blade root element and a stream deflection portion adjoining the blade root element (12) in the longitudinal direction of the blade (RR); respective centroids (24) of blade cross-sectional areas of the stream deflection portion residing on a common stacking axis (26). It is provided that, starting from a first centroid (24) of a first blade cross-sectional area adjoining the blade root element (12), the stacking axis (26) extend within a cone (28) whose apex resides within the first centroid (24), and whose cone height (KH) extends orthogonally to the plane of the blade cross-sectional area; the angle (?) of the cone (28) being greater than 0° and smaller than or equal to 4°; preferably greater than or equal to 0.5° and smaller than or equal to 2°.

Abstract: A heat transfer arrangement includes two or more heat transfer cells. The heat transfer cells together define a boundary between a higher temperature region and a lower temperature region. Each of the two or more heat transfer cells includes two or more walls defining a fluid tight cavity. One or more wick is fused to an inner surface of one or more of the walls to wick liquid from a lower temperature portion of the cavity to a higher temperature portion of the cavity. Combustors having heat transfer arrangements with heat transfer cells and methods of making heat transfer arrangements are also described.

Abstract: A combustor for a turbomachine includes a rich combustion zone and a low temperature zone downstream of the rich combustion zone. A heat exchanger is positioned downstream of the rich combustion zone and upstream of the low temperature zone. The heat exchanger includes a plurality of air passages, a plurality of air inlets in fluid communication with the plurality of air passages, and a plurality of combustion gas passages. Each of the combustion gas passages extends between a combustion gas inlet in fluid communication with the rich combustion zone and a combustion gas outlet in fluid communication with the low temperature zone. The plurality of combustion gas passages are in thermal communication with the plurality of air passages.

Abstract: A gas turbine engine includes a supply air conduit fluidly connected to an inlet of a combustion chamber to convey supply air to the combustion chamber, an exhaust conduit fluidly connected to an exit of the combustion chamber to convey exhaust gases away from the combustion chamber, and a recuperator defining a first flow path and a second flow path therethrough, the second flow path being in heat transfer communication with the first flow path, the first flow path defining part of the supply air conduit, the second flow path defining part of the exhaust conduit. Methods of operating the engine are also provided.

Abstract: A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor. The high pressure compressor has a downstream most location. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor and a heat exchanger, which passes the air back to a location to be cooled. The boost compressor is driven by a shaft which drives the lower pressure compressor.

Abstract: A turboshaft engine for a helicopter, comprising a case inside which a gas generator and a turbine are accommodated, the turbine being mounted on a power shaft that extends along a longitudinal direction. The turboshaft engine further comprises means for removably mounting the power shaft into a reduction gearbox inside which at least one gear of a first reduction stage is accommodated. The means for removably mounting the power shaft include a pinion having a central bore, the shape of which is adapted to that of the power shaft in such a way that the pinion can slide over the power shaft; furthermore, the contour of the pinion is adapted to the shape of the gear of the first stage in such a way that the pinion can form a leading input pinion of the gearbox in said gear once the power shaft has been mounted in the reduction gearbox.

Abstract: A guide vane for a turbomachine is disclosed. The guide vane includes a heat pipe wall that is interpenetrated by a capillary system, which has a continuous material transition from a first surface, which delimits the guide vane toward the outside, to a second surface, which lies opposite to the first surface and delimits an evaporation cavity in the interior of the guide vane. Further disclosed is a method for producing a guide vane having a heat pipe wall, wherein at least the heat pipe wall is formed by additive manufacture.

Abstract: A recuperator includes a monolithic heat exchanger core having a first side proximal to a combustor inlet and a turbine outlet, and a second side that includes an exhaust outlet. A compressed air inlet is located on the second side, and a compressed air outlet is located on the first side. The compressed air outlet supplies air to a combustor. A first plurality of passageways connects the compressed air inlet to the compressed air outlet. A turbine exhaust inlet is located on the first side, and a turbine exhaust outlet is located on the second side. A second plurality of passageways connects the turbine exhaust inlet to the turbine exhaust outlet. The first and second plurality of passageways are defined by parting plates that extend radially outward in a spiral pattern that maintains a substantially equal distance between adjacent parting plates.

Abstract: An internal combustion engine system includes a compressor arranged to compress air, at least one combustor, at least one of the at least one combustor being arranged to receive the compressed air, and an exhaust treatment device arranged to process exhaust gases produced by at least one of the at least one combustor, a heat exchanger arranged to receive the compressed air from the compressor before it reaches the at least one of the at least one combustor, and wherein the heat exchanger is arranged to transfer heat from the compressed air to the exhaust treatment device.

Abstract: An internal combustion engine system includes at least one combustor, a compressor arranged to compress air, an air guide arranged to guide compressed air from the compressor to at least one of the at least one combustor, an expander arranged to expand exhaust gases from at least one of the at least one combustor and to extract energy from the expanded exhaust gases, and an exhaust guide arranged to guide exhaust gases from at least one of the at least one combustor to the expander, wherein the exhaust guide is at least partly integrated with the air guide.

Abstract: One of the objects of the invention is to provide a water-saving type advanced humid air gas turbine system (AHAT) that can decrease the amount of makeup water to be supplied from the outside, by reducing the amount of water consumed when the gas turbine system is starting up, shut down, or subjected to load rejection. The gas turbine system includes a compressor, the compressed air header for generating humidified combustion air, a combustor for generating combustion gas, and the turbine. When the gas turbine system is starting up, shut down or subjected to load rejection, steam coming from the heat recovery steam generator is recovered by blocking the first steam system and making the second steam system communicate with the heat recovery steam generator.

Abstract: An exhaust system for a gas turbine engine, such as an APU, comprises a pressure vessel having an annular wall circumscribing an exhaust plenum. The annular wall is composed of an arrangement of individual tubes assembled side-by-side around a central axis of the exhaust plenum. The tubes are fed with pressurized cooling air, such as P3 air. A heat exchanger in heat transfer relationship with the exhaust gases flowing through the exhaust plenum receives air from the tubes. The heat transferred from the exhaust gases to the air circulated through the heat exchanger may be used to provide pre-heated air to the engine combustor.

Abstract: The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly comprises a volute walled enclosure defining a spiral scroll pitch axis disposed at least partially circumferentially around a centerline axis of the gas turbine engine, in which the walled enclosure is defined around the pitch axis, and the walled enclosure defines a combustion chamber therewithin.

Abstract: A system includes a vehicle having a body and a power generation system. The power generation system includes first and second tanks each configured to receive and store a refrigerant under pressure. The power generation system also includes at least one generator configured to generate electrical power based on a flow of the refrigerant between the tanks. The first tank is configured to be cooled by one of ambient air and water to a lower temperature, and the second tank is configured to be warmed by another of the ambient air and the water to a higher temperature. The first tank or associated heat exchanger can be positioned such that the first tank is above the water's surface when a portion of the body breaches the surface. The second tank or associated heat exchanger can be positioned such that the second tank is below the water's surface when a portion of the body breaches the surface.

Abstract: An example method may comprise providing a composite pumped thermal system having a plurality of subunits, each configured for operation in a thermal storage mode and a power generation mode; operating the system in power output mode with a power output level at an intermediate output level between 0% and 100% of a maximum output level of the system; reducing the power output level to 0% of the maximum output level by reducing a power output of a first subunit operating in a power generation mode; and at 0% of the maximum output level, wherein a power input level of the system is also at 0% of a maximum input level of the system, increasing the power input level to an intermediate input level between 0% and 100% of the maximum input level by increasing a power input of a second subunit operating in a thermal storage mode.

Abstract: A multi-spool gas turbine engine comprises a low pressure (LP) spool and a high pressure (HP) spool independently rotatable about a central axis. The LP pressure spool has an LP compressor and an LP turbine. The HP spool has an HP turbine and an HP compressor. An accessory gear box (AGB) is drivingly connected to the HP spool. The LP compressor is disposed axially between the HP compressor and the AGB. A gear train drivingly couples the LP compressor to the LP turbine. The gear train is integrated to the AGB.

Abstract: A fuel circuit of an aircraft engine including a fuel tank; an engine fuel system including a low-pressure pump and a high-pressure pump, and a fuel recirculating pipeline connected to the engine fuel system; and a fuel recirculating valve arranged so as to switch between an open position and a closed position according to the pressure differential of the low-pressure pump, the valve being able to obstruct the fuel recirculating pipeline in the closed position, and to bring the fuel recirculating pipeline into communication with the fuel tank in the open position.

Abstract: A vehicle (100) comprising: an engine (102); a system for starting the engine (102); a fault detection module (120); an electrical power source (110); and a controller (116, 122). The controller (116, 122) is configured to, responsive to the fault detection module (120) detecting a fault occurring with the engine (102): determine a window in which to attempt to start the engine (102); control the electrical power source (110) to provide electrical power to the system for starting the engine (102); and control the system for starting the engine (102) to attempt to start the engine (102) using the supplied electrical power only during the determined window.

Abstract: A heat exchanger assembly includes an outer manifold defining an outer cavity. An inner cavity is defined by an inner shell supported within the outer manifold and at least partially surrounded by the outer cavity. The inner shell includes a plurality of impingement openings for directing airflow into the inner cavity. An inner manifold is supported within the inner cavity. The inner manifold is exposed to impingement airflow through the plurality of impingement openings in the inner shell. The inner manifold includes a plurality of flow passages and at least one insulator pocket substantially aligned with the plurality of flow passages. A cooled cooling air system for a gas turbine engine and a gas turbine engine assembly are also disclosed.

Abstract: A system includes a turbine combustor, which includes a head end portion having a head end chamber. The head end portion includes an exhaust gas path, a fuel path, and an oxidant path. The turbine combustor also includes a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and an end plate having at least one port coupled to the exhaust gas path or the oxidant path. The head end chamber is disposed axially between the cap and the end plate.

Abstract: A cooling system for a gas turbine is provided that may include a drive shaft, a shield of a combustor of the gas turbine engine, and a conduit. The drive shaft may be configured to mechanically couple a compressor of the gas turbine engine to a turbine of the gas turbine engine. The shield may be positioned between the compressor and the turbine. The combustor may be configured to drive the turbine. The conduit may be configured to supply a cooling fluid to a gap between an outer surface of the drive shaft and the shield of the combustor.

Abstract: A portable green power system is disclosed that is capable of generating electric power based on green technologies (i.e., environmentally friendly) of high performance, low emissions, and low noise. The portable power system consists of three key design features including a free-floating shaft, an electric motor assisted airblast injector and four concentric channel flows. The engine is partitioned into separate channels or passages for the compressed air, hot gases, recuperation, and the engine case and are organized into four concentric channels for portable design and easy maintenance considerations. The concentric channel design also facilitates fully developed flow in each channel for reduction of vibration and noise. The four concentric channels include turbine concentric channel, compressor concentric channel, recuperator concentric channel and engine case concentric channel. Two-way bypass rings are used for cross flows among these concentric channel flows.

Abstract: A turboshaft engine including a low-pressure compressor, a high-pressure compressor, a low-pressure turbine, a high-pressure turbine, and a regulator for regulating a speed of rotation of the low-pressure turbine to a speed that is substantially constant. The low-pressure turbine is coupled by a first shaft to the high-pressure compressor, while the high-pressure turbine is coupled by a second shaft to the low-pressure compressor.

Abstract: Disclosed is a heat exchanger including: a heat exchanger body; a gas inlet for introducing exhaust gas into the heat exchanger body; a coolant inlet for introducing a coolant into the heat exchanger body; a gas outlet for discharging the exhaust gas that is cooled by heat exchange with the coolant; and a coolant outlet for discharging the coolant that completes heat exchange with the exhaust gas. In this case, the heat exchanger body includes: a laminated tube core formed by laminating a plurality of gas channels side by side; a housing formed so as to enclose the laminated tube core except for opposite ends thereof; and a wave fin plate integrally provided with a plurality of wave fins and arranged within each of the gas channels, wherein each of the wave fins includes a fixed pitch section, and a variable pitch section.

Abstract: A method for assembling a variable geometry turbomachine with a bearing housing, an adjacent turbine housing, a turbine wheel rotating in the turbine housing about a turbine axis; an inlet passage upstream of the turbine wheel between inlet surfaces of first and second wall members, one wall member moveable along the turbine axis to vary the inlet passage size; vanes across the inlet passage connected to a first wall member; an array of vane slots defined by the second wall member to receive the vanes for relative movement between the wall members; the second wall member comprising a shroud defining vane slots; the second wall member supported by a support member retained by a mounting feature; the mounting feature being one of the bearing housings, the turbine housing, or the actuation element; and the shroud is fixed to the support member.

Abstract: A seasonal process that captures stores and uses water in an ambient temperature-dependent manner to improve the efficiency of a natural gas power plant, comprising: (a) providing a natural gas power plant, the natural gas power plant having a flue gas stream, a cooling tower, and a gas turbine; (b) providing a water collection system; (c) providing a water storage facility; wherein the flue gas stream comprises uncondensed water vapor; wherein the water collection system is operably connected to the flue gas stream and the flue gas stream is directed to flow, at least in part, into the water collection system; wherein the water collection system is operably connected to the water storage facility; wherein the water storage facility is operably connected to the cooling tower and the water storage facility is operably connected to the gas turbine; wherein the process comprises the following steps of condensing flue gas water or using water that has been condensed from the flue gas stream based on outdoor ambie

Abstract: A power plant (1) that includes at least one of a gas turbine (GT), a steam turbine (ST) with a water-steam cycle, and a heat recovery steam generator (B) operatively connected to a heat generating member such as solar energy system (Ssolar) by means of a primary circuit (10a, 10b, 10c) and a secondary circuit system (20a). The primary heat transfer circuit (10a, 10b) includes solar heating system (Ssolar) configured to heat a primary fluid (10), and the secondary circuit (20a) comprises a flow line (20A) for a secondary flow (20) and a main heat exchanger (23) to exchange heat between the secondary water flow and a gas turbine inlet air flow (2). A first line (10B) in the primary circuit (10b) leads to a first heat exchanger (12) to heat the water flow in the secondary circuit (20a).

Abstract: A turbocharged internal combustion engine system includes at least one high pressure turbocharger system mounted on-engine and at least one low pressure turbocharger system mounted off-engine. An intercooler can further be mounted off-engine with the low pressure turbocharger and an aftercooler can be mounted on-engine with the high pressure turbocharger.

Abstract: A gas turbine has a compressor, a central housing, at least one combustion chamber, an expansion turbine, and a heat exchanger. Each combustion chamber is fluidically connected to the expansion turbine via an inner housing which is guided through the interior of the central housing. The compressor is fluidically separated from the interior of the central housing by an annular collection chamber connected to an outlet of the compressor and which has a number of discharge lines which are connected to the cold side of the heat exchanger during operation. Each combustion chamber is designed as a silo combustion chamber, and each silo combustion chamber has an inner wall, which delimits a combustion chamber, and an outer wall, and the outer wall surrounds the inner wall, thereby forming a cavity. The inner wall transitions into the inner housing, and the cavity transitions into the interior of the central housing.

Abstract: A turbine system is provided. The turbine system includes a compressor configured to compress ambient air and a combustor configured to receive compressed air from the compressor, and to combust a fuel stream to generate an exhaust gas. The turbine system also includes a turbine for receiving the exhaust gas from the combustor to generate electricity; wherein a first portion of the exhaust gas is mixed with the ambient air to form a low-oxygen air stream, and wherein the low-oxygen air stream is compressed using the compressor, and is directed to the combustor for combusting the fuel stream to generate a low-NOx exhaust gas.

Abstract: A method of recovering heat energy from a cooling medium used to cool hot gas path components in a turbine engine includes cooling one or more hot gas path components with the cooling medium; supplying spent cooling medium used to cool the one or more hot gas path components to a heat exchanger; supplying air (e.g., compressor discharge air) to the heat exchanger so as to be in heat exchange relationship with the spent cooling medium and thereby add heat to the compressor discharge air; and supplying the air heated in the heat exchanger to at least one combustor.

Abstract: A gas turbine system (1A) includes a gas turbine unit (2) and a cooling fluid generator (5). The gas turbine unit (2) includes a first compressor (21) and a first expansion turbine (23) coupled to each other by a first shaft (22), a combustor (26), and a fuel tank (30). A fuel held in the fuel tank (30) circulates through a fuel circulation passage (31). A working fluid that has a pressure increased by the first compressor (1) is extracted from the gas turbine unit (2). The cooling fluid generator (5) includes a cooler (55) for cooling, with the fuel flowing through the fuel circulation passage (31), the working fluid that has been extracted from the gas turbine unit (2), and a second expansion turbine (53) for expanding the working fluid that has flowed out of the cooler (55).

Abstract: A method for manufacturing an inexpensive micro gas turbine has an existing compressor-turbine unit divided into two separate parts being a compressor and a turbine. The compressor and turbine shafts are joined. Two existing bearing units are taken, wherein one of them may belong to the existing compressor-turbine unit. The rotor of an existing generator is mounted on the joined shaft. A generator housing is manufactured and connected to the bearing units. The stator of an existing generator is mounted into the generator housing. Energy input into the working cycle of the gas turbine can be implemented by adding either an internal burner or external burner with a heat exchanger. By using inexpensive and often mass produced off-the-shelf components, a cost effective micro gas turbine can be derived.

Abstract: A reaction-jet helicopter with a recuperator. Hot gas exiting the recuperator is directed to the helicopter's hollow-body rotor blades to increase the energy of the air exiting the jets and thus increase thrust and improve fuel efficiency. Hot gas exiting the recuperator may also be directed to the gas turbine of the helicopter's engine, further increasing fuel efficiency. A splitter valve on the exit side of the recuperator may be employed to direct exiting gas for one or more desired uses. The recuperator includes a heat exchanger, preferably an all-prime surface heat exchanger. The recuperator system may be combined with a circulation control system on the hollow-body rotor blades to further increase fuel efficiency.

Abstract: A can-annular gas turbine engine combustion arrangement (10), including: a combustor can (12) comprising a combustor inlet (38) and a combustor outlet circumferentially and axially offset from the combustor inlet; an outer casing (24) defining a plenum (22) in which the combustor can is disposed; and baffles (70) configured to divide the plenum into radial sectors (72) and configured to inhibit circumferential motion of compressed air (16) within the plenum.

Abstract: A method and gas turbine are provided for the reliable purging of an exhaust gas recirculation line of the gas turbine with exhaust gas recirculation without the use of additional blow-off fans. A blow-off flow of the compressor is used for the purging of the exhaust gas recirculation line. The gas turbine can include at least one purging line which connects a compressor blow-off point to the exhaust gas recirculation line.