Abstract: A gas turbine system having a plasma actuator flow control arrangement including a compressor section for compressing an airstream, wherein the compressor section includes at least one inlet guide vane for controlling the airstream proximate an inlet portion of the compressor section. Also included is a turbine inlet assembly for ingesting the airstream to be routed to the compressor section. Further included is a plasma actuator disposed within at least one of the inlet portion of the compressor section and the turbine inlet assembly for controllably producing an electric field to manipulate a portion of the airstream.

Abstract: A gas turbine engine includes a core housing that has an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. The shaft supports a compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A geared architecture is coupled to the shaft, and a fan coupled to and rotationally driven by the geared architecture. The geared architecture includes a sun gear supported on the second end. A first bearing supports the shaft relative to the intermediate case and a second bearing supporting the shaft relative to the inlet case. The second bearing is arranged radially outward from the shaft.

Abstract: Provided is a gas turbine including: a first compressor which compresses air; a mixer which adds the compressed air from the first compressor to fuel and generates a fuel mixture; a combustor which combusts the generated fuel mixture from the mixer; a plurality of flow meters which adjusts an amount of the air or the fuel injected into the mixer; and a control unit which maintains the Wobbe Index of the fuel mixture within a predetermined Wobbe Index rang.

Abstract: A method for assembling a gas turbine engine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, and coupling a low-pressure compressor between the core gas turbine engine and a motor such that the low-pressure compressor is driven only by the motor.

Abstract: A power plant configured to include a recirculation loop about which a working fluid is recirculated. The recirculation loop may include a plurality of components configured to accept an outflow of working fluid from a neighboring upstream component and provide an inflow of working fluid to a neighboring downstream component. The recirculation loop may include: a recirculation compressor; an upstream combustor; a high-pressure turbine; a downstream combustor; a low-pressure turbine; and a recirculation conduit configured to direct the outflow of working fluid from the low-pressure turbine to the recirculation compressor. The power plant further may include: an oxidant compressor configured to provide compressed oxidant to one of the upstream combustor and the downstream combustor; and means for extracting a portion of the working fluid from an extraction point disposed at a predetermined location on the recirculation loop.

Abstract: The present invention provides a system and method of operating a combined-cycle powerplant at part-load without shutting down an HRSG and steam turbine. The present invention may apply to a powerplant operating in an open-cycle mode. The present invention may also apply to a powerplant operating in a closed-cycle mode.

Abstract: The present invention provides a system and method that yields an exhaust stream that includes a relatively high concentration of a desirable gas and is also substantially oxygen-free. This desirable gas includes, but is not limited to: Carbon Dioxide (CO2), Nitrogen (N2), or Argon. The present invention also provides a way to control the physical property of the exhaust stream.

Abstract: Embodiments of the present invention provide to a cooling and sealing air system for reheat gas turbine powerplant operating in a configuration that includes stoichiometric exhaust gas recirculation configuration. A user may have the flexibility in determining where the cooling and sealing flow derives. This may include and enhanced oil recovery system, a concentrated carbon system, etc.

Abstract: A power plant configured to include a recirculation loop about which a working fluid is recirculated, the recirculation loop comprising a plurality of components configured to accept an outflow of working fluid from a neighboring upstream component and provide an inflow of working fluid to a neighboring downstream component. The recirculation loop may include: a recirculation compressor; an upstream combustor; a high-pressure turbine; a downstream combustor; a low-pressure turbine; and a recirculation conduit configured to direct the outflow of working fluid from the low-pressure turbine to the recirculation compressor. The power plant may include: an oxidant compressor configured to provide compressed oxidant to both the upstream combustor and the downstream combustor; and means for extracting a portion of the working fluid from an extraction point disposed on the recirculation loop.

Abstract: A gas turbine engine has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially inwardly of the outer bypass duct. The booster fan delivers air into a radially middle duct, and across a cold turbine into a radially inner core duct being directed into a compressor. From the compressor, air flows axially in a direction back toward the fan through a combustor section, and across an exhaust of the turbine section as directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method is also disclosed.

Abstract: Disclosed herein is a system comprising an air reactor; where the air reactor is operative to oxidize metal oxide particles with oxygen from air to form oxidized metal oxide particles; a fuel reactor; where the fuel reactor is operative to release the oxygen from the oxidized metal oxide particles and to react this oxygen with fuel and steam to form syngas; a water gas shift reactor located downstream of the fuel reactor; where the water gas shift reactor is operative to convert syngas to a mixture of carbon and hydrogen; a combustor; and a gas turbine; the combustor being operative to combust the hydrogen and discharge flue gases derived from the combustion of hydrogen to drive the turbine; where the exhaust from the turbine is carbon free.

Abstract: A gas turbine engine and method of controlling the gas turbine engine that may be utilized in a power grid having a plurality of additional power generation sources. The gas turbine engine is configured with a compressor having an enlarged mass flow volume. The gas turbine engine may be operated at a base load for supplying power to the power grid at a part load and optimum efficiency for the engine, and may be ramped up to a higher output to supply a peak load output to the power grid.

Abstract: An energy generation system and method are presented for use in operating a heat engine. The energy generation method comprises: reducing a CO2 gas into CO and O2 gases; reacting said CO and O2 gases, thus combusting the CO gas, and yielding a substantially pure CO2 outlet gas; and supplying said CO2 outlet gas to the heat engine as a working gas in its heat-to-work generation process.

Abstract: A gas turbine system comprising, a diffuser operative to diffuse an airstream output from a compressor, a fuel nozzle operative to receive fuel and emit the fuel in a combustor, and at least one bleed duct operative to direct bleed air from down stream of the combustor to the fuel nozzle.

Abstract: A gas turbine engine having a compressor section using blades on a rotor to deliver a gas at supersonic conditions to a stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration of the gas to subsonic conditions and to deliver a high pressure gas to combustors. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of two to one (2:1) or more, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct.

Abstract: A fan rotor blade includes a blade body constructed of a composite material, a blade root constructed of the composite material, and a sheath attached to a leading edge of the blade body. The sheath includes a sheath main body and a pair of joint flanges, and is segmented into a sheath base segment and a sheath top segment. The sheath top segment has a longer length than a length of the sheath base segment along a span direction. A sheath length of the sheath main body at an assumed impact position with an obstacle is not shorter than 10% chord and not longer than 60% chord. A sheath length of the sheath along an end edge of the fan rotor blade is not shorter than 40% chord. The fan rotor blade possesses sufficient impact resistance and can be simplified and light-weighted.

Abstract: A fan blade comprises a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. The fan blade has a dovetail, and an airfoil extending radially outwardly from the dovetail. Material is deposited within the channels, with one type of material being selected to provide additional stiffness to the fan blade, and a second type of material being selected for having good damping characteristics. A method and gas turbine engine are is also disclosed.

Abstract: In a cooling structure for a recovery-type air-cooled gas turbine combustor having a recovery-type air-cooling structure that bleeds, upstream of the combustor, and pressurizes compressed air supplied from a compressor, that uses the bled and pressurized air to cool a wall, and that recovers and reuses the bled and pressurized air as combustion air for burning fuel in the combustor together with a main flow of the compressed air, wall cooling in which cooling air is supplied to cooling air passages formed in the wall of the combustor to perform cooling involves a downstream wall region, closer to a turbine, that is cooled using the bled and pressurized air as the cooling air and an upstream wall region, closer to a burner, that is cooled using, as the cooling air, bled compressed air bled from a main flow of the compressed air through a housing inner space.

Abstract: The present invention relates to a jet engine including protrusions (1) for preventing the increase of the velocity gradient of a fluid in a mixed layer of a jet flow and an external air flow by bending the mixed layer, when viewed from the side of a jet flow injected.

Abstract: A gas-turbine combustion chamber arrangement includes a flame tube, a diffuser element arranged upstream of the flame tube in the flow direction, the diffuser element including an annular duct, and an axial compressor arranged upstream of the diffuser element. The diffuser element features an annular guide vane area in which guide vanes are arranged, which for redirecting an incoming flow are provided at an angle (?) in a range between 28° and 32° relative to a central axis of the gas turbine. Downstream of the guide vane area, a diffuser area is arranged, the diffuser area not being provided with flow-guiding elements affecting the flow, where burners arranged in the annular combustion chamber are provided with their burner axes at an angle (?) between 40° and 50° relative to the central axis.

Abstract: A gas turbine power generation plant including: a solid fuel gasifier for the production of a fuel gas stream, an arrangement for fuel gas treatment, a combustor for receiving the fuel gas stream and for the production of a flue gas stream, a gas turbine unit having an inlet for said flue gas stream and being mechanically coupled to an electric generator for the extraction of useful work; a compressor unit for the supply of compressed oxygen to the combustor. A steam generator is arranged for heat recovery in the flue gas stream downstream of the turbine unit positioned for water recovery in the flue gas stream, said condenser having a connection for water supply to the steam generator, and the steam generator is connected for supply of steam to the combustor for contributing as process gas. The invention also concerns a method for operating a power plant and an arrangement and a method for fuel gas treatment.

Abstract: A transition piece of a combustor which is sustainable even under conditions of more severe thermal environments is provided in the present invention. A transition piece of a combustor is provided with a cylindrical trunk main body, a cylindrical exit trunk part which is joined to the downstream end of the trunk main body and which cooperates with the trunk main body to constitute a trunk part, and an inner flange which extends from the downstream end part of the exit trunk part toward the outer periphery side of the exit trunk part. The exit trunk part and the inner flange are of an one-piece product. On the exit trunk part, there is formed a groove, and there is formed a cooling fluid passage which opens at the groove.

Abstract: A turbine engine includes a compressor section, a combustor arranged in fluid-receiving communication with the compressor section, a turbine section arranged in fluid-receiving communication with the combustor and a gearbox assembly coupled to be driven by the turbine section. The gearbox assembly is located at an axial position that is aft of the compressor section.

Abstract: A method is disclosed for operating a gas turbine power plant having a gas turbine, a heat recovery steam generator and an flue gas splitter which splits flue gases into a first flue gas flow for recirculation into an inlet flow of the gas turbine and into a second flue gas flow for discharge to an environment. An oxygen-depleted gas can be used in an open cooling system for cooling hot gas parts of the gas turbine. A split compressor intake can be provided for separate feed of recirculated flue gas and fresh air into a compressor intake. Compressor blades can include a separating band which blocks intermixing of recirculated flue gas and fresh air during compression.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages.

Abstract: A power plant and method of operation is provided. The power plant comprises at least one main air compressor, an oxidizer unit configured to deliver a compressed oxygen-rich gas flow to at least one gas turbine assembly. Each assembly comprises a turbine combustor for mixing the compressed oxygen-rich gas flow with a recirculated gas flow and a fuel stream to burn a combustible mixture and form the recirculated gas flow. The assembly also comprises a recirculation loop for recirculating the recirculated gas flow from a turbine to a turbine compressor. The assembly further comprises a recirculated gas flow extraction path for extracting a portion of the recirculated gas flow from the assembly and delivering this to a gas separation system. The gas separation system separates the portion of the recirculated gas flow into a nitrogen portion and a carbon dioxide portion.

Abstract: There is provided an axial bearing load distribution system for a gas turbine engine of the type having a low pressure rotor supported by axial bearings. The system comprises a line having an inlet end positioned in a high-pressure compressor gas path downstream of any compressor stage provided with a variable geometry. The line is adapted to sense static pressure in the high-pressure compressor gas path. The line has an outlet end producing the static pressure. An air-tight pressure actuator is operatively connected to the outlet end and to one of the axial bearings to exert a force on the axial bearing proportionally to a pressure of the outlet end.

Abstract: A turbomachine including an annular combustion chamber, a centrifugal compressor, an annular diffuser enabling the flow of gas leaving the compressor to be diffused and directing this flow of gas towards the combustion chamber, and an outer casing surrounding the outside of the combustion chamber is disclosed. The diffuser includes an upstream portion oriented radially and presenting diffusion passages connected to the outlet from the compressor, an intermediate portion that is elbow-shaped, and a downstream portion having a series of circularly spaced-apart flow-straightening vanes. The flow stream in the downstream portion is delimited externally by the outer casing. The outer casing presents a shoulder against which the outer downstream edge of the intermediate portion comes into abutment.

Abstract: A gas turbine engine turbine cooling system includes an impeller and a diffuser directly downstream of the impeller, a bleed for bleeding clean cooling air from downstream of the diffuser, and one or more channels in fluid communication with the bleed. Each of the channels having a generally radially extending section followed by a generally axially aftwardly extending section terminating at an annular cooling air plenum connected to accelerators. The radially and axially aftwardly extending sections may be connected by a bend section of the cooling air channel and the axially aftwardly extending section may be angled radially inwardly going from the bend section to the cooling air plenum. Each of the cooling channels includes an inner wall formed by a forward end wall extending radially outwardly from an inner combustor casing, an annular cover covering a radially inner portion of the forward end wall, and the inner combustor casing.

Abstract: A gasifying agent supply path A from an axial flow compressor 21 which boosts pressure of a gasifying agent to a gasifying furnace 2 is branched, and a gasifying agent bypass path D having an escaping pressure adjusting valve 23 is provided. The flow quantity or pressure of the gasifying agent supplied to the gasifying furnace 2 from the gasifying agent supply path A can be adjusted according to the degree of opening of the adjusting valve 23 disposed in the gasifying agent bypass path D, whereby providing a control valve in the gasifying agent supply path A is no longer necessary. Thus, pressure loss at the gasifying agent supply path A can be suppressed, and the discharge pressure of the axial flow compressor 21 can be greatly reduced.

Abstract: A diffuser is provided that includes a first wall, a second wall, and a first plasma actuator. The first wall has a radially-extending section and a curved section. The second wall has a radially-extending section and a curved section that are spaced apart from the radially-extending section and the curved section of the first wall such that the curved section of the second wall is disposed radially inwardly from the curved section of the first wall and a flow path is defined therebetween. The first plasma actuator is disposed on the curved section of the second wall, and the first plasma actuator is adapted to generate a first electric field to ionize a first portion of air flowing along the flow path to form a plurality of ionized species capable of inducing a second portion of air to flow in a desired direction.

Abstract: A diffuser system for a compressor for a gas turbine engine includes a diffuser and a plasma actuator. The diffuser comprises a first wall and a second wall. The first and second walls form a diffuser flow passage therebetween. The plasma actuator is disposed at least partially proximate the second wall. The plasma actuator is adapted to generate an electric field to ionize a portion of air flowing through the flow passage.

Abstract: Upon cooling to 15 to 45° C., a process for the treatment of raw product gas generated by pressure gasification of solid fuels comprises the removal of HCN and NH3 in a preliminary stage, of H2S and COS and possibly other sulfur-containing compounds in a first stage and of CO2 in a second stage by physisorption with cold oxygenate, and the pure product gas is supplied to the direct reduction of iron ore as reduction gas and/or as fuel gas. An improvement of the process consists in that recycle gas loaded with CO2 and steam, which is branched off from the circuit of the recycle gas of the direct reduction of iron ore, is admixed to the desulfurized product gas upon removal of the steam contained therein.

Abstract: A system for cooling the impeller of a centrifugal compressor in a turbomachine is disclosed. The compressor supplies an annular diffuser. The diffuser includes an end-piece that extends downstream and along the impeller of the compressor and is covered on the upstream side by an annular metal sheet. The sheet delimits, with the impeller of the compressor, a first annular passageway to carry away the air taken from the outlet of the compressor and, with the end-piece of the diffuser, a second annular passageway to carry away a portion of the air flow coming out of the diffuser.

Abstract: An axial flow positive displacement turbine includes inner and outer bodies having offset inner and outer axes respectively extending between a relatively high pressure inlet and a relatively low pressure outlet. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades wound about the inner and outer axes respectively. The inner and outer helical blades extend radially outwardly and inwardly respectively. Each of the bodies has at least two blades. There is one more or one less outer helical blades than inner helical blades. The inner and outer bodies may both be rotatable about inner and outer axes and geared together in a fixed gear ratio. The turbine may have first and second sections with a first twist slope greater than a second twist slope respectively of the inner and outer helical blades.

Abstract: The power plant combusts a hydrocarbon fuel with oxygen to produce high temperature high pressure products of combustion. These products of combustion are routed through an expander to generate power. The products of combustion are substantially free of oxides of nitrogen because the oxidizer is oxygen rather than air. To achieve fast starting, oxygen, fuel and water diluent are preferably stored in quantities sufficient to allow the power plant to operate from these stored consumables. The fuel can be a gaseous or liquid fuel. The oxygen is preferably stored as liquid and routed through a vaporizer before combustion in a gas generator along with the hydrocarbon fuel. In one embodiment, the vaporizer gasifies the oxygen by absorption of heat from air before the air is routed into a separate heat engine, such as a gas turbine. The gas turbine thus operates on cooled air and has its power output increased.

Abstract: Gas turbine engine systems involving hydrostatic face seals are provided. In this regard, representative compressor assembly for a gas turbine engine includes a compressor having a hydrostatic seal formed by a seal face and a seal runner.

Abstract: A heat engine, includes at least one Liquid Ring Rotating Casing Compressor (LRRCC) having a fluid inlet and a fluid outlet, a combustion chamber in fluid communication with the output of the LRRCC, and at least one expander having a fluid inlet and a fluid outlet. The fluid inlet communicates with the combustion chamber.

Abstract: A gas turbine systems of reducing NOX emissions and enhancing operability comprises a compressor; a combustor disposed downstream of and in fluid communication with the compressor; a turbine assembly disposed down stream of and in fluid communication with the combustor; an oxygen-enriched gas source disposed in selective fluid communication with the compressor, the combustor, or a combination of the foregoing, wherein the oxygen-enriched gas source is a pressure swing absorption system, an electrolyzer, or a membrane reactor.

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: A gas turbine engine has components including a compressor, a combustor, and a turbine. At least one component is radially bladed having at least one row of radially extending rotatable blades and at least another is a worm component having an inner body disposed within an outer body. The inner and outer bodies have offset inner and outer axes, intermeshed inner and outer helical blades wound about the inner and outer axes respectively, and at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes. An aircraft gas turbine engine has components in serial downstream flow relationship including a fan, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine. At least one of the components is radially bladed and at least one of the components is a worm component.

Abstract: When both engines operate properly, a control apparatus for an aircraft performs control of thrust and attitude of an aircraft using an output that is produced evenly by the two engines. When a failure occurs in one of the two engines, the control apparatus performs the control of thrust and attitude of the aircraft by increasing an output of the remaining engine that operates properly to an emergency output. When the failure occurs in one of the two engines, the control apparatus makes an engine output that is used for the control of thrust and attitude of the aircraft lower than an engine output that is used when both engines operate properly, until the remaining engine that operates properly is enabled to produce the emergency output.

Abstract: A method of assembling a combustion system includes providing a gas turbine engine that includes a gas turbine section coupled downstream from a combustion chamber and coupling a source of oxygen to the gas turbine engine such that a stream of oxygen discharged from the source facilitates displacing nitrogen in the working fluid of the gas turbine engine and facilitates decreasing emissions generated within the gas turbine engine.

Abstract: An apparatus and method converts a power generation combined cycle (CC) power plant to a load management compressed air energy storage (CAES) power plant. The CC power plant includes at least one combustion turbine, a heat recovery steam generator (HRSG) to receive exhaust heat from an associated combustion turbine, a steam turbine associated with the HRSG, and an electric generator associated with the steam turbine. An air storage stores compressed air. At least one compressor supplies the air storage with compressed air so that off peak energy can be converted to compressed air energy stored in the air storage. Compressed air from the storage is received by the HRSG and the HRSG provides heat to compressed air received from the air storage. The steam turbine receives heated compressed air from the HRSG and expands the heated compressed air to produce power.

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

Abstract: An orbiting combustor nozzle (OCN) engine, having a rotating assembly comprising a co-rotating compressor and nozzle wheel enclosed within a non-rotating outer casing, defining a rotating combustion chamber, is disclosed. Combustion occurs in the combustion chamber in a vortex of gas that rotates at the same angular velocity as the rotating assembly. Also disclosed, is a method of cooling a blade of a rotating wheel, such as a turbine wheel or nozzle wheel, by projecting cool air at the base of the vane form a nozzle corotating with the blade. Such cooling is easily implemented in an OCN engine with use of an innovative annular combustor. Also disclosed is a method of countering axial backflow by use of a combustion chamber compressor.

Abstract: A work extraction arrangement (10) comprises a cooling assembly (12) for cooling a gas to provide a working fluid capable of doing work. The arrangement (10) further includes storage means (14) for storing the working fluid and a turbine assembly (18) for extracting work from the working fluid. A fluid delivery assembly (16) is also provided to deliver the working fluid to the turbine assembly (18).

Abstract: An improved combustion air charger, such as a turbocharger or a supercharger, includes a housing (10) having a rotary shaft (18) journalled therein. At least one compressor wheel (20,22) is located on the shaft (18). The housing (10) includes an ambient inlet (30) as well as a compressed air outlet (32) and a heat exchanger (36) is located between at least one of the compressor wheels (20) and the outlet (32) and is arranged so that air flow through the heat exchanger (36) is generally in the radially inward direction.

Abstract: Two spool gas turbine engines are often used to drive variable speed loads, such as an electric generator, or the fan/propeller of aircraft engines. The gas turbine engine must be designed to withstand transient speed and temperature conditions which are encountered when sudden changes to the load on the generator, fan, or propeller occur. By adding a relatively small motor/generator to the gas generator spool of the gas turbine engine, the compressor speed and airflow can be quickly adjusted to compensate for external load changes. This reduces the severity and duration of the transient conditions, resulting in decreased operation and reliability problems such as overspeed, compressor surge, and high turbine temperature. The motor/generator may also be used as an engine starting device.

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