Abstract: It is the objective of the present invention to enable smooth rotation of the grid plate and normal operation of the bypass valve, regardless of the operational state of the gas turbine.

Abstract: Sliding-Action Magneto-Mechanical Injector Throttling Device (SLAMMIT) provides on-demand, yet accurate, throttling of the mass flow of the fuel and/or oxidizer into the combustion chamber of a vortex injector. At least two SLAMMIT sub-assemblies comprise the SLAMMIT Device and each sub-assembly is integrated into a manifold and is driven to slide in a given direction by a drive block that is internal to the sub-assembly. The drive block is, in turn, actuated by an electromagnet that is external to the SLAMMIT sub-assembly. As the SLAMMIT sub-assemblies slide, flappers inside the sub-assemblies achieve the effective opening size of the injection orifices anywhere between fully open and fully closed.

Abstract: A variable geometry pre-mixing fuel injector (50) for injecting a fuel/air mix in a downstream direction, comprising: an air inlet (60); a fuel inlet (58) positioned downstream of the air inlet (60); a duct (56) extending at least downstream of the fuel inlet (58) to define a fuel and air pre-mixing zone (62), that narrows to form an opening (64); and means for varying the flow of fuel/air mix from the pre-mixing zone (62) through the opening (64).

Abstract: A vernier duct blocker comprising a plurality of vanes each having a width and comprising a forward portion and an aft portion defining a plurality of gas paths each of the plurality of vanes being separated by a plurality of widths, and a rotatably movable ring interposed between the forward portion and the aft portion comprising a plurality of openings each having a width, wherein the width of one of the plurality of vanes differs from the width of another one of the plurality of vanes.

Abstract: A combustor for a gas turbine includes a combustor body having an aperture and a casing enclosing the combustor body and defining a passageway therebetween for carrying compressor discharge air. There is at least one injection tube for supplying an amount of the compressor discharge air into the combustor body and the injection tube is disposed between the aperture and through the casing. A collar is disposed at the passageway and surrounds the injection tube so that the injection tube passes through the collar. A gap is disposed between the collar and the injection tube. The collar has a plurality of openings. A method for quenching combustion in a gas turbine includes supplying a fixed amount of compressor discharge air into a body of a combustor of the gas turbine and supplying a variable amount of compressor discharge air into the body. The fixed amount of compressor discharge air is disposed concentrically around the variable amount of compressor discharge air.

Abstract: While commercial jet aircraft are capable of transporting large pay load economically, the same is not true for rockets. To solve this problem, a hybrid propulsion system is proposed for use in Horizontal Take-Off and Land (HOTOL) craft. The purpose is to maximized the use of ambient oxygen and minimize the use of cryogenic oxygen. At the core of the system is a jet engine whose after burner is modified to act as an evaporator. Liquid oxygen is pumped in, vaporized and ducted forward to the air intake through a gate. The gate is designed to control the mix of ambient oxygen and cryogenic oxygen going into the engine. It is also used as a hear shield to protect the engine from reentry temperatures.

Abstract: Apparatus for premixing fuel and air to provide a fuel/air mixture includes a mixing tube configured for receiving fuel and air, a mixing tube axis, and a mixing tube exit for discharging a fuel/air mixture. The apparatus further includes a mixture valve associated with the mixing tube exit and including inner and outer valve members that define an exit flow area. The defined exit flow area includes at least two segmented, substantially opposed area portions with respect to angular position about the mixing tube axis for directing the mixture flow, and at least one of the inner and outer valve members is movable relative to the other of said valve members to selectively vary the defined exit flow area with respect to time. In a gas turbine gas generator or engine application, a separate controllable combustion air valve can be used with a fuel valve to provide controlled fuel/air ratios for the mixture.

Abstract: An aerodynamically stabilized premixing burner includes a swirl generator for the production of a rotating combustion air flow, and a device for the introduction of at least one fuel into this combustion air flow. The burner is advantageously provided with a device for the introduction of an axial air flow into the center of the generated rotational flow. This axial air flow is controllable in order to affect the position and intensity of the flame-stabilizing recirculation zone at the burner mouth.

Abstract: A gas turbine combustor that controls flow rate of air flowing into a primary combustion zone for controlling a local fuel-air ratio comprises no sliding portion that is liable to cause sticking or biting of components operating in high temperature, thereby providing a simple, reliable and efficient combustor and a combustion control method thereof. The gas turbine combustor comprising a liner provided in a combustor case and a bypass duct provided in the liner and enabling a control of flow rate of air supplied into a primary combustion zone via a swirler by causing a portion of the air to pass through the bypass duct, further comprises a float, made of a magnetic substance, provided in the bypass duct so as to open and close the bypass duct by the position of movement of the float and an electromagnetic coil provided outside of the combustor case corresponding to the position of the float so as to move the float.

Abstract: Method and arrangement for providing a gas turbine (1) having a first compressor (2), a combustion chamber (16) and a first turbine (11), the turbine being adapted to drive the compressor via a first shaft (10a, 10b). The gas turbine also has a bleed valve (12) arranged upstream of the first turbine for conducting part of a gas compressed by the compressor past it during engine braking. The invention also relates to a method for engine-braking a gas turbine.

Abstract: There is provided a combustor to burn fuel, comprising a bypass passage connected to one side of the combustor to supply air into the combustor; and an annular passage provided around the combustor and connected to the bypass passage, wherein air supplied through the bypass passage passes in the annular passage in the circumferential direction, and is uniformly supplied into the combustor in the circumferential direction thereof through an opening which connects the combustor and the annular passage. Accordingly, compressed air passing through the bypass passage can be supplied uniformly into a tail portion of the combustor, and unevenness of temperature distribution in a cross section of the combustor tail portion can be reduced.

Abstract: It is the objective of the present invention to enable smooth rotation of the grid plate and normal operation of the bypass valve, regardless of the operational state of the gas turbine.

Abstract: A gas turbine engine includes: an air flow control system installed in an air intake path for introducing air to a compressor. The air intake path is located outside and upstream with respect to the compressor. The engine also includes intake air flow control means for controlling an intake air flow by operating the air flow control system according to a load of the engine so as to maintain an air-to-fuel ratio in the combustor within a proper range suited to suppress a discharge of an atmospheric pollutant.

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 turbojet engine with improved thrust and high-altitude capabilities. Arrangements are provided for injecting liquid oxygen or other oxidizer into the turbojet engine before the compressor section. Cooling the incoming air by the liquid oxygen reduces the air volume, which allows a fixed inlet to be matched to varying flow conditions, allowing a greater mass of air to be ingested by the compressor section and results in a lower compressor outlet temperature. Increased mass flow, combined with more fuel results in higher exhaust gas temperatures and greater thrust. The addition of oxygen to the inlet air flow allows the engine to operate at higher altitudes by preventing flameout due to rarefied air.

Abstract: A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors this impact is severe because emission levels are significantly dependent on the primary combustion zone flame temperature. The method of the present invention includes a step of changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for combustion and an air mass flow for cooling in order to ensure that flame temperature in a primary combustion zone of a combustor are maintained substantially the same whether the gas turbine engine is manufactured to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine.

Abstract: A gas turbine plant for limiting a sudden increase of load of the gas turbine, i.e., of the amount of fuel, and suppressing a stress of the turbine, or for maintaining a suitable fuel-air ratio is disclosed. The plant includes a controller comprising a section for calculating a governor signal for controlling the degree of opening of the fuel valve, based on a revolution speed of the gas turbine; and a section for calculating a load-limiting signal for following the governor signal, wherein when the governor signal decreases, the load-limiting signal is larger than it by a predetermined value, while when the governor signal increases, the increase rate of the load-limiting signal has a predetermined upper limit. The controller also comprises a limiting section, into which both signals are input, for limiting the upper value of the governor signal by using the load-limiting signal as an upper limit.

Abstract: A bypass air injection scheme for a combustor of a gas turbine. Combustor includes a body with an inner liner and a casing enclosing the body with a passageway defined therebetween. A predetermined amount of the compressor discharge air passing through the passageway is extracted through a manifold. A conduit feeds the extracted air into an injection manifold having a plurality of injection tubes for injecting the extracted air into the combustor bypassing the reactor. The injection tubes and the injection manifold are disposed in a substantially common axial plane.

Abstract: A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors this impact is severe because emission levels are significantly dependent on the primary combustion zone flame temperature. The method of the present invention includes a step of changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for combustion and an air mass flow for cooling in order to ensure that flame temperature in a primary combustion zone of a combustor are maintained substantially the same whether the gas turbine engine is manufactured to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine.

Abstract: A combustor having a combustion liner and at least one combustor orifice assembly, the combustor orifice assembly comprising a boss, an orifice plate that defines an orifice, the orifice plate having a bottom surface that is adapted to be received by the boss, and a retaining ring, whereby the orifice plate is retained between the retaining ring and the boss.

Abstract: A bypass air injection scheme for a combustor of a gas turbine. Combustor includes a body with an inner liner and a casing enclosing the body with a passageway defined therebetween. A predetermined amount of the compressor discharge air passing through the passageway is extracted through a manifold. A conduit feeds the extracted air into an injection manifold having a plurality of injection tubes for injecting the extracted air into the combustor bypassing the reactor. The injection tubes and the injection manifold are disposed in a substantially common axial plane.

Abstract: A fuel injector including a combustion air flow conduit, a fuel inlet and, swirlers to mix the air and fuel flowing therethrough, additionally comprising fluidic control diverters including at least one control port, such that flow of control air through said control port allows variation in the degree of flow resistance to which combustion air is subjected. For example, control air flowing through the control port may impart swirl to the combustion air flow from the inlet, thereby subjecting the combustion air flow to increased resistance. Alternatively a fluidic diverter may selectively divert the main flow to either the first or second sub-conduits, each sub-conduit subjecting combustion air to different degrees of flow resistance.

Abstract: There is provided a combustor to burn fuel, comprising a bypass passage connected to one side of the combustor to supply air into the combustor; and an annular passage provided around the combustor and connected to the bypass passage, wherein air supplied through the bypass passage passes in the annular passage in the circumferential direction, and is uniformly supplied into the combustor in the circumferential direction thereof through an opening which connects the combustor and the annular passage. Accordingly, compressed air passing through the bypass passage can be supplied uniformly into a tail portion of the combustor, and unevenness of temperature distribution in a cross section of the combustor tail portion can be reduced.

Abstract: A bypass air injection scheme for a combustor of a gas turbine. Combustor includes a body with an inner liner and a casing enclosing the body with a passageway defined therebetween. A predetermined amount of the compressor discharge air passing through the passageway is extracted through a manifold. A conduit feeds the extracted air into an injection manifold having a plurality of injection tubes for injecting the extracted air into the combustor bypassing the reactor. The injection tubes and the injection manifold are disposed in a substantially common axial plane.

Abstract: An aerodynamically stabilized premix burner essentially comprises a swirl generator (100) for generating a rotating combustion air flow (141), and means for introducing at least one fuel (142) into said combustion air flow. Furthermore, the burner is equipped with means (112) for introducing an axial air flow into the center of the generated rotational flow (144). According to the invention, this axial flow can be controlled, thus enabling an influence on the position and intensity of a flame stabilizing recirculation zone (123).

Abstract: A device (31) for connection of a nozzle (23) of a pre-mixing chamber (11) of a gas turbine, to a housing (12) of the pre-mixing chamber (11) comprises a flange (33) which clasps and retains the nozzle (23). The flange (33) is connected in a detachable manner to the housing (12) of the pre-mixing chamber (11), so as to render the nozzle (23) integral with the housing (12) of the pre-mixing chamber (11).

Abstract: A gas turbine combustion includes a combustion chamber mounted within an air supply manifold. The combustion chamber preferably has a fixed downstream portion and a telescopically-movable upstream portion, a burner head provided with a fuel injector, and a primary air inlet from the manifold into the combustion chamber defined between the burner head and an upstream end of the telescopically-movable upstream portion. Movement of the upstream portion of the combustion chamber towards the burner head serves to restrict the primary air inlet while opening a secondary air inlet from the manifold into the combustion chamber downstream of the burner head. Movement of the upstream portion of the combustion chamber away from the burner head serves to open the primary air inlet while restricting the secondary air inlet.

Abstract: A flow controller (5) for supplying air to a combustor and a combustor incorporating the same are disclosed. The flow controller comprising a conduit (6, 7, 8) and a control port (9), the conduit including a main section (8) dividing into at least two secondary sections (6, 7) at a junction and the control port being positioned in the conduit adjacent to the junction. In one embodiment, the control port is connected to a reservoir (10) wherein, in use, a change in the flow rate of a main airflow flowing through the main section of conduit causes a control airflow to flow either into or out of the control port whereby the main airflow is selectively diverted into one or other of the secondary sections of conduit. The main airflow may coanda around a surface of the main section. The control port may also be connected to the conduit further upstream of the junction so as to form a control loop (16). The main section of conduit may comprise a convergent-divergent duct.

Abstract: A control and method for arresting flashback in a gas turbine engine combustion system having a venturi for delivering a mixture of air and fuel to a combustion chamber and a valve for controlling the amount of air flowing to the venturi. The control and method includes a flashback detection routine, a valve position trim routine, and a reference flame temperature adjustment routine. The flashback detection routine detects a flashback in the venturi by comparing the temperature at the venturi to the temperature of the air entering the valve. The valve position trim routine receives this flashback signal and in response causes the valve to open until the flashback is arrested. Finally, to prevent the flashback from recurring, the reference flame temperature adjustment routine adjusts a reference flame temperature in the control system so as to prevent the valve from returning to the position at which the flashback occurred.

Abstract: A combustion chamber assembly (22) comprises a primary, a secondary and a tertiary fuel and air mixing ducts (54,78,98) to supply fuel and air to primary, secondary and tertiary combustion zones (40,42,44). Each of the primary, secondary and tertiary fuel and air mixing ducts (54,78,98) comprises a pair of axial flow swirlers (56,60,80,84,102,104) arranged coaxially to swirl the air in opposite directions and fuel injectors (62, 86,106) to supply fuel coaxially of the respective axial flow swirlers (56,60,80,84,102, 104). Valves (66,90) are provided to control the supply of air to the primary and the secondary fuel and air mixing ducts (54,78) respectively. A duct (122,116) is arranged to supply cooling air and dilution air to the combustion chamber (22). The amount of air supplied to the primary, secondary and tertiary fuel and air mixing ducts (54,78,98) and the duct (122,116) is measured.

Abstract: Dilution sleeves are provided in radially aligned openings in the combustion liner and flow sleeve of a combustor for a gas turbine. The sleeves have a flange for seating on a collar of the flow sleeve about the opening therethrough enabling the dilution sleeve to extend through the aligned openings. A cover is removably mounted on the outer casing and a spring bears between the cover and the dilution sleeve flange to maintain the dilution sleeve in the openings. Dilution sleeves having different cross-sectional flow areas may be provided in lieu of initially installed dilution sleeves upon comparing measured emission levels with desired emission levels and ascertaining the desired increase or decrease in cross-sectional flow area through the dilution sleeves.

Abstract: Gas turbine combustor by-pass valve device for opening and closing a by-pass valve is improved to uniformly control air supply into a combustion area for appropriate combustion. A drive shaft 21 for opening and closing a driven by-pass valve 20 is provided in turbine casing 010 where an outside obstruction is located which would interfere with a projecting drive shaft 09. The driven shaft 21 has a short length to be provided in the turbine casing 010. An adjacent main driving shaft 23 for opening and closing main driving by-pass valve 22 is provided adjacent to the driven shaft 21. Link mechanism 26 is provided between the adjacent main driving shaft 23 and the driven shaft 21 so that rotary movement of adjacent main driving shaft 23 driven by outside drive means via the drive shaft 09 is transmitted to the driven shaft 21 and, thus, to the driven by-pass valve 20.

Abstract: A gas turbine engine comprises a centrifugal compressor (4), an air diffuser (8), a heat exchanger (10), combustion apparatus (12), and first and second turbines (14,18). The combustion chamber assembly (22) comprises a primary, a secondary and a tertiary fuel and air mixing ducts (54,78,98). The compressor (4), diffuser (8), primary and secondary fuel and air mixing ducts (54,78) and turbines (14,18) all comprise means (6,8,16,20) for varying the mass flow area at their inlets such that in operation the amount of air mass through each component may be independently variable. Under part power conditions the mass flow is reduced and under full power conditions the mass flow is increased thereby maintaining a substantially constant gas cycle throughout the engine.

Abstract: A combustor for a gas turbine engine uses compressed air to cool a combustor liner and uses at least a portion of the same compressed air for combustion air. A flow diverting mechanism regulates compressed air flow entering a combustion air plenum feeding combustion air to a plurality of fuel nozzles. The flow diverting mechanism adjusts combustion air according to engine loading.

Abstract: A variable length pre-mixer assembly comprises an upstream end for receiving compressed air from a compressor and a downstream end disposed in flow communication with a combustor. Pre-mixer assembly comprises an upstream forward clamp, a swirler assembly having a plurality of circumferentially spaced apart vanes disposed adjacent the upstream end for swirling compressed air channeled therethrough. An elongate centerbody has a first end joined to and extending through the swirler and a second end disposed downstream therefrom. A downstream fuel nozzle shroud has an outlet in flow communication with the combustor. Additionally, at least one removably disposed fuel nozzle spacer is alternatively disposed between a first position between the upstream forward clamp and the swirler assembly and a second position between the swirler assembly and the downstream fuel nozzle so as to change the relative position of the swirler assembly and alter the pre-mixer assemblies acoustical resonance characteristics.

Abstract: A method and device are provided to enable optimizing combustion conditions of a continuous combustion device to produce low emissions of nitric oxide, carbon monoxide and hydrocarbons at all operative conditions. The continuous combustion device includes a slidable baffle to regulate, according to power levels, not only an airflow directly into a primary combustion zone and a secondary combustion zone but also an airflow into a fuel/air premix device to maintain the fuel/air ratio in the primary combustion zone optimized both at an average level and in local areas. Such that, low objectionate or harmful emissions can be reached without performance penalties of the combustion device, such as anti-ignition, flashback or flameout.

Abstract: Disclosed is a premix injector for mixing air and fuel and injecting the mixture into a combustion chamber. The premix injector includes an air blast fuel nozzle, a venturi, and a premix chamber. The venturi extends from an inlet to an exit which is in fluid communication with a combustion chamber. Importantly, the venturi has a jet deflector along its interior wall near its exit and on the side of the venturi nearest the exit of the combustor.

Abstract: Gas turbine combustor by-pass valve device for opening and closing by-pass valve is improved to control uniformly air supply into combustion area for appropriate combustion. Drive shaft 21 for opening and closing driven by-pass valve 20 is provided in turbine casing 010 where outside obstruction is located to interfere with projecting drive shaft 09. The driven shaft 21 is made in short length to be provided in the turbine casing 010. Adjacent main driving shaft 23 for opening and closing main driving by-pass valve 22 is provided adjacently to the driven shaft 21. Link mechanism 26 is provided between the adjacent main driving shaft 23 and the driven shaft 21, thereby rotary movement of adjacent main driving shaft 23 driven by outside drive means via the drive shaft 09 is transmitted to the driven shaft 21 and thus to the driven by-pass valve 20.

Abstract: The invention applies to an air bypass control device which can bypass a portion of the compressed air in the space within the casing into the tail pipe connected to a combustion chamber via a control valve and a bypass channel. The invention includes a valve mechanism including a flat sliding ring, and a valve operating mechanism. The valve mechanism intersects a number of bypass air channels each of which is connected to a pipe located in the space inside the casing. A number of openings are arranged in the flat sliding ring for bypassing the air to the bypass air channels. The valve operating mechanism, one end of which is connected to the flat sliding ring, causes the flat sliding ring to rotate back and forth. When the operating mechanism rotates the flat sliding ring, the openings in the flat sliding ring rotate so as to coincide with or move away from the openings of the bypass channels.

Abstract: Gas turbine combustor by-pass valve device for opening and closing a by-pass valve is improved to uniformly control air supply into a combustion area for appropriate combustion. A drive shaft 21 for opening and closing a driven by-pass valve 20 is provided in turbine casing 010 where an outside obstruction is located which would interfere with a projecting drive shaft 09. The driven shaft 21 has a short length to be provided in the turbine casing 010. An adjacent main driving shaft 23 for opening and closing main driving by-pass valve 22 is provided adjacent to the driven shaft 21. Link mechanism 26 is provided between the adjacent main driving shaft 23 and the driven shaft 21 so that rotary movement of adjacent main driving shaft 23 driven by outside drive means via the drive shaft 09 is transmitted to the driven shaft 21 and, thus, to the driven by-pass valve 20.

Abstract: A lean-premix-prevaporization combustion system has a combustion chamber and a premixed injector that injects a hot gas, formed from the ignition of a lean mixture of air and fuel, into the combustion chamber. A pilot injector is mounted to the wall of the combustion chamber and injects fuel into the combustion chamber. Upon entering the combustion chamber this fuel ignites to form a fuel rich zone which stabilizes the flame in the combustor.

Abstract: A gas turbine engine carburetor includes a fuel injector and a cooperating air swirler for injecting fuel and air into a combustor. The fuel injector includes a hollow body joined to a supporting stem for receiving fuel therein for flow through an injector tip slidingly mounted to the injector body for movement relative thereto. The air swirler surrounds the injector tip and is spaced form the injector body to define an air inlet, and is spaced from the injector tip to define an air outlet. A spring operatively engages the injector body and the injector tip and is preloaded for biasing the injector tip to an initial position. The spring is sized so that increasing pressure of the fuel in the injector body further loads the spring for moving the injector tip from the initial position to a displaced position, with movement of the injector tip modulating airflow through the swirler for in-turn modulating the ratio of discharged fuel and air.