Abstract: A combustion control system for a turbine engine is disclosed. The combustion control system includes a fuel injector having a main fuel supply and pilot fuel supply coupled to a combustor of the turbine engine. The combustion control system also includes a sensor coupled to a transfer tube. The transfer tube is fluidly coupled to the combustor, and the sensor is configured to detect a pressure pulse in the combustor. A semi-infinite coil is also coupled to the transfer tube. The combustion control system also includes a controller electrically connected to the sensor. The controller is configured to compare an amplitude of the pressure pulse within a frequency range to a threshold amplitude, and adjust the pilot fuel supply in response to the comparison.

Abstract: An engine air supply system includes an air source, which is a gas turbine engine in one example. A component, such as an environmental control system component, is interconnected to the air source by a conduit that includes a supply flow direction. A check valve is arranged in the conduit. The check valve includes a valve portion moveable in the supply flow direction from a closed position to an open position. The closed position is arranged at an acute angle relative to the supply flow direction. The check valve includes first and second valve portions that are hemi-elliptical in shape. The first and second valve portions are non-planar and arranged approximately 90 degrees apart when in the closed position. The first and second valve portions move toward one another from the closed position to the open position.

Abstract: A gas turbine engine system includes a first nozzle section associated with a gas turbine engine bypass passage and a second nozzle section that includes a plurality of positions relative to the first nozzle section. In at least one of the positions, there is a gap between the first nozzle section and the second nozzle section. A movable door between the first nozzle section and the second nozzle section selectively opens or closes the gap.

Abstract: A combustor of gas turbine engine, including: a fuel spray portion that sprays fuel to create a diffusion combustion region in a combustion chamber, the fuel spray portion including a fuel atomizing portion that atomizes the fuel, and a diffusion passage portion disposed downstream of the fuel atomizing portion, the diffusion passage portion having a spreading trumpet-like shape and diffuses the fuel and the air; a pre-mixture supply portion that supplies a pre-mixture gas including the fuel and air to create a pre-mixture combustion region in the combustion chamber, the pre-mixture supply portion being positioned concentrically with the fuel spray portion to surround the fuel spray portion; and a fuel diffusion restraining member disposed on an inner circumferential face of the diffusion passage portion for restraining a diffusion of injected fuel by separating a stream of the injected fuel away from the inner circumferential face.

Abstract: A method and device for adding special substances to the gaseous outflow of the jet engine in order to create a “virtual wall” of increased pressure zone behind the jet engine nozzle which can serve as a support for the jet engine gas outflow to push against, thus increasing the thrust power of the jet engine. This increase in acceleration power results in the accelerated movement of the jet engine equipped vehicle or higher fuel efficiency. A device that adds the special substances to the gaseous outflow is proposed. Characteristics of the special substances, which if added into the jet engine gaseous outflow may create a “virtual wall” of increased pressure zone behind the jet engine, are proposed.

Abstract: A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction.

Abstract: A system and method for accurately supplying fuel flow to a gas turbine engine from a fuel metering pump regardless of variations in operating conditions of the fuel metering pump. The system determines an updated flow characteristic curve for an electrically powered positive displacement pump that is configured to supply fluid via a valve that is configured to open at a predetermined fluid inlet pressure. Electrical current is supplied to the pump to thereby cause the pump to supply the fluid to the valve. The electrical current supplied to the pump is monitored to determine when the valve opens, and one or more points on the updated flow characteristic curve are determined based on the determination of when the valve opens.

Abstract: An axial flow positive displacement compressor has an inlet axially spaced apart and upstream from an outlet. Inner and outer bodies have offset inner and outer axes extend from the inlet to the outlet through first and second sections of a compressor assembly in serial downstream flow relationship. 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. The helical blades have first and second twist slopes in the first and second sections respectively. The first twist slopes are less than the second twist slopes. An engine including the compressor has in downstream serial flow relationship from the compressor a combustor and a high pressure turbine drivingly connected to the compressor by a high pressure shaft.

Abstract: A bushing for assembling an exhaust duct liner with an exhaust duct in a gas turbine engine comprises a body, a bushing opening and a first tab. The body is insertable into a duct opening in an exhaust duct. The bushing opening receives a shaft of a liner fastener, wherein the fastener is connectable with a duct liner. The first tab extends into the duct opening and prevents rotation of the liner fastener.

Abstract: The invention relates to a device for injecting a mixture of air and fuel into a combustion chamber of a turbomachine where the supply of air is improved. The invention relates more particularly to a new type of sliding bushing.

Abstract: A fuel manifold for a gas turbine engine having a first peripheral surface having a first channel defined therein and a second peripheral surface having a second channel defined therein, each of the first and second channels being sealingly enclosed to define a corresponding conduit.

Abstract: A water treatment and pressurization system for the adiabatic cooling of comburent air destined for plants using gas turbines (15), run by measuring, control and regulation units, comprising a lifting and pressurizing station (16) of vaporization water at a varying flow-rate for a maximum operating pressure, preferably up to 120 bar, associated with a series of nozzles (20) situated on nozzle-holder ramps (12) downstream of which there is at least one housing unit (44) for humidity and temperature probes (52-55). The lifting station (16) comprises at least two pumps (22) with relative auxiliaries devices connected to nozzle-holder collectors (39).

Abstract: A fuel-flow-rate control device, a power generation system, and a fuel-flow-rate control method which can prevent overshooting of a gas turbine output (gas turbine inlet temperature) and which can improve power generation efficiency are provided. The fuel-flow-rate control device includes a computing portion for obtaining a state quantity relating to operating conditions and temperature conditions of a gas turbine as an input signal and computing a fuel-flow-rate command for controlling a fuel flow rate supplied to a combustor based on the above input signal, and a second selection circuit for setting the above fuel-flow-rate command to be not more than a fuel-flow-rate upper limit. The fuel-flow-rate upper limit is a fuel flow rate at which the gas turbine inlet temperature is set to be not more than a predetermined upper temperature limit.

Abstract: It is known that overshoot in fuel flow rate as a result of compensating for engine heat soak effects can create transient over values in desired thrust parameters. These over values may be displayed and/or utilised in other engine control systems, and although transient may create problems within the engine and apprehension with a user. By adjusting the normally calculated fuel flow rate to a fuel regulator by the introduction of a fuel flow adjustment dependent upon a variable which is related to heat soak effects it is possible to reduce the extent of overshoot as well as the transient time period of that overshoot to ongoing operational state. The variable used may be direct or indirect and will generally utilise a temperature sensor within the engine and/or other engine control procedures which may be extrapolated from such sensor values to provide a variable for heat soak compensation.

Abstract: A system for driving first and second accessory machines of a double-bodied turbine engine with an LP shaft and an HP shaft is disclosed. The system includes a first power train disposed between the shaft of the HP rotor and the first machines, which mechanically drives the first machines, and a first coupling means and a second power train between the shaft of the LP rotor and the second machines arranged so as to drive the said second machines. The system also includes a second coupling means between the first power train and the second power train allowing the second accessory machines to be driven by the shaft of the HP rotor, particularly when the engine operates at high speeds. The system may include a gearbox with at least two speed ratios and the first coupling means may be arranged to selectively couple one or other of the two ratios or else to decouple the mechanical transmission from the shaft of the LP rotor.

Abstract: A rocket engine system includes a combustion chamber defining a centerline axis, an oxidizer supply, a first fuel delivery circuit connected to a fuel supply, a second fuel delivery circuit connected to the fuel supply, and an injector assembly positioned at the combustion chamber. The injector assembly includes a faceplate having a plurality of openings therethrough, a first injector element connected to the first fuel delivery circuit and extending into one of the openings in the faceplate, and a second injector element connected to the second fuel delivery circuit and extending into another of the openings in the faceplate. Annular oxidizer outlets are formed at the openings in the faceplate and connected to the oxidizer supply to deliver oxidizer to the combustion chamber.

Abstract: A rotary cup fuel injector for use in a gas turbine engine, the rotary cup injector being rotatably secured to the rotor shaft and positioned radially inward of the combustor, the rotary cup injector having a front face with a parabolic shape and a rear face with a slanted and flat shape. The front and rear faces of the injector form a thin film of fuel on the surfaces and—because of the high rotational speed—produce fine droplet's of fuel to be injected into a combustion chamber. The two faces inject fuel into two combustion zones of the combustor.

Abstract: The arrangement comprises a fan by-pass duct located within the nacelle and having an inlet and an outlet. The outlet is generally oriented substantially radially and at an intermediary location along the nacelle. The nacelle has an aft section with an initially convex and substantially outwardly extending surface adjacent to the outlet of the fan by-pass duct. The surface of the aft section decreases in curvature and becomes concave towards a rear end of the engine.

Abstract: An air storage plant comprises a storage volume for a pressurized storage fluid, a storage fluid expansion machine and a generator which is arranged with the expansion machine on a common power train. During the start up of the air storage plant, the generator is operated at least temporarily electromotively in order to assist the acceleration of the rotor of the expansion machine. This allows a more rapid acceleration of the expansion machine to the rated rotational speed and, consequently, earlier synchronization and an earlier power output than acceleration caused solely by the storage fluid flowing through.

Abstract: A method enables a gas turbine engine to be operated. The method includes directing fluid flow from a source into an inlet of a valve, channeling the fluid flow entering an inlet portion of the valve towards an outlet portion of the valve such that a direction of the fluid flow is changed within the inlet portion, and controlling the amount of fluid flow entering the outlet portion of the valve by selectively positioning a valve disk coupled within the inlet portion of the valve by a valve disk axle. The method also comprises channeling the fluid flow from the inlet portion of the valve through the outlet portion of the valve and into a fluid supply pipe, wherein the valve outlet portion has a substantially right cylindrical shape such that a direction of fluid entering the body outlet portion remains substantially constant therethrough.