Abstract: A system includes a first pump connected to an inlet line and connected to a first outlet line for supplying a first sub-system over a first pressure schedule. A second pump is connected to the inlet line and connected to a second outlet line for supplying a second subsystem over a second pressure schedule. A backup selector is in fluid communication with the first and second outlet lines. The backup selector is configured to switch to a first backup mode to supply the first sub-system from the second pump upon failure of the first pump. The backup selector is configured to switch to a second backup mode to supply the second sup-system from the first pump upon failure of the second pump.

Abstract: In accordance with one exemplary embodiment of the present disclosure, a method for providing overspeed protection for a gas turbine engine is provided. The gas turbine engine may include an engine core and an engine shaft. The method may include determining an overspeed condition of the engine. The overspeed condition may be indicative of an above normal rotational speed of the engine shaft. The method may also include reducing an airflow through the engine core of the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.

Abstract: A fuel split control arrangement is provided. The arrangement includes a staged cooling flow control valve and cooling check valve. The staged cooling flow control valve and cooling check valve is connected between the primary and secondary tips of a nozzle in a turbine engine. The staged cooling flow control valve and cooling check valve includes a valve member arrangement operable to prevent fuel flow from the secondary fuel supply manifold to the secondary tip and simultaneously allow fuel flow from the secondary fuel supply manifold to the primary tip such that the primary tip receives fuel flow from both the secondary fuel supply manifold and the primary fuel supply manifold.

Abstract: A fuel system for a gas turbine engine, which includes a combustor section and an actuator, includes a fuel source, a combustor system, and an actuation system. The combustor system includes a combustor pump that is fluidly connected to the fuel source and to the combustor section, with the combustor pump being mechanically connected to and powered by an electric motor. The actuation system includes an actuator pump that is fluidly connected to the fuel source and to the actuator, with the actuator pump being mechanically connected to and powered by a gearbox or an electric motor.

Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique reheat system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and reheat systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: A burner (1) for a gas turbine includes a duct (2) enclosing a plurality of vortex generators (3) and, downstream of them, a lance (5) provided with nozzles (6) for injecting a gaseous fuel. The burner (1) also includes a mixer (7) for diluting and mixing the gaseous fuel with air to form a mixture. The mixer (7) is connected to the nozzles (6) for feeding them with the mixture. A method includes feeding the gaseous fuel in the burner (1).

Abstract: A fluid flow control system includes a valve, in which a control element regulates flow through a metering orifice. A further control element regulates flow through an orifice downstream of the orifice and is responsive to the pressure downstream of the orifice and to an opposing control pressure on a line. The element is positioned in accordance with the pressure in a chamber controlled by an electrical valve. The pressure in line is set to provide a required pressure drop across the orifice.

Abstract: A fuel control system for reheat burners of a gas turbine engine has a plurality of metering valves for respective burners, and throttle valves in series with the respective metering valves. A pressure regulating valve is provided for introducing pressurized fuel into fuel manifolds downstream of the respective throttle valves when the metering and throttle valves are shut. The pressure regulating valve also acts to relieve pressure in low pressure parts of the system when the latter is closed down and to prevent excessive temperature rise at the inlet of a fuel supply pump. The metering valves include pressure return ports which communicate with the metering valve outlets when those valves are shut.

Abstract: An afterburner on a turbofan or fan-jet engine contains a fuel system having a fuel control delivering fuel to a plurality of injection zones. As the power lever is advanced, for afterburner operation, fuel is delivered sequentially to the afterburner through different zones until it reaches the last zone. The last zone comprises a set of two axially spaced sprayrings located adjacent the outer wall of the afterburner, one spraying being located upstream of the other spraying. The downstream sprayring has a splash plate located radially inwardly from each nozzle to provide a barrier to the fuel spraying inwardly for directing a portion of the spray downstream over the outward radial portion of the afterburner near the afterburner wall.

Abstract: This invention serves to improve augmentor effectiveness of a turbine fan engine that has a bypass airstream and a core stream by synthesizing signals indicative of both the airflow of the bypass stream and core stream and directly scheduling fuel/air ratio for both streams and ascertaining the desired fuel flow to be used to meter fuel to each of the streams.

Abstract: For improved thrust responsiveness and smooth transition of the various zones of an augmentor of an augmented jet engine powered aircraft, the time to prefill the fuel manifolds of the zones are calculated from preselected parameters so as to be on line upon light-off. The throttle lever signal is rate limited so that the preascertained manifold volume of each zone divided by the zone filling fuel flow produces a signal indicative of the time to open the normal fuel fill valve to prefill the manifold at the proper time and in the right sequence using a rate limited throttle lever signal.

Abstract: A turbine is stabilized in high speed, high altitude flight conditions by reducing the maximum augmenter fuel/air ratio in response to certain pressure and temperature conditions. Temperatures and pressures indicative of those at the combustor are sensed and the augmenter fuel schedule is accordingly modified to a level which provides reduced fuel/air ratios and stable burning conditions.

Abstract: A thrust augmented twin spool turbofan engine system to control instability at high altitude, low Mach number conditions wherein an engine electronic control monitors engine inlet temperature, engine burner pressure and Mach number, and inhibits fuel flow to the outermost augmentor segment when the engine inlet temp drops below 25.degree. F, when engine burner pressure drops below 120 psia or when the Mach number drops below 0.4. When fuel flow to the outermost augmentor is inhibited, upmatch logic modifies the variable nozzle AJ trim signal closed 8% and the power level angle trim signal up 4.degree..

Abstract: A fuel distributor valve for splitting and proportioning fuel feeding more than one set of fuel nozzles of a turbine type power plant is improved upon by adding thereto means to prefill the secondary nozzle and its attendant manifold and fuel passages immediately preceding actuation.

Abstract: This invention relates to a fuel distribution valve for a turbine type power plane capable of supplying fuel to a set of primary nozzles and proportioning the flow to a set or sets of secondary nozzles upon initiation of a command signal which may be manifested by the fuel control.

Abstract: In order to detect effective operation of the reheat system of a turbo-jet ngine, a detection device is provided which is adapted to produce an output signal when such effective operation is sensed. The detection device includes means for sensing the pressure of the gas flow in the engine at a pair of preselected positions and feeding signals to processing means related to the pressures so sensed. When there is a preselected difference between the two signals, the output signal referred to above is generated.

Abstract: A control circuit arrangement for a gas turbine engine has first and second identical control circuits which are responsive to groups of input signals to provide nominally identical first and second output signals. It is arranged that input signals to the first control circuit are nominally identical with corresponding input signals to the second control circuit. Means are provided, responsive to malfunction of either one of the first and second control circuits, to render the malfunctioning circuit inoperative and to render the other of the control circuits operative. A third control circuit is responsive to at least one pair of corresponding input signals to the first and second circuits, to provide a third output signal to the engine. The first, second and third output signals do not control the engine reheat system, and the arrangement may include a fourth control circuit for controlling this reheat system.