Abstract: Disclosed herein is a “real time” Time Limited Dispatch (TLD) fault management system and method for evaluating the operational suitability of an engine's electronic control system. The TLD system disclosed herein uses a software algorithm to compute or predict the probability of mission success for a given upcoming mission length (e.g., two hours) and the time remaining to repair control system faults before dispatch is disallowed or the flight suspended, regardless of the probability of success.

Abstract: A gas turbine plant includes a combustion section, a turbine section, an exhaust section, a temperature detecting unit, and a monitoring unit. The combustion section combusts fuel using air to generate combustion gas. The turbine section is driven with the combustion gas from the combustion section. The exhaust section is connected to the turbine section to exhaust the combustion gas from the turbine section. The temperature detecting unit is provided in the exhaust section to measure a temperature of the combustion gas. The monitoring unit generates a warning signal based on a tolerable level and data corresponding to a temporal change of the temperature measured by the temperature detecting unit to indicate an extraordinary state of the gas turbine plant.

Abstract: A gas turbine engine having an exhaust casing that includes a plurality of fairings that shield struts that are affixed to and extend between concentric rings. Each fairing has a moveable tail section that is adjusted during turbine operation to change the angle of attack of the exhaust gases to minimize vortex shedding and the corresponding vibrations that result.

Abstract: The present invention relates to a gas storage power plant (1) with a gas store (8), a turbogroup (2) and a gas supply line (9) which leads from the gas store (8) to the turbogroup (2). A gas supply control device (12) is arranged in the gas supply line (9). So that a gas flow cam be provided, even in an emergency, the gas supply control device (12) has a main line (14) and a bypass line (19). The main line (14) forms a section of the gas supply line (9). In the main line (14) is arranged a main valve arrangement (15) which shuts off the main line (14) in an emergency. The bypass line (19) bypasses the main valve arrangement (15). In the bypass line (19) is arranged a bypass valve arrangement (20) which opens the bypass line (19) in an emergency.

Abstract: A gas turbine plant includes a combustion section, a turbine section, an exhaust section, a temperature detecting unit, and a monitoring unit. The combustion section combusts fuel using air to generate combustion gas. The turbine section is driven with the combustion gas from the combustion section. The exhaust section is connected to the turbine section to exhaust the combustion gas from the turbine section. The temperature detecting unit is provided in the exhaust section to measure a temperature of the combustion gas. The monitoring unit generates a warning signal based on a tolerable level and data corresponding to a temporal change of the temperature measured by the temperature detecting unit to indicate an extraordinary state of the gas turbine plant.

Abstract: A bearing assembly for a gas turbine engine rotor includes a paired race, a bearing, a mounting joint, and a plurality of mechanical fuses. The paired race includes an outer race and an inner race. The bearing is between the inner and outer races, and is configured to support the rotor on a support frame. The mounting joint includes a joint inner race and a joint outer race. At least one of the joint inner race and the joint outer race includes a spherical surface. The mounting joint is configured to reduce dynamic loads to the gas turbine engine structure and static bending to the rotor. The plurality of mechanical fuses extend through at least one of the joint inner race and the joint outer race.

Abstract: A system and a method for detecting gas turbine engine hot section condition using temperature measurements during engine operation. The system comprises a sensing unit for sensing a temperature distribution across a hot combustion gas stream generated by a gas turbine engine combustor. A signal processor receives temperature signals from the sensing unit and generates a combustor malfunction signal when the difference between a maximal temperature and a minimal temperature of the sensed temperature distribution is greater than a predetermined acceptable delta value.

Abstract: An improved air turbine starter that includes fluid flow control devices. The devices may be check valves, for example normally open check valves. The check valves may be located in fluid flow paths between the starter and the gearbox to which it is mounted. The starter may also include a ring seal about the output shaft to restrict fluid flow over the shaft.

Abstract: A single-shaft combined plant having an emergency shut-off oil system is provided. The emergency shut-off oil system is constituted such that when a steam governing valve tripping electromagnetic valve is opened, only a steam turbine is stopped; a master tripping electromagnetic valve is connected to a fuel gas control valve emergency shut-off oil line, a fuel oil control valve emergency shut-off oil line, and a steam governing valve emergency shut-off oil line via check valves; and when the master tripping electromagnetic valve is opened, both the steam turbine and a gas turbine are stopped. Thus, only the steam turbine can be stopped. Even if a tripping valve provided on the fuel gas control valve emergency shut-off oil line or the fuel oil control valve emergency shut-off oil line does not open because of a breakdown, the gas turbine can be stopped reliably.

Abstract: A compressor in a multi-stage axial form of construction, with a rotor which is mounted overhung and includes a plurality of moving-blade rings on blade carriers connected to one another, and with a blade arrangement, in which the moving-blade ring of the first stage forms the blade cascade arranged furthest upstream. At least one of the rotating blade carriers is produced in an MMC form of construction, that is to say as a metal component fiber-reinforced at least in regions, and the rotary bearing absorbing the large part of the radial loads occurring on the rotor has a predetermined breaking point which, when a defined radial load is exceeded, allows a radial shift of the rotor, with the result that the latter brushes against the stator.

Abstract: A method for controlling an aircraft engine using a control system enables an engine to be operated at low power while hail is ingested. The control system includes a processor coupled to the aircraft engine. The method comprises receiving a plurality of sensed inputs from the aircraft engine, receiving current engine environmental operating conditions, determining a reference value for a controlled variable from a fuel flow schedule, generating a fuel-air-ratio for the reference value based on current engine environmental operating conditions, and enriching combustor fuel staging in response to the fuel-air-ratio.

Abstract: A compressor casing with a volute-shaped flow duct is fastened by means of a rigid fixing arrangement to the bearing casing of the turbomachine, with simple and low-cost means in such a way that the emergence of fragments of a burst compressor impeller from the compressor casing can be prevented. The compressor casing has an outer spiral casing, which surrounds a duct section of the flow duct deflected towards the outside into the radial direction (B), and an inner casing insert piece, which is provided in the radial direction (B) between the spiral casing and the compressor impeller and whose inner contour, together with the outer contour of the hub of the compressor impeller, forms the duct section of the flow duct extending essentially in the axial direction (A).

Abstract: A thrust reverser actuator lock mechanism comprising a rotatable shaft, rotation of which in one direction from a rest position drives an associated thrust reverser from a stowed position towards an operative position in use, retractable abutment means having a rest position abutting an element rotatable with the shaft to prevent rotation of the shaft, resilient means urging said abutment means to said rest position, and, mechanical latch means sensitive to the speed of rotation of said shaft for latching said abutment means in a retracted position against the action of said resilient means when the rotational speed of said shaft exceeds a predetermined value.

Abstract: For regulating engine exhaust and for environmental reasons, aircraft users are restricted from expelling engine fluids from engines onto airport ramps. All such fluid must be collected and subsequently burned or properly disposed of. The present invention installs witness drain valves in the drain lines between seal cavities and environmental collector tank. The witness drain valves have a small reservoir that will retain a known volume of fluid. As fluid passes from a leaking seal to the collector tank, a small sample is captured in the witness drain valve. Once the witness drain valve reservoir is full, the leaking fluid then flows on to a collector tank, which is also provided. During regular engine maintenance, technicians push on a spring loaded drain valve located on the witness drain valve reservoir. If fluid is detected, the seal is beginning to leak, and corrective maintenance may be scheduled while the leak rate is still within operational limits.

Abstract: A gas turbine system comprises an alarm signal calculation circuit, a shutdown calculation circuit and a flashback-error signal prevention calculation circuit. The alarm signal calculation circuit, the shutdown calculation circuit and the flashback-error signal prevention calculation circuit are integrated in a combustion monitoring device for monitoring combustion condition of combustion gas in a gas turbine-combustor.

Abstract: Flame arrestor to cover aircraft engines made up of one ventilation wire mesh (6), one upper metallic plate (9) where wire mesh sits (6) on the edges of a circular hole (10) and a wall (25) which is located next to a chamfer (26) placed at the edge of a central hole (5) existing in the platform (3). On the lower side of the thin composite wall (25) there is a ring (16) with outer flange whose width coincides with that of the wall, and another flanged ring (14) coinciding in height with the chamfer (26), creating an interior cavity (27) where gases are conducted and accumulated. All these elements are joined together by some bolts (22) that go through them and finish with a lower metallic plate (12) and an octagonal shaped part (19) separated by a specific distance established by the appropriate elements.

Abstract: A single-shaft combined plant having an emergency shut-off oil system is provided. The emergency shut-off oil system is constituted such that when a steam governing valve tripping electromagnetic valve is opened, only a steam turbine is stopped; a master tripping electromagnetic valve is connected to a fuel gas control valve emergency shut-off oil line, a fuel oil control valve emergency shut-off oil line, and a steam governing valve emergency shut-off oil line via check valves; and when the master tripping electromagnetic valve is opened, both the steam turbine and a gas turbine are stopped. Thus, only the steam turbine can be stopped. Even if a tripping valve provided on the fuel gas control valve emergency shut-off oil line or the fuel oil control valve emergency shut-off oil line does not open because of a breakdown, the gas turbine can be stopped reliably.

Abstract: A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) has an upstream portion (56), a blade containment portion (54) and a transition portion (58). The upstream portion (56) has a flange (52) connecting the metal containment casing (40) to an axially adjacent casing. The upstream portion (56) of the casing (40) has a greater diameter (D1) than the diameter (D2) of the blade containment portion (54) and the blade containment portion (54) has a greater thickness (T2) than the thickness (T1) of the upstream portion (54). The transition portion (58) connects the blade containment portion (54) and the upstream portion (56) to transmit loads from the blade containment portion (54) to the upstream flange (42).

Abstract: This invention relates to a method for the detection of a shaft failure in a turbomachine with the object of initiating thereupon an appropriate speed-limiting action, more particularly a rapid fuel shut-off on an aero gas-turbine system, in which a torque-exerting turbine rotor and a torque-recipient unit are connected via the shaft (3) to be monitored for failure, said shaft being supported at its ends in at least two roller bearings (6, 7). In this method, the rotational frequencies (fn1, fn2) of the two shaft ends of the shaft compared with each other continually and essentially in real time, with a failure of the shaft (3) inferred if the rotational frequency (fn2) of the roller bearing (7) on the side of the turbine rotor exceeds the rotational frequency (fn1) of the roller bearing (6) on the side of the torque-recipient unit.

Abstract: A fuel system comprising a low pressure fuel pump having an outlet which is connected to an inlet of a high pressure pump arranged, in use, to supply fuel to an engine. The fuel system her comprises at least one actuator controlled by a servo-valve, wherein the servo-valve has a high pressure connection connected to the high pressure side of the high pressure pump and a low pressure connection connected upstream of the outlet of the low pressure pump.

Abstract: A flameout detection system for an engine that facilitates detection of flameout in the engine in a cost-effective and reliable manner is described. A method implemented by the device includes the steps of detecting a rate of change of gas generator speed, also described as engine deceleration rate, and declaring a flameout if a deceleration rate of the engine is greater than a pre-determined threshold.

Abstract: A combustor for a gas turbine engine includes a fuel delivery system that uses circumferential fuel staging. The fuel delivery system includes a plurality of fuel supply rings and a backpurge sub-system. The fuel supply rings are arranged concentrically at various radial distances to supply fuel to a combustor through a plurality of combustor manifolds and pigtails. The backpurge system uses high temperature and high pressure combustor air to purge fuel from non-flowing fuel supply rings, combustor pigtails, and combustor manifolds. Additionally, the fuel delivery system includes at least two orifices to minimize pressure decays during filling stages.

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 gas turbine system comprises an alarm signal calculation circuit, a shutdown calculation circuit and a flashback-error signal prevention calculation circuit. The alarm signal calculation circuit, the shutdown calculation circuit and the flashback-error signal prevention calculation circuit are integrated in a combustion monitoring device for monitoring combustion condition of combustion gas in a gas turbine-combustor.

Abstract: A fuel injector for use in a gas turbine engine includes an inlet stem with a bore formed therein and an insert disposed in the bore. The insert has a cavity formed therein for receiving a fuel filter. The use of the insert allows the upstream end of the inlet stem to be connected to a fuel manifold with a double seal fitting.

Abstract: A windmilling brake system for a turbine engine includes a brake drum (14) on an interior surface of an engine rotor. The drum circumscribes a brake unit (37) that includes a brake ring (38) with brake shoes (42) each connected to the ring by respective springs (44). A leg (45) extends from each shoe and toward the ring. The ring is sandwiched axially between bolting flanges (28, 29) on forward and aft carrier portions (24, 25) of a two piece, variable stiffness, dual load path rotor bearing support. Nonsacrificial fasteners secure the ring to one of the flanges while frangible fasteners (52) secure the flanges to each other. The frangible fasteners also extend through an eye (47) in each leg to deflect the springs and hold the brake shoes in an armed state out of contact with the drum. Upon being exposed to abnormal imbalance loads, the frangible fasteners fail in tension to disable one of the two load paths.

Abstract: Plugs for protecting internal spaces of rocket combustion chambers against moisture, dust, and other environmental factors. Each plug includes a central rod with a bracket fastened to it. The plug also includes a sleeve with radially extending structural ribs. Spring-loaded cams with rollers are securely hinged at the ends of the ribs. In addition, a spring-loaded limiter and a valve are mounted on the central rod so that they can possibly move relative to the central rod. The limiter includes a sleeve and a conical shell that are connected by rod ties. The valve includes a metal stamped conical plate that forms a gas-tight fit with the rod. A sealing ring of elastic material is positioned on a peripheral part of the plate. The set of spring-loaded cams and the limiter secure the self-mounting plug in a working position and make the valve operation independent of the operation of other plug components.

Abstract: A fuel nozzle system for use in a combustor utilized in a combustion turbine for reducing nitrogen oxides and other pollutants including an annular fuel distribution manifold separately mounted away from a diffusion nozzle, said annular manifold having a plurality of fuel emitting passages or holes disposed along the downstream side of the manifold, said manifold being mounted in a position away from the diffuser nozzle body to allow air to stream around the manifold on all sides allowing for a thorough mixture of fuel and air around the annular manifold for better premixing in the combustion chamber.

Abstract: Stress occurring in a moving blade in a gas turbine stopping process is decreased. Time t1 is load decrease start or fuel throttling start, time t2 is no load operation start, time t3 is fuel shut-off and time t4 is a time of largest stress. A 4/4 load maintained until t1 decreases gradually to a 0/4 load at t2, which is then maintained until t3 and then decreases further. The rotational speed is the rated speed until t2, at which point it is controlled to be decreased gradually to about 60% of the rated rotational speed at t3. The metal differential temperature between a moving blade point A and a platform point B is constant until t1 and is then decreased slightly between t1 and t2 and between t2 and t3. Differential temperature &Dgr;t, largest after t3, occurs at t4.

Abstract: A gas-turbine engine having means capable of determining the temperature inside a combustion chamber without mounting a special temperature sensor therein and of controlling the operation of the components according to the detected inside temperature of the combustion chamber, which is provided with means for measuring a resistance value of a glow plug driven with a constant current, means for measuring a flow rate of air supplied to the combustion chamber and means for determining an inside temperature of the combustion chamber by searching a specified temperature corresponding to a measured value of glow-plug-resistance and a measured air-flow-rate from a table holding therein resistance-temperature characteristic data of the glow plug predetermined for airflow rate as parameter.

Abstract: A support structure for a gas turbine engine includes a support arm (214, 216) extending between a low pressure shaft (202) and a rotor. The support arm includes a fuse (220) having a low failure point. A high pressure stub shaft (270) axially and radially supports the low pressure shaft (202) after fuse failure. An axial gap (A) between a portion of the low pressure shaft and the stub shaft permits movement of the low pressure shaft after fuse failure. A radial gap (B) between the stub shaft (270) and the low pressure shaft (202) allows radial deflection of the low pressure rotor system after fuse failure.

Abstract: A turbojet-engine cowling combined with a thrust reverser comprising a large-displacement displaceable component (7) includes an electrically grounding mechanism for the displaceable component (7) when in its forward-thrust position. The grounding mechanism comprises an elastic device (20) dedicated to shunt the electric current away from any mechanical member used in the displacement without any displaceable connecting element.

Abstract: The present invention is addressed to a control logic for determining the occurrence of shaft decoupling in a gas turbine engine. The control logic in the preferred embodiment receives inputs for shaft rotational speed and/or compressor pressure and uses these parameters for making a determination of shaft decoupling in fractions of a second, before serious damage to the gas turbine engine can occur. The control logic also utilizes multiple interval sampling, and sampling over multiple channels to verify any determination of shaft decoupling. Once a shaft decouple has been verified, fuel flow to the engine is cut off, thus shutting down the engine.

Abstract: A fluid flow system for supplying fuel to an engine, the system including a fluid flow valve having a valve element movable alternatively to a first operative position in which a relatively low fluid flow rate is permitted through the valve, for achieving a normal gradual shut-off of fuel supply, and a second operative position in which a relatively high fluid flow rate is permitted through the valve, for achieving a rapid emergency shut-off of fuel supply. Also disclosed is a fluid flow valve for use in the system. The invention has application in aircraft gas turbine engines.

Abstract: The present invention is addressed to a control logic for determining the occurrence of shaft decoupling in a gas turbine engine. The control logic in the preferred embodiment receives inputs for shaft rotational speed and/or compressor pressure and uses these parameters for making a determination of shaft decoupling in fractions of a second, before serious damage to the gas turbine engine can occur. The control logic also utilizes multiple interval sampling, and sampling over multiple channels to verify any determination of shaft decoupling. Once a shaft decouple has been verified, fuel flow to the engine is cut off, thus shutting down the engine.

Abstract: An apparatus is provided for use in monitoring for destructive wet compression power augmentation-related casing distortions in an industrial gas turbine equipped with and employing wet compression power augmentation, in the form of a) an outer ring member having an inner diameter which exceeds the outer diameter of a gas turbine section downstream of the compressor, b) three or more structural members spaced substantially equally over the outer ring member's inner circumference and which extend radially inwardly in a common plane to define a central opening about the gas turbine, with the common plane defined by the three or more members being parallel to a plane including the outer ring member over its circumference and the outer ring member's center of mass and with one of the three inwardly-extending members being equipped at its inner end with a socket or ball element of a ball and socket joint, and c) a laser reflector positioned on the outer ring member.