Abstract: A split discharge vane pump is disclosed having a pump body that includes an interior pumping chamber having a central axis and defining a continuous peripheral cam surface, the cam surface including four quadrantal cam segments, wherein diametrically opposed cam segments have identical cam profiles, and each cam segment defines an inlet arc, a discharge arc and two seal arcs. A rotor is mounted for axial rotation within the pumping chamber and a plurality of circumferentially spaced apart radially extending vanes are mounted for radial movement within the rotor, wherein the plurality of vanes define an equal number of circumferentially spaced apart buckets which extend between the rotor and the cam surface of the pumping chamber for carrying pressurized fluid.

Abstract: A split discharge vane pump is disclosed having a pump body that includes an interior pumping chamber having a central axis and defining a continuous peripheral cam surface, the cam surface including four quadrantal cam segments, wherein diametrically opposed cam segments have identical cam profiles, and each cam segment defines an inlet arc, a discharge arc and two seal arcs. A rotor is mounted for axial rotation within the pumping chamber and a plurality of circumferentially spaced apart radially extending vanes are mounted for radial movement within the rotor, wherein the plurality of vanes define an equal number of circumferentially spaced apart buckets which extend between the rotor and the cam surface of the pumping chamber for carrying pressurized fluid.

Abstract: A multiple stage pump for delivering fuel to an engine is disclosed which includes a pump housing, a boost stage operable at engine start to draw fuel into the pump housing at a boost stage pressure, a first pumping stage operable upon engine start for receiving fuel from the boost stage and delivering the fuel from the pump housing to a fuel metering unit, a second pumping stage operable upon engine start and during engine cruise operation for receiving fuel from the boost stage and delivering the fuel from the pump housing to said fuel metering unit, and a switching valve in fluid communication with the first and second pumping stages, and configured to control fuel flow through the first pumping stage in dependence on changes in boost stage conditions such as pressure or shaft speed.

Abstract: A split discharge vane pump is disclosed having a pump body that includes an interior pumping chamber having a central axis and defining a continuous peripheral cam surface, the cam surface including four quadrantal cam segments, wherein diametrically opposed cam segments have identical cam profiles, and each cam segment defines an inlet arc, a discharge arc and two seal arcs. A rotor is mounted for axial rotation within the pumping chamber and a plurality of circumferentially spaced apart radially extending vanes are mounted for radial movement within the rotor, wherein the plurality of vanes define an equal number of circumferentially spaced apart buckets which extend between the rotor and the cam surface of the pumping chamber for carrying pressurized fluid.

Abstract: A two-stage system for delivering fuel to a gas turbine including a first stage variable pump for serving as a primary source of fuel, a second stage fixed pump for selectively supplementing the variable pump, a bypass valve connected to the fixed pump for loading and unloading the fixed pump and a regulator valve assembly connected to the variable pump and the bypass valve for controlling operation of the variable pump and the bypass valve. Preferably, the two-stage system also includes a control valve connected to the regulator valve assembly for setting a pressure differential across the regulator valve assembly and, thereby, loading and unloading the fixed pump.

Abstract: A two-stage system for delivering fuel to a gas turbine including a first stage variable pump for serving as a primary source of fuel, a second stage fixed pump for selectively supplementing the variable pump, a bypass valve connected to the fixed pump for loading and unloading the fixed pump and a regulator valve assembly connected to the variable pump and the bypass valve for controlling operation of the variable pump and the bypass valve. Preferably, the two-stage system also includes a control valve connected to the regulator valve assembly for setting a pressure differential across the regulator valve assembly and, thereby, loading and unloading the fixed pump.

Abstract: A vane pump assembly including a cam ring having an elliptical inner bore defining a hydraulic pumping chamber, the pumping chamber having an interior camming surface. The cam ring defines ports for admitting fluid into the pumping chamber. A rotor, within the cam ring, defines a plurality of radial vane slots. A vane assembly is supported in each vane slot to define vane buckets. Each vane assembly has an end dynamic vane seal for reducing leakage between the buckets. Front and rear side plates, separated by an annular spacer, enclose the pumping chamber. The pump assembly may also include floating front and rear rotor seals for reducing radially inward leakage. Each rotor seal is disposed within a groove formed in the rotor, wherein discharge pressure urges the rotor seals axially outward from the pumping chamber to create an effective seal against the respective side plate.

Abstract: A method from discriminating between spurious and genuine surges in a gas turbine engine is provided which includes the steps of receiving an engine speed signal over a global engine surge investigation region that includes a plurality of operating regions (e.g. speed bands) in which engine surges can occur, identifying a specific operating region in which an engine surge event occurs, incrementing a surge counter corresponding to the operating region in which the engine surge event occurred, identifying the operating regions in which no engine surge event occurred, decrementing a surge counter corresponding to each operating region in which no engine surge event occurred; enabling a surge avoidance signal when the magnitude of the surge counter for a particular operating region has reached a predetermined value; and adapting an engine acceleration schedule in the operating region corresponds to the surge avoidance signal.

Abstract: A vane pump is disclosed for use with gas turbine engines that is adapted and configured to provide a failure mode similar to that of a traditional gear pump. The vane pump includes a pump housing, a cam member, a cylindrical rotor member and a mechanism for communicating a high pressure fluid from the discharge arc region to the inlet arc region when the tip surface of each vane element has experienced a predetermined amounted of wear so as to prevent pump startup. The tip surface of each vane element wears as a result the sliding contact with the circumferential surface of the pumping cavity.

Abstract: Fuel control systems for use with a gas turbine engines which accounts for real-time thermodynamic engine effects when attempting to match or track the NDOTActual rate to the NDOTDemand rate. The fuel control system includes a mechanism for measuring several engine operating parameters and a mechanism for determining an initial engine fuel demand based on the measured engine operating parameters. The control system further includes a mechanism for estimating, during engine operation and based on the measured operating parameters, the amount of heat transferred between fuel combustion gases and the engine metal and estimating an effective fuel flow adjustment based therefrom. The control system disclosed herein also includes a mechanism for determining a final engine fuel demand based on the initial predicted engine fuel demand and the estimated effective fuel flow adjustment.

Abstract: A vane pump is disclosed for use with gas turbine engines which has pressurized fluid supplied to the undervane portion of the vane elements to balance the forces imparted thereon. The vane pump includes a pump housing, a cam member, a cylindrical rotor member and a chamber. The chamber is defined within the housing and positioned for fluid communication with the undervane portion of each vane element to provide a desired pressure thereto. The chamber is in fluid communication with a first pressure source and a second pressure source, wherein the first pressure source is associated with the discharge arc segment of the pumping cavity, and the second pressure source is associated with the inlet arc segment of the pumping cavity.

Abstract: An adaptive aero-thermodynamic engine model is disclosed which incorporates a plurality of model engine operating parameters, a plurality of nominal component efficiencies and corresponding efficiency modifier functions. The engine model is adapted by measuring a plurality of engine operating parameters corresponding to the plurality of model engine operating parameters during steady state operation of the engine over a plurality of data points, matching each of the model engine operating parameters to respective measured engine operating parameters by iteratively adapting each of the nominal component efficiencies using the corresponding efficiency modifier functions, estimating actual component efficiencies based upon the adapted nominal component efficiencies, and inputting the estimated actual component efficiencies into the engine model.

Abstract: Disclosed is a system and method for monitoring the vibration levels of gas turbine engines. The vibration monitoring system acquires vibration data from an engine, and processes the data with advanced algorithms to determine engine component health, both in a diagnostic and prognostic fashion. The method includes the steps of measuring an operating parameter and a corresponding set of vibration amplitudes for a plurality of rotating component during a period of operation and normalizing the set of measured vibration amplitudes based on established amplitude limits. The set of normalized amplitude data points are stored in parameter-based data blocks, which extend over a predetermined range of the operating parameter. For each data block, a time period remaining to reach the established amplitude limits is estimated based on changes in the normalized amplitude data points stored in the data blocks.

Abstract: A multi-mode shutdown system in combination with a fuel metering unit of an engine to prevent normal fuel delivery during engine malfunction such as the engine overspeeding. The multi-mode shutdown system includes a shutdown solenoid capable of closing a pressurizing valve to prevent fuel flow to the engine for creating a shutdown mode of operation with no fuel flow to the engine. The multi-mode shutdown system also includes a minimum flow solenoid in fluid communication a source of fuel at a minimum flow rate for creating a minimum flow mode of operation with fuel provided to the engine at the minimal flow rate. In the minimum flow mode, the shutdown solenoid and minimum flow solenoid establish a flow path for the fuel to the engine manifold at the minimal flow rate. During normal operation, the fuel metering unit regulates the fuel flow to the engine.

Abstract: A power turbine speed control system for a helicopter is disclosed which includes components for generating a power turbine speed signal based upon a demanded rotor speed, a high-order filter for filtering the power turbine speed signal by effectuating a rapid attenuation of main and tail rotor torsional frequencies in the power turbine speed signal without compromising phase at low frequencies, and a governor for providing isochronous power turbine speed and rotor speed control based upon the filtered power turbine speed signal.

Abstract: A fuel metering unit for controlling a variable displacement pump including a main metering valve in fluid communication with the pump for metering an output of the pump, a pressure regulator in fluid communication with the metering valve to create a spill return and a control valve in fluid communication with the pressure regulator and the pump for regulating the spill return flow so the spill return flow is maintained substantially constant at a low level to minimize the heat generated by recirculation by setting a displacement of the pump.

Abstract: A system is disclosed for determining the total torque required at the main and tail rotors of a helicopter for use in feed-forward rotor torque anticipation which includes a polynomial neural network adapted and configured to predict the aerodynamic torque at the main and tail rotors with the helicopter in motion based upon a plurality of pilot inputs and airframe inputs, a main rotor load map for determining the torque at the main rotor in hover out of ground effects based upon main rotor speed and collective stick position, a tail rotor load map for determining the torque at the tail rotor with the helicopter stationary based upon main rotor speed and pedal position, and a processor for calculating the required total torque at the main and tail rotors by summing the outputs of the polynomial neural network, and the main and tail rotor load maps.

Abstract: A system for performing feed-forward anticipation of rotor torque demand on a helicopter engine is disclosed which includes a flight control computer adapted and configured to predict the total torque required at the main and tail rotors of the helicopter, and an engine fuel control system adapted and configured to compute the rate of change of the total torque, convert the rate of change of the total torque to an engine acceleration/deceleration rate, and obtain a demanded engine acceleration/deceleration rate therefrom.

Abstract: Analog circuitry is disclosed for conditioning a signal from linear and rotary variable differential transformers having a primary winding, a pair of secondary windings and a movable core. The circuitry includes a unique closed loop negative feedback mechanism which, over time, adjusts the frequency of a voltage controlled oscillator so that a steady-state condition is achieved within the circuitry, whereby the total integrated value of the secondary winding voltages at an integrator remains equal to a reference voltage, thereby reducing the computational burden associated with solving an equation to determine the position of the movable core of the transformer.

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.