Abstract: A variable geometry vane for use in a turbine engine. The vane can be radially mounted in a shroud ring while outside the turbine engine. The shroud and vane assembly can then be mounted to an engine hub without disassembly of the shroud, eliminating the need for a split ring shroud. Once located surrounding the hub, vanes are slid radially inward until a radially inward vane button engages a hole within the hub. Vanes are locked in place using clips slid into slots within the shroud. The clips are retained in place using an adjacent engine part bolted to the face of the shroud. Once in place within the engine, vanes are attached to a control arm for airflow adjustment.

Abstract: A component trend monitoring system for monitoring the performance of components and comparing the performance with stored performance data to accurately trend and predict the failure of the components. The system includes computer chips attached to the various components, for receiving and storing historical and performance data about each component, and a processor for retrieving the stored data from the memory chips. The processor receives and analyzes the data against historical data for predicting failure based upon past trends within the historical data. The processor also provides a signal for impending failure of a given component.

Abstract: A system for starting an APU, including an air control valve assembly located in the air flow passageway extending between a source of pressurized air and a turbine power modulator. The system further includes a fuel control valve assembly located in the fuel flow passageway extending between a source of jet fuel and the turbine power modulator. Upon energizing the air control and fuel control valves, a mixture of compressed air and jet fuel entering the turbine power module is ignited, creating a flow steam of hot gases for driving a gas turbine to power the APU.

Abstract: The present invention is directed to a fluidic system and method for controlling the airflow to a lean premix combustor. The system and method as disclosed allow for reduced power, which results in reduced emissions, while at the same time providing excellent performance. This is accomplished through the use of fluidic means, which do not have the problems associated with hot moving parts of prior art mechanical means. Specifically, the introduction of an airflow downstream from openings in the dilution section cause a local boundary layer separation forcing air into the dilution holes.

Abstract: A method and system for surge detection within a gas turbine engine, comprises: measuring the compressor discharge pressure (CDP) of the gas turbine over a period of time; determining a time derivative (CDPD ) of the measured (CDP) correcting the CDPD for altitude, (CDPDCOR); estimating a short-term average of CDPDCOR2; estimating a short-term average of CDPDCOR; and determining a short-term variance of corrected CDP rate of change (CDProc) based upon the short-term average of CDPDCOR and the short-term average of CDPDCOR2. The method and system then compares the short-term variance of corrected CDP rate of change with a pre-determined threshold (CDPproc) and signals an output when CDProc>CDPproc. The method and system provides a signal of a surge within the gas turbine engine when CDProc remains>CDPproc for pre-determined period of time.

Abstract: A nickel base single crystal compliant layer on a ceramic blade has the capability to sustain high stresses and high operating temperature. Layers of nickel and platinum bonded on a single crystal superalloy over a sputtered gold-chromium layer support the high stress levels at elevated temperature without extrusion of the soft platinum or nickel layer and without destruction of an NiO compliant surface. The compliant layers have survived stress and temperature conditions without failure to the ceramic blade and the system can be stressed/heated and unloaded/cooled repeatedly without damage to the ceramic blades. A single crystal nickel base superalloy (i.e., SC180) has high strength properties at elevated temperature. Thin layers of chromium followed by gold are e-beam evaporated on one side of a polished surface of the alloy. Pure nickel is electroplated over this e-beam gold-chromium layer. Platinum is either electroplated or plated electrolessly over the nickel layer.

Abstract: A dual function rapid shutdown and ecology system for fuel delivery systems for engines, specially aircraft gas turbine engines, is disclosed. The dual function is accomplished in a single module operated by a single electro-magnetic solenoid valve commanded by the engine electronic control unit. Upon actuation of the solenoid valve, a large spring loaded piston strokes to the extreme of its travel creating a cavity having a volume sufficient to accommodate all fuel leftover in the fuel manifold and distribution system at shutdown, thus preventing atmospheric pollution or engine damage upon subsequent operation. Simultaneous with actuation of the solenoid valve, fuel pressure differentials cause a small piston to stroke to the extreme of its travel opening fuel passageways and causing all the fuel being delivered to the engine combustion chamber to be bypassed back to pump inlet, thus effectively accomplishing the rapid shutdown function.

Abstract: A sensor error compensation system and method is provided that facilitates improved sensor error detection and compensation. The sensor error compensation system includes an expected value generator and a sensor fault detector. The expected value generator receives sensor data from a plurality of sensors in a turbine engine. From the sensor data, the expected value generator generates an expected sensor value for a sensor under test. The expected sensor value is passed to the sensor fault detector. The sensor fault detector compares the expected sensor value to a received sensor value to determine if a sensor error has occurred in the sensor under test. If an error has occurred, the error can be compensated for by generating a replacement sensor value to substitute for erroneous received sensor value.

Abstract: A method for forming a carbon deposit inhibiting thermal barrier coating for an internal element or component of a gas turbine engine. Such coating includes a layer of thermal barrier material coated onto the surface of an engine component that will be exposed to the flow of burning engine gases. Such coating further includes a layer of carbon deposit inhibiting material coated on top of the layer of thermal barrier material.

Abstract: An electronic circuit measures a pulse frequency and/or a pulse period of pulses in a sensor signal originating in a sensor coil, the pulses being zero crossing pulses. The circuit includes a filter stage having an input connected to the sensor coil, the filter stage being for removing electrical noise from the sensor signal to provide a filtered sensor signal. The circuit also has a signal strength sensing circuit connected to receive at least one of the sensor signal and the filtered sensor signal, the signal strength sensing circuit producing a variable threshold signal, which is a substantially monotonically non-decreasing function of a strength of the sensor signal. A variable threshold zero crossing detector is connected to receive the filtered sensor signal and the variable threshold signal. The variable threshold zero crossing detector has an upper threshold to test for zero crossing in a positive direction and a lower threshold to test for zero crossing in a negative direction.

Abstract: A heat shield for a combustor dome includes U-shaped baffles on the outer diameter area of the upstream surface of the heat shield. The baffles are clocked with respect to the impingement openings in the combustor dome. The baffles increase cooling of the heat shield by segregating the cooling air flow from the impingement openings and by reducing cross-flow at the outer diameter of the heat shield. The baffles also function as heat shield stiffeners. Slots extend radially inward from the outer rim of the heat shield. Keyholes are at the inner ends of the slots. The slots and keyholes reduce the hoop stresses of the heat shield.

Abstract: A method for generating a power setting parameter table. The method includes the steps of generating an index from a plurality of first and second inputs and determining a power setting parameter corresponding to each index and second input. The first inputs may include flight speed and temperature values and the second inputs may include altitude values.

Abstract: A powder for metal injection molding of has a silicon content of less than 0.1%. Silica inclusions are substantially eliminated in the finished molded product.

Abstract: A lubricating and cooling system for a high speed generator that directs a lubricating and cooling medium through the generator housing. The lubricating and cooling medium may be supplied to the generator on either end of the housing. A portion of the medium is supplied to the generator bearings. The remaining portion then flows through the rotor shaft, through the rotor, back to the shaft, where a portion may be sprayed onto the rectifier assemblies, then passed through the stator, and out of the generator.

Abstract: A high speed generator with a hydraulic rotor mounting system that dampens rotor vibrations at the rotor's critical speeds. Oil is supplied to a gap formed between the outer race of the rotor bearing assembly and the bearing liner. The oil provides soft bearing support for, and viscous damping of, the rotor.

Abstract: A system and method for performing RCM analysis is disclosed. The system is an automated system for performing RCM analysis/maintenance program development requirements. The invention adheres to MSG-3 standards and guidelines. The system provides a user interface which is broken down in a hierarchical fashion which easily allows a user to enter data in accordance with MSG-3 procedures. A database includes one or more systems. Systems can be further refined to include one or more subsystems, sub-subsystems and parts. RCM analysis is performed at a Maintenance Significant Item (MSI) level which includes defining reliability data for the MSI. A part, by definition is an MSI. However, a subsystem or a system can also be an MSI. A system includes functions. A function can have one or more failures associated with it. There can be one or more effects associated with a failure. There can be one or more causes for an effect.

Abstract: A ceramic finger seal for use between a housing and a combustor liner to inhibit air passage therebetween and for use in fluid sealing between a rotating shaft and a housing circumscribing the rotating shaft. The ceramic finger seal has at least two annular diaphragm members constructed of two or more diaphragm segments bonded end to end by ceramic cement or other high temperature joining compounds. The diaphragm members may be partitioned into a generally continuous inner diameter portion and a segmented outer diameter portion or the reverse thereof. The segmented portion includes finger elements spaced uniformly apart forming gaps therebetween and extend radially outward or inward terminating in a foot portion. The rolled edge on the finger is formed by laser cutting to prevent gouging of the combustor liner surface.

Abstract: An integrated cabin pressure control system valve that uses a dual, redundant channel electronic control unit for both control of the valve and to supply alarm, indication, and control signals to the aircraft's avionics system. Each channel in the electronic control unit includes an instrumentation and control circuit that uses multiple, dissimilar sensors and signals for warnings, indications, and controls. This configuration reduces the likelihood for a common mode failure that could result in a postulated gradual decompression without indication event.

Abstract: A system and method for trepanning holes into a work piece as relative movement between the work piece and a pulsed laser occurs. As a cylindrical work piece rotates for example, a position controlled pulse laser fires a first series of timed pulses. During each subsequent rotation of said work piece another series of pulses is fired such that the periphery of a row of identical holes is cut into the cylindrical work piece.

Abstract: A new improved system and method for end turn retention for wires on a generator rotor for use in high speed applications such as in aircraft applications. The rotor includes a shaft, spokes, supports, and wire winding coils, and at least one cap device. The spokes extend radially outwardly from the shaft, and each support is positioned on an associated spoke. Each coil wraps around an associated support and spoke. Each cap device is coupled to an end of its associated spoke to prevent the windings from moving radially outwardly while the rotor spins. Each support is coupled to an associated cap device, and includes at its radially inward edge a flange protruding away from the respective spoke. Because of the flange and the cap device, slack of the wire coil between the flange and the associated cap is taken up.