| Patent application number | Description | Published |
|---|
| 20090155088 | DUST HOLE DOME BLADE - A hollow turbine airfoil includes a tip cap bounding an internal cooling circuit between opposite pressure and suction sidewalls. The tip cap includes an internal dome surrounding a dust hole, and the dome is inclined inwardly toward the airfoil root both transversely between the opposite sidewalls and chordally between opposite leading and trailing edges of the airfoil. | 06-18-2009 |
| 20090169356 | Plasma Enhanced Compression System - A compression system is disclosed, the compression system comprising a rotor having a circumferential row of blades each blade having a blade tip, a static component located radially outwardly and apart from the blade tips, a detection system for detecting an instability in the rotor during the operation of the rotor, and a mitigation system that facilitates the improvement of the stability of the rotor when an instability is detected by the detection system. A gas turbine engine comprising a detection system for detecting an instability during the operation of the fan section and a mitigation system that facilitates the improvement of the stability of the fan section is disclosed. | 07-02-2009 |
| 20090169362 | Instability Mitigation System - An instability mitigation system is disclosed, comprising a detection system for detecting an onset of an instability in a rotor during the operation of the rotor, a mitigation system that facilitates the improvement of the stability of the rotor when the onset of instability is detected by the detection system, a control system for controlling the detection system and the mitigation system. | 07-02-2009 |
| 20090169363 | Plasma Enhanced Stator - A compression system is disclosed, the compression system comprising a stator stage having a row of a plurality of stator vanes arranged around a centerline axis, each stator vane having a vane airfoil and at least one plasma actuator located on the stator stage. Exemplary embodiments of a detection system for detecting an instability in a compression system rotor and a mitigation system that facilitates the improvement of the stability of the rotor are disclosed. | 07-02-2009 |
| 20090169367 | Instability Mitigation System Using Stator Plasma Actuators - An instability mitigation system is disclosed, comprising a stator stage located axially proximate to a rotor, the stator stage having a row of a plurality of stator vanes arranged around a centerline axis, and a mitigation system comprising at least one plasma actuator mounted on the stator vane that facilitates the improvement of the stability of the rotor, and a control system for controlling the operation of the mitigation system. An instability mitigation system further comprising a detection system for detecting an onset of an instability in a rotor and a control system for controlling the detection system and the mitigation system are disclosed. | 07-02-2009 |
| 20100047055 | Plasma Enhanced Rotor - A compression system is disclosed, the compression system comprising a rotor having a plurality of blades arranged around a centerline axis, each blade having a blade airfoil and a blade tip, and at least one plasma actuator located on a blade. Exemplary embodiments of a detection system for detecting an instability in a compression system rotor and a mitigation system comprising at least one plasma actuator mounted on a blade to facilitate the improvement of the stability of the rotor are disclosed. | 02-25-2010 |
| 20100047060 | Plasma Enhanced Compressor - A gas turbine engine is disclosed, comprising a compressor having a circumferential row of blades, a casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one plasma generator located on the casing. The plasma generator comprises a first electrode and a second electrode separated by a dielectric material. The gas turbine engine further comprises an engine control system which controls the operation of the plasma generator such that the stable operating range of the compressor is increased. | 02-25-2010 |
| 20100158696 | CURVED PLATFORM TURBINE BLADE - A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform. | 06-24-2010 |
| 20100170224 | PLASMA ENHANCED BOOSTER AND METHOD OF OPERATION - A booster system is disclosed, comprising a first rotor stage having a plurality of first rotor blades spaced circumferentially around a rotor hub with a longitudinal axis and having a first pitch-line radius extending from the longitudinal axis, a last rotor stage located axially aft from the first rotor stage, the last rotor stage comprising a plurality of last rotor blades spaced circumferentially around the longitudinal axis and having a second pitch-line radius extending from the longitudinal axis, and a gooseneck duct located axially aft from the last rotor stage and capable of receiving an airflow, the gooseneck duct comprising an inlet end and an exit end located at a distance axially aft from the inlet end and having at least one plasma actuator mounted in the gooseneck duct. | 07-08-2010 |
| 20100172747 | PLASMA ENHANCED COMPRESSOR DUCT - A compression system is disclosed, comprising a first compressor having a first flowpath, a second compressor having a second flowpath located axially aft from the first compressor, and a transition duct capable of flowing an airfow from the first compressor to the second compressor, the transition duct having at least one plasma actuator mounted in the transition duct. | 07-08-2010 |
| 20100180572 | FLADE FAN WITH DIFFERENT INNER AND OUTER AIRFOIL STAGGER ANGLES AT A SHROUD THEREBETWEEN - A FLADE fan assembly includes radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline. Inner and outer chords extend between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively. Inner and outer stagger angles between the inner and outer chords respectively at the shroud and the centerline are different. The radially outer airfoils may outnumber the radially inner airfoils and particularly by a ratio in a range of 1.5:1 to about 4:1. Load paths or radii may extend radially through the inner and outer airfoils and through the rotating shroud between the inner and outer airfoils and may pass near or through the inner and outer leading edges and through the inner and outer trailing edges. | 07-22-2010 |
| 20100251696 | PLASMA ENHANCED RAPIDLY EXPANDED GAS TURBINE ENGINE TRANSITION DUCT - A plasma enhanced rapidly expanded duct system includes a gas turbine engine inter-turbine transition duct having radially spaced apart conical inner and outer duct walls extending axially between a duct inlet and a duct outlet. A conical plasma generator produces a conical plasma along the outer duct wall. An exemplary embodiment of the conical plasma generator is mounted to the outer duct wall and including radially inner and outer electrodes separated by a dielectric material. The dielectric material is disposed within a conical groove in a radially inwardly facing surface of the outer duct wall. An AC power supply is connected to the electrodes to supply a high voltage AC potential to the electrodes. | 10-07-2010 |
| 20100284780 | Method of Operating a Compressor - A method of operating a compressor having a row of blades for preventing a compressor stall is disclosed, the method comprising the steps of mounting a plasma generator in a casing or a shroud radially outwardly and apart from the blade tips wherein the plasma generator comprises a radially inner electrode and a radially outer electrode separated by a dielectric material; and supplying an AC potential to the radially inner electrode and the radially outer electrode. | 11-11-2010 |
| 20100284785 | Fan Stall Detection System - A system for detecting onset of a stall in a rotor is disclosed, the system comprising a sensor located on a static component spaced radially outwardly and apart from tips of a row of blades arranged circumferentially on the rotor wherein the sensor is capable of generating an input signal corresponding to a flow parameter at a location near the tip of a blade, a control system capable of generating a rotor speed signal, and a correlation processor capable of receiving the input signal and the rotor speed signal wherein the correlation processor generates a stability correlation signal. | 11-11-2010 |
| 20100284786 | Instability Mitigation System Using Rotor Plasma Actuators - An instability mitigation system is disclosed, comprising a rotor having a row of blades arranged around a centerline axis, and a mitigation system comprising at least one plasma actuator mounted on a blade that facilitates the improvement of the stability of the rotor, and a control system for controlling the operation of the mitigation system. An instability mitigation system further comprising a detection system for detecting an onset of an instability in a rotor and a control system for controlling the detection system and the mitigation system are disclosed. | 11-11-2010 |
| 20100284795 | Plasma Clearance Controlled Compressor - A plasma leakage flow control system for a compressor is disclosed, comprising a circumferential row of compressor blades, an annular casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one annular plasma generator located on the annular casing. The annular plasma generator comprises an inner electrode and an outer electrode separated by a dielectric material. A gas turbine engine having a plasma leakage flow control system further comprises an engine control system which controls the operation of the annular plasma generator such that the blade tip leakage flow can be changed. | 11-11-2010 |
