Abstract: An external flap vectoring mechanism on an axisymmetric gas turbine exhaust nozzle, the external flap vectoring mechanism comprising a plurality of external flaps, each such flap having first and second flaps, the first flap pivotably connected to a sync ring and the second flap pivotably connected to the aft end of the first flap thereby providing for lateral movement of the second flap relative to the first.

Abstract: The output of gas turbines is enhanced by gas moisturization using a water contact tower and a pumped water recirculation loop with low pressure steam addition thereto.

Abstract: The present invention is a multiple layered nozzle liner for two-dimensional nozzles which provides both convective and film cooling, and incorporates a highly maintainable thermal barrier coating.

Abstract: A sync-ring assembly for use on a axisymmetric gas turbine exhaust nozzle, the sync-ring having a semi-spherical outward surface received within and slidably contacting the cylindrical inner surface of a liner. The sync-ring runs along guide tracks mounted to the case of the nozzle, and is positioned along the liner and rotated with respect to the liner by a plurality of actuators pivotably connected to the sync-ring.

Abstract: The cost and bulk of a speed reducing transmission required to provide low speed rotational power from a gas turbine engine is avoided by employing bearings (16, 18) jornalling a high speed shaft (12) of the engine with a power takeoff in the form of a tubular shaft (62) having bearing receiving and retaining openings (82) to act as a bearing cage for bearing elements (64, 66) disposed between inner and outer bearing races (68, 70). Upon rotation of the high speed shaft (12), the bearing elements (64, 66) will move in an epicyclic fashion thereby driving the tubular shaft (62) at a reduced rotational rate allowing it to drive loads such as a dynamoelectric machine (90) or a ducted fan (48) at rotational speeds less than the rotational speed of the high speed shaft (12).

Abstract: An on/off surge prevention control and method for a gas turbine engine having a variable geometry diffuser is provided. This control receives exhaust gas temperature and compressor discharge pressure signals from the engine, and a signal from the aircraft indicative of a need for bleed air. When the aircraft signal is received, the control opens the diffuser to its maximum open setting, and when said aircraft signal is absent closes said diffuser to its minimum open setting. In the event that a faulty aircraft signal is received, the control senses changes in EGT, P3 and dP3/dt and compares these parameters to preselected values indicative of the compressor nearing surge. When the measured values reach the preselected values, the control closes the diffuser to it minimum open setting. By using a temperature signal in determining when to close the diffuser, unwanted closings due to operating transients in compressor discharge pressure are provided.

Abstract: A method and apparatus are disclosed for spoiling thrust from combustion gases discharged from an aircraft gas turbine engine at ground idle operating condition. The method comprises the step of positioning a secondary exhaust flap of the exhaust nozzle to form a diffuser for the combustion gases at the ground idle operating condition for maintaining attachment of the combustion gases along the secondary exhaust flaps for spoiling thrust. An exemplary and preferred exhaust nozzle is provided wherein the secondary exhaust flaps are positionable in part independently of primary exhaust flaps so that the primary and secondary flaps may be disposed together in different positions during ground idle, dry, and augmented operating conditions of the engine.

Abstract: A power plant with efficient emission control and high turbine inlet temperatures is disclosed. The power plant includes a combustor for the combustion of carbonaceous sulfur-bearing fuel. The combustion of this fuel produces a hot gas with SO.sub.x and NO.sub.x contaminants. This gas is conveyed to a refractory heat exchanger where some of the heat from the gas is transferred to a pressurized air stream. The gas is then conveyed to a fluidized bed reactor. The fluidized bed reactor includes a central chamber with a fluidized bed positioned at the base of the chamber. Heat exchangers are positioned within the fluidized bed. These heat exchangers preheat the pressurized air stream which is then conveyed to the refractory heat exchanger and later conveyed to a turbine assembly. The fluidized bed reactor also includes circulating particulate matter, such as CaO. Ammonia may also be injected into the fluidized bed reactor. When operating at a temperature of at least 1,500.degree. F.

Abstract: Inefficiencies in the operation of auxiliary power units producing electric and hydraulic power along with bleed air resulting from independence in the demand for power may be minimized in a system including at least one bleed air consuming system (84, 86), an electrical generator (92), a hydraulic pump (90), and a turbine wheel (10, 20) for driving the generator (92) and the pump (90). Also included is a combustor (32) for receiving fuel and compressed air and producing gases of combustion to drive the turbine wheel (10, 20). A rotary compressor (10, 14) is coupled to the turbine wheel to be driven thereby. The compressor (10, 14) is a radial discharge compressor with an impeller having blades (14) extending from an inlet end (40) to a discharge end (42) and a shroud (18) to the blades (14). Two axially spaced annular ports (44, 46; 44, 50) are adjacent the discharge end (42).

Abstract: An apparatus and method for effecting the disassembly of an annular combustor for the maintenance of very large power generation gas generators such as those used in military aircraft engines, commercial aircraft engines, and smaller power generation turbines. The apparatus utilizes rollers which are attachable to a lower half outer casing. An inversion ring located radially inward from the lower half outer casing is supported by the rollers. By disconnecting a removable upper half outer casing, the combustor segments of a first section of the combustor can be removed. Supports connected to the first section of the combustor are secured by pins to a tool ring which is in turn secured to the inversion ring so as to create a closed path. By removing pins which secure the inversion ring and lower half outer casing to supports connected to a second section of combustor segments, the combustor can be rotated so that the second section of formerly inaccessible segments can be easily removed.

Abstract: An ion beam and jet stream motor useful as motive and propulsive forces is formed by generating a collimated ion beam and projecting the collimated ion beam into an electrically charged, tubular electrode. This is done with an ion beam motor having a pointed electrode mounted adjacent an end of a tubular electrode coupled with a high voltage power supply. The generated ion jet stream is useful in controlling or extinguishing flames.

Abstract: A fuel manifold is disclosed for providing fuel to a combustor disposed radially inside an annular casing. The manifold is disposed inside the casing and includes an arcuate manifold tube, a thermal insulation layer surrounding the tube, and a cover layer surrounding the insulation layer which is substantially rigid for protecting the insulation layer from physical damage.

Abstract: A method of obtaining extraction airflow from a compressor includes accelerating the extraction airflow to at least Mach 1 for obtaining choked airflow and decelerating the choked airflow to a speed less than Mach 1. An apparatus for carrying out the method includes a compressor casing having an extraction airflow port, first means for accelerating the extraction airflow channeled through the port to at least Mach 1 for obtaining choked airflow, and means for decelerating the choked airflow to a speed less than Mach 1. In an exemplary embodiment, a converging-diverging nozzle is provided for accelerating the extraction airflow to at least Mach 1 and then decelerating the choked airflow.

Abstract: A thrust reverser for use with turbo-fan aircraftt engines; in particular engines mounted on an aircraft fuselage. Four radially spaced openings around the engine each is closed by a stowed door. An actuator is provided to move each door to a deployed position extending through the opening, near the aft end of the opening. The aft end of each door extends into the tailpipe and directs air flow out through the opening, where the forward end of the door further directs the flow in an outwardly and forwardly direction. Doors adjacent to the aircraft fuselage are shaped to guide reverse airflow away from direct impingement on the fuselage. Deployable strakes are mounted on doors adjacent to the fuselage. The strakes are typically spring biased toward a stowed position flat against the inside of the door and are moved to a deployed position by aerodynamic forces when the doors are deployed. In the deployed position, they are located so as to deflect air flow away from the fuselage or other structures.

Abstract: In a fuel supply system for a space missile or a spacecraft in which the thrusters are supplied with liquid or gaseous fuel from a fuel tank in which the tank pressure decreases continuously during the operational life of the system, the fuel throughput and thus the thrust of the respective thruster or thrusters is maintained substantially constant by the arrangement of a constant flow device in the fuel line between the tank and the reaction chamber of the system. The constant flow device is a self regulating pressure loss device realized by increasing or decreasing the through-flow area of the device in response to changing fuel supply pressures.

Abstract: A simplex air blast fuel injection system for the atomization of fuel for ignition to drive a gas turbine includes a simplex nozzle which receives fuel from a fuel pump powered by the turbine over a range of pressures between maximum and minimum pressures during the operation of the turbine, and also receives fuel at a substantially lower pressure than the minimum fuel pressure when the turbine is cranked during startup. The fuel is discharged from the nozzle orifice as a swirling stream of atomized fuel during turbine operation, and as a film which is insufficiently atomized to initiate ignition during the turbine startup. An air compressor is also powered by the turbine to supply air at a low pressure to the fuel issuing from the nozzle orifice during both turbine operation and startup.

Abstract: A method and apparatus which facilitate separation of a gas turbofan powerplant into modules for shipping, maintenance and repair is disclosed. Various construction details are developed which provide means for mounting a fan cowling to an engine core in a manner which permits transference of operational loads from the fan cowling to the engine core and separation of the fan cowling from the engine core. In one embodiment, a fan cowling (46) is attached to an engine core (18) by a plurality of radially extending through struts (64). The through struts include a bolted joint (72) which permits separation of a powerplant (12) into a first module and a second module. For this embodiment, a method for varying between an assembled and disassembled condition is comprised of manipulating the joints between an engaged and disengaged position and axially moving the separate modules along a longitudinal centerline (14).

Abstract: A thrust reverser for jet engines comprising a pair of thrust reverser doors pivotally mounted on an axis which is substantially diametrically positioned with respect to the exhaust nozzle of a jet engine so as to pivot between a stowed position in which the doors are out of the direct path of exhaust of the engine but subjected to the static pressure of the jet engine over substantially the entire length of the doors, and a deployed position in which the doors are in the path of the engine exhaust for deflecting the exhaust and creating a braking thrust, a latch mechanism for securing the doors in the stowed position, a suitable port for directing a portion of the static pressure of the jet engine toward the doors for exerting the static pressure against the doors, an actuator for releasing the latch mechanism so that the doors may pivot to the deployed position, a valve operatively associated with the latch mechanism for relieving at least a portion of the static pressure of the jet engine acting on an upst

Abstract: A modulating surge prevention control and method for a gas turbine engine having a variable geometry diffuser is provided. The control calculates a maximum permissible compressor discharge pressure from a predetermined algorithim that is representative of the compressor discharge pressure when the compressor is operating at its minimum permissible surge margin with the diffuser in its maximum open position. The control also receives a signal from a sensor measuring the actual compressor discharge pressure. A error signal is formed by taking the difference between the measured pressure signal and the calculated signal. The control then continously adjusts the area of the diffuser so as to maintain the actual compressor discharge pressure at or below the calculated pressure. The calculated pressure is also corrected for variations in ambient temperature and altitude.

Abstract: In a gas turbine dual fuel nozzle including a main nozzle body with a support flange having a liquid fuel and atomizing air nozzle structure centrally extending therethrough with a fuel and atomizing air discharge structure arranged at its free end and a fuel gas supply structure arranged around the free end of the fuel and atomizing air discharge structure wherein the fuel gas supply structure has a front face extending inwardly adjacent the fuel and atomizing air discharge structure and having a central opening permitting the discharge of liquid fuel and atomizing air therethrough, the front face has bores extending therethrough in radial symmetry in a circular array and radial slots formed therein between said bores and the central opening so as to eliminate hoop stresses in the front face around its central opening.