Abstract: A power production process integrates geothermal steam and fossil fuel energy sources to give a higher energy efficiency than is normally obtained when using these energy sources individually. Geothermal steam is partially diverted from a steam turbine and injected into a combustion turbine. Although the steam turbine output is reduced by the diversion of steam, the plant efficiency and total plant output are improved.

Abstract: The lens of a pair of sunglasses may be quickly replaced in its associated frame by inserting the top portion of the lens within an arcuate-shaped recess of the frame and snap fitting a plurality of dowels carried by the frame into corresponding sockets formed in the lens. Notches provided on opposite sides of each dowel facilitate engagement of the dowel within the recess. A V-shaped nose bridge is also secured to a correspondingly shaped notch in the lens and prevented from removal therefrom by a pair of lugs directed inwardly from opposite edges of the notch. A nose support is secured to the bridge by inserting pegs carried by the bridge into homes formed in the support.

Abstract: A gas turbine fuel nozzle and method of fuel flow provide resistance to coking of the fuel by means of a multiple passage heat transfer cooling circuit. Fuel streams to primary and secondary sprays of pilot and main nozzle tips are arranged to transfer heat between the pilot primary fuel stream and each of the main secondary fuel stream and the pilot secondary fuel stream. This protects the fuel in the streams from coking during both low flow, lower engine heat conditions and high flow, high engine heat conditions. This nozzle and flow can protect engines with both single tip and dual tip nozzles.

Abstract: The damping system comprises at least one resonant acoustic cavity disposed around the combustion chamber and having a shape and dimensions such that it functions simultaneously as a quarter-wave resonator and with tangential coupling the resonant acoustic cavity comprises:a) a main annular part whose half axial section has a very elongate shape with a width dimension "e" which is very small compared to its longitudinal dimension "L.sub.1 " which extends substantially parallel to the axis of symmetry of the combustion chamber, the mean radius "R" of the main annular part being close to the equivalent radius of modes of oscillation to be damped, and b) an annular coupling part which originates from the main annular part and which opens into the combustion chamber near to a longitudinal or radial pressure anti-node, the annular coupling part having a length "L.sub.2 " in a half axial section and a width dimension "h" very much less than the sum of the longitudinal dimension "L.sub.

Abstract: A system and method for resisting thermoacoustic oscillations in systems comprised of hot and cold components is disclosed. More particularly, a combined cycle power generation system 32 having a gas turbine 40, a gas turbine discharge duct 34, and a gas turbine recuperator 36 and 38 is disclosed. The system 32 is designed to resist severe thermoacoustic oscillations over its entire load range by providing for an asymmetrical arrangement of the hot section L-l, including the gas discharge duct 34 and the plenum 36 of the recuperator, and the cold section l, including the heat exchange tubes 38 of the recuperator. Also disclosed is a steam generation system 42 having a plenum 46, a burner 48, and a furnace 44. The steam generation system 42 is also designed to resist severe thermoacoustic oscillations by providing for an appropriate burner length L and by providing for an asymmetrical arrangement of a hot burner section L-l and a cold burner section l within the burner 48.

Abstract: An engine has a shroud which surrounds one of a propfan and a propeller having blades. The shroud has a variable geometry. A direction of the air flow inside a duct of the shroud is reversible via an adjustment of the blades for the reversal of the thrust of the engine. A separately movable nozzle ring forms a rearward end of the shroud. The nozzle ring is axially displaceable to an extent such that its trailing edge forms wherein air flow is promoted around the end of the shroud.

Abstract: A system for burning biomass to fuel a gas turbine 10 which generally comprises a pressurized combustion chamber 54, a feeder device 14 for feeding biomass particles into the combustion chamber 54, an air compressor 82 for supplying compressed air to the combustion chamber 54, an ash extracting device 92 for removing ash from the combustion gases 75, a turbine 116 and a central controller 126 for monitoring and controlling various aspects of the system 10. The biomass is fed into the combustion chamber 54 where the particles combust and produce highly pressurized combustion gases 75. The ash extracting device 92 removes the ash in the combustion gases 75 before the combustion gases 75 enter the turbine 116. The highly pressurized combustion gases 75 enter the turbine 116 where they expand to produce work and cause the blades of the turbine 116 to rotate. The turbine 116 drives an electric generator which is linked to a power transmission line through any suitable switching gear.

Abstract: In a method for reducing the pressure of a gas (12) from a primary network, this gas (12) is first fed through a heat exchanger (9) whose temperature potential comes from the exhaust gases (8) of a gas turbine (2), this gas turbine (2) being a constituent part of a gas turbine group (1, 2, 3, 4). Downstream of this heat exchanger (9), the gas (14) is admitted to an expander (10) which drives a compressor (11). The reduced pressure gas (15) from the expander (10) is used to operate the combustion chamber (4) of the gas turbine group. The compressor (11) provides a certain quantity of compressor air (17) which is introduced into the compressor (1) of the gas turbine group. Because both the thermal treatment of the gas (12) from the primary network and the compressor air (17) become available by using internal energy released by the process, the electricity yield from the generator (3) of the gas turbine group is increased in a manner specific to efficiency.

Abstract: In accordance with the present invention, a diffuser for a gas turbine engine having a compressor providing compressed airflow thereto is disclosed having an outer wall and an inner wall, with a plurality of circumferential splitter vanes disposed therebetween to define a plurality of channels for diffusing airflow therethrough. The splitter vanes have an aft end and a leading edge, with the aft end being thicker and tapering in size to the leading edge. The splitter vanes also have a relatively thick bluff base region in order to better spread the airflow radially.

Abstract: An exhaust-through-the-hub system described herein includes an apparatus for discharge of exhaust gases from a marine outboard motor to the outer perimeter of an attached pump jet. Exhaust gas is ducted downwardly through the central body of the motor and rearwardly into a plenum cavity positioned in the pump jet. At least one hollow stator vane receives the exhaust gas and discharges the exhaust gas through the stator housing at a substantial depth below the water line, thereby resulting in a quieter running engine. The exhaust-through-the-hub system provides forward thrust when the motor is in forward gear and reverse thrust when the motor is in reverse gear.

Abstract: A gas turbine engine backbone deflection control apparatus to counter the effects of backbone bending due to gust, thrust. and maneuver loads by introducing a controlled backbone counter-bending moment by applying controlled tensioning forces only between axially spaced apart frames connected by the backbone. One embodiment of the invention, for a high bypass ratio turbofan engine, provides a hydraulically powered actuator to produce tensioning forces in cables connected between a fan frame and a turbine frame and the actuator is controlled by the engines digital electronic control system using input signals generated by inlet moment load sensors and/or blade tip clearance sensors.

Abstract: A method and control system for modulating a starter turbine (14) speed to a predetermined reference speed to prevent crash engagement with a turbine engine (16) during restart. The turbine engine (16) is coupled to the starter turbine (14) by a ratchet and pawl clutch (17), and crash engagement is prevented by modulating the starter turbine (14) speed to the predetermined reference speed, which is below a minimum pawl engagement speed, until the pawls have locked-in. A control system (10) in accordance with the present invention includes an electronic control (18) section and a mechanical pneumatic actuation means (20) which operate to limit the speed of the starter turbine (14) to the predetermined reference speed which is below the minimum speed at which crash engagements occur. The electronic control (18) provides an adjustment signal (26) corresponding to the difference between a sensed starter turbine speed signal (24) and a reference speed signal (49).

Abstract: A low noise power plant (100) for providing thrust to a missile (102) having a solid fuel propellant (104) for generating a pressurized gas. A turbine (106) converts the pressurized gas to rotary motion and a drive shaft (108) transfers the rotary motion to a load (110). In a preferred embodiment, the power plant (100) is utilized to drive a projectile (102). A solid fuel stick (104) located within a combustion chamber (112) is ignited and burned to provide pressurized gas which is directed to the turbine (106) via an exhaust tube (114). The pressurized gas is at a relatively low pressure and volume which minimizes the generation of noise. The turbine (106) and the drive shaft (108) are each rotated by the pressurized gas. The gases expelled from the turbine (106) are near atmospheric pressure which further minimizes the generation of noise. The power of the rotating drive shaft (108) can be converted to useful power by a speed reduction gearbox (140).

Abstract: A free-floating damper system is provided wherein a damper housing is configured to receive a damper arm for free-floating movement in the x/y plane while restricting similar movement in the z plane. The damper arm is specially configured with first and second wear bushings positioned in a spring biased support to insure the frictional generation of coulomb dampening forces between the damper arm bushings and the damper housing. The damper can be fixedly mounted to a portion of a gas turbine engine such as the turbine frame and a portion of the damper arm can be attached through a mounting bracket to an accessory tube of the engine to dissipate vibrational forces which otherwise can damage the accessory tube.

Abstract: A cascade type fan jet engine thrust reverser system. A radially arranged opening is provided along the aft edge the of fan cowl of a fan jet engine. Cascade sets each including a plurality of turning vanes are fixedly positioned in each opening. A blocking door and an actuating linkage system are positioned flush with the inner wall of the fan cowl adjacent to the openings, with the linkage system substantially out of the air flow path during normal engine operation. A sleeve like member covers the outer surface of the cascade sets and at least partially covers the stowed linkage system. When reverse thrust is desired, the sleeve is caused to translate aft, uncovering the cascade set and linkage. The linkage system is caused to move the blocking doors to positions where air flow through the fan cowl is substantially blocked and diverted out through the cascade sets in an outward and reverse direction. Upon completion of thrust reversal operation, these components are returned to the stowed position.

Abstract: A fuel nozzle for the combustor of gas turbine engines includes evacuated radial and axial bellows concentrically mounted to the fuel passages to prevent coking of the fuel passages and maintain the structural integrity of the integral parts and particularly the weld joints and the method of construction is disclosed.

Abstract: A fluid flow duct such as the jet pipe of an aircraft gas turbine powerplant has alternatively selectable outlets so that thrust may be directed through either an axial discharge nozzle or through vectorable lift nozzles. Side outlets in the jet pipe leads to lift nozzle on port and starboard sides of the aircraft. Nozzle selection is made by means of a composite diverter valve comprising a sleeve valve to cover the side outlets and a segmented blocker valve to close the jet pipe and deflect engine exhaust through the side outlets. The blocker valve segments are carried on the sleeve valve for simultaneous deployment. The segments are adapted to delay the opening of the side outlets as the sleeve valve translates axially. Specially extended segments co-operate with a shaped duct wall adjacent the outlets to delay their uncovering.

Abstract: A gas turbine engine flow mixer includes at least one chute having first and second spaced apart sidewalls joined together at a leading edge, with the sidewalls having first and second trailing edges defining therebetween a chute outlet. The first trailing edge is spaced longitudinally downstream from the second trailing edge for defining a septum in the first sidewall extending downstream from the second trailing edge. The septum includes a plurality of noise attenuating apertures.

Abstract: A combined support and seal ring supports the aft end of an annular combustor and provides a seal to contact the leading edge of the platform of the adjacent stator vane for sealing the cooling air from the gas path in a gas turbine engine.

Abstract: A thrust reverser for a turbojet engine is disclosed having a movable component, such as a thrust reverser door, operatively associated with an engine housing, and vanes formed on the upstream edge portion of the movable component and extending inwardly from an interior surface. The vanes, which extend in a direction generally parallel to a longitudinal axis of the engine, are located in an array which extends across the upstream edge portion of the movable component from one side to the other. The vanes each may be generally triangular in configuration and have one side attached to the inner surface of the movable component and another side attached to a gas flow deflector extending laterally across the front edge of the movable component.