Abstract: A hydraulic air compressor (HAC) and system and method are set forth for aerobic treatment of waste effluent and for generation of power. The waste liquid is supplied to an upper end of a down shaft for the HAC which includes injection of air into the liquid for compression and for aerobic treatment of the liquid. The liquid falls to a separator where compressed air is liberated from the liquid. The liquid is returned to, for example, a sludge pond for recirculation and treatment. The compressed air is supplied as combustion air to a power generation unit such as a gas turbine for generation of electricity.

Abstract: A magnetically assembled cooling fan is disclosed. The cooling fan has an annular permanent magnet received therein and a metal plate with a pair of diagonally formed winged sections. The pair of diagonally formed winged sections are able to attract the fan assembly downward with respect to the housing, such that the problem caused by frictional resistance is overcome. Furthermore, a thrust bearing is provided at the free end of the shaft of the fan assembly so as to enable the shaft to rotate smoothly.

Abstract: The present invention is directed to gas turbine engines in which distinct components are integrally cast so as to increase resistance to thermal stress and thus decrease the amount of cooling airflow required to maintain the structural integrity of the components. The inner duct wall of a reverse airflow duct is integrally cast with a circumferentially extending shroud surrounding the stator vanes forming the turbine nozzle. The integral casting permits the inner duct wall to withstand greater degrees of thermal stress and thus require less cooling.

Abstract: A single energy storage capacitor is used to apply electrical energy to selected propellant modules, each module generating thrust in a desired direction by the high voltage induced vaporization of the copolymer spacer material in a conventional coaxial cable within the selected module. A lightweight, low cost, and EMI free thruster is thus provided.

Abstract: Systems and related methods pump fluid through a pump. The pump comprises a pump chamber, which is responsive to applied pressures to convey fluid. The systems and methods place an electrode in the pump chamber which, in use, is coupled to a current source. The electrode generates an electrical field in the pump chamber that varies according volume of fluid in the pump chamber. The systems and methods register variations in the electrical field as fluid is conveyed through the pump chamber.

Abstract: A gas turbine power plant with no intercooler for compressed air includes a compressor, a combustor for burning fuel with compressed air from the compressor to produce combustion gas, a turbine driven by the combustion gas, a generator driven by the turbine to generate electric power, a regenerative heat exchanger which heats the compressed air with the heat of exhaust gas of the turbine and has a water spray arranged therein for spraying water droplets onto the compressed air therein, and a spray device directly communicating with the compressor for spraying water onto compressed air of high temperature from the compressor to humidify the compressed air, the compressed air being led to the regenerative heat exchanger.

Abstract: The invention relates to an oil pump driven by a hydraulic motor, that is itself driven by fuel pumped by a remote fuel pump through the engine fuel line. The hydraulic fuel driven oil pump is particularly advantageous for use in a gas turbine engine, to reduce dependence on or completely eliminate the auxiliary gear box (AGB) conventionally used to mechanically connect various engine systems with an engine shaft. Separating the oil pump and other fuel/oil system components from the AGB enables the rationalization of these systems and allows designers to reconfigure systems into a compact unit including the oil pump, separator, oil tank, heat exchanger and filters for fuel and oil. Using pressurized fuel to hydraulically drive the oil pump frees the oil system from location restraints and operating limitations, and permits recovery of otherwise wasted energy from the fuel bypass circuit during idling and takeoff.

Abstract: An apparatus for moving fluid from a first location to a second location comprises a housing containing a pump body having a central passageway with a fluid inlet and first and second fluid outlets in communication with the passageway. A shuttle having first and second fluid chambers is movable within the passageway of the body between first and second positions. First, second, third, and fourth generally annular shaped fluid passageways provided in the shuttle permit selective fluid communication between the first and second fluid chambers of the shuttle and the inlet and outlet ports of the pump body. First and second inlet passageways provided in the shuttle permits selective fluid communication between the inlet of the pump body and the first and second fluid chambers of the shuttle. A piston is reciprocally movable within the shuttle chambers by a uniquely configured operating mechanism, such as a cam ring.

Abstract: A pipeline duct through a discharge opening (17) of a vane support housing (1) and an opening (6) in an outer wall (3) of a compressor housing of a gas turbine. The upper part of the pipe (2) is firmly clamped with a flange (14) and seals (7) between the bleeder connection (15) and the outer wall (3) by means of fastening elements (16). The lower part of the pipe (2) is sealed by a piston ring (8). The piston ring (8) is guided by two fastening rings (9, 10), which are mounted in the vane support housing (1) by fastening elements (16). The fastening rings (9, 10) make possible a free movement of the pipe (2) and the housing (3) in relation to the vane support housing (1) in the horizontal direction due to their free spaces (11, 12, 13).

Abstract: A pulse plasma thruster (50) utilizes a vapor producing solid (54) and a micro-sized heater (52) to produce a high pressure vapor that is directed into an ignition chamber (58) and to a thrust discharge chamber (70). The thrust discharge chamber (70) comprises two oppositely disposed electrode plates (72, 74) and oppositely disposed fuel propellants sources (60, 62). The passageway (56) leading from vapor producing solid (54) to the thrust discharge chamber (70) is configured to permit uniform feeding of the vapors to the thrust discharge chamber (70). A pair of electrode terminals (82, 84) extend from the electrode plates (72, 74) and through a housing (88). A power source (100) is coupled to the terminals (82, 84) and provides the ignition signals necessary to cause a spark and a breakdown to a useful plasma arc by controlling the voltage-current shape of the ignition signal.

Abstract: A propulsion system or aircraft engine for a helicopter or other aircraft includes an aerodynamic pod with a forward facing inlet for receiving a flow of ram air and a rearwardly facing exhaust or outlet. The system also includes a vertical shaft and one or more rotatable turbine assemblies mounted on the vertical shaft. Each of the turbine assemblies includes an inner compressor section having a plurality of blades with a first pitch and an outer turbine section having a plurality of blades at a reverse pitch. The compressor and turbine sections both forming part of a single disk or wheel. The system also includes a fuel injector for injecting fuel into the combustion chamber and an igniter for igniting the fuel air mixture within the chamber. A housing or channel directs the ram air through an angle of about 90° and through the compressor section and into the combustion chamber.

Abstract: A method for determining the appropriate hole parameters to achieve the desired airflow in a swirler with as-cast air jet holes includes the steps of determining the desired airflow through the holes and selecting a hole angle for the holes. Next, the ratio of the hole exit area to the hole inlet area is calculated based on the desired airflow and the selected hole angle using a regression equation. Then a value is determined for either of the hole exit area or the hole inlet area, and the other area is calculated from the known ratio. Once the hole angle, hole exit area and hole inlet area have been determined, then a swirler can be cast with as-cast holes using these hole parameters.

Abstract: In a method of controlling and regulating a power plant (50), in which power plant (50) thermal power is generated in a combustion chamber (35) from a gaseous fuel and the thermal power is at least partially converted into electrical power in conversion equipment (36), and in which power plant (50) the fuel for the combustion chamber (35) is produced in a fuel producer (31) from a feed product with the application of thermal and/or electrical power, which is removed at the outlet of the conversion equipment (36), and said fuel is passed on to the combustion chamber (35), optimal stability with a simultaneously wide control dynamic range are achieved in that the production of the fuel in the fuel producer (31) is stabilized by a first control loop (31, 51, 53, 60), and the conversion of the fuel into electrical power in the conversion equipment (36) is stabilized by a second control loop (36, 33, 55, 56, 58), and in that the power plant (50) as a whole is kept within a predefined operating range (a, b) by coup

Abstract: An igniter that uses the change or fluctuation pressure in a system or process to generate electrical energy by means of a piezoelectric element. This electrical energy is then relayed to an ignition device or devices that ignites combustible liquid or mixture of liquids and gasses or mixtures of gasses. The ignition can take place either in the systems combustion chamber, or, in the case of burn off of excess gasses/fluids, at the systems vent.

Abstract: A variable displacement compressor contains a displacement control valve system for controlling a displacement of fluid for compression. The displacement control valve system comprises a pressure sensing means for sensing a pressure of a suction chamber (63) or a pressure of a crank chamber (23), a transmission rod (101) supported so as to be capable of passing through a valve casing with an end thereof being in contact with this pressure sensing means, a valve body (127) for opening/closing a communication path between a discharge chamber (65) and a crank chamber (23) in correspondence to extension or contraction of the pressure sensing means while the other end of the transmission rod (101) is in contact with the valve body (127), and a solenoid (123) for applying an electromagnetic force to this valve body (127). A valve shaft (131) of the valve body (127) is supported so as to be capable of passing through a stator (111) of the solenoid (123).

Abstract: A radial flow turbine has a rotor with an internal cavity that includes a vaporization section and a condensation section. The condensation section is disposed radially inward toward the shaft and the vaporization section extends radially outward adjacent to the surface of the rotor blade. The vaporization section includes a series of pockets for dispersing the cooling fluid within each blade, and a cascaded series of capture protrusions to distribute the liquid coolant to the successive radially-arrayed pockets. A working system includes a centrifugal compressor which feeds a compressed air fuel mixture to an annular combustion chamber that, in turn, feeds the combustion gases along a radial direction to impinge on the surface of the cooled radial flow rotor. Optionally, the system is a regenerative system including a heat exchange sub-assembly which couples heat from the exhaust stream to a position between the compressor and combustion chamber.

Abstract: The invention relates to a method of inhibiting instability during operation of a gas turbine engine, where the instability is due to the uncontrolled interaction between the air filled gap defined by a heat shield and a fuel passage in a conventional fuel injector. The invention is a method of pre-treating the fuel injectors to form a precipitant, such as coke, within the insulating air gap in a controlled and predictable manner prior to installation of the injector into the engine. In this way, the precipitant is present on initial engine operation and impedes the flow of air and fuel within the gap, thus substantially reducing or eliminating engine instability.

Abstract: A controller is disclosed that operates a gas turbine such that a desired reserve power capacity is maintained. The inlet guide vane angle of the compressor is applied as an indicator of the reserve capacity of the gas turbine. The actual inlet guide vane angle is continuously compared to an intended inlet guide vane angle that corresponds to a desired reserve capacity. A controller adjusts the fuel flow to the gas turbine to adjust the turbine output power and thereby maintain the actual inlet guide vane angle at the intended value corresponding to the desired reserve capacity.

Abstract: A lean-burn combustor for a gas-turbine engine has a radial inflow pre-mixing, pre-swirling burner with a central burner face which forms the upstream wall of a pre-chamber of the combustor. A circular recess is formed in the burner face, the recess having at least one pilot fuel injector for introducing pilot fuel tangentially into the recess, whereby the burner runs cooler and combustion characteristics are improved.

Abstract: A fuel injector (32) for a gas turbine engine combustion chamber (22) comprises a fuel injector nozzle (34) and a fuel feeding member (36). A wire mesh (76) is located in a space (74) defined between a hollow outer member (72) arranged around and spaced from a hollow inner member (70) of the fuel feeding member (36) and a fuel nozzle body (54) of the fuel injector nozzle (34). The wire mesh (76) rubs against the hollow outer member (72), the hollow inner member (70) and the fuel nozzle body (54) to frictionally damp vibrations of the fuel injector (32).