Abstract: A process for upgrading pyrolysis oil that includes heating pyrolysis oil in the absence of added catalyst at 100° C. to 200° C. temperature and 50 bar to 250 bar pressure, and heating the product of the first heating in the absence of added catalyst at 200° C. to 400° C. temperature and 50 bar to 250 bar pressure. Also, the product obtained by this process and the use of treated pyrolysis oil. Further, methods where the treated pyrolysis oil is fed to a power plant for producing electricity; is burned in a boiler for producing heating oil and/or is used as transportation fuel or as a blending component in transportation fuel.

Abstract: A gas turbine engine includes a nacelle, a lower bifurcation structure, and a heat exchanger. The nacelle extends circumferentially around an engine core and defines a fan bypass duct that is substantially annular between an inner wall and an outer wall. The lower bifurcation structure extends between the inner wall and the outer wall, bifurcating the fan bypass duct. The lower bifurcation structure defines a bifurcation duct extending along a central axis of the lower bifurcation structure. A heat exchanger is positioned in the bifurcation duct.

Abstract: This invention of a continuous motion revolving piston engine describes a machine comprising piston(s) fitted to rings that revolve around a stator circular base which has a cavity in which a disc fits to create a closed combustion compartment together with the casing. The disc has a disc cavity to allow the piston to pass. The rotation of the disc and piston are synchronized to allow the piston to pass through the disc cavity. As there are no reciprocating parts and optionally enables an oil free operation, it is more efficient and has cleaner exhaust than existing engines.

Abstract: A gas turbine health monitoring fuel system including a fuel splitter, a first and second fuel nozzle, a first and second fuel pump, and a common drive coupled to the first and second fuel pumps. The first and second fuel pumps are downstream from the fuel splitter. The first fuel nozzle is fluidly coupled to the first fuel pump by a first fuel stream. The second fuel nozzle is fluidly coupled to the second fuel pump by a second fuel stream. The common drive is configured to drive the first and second fuel pumps at a same speed. The controller system is configured to determine a first fuel pressure in the first fuel stream, determine a second fuel pressure in the second fuel stream, and identify a difference between the first and second fuel pressures.

Abstract: A device and a method of temporarily increasing power of at least a first turbine engine is disclosed. The device includes a coolant liquid tank and a first injection circuit connected to the tank and leading to at least one injection nozzle suitable for being installed upstream from at least one compressor stage of the first turbine engine. This first injection circuit includes at least a first flow valve configured to open when a pressure exceeds a predetermined threshold compared with a downstream pressure from at least one compressor stage of a second turbine engine so as to enable the coolant liquid to flow towards the injection nozzle of the first injection circuit.

Abstract: The present disclosure relates to a centering device for a nacelle of a turbojet engine providing the flush centering of an outer downstream panel of a thrust reverser with respect to a cowl of a fan casing. The centering device includes, in one single piece: a sub plate allowing the fixing of the centering device to the fan casing; a first positioning arm integrally formed with the sub plate, protruding upstream, in such a manner as to form, with respect to a directing axis (A) of the nacelle; a first radial abutment designed for guiding the cowl of the fan casing; and a second positioning arm, integrally formed with the sub plate, protruding downstream, in such a manner as to form, with respect to the directing axis (A) of the nacelle, a second radial abutment designed for guiding the outer downstream panel.

Abstract: The present disclosure relates generally a system for preventing relative rotation between three components. The three components include tabs and slots such that at least one first tab and at least one second tab on one component is disposed within at least one slot formed in the other two components to prevent relative rotation between any two of the three components.

Abstract: In a gas turbine engine, an annular intermediate-temperature space is formed by a first partition member extending from an inner platform radially inward and a second partition member having a radially inner end portion fixed to the first partition member and a radially outer end portion facing the inner platform, the inner platform being connected to radially inner ends of nozzle guide vanes of a turbine, and the intermediate-temperature space overlapping with the inner platform over substantially its axial entire length. The low-temperature space, supplied with a low-temperature air from a compressor, is formed on a radially inside of the second partition member. Therefore, a temperature of the intermediate-temperature space is maintained at an intermediate temperature between those of a combustion gas and the air, reducing a temperature difference of the inner platform from an outer platform and the vanes to reduce a thermal stress.

Abstract: An apparatus for controlling a gas-turbine aeroengine is configured to calculate a fuel command to supply fuel based on a calculated desired rotational speed of a low-pressure turbine calculated from an operation angle of a thrust lever installed at an aircraft cockpit pilot's seat, determines whether it is a time point for outputting a command to open/close a bleed-off valve equipped at a high-pressure compressor connected to a high-pressure turbine and to supply the fuel command based on the time point when it is determined to be the time point for outputting the command to open/close the bleed-off valve.

Abstract: An annular venturi burner assembly and Stirling engine. The annular venturi burner injects fuel into combustion air flowing axially through a port with an annular cross section. The fuel enters the annular cross-section from the outside diameter. The flow of air through the annular section creates suction that draws the fuel through the ports. A venturi bushing directs the flow of fuel to provide improved and more uniform mixing of fuel and air.

Abstract: A helicopter engine air intake including an anti-icing grid that provides a large bypass flow in event of icing. The air intake includes air intake lips and an anti-icing grid mounted on outer ends of the air intake lips, being interposed in the air flow penetrating into the air intake, at least one air intake lip being formed by a thin metal sheet.

Abstract: A gas turbine engine has a fan rotor for delivering air into a bypass duct and into a core airflow duct. Air in the core flow duct passes axially downstream from the fan and past a reverse core engine including a turbine section, a combustor section, and a compressor section. The core airflow duct reaches a turning duct which turns the airflow radially inwardly to communicate with an inlet for the compressor section. Air in the compressor section passes to the combustor section. Products of the combustion pass downstream across a turbine rotor. An exhaust turning duct communicates products of the combustion from a full cylindrical portion downstream of the turbine rotor through a plurality of circumferentially separated mixing lobe outlets to mix with the bypass air in the bypass duct. The bypass duct extends past the mixing lobe outlets, and is defined circumferentially intermediate the mixing lobe outlets.

Abstract: The application relates to a system for using the waste heat of an internal combustion engine through the Clausius-Rankine cycle. Such system prevents operating medium from the Clausius-Rankine cycle from leaking into combustion air or exhaust air. The system has a first flow channel formed by at least one first limiting component and a second flow channel formed by at least one second limiting component. The system has a fluid-conducting connection to the surroundings or to a receiving chamber from the first limiting component and preferably from the second limiting component, so that in the event of a leak the operating medium is conducted into the surroundings or into the receiving chamber.

Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor discharge casing, a number of combustors configured in an annular array, and a number of aft mounting assemblies. An aft mounting assembly mounts a combustor to an inner diameter of the compressor discharge casing.

Abstract: A fuel nozzle assembly for a gas turbine engine is disclosed herein. The fuel nozzle assembly may include a fuel injector including an outer jacket having a first end and a second end with a threaded surface disposed therebetween. The first end of the fuel injector may include a cylindrical sealing surface. The fuel nozzle assembly also may include an annular hub including an aperture having a first end and a second end with a threaded surface disposed therebetween. The aperture may be configured to at least partially house the fuel injector therein and includes a conical seat about the first end. The cylindrical sealing surface may swage inward along the conical seat to form a seal therebetween as the liquid fuel injector is threaded into the aperture.

Abstract: A vehicle propulsion system includes an air heating chamber that receives inlet air from an air intake chamber and provides thrust through an exhaust chamber. A battery powered pulse generator generates a pulsed electrical output signal. An amplifier amplifies the pulsed electrical output signal to provide an amplified pulsed power output signal to the air heating chamber. The amplified pulsed power output signal directly heats the inlet air to generate thrust through the exhaust chamber.

Abstract: A stator airfoil of a gas turbine engine according to one embodiment includes at least two winglets projecting transversely from opposed sides of a stator airfoil, respectively. Each winglet includes a leading edge axially and outwardly extending from one of the opposed sides of the stator airfoil and a trailing edge extending from the stator airfoil to join with the leading edge of the winglet. The winglets therefore provide a wide trailing edge thereof to aerodynamically manage boundary layers and micro-shocks of a working fluid.

Abstract: A power plant (10) having a first and second turboshaft engines (11, 16) and an emergency system (20) for injecting fluid into said engines (11, 16). First and second pressurization pipes (26, 28) connect a tank (21) to each gas generator of the engines. In addition, the system (20) includes an injector device (35, 40) for each engine, which device comprises an injector pipe (36, 41) connecting said tank (21) to at least one injector nozzle (31). A distributor (51, 52) is arranged on each injector pipe (36, 41), each valve (51) feeding one of the engines while being connected to the gas generator of the other engine.

Abstract: A concentrating solar power collector plant is provided in which a pressurized solar power receiver with an associated gas turbine and a low-pressure solar power receiver are used together with a common thermal energy storage system. Exhaust from the gas turbine is connected to the thermal energy storage system to deliver residual heat to the thermal energy storage system in addition to that received from the low-pressure solar power receiver. The pressurized solar power receiver may be a separate unit from the low-pressure receiver and at least some heliostats are controlled to redirect reflected solar energy from one solar power receiver to the other. The pressurized solar power receiver may alternatively be combined with the low-pressure receiver in a single unit having a heat receiving part of a high-pressure receiver and a flow passage for heating air between an inlet and an outlet to form the low pressure receiver.

Abstract: A method for adjusting startup floor pressure levels of HRSG steam circuits is implemented by a pressure controlling computing device including a processor and a memory. The method includes receiving a plurality of measured plant operating values associated with a HRSG steam circuit, identifying a plurality of candidate pressure levels for use in pressurizing the HRSG steam circuit, determining a calculated steam velocity level for each of the plurality of candidate pressure levels, identifying a steam velocity limit for a steam piping section of the HRSG steam circuit, selecting a lowest pressure level of the plurality of candidate pressure levels, wherein the lowest pressure level is associated with a determined calculated steam velocity level that does not exceed the identified velocity limit, and pressurizing the HRSG steam circuit to the selected lowest pressure level.