Abstract: A tribological and creep resistant system configured to operate at temperatures in excess of 700° C. A seal body extends between a leading edge and a trailing edge. A first component contact surface is adjacent the leading edge and a second component contact surface is adjacent the trailing edge. The seal body is formed from a high entropy alloy.

Abstract: Electrical power systems for distributing electrical power in aircraft are described. One such electrical power system comprises: an electrical power source configured to output a number R?2 of dc power channels, each dc power channel having a respective index r=(1, . . . , R); and a group of N dc load channels connected to the R dc power channels by a switching arrangement, wherein each dc load channel has a respective index n=(1, . . . , N) and R<N?2R. The switching arrangement is operable to connect the r-th power channel to the n-th load channel according to a relationship r(n).

Abstract: An aircraft turbine engine includes a gas generator and a fan arranged upstream of the gas generator and configured to generate a main gas flow, of which one portion flows in a stream from the gas generator to form a primary flow, and of which another portion flows in a stream around the gas generator to form a secondary flow. The gas generator includes a low pressure body having a rotor driving the fan by means of a crown of a mechanical planetary reduction gear. The turbine engine further includes an electrical machine mounted coaxially around the reduction gear and having a rotor rotated by the crown of the reduction gear, and a stator extending around the rotor of the electrical machine.

Abstract: A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

Abstract: Improved gimbal systems, apparatus, articles of manufacture and associated methods are disclosed. Examples include a panel including a window, the window to define an aperture for a sensor; a platform to mount the sensor, the platform including a first pinion; a first stepper motor to move the first pinion about a first arched rack; a gimbal body including the first arched rack and a second pinion; and a second stepper motor to move the second pinion about a second arched rack, the second arched rack positioned orthogonally to the first arched rack.

Abstract: A turbine shaft of a turbomachine extending along a longitudinal axis (A) includes a main tubular portion with a length L1 and a maximum outer main diameter. The shaft further includes a secondary tubular segment with a length L2 and a maximum outer secondary diameter greater than the maximum outer main diameter. The secondary tubular segment extends radially from the shaft such that the main tubular portion extends on either side of the secondary tubular segment along the longitudinal axis (A). The secondary tubular segment includes a weak point that is configured to break the shaft into two distinct parts when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value, and thus cause retraction of the turbine.

Abstract: An aspect of the present disclosure provides a diagnosis device for an internal combustion engine. The internal combustion engine 1 includes a variable geometry type turbocharger 14, and the turbocharger includes a variable vane 28, a link mechanism configured to operate the variable vane, and an actuator 29 configured to drive the link mechanism. The diagnosis device includes a control unit 100 configured to control an opening degree of the variable vane by controlling the actuator. The control unit determines that an abnormality has occurred in the link mechanism of the turbocharger when an operating time of the internal combustion engine in a predetermined operating region exceeds a predetermined upper limit value and a differential pressure between a target boost pressure determined according to an operating state of the internal combustion engine and an actual boost pressure exceeds a predetermined upper limit value.

Abstract: Various embodiments herein pertain to apparatus and methods that utilize the water and existing chemicals to generate a foam. The foam can be introduced at that gas-path entrance of the equipment, where it contacts the stages and internal surfaces, to contact, scrub, carry, and remove fouling away from equipment to restore performance. Various embodiments include operating a gas turbine engine; measuring the performance of the engine during operation; determining that the engine should be foam washed based on the measurements; mixing pressurized gas with pressurized liquid and creating a supply of foam; and streaming the supply of foam into the engine.

Abstract: A turbo shield with a slit, wherein the slit is configured to allow an inner diameter across the turbo shield to increase and decrease without altering the properties of fibers associated with the turbo shield.

Abstract: A method for forming a ceramic matrix composite (CMC) component with an internal cooling channel includes partially densifying a first fiber preform to form a portion of a final ceramic matrix volume, machining a first channel into a surface of the partially densified first fiber preform, covering the first channel with a fibrous member to form a near net shape fiber preform with an internal passage formed by the first channel and the fibrous member, and densifying the near net shape fiber preform.

Abstract: An energy generation system for converting combustible fluid from a nontraditional combustible fluid source to useable energy. The energy generation system including a fluid storage system including a compressor and at least one storage tank, the compressor configured to pressurize a combustible fluid from a combustible fluid source for storage in the one or more storage tanks; and an energy recovery system configured to receive the combustible fluid from the at least one storage tank, the energy recovery system including: a turboexpander configured to depressurize the combustible fluid received from the at least one storage tank; a motor-generator configured to input the combustible fluid as depressurized by the turboexpander, and generate electrical energy from the combustible fluid; and an organic Rankine cycle (ORC) system configured to generate electrical energy based on a temperature differential between the combustible fluid input to the motor-generator and a waste heat produced by the motor-generator.

Abstract: A method includes determining a value of an operational motor current limit and setting a value of a startup current limit equal to a predetermined value in excess of the value of the operational motor current limit if a set of predetermined conditions is satisfied. The method includes determining that operation of the engine has been interrupted, operating the electric motor of the variable valve timing mechanism with a current having a magnitude that is less than or equal to the startup current limit after determining that operation of the engine has been interrupted, determining that operation of the engine has resumed, and operating the electric motor of the variable valve timing mechanism with a current having a magnitude that is less than or equal to the operational motor current limit after determining that operation of the engine has resumed.

Abstract: An expandable engine fluid catcher that is configured to attach to an engine fluid filter, such as an oil filter, and catch engine fluid as the fluid filter is removed from the engine. An engine may be part of a vehicle and the engine fluid filter may be an oil filter. An expandable engine fluid catcher has a retainer portion having a retainer band that is secured around the engine fluid filter. Most engine fluid filters are cylindrical in shape and therefore a band, and in particular an elastic band, may be used to attach the expandable engine fluid catcher to the fluid filter. A pleated portion of the expandable engine fluid catcher has a plurality of pleats that extend from the retainer band upward to an expandable end that can be flared out, or expanded, to provide a larger diameter for catching engine fluid therein.

Abstract: A method of controlling an electric oil pump (EOP) for a vehicle includes, if a current temperature of oil is lower than a reference temperature, determining whether an EOP RPM is lower than a minimum driving RPM, if the EOP RPM is lower than the minimum driving RPM, applying a first reduction rate for a first setting time and reducing a target line pressure and an instruction RPM of the EOP, if the EOP RPM is equal to or higher than the minimum driving RPM, determining whether vibration of the EOP RPM is generated above a reference vibration, and if the vibration is generated above the reference vibration, applying a second reduction rate for a second setting time and reducing the target line pressure or the instruction RPM of the EOP.

Abstract: An exhaust muffler for an exhaust system of an internal combustion engine, especially for a vehicle, includes a muffler housing with a flow volume (42), through which exhaust gas can flow, an exhaust gas inlet (28) and an exhaust gas outlet (36). A first resonator chamber (44) is open towards the flow volume (42) via a first resonator neck (68). A second resonator chamber (46) is open towards the flow volume (42) via a second resonator neck (74). A resonator pipe (52) provides the first resonator neck (68) and the second resonator neck (74).

Abstract: Disclosed herein are monolith oxidation catalysts for the destruction of CO and volatile organic compounds (VOC) chemical emissions, in particular, the destruction of light alkane organic compounds. The catalysts contain high surface area refractory oxides of silica- and hafnia-doped zirconia and silica, or tin oxide or stabilized alumina; and at least one platinum group metals, in particular platinum metal, or a combination of platinum and palladium.

Abstract: One or more techniques and/or systems are disclosed for providing localized heating within an engine exhaust aftertreatment system. The localized heating includes DEF injector nozzle heating with a DEF dispensing system having a DEF fluid supply and a DEF injector fluidly coupled to the DEF fluid supply. The DEF injector includes a DEF injector nozzle. The DEF dispensing system further includes a DEF heater positioned in proximity to the DEF injector nozzle. The DEF heater is configured to locally heat an area surrounding the DEF injector nozzle.

Abstract: A method for determining a reference value of a presence of at least one substance (NOx) occurring in an exhaust gas stream of an internal combustion engine (101), wherein the at least one substance is subjected to exhaust treatment, the exhaust treatment being carried out in dependence on the reference value (Emref; Emref,1; Emref,2) When the internal combustion engine (101) is started: accumulating the occurrence (EmACC,1; EmACC,2) of the at least one substance (NOx) downstream from the exhaust treatment during a first period, and determining whether to redetermine the reference value (Emref; Emref,1; Emref,2) based on the accumulated occurrence (EmACC,1; EmACC,2) of the at least one substance (NOx).

Abstract: A control module for an aftertreatment system that includes a selective catalytic reduction (SCR) catalyst and an oxidation catalyst, comprises a controller configured to be operatively coupled to the aftertreatment system. The controller is configured to determine an actual SCR catalytic conversion efficiency of the SCR catalyst. The controller determines an estimated SCR catalytic conversion efficiency based on a test sulfur concentration selected by the controller. In response to the estimated SCR catalytic conversion efficiency being within a predefined range, the controller sets the test sulfur concentration as a determined sulfur concentration in a fuel provided to the engine. The controller generates a sulfur concentration signal indicating the determined sulfur.

Abstract: The present disclosure provides an exhaust gas purification material and an exhaust gas purification device that can efficiently remove harmful components even after being exposed to high temperature. Such exhaust gas purification material comprises metal oxide particles and noble metal particles supported on the metal oxide particles. The noble metal particles have a particle size distribution with a mean of 1.5 nm and 18 nm and a standard deviation of less than 1.6 nm.

Abstract: A catalytic converter includes a catalyst substrate including a body having a length and defining a plurality of zones along the length, with each zone having at least one cross-sectional structure defining a plurality of cells forming an exhaust gas flow path through the length via cells of adjacent zones, and the cells being more densely arranged within the at least one cross-sectional structure of an upstream zone than an adjacent downstream zone. The catalytic converter also includes a wash-coat layer deposited on surfaces of the cells forming active surface area configured to react with exhaust gas traveling along the length. The exhaust gas flows along the exhaust gas flow path through the cells such that more active surface area is available for reaction in each upstream zone than an adjacent downstream zone.

Abstract: An exhaust gas purification device including: a first case communicating with an exhaust manifold of an engine and internally including a first exhaust gas purification body for removing a carbon compound; and a second case communicating with an exhaust outlet of the first case and internally including second exhaust gas purification bodies for removing a nitrogen compound. The first case and the second case are arranged above the engine and in an L-shape to respectively extend along two side surfaces of the engine, the two side surfaces being adjacent to each other.

Abstract: A process for detecting reductant deposits includes accessing data indicative of signal output from a radiofrequency sensor positioned proximate a decomposition reactor tube; comparing the data indicative of signal output from the radiofrequency sensor to a deposit formation threshold; and activating a deposit mitigation process responsive to the data indicative of signal output from the radiofrequency sensor exceeding the deposit formation threshold.

Abstract: In one aspect, a system is provided and includes an engine including an exhaust valve, an exhaust manifold downstream of the exhaust valve and a muffler downstream of the exhaust manifold. The system also includes a catalyst positioned downstream of the exhaust valve.

Abstract: Various methods and systems are provided for controlling air flow through an engine by adjusting an electric turbocharger of a vehicle. In one embodiment, a system for a vehicle comprises an electric turbocharger comprising a compressor, an exhaust turbine coupled to the compressor via a shaft, and an electric machine mechanically coupled to the shaft; and a controller including a processor and instructions stored on a non-transient memory of the controller that, when executed, cause the controller to: adjust an amount of power provided to or extracted from the shaft by the electric machine based on at least one of a speed of the electric turbocharger, a cylinder pressure, and an exhaust gas temperature. By adjusting the amount of power provided to or extracted from the electric machine, the exhaust gas temperature and the speed of the electric turbocharger may be efficiently maintained within a desired operating range.

Abstract: An energy storage plant includes a casing for the storage of a working fluid other than atmospheric air, in a gaseous phase and in equilibrium of pressure with the atmosphere; a tank for the storage of said working fluid in a liquid or supercritical phase with a temperature close to the critical temperature; wherein said critical temperature is close to the ambient temperature. The plant is configured to carry out a closed thermodynamic cyclic transformation, first in one direction in a charge configuration and then in the opposite direction in a discharge configuration, between said casing and said tank; wherein in the charge configuration the plant stores heat and pressure and in the discharge configuration generates energy.

Abstract: Methods and systems for operating a rotorcraft comprising a plurality of engines are provided. A request to enter into an asymmetric operating regime (AOR), in which at least one active engine of the plurality of engines is operated in an active mode to provide motive power to the rotorcraft and at least one standby engine of the plurality of engines is operated in a standby mode to provide substantially no motive power, is obtained. Engine usage data for the plurality of engines, including at least one first engine and at least one second engine, is determined. Based on the engine usage data, one of the at least one first and second engines is operated as the at least one active engine for the AOR, and the other one of the at least one first and second engines is operated as the at least one standby engine for the AOR.

Abstract: Control of low pressure recoup air in a gas turbine engine disposed in a gas turbine enclosure with low pressure recoup air piping coupled to a gas turbine combustion exhaust and gas turbine engine enclosure is disclosed. A first valve of the piping controls a flow of the recoup air to the gas turbine combustion exhaust. A second valve of the piping diverts the recoup air to the enclosure for eventual flow to the air intake. A controller controls the flow of the recoup air from the piping to the exhaust and/or the enclosure as a function of ambient and air intake temperature measurements, and a predetermined temperature requirement having an ambient temperature constraint and an air intake temperature differential constraint.

Abstract: An optimized protection against ice on the inner and outer faces of an aircraft engine nacelle air intake with the air intake including an outer face and an inner face meeting at a line at the longitudinally extreme, called extremum line, an acoustic panel being installed on the inner surface of a part of the inner face. An elimination system based on vibration of the ice formed is put in place on at least a part of the outer face and an ice formation prevention system using a hot fluid is put in place on at least a part of the inner face and either an ice elimination system or an ice formation prevention system using a hot fluid is installed on the inner face and on the outer face, a marking line marking the boundary between the two systems.

Abstract: An air intake system for an aircraft, which is switchable between a performance mode and a filtered mode, includes a duct forming filtered air inlet slits. The air intake system also includes interconnected gills adjacent to the filtered air inlet slits. The gills are movable between various gill positions including a closed position substantially covering the filtered air inlet slits and an open position substantially exposing the filtered air inlet slits. The air intake system also includes an actuator configured to move the gills into the closed position in the performance mode and the open position in the filtered mode.

Abstract: Structures, such as compressor casings, for reducing a thermal gradient are provided. For example, a compressor case is split such that it includes first and second case segments. The first case segment extends over a first portion of the compressor case circumference and comprises a first inner structure, a first outer structure, and a first porous structure integrally formed as a monolithic component. The first porous structure is defined between the first inner structure and the first outer structure. The second case segment extends over a second portion of the compressor case circumference and comprises a second inner structure, a second outer structure, and a second porous structure integrally formed as a monolithic component. The second porous structure is defined between the second inner structure and the second outer structure. Methods of cooling structures such as compressor casings also are provided.

Abstract: A passive flow splitting system for use in a turbine engine control system to provide split fuel flow to two fuel manifolds to supply primary and secondary fuel injectors for the particular combustion zones thereof utilizing intentionally different split ratios dependent on ascending or descending combustion fuel flow is provided. The system includes a passive fuel divider valve (FDV) that includes a primary piston and a secondary piston. The primary piston is moveable independently from the secondary piston during a portion of its stroke, and is hydro-locked to the secondary piston during another portion of its stroke. An ecology valve is also provided to purge the fuel from the primary and/or secondary manifolds during different modes of operation. A transfer valve is included to control the position of ecology piston of the ecology valve.

Abstract: A torch igniter for a combustor of a gas turbine engine includes an igniter body and an igniter head. The igniter body is disposed within a high-pressure case of a gas turbine engine and extends primarily along a first axis, and includes an annular wall and an outlet wall. The annular wall surrounds the first axis and defines a radial extent of a combustion chamber therewithin. The outlet wall is disposed at a downstream end of the annular wall, defines a downstream extent of the combustion chamber, and includes an outlet fluidly communicating between the combustion chamber and an interior of the combustor. The igniter head is removably attached to the igniter body at an upstream end of the annular wall, wherein the igniter head defines an upstream extent of the combustion chamber, and includes an ignition source and a fuel injector.

Abstract: A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gear layshafts that each support a first stage planet gear and a second stage planet gear, and a ring gear. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and the plurality of planet gear layshafts have a tubular shape.

Abstract: The present disclosure provides an electrically gear turbofan that includes a fan; a first spool shaft; and an electrical gearbox including: an armature winding connected to the first spool shaft and coupled to a power source; and a magnetic receiver connected to the fan, and wherein an air gap is defined between the armature winding and the magnetic receiver. The turbines and electrical gearing enable an operator to rotate the spool shaft at a first rotational speed; power an armature winding to generate an armature magnetic field, wherein the armature magnetic field rotates at a second rotational speed; transfer rotational energy via the armature magnetic field from the spool shaft to the magnetic receiver; and rotate the fan at a third rotational speed. In some aspects, the third rotational speed is controlled via a direction and a magnitude of the second rotational speed relative to the first rotational speed.

Abstract: A gas turbine engine configured with an engine core. A fan located upstream of the engine core, the fan comprising a plurality of fan blades; and a gearbox arranged to receive an input from the core shaft and to output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft. The gearbox being an epicyclic gearbox comprising a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted, the planet carrier having an effective linear torsional stiffness and the gearbox having a gear mesh stiffness between the planet gears and the ring gear. Additionally, the product of the effective linear torsional stiffness of the planet carrier and the gear mesh stiffness between the planet gears and the ring gear is greater than or equal to 5.0×1018N2m?2.

Abstract: A speed reducer, particularly of an aircraft, includes a central sun gear mounted to rotate with a drive shaft about a rotation axis X, an annular ring gear coaxial with the X axis, and a plurality of planet gears arranged about the X axis and mounted to be movable on a planet carrier. The planet gears engages the sun gear and the annular ring gear, which extends around the planet gears. The speed reducer further includes a lubricant recovery device having a pipe for recovering lubricant discharged from the reducer by centrifuging. The recovery device has scoops mounted to pivot about a pivot axis P on a movable member of the speed reducer that rotates about the X axis between a deployed state and a rest state.

Abstract: An engine for an aircraft includes an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox. The gearbox is an epicyclic gearbox and comprises a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The radial bending stiffness of the planet carrier is equal to or greater than 1.20×109 N/m, and/or the tilt stiffness of the planet carrier is greater than or equal to 6.00×108 Nm/rad. A method of operation of such an engine is also disclosed.

Abstract: A flow rate per unit time of fuel fed to a gas turbine is calculated. A flow rate per unit time of air fed to the gas turbine is calculated. A turbine inlet temperature is calculated through use of a physical model formula expressing a relationship of input and output of thermal energy relating to a combustor of the gas turbine. A fuel distribution ratio for each of a plurality of fuel supply systems connected to the combustor is calculated based on the turbine inlet temperature.

Abstract: An aircraft including lean-burn gas turbine engines operating in pilot-plus-mains mode with a given initial fuel flow W0, a method of controlling the optical depth of contrails produced by a first group of engines includes the steps of (i) reducing fuel flow to each engine in the first group to change the operation of each engine from pilot-plus-mains mode to pilot-only mode, and (ii) adjusting fuel flow to one or more engines in a second group of engines such that the total fuel flow to engines of the second group is increased, all engines of the second group remaining in pilot-plus-mains mode, and wherein the set of lean-burn engines consists of the first and second groups. Depending on atmospheric conditions, the average optical depth of contrails produced by the engines may be enhanced or reduced compared to when all engines operate in pilot-plus-mains mode with a fuel flow W0.

Abstract: A propulsion system for an aircraft includes a gas turbine engine and a fuel tank, wherein the fuel includes at least a proportion of a sustainable aviation fuel—SAF—having a density between 90% and 98% of the density, ?K, of kerosene and a calorific value between 101% and 105% the calorific value CVK, of kerosene. The engine includes a combustor; and a fuel pump arranged to supply a fuel thereto at an energy flow rate, C, the pump being arranged to output fuel at a volumetric flow rate, Q, the percentage of fuel passing through the pump not provided to the combustor being referred to as a spill percentage. The fuel include X % SAF, where X % is in the range from 5% to 100%, and has a density, ?F, and a calorific value CVF.

Abstract: A method of determining a calorific value of fuel supplied to a gas turbine engine of an aircraft comprises sensing at least one engine parameter during a first time period of aircraft operation during which the gas turbine engine uses the fuel; and, based on the at least one sensed engine parameter, determining a calorific value of the fuel. The sensing may be repeated such that the at least one engine parameter is monitored over time. The gas turbine engine may be a propulsive gas turbine engine of the aircraft or a gas turbine engine of an auxiliary power unit of the aircraft.

Abstract: A method and system for controlling fuel flow to an aircraft engine during start are provided. Following light-off, an actual value of at least one engine operating parameter is obtained. Based on a difference between the actual value and a target value, a first command is generated to cause fuel flow to be provided to the engine's combustor according to a computed fuel flow rate defined by a fuel schedule of the engine. When the computed fuel flow rate is within a fuel flow rate limit, the first command is output. Otherwise, a limiting factor is applied to the computed fuel flow rate to limit a reduction in fuel flow to the combustor and a limited fuel flow rate is obtained, and a second command is output to cause fuel flow to be provided to the combustor according to the limited fuel flow rate.

Abstract: To control a hybrid dynamical system, a predictive feedback controller formulates a mixed-integer nonlinear programming (MINLP) problem including nonlinear functions of continuous optimization variables representing the continuous elements of the operation of the hybrid dynamical system and/or one or multiple linear functions of integer optimization variables representing the discrete elements of the operation of the hybrid dynamical system. The MINLP problem is formulated into a separable format ensuring that the discrete elements of the operation are present only in the linear functions of the MINLP problem. The MINLP problem is solved over multiple iterations using a partial convexification of a portion of a space of the solution including a current solution guess. The partial convexification produces a convex approximation of the nonlinear functions of the MINLP without approximating the linear functions of the MINLP to produce a partially convexified MINLP.

Abstract: Spark ignition engine operation at higher RPM so as to reduce alcohol requirements in high efficiency alcohol enhanced gasoline engines is disclosed. Control of engine upspeeding (use of a higher ratio of engine RPM to wheel RPM) so as to achieve an alcohol reduction objective while limiting any decrease in efficiency is described. High RPM alcohol enhanced gasoline engine operation in plug-in series hybrid powertrains for heavy duty trucks and other vehicles is also described.

Abstract: Systems, apparatuses and methods in interoperating with multiple clean energy sources, such as pneumatic energy, electrical energy, hydrogen energy and steam energy, with engine configurations employing theses clean energy sources dynamically and synchronously. Further embodiments including fossil fuel energies.

Abstract: Fuel management system for enhanced operation of a spark ignition gasoline engine. Injectors inject an anti-knock agent such as ethanol directly into a cylinder. It is preferred that the direct injection occur after the inlet valve is closed. It is also preferred that stoichiometric operation with a three way catalyst be used to minimize emissions. In addition, it is also preferred that the anti-knock agents have a heat of vaporization per unit of combustion energy that is at least three times that of gasoline.

Abstract: A method provides for operating an engine configured to use a plurality of differing fuels. The method includes determining a fuel combustion ratio of the plurality of differing fuels associated with at least one engine cylinder of the engine based at least in part on one or more of a plurality of characteristic profiles. This maintains one or more of a plurality of actual values associated with usage of the plurality of differing fuels relative to defined corresponding threshold values. The fuel combustion ratio includes a ratio of the plurality of differing fuels to be delivered to the at least one engine cylinder. A fuel delivery system delivers the plurality of differing fuels to the at least one engine cylinder based on the fuel combustion ratio.

Abstract: A system includes a fuel tank and a dehydration reactor that are configured to provide a primary fuel and a pilot fuel to a power system. The fuel tank is configured to store the primary fuel and is fluidly connected to a reactor feed line and a primary fuel line provide the primary fuel. The dehydration reactor is configured to receive the primary fuel via the reactor feed line and convert a portion of the primary fuel to the pilot fuel and a byproduct. The power system is configured to receive the pilot fuel from the dehydration reactor to initiate combustion of the primary fuel. The power system also includes a cylinder with an internal piston that receives the pilot fuel and the primary fuel, contains the combustion reaction, and generates power from the combustion reaction; and contains the combustion reaction.

Abstract: An engine system, includes a bypass line branched from an intake line upstream of an intercooler and joining the intake line downstream of the intercooler; a condensed water separation line branched from the intake line upstream of the intercooler and joining the intake line upstream of the intercooler; a condensed water separation module provided in the condensed water separation line and configured to separate condensed water contained in a mixture flowing through the condensed water separation line; and a four-way valve provided in the intake line between a compressor and the intercooler, and selectively operated so that the mixture of the outside air and the recirculation gas introduced to the upstream of the intercooler passes through the intercooler, flows through the bypass line, or flows through the condensed water separation line.