Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a scallop formed along at least one surface of the groove, wherein the scallop is configured to provide a flow path, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors made of CMC material and forming a turbine ring, each ring sector including an annular base with respective end portions having edges that are held facing an edge of the end portion of the annular base of a sector that is adjacent in the turbine ring. The assembly includes resilient holder devices for holding the ring sectors in position on the ring support structure, and each resilient holder device includes a spring element present beside the outside face of the ring support structure.

Abstract: A stator assembly includes a platform located on a radially inner end of a plurality of vanes that connects a first vane to a second vane. There is a platform groove on a radially inner side of the platform between the first vane and the second vane.

Abstract: An airfoil includes an airfoil body extending from an inner diameter platform to an opposed outer diameter platform along a longitudinal axis. The airfoil body defines a leading edge and a trailing edge and has a cavity defined between the leading edge, the trailing edge, the inner diameter platform and the outer diameter platform. The cavity includes an airfoil protrusion extending inward from an inner surface of the airfoil body. The airfoil includes a baffle body within the cavity extending along a baffle body axis. The baffle body has a baffle protrusion extending along a central protrusion axis at an angle with respect to the baffle body axis. The end of the baffle protrusion abuts an end of the airfoil protrusion. A flow path is defined between the inner surface of the airfoil body and the outer surface of the baffle body.

Abstract: An engine component for isolating a first pressure and/or first flow and a second pressure and/or second flow is provided. The engine component may comprise a body portion, a first seal element and a second seal element. The body portion may include a first standoff and a second standoff. The first seal element housed within the body portion. The second seal element may also be housed within the body portion. The second seal element may be coupled to the first seal element.

Abstract: A casting core for a Blade Outer Air Seal includes a heat exchange cavity core section in communication with a first plenum section and a second plenum section, the first plenum and the second plenum section are of a thickness greater than the heat exchange cavity section.

Abstract: The invention proposes a guide arm for guiding at least one element having an elongated shape (20), corresponding to a set of cables and/or pipes. The arm comprises an inner cavity (62) opening on the outside of the arm at each of the ends thereof, and in which the elements having an elongated shape can extend. According to the invention, this structure more particularly comprises: a frame (8) comprising a beam (18) linked to means (30, 36, 44) for holding the elements having an elongated shape on the outside and along the beam, and a cover (54) of which the walls (56, 58) cover the holding means of the frame, and are engaged with the beam, in such a way as to form the inner cavity in which the elements having and elongated shape extend, shock-absorbing means (68) being arranged between the means (30, 36, 44) for holding the elements having an elongated shape (20), and the longitudinal walls (56, 58), in such a way as to reduce and damp the movements of the means for holding in the cavity (62).

Abstract: A gas turbine engine includes an engine static structure. A fairing is supported relative to the engine static structure and configured to provide a flow path surface of a flow path extending in an axial direction. A seal plate has first and second ends radially spaced from one another with respect to the axial direction. The first end is operatively secured to the engine static structure. The second end is configured to seal relative to the fairing. The seal plate includes a portion between the first and second ends that extends substantially in the axial direction and configured to permit the second end to move away from the fairing in the axial direction relative to the first end in response to thermal growth.

Abstract: A flow path component includes a platform having at least one radially aligned face. A chordal seal extends axially from the radially aligned face. The chordal seal includes a first curved face configured to prevent edge line contact under deflection conditions while the flow path component is installed in an engine.

Abstract: Aspirating face seal between high and low pressure regions of turbomachine between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces, starter tooth mounted on the rotatable member operable to sealingly engage abradable starter seal land on the non-rotatable member, and annular pocket in an abradable coating or other abradable material of starter seal land. Abradable material may be in radially inwardly facing groove extending into non-rotatable member. Pocket may extend radially outwardly from a cylindrical radially outer abradable surface to pocket bottom which includes thin abradable material layer groove surface along the non-rotatable member. Pocket may extend axially aftwardly from annular forward groove side surface into abradable coating. Pocket may be bounded axially by abradable material. Pocket may be tapered having taper decreasing axially aftwardly away from annular forward groove side surface.

Abstract: This disclosure relates to a gas turbine engine including a blade outer air seal (BOAS) mounted radially outwardly of a blade. The engine further includes a BOAS support. A radial dimension of the BOAS support is selectively changeable in response to a flow of fluid through the BOAS support to adjust a radial position of the BOAS relative to the blade.

Abstract: A method to design a turbine including: estimating rates of thermal radial expansion for each of a stator and a rotor corresponding to a period of operation of the turbine; estimating a clearance between the rotor and the stator based on the rates of thermal radial expansion, and determining a mass or surface area of the stator or rotor based on the clearance.

Abstract: An impingement manifold includes a fluid inlet passage and a pressurized chamber. The pressurized chamber includes at least one lobe. The at least one lobe includes a flow improving feature configured to minimize vorticity of a flow field within the pressurized chamber, and at least one flow outlet.

Abstract: An apparatus comprising a meter device with a rotating component configured to rotate in response to a flowing fluid, an indexing unit coupled with the meter device and configured to process signals from the meter device resulting in values for measured parameters of a flowing fluid, and an energy harvester coupled to the pair of impellers, the energy harvester comprising a first harvesting unit and a second harvesting unit that co-operate to generate an electrical signal, the first harvesting unit configured to co-rotate with the pair of impellers, the second harvesting unit comprising a hollow, magnetic core disposed proximate the first harvesting unit.

Abstract: A gas turbine engine including a compressor, a turbine, and a variable-ratio unit is disclosed. The turbine is coupled to the compressor to drive rotation of multiple stages of the compressor. The variable-ratio unit is configured to transmit rotational power from the turbine to at least one stage of the compressor to drive rotation of the at least one stage of the compressor.

Abstract: A drain includes a vortex throttle, to remove water from a pressure sensing line. The vortex throttle resists the flow of air through it. Therefore, for a given diameter of inlet and outlet ports the mass flow rate through the vortex throttle is much smaller than through a plain hole of the same diameter. The inlet and outlet ports may therefore be made larger than in known arrangements (so reducing the risk of blockage), but the operation of the vortex throttle restricts the mass flow of air through the drain pipe (so minimizing the detrimental effects on the engine's operation). Collected water effectively drains from the pressure sensing line, without the disadvantages of known arrangements.

Abstract: An exhaust gas diffuser for a gas turbine engine whose inlet geometry can be selectively controlled to change the angular orientation of the diffuser at the location where the exhaust gas exits the last stage row of blades of the turbine section of the gas turbine engine. An end portion of the gas diffuser proximate the last stage row of blades can include one or more actuated sections that are independently controlled to change the angular orientation of the inlet geometry of the diffuser. In one embodiment, the angular orientation of the actuated sections is set at the manufacturing level for the service location of the engine. In another embodiment, the angular orientation of the actuated sections is selectively controlled based on the operating conditions of the engine. In another embodiment, the angular orientation of the actuated sections is controlled by pneumatic pressure from a compressor section of the engine.

Abstract: A variable vane system for a gas turbine engine includes a geared unison ring driven by a drive gear, the geared unison ring axially slidable parallel to an engine axis with respect to the drive gear as the rotation of the unison ring results in axial motion that is accommodated by the axial sliding between a gear mesh of the geared unison ring and the drive gear.

Abstract: A variable vane system includes a first variable vane stage with a multiple of first actuator gears, each of the multiple of first actuator gears mounted to a respective variable vane of the first variable vane stage, and a second variable vane stage with a multiple of second stage actuator gears. Each of the multiple of second stage actuator gears mounted to a respective variable vane of the second variable vane stage, an extended geared unison ring driven by the drive gear, wherein the extended geared unison ring spans at least a first variable vane stage and a second variable vane stage, each of the multiple of first and second stage actuator gears driven by the extended geared unison ring.

Abstract: A pivot shaft assembly for a turbocharger with variable turbine geometry (VTG) is provided. The pivot shaft assembly may include a pivot shaft, a pivot fork extending from the pivot shaft, a VTG lever disposed on the pivot shaft, and a retention collar axially coupled to the pivot shaft such that the VTG lever is axially aligned with the retention collar and the pivot shaft.

Abstract: A nozzle guide vane for a gas turbine engine is disclosed herein. The nozzle guide vane includes an inner endcap, an outer endcap, and at least one airfoil that extends from the inner endcap to the outer endcap. The nozzle guide vane further includes at least one composite heat shield component adapted to shield metallic components from high temperature gasses.

Abstract: Sealing configurations with active cooling features are provided. A forward sealing configuration may comprise a forward bellows spring configured to interface with a forward seal plate. An aft sealing configuration may comprise an aft bellows configured to interface with an aft seal plate. The forward bellows spring and the aft bellows spring may be configured to provide an axial force against each respective seal plate. The forward seal plate and the aft seal plate may include cooling holes configured to deliver a lubricating fluid to each respective seal interface to provide active cooling to each respective sealing configuration.

Abstract: A bearing assembly (2) is provided, in particular for a turbomachine, including: an inner bearing race (3); an outer bearing race (4) having at least one cooling channel (15) formed within it or in its outer surface; rolling elements (7) made of ceramic and disposed between the inner bearing race (3) and the outer bearing race (4); and a surrounding bearing ring (9) connected to the outer bearing race (4) and configured to form a squeeze film (10) of oil between its outer surface and an opposite inner surface of a housing (1) in which the bearing assembly can be mounted.

Abstract: The presently disclosed embodiments utilize a rear bearing sleeve interposed between an inner surface of an exhaust housing of a gas turbine auxiliary power unit and the rear roller bearing supporting a turbine within the exhaust housing. In some embodiments, the rear bearing sleeve includes a lubricant supply channel formed in an outer surface thereof for receipt of a supply of lubricant, and at least one lubricant supply opening between the outer surface and an inner surface thereof, the inner surface of the bearing sleeve forming an outer race of the rear roller bearing. The at least one lubricant supply opening supplies the lubricant to a gap between the rear roller bearing and the rear bearing sleeve for formation of a squeeze film viscous damper therebetween.

Abstract: A bearing housing for a turbocharger is disclosed. The bearing housing includes a first end proximate to a turbine wheel of the turbocharger and a second end proximate to a compressor wheel of the turbocharger. The bearing housing further includes a central chamber disposed between the first end and the second end and configured to house, at least, the shaft. The bearing housing further includes an oil drain disposed radially outward of the shaft and configured for directing oil out of the bearing housing and an oil core disposed radially outward of the shaft and radially inward of the oil drain, the oil core configured for communicating oil towards the oil drain and having an inner wall. The bearing housing includes one or more strakes protruding radially inward from the inner wall, the one or more strakes configured to direct oil within the oil core towards the oil drain.

Abstract: An oil system of a turbine engine and a method for driving an oil pump of such oil system are disclosed. In various embodiments, the oil system comprises an oil pump for fluid communication with one or more lubrication loads of the turbine engine, a first source of motive power and a coupling device. The first source of motive power is drivingly engaged to the oil pump for driving the oil pump during a first mode of operation. The coupling device is configured to drivingly disengage a second source of motive power from the oil pump during the first mode of operation and drivingly engage the second source of motive power with the oil pump to drive the oil pump during a second mode of operation.

Abstract: A turbine exhaust case frame (100) comprises an inner ring (104), an outer ring (102), and a plurality of load-bearing struts (106). The inner ring is configured to carry load from inner bearings. The outer ring features a multi-function boss (116) with a service line aperture (124) and a mounting point for the turbine exhaust case. The load-bearing struts connect the inner ring to the outer ring, and have a service line passage (128) extending from the service line aperture to the inner ring.

Abstract: A turbine exhaust case (28) comprises a fairing (120) defining an airflow path through the turbine exhaust case, and a multi-piece frame (100). The multi-piece frame is disposed through and around the fairing to support a bearing load, and comprises an inner ring (104), an outer ring (102) disposed concentrically outward of the inner ring, a plurality of bossed covers (110), and a plurality of radial struts (106). The plurality of bossed covers are bolted to the outer ring at locations circumferentially distributed about the outer diameter of the outer ring. The plurality of radial struts pass through the fairing and are secured via non-radial connectors (112, 114) to the inner ring and the bossed covers.

Abstract: An aircraft casing structure including a shroud surrounding the engine and made up of a plurality of sectors; a plurality of radial arms, each mounted between two adjacent shroud sectors and each having a base; and a plurality of fasteners for fastening the shroud sectors on the bases of the radial arms; the fasteners including a plurality of plates each mounted flush in a respective groove of corresponding shape in a shroud sector, and a set of headed bolts held captive in the plate by a difference of diameter between their shanks and their threads, a set of captive nuts being fastened to the bases to provide a secure connection between the shroud sectors and the radial arms by each nut receiving the thread of a respective captive bolt of the set of headed bolts.

Abstract: A method for generating electricity by means of a thermal power plant and a liquid vaporization apparatus involves producing heat energy by means of the power plant and using the heat energy to vaporize water or to heat water vapor, expanding the water vapor formed in a first turbine and using the first turbine to drive an electricity generator in order to produce electricity, vaporizing liquefied gas coming from a cryogenic storage in order to produce pressurized gas, reheating the pressurized gas with a part of the water vapor intended for the first turbine of the power plant and expanding the pressurized fluid in a second turbine to produce electricity.

Abstract: A method for generating electricity by means of a nuclear power plant and a liquid vaporization apparatus involves producing heat energy by means of the nuclear power plant and using the heat energy to vaporize water or to heat water vapor, expanding the water vapor formed in a first turbine and using the first turbine to drive an electricity generator in order to produce electricity, vaporizing liquefied gas coming from a cryogenic storage in order to produce a pressurized gas, reheating the pressurized gas with a part of the water vapor intended for the first turbine of the power plant and expanding the pressurized fluid in a second turbine to produce electricity.

Abstract: The invention relates to a method for regulating a condenser in a thermal cycle apparatus, in particular in an ORC apparatus, wherein the thermal cycle apparatus comprises a feed pump for conveying liquid working medium with an increase in pressure to an evaporator, the evaporator for evaporating and optionally additionally superheating the working medium with a supply of heat, an expansion machine for generating mechanical energy by expansion of the evaporated working medium, a generator for at least partially converting the mechanical energy into electrical energy, and the condenser for condensing the expanded working medium, and wherein the method comprises the following steps: determining a rotational speed of the generator or of the expansion machine; determining, without the use of a temperature sensor, a temperature of cooling air supplied from the condenser; determining from the determined generator or expansion machine rotational speed and the determined cooling air temperature, a condensation setpoi

Abstract: At crank angle CA10 at which the switch request of the drive cam was issued, the ejection operations of the pins at all the solenoid actuators started simultaneously. The ejected pins are seated on the cam carriers at crank angle CA12. The pin seated on the cam carrier moves along the grooves in accordance with the rotation of the cam carrier. The earliest finish timing of the switch operation of the drive cam is at crank angle CA13 (#4 cylinder). At the crank angle CA13, drive of the fuel injector and the ignition device in each cylinder is permitted.

Abstract: A valve train for an internal combustion engine may include a camshaft and a cam follower. The valve train may also include two first cams arranged on the camshaft in a torque-proof manner and at an axial distance from one another. Each of the two first cams may include an identical first cam contour. The valve train may also include two second cams arranged on the camshaft in a torque-proof manner and at an axial distance from one another. Each of the two second cams may also include an identical second cam contour. The two first cams and the two second cams may alternate in an axial direction on the camshaft. The cam follower may be axially adjustable between a first and second position, and may be drivingly connected to the two first cams in the first position and drivingly connected to the two second cams in the second position.

Abstract: A number of variations may include a product comprising a latching solenoid comprising: a valve; a spring operatively connected to the valve; a base plate adjacent the valve, wherein the base plate is constructed and arranged to maintain residual magnetism; an armature adjacent the base 10 plate and operatively connected to the spring; a pin disposed within the armature and operatively connected to the valve; wherein the latching solenoid includes a coil, wherein when the latching solenoid is energized the coil pulls the armature in a first direction toward the base plate; and wherein when the latching solenoid is energized the base plate becomes residually 15 magnetized so that when the armature moves in the first direction toward the base plate the armature magnetically latches to the base plate and remains attached to the base plate when the latching solenoid is de-energized.

Abstract: A camshaft adjuster (1) for variably adjusting an outer camshaft (5) and an inner camshaft (7) that is arranged concentrically thereto, including a stator (2) that can be connected to the outer camshaft (5), and a rotor (3) that is arranged concentrically to the stator (2), wherein the rotor (3) can be connected to the inner camshaft (7) in the manner of a first joint (9) on a first spherical contact surface (27). In order to axially secure the rotor (3) on the inner camshaft (7), force can be applied to the rotor (3) by way of a screw (4). The screw (4) can be connected to the inner camshaft (7) in the manner of a second joint (12) on a second spherical contact surface (28). A camshaft adjuster-camshaft combination having a camshaft adjuster, wherein the outer camshaft (5) is fixed on the stator (2) in a rotationally secured manner, and the inner camshaft (7) is fixed on the rotor (3) in a rotationally secured manner.

Abstract: A variable cam timing system in an engine is provided. The variable cam timing system includes a camshaft receiving rotational input from a crankshaft. The camshaft includes a valve cam rotationally actuating a valve coupled to a cylinder and a null cam actuating a null follower including a null spring exerting a return force on the null cam during interaction between the null cam and the null follower, where the null follower is independent from the cylinder.

Abstract: An oil reservoir for a variable camshaft phaser, comprising a locking cover including a front surface including a pool, the pool having a plurality of through-bores, a rear surface including a locking pin channel, a radially inward facing surface, and a radially outward facing surface, and an oil reservoir cover secured to the front surface of the locking cover.

Abstract: In a hydraulically-operated vane rotor equipped variable valve timing control device for an internal combustion engine, a fluid-communication control mechanism is configured to switch, after having started the engine, a communication hole from a communicated state to a fluid-communication restricted state prior to switching operation of a lock mechanism from a lock state in which rotary motion of a vane rotor relative to a housing is restricted to an unlock state in which rotary motion of the vane rotor relative to the housing is enabled. As a result of this configuration, it becomes possible to apply, after having started the engine, an appropriately controlled hydraulic pressure to all of vanes, with hydraulic pressure supplied to either all phase-retard chambers or all phase-advance chambers, thereby ensuring a good control responsiveness of the vane rotor.

Abstract: A system that provides adjustable actuation timing of one or more valve(s) (16) in a piston engine includes a position sensor (12) and a variable valve actuation assembly (10). The valve(s) (16) can be intake and/or exhaust valves in an internal combustion engine of an automobile. The position sensor (12) takes position readings of the valve(s) (16) as the valve(s) (16) actuate in the piston engine. The variable valve actuation assembly (10) controls actuation timing of the valve(s) (16). Actuation timing of the valve(s) (16) is adjustable based, in part or more, upon one or more position reading(s) of the position sensor (12). The variable valve actuation assembly (10) can be a lost motion assembly (10).

Abstract: A modified rocker assembly having an offset end is designed for engine heads having an obstruction preventing use of a symmetric switching rocker arm. The modified rocker assembly has an obstructed side and a non-obstructed side and has an outer structure with a first end, and an inner rocker structure fitting within the outer structure, the inner structure also having a first end. The modified rocker assembly has an axle pivotally connecting the first ends of inner structure to the outer structure, such that the inner structure pivots within the outer structure around the axle. At least one torsion spring on one side of the axle rotationally biases the inner structure relative to the outer structure. The outer structure is offset on the obstructed side as it extends from the second end toward the first end, creating the first offset portion to provide additional clearance on the obstructed side.

Abstract: A system and method for sensing a camshaft barrel position of a sliding camshaft includes at least one sliding camshaft having at least one camshaft barrel and at least one position shifting slot disposed in the at least one camshaft barrel. At least one actuator is provided for engaging the at least one position shifting slot on the rotating sliding camshaft and shifting position of the at least one camshaft barrel and at least one sensor is provided for detecting the shifted position of the at least one camshaft barrel wherein the camshaft barrel includes position identifying features.

Abstract: A single valve compression release bridge brake is provided. The single valve compression release bridge brake includes a braking piston (160) integrated into an inner end of a valve bridge (400) which is located under a rocker arm (210) of an engine. The braking piston (160) is slidably disposed in a braking piston bore (190) opened downwards from the inner end of the valve bridge (400). The lower end of the braking piston (160) is connected to the inner exhaust valve (3001). Oil is supplied to the braking piston bore (190) in the valve bridge (400). The inner end of the valve bridge (400) above the braking piston (160) is pushed upwards against the rocker arm (210) by oil pressure, and a hydraulic linkage is formed between the braking piston (160) and the valve bridge (400).

Abstract: Provided is an engine oil deterioration diagnosis device (10) comprising annual traveling distance calculating part (16), a used hour calculating part (18), a severe condition determining part (20), an oil traveling distance calculating part (22), an oil traveling distance accumulating part (24), and an engine oil deterioration diagnosis part (26) for diagnosing that engine oil is in a state of deterioration when an oil traveling distance accumulated by the oil traveling distance accumulating part reached a predetermined value, wherein the oil traveling distance calculating part (22) comprises an oil traveling distance addition correcting part (32) for calculating the oil traveling distance by adding a predetermined value to the traveling distance when the severe condition determining part determines the state as the severe condition.

Abstract: A breather chamber structure for an internal combustion engine wherein the breather chamber can be disposed compactly and the degree of freedom in the layout of the parts of the internal combustion engine can be raised. The breather chamber structure includes a crankcase, a cylinder body provided upwardly on the crankcase, and a breather chamber configured to separate oil from oil mist in the crankcase. The breather chamber includes a crankcase side breather chamber provided in the crankcase and open to a joining plane between the crankcase and the cylinder body, and a cylinder side breather chamber provided in the cylinder body and open to the joining plane.

Abstract: To improve the oil separation performance in an oil separation device for an internal combustion engine. The oil separation device (10) comprises a gas liquid separation passage (56) internally defined by a lower wall, an upper wall and a pair of side walls, and extending in a horizontal direction, a gas inlet (54) and a gas outlet (63) provided on either end of the gas liquid separation passage, a plurality of lower partition walls (56H) projecting upward from the lower wall, and a plurality of upper partition walls (56J) projecting downward from the upper wall. The lower partition walls and the upper partition wall are tilted with respective the length wise direction in plan view so as to define a spiral passage. The lower wall is inclined with respect to a horizontal plane such that an upstream part of the lower wall is lower than a downstream part of the lower wall with respect to a direction of the swirl flow.

Abstract: An engine assembly includes a diesel internal combustion engine and an aftertreatment system coupled to the diesel internal combustion engine. The aftertreatment system includes a diesel oxidation catalyst coupled to the diesel internal combustion engine such that the diesel oxidation catalyst receives exhaust gases from the diesel internal combustion engine. The aftertreatment system includes a plasma generator in fluid communication with the diesel oxidation catalyst, wherein the plasma generator is upstream of the diesel oxidation catalyst and downstream of the diesel internal combustion engine, and the plasma generator is configured to generate oxidizers to at least partially oxidize hydrocarbons in the exhaust gases exiting the diesel internal combustion engine.

Abstract: Methods and systems are provided for controlling particulate filter temperature during non-combustion conditions. In one example, a method for an engine includes responsive to a particulate filter temperature above a threshold temperature and while operating the engine with deceleration fuel shut-off (DFSO), fully closing a throttle valve configured to regulate flow of intake air to the engine, and responsive to intake manifold pressure dropping below a threshold pressure while the throttle valve is fully closed, adjusting a position of the throttle valve based on the particulate filter temperature.

Abstract: An exhaust system for a marine propulsion device having an engine and a driveshaft housing. An exhaust manifold having a downstream end with an outer surface conveys exhaust gas from the engine. An exhaust conduit having an upstream end with an outer surface conveys the exhaust gas to the driveshaft housing. A flexible coupler couples the downstream end of the exhaust manifold and the upstream end of the exhaust conduit, retaining a gap between them. A metallic coil is aligned with the flexible coupler, which biases the metallic coil into contact with the outer surfaces of the exhaust manifold and the exhaust conduit to conduct heat between them. First and second clamps engage outer surfaces of the flexible coupler to cause inner surfaces of the flexible coupler to sealingly engage the outer surface of the exhaust manifold, and the outer surface of the exhaust conduit, respectively.

Abstract: A method for controlling an emission amount in an exhaust gas stream emitted from a power generation system is presented. The method includes determining a pre-catalyst emission level using a combustion engine model. The method further includes determining a post-catalyst emission level using a three-way catalyst model based on the pre-catalyst emission level. Furthermore, the method includes determining an adjusted post-catalyst emission level based on the post-catalyst emission level. Moreover, the method includes determining a difference between the post-catalyst emission level and the adjusted post-catalyst emission level and comparing the difference with a threshold value. Additionally, the method includes determining whether to adjust an actual value of an engine operating parameter based on the comparison such that the emission amount in the exhaust gas stream is maintained below an emission regulatory limit. An engine controller and a power generation system employing the method are also presented.