51 results about "Lean burn" patented technology

A gas turbine engine includes: a rich burn, quick quench, lean burn combustor having a number of fuel spray nozzles in the range 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. An nvPM emissions index ratio is defined as:EIidle×Wf,idleEImaxTO×Wf,maxTOwhere: EIidle and EImaxTO are respectively the nvPM emissions index in mg / kg of gas turbine engine if operating at around 7% or 100% available thrust for given operating conditions; Wf,idle and Wf,maxTO are respectively the rate of fuel flow to fuel spray nozzles in kg / s at around 7% or 100% available thrust for given operating conditions. The fuel-flow nvPM emissions index ratio is less than 0.08. The gas turbine engine is configured to provide fuel including sustainable aviation fuel to fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.

A gas turbine engine for an aircraft. The gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. An MTO nvPM emissions index ratio is defined as:EImaxTO,SAFEImaxTO,FFwhere: EImaxTO,SAF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the fuel spray nozzles comprises a sustainable aviation fuel (SAF); and EImaxTO,FF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the fuel spray nozzles is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1. The gas turbine engine is configured to provide fuel comprising a SAF to the fuel spray nozzles. Also disclosed is a method of operating a gas turbine engine.

A gas turbine engine includes: a rich burn, quick quench, lean burn combustor having a number of fuel spray nozzles in range of 14-22 or a number of fuel spray nozzles per unit engine core size in range 2 to 6. An MTO nvPM emissions index ratio is:EImaxTO,SAFEImaxTO,FF×Wf,maxTOwhere: EImaxTO,SAF and EImaxTO,FF are respectively the nvPM emissions index in mg / kg when operating around 100% available thrust for given operating conditions if fuel provided to fuel spray nozzles includes either sustainable aviation fuel (SAF) or fossil-based hydrocarbon fuel; Wf,maxTO is mass flow rate of fuel provided to fuel spray nozzles in kg / s when gas turbine engine is operating at around 100% available thrust for given operating conditions. MTO nvPM emissions index is less than 2. The gas turbine engine is configured to provide fuel including SAF to fuel spray nozzles. Also disclosed is method of operating gas turbine engine.

A gas turbine engine for an aircraft. The gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. A first idle-MTO nvPM emissions index ratio is defined as:EIidle / EImaxTO where: EIidle is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 7% available thrust for given operating conditions; and EImaxTO is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 100% available thrust for the given operating conditions. The first idle-MTO nvPM emissions index ratio of the gas turbine engine is less than 0.8. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel (SAF) to the fuel spray nozzles. A method of operating the gas turbine engine is also disclosed.

A gas turbine engine for an aircraft. The gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. A fuel-flow nvPM emissions index ratio is defined as:EIidle×Wf,idleEImax⁢TO×Wf,maxTOwhere: EIidle is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 7% available thrust for given operating conditions; and EImaxTO is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 100% available thrust for the given operating conditions; Wf,idle is the rate of fuel flow to the fuel spray nozzles in kg / s at around 7% available thrust for the given operating conditions; and Wf,maxTO is the rate of fuel flow to the fuel spray nozzles in kg / s at around 100% available thrust for the given operating conditions. The fuel-flow nvPM emissions index ratio of the gas turbine engine is less than 0.08. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel (SAF) to the fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.

A gas turbine engine for an aircraft includes a rich burn, quick quench, lean burn (RQL) combustor having 14-22 fuel spray nozzles or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. A first idle-MTO nvPM emissions index ratioEIidleEImaxTO.EIidle is the nvPM emissions index in mg / kg of the gas turbine engine if operating at around 7% available thrust for given operating conditions. EImaxTO is the nvPM emissions index in mg / kg of the gas turbine engine if operating at around 100% available thrust for the given operating conditions. The first idle-MTO nvPM emissions index ratio of the gas turbine engine is less than 0.8. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel (SAF) to the fuel spray nozzles.

The invention provides a pre-combustion chamber jet ignition device for broadening the lean burn limit of a methanol engine based on a flow baffle, which comprises a pre-combustion chamber shell, a fuel injector body, a spark plug body and the flow baffle, and is characterized in that the upper part of the pre-combustion chamber shell is provided with a fuel injector mounting groove for mounting the fuel injector body and a spark plug mounting groove for mounting the spark plug body; a primary jet flow cavity is formed in the middle, and a secondary jet flow cavity is formed in the lower part; a jet hole is formed in the bottom end of the second-stage jet cavity and communicates with a main combustion chamber of the engine. The combustor is used for spraying high-energy flames to the main combustion chamber so as to ignite combustible mixed gas in the main combustion chamber; the flow baffle is mounted at the internal joint of the first-stage jet flow cavity and the second-stage jet flow cavity; the pre-combustion chamber shell is fixed to an engine cylinder cover through a pressing plate and bolts. The energy of combustion flames generated by the pre-combustion chamber is improved, the injection duration is prolonged, the methanol lean-burn limit is finally widened, and the cold start problem of a methanol engine can be solved.

The invention relates to a cooperative control method and system for lean-burn emission of a marine low-zero carbon fuel engine. The method comprises the steps that real-time in-cylinder pressure and temperature data are collected, and an in-cylinder pressure curve and an in-cylinder temperature curve are obtained through time sequence alignment, filtering denoising and interpolation fitting processing; extracting time sequence data based on the curve, calculating average effective pressure and peak temperature in a cylinder to determine a current load interval, and marking a risk tag sequence; calculating the generation rate of the nitrogen oxides and the particulate matters by matching with reaction condition parameters, and extracting reverse variation characteristics to obtain strong mutual exclusion correlation of the nitrogen oxides and the particulate matters; and based on the associated starting model, predicting and controlling the output oil injection quantity and the air inflow adjusting quantity, calculating the transient time sequence lag quantity through a dynamic lag model, and after superposition, calibrating through a combustion phase matching algorithm to generate an oil injection timing and air inlet valve opening control instruction after transient adjustment. The method is adaptive to the combustion characteristics of low-zero-carbon fuel, emission contradictions are accurately captured, transient emission peak values are avoided, and multi-pollutant collaborative control is achieved.

A lean-burn combustor (16) comprising: a plurality of lean-burn fuel injectors (50), each lean-burn fuel injector comprising a fuel supply arm (52) and a lean-burn fuel injector head (54) with a lean-burn fuel injector head tip (72), the lean-burn fuel injector head comprising a pilot fuel injector and a main fuel injector arranged coaxially with the pilot fuel injector and radially outwardly; a combustor chamber (60) extending in an axial direction (62) and comprising a radially inner annular wall (64), a radially outer annular wall (66) and a metering plate (68) defining a size and shape of the combustor chamber, wherein the combustor chamber comprises a primary combustion zone (80) and a secondary combustion zone (82); and a pre-diffuser (90) for providing compressed air to the lean-burn fuel injector head (54).

A method of operating a gas turbine engine. The gas turbine engine includes an accessory gearbox arranged to power one or more engine accessories, and a combustor in which fuel is combusted and a fuel-oil heat exchanger arranged to transfer heat between oil and fuel that is provided to the combustor. An average temperature of lubricating oil is at least 180° C. on exit from the accessory gearbox at cruise conditions. The method includes transferring heat from the oil to the fuel before the fuel enters the combustor so as to raise the fuel temperature to an average of at least 135° C. on entry to the combustor at cruise conditions. Also provided is a gas turbine engine.

The present disclosure is directed to a method of operating a combustion system to attenuate combustion dynamics. The method includes flowing, via a compressor section, an overall supply of air to the combustion system; flowing, via a fuel supply system, an overall flow of fuel to the combustion system; flowing, to a first fuel nozzle of the combustion system, a first supply of fuel defining a richer burning fuel-air mixture at the first fuel nozzle; flowing, to a second fuel nozzle of the combustion system, a second supply of fuel defining a leaner burning fuel-air mixture at the second fuel nozzle; and igniting the richer burning fuel-air mixture and the leaner burning fuel-air mixture to produce an overall fuel-air ratio at a combustion chamber of the combustion system.

A combustor for rich-quench-lean combustion includes a combustor shell, a combustion chamber delimited by the combustor shell, and fuel injectors. The combustion chamber includes a primary zone, a quench zone, a secondary zone, and an outlet arranged in axial flow series. Openings through the combustor in the quench zone provide a quench air flow into the quench zone. A method for rich-quench-lean combustion for the combustor includes contemporaneously injecting a rich air-fuel mixture into the primary zone and injecting a second air flow into the quench zone in which the second air flow is equal to or less than four times the primary air flow.

The invention belongs to the technical field of catalysis, and particularly relates to a copper-based SCR catalyst and a preparation method thereof. According to the copper-based SCR catalyst, cordierite serves as a carrier, a first coating and a second coating are sequentially arranged on the carrier, the first coating is Cu-SSZ-39, and the second coating is Cu-SSZ-13; the ratio of silicon to aluminum of the Cu-SSZ-39 is (10-18): 1; the copper content of the Cu-SSZ-39 is 2.0 to 3.0 percent by weight; the ratio of silicon to aluminum of Cu-SSZ-13 is (15-25): 1; and the copper content of the Cu-SSZ-13 is 0.5 to 1.5 percent by weight. The copper-based SCR catalyst shows excellent NOx conversion efficiency in a wide temperature range of 200-600 DEG C, gives consideration to cold start and high-load working conditions, has good thermal stability and sintering resistance, and is suitable for a complex environment of high-temperature fluctuation in gasoline engine lean-burn exhaust.

A gas turbine engine for an aircraft. The gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. An MTO nvPM emissions index ratio is defined as:EImaxTO,SAFEImaxTO,FFwhere: EImaxTO,SAF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the fuel spray nozzles comprises a sustainable aviation fuel (SAF); and EImaxTO,FF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the fuel spray nozzles is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1. The gas turbine engine is configured to provide fuel comprising a SAF to the fuel spray nozzles. Also disclosed is a method of operating a gas turbine engine.

The application discloses a lean-burn engine control method, device and engine system. The lean-burn engine control method comprises the following steps: obtaining a current torque and a target torque; when the current torque is less than the target torque, obtaining an average effective pressure and an excess air coefficient; when the average effective pressure is in a first pressure range and the excess air coefficient is in a first coefficient range, adjusting an ignition angle, increasing air content and combustible content in a cylinder, and increasing the current torque to the target torque. By using the above technical scheme, the current torque can be increased, the thermal efficiency can be ensured to be high, and the combustion center can be prevented from changing, the ignition angle can be prevented from being large, and the lean-burn engine can be prevented from being damaged by knocking.

The application discloses a kind of vehicle and the aftertreatment device, method and system of lean gasoline engine, device includes the first end of particle trap and exhaust manifold are connected, second end is respectively connected with the first end of control valve and bypass valve;The second end of control valve is connected with the first end of lean NOx trap, the second end of lean NOx trap is connected with the first end of three-way catalytic converter;The second end of bypass valve is connected with the first end of three-way catalytic converter;The control end of control valve and bypass valve is electrically connected with control unit;When equivalent ratio condition is determined, control bypass valve opens, control valve closes;When lean burn condition is determined, control bypass valve closes, control valve opens;When regeneration condition is determined, control bypass valve and control valve are opened, and water jet is controlled by water jet device.The technical scheme provided by the application can realize the collaborative regeneration of particle trap and lean NOx trap by water jet device to generate water gas reaction.

The present application aims to suppress useless update of a sub-feedback learning value caused by execution of active control of air-fuel ratio. A control device of an internal combustion engine is capable of executing air-fuel ratio sub-feedback control, sub-feedback learning control, and active control of air-fuel ratio. In the sub-feedback learning control, the control device executes rich adhesion update processing that updates the sub-feedback learning value so that the post-update target air-fuel ratio becomes an air-fuel ratio more biased toward the lean side than the pre-update target air-fuel ratio, in the case where a rich adhesion condition indicating a state in which lean burn failure has not been detected continuously after switching of the target air-fuel ratio from a rich air-fuel ratio to a lean air-fuel ratio based on the air-fuel ratio sub-feedback control is satisfied. In the active control of air-fuel ratio, the control device forcibly performs switching of the target air-fuel ratio between a lean air-fuel ratio and a rich air-fuel ratio. The control device prohibits execution of the rich adhesion update processing during execution of the active control of air-fuel ratio.

The present invention belongs to the field of catalytic technology, and in particular relates to a copper-based SCR catalyst and a preparation method thereof. The copper-based SCR catalyst of the present invention uses cordierite as a carrier, and a first coating and a second coating are sequentially provided on the carrier, wherein the first coating is Cu-SSZ-39 and the second coating is Cu-SSZ-13; the silicon-aluminum ratio of Cu-SSZ-39 is (10-18):1; the copper content of Cu-SSZ-39 is 2.0-3.0%wt; the silicon-aluminum ratio of Cu-SSZ-13 is (15-25):1; and the copper content of Cu-SSZ-13 is 0.5-1.5%wt. The copper-based SCR catalyst of the present invention exhibits excellent NO reduction in a wide temperature range of 200-600°C. x Conversion efficiency, taking into account both cold start and high load conditions, with good thermal stability and anti-sintering performance, suitable for the complex environment of high temperature fluctuations in gasoline engine lean burn exhaust.

The present application belongs to the technical field of vehicle engineering, and particularly relates to a particle trap regeneration method, device, storage medium and controller; through reversing the installation of the particle trap and interfacing the rotating purging component, the regeneration of the trap is realized on the engine tail gas pipeline; wherein, in order to improve the regeneration effect, a cyclic or intermittent variable working condition control process can be introduced; through setting the first type of working condition and / or the second type of working condition and switching, the pulsating tail gas output is introduced; in the process, high load and high speed and low load and low speed working conditions can be respectively used to realize different excitation states of the tail gas; in addition, the preset lean burn working condition and high temperature tail gas configuration can be combined to further improve the regeneration effect; at the same time, the differential pressure detection closed loop of the two ends of the trap can be introduced to optimize the monitoring ability of the regeneration process, timely end the regeneration process, and improve the operation efficiency; the application of the related products will be helpful to reduce the emission of the internal combustion engine and improve the fuel consumption.

The present application relates to the technical field of engine, and discloses a matching method of a supercharger for a lean-burn engine and a supercharger for a lean-burn engine, the matching method of the supercharger for the lean-burn engine comprising: obtaining target performance parameters of the engine; obtaining design parameters of the supercharger required by lean-burn combustion and equivalent ratio combustion of the engine under the target performance parameters of the engine; and adjusting and verifying performance parameters of the supercharger required by lean-burn combustion of the engine according to the design parameters of the supercharger required by lean-burn combustion and equivalent ratio combustion of the engine under the target performance parameters of the engine, until the engine can reach the target performance parameters under the performance parameters of the supercharger under lean-burn combustion. The matching method of the supercharger for the lean-burn engine and the supercharger for the lean-burn engine can realize large pressure end flow and small vortex end flow of the supercharger to match the demand of the lean-burn engine under the condition of meeting the design requirements of the supercharger in the early stage.

A method of operating a gas turbine engine having a lean burn staged combustion system having a combustor in which fuel is combusted. The gas turbine engine includes a fuel-oil heat exchanger arranged to transfer heat between oil and fuel that is provided to the combustor. The method includes transferring heat from the oil to the fuel before the fuel enters the combustor so as to lower the fuel viscosity to 0.58 mm2 / s or lower on entry to the combustor at cruise conditions.

The invention relates to a diesel and natural gas dual-fuel engine lean burn system and an operation method, the diesel and natural gas dual-fuel engine lean burn system comprises a pre-combustion chamber, a dual-fuel injector system, a natural gas injection system, an exhaust back pressure adjusting system, a heat and power combined supply circulation system, a cold energy utilization system and the like, and engine fuel injection precision control is achieved through the dual-fuel injector system and the diesel injection system. Two working modes of a pure diesel oil combustion mode and a dual-fuel combustion mode are achieved, lean combustion of the engine is achieved through an exhaust back pressure adjusting system and pre-combustion chamber micro-jet ignition, the electric energy and heat energy requirements of the system are met through a heat and power combined supply circulation system, and cold energy is provided for equipment through a cold energy utilization system; and meanwhile, emission of combustion pollutants of the engine is reduced. And the economical efficiency, the dynamic property and the environmental protection property of the engine under the full-working-condition operation condition are improved.

A gas turbine engine 10 for an aircraft comprising a rich burn quick quench, lean burn (RQL) combustor 16 having a number of spray nozzles 403, 404, in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range of 2-6, with the engine configured to provide fuel comprising sustainable aviation fuel to the spray nozzles. The engine operation is characterised by specific non-volatile particulate emission ratio beign related to the bypass ratio. The fuel spray nozzles may comprise one or more duplex nozzles and one more single flow nozzles and preferably the combustor comprises 10-14 duplex fuel spray nozzles and 4-8 signle flow fuel spray nozzles. The duplex fuel spray nozzles are arranged in groups about the circumference of the combustor and optionally wherein the groups duplex fuel spray nozzles comprise at least two groups arraned dimametrically opposite each other. A corresponding method is also claimed. Fig 6

A method of operating a four-stroke multi-cylinder piston engine by combustion of a first fuel in which the cylinders have a fixed geometric compression ratio, is characterized in that air is compressed by a single-stage compressor (28) of a turbocharger (26) coupled to the engine (10): in accordance with the duty cycle and the ignition sequence, the air is compressed by the single-stage compressor (28) of the turbocharger (26); filling the combustion chamber of each cylinder (12) with compressed air and a first fuel; providing a second fuel into the cylinder to be ignited and become ignited; the first fuel is ignited by the second fuel and is combusted as lean burn; a single stage turbine (30) directing exhaust gas generated by combustion to a turbocharger (26) in which the exhaust gas expands to generate work for operating a compressor; directing the exhaust gas to a NOx reduction catalyst (38) at which NOx emissions are reduced; and when the engine (10) is operated at a power less than 75% of its nominal maximum power and when at least 30% of the heat released in the combustion comes from ammonia as a first fuel, cooling the exhaust gas prior to directing the exhaust gas to the NOx reduction catalyst (38). The invention also relates to a four-stroke multi-cylinder internal combustion piston engine (10) configured to burn a first fuel comprising ammonia and a second fuel.

A gas turbine engine for an aircraft includes a rich burn, quick quench, lean burn combustor having 14-22 fuel spray nozzles or 2-6 fuel spray nozzles per unit engine core size. A thrust nvPM emissions index ratio isEImaxTO / FmaxTOEIidle / Fi⁢d⁢l⁢e.EIidle is the nvPM emissions index in mg / kg of the gas turbine engine operating at around 7% available thrust for given operating conditions. EImaxTO is the nvPM emissions index in mg / kg of the gas turbine engine operating at around 100% available thrust for the given operating conditions. FmaxTO is the thrust of the gas turbine engine at around 100% available thrust in kN. Fidle is the thrust of the gas turbine engine at around 7% available thrust in kN. The thrust nvPM emissions index ratio is greater than 0.09. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel to the fuel spray nozzles.

The invention discloses an engine fuel combustion control method and device based on a high-pressure gas supply system, and relates to the field of engine combustion control. The method comprises the following steps: acquiring load state data of an engine within a first duration; based on the load state data, whether the engine meets the condition of switching to a lean burn mode or not is judged, and when the switching condition is met, the engine is controlled to be switched to the lean burn mode; on the basis of the load fluctuation condition of the engine, the energy compensation demand change condition of the engine within the second duration after switching is predicted, and compensation information is obtained; and on the basis of the compensation information, configuration information of the high-pressure gas supply system and the engine within the second duration is determined. According to the scheme provided by the embodiment of the invention, the combustion stability in a lean combustion mode can be improved, and the engine performance is improved.

The invention belongs to the technical field of automobile engine air-fuel ratio control, particularly discloses an MAP self-updating lean-burn air-fuel ratio feedforward control method and system based on iterative learning, and aims to solve the problems of high calibration cost, oxygen sensor feedback delay and long-term precision reduction in lean-burn engine air-fuel ratio control. According to the method, accurate control over the air-fuel ratio is achieved through parameterized feedforward controller design, MAP table dynamic updating and a bilinear interpolation algorithm, the calibration cost is remarkably reduced by 80% or above, the transient working condition control error is stabilized within + / -1.5%, high precision is still kept after long-term operation, and the method is suitable for in-cylinder direct injection, air inlet channel injection and mixed injection engines.

There is provided a method of operating a gas turbine engine 10, the gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor 16 having a number of fuel spray nozzles (403,

The application discloses a cylinder cover, an engine and a vehicle, and relates to the technical field of engines, and specifically discloses a cylinder cover, which comprises a cylinder cover body and a pre-chamber structure, the cylinder cover body is formed with a combustion chamber, the pre-chamber structure comprises a shell and a piston, the shell is arranged on the cylinder cover body, the shell is formed with a spray hole, the piston is arranged in the shell to divide a space in the shell into a pre-chamber and an adjusting chamber, the adjusting chamber and the spray hole are both communicated with the combustion chamber, and the piston is movable in the shell to selectively communicate one of the pre-chamber and the adjusting chamber with the spray hole under the action of pressure. By arranging the pre-chamber structure on the cylinder cover body, arranging the piston in the shell, dividing the shell into the pre-chamber and the adjusting chamber, moving the piston relative to the shell, and arranging the spray hole on the shell and communicating the spray hole with the combustion chamber, the internal pressure of the pre-chamber structure can be increased, the internal gas flow of the pre-chamber structure can be enhanced, the dilution of lean burn of the engine can be improved, and the thermal efficiency of the engine can be improved.