Showing papers on "Afterburner published in 2019"
TL;DR: In this article, the authors proposed physical and optical quantitative methods for measuring the total fuel distribution in the dual-modal (afterburner/ramjet) combustor with an integrated flameholder.
15 citations
08 Sep 2019
TL;DR: Developed database of aviation materials and expert system of decision-making of computer-aided design of aviation engines and ground power plants on their basis to optimize the weight dimension characteristics of the main components of aircraft engines in the early stages of design are described.
Abstract: In the article it is described developed database of aviation materials and expert system of decision-making of computer-aided design of aviation engines and ground power plants on their basis. The database of aviation materials contains information on the properties and characteristics of a large number of materials used in the design of aircraft engines. The system allows automated selection of materials for parts and assembly units. In this case, the thermogasdynamic calculation of the engine as a whole, a detailed aerodynamic calculation of the assembly units and its strength calculation are performed. In the article it is shown description of mathematical model scheme of expert system. There are simulation results of low-pressure compressor (with different laws of profiling flow passage and different number of stages) for turbojet bypass engine with afterburner of the fourth generation of military high-maneuverable aircraft; there are shown also simulation results of high-pressure compressor for turbofan engine with a high bypass ratio for a civil aircraft, and also results of modelling of rotor blade of fan. Results of simulation were compared with construction of series-produced engines. Using the developed system, it is possible to optimize the weight dimension characteristics of the main components of aircraft engines in the early stages of design.
5 citations
Patent•
09 Apr 2019
TL;DR: In this article, an integrated afterburner capable of applying a two-stage swirler is presented. But the two stages are in axial design and radial design, and a low-speed back flow area which is stable, large in sizerange and high in vortex flow more easily forms on the downstream.
Abstract: The invention provides an integrated afterburner capable of applying a two-stage swirler. A turbine rear flow stabilizing supporting plate and a flame stabilizer are replaced with the two-stage swirler, a venturi tube structure is designed at an outlet of the swirler, the two stages of the swirler are in axial design and radial design, and a low-speed back flow area which is stable, large in sizerange and high in vortex flow more easily forms on the downstream. Fuel oil channels are formed in first-stage axial swirler blades, fuel oil spraying holes are formed in the side surfaces and the tails of the blades, and a supporting plate structure is disposed at spraying openings. Fuel oil absorbs heat in the fuel oil channels to be pre-heated, and then the fuel oil is sprayed out of the fuel oil spraying holes in the first-stage axial swirler blades and collides with supporting plates. The integrated afterburner capable of applying the two-stage swirler has the advantages that the two-stage swirler and the venturi tube structure are creatively applied to the afterburner, a unique blade structure which is provided with the supporting plates and can spray oil is additionally arranged, and the fuel oil atomization effect, burning stability and burning efficiency can be effectively improved.
3 citations
TL;DR: In this paper, a numerical model of propulsion and heat transfer is established for the nuclear jet engine to verify the feasibility of the novel nuclear heat exchanger, which is directly put into the combustion chamber to heat compressed air.
3 citations
Patent•
29 Mar 2019
TL;DR: In this paper, a cavity trapped vortex and rectifying support plate combined type integrated afterburner was used to improve the combustion efficiency and stability, and the ignited high-temperature air and air in the outer duct were promoted to mix, and played a role in rectification and stabilization of combustion.
Abstract: The invention provides a cavity trapped vortex and rectifying support plate combined type integrated afterburner. The ignition stability can be improved effectively, and the swirling intensity of a backflow area and the fuel atomization effect are improved, so that the combustion efficiency and stability are improved. A rectifying support plate flame stabilizer is combined with cavity trapped vortex; on one hand, air flow of inner and outer ducts enters a cavity from different positions, and a trapped vortex area is formed; duty-level flame is generated, so that mixed gas of a main flow area is ignited; on the other hand, a stable main backflow area with a certain gas backflow amount and in an appropriate size is formed downstream; and ignited high-temperature air and air in the outer ductare promoted to mix, and play a role in rectification and stabilization of combustion. The integrated afterburner has the advantages that the structural design of a cavity duty stabilizer is added atthe rear edge of the rectifying support plate flame stabilizer on the original basis of the integrated afterburner, and the ignition ability under the rich oil and high altitude conditions can be improved effectively; and the high combustion stability and efficiency are ensured.
2 citations
31 Jul 2019
TL;DR: In this article, the continuous-detonation afterburner (CDA) for the TJ100S-125 turbojet engine was designed and fabricated at the ICP.
Abstract: The objective of the work summarized in this paper is to develop, fabricate, and test the continuous-detonation afterburner (CDA) for the commercially available small-size TJ100S-125 turbojet engine [1]. The TJ100 turbojet engine is equipped with a single-stage centrifugal compressor and axial turbine, operates on the standard aviation kerosene TS-1 (Russian analog of Jet-A), and possesses the maximum thrust of about 1250 N. To keep the gas temperature ahead of the turbine at a su©ciently low level (∼1200 ◦C at most), the overall air-to-fuel equivalence ratio in the turbojet is quite high (attains the value of 4.0 to 6.0), i. e., a large amount of hot compressed air expels to the atmosphere together with combustion products. The motivation of our research is to explore the possibility of afterburning this air in the mixture with additionally injected kerosene by mounting the CDA downstream from the turbojet turbine. The CDA is designed based on multivariant parametric threedimensional numerical simulations ful¦lled at the ICP using the computational technology reported elsewhere [2] and is fabricated at the ICP. The in§uence of the CDA on turbojet operation due to back-
2 citations
Patent•
26 Feb 2019
TL;DR: In this article, a turbojet engine afterburner combustion chamber combustion zone stabilization method includes colliding with each other paired fuel-air jets radial supply into the incident flow Each pair of colliding jets axes are located in the passing through the engine axis plane Each pair axes are inclined towards each other Angle between the axes is 45-120 degrees.
Abstract: FIELD: engines and pumpsSUBSTANCE: turbojet engine afterburner combustion chamber combustion zone stabilization method includes colliding with each other paired fuel-air jets radial supply into the incident flow Each pair of colliding jets axes are located in the passing through the engine axis plane Each pair axes are inclined towards each other Angle between the axes is 45–120 degreesEFFECT: invention is aimed at increase in the afterburner combustion chamber reliability, hydraulic losses and the infrared radiation level reduction3 cl, 4 dwg
1 citations
Patent•
29 Mar 2019
TL;DR: In this paper, an integrated afterburner adopting adjustable preheating struts is presented, where strut flame stabilizers are connected with a central cone body through adjustable bolts, and the deflection angle of each strut stabilizer can be adjusted in real time according to actual work conditions.
Abstract: The invention provides an integrated afterburner adopting adjustable preheating struts. Strut flame stabilizers are connected with a central cone body through adjustable bolts, and the deflection angle of each strut flame stabilizer can be adjusted in real time according to actual work conditions. High-temperature mixed gas enters the struts from small intake holes formed in the two side surfacesof each strut flame stabilizer, fuel oil in a fuel oil channel is heated, and then the high-temperature mixed gas is sprayed out towards the center from small spray holes formed in the middle portionof a V-shaped groove of each strut flame stabilizer. After being heated, the fuel oil is sprayed out by direct injection type spray nozzles on the two sides of V-shaped grooves of the strut flame stabilizers, and after being further heated, the fuel oil burns in a low-speed backflow area on the back side. Since being heated, the fuel oil has good atomization and evaporation effects, the oil-gas mixing time in the low-speed area is long, and the oil-gas mixing effect is good, ignition and stable communication can be achieved under the condition of a small oil-gas ratio; and the adjustable strutflame stabilizers can be suitable for work states in larger range, and the performance of an engine is improved.
1 citations
01 Sep 2019
TL;DR: In this article, the authors analyzed the parameters and characteristics of various options for creating a gas-turbine-driven compressor plant for a gascompressor unit on the basis of the AL-31F aviation two spool turbojet engine with afterburner.
Abstract: Methods for converting aviation gas turbine engines when creating a gas-turbine-driven compressor plant for driving a gas compressor unit when transporting gas and gas turbine power plants in the power industry, various options for changing workflow and power circuits are considered. Using simulation modeling, the authors analyzed the parameters and characteristics of various options for creating a gas-turbine-driven compressor plant for a gas-compressor unit on the basis of the AL-31F aviation two spool turbojet engine with afterburner. The article shows the successive stages of the modernization of the scheme and changes in the parameters of the model of the aviation two spool turbojet engine with an afterburner with various conversion options in the gas-turbine-driven compressor plants for ground application. The criteria used are the full efficiency, the net power of the free turbine, the specific fuel consumption, the introduced structural changes and the overhaul life of the gas-turbine-driven compressor plant.
1 citations
Patent•
14 Nov 2019
TL;DR: In this article, an afterburner with fixed bushing is installed on fuel tank cover, coaxial to secondary air feed nozzle is installed coaxially through bushing in after-burner mouth, cone-shaped nozzle of which contains tangentially shifted side cuts, and cover is made in the form of truncated pyramid and is located above fuel tank with slotted gaps for supply of primary air.
Abstract: FIELD: heating equipment.SUBSTANCE: invention relates to heat engineering, namely to devices for burning waste oil products, including used oil and off-grade oil products, as well as diesel fuel and crude oil of any grade, fuel oil, furnace oil, vegetable oils and fats of any origin, oil sludge and oil wastes. Burner device comprises fuel tank with cover, afterburner and bushing, afterburner end part with fixed bushing is installed on fuel tank cover, coaxial to secondary air feed nozzle is installed coaxially through bushing in afterburner mouth, cone-shaped nozzle of which contains tangentially-shifted side cuts, and cover is made in the form of truncated pyramid and is located above fuel tank with slotted gaps for supply of primary air.EFFECT: technical result is providing a flame of high-temperature combustion for different types of fuel of different viscosity and low emission of pollutants during their combustion.2 cl, 8 dwg, 1 tbl
1 citations
Patent•
04 Sep 2019
TL;DR: In this paper, a method for controlling operation modes of an afterburner combustion chamber is proposed, which includes measurement of engine control lever position, measurement of total air pressure behind compressor, and measurement of air temperature at engine inlet.
Abstract: FIELD: machine building.SUBSTANCE: invention relates to the field of automatic control of a gas-turbine engine, namely to a method for controlling operation modes of an afterburner combustion chamber. Proposed method comprises measurement of engine control lever position, measurement of total air pressure behind compressor, measurement of air temperature at engine inlet, and control of fuel feed to afterburner combustion chamber. Temperature of the gas flow at the outlet of the afterburner combustion chamber is additionally measured and the position of the distribution valve of the fuel manifolds is controlled.EFFECT: invention allows increasing completeness of fuel combustion in afterburner combustion chamber.1 cl, 3 dwg
Patent•
15 Mar 2019
TL;DR: In this article, the authors proposed a reduction in the thermal load on the heat shield, which increases its service life and increases the engine reliability, which is aimed at reducing the total energy consumption of the afterburner.
Abstract: FIELD: engine building.SUBSTANCE: bypass turbofan engine afterburner combustion chamber comprises a housing with a heat shield installed therein with the cooling channel formation between them, diffuser, and the front-end device. Diffuser is formed by the chamber body and behind the turbine cuff. Front-end device includes rigidly fixed relative to the housing radial flame stabilizers and the annular flame stabilizer. Afterburner combustion chamber is additionally equipped with rigidly connected by the end face to the annular flame stabilizer outer diameter edge the annular shield with the formation between the annular and heat shields tapering in the main gas flow direction of the concentric annular channel. Annular shield is rigidly fixed relative to the heat shield.EFFECT: invention is aimed at reduction in the thermal load on the heat shield, which increases its service life and increases the engine reliability.1 cl, 2 dwg
Patent•
18 Jun 2019
TL;DR: In this paper, a multi-core-engine turbofan aerial power system with an afterburner and an aerial vehicle is presented, which has the world's highest bypass ratio, lowest noise and is most fuel-efficient with the afterburners and the aerial vehicle.
Abstract: The invention discloses a multi-core-engine turbofan aerial power system with an afterburner and an aerial vehicle. According to the system a designing idea of an existing jet-propelled turbofan aerial engine is changed, two counter-rotating fans are used for improving air suction and pressurizing efficiency, multiple turboshaft aerial engines are taken as core engines, an afterburner device is used for greatly improving the power of the engines in a short period of time, only one core engine is controlled to operate through a clutch, or multiple core engines are allowed to operate simultaneously; large flow-rate high-pressure air blow is blown into a pressure cavity to allow the pressure cavity to become a buffering device of air flow blown out by each nozzle assembly and become a silencing device for reducing noises generated by fan operation and fuel explosion and burning, the internal combustion time of fuel in the aerial vehicle is prolonged, and the benefit of the fuel is improved; a user is allowed to adjust the flow rate and jetting directions of air blown out by vector nozzles which are arranged in the periphery of the aerial vehicle and communicated with the pressure cavity, the simplicity of aerial vehicle manipulating is increased, and the multi-core-engine turbofan aerial power system which has with the world's highest bypass ratio, lowest noise and is most fuel-efficient with the afterburner and the aerial vehicle are creatively invented.
Patent•
13 May 2019
TL;DR: In this article, a special effect device that is used to produce a simulated flame that has the shape and color characteristics of the flame produced by a jet afterburner was presented.
Abstract: The invention is directed to special effect device that is used to produce a simulated flame that has the shape and, if desired, the color characteristics of the flame produced by a jet afterburner. In one embodiment, the device includes a steam system for providing a stream of steam, a steam accelerator for applying a high-speed and highly linear stream of air to steam provided by the steam system to produce at steam cloud with a highly linear shape similar to the shape of the flame produced by a jet afterburner, and a lighting system to project desired colors onto the linear steam cloud.
Patent•
28 Mar 2019
TL;DR: In this article, a regenerative cooling-type afterburner with acoustic cavity and baffle plates was proposed for an aircraft with an altitude of 20-50 km and reach a speed of Mach 2-5.
Abstract: An aerospace turbofan engine that injects oxygen-enriched gas from an inlet includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a first afterburner outer ring. An aerospace turbofan engine that injects oxygen-enriched gas from an inlet and an afterburner individually or simultaneously includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a second afterburner outer ring. The aerospace turbofan engines which fully utilize oxygen in the atmosphere for combustion and work in various flight altitude ranges adopt regenerative cooling-type afterburners with acoustic cavity and baffle plates, so that an aircraft can fly to an altitude of 20-50 km and reach a speed of Mach 2-5. Variants of the aerospace turbofan engines are disclosed.
Patent•
21 Jun 2019
TL;DR: In this article, a rectifying supporting plate structure of an afterburner was designed, and the structure is high in heat storing capacity, and a high-temperature area can be kept around the oil injecting hole, so that the fuel oil can be conveniently evaporated and atomized; in addition, the injected-out fuel oil directly impacts the peripheral rectifying plate provided with a large amount of pores.
Abstract: The invention provides a rectifying supporting plate structure of an afterburner. The rectifying supporting plate structure of the afterburner is characterized in that part of turbine afterflow directly enters an air current channel between a peripheral rectifying plate and an inner rectifying supporting plate flame stabilizer and is capable of heating fuel oil in a fuel oil channel while flowingthrough the inner rectifying supporting plate flame stabilizer; the fuel oil injected out from an oil injecting hole is mixed with hot air current so as to realize burning in a reflowing area; and therest turbine afterflow enters an air current channel between the peripheral rectifying plate and the inner rectifying supporting plate flame stabilizer after flowing through the peripheral rectifyingplate provided with a large amount of pores so as to participate in burning. According to the rectifying supporting plate structure of the afterburner, the peripheral rectifying plate provided with alarge amount of pores is designed; the structure is high in heat storing capacity, and a high-temperature area can be kept around the oil injecting hole, so that the fuel oil can be conveniently evaporated and atomized; in addition, the injected-out fuel oil directly impacts the peripheral rectifying plate provided with a large amount of pores so as to further atomized and doped with gas, and asa result, stable igniting and burning can be realized; the stable working scope of the afterburner is expanded; and the burning efficiency is improved.
Patent•
12 Apr 2019
TL;DR: In this paper, an aero engine thermal management system with hot oil tank returnable oil is described, and an oil return oil-way is additionally arranged on an after-burner fuel flow path and located in front of a afterburner.
Abstract: The invention discloses an aero engine thermal management system with hot oil tank returnable oil. The aero engine thermal management system with the hot oil tank returnable oil is characterized in that an oil return oil-way is additionally arranged on an afterburner fuel flow path and located in front of a afterburner 17, and oil mass of an afterburner oil-way is increased; during high-speed flight, after the fuel of the afterburner fuel flow path flows through an afterburner fuel distributer of an afterburner oil-way assembly accessory 16, the fuel oil flow entering the afterburner 17 is controlled to meet requirements, and the remaining fuel flows into a high-temperature fuel tank 7 for temporary storage; during low-speed flight, the fuel in the high-temperature fuel tank 7 penetrates through a first empty-oil heat exchanger 5, and the low-temperature incoming flow air is used for cooling the high-temperature fuel, and finally the fuel is collected into the fuel tank. According to the aero engine thermal management system with the hot oil tank returnable oil, the problem of insufficient fuel heat sink at the time of high-speed flight is solved without changing a conventional thermal management system solution, and the aero engine thermal management system with the hot oil tank returnable oil has the advantages of easy implementation, easy transformation and high efficiency.
Patent•
28 May 2019
TL;DR: In this paper, a modular device for a fuel cell system, including a start-up burner, a reformer, an after-burner, and a heat exchanger which are all disposed in one chamber.
Abstract: A modular device for a fuel cell system, includes a start-up burner, a reformer, an afterburner, and a heat exchanger which are all disposed in one chamber. The reformer surrounds the start-up burner,and the afterburner is located above the start-up burner and surrounds the reformer. The heat exchanger surrounds the afterburner and the reformer.
01 Aug 2019
TL;DR: Goal-Oriented (GO) method is used to analyze the reliability of an aero-engine fuel system with afterburner combustion chamber and shows that it is reasonable and the GO method can be used for the reliability analysis of aero -engine systems.
Abstract: An aero-engine fuel system is an important part of an aero-engine, and its reliability directly affects the operation of the aero-engine. To improve the reliability of aero-engines, this paper uses Goal-Oriented (GO) method to analyze the reliability of an aero-engine fuel system with afterburner combustion chamber. Firstly, the GO model is established by the structural schematic diagram of an aero-engine fuel system with an afterburner combustion chamber, and the qualitative analysis and quantitative calculation are carried out according to the operation rules of operators and signal flows in the GO model. Then the minimum cut set and quantitative reliability level of the fuel system are obtained respectively. Finally, the results are compared with the results by the fault tree analysis (FTA) method. The comparison result shows that the reliability analysis of the aero-engine fuel system by the GO method is reasonable and the GO method can be used for the reliability analysis of aero-engine systems.
Patent•
04 Sep 2019
TL;DR: In this paper, an afterburner combustion chamber control system consisting of series-augmented pump, nozzle and after-burner regulator, after-burger fuel distributor, and N fuel collectors is presented.
Abstract: FIELD: machine building.SUBSTANCE: invention relates to the field of automatic control of a gas-turbine engine, namely to a control system of operation modes of an afterburner combustion chamber. Afterburner combustion chamber control system comprises series-augmented pump, nozzle and afterburner regulator, afterburner fuel distributor, and N fuel collectors. Inputs of fuel manifolds are combined and connected to output of up-down fuel distributor, and outlets are output of system. Gas flow temperature transducer arranged at the outlet of afterburner combustion chamber and control valve of fuel distribution manifold valve arranged on afterburner fuel distributor case is additionally introduced. Output of fuel manifold control valve of fuel manifolds is connected to second input of afterburner distributor.EFFECT: invention allows increasing completeness of fuel combustion in afterburner combustion chamber.1 cl, 3 dwg
Patent•
07 Nov 2019
TL;DR: In this article, an automatic control of multi-mode gas turbine engines (GTE) with afterburner combustion chamber (ACC) is presented. But the authors focus on the use of the after-burner as a secondary combustion chamber.
Abstract: FIELD: engine building.SUBSTANCE: invention relates to aircraft engine building and can be used in electronic-hydromechanical systems for automatic control of multi-mode gas turbine engines (GTE) with afterburner combustion chamber (ACC). In the known method for control of gas turbine engine with afterburner combustion chamber (ACC) additionally measuring area of critical section of jet nozzle, generating a signal F equal to the ratio of the degree of reduction of gas pressure on the turbine to the measured area of the critical cross-section of the jet nozzle, generating a signal Frat equal to the ratio of the deviation of the current value of the signal F from its average value to its average value, preliminary by results of tests determining values Fgr and Fgr2, corresponding to values of signal Frat at start-up and extinction of afterburner respectively, when the signal Frat exceeds the preset positive value Fgr, the combustion in the afterburner combustion chamber is determined and the augmenter of the afterburner combustion chamber is switched off, and at start of afterburner combustion chamber with reduction of signal Frat below lower preset negative value Fgr2, extinguishing of afterburner combustion chamber is determined and supply of fuel into augmenter is stopped.EFFECT: higher reliability of determination of combustion in afterburner combustion chamber, reduced weight of engine due to exclusion of flame sensors in afterburner combustion chamber and electric wires to them, and also increased speed of reaction of system in part of detection of combustion of fuel in afterburner combustion chamber.3 cl, 1 dwg
Patent•
24 Jan 2019
TL;DR: In this paper, a method for ensuring the gas-dynamic stability of a turbojet engine under extreme conditions of operation is presented to ensure the nonuniformity of the air flow at the engine inlet without the use of additional liquids and without loss of thrust in the afterburner mode of engine operation.
Abstract: FIELD: engines and pumps.SUBSTANCE: method for operation of a turbojet engine relates to the field of aircraft engine construction, in particular to methods for ensuring the gas-dynamic stability of turbojet engines under extreme conditions of operation. At first, for this type of engine, tests are conducted at maximum and afterburner modes of engine operation, and thrust Ris measured in these modes, as well as the discharge pressure of the low pressure compressor P, the total air flow through the engine G, the discharge pressure of the high pressure compressor P, the turbine exhaust pressure P, the pressure at the engine intake P, and the relation is calculated,,, then the degree of expansion in the turbines πis successively changed upwards, at least discretely, with at least three values of πthe current values of the above parameters are measured and the above relations are calculated, the deviations of the current values from the initial values,,are calculated, functionsand δπ=f(δR) are developed using them, then using the predetermined amount of short-term increase in gas-dynamic stability reserves and / or short-term decrease in thrust when increasing the unevenness of the air flow at the engine intake, the value of change of δπis determined and additionally introduced into the electronic controller of the engine as a program to maintain the degree of expansion in the turbines while increasing the unevenness of the air flow at the engine inlet, and in the afterburner modes of operation of the engine additional fuel supply is provided to the fuel headers of the afterburner chamber for partial recovery of engine thrust.EFFECT: method allows to ensure the gas-dynamic stability of the engine with an increase in the non-uniformity of the air flow at the engine inlet without the use of additional liquids and without loss of thrust in the afterburner mode of engine operation.1 cl, 4 dwg, 4 tbl
19 Aug 2019
Patent•
07 Nov 2019
TL;DR: In this paper, a gas turbine engine (GTE) with an augmenter mounted on a supersonic maneuvering aircraft is described, and a controlled throttle is installed in the main line communicating the siphon gate loop with the oil tank.
Abstract: FIELD: machine building.SUBSTANCE: invention relates to machine building, particularly, to oil system of aircraft gas turbine engine (GTE) with augmenter mounted on supersonic maneuvering aircraft. Technical result is achieved due to that known oil system of aviation GTE with afterburner chamber comprises siphon gate installed in oil supply line, which rising branch is connected via second output of controlled two-position valve with oil cavity of section of two-section fuel-oil heat exchanger, fuel cavity of which is communicated with main line of fuel supply to main combustion chamber, and falling branch is interconnected with oil cavity of section of two-section fuel-oil heat exchanger, fuel cavity of which is interconnected with main line of fuel supply into augmenter combustion chamber. Controlled throttle is installed in the main line communicating the siphon gate loop with the oil tank.EFFECT: technical result of invention is increase in GTE operation reliability by simplifying throttle adjustment and providing stability of oil supply pressure at start-up.1 cl, 1 dwg
01 Nov 2019
TL;DR: In this article, a method of carrying out steady-state CFD analysis followed by acoustic analysis, to capture the acoustic cavity modes for different after-burner models was considered for the study to predict the optimum afterburner.
Abstract: Capturing and simulating combustion instabilities in afterburner, leading to screech, is very difficult Carrying out the transient analysis requires large computational facilities and there is a limitation of considering the reverse effect of acoustics on flow and combustion A novel method of carrying out steady-state CFD analysis followed by acoustic analysis, to capture the acoustic cavity modes for different afterburner models was considered for the study to predict the optimum afterburner Eight afterburners were modelled, with different area ratios, nozzle angles and equivalence ratios The numerical calculations had been performed, by using ANSYS® Fluent, with realizable k- e model and SIMPLE algorithm by enabling energy equation Kerosene (C12H23) was considered as fuel with virtual fuel injectors with species transport for modelling combustion and finite-rate/ eddy dissipation model for solving the multiple simultaneous chemical reactions Maximum Mach number was observed for the model with an equivalence ratio of 058, area ratio of 52 and nozzle angle of 6o and with minimum O2 mass fraction of 0144 and maximum CO2 mass fraction of 0075 due to complete combustion The computational results were imported into Actran™ for acoustic analysis It is found that the 10-20 dB less mean square pressure values; with maximum transmission loss of 755 dB at 530 Hz, 707 Hz at 990 Hz; was observed for the afterburner model with equivalence ratio of 058, area ratio of 52 and nozzle angle of 6o, indicating the maximum absorption of acoustic energy and mitigation of screech instabilities for the designed inlet conditions
Patent•
30 Oct 2019
TL;DR: In this paper, the afterburner of a pellet burner is characterized by a guiding pull rod, which makes a reciprocating movement and is connected by means of an articulated joint and guides to a movable ring.
Abstract: The pellet burner afterburner according to the present invention is installed in the burner at the border of a combustion chamber (2) and a fuel inlet (3) being the terminal section of an internal feeding pipe (4), seated on the feeding pipe (4).Furthermore, the afterburner according to the present invention is characterized in that it contains a guiding pull rod (5), which makes a reciprocating movement and is connected by means of an articulated joint (6) and guides (7) to a movable ring (8), which has cut-outs (9) on its perimeter, adapted to both the number and the shape of the profiled guiding vanes (10), which are fitted at equal intervals to the mounting plate (11), whereby the ring (8) is slide-mounted on to the guiding vanes (10).