Showing papers on "Afterburner published in 2016"

Ignition and combustion of pyrotechnic compositions based on micro- and nanoparticles of aluminum diboride in air flow in a two-zone combustion chamber

Abstract: This paper presents the experimental study of ignition and combustion of micro- and nanoparticles of aluminum diboride as part of pyrotechnic energy-saturated compositions in a gas generator with an air afterburner chamber and the thermodynamic calculations of combustion of pyrotechnic compositions based on aluminum diboride in air. The discharge of the combustion products from the afterburner chamber is recorded on video. It is shown that replacing micron aluminum diboride by powdered diboride with a mass-average diameter of particles equal to ≈270 nm in the pyrotechnic composition and increasing the pressure in the afterburner chamber cause the combustion efficiency in air to increase by 5–20%.

Pre-evaporation type integrated afterburner

Abstract: The invention provides a pre-evaporation type integrated afterburner. An oil cavity is formed inside an afterburning inner cone, and is connected with a fuel oil channel inside a rectification support plate flame stabilizer. Fuel oil is heated in the oil cavity to become gas or a supercritical body, and then the gas or the supercritical body enters the fuel oil channel inside the rectification support plate flame stabilizer and is sprayed out from direct-injection type spraying nozzle small holes in the two sides. The spraying nozzle small holes are reasonably formed so that the mixing effect of the fuel oil and the gas can be effectively improved, and the burning efficiency is improved. In addition, a large amount of heat is transmitted to the fuel oil through the afterburning inner cone, so that the self temperature is decreased, and the infrared stealth performance is effectively improved. The pre-evaporation type integrated afterburner has the beneficial effects that on the basis of an integrated afterburner structure, by reasonably leading in the structure of the oil cavity inside the afterburning inner cone and the structure of the fuel oil channel inside the rectification support plate flame stabilizer and reasonably forming the direct-injection type spraying nozzle small holes, the burning efficiency is effectively improved, and the infrared stealth performance is effectively improved.

Two regenerative cooling afterburners with sound cavities and application thereof

Abstract: The invention relates to two regenerative cooling afterburners with sound cavities In order to overcome the defects of the existing afterburners and enlarge the application ranges, a straight-groove sound cavity for shock absorption is arranged and an integrated groove-milled connection structure employing kerosene or liquid hydrogen fuel or hydrogen peroxide having a medium concentration within the range of 70-79% as a regenerative cooling agent is adopted so that the reliability of the afterburner can be improved, and the working time, the service life, and the flight height and the speed can be increased A schematic diagram of a related supply system is given in addition to the structures of the afterburners The afterburners are mounted at the rear portion of an aero-gas turbine engine to form a long-augmentation aero-gas turbine engine and a tandem turbo-rocket combined engine The afterburners can be provided for a plurality of high-speed airplanes as power devices, and are particularly applicable to novel supersonic airliners and advanced space tourism aircrafts Besides, the afterburners also can be used as auxiliary winged rocket propulsion and withdrawal engines or low-turbine total temperature gas turbine engines for other purposes

Afterburner and turbine engine

Abstract: The invention provides an afterburner and a turbine engine. The afterburner comprises an outer cylinder assembly, a center body assembly, an oil way assembly, an annular combustion chamber and an igniter; the center body assembly comprises a front body, a middle body and a rear body, wherein the front body is located at the axial front end of the afterburner and forms a gas inlet, accepting entry of oxygen-containing gas, of the annular combustion chamber with the outer cylinder assembly, the middle body is located behind the front body along the axis and is connected to the front body and integrated with the front body, and the rear body is located behind the middle body in the axial direction, is arranged in the middle body in a slid and sleeved mode and forms a gas outlet of the annular combustion chamber with the outer cylinder assembly; the igniter is arranged at the corresponding part, forming the annular combustion chamber with the outer cylinder assembly, of the center body assembly and is used for igniting fuel gas formed by fuel and the oxygen-containing gas entering the annular combustion chamber, then rotation and knocking combustion of the fuel gas are realized, and therefore the problem that combustion of the afterburner is instable is solved, the heat efficiency of combustion is improved, and the power capability of working media is improved.

Initiation of Damage to the Hot Part of Aircraft Turbine Engines

Abstract: Abstract In the paper, the initiation causes of damage to flame tubes of a basic combustion chamber and turbine units, which are the most common in the operation process of aircraft turbine engines (ATE), were presented. They were illustrated with the use of numerous examples of progressing degradation of the surface condition of parts and components of various types of aircraft engines which was found during endoscopic controls. On the basis of the systematic observation results, the process of destruction of the turbine rotor ring blades’ surface was discussed. The attention was paid to the current and still valid evaluation of the aircraft turbine engine’s suitability for further operation, taking into account the specifics of its use.

Experimental investigation into performance of integrated hotbox in 1-kW solid oxide fuel cell system

Abstract: An experimental investigation is performed to evaluate the performance of an integrated hotbox in a 1-kW solid oxide fuel cell (SOFC) system fed by natural gas. The integrated hotbox comprises all the main balance of plant components of an SOFC system, i.e. afterburner, reformer, and heat exchanger, and it not only reduces the physical size of the system but also yields improved system efficiency. The experimental results show that under optimal operating conditions, the combined H2 and CO content of the reformate gas is approximately 70%, while both anode and cathode in-gas temperatures are around approximately 750°C.

Aero-engine afterburner oil supply quantity calculation method

Abstract: The invention discloses an aero-engine afterburner oil supply quantity calculation method and belongs to the field of engine design. The thrust requirement of any engine work point is calculated according to engine bin pressure PH and engine inlet air total temperature T1, and the total oil quantity requirement of an afterburner is calculated according to the thrust requirement; besides, the oil supply quantity corresponding to the afterburner is checked according to a current accelerator rod angle alpha0 and a gas compressor post pressure P3; the total oil quantity requirement is compared with the oil supply quantity of the afterburner so that ratio parameters of the afterburner below the engine work points can be obtained; the function relation f(T1,PH) between the ratio parameters, the engine bin pressure PH and the engine inlet air total temperature T1 can be obtained, and finally an aero-engine afterburner oil supply quantity two-dimensional function Wfa=f(alpha0)*f(T1,PH)*f(P3) is formed. By means of the method, the afterburner oil supply quantity at any work point can be adjusted, and current states of other work points are not affected.

Design and Experimentation of Simulated Combustor Model for Aircraft Afterburner Applications

Abstract: Abstract An experimental study of the recirculation zone and mixing lengths for bluff-body stabilized flames is conducted at non-reactive conditions. This paper reports the prediction of recirculation zone length from dynamic pressure measurements. The auxiliary turbulence created from the wall of the combustor is also studied and maintained to levels as low as 5%. The experiments are conducted by varying the velocity from 5 m/s to 8 m/s for V-Gutters bluff-body with induced angles of 60, 90 and 120o. These gutters are maintained at same blockage ratio so that gutter angle to flow velocity is studied. It is inferred from the experiment that as the velocity in the duct increases, the length of the recirculation zone varies 5 mm for all V-Gutter angle. However, an increase in the V-gutter angle is observed to greater effect than an increase in the velocity, recirculation zone length which varied from 70 mm for 60o V-gutter to 150 mm for 120o V-gutter. Simultaneously a sharp reduction in shear distribution along the length of the combustor are observed, it influences in understanding the mixing characteristics in combustion.

Precooled air breathing engine

Abstract: There is provided a hypersonic air-breathing engine having an air passage with an inlet, an outlet, and an air flow, and a turbojet between the inlet and the outlet There is an air bypass around the turbojet, an afterburner downstream of the turbojet and air bypass, and valves selectively restrict air flow through the turbojet and air bypass The turbojet valve and air bypass valve are controlled to define a first mode where air flow through the air bypass is restricted and air flow through the turbojet is unrestricted, a second mode where air flow through the air bypass is increased relative to the first mode and the air flow through turbojet is reduced relative to the first mode, and a third mode where air flow through the air bypass is increased relative to the second mode and air flow through the turbojet is reduced relative to the second mode Nanoparticles may be used to enhance the rate of heat transfer of the pre-cooler and contribute to heat release through combustion

Device utilizing liquid carbon dioxide gasification to improve thrust of aircraft

Abstract: A device utilizing liquid carbon dioxide gasification to improve thrust of an aircraft mainly comprises a turbine/ramjet engine, an air compressor, a combustion chamber, a turbine, an afterburner, a liquid carbon dioxide storage tank, a one-way valve, a liquid carbon dioxide storage tank output header pipe, a branch pipe, an automatic adjusting valve, a thrust augmentation nozzle, an automatic control device, a temperature sensor, a pressure sensor and an adjustable spraying port. Taking the turbine/ramjet engine as an example, the device can utilize heat absorbed during liquid carbon dioxide gasification, the size in the gas state is expanded, the stable inert gas characteristic is achieved, and therefore the work temperature of the engine is lowered; the thrust of the aircraft is improved; and oxidation of the surfaces of the turbine, the afterburner and the adjustable spraying port due to high-temperature combustion gas is reduced. The running work condition of the engine, the quality, the safety, the service life and the flight hidden performance of the aircraft are optimized. The device can be conveniently arranged on other aircrafts.

Understanding Blowout Phenomena to the Induced Angle of V-Gutter-Stabilized Flames

Abstract: Abstract The combustion and flame blowout characteristics are investigated in a vitiated environment by placing the 60°, 90° and 120° V-gutters. The blowout is initiated through varying the equivalence ratio of reactants’ flow rates. The blowout is mainly investigated in ultra-lean condition where the equivalence ratio ranges from 0.18 to 0.8, by varying the length of the combustor; the blowout of flame takes place more quickly; it occurred in all tested gutter angles. On increasing the gutter angle from 60° to 120° the flame blowout takes place at Reynolds number from 2,500 to 6,000, which is inversely proportional to the gutter-induced angle of the gutter. The flame flashback possibility occurs due to aggression of the flame marching towards the blowout. The 120° V-gutter has possible flashback since the blowout takes place at very low Reynolds number. As the length of the combustor increases, it is also evident that flashback phenomenon occurred in the rigorous flame just before the flame blowout.

Test device and test method for lubricating oil cut-off of aero-engine afterburner fuel regulator

Abstract: The invention provides a test device and test method for lubricating oil cut-off of an aero-engine afterburner fuel regulator By transforming a test device for an afterburner fuel regulator and adding a temperature measurement device on the afterburner fuel regulator, the invention achieves the purpose of monitoring whether a bearing of the afterburner fuel regulator works abnormally, solves the problem that an original test device for the afterburner fuel regulator does not meet lubricating oil cut-off test conditions and the problem of how to monitoring the working status of the afterburner fuel regulator after the lubricating oil cut-off, verifies whether the lubricating oil cut-off of the afterburner fuel regulator would cause damage to the bearing or an abnormal increase in temperature of a housing, and finds out the working time of the afterburner fuel regulator when the housing does not break after the lubricating oil cut-off The test method facilitates the quick analysis of causes of failure of the bearing of the afterburner fuel regulator and the increase in the temperature of the housing

Battery of solid oxide fuel cells

Abstract: FIELD: engines.SUBSTANCE: invention relates to the battery of solid oxide fuel cells which consists of an air supply unit including a flange with a nozzle with a calibrated washer, an air flow spreader, a central flange with holes for installation of tubes with seals for air supply into fuel elements; heat exchange chamber with heat exchanger in the form of a cylinder made of porous material with axial channels and with tubes installed with a gap to feed air into fuel elements, a screen, a catalytic afterburner for residual fuel containing porous material covered with a catalyst in made in the form of tubular grating with open ends of fuel elements fixed in it and air supply tubes passing through. Chambers of electrochemical oxidation of fuel with fuel elements closed ends of which are directed toward reactor of partial oxidation of primary fuel with air, are fixed relative to the body by means of a ceramic flange with recesses and with channels for fuel supply from the reactor of partial oxidation of primary fuel with air. Reactor of partial oxidation of primary fuel with air is made in the form of disk made of porous material covered with a catalyst. Unit for supply of mixture of primary fuel with air including top flange with nozzle with a calibrated washer and cylinder with axial channel ending with diffuser is made of heat-insulating material and provides lowering of operating temperature of primary fuel. Higher efficiency of electrochemical generator based on solid oxide fuel cells is the technical result of the invention.EFFECT: fuel utilization factor in the battery comes up to 85 %.1 cl, 4 dwg

Piston-turbine compound engine

Abstract: Provided is a piston-turbine compound engine, comprising a piston-type main engine (10), a turbine engine (12), an air channel (18), a turbine working-medium channel (14), an afterburner device (16), a bypass channel (20), and an air flow control device (38); the afterburner device (16) is arranged on the turbine working-medium channel (14), and the afterburner device (16) heats the turbine working medium by means of combustion; the bypass channel (20) is connected between the outlet part of a compressor and the afterburner device (16); the air flow control device (38) is used for controlling the compressed air of the compressor to enter a cylinder of the main engine, or to be delivered to the afterburner device (16) via the bypass channel (20). The piston-turbine compound engine addresses the issue of uninterrupted operation of an engine unit.

Two aerospace turbofan engines

Abstract: The invention relates to two aerospace turbofan engines. The first one is to feed rich oxygen in an intake way. The second one is to feed rich oxygen singly or synchronously in the intake way and an afterburner. Aiming at limited working height of an aviation turbofan engine, an intake way rich oxygen injecting module is arranged, a main structure of a traditional aviation turbofan engine is continuously used, and two sound cavity and separation regenerative cooling afterburners are adopted, so that the aviation turbofan engine can be changed to two aerospace turbofan engines capable of working at any height. The aerospace turbofan engine is an aerospace integral engine mainly adopting the traditional aviation turbofan engine, is excellent in technical succession, and facilitates development and application. The aerospace turbofan engine can propel an aircraft to fly at a 30-50 km height and a 3-5 M speed, or even more highly and more quickly, and is suitable for multiple aerospace integral aircrafts repeatedly used by multiple times.

Turbine-Based Engines: Turbojet, Turbofan, and Turboramjet Engines

Abstract: This chapter handles turbine-based engines (turbojet, turbofan, and turboramjet). This chapter starts with historical prospective and a classification of each engine. Next, thermodynamic and performance analyses for ideal and real cycles are introduced. Turbojet engine was coinvented in the 1930s by British and German activities. Analyses of single and double spools in the presence and absence of afterburner are described. Though rarely used in airliners or military planes in present days, it is still used in micro-turbojets and turbojets powering rockets during sustained flight.