scispace - formally typeset
Search or ask a question

Showing papers on "Afterburner published in 2014"


Journal ArticleDOI
TL;DR: In this article, a transient, coupled 3D computational fluid dynamics/computational solid mechanics model of a complete solid oxide fuel cell system and its experimental validation is presented, which includes all system components; namely the fuel cell stack, afterburner, pre-reformer, air preheater and auxiliary components.

50 citations


Proceedings ArticleDOI
27 Mar 2014
TL;DR: In this paper, a numerical engine cycle comparison was made between the Inter-Turbine Burner (ITB) cycle and a conventional afterburning cycle using the Numerical Propulsion System Simulation (NPSS).
Abstract: : An Inter-Turbine Burner (ITB) represents a novel mechanism for generating additional work from a gas turbine engine in applications where an afterburner would typically be used. An ITB can achieve higher thermal e ciencies over a typical afterburner while also generating shaft work versus only additional thrust. In an e ort to investigate the potential applications for the ITB, a numerical engine cycle comparison was made between the ITB cycle and a conventional afterburning cycle using the Numerical Propulsion System Simulation (NPSS). In the case of thrust augmentation, the ITB model outperformed the afterburning model when Thrust Specific Fuel Consumption (TSFC) is compared to increased thrust, but resulted in decreased fan e ciency and High Pressure Compressor (HPC) stall caused by fan overspeed. In the case of Power Extraction (PX) augmentation the ITB engine achieves similar TSFC results without experiencing component e ciency loss or approaching HPC stall. For the PX augmentation model, the pressure drop across the ITB was varied from 4% to 20%. Large pressure drops were found to increase the TSFC and reduce the HPC stall margin for the ITB model. ITBs are expected to achieve pressure drops between 3% and 5% and for this range the ITB will continue to be more fuel e cient than the afterburning engine model. An experimental investigation was performed focused on integrating the AFIT ITB to accept a common flow source. Three common flow source di users with core to bypass inlet area percentage ratios of 80/20, 70/30, and 60/40 were tested. All three di user designs were found to su er from flow reversal in the bypass stream caused by instances of greater total pressure in the core flow than in the bypass flow. The baseline thrust performance for the JetCat P200 Small Turbine Engine (STE), which will serve as the AFIT ITB vitiated air source, was determined and found to be consistent with manufacturer specifications.

8 citations


Patent
23 Apr 2014
TL;DR: In this paper, a liquid gas afterburner jet engine and a method for realizing after-burning flying of a jet plane were presented, where the jet engine consisted of an air incoming way, a gas compressor, burning chambers with fuel nozzles, a turbine, an after-burner, a tail nozzle and liquid gas noizles extending into the afterburners.
Abstract: The invention provides a liquid gas afterburner jet engine and a method for realizing afterburning flying of a jet plane. The jet engine comprises an air incoming way, a gas compressor, burning chambers with fuel nozzles, a turbine, an afterburner, a tail nozzle and liquid gas nozzles extending into the afterburner. By the method, the jet engine can be ensured to fully utilize thermal expansion of liquid gas to do work during afterburning propelling, and thrust of the jet engine is increased more efficiently, so that burning efficiency of the jet engine is improved obviously, thrust is increased, power cost is lowered, environmental pollution is reduced, and probability of being attacked by an infrared weapon can be lowered.

6 citations


01 Jan 2014
TL;DR: In this article, the progress and current state of afterburner were overviewed, and the advanced characteristics and new requirements of after-burner are analyzed, including the high inlet core flow temperature, the required significant high augmentation temperature, less aerodynamic loss, light weight, and good stealth performance.
Abstract: The progress and current state of afterburner were overviewed.The development of design technology is a result of the elevated performance requirements of aeroengine afterburner.The advanced characteristics and new requirements of afterburner were analyzed,including the high inlet core flow temperature,the required significant high augmentation temperature,less aerodynamic loss,lighter weight,good stealth performance and so on.The new structure and design technology of advanced afterburner were investigated,such as the air cooled flameholder and spray bar,afterburner integration design,evolvement of pilot flameholder,adjustable heat shield cooling,stealth performance design and numerical simulation.The development trend of variable cycle engine,hyper burner,trapped vortex afterburner and pulse detonation afterburner were forecasted.

5 citations


Journal ArticleDOI
TL;DR: Calculation results reveal that the local temperature distribution at the leading edge section of flame holder is improved under the action of streamwise vortices shedding from chevron mixers, and the combustion efficiency increased by 3.5% compared with confluent mixer under the same fuel supply scheme.
Abstract: To improve the performance of the afterburner for the turbofan engine, an innovative type of mixer, namely, the chevron mixer, was considered to enhance the mixture between the core flow and the bypass flow. Computational fluid dynamics (CFD) simulations investigated the aerodynamic performances and combustion characteristics of the chevron mixer inside a typical afterburner. Three types of mixer, namely, CC (chevrons tilted into core flow), CB (chevrons tilted into bypass flow), and CA (chevrons tilted into core flow and bypass flow alternately), respectively, were studied on the aerodynamic performances of mixing process. The chevrons arrangement has significant effect on the mixing characteristics and the CA mode seems to be advantageous for the generation of the stronger streamwise vortices with lower aerodynamic loss. Further investigations on combustion characteristics for CA mode were performed. Calculation results reveal that the local temperature distribution at the leading edge section of flame holder is improved under the action of streamwise vortices shedding from chevron mixers. Consequently, the combustion efficiency increased by 3.5% compared with confluent mixer under the same fuel supply scheme.

3 citations


Journal ArticleDOI
TL;DR: In this article, an acoustic simulation of hot jets issuing from a rectangular hypersonic nozzle was carried out, and the authors established a method capable of predicting the acoustic characteristics of the high-temperature and high-velocity jets issued from the realistic hypersenic nozzle having a complicated geometry.
Abstract: Acoustic simulation of hot jets issuing from a rectangular hypersonic nozzle was carried out. The aim of this study is, even though qualitative to some extent, to establish a method capable of predicting the acoustic characteristics of the high-temperature and high-velocity jets issuing from the realistic hypersonic nozzle having a complicated geometry. Two kinds of test nozzles, 2.4% scaled model with afterburner for hot jet experiments and 1.0% scaled model for cold-air/helium mixture jet experiments, were manufactured and tested. By using a high-enthalpy wind-tunnel plant, acoustic characteristics of the hot jets issuing from the rectangular hypersonic nozzle for several representative but realistic high-temperature and high-velocity jet conditions were obtained. At the same time, by using a small anechoic chamber, the acoustic characteristics of the hot jets were duplicated using cold-air/helium mixture jets having the same velocities. Although we have to pay attention to some noted exceptions, the di...

3 citations


01 Jan 2014
TL;DR: In this paper, a component-level mathematical model of supersonic inlet with bleeding adjustment was developed to study of integrated performance for supersonIC inlet/engine. And the engine installed thrust was verified to be effectively enhanced 3% by the bleeding adjustment of inlet when the aircraft worked at the middle and afterburner states.
Abstract: A component-level mathematical model of supersonic inlet with bleeding adjustment was developed to study of integrated performance for supersonic inlet/engine.Meanwhile,a coupling mathematical model of supersonic inlet and turbofan engine was built via a biaxial turbofan engine component-level models and inlet component-level models to describe their collaborate relationship.The properties of outside and inside flux of the intake were calculated base on this integrated component-level model for inlet/engine.Inlet bleeding properties in supersonic working mode were also analyzed.At last,the engine installed thrust was verified to be effectively enhanced 3% by the bleeding adjustment of inlet when the aircraft worked at supersonic flight in the middle and afterburner states.

3 citations


Patent
03 Jul 2014
TL;DR: In this article, a method for controlling the fuel gas supply of a fuel cell installation was proposed, in which the temperature in the fuel cell stack was controlled by the manipulated variable of the air supply.
Abstract: The invention relates to a method for controlling the fuel gas supply a fuel cell installation. In a first control circuit 1, the temperature in the fuel cell stack 7 is controlled by the manipulated variable of the air supply. In a second control loop, a temperature is controlled in the afterburner via the command value of the fuel gas supply 2, which represents the fuel gas utilization. This makes it possible to operate a fuel cell even with fluctuating gas qualities perfectly.

2 citations


29 May 2014
TL;DR: In this paper, the authors used the aeroengine afterburner operating process organization principles while designing afterburning chambers for the combined-cycle plant and the main technical solutions of such after-burning chambers design and approaches to fueling automated control system algorithm development is given as well.
Abstract: The high efficiency of using of the aeroengine afterburner operating process organization principles while designing afterburning chambers for the combined-cycle plant is shown in the article. The main technical solutions of such afterburning chambers design and approaches to fueling automated control system algorithm development is given as well.

2 citations


Proceedings ArticleDOI
28 Jul 2014
TL;DR: In this paper, a lobe mixer for hyperburner was designed, and the characteristics of the lobe mixer were evaluated by numerical simulation and the results showed that the streamwise votex created by the lobe can not only promote core and bypass flow mixing but also supply a more uniform fuel concentration.
Abstract: A hyperburner of a TBCC works in a wider operation range than an afterburner or a ramjet combustor. To meet the rigorous operation condition of a large bypass ratio engine under the whole flight range, core and the bypass flow should be mixed thoroughly. In this paper a lobe mixer for hyperburner was designed. Flow field and fuel distribution downstream the lobe mixer were studied by numerical simulation, and the characteristics of the lobe mixer was evaluated. Also, hyperburner combustion performance under different injection pattern was discussed. The results show that the streamwise votex created by the lobe can not only promote core and bypass flow mixing but also supply a more uniform fuel concentration. Staggered fuel injection from the both sides of lobe mixer radial can supply homogeneous fuel-air mixture for combustion, thus improve the hyperburner ignition characteristics and speed up the flame spreading procedure. The fuel injected from the lobe mixer outlet is benefit for the hyperburner performance.

2 citations


Patent
12 Nov 2014
TL;DR: In this article, a fuel supply device of an afterburner is provided with a fuel feed pipe, an inner side cooling cavity, fuel nozzles, air supply pipes, inner side wall face, a resonant cavity body, a slit, a V-shaped baffle plate, an outer side cooling cavities, outer side wall faces, and outer side cavity air inlets.
Abstract: The utility model discloses a fuel supply device of an afterburner, and relates to a fuel supply device. The fuel supply device of an afterburner is provided with a fuel feed pipe, an inner side cooling cavity, fuel nozzles, air supply pipes, an inner side wall face, a resonant cavity, a resonant cavity body, a slit, a V-shaped baffle plate, an outer side cooling cavity, an outer side wall face, outer side cooling cavity air inlets and inner side cooling cavity air inlets, wherein the fuel feed pipe is disposed at the head part of the fuel supply device; the air supply pipes are disposed on the two sides of the fuel supply device, three air supply pipes being uniformly arranged on each side; fuel liquid drops are ejected from the slit; cooling air enters into the outer side cooling cavity and the inner side cooling cavity through the outer side cooling cavity air inlets and the inner side cooling cavity air inlets respectively; the V-shaped baffle plate is installed at the tail part of the fuel supply device; both the inner side wall face and the outer side wall face are provided with cooling holes; and part of the cooling air in the inner side cooling cavity and the outer side cooling cavity is sprayed out from the cooling holes, to form cooling air films at the surface of the inner side wall face and the outer side wall face. With adoption of the fuel supply device provided by the utility model, complete atomization of the fuel is realized, thereby reducing emission of pollutants; and the difficulty that inlet air streams of the afterburner of an aero-engine are high in speed and temperature is effectively overcome.

Patent
17 Sep 2014
TL;DR: In this paper, the utility model provides a non-premixing central air supply multi-pipe gas afterburner for a high-speed flue gas flowing area, uniform temperature distribution, shortening of the length of the inlet flue of a waste heat boiler, reduction of the cost, and the like.
Abstract: The utility model provides a non-premixing central air supply multi-pipe gas afterburner A barrel is a segmental of metal pipe; holes in the two ends of the pipe are hermetically connected with an air side disk and a flue gas side disk respectively; the centers of the air side disk and the flue gas side disk are provided with through holes; air nozzles penetrating the length are hermetically connected in the through holes; six gas nozzles which are uniformly distributed on a circular ring taking the air nozzles as the centers are arranged on the flue gas side disk; a hole is formed in a position, which is not communicated with the air nozzles, on the barrel, and is hermetically connected with a fuel gas inlet pipe The non-premixing central air supply multi-pipe gas afterburner has the characteristics of simple basic structure, large demand range of applicable fuel replenishing amount, stable combustion in a high-speed flue gas flowing area, uniform temperature distribution, shortening of the length of the inlet flue of a waste heat boiler, reduction of the cost, and the like


Patent
27 Aug 2014
TL;DR: In this paper, the authors proposed a non-premixed central air supply multi-tube gas afterburner, which can be used for stable burning in high speed flue gas flow area, the temperature is uniformly distributed, the length of a waste heat boiler inlet flue can be shortened, and accordingly the cost is reduced.
Abstract: The invention provides a non-premixed central air supply multi-tube gas afterburner. A cylinder is a section of metal tube; two end holes of the tube are in closed connection with an air side disk and a flue gas side disk respectively; centers of the air side disk and the flue gas side disk are provided with a through hole; an air nozzle is connected into the through hole in a closed mode and communicated in the length direction; the flue gas side disk is provided with six gas nozzles which are uniformly distributed on a circular ring with the air nozzle as the center; a hole formed at a cylinder position which is not communicated with the air nozzle is in closed connection with a gas inlet tube. According to the non-premixed central air supply multi-tube gas afterburner, the basic structure is simple, the suitable afterburning quantity demand range is large, stable burning can be performed in a high speed flue gas flow area, the temperature is uniformly distributed, the length of a waste heat boiler inlet flue can be shortened, and accordingly the cost is reduced.

Journal ArticleDOI
TL;DR: In this paper, a miniaturized combustor was designed that can produce open supersonic methane-air flames amenable to laser diagnostics, and the salient parameters of operation were explored experimentally and flameholding was verified computationally using a well-stirred reactor model.
Abstract: A miniaturized combustor has been designed that can produce open supersonic methane–air flames amenable to laser diagnostics. The combustor is based on a two-stage design. The first stage is a vitiation burner that provides ignition and flameholding. The design of the vitiation burner was inspired by well-known principles of jet engine combustors. The salient parameters of operation were explored experimentally, and flameholding was verified computationally using a well-stirred reactor model. Both experiments and computations were used to verify a traditional scaling used in jet engine combustor design. The second stage of the combustor generated an external supersonic flame, operating in premixed and partially premixed modes. The equivalence ratio of the external supersonic flame was varied, as well as the total mass flow rate, and the overall flame phenomenology was examined, specifically supersonic flame length. The very high Reynolds numbers and strain rates present in the supersonic flames should pro...

01 Apr 2014
TL;DR: The afterburner system is supplied the gas O2 and gas CH4 to reduce the harmful exhaust gas in the combustion chamber of the liquid rocket engine for KSLV-II in NARO Space Center as mentioned in this paper.
Abstract: Combustion Chamber Test Facility (CCTF) is under construction to test the combustion chamber and the gas generator of liquid rocket engine for KSLV-II in NARO Space Center. The CCTF includes the afterburner which is combustion system to reduced the harmful products of gas generator. The afterburner system is supplied the gas O2 and gas CH4 to reduced the harmful exhaust gas. The CCTF Afterburner system is simulated and analysed by AMESim program through the all of gas supply system components. This study is performed to determine the pipes, orifice diameter, and gas supply conditions according to the total gas consumption from analysis of gas supply system.


Patent
24 Dec 2014
TL;DR: In this article, an efficient waste-gas utilization device using a turbine, comprising a waste gas channel, an afterburner device, and a turbine was presented, which was used for fluid communication with the waste gas source.
Abstract: Provided is an efficient waste-gas utilization device using a turbine, comprising a waste gas channel, an afterburner device, and a turbine. The waste gas channel is used for fluid communication with a waste gas source. The afterburner device is arranged on the waste gas channel; the afterburner device is used for further combustion of the waste gas in the waste gas channel, so as to form a waste gas combustion product. The turbine is in fluid communication with the waste gas channel, so as to be driven, by the waste gas combustion product in the waste gas channel, to rotate and thereby drive a load.