Showing papers on "Afterburner published in 2005"

Trapped vortex cavity afterburner

Abstract: A trapped vortex cavity afterburner includes one or more trapped vortex cavity stages for injecting a fuel/air mixture into a combustion zone. The trapped vortex cavity afterburner is operable to provide all thrust augmenting fuel used for engine thrust augmentation. Each stage has at least one annular trapped vortex cavity. The trapped vortex cavity afterburner may be a multi-stage afterburner having two or more trapped vortex cavity stages ganged for simultaneous ignition or operable for sequential ignition. One embodiment of the annular trapped vortex cavity is operable to raise a temperature of an exhaust gas flow through the afterburner about 100 to 200 degrees Fahrenheit. Each of the trapped vortex cavity stages may be operable to produce a single or a different amount of temperature rise of the exhaust gas flow through the afterburner. A chevron shaped trapped vortex cavity and having zig-zag shaped leading and trailing edges may be used.

Optical Diagnostics for Characterization of a Full-Size Fighter-Jet Afterburner

Abstract: In the present work the feasibility of using various optical/laser based techniques for characterization of the afterburner of a full-size aircraft engine have been investigated. The tests have been performed on-site at Volvo Aero Corporation and were mainly directed towards surface thermometry using thermographic phosphors and fuel visualization. All applications were studied for different engine running conditions, including various use of the afterburner (A/B). Laser-Induced Fluorescence (LIF) was employed for fuel visualization to investigate to what extent unburned fuel exits the afterburner. Laser-Induced Phosphorescence (LIP) from thermographic phosphors was used to measure two-dimensional surface temperatures on the outlet nozzle of the afterburner. In addition, the spectral characteristics of the burning jet stream were investigated. Copyright

Thrust vectoring missile turbojet

Abstract: A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. A thrust vectoring system is joined between a compressor and the nozzle. A controller is operatively joined to the thrust vectoring system for selectively varying distribution of air bled from the compressor into the exhaust nozzle for vectoring propulsion thrust.

Self powdered missile turbojet

Abstract: A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. An integral starter-generator is disposed inside the core engine and is joined to the rotor for equal speed rotation therewith. An electrical controller coordinates operation of the engine for subsonic, transonic, and supersonic operation of the engine in a missile self-powered by the starter-generator.

SOFC and gas turbine power systems—Evaluation of configurations for CO2 capture

Abstract: Publisher Summary This chapter highlights that pressurized solid oxide fuel cells (SOFC) integrated in a gas turbine cycle is a promising power generation concept The benefit of such combined systems is the potential for high electrical efficiency at small scale By including an afterburner for the fuel cell, the remaining fuel in the anode exit gas is fully converted to water and CO2 while the anode and cathode streams from the fuel cell are kept separated This enables the CO2 capture from an exhaust stream consisting of only CO2 and water This chapter evaluates, three afterburner technologies based on different membrane conductors from the perspective of thermodynamic cycle analysis and materials technology The total SOFC and gas turbine system with the different afterburners has been modeled in a general purpose flow sheet simulator, and mass and energy balances have been calculated The electrical efficiency has been determined and compared for each of the three afterburners The potential of the three technologies for future use as afterburners is evaluated

Supersonic missile turbojet engine

Abstract: A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. A controller is operatively joined to the core engine and afterburner and configured for scheduling fuel thereto for operating the afterburner dry during subsonic flight operation of the engine, wet during transonic flight, and dry during supersonic flight.

A Performance Study of a Super-cruise Engine with Isothermal Combustion inside the Turbine

Abstract: Current thinking on the best propulsion system for a next-generation supersonic cruising (Mach 2 to Mach 4) aircraft is a mixed-flow turbofan engine with afterburner. This study investigates the performance increase of a turbofan engine through the use of isothermal combustion inside the high-pressure turbine (High-Pressure Turburner, HPTB) as an alternative form of thrust augmentation. A cycle analysis computer program is developed for accurate prediction of the engine performance and a supersonic transport cruising at Mach 2 at 60,000 ft is used to demonstrate the merit of using a turburner. When assuming no increase in turbine cooling flow is needed, the engine with HPTB could provide either 7.7% increase in cruise range or a 41% reduction in engine mass flow when compared to a traditional turbofan engine providing the sane thrust. If the required cooling flow in the turbine is almost doubled, the new engine with HPTB could still provide a 4.6% increase in range or 33% reduction in engine mass flow. In fact, the results also show that the degradation of engine performance because of increased cooling flow in a turburner is less than half of the degradation of engine performance because of increased cooling flow in a regular turbine. Therefore, a turbofan engine with HPTB will still easily out-perform a traditional turbofan when even more cooling than currently assumed is introduced. Closer examination of the simulation results in off-design regimes also shows that the new engine not only satisfies the thrust and efficiency requirement at the design cruise point, but also provides enough thrust and comparable or better efficiency in all other flight regimes such as transonic acceleration and take-off. Another finding is that the off-design bypass ratio of the new engine increases slower than a regular turbofan as the aircraft flies higher and faster. This behavior enables the new engine to maintain higher thrust over a larger flight envelope, crucial in developing faster air-breathing aircraft for the future. As a result, an engine with HPTB provides significant benefit both at the design point and in the off-design regimes, allowing smaller and more efficient engines for supersonic aircraft to be realized.

Method and apparatus for providing an afterburner fuel-feed arrangement

Abstract: Method and apparatus for providing an afterburner fuel-feed arrangement including an elongate fuel spraybar for distributing fuel to the afterburner section of a turbo-combustion engine. The spraybar has a longitudinal axis and includes a fuel-receiving spray head in fluid communication with a plurality of elongate fuel pipes surrounded by an elongate, aerodynamic-shaped shroud. The spray head is configured to be mounted in a casing of a turbo-combustion engine which projects the surrounded fuel pipes into an interior through-core of the engine in cross-wise orientation to a core gas flow thereof. The shroud has an interior lateral sidewall that includes a pipe-receiving portion configured to abuttingly engage a corresponding shroud-engaging portion of an exterior surface of one of the fuel pipes. The pipe-receiving portion is configured to substantially radially fix a fuel pipe, received therein, relative to the shroud. In this manner, the fuel pipes are supported along their length, and when the pipes are abuttingly engaged with the shroud, the braced configuration is stiffened which raises the eigenfrequencies of the assembly into ranges higher than those of the incorporating engine.

System consisting or fuel cell, afterburner and heat exchanger

Abstract: The system includes a fuel cell (1), and an afterburner (6) for its exhaust gas, to which air is supplied as an oxidizing agent. A heat exchanger (9) warms up the air flow supplied to the fuel cell using the exhaust gas from the afterburner. A unit (23) containing the heat exchanger, a unit (22b) containing the afterburner, and a unit (21) containing the fuel cell are arranged one above the other to form a stack. The afterburner is formed as a surface burner.

Analysis of a Simple Solid Oxide Fuel Cell System with Gas Dynamic in Afterburner and Connecting Pipes

Abstract: A simple solid oxide fuel cell plant is analysed based on the first law of thermodynamics approach. This system consists of a solid oxide fuel cell stack, a steam reformer, a mixer, a vaporiser, an afterburner, and two pre-heaters. To simplify the study, the enthalpy at each node of the system is normalized with the lower heating value of the inlet fuel. A gas dynamic model for calculating the flow in the pipes connecting the system components is considered and can be used to estimate the flow velocity and friction-induced pressure drop in the piping. Though the effect of a friction-induced pressure drop can be significant in a sizeable integrated solid oxide fuel cell-gas turbine power plant, it does not significantly affect the plant efficiency in this study, due to rather short piping used in this simple power system. A steady flow energy equation and the Rayleigh line flow assumption are applied to the afterburner to calculate the exit flow temperature, velocity and pressure.

Air and fuel delivery system for a post combustor burning ring

Abstract: The device has distributing cases housed in sectors (38) of a spray ring (26), where air is supplied to the cases through one of their ends extending inside an afterburner flame holder arm (14). The device is housed inside the arm, and extends between the spray ring and an external wheel case of an afterburner inside the arm. Each case has an air inlet opening formed by cutting an end of the sectors.

Flow Investigations in an Aero Gas Turbine Engine Afterburner

Abstract: This paper is concerned with the prediction of flow and flame characteristics behind complex flame stabilizer used in aero gas turbine afterburners. The numerical calculation is performed using SIMPLE algorithm with unstructured grid arrangement in which time averaged transport equation for mass, momentum, turbulence and energy are solved using finite volume method. The turbulence effects are simulated using RNG κ-e model. Flow analysis has been carried out for the non-reacting and reacting conditions. Meshing of the flow domain is done in GAMBIT. A detailed analysis of non-reacting flow in a 60°sector afterburner from inlet to exit of the afterburner is carried out in FLUENT solver code. The various thermodynamic properties are analyzed and presented along the length of the afterburner. Three different combustion models viz. prePDF, eddy dissipation and finite rate/eddy dissipation model are used in order to predict the reacting flow. An experimental investigation of the three-dimensional confined flow fields behind a “V” shaped complex flame stabilizer in an isothermal model of an afterburner is carried out to validate the CFD code. From the present study it is concluded that the prediction procedure adopted especially for non-reacting flow can be used with confidence in the development of an afterburner at a lower cost. Since measurements were not possible under reacting conditions no attempt has been made for reacting flow validation.Copyright © 2005 by ASME

Fuel injector with protection means and gas turbine engine with such a fuel injector

Abstract: The engine has a gas flow reheating duct with an afterburner flame holder arm (8) having an open enclosure. The enclosure has a wall (8`) within which a fuel injecting tube (8b), injecting a fuel (10) in a direction, is extended. The arm has a radial cooling jacket (8a) in a side of the wall forming a U shaped section, and a protection foil (8d) interposed between the tube (8b) and the wall, in the direction of fuel injection.

Afterburner with assured ignition

Abstract: The engine has an afterburner with an annular fuel injection ramp (34), and a spark plug (42) mounted in the vicinity of the ramp. The afterburner has an ignition injector (48) installed opposite to the plug and having a jet pipe for pulverization of fuel. The injector is connected to a conduit (49) that delivers fuel to the injector from a fuel source, under a controlled pressure independent of the supply conditions of the ramp.

Engineering an afterburner for a miniature gas turbine engine

Abstract: Purpose – This paper is concerned with the theoretical and practical engineering development issues, necessary for the design, build and test of an afterburner thrust augmentation system for a model aircraft gas turbine engine.Design/methodology/approach – Research into key combustion parameters including, flame holder diameter, flame holder edge velocity, burner velocity and equivalence ratio were undertaken. This information was used as the basis for the design and fabrication of the afterburner combustion system. The after burner system had been designed to fit a Wren MW54 model gas turbine engine, that included FADEC control for the mother engine. Substantial testing of the afterburner system was undertaken.Findings – Changes in “dry” and “wet” jet efflux temperature while the engine is accelerating from idle to full power are found. The increase in temperature between the dry and wet case are not markedly different, demonstrating the poor quality of the afterburner flame: the testing of the afterburn...

Thermodynamic Analysis of Turbofan Engine

Abstract: The present work deals with a detailed parametric thermodynamic analysis of all the possible configurations of turbofan engine (two and three spool with or without mixer and/ afterburner) employing transpiration cooling technique for turbine blade cooling. The study is focused on design point performance and is of general nature rather than an application specific parametric study. The analysis has been carried out by selecting/developing models for various components of engine. A computer program has been written which is capable of predicting engine dependent parameters (i.e. specific thrust, thrust specific fuel consumption, propulsive efficiency, efficiency of energy conversion and overall efficiency) at varying independent parameters at any flight condition and for any set of operating parameters. A set of multi-dimensional carpet plots predicting the effect of dependent in terms of independent parameters has been presented considering transpiration cooling for turbine blades and the temperature effect on specific heat of air/gas. Besides giving the comparative design point performance for a class of turbofan engine, these results could also be useful in assessing the relative benefits of extending technology to new engine configurations. Though, for a realistic mission application, the difference in performance at various thrust sizing conditions and at cruise conditions critical for fuel burn is a key characteristic in selecting the appropriate cycle, however this study could be useful in selecting in general the cycle configuration for a particular need with its optimum operating parameters.

Large Eddy Simulation of Pollutant Performance in an Afterburner

Abstract: The k-equation subgrid-scale model is used for large-eddy simulation(LES) of the pollutant performance in the model afterburner with V-gutter flame stabilizer. A two-step turbulent combustion subgrid-scale model is employed for calculating carbon monoxide CO concentration. The NO subgrid-scale pollutant formation model is applied to the evaluation of the rate of NO formation. The EBU combustion subgrid-scale model is used to determine the chemical reaction rate. The heat flux model is applied to prediction of the heat flux. Agreement between the predictions and experiments shows that pollution formation subgrid-scale models can be used to predict pollutant emissions in an afterburner.

Off-design Performance of Turbojet Engine for Sub-scale Supersonic Unmanned Plane

Abstract: The preliminary analysis is conducted for a turbojet engine of the Supersonic Unmanned Plane with a single spool, a convergence nozzle, a pitot intake and an afterburner. The error matrix method is employed, in which the compression ratio at the compressor, turbine inlet temperature and turbine expansion ratio are selected as independent variables for turbojet operation, then evaluated the three error vector components. The error vector is composed of the flow rate balance at compressor and turbine inlets, the compressor-turbine power balance, and pressure-mass flow rate balance at nozzle throat. To obtain solutions, the norm of error vector must be reduced to very small value by Newton iterative procedure. In the present study, compressor inlet diameter, turbine inlet temperature (TIT) limit are 0.14m, 1273K, respectively. The present engine models are operational along the constant flight dynamic pressure path of 50 kPa in transonic region ( Mach 0.9 to 1.3 ) The present study is focused on the effects of compression ratio and air flow rate at compressor on thrust level and the feasibility to break the sound barrier. For the feasibility study, the aerodynamic configuration of aircraft is proposed and its aerodynamic characteristic is also evaluated. Then, the possibility to break the sound barrier is discussed by comparing the thrust to the drag.

CFD study of isothermal flow in an afterburner system

Abstract: This paper focuses a detailed numerical prediction of non-reacting flow analysis in a practical 1/3 scaled model gas turbine afterburner system. The analysis is performed using SIMPLE algorithm in a body-fitted multi-block grid using STAR-CD software. The turbulence is simulated using standard k-e model. The validation of software is carried out in a afterburner model by comparing axial, radial and circumferential velocities at various axial locations. The agreement between the prediction and experimental data are quite reasonable. The analysis is extended to the flow in a practical afterburner system. The afterburner system consists of an annular diffuser, a complex three-dimensional flame stabilizer, a liner with chute, screech and cooling rings holes and a convergent nozzle. The wall static pressures are compared with experimental data obtained from rig results for both core and bypass casing. The agreement between CFD prediction and experimental data are in close agreement. The predicted length of the re-circulation zone of the lower radial gutter is larger (2.7 times width of the gutter) than upper radial gutter, which is about 2.3 times width. This is due to combined effect of annular diffuser and lower radial gutter. But the length of the re-circulation zone of the annular ring is slightly less than (0.94 times) the width of the v-gutter. The effect of different mass flow rates on the afterburner performance is also evaluated and it is observed that mass flow rate does not affect the re-circulation zone characteristics. An increase of 20% in mass flow rate increases the exit nozzle velocity by 35%.

Optimization control of minimum fuel consumption at aero-engine afterburning condition

Abstract: The characteristic of fuel consumption at aero-engine afterburning condition was analyzed.Based on the fact that the efficiency of main combustor is higher than that of the afterburner,this article puts minimum fuel consumption mode into use at aero-engine afterburning condition.Linear Programming was used to optimize the aero-engine performance.Digital simulations show that the specific fuel consumption was decreased by 5%~7%.The benefit of minimum fuel consumption mode at afterburning condition is much more than that of non-afterburning condition.It has great application potential in engineering.

Diesel engine exhaust gases two-stage soot filter

Abstract: FIELD: mechanical engineering; diesel engines ^ SUBSTANCE: invention can be used for cleaning exhaust gases of diesel engines Proposed two-stage soot filter of diesel engine exhaust system contains housing of rotation chamber with inlet and outlet branch pipes, swirler, soot collector with afterburner and additional filtering element Housing of rotation chamber is made double-walled, with head isolator placed in space between walls Soot collector with afterburner is enclosed in cup installed for longitudinal displacement along guides inside cylinder Control return mechanism is installed in cylinders after soot collector Return mechanism consists of spring and rod, and additional filtering element is located in space between cylinder and filter housing and is furnished with electric heater ^ EFFECT: provision of effective cleaning of exhaust gases from participles of soot, reduced fuel consumption and power losses at different modes of operation of diesel engine, increased service life of filter and its overhaul life ^ 4 dwg

By-pass engine afterburner

Abstract: FIELD: mechanical engineering; gas-turbine engines. ^ SUBSTANCE: proposed afterburner of by-pass engine contains behind-the-turbine and fan inlet channels, separating ring ferrule between channels, central body, posts connecting central body with separating ferrule, housing with heat shield, discharge nozzle manifolds and flame stabilizer. Flame stabilizer is installed in end face of separating ferrule. Discharge nozzle manifolds are arranged in behind-the-turbine and fan inlet channels before flame stabilizer. ^ EFFECT: minimization of length and mass of afterburner, reduced losses of total pressure, improved efficiency of cooling of construction members. ^ 3 dwg

Afterburner device ignition performance improving method for turbofan engine, involves guiding fraction of primary flow in ignition zone so that zone temperature is greater than secondary flow temperature to favor ignition of afterburner

Abstract: The method involves guiding a fraction of primary flow (10) in an ignition zone (34) of an afterburner in order to maintain the temperature in the zone at a value greater than value of secondary flow (20) in a manner to favor ignition of the afterburner. The primary flow is hot and the secondary flow is cool, where the fraction of primary flow is injected in an upstream part of the zone. An independent claim is also included for an afterburner device for a turbofan engine.

Device for fixing a burner ring in an afterburner combustion chamber of a turbojet engine

Abstract: Device for fixing a burner ring onto flameholder arms ( 14 ) in an afterburner combustion chamber of a turbojet engine, the burner ring being formed of ring sectors ( 12 ) placed more or less end to end and the ends of which are housed and guided between two circumferentially-directed parallel plates ( 34, 36 ) of the flameholder arms ( 14 ) and are immobilized between these plates ( 34, 36 ) by locking pieces ( 52 ) which are themselves held between the plates ( 34, 36 ) by immobilizing means ( 54, 56 ) engaged in aligned orifices ( 58, 60, 64 ) in the plates ( 34, 36 ) and in the locking pieces ( 52 ).

Large-eddy simulation of two-phase reacting flow in model combustor

Abstract: The gas-droplet two-phase reacting flow in a model combustor with the V-gutter flame holder is studied by an Eulerian-Lagrangian large-eddy simulation (LES) approach. The k-equation subgrid-scale model is used to simulate the subgrid eddy viscosity, and the eddy-break-up (EBU) combustion subgrid-scale model is used to determine the chemical reaction rate. A two-step turbulent combustion subgrid-scale model is employed for calculating carbon monoxide CO concentration, and the NO subgrid-scale pollutant formation model for the evaluation of the rate of NO formation. The heat flux model is applied to the prediction of radiant heat transfer. The gas phase is solved with the SIMPLE algorithm and a hybrid scheme in the staggered grid system. The liquid phase equations are solved in a Lagrangian frame in reference of the particle-source-in-cell (PSIC) algorithm. From simulation results, the exchange of mass, moment and energy between gas and particle fields for the reacting flow in the afterburner with a V-gutter flame holder can be obtained. By the comparison of experimental and simulation results, profile temperature and pollutant of the outlet are quite in agreement with experimental data. Results show that the LES approach for predicting the two-phase instantaneous reacting flow and pollutant emissions in the afterburner is feasible.

Body-fitted coordinate systems for large-eddy simulation of the model afterburner

Abstract: In this paper, the k-equation subgrid-scale model is used for the large-eddy simulation(LES) of turbulent chemically reacting flows in the model afterburner with the V-gutter flame holder. Two dimensional body-fitted grid is generated by using the zonal methods, the EBU combustion subgrid-scale model is employed to determine the chemical reaction rate, the heat flux model is applied to prediction of the heat flux, SIMPLE algorithm and hybrid scheme are used with the staggered grid system, wall function is applied to treating near wall region. Prom the results of the numerical simulation, the recirculation zone is found behind the V-gutter flame holder. The experiments are preformed in the combustion laboratory. The numerical results are well agreement with experimental measurements of temperature. The results show that the large-eddy simulation method by body-fitted grid may be used to investigate reacting flows and combustion process in practical combustors.

Method to control fuel delivery into afterburner

Abstract: FIELD: aircraft industry. ^ SUBSTANCE: invention relates to automatic control system of aircraft gas-turbine engines, particularly, to method of control of fuel delivery into afterburner of gas-turbine engine. According to proposed method including preliminary filling of afterburner manifold with fuel by signal to cut in afterburner manifold and change over of afterburner meter into preset position, conformity of current position of afterburner meter and flow rate of afterburner fuel is additionally set, and preliminary filling of afterburner manifold is done by shifting meter at preset speed to increase fuel flow rate at time determined by preliminarily set values of afterburner manifold volume, preset speed of movement of meter and minimum flow rate of afterburner fuel from moment of reception afterburner manifold cut-in signal at expiration of which afterburner meter is shifted at preset speed to position corresponding to minimum flow rate of afterburner fuel, after which afterburner meter is set into preset position. ^ EFFECT: improved dynamic characteristics of engine by reducing afterburner response time. ^ 2 cl, 1 dwg

Planar and Tubular Solid Oxide Fuel Cells - Comparison of Transient Process Behaviours

Abstract: This thesis focuses on three main areas within the field of SOFC/GT-technology:• Development of a dynamic SOFC/GT model• Model calibration and sensitivity study• Assessment of the dynamic properties of a SOFC/GT power plantThe SOFC/GT model developed in this thesis describes a pressurised tubular Siemens Westinghouse-type SOFC, which is integrated in a gas turbine cycle. The process further includes a plate-fin recuperator for stack air preheating, a prereformer, an anode exhaust gas recycling loop for steam/carbon-ratio control, an afterburner and a shell-tube heat exchanger for air preheating. The fuel cell tube, the recuperator and the shell-tube heat exchanger are spatially distributed models. The SOFC model is further thermally integrated with the prereformer. The compressor and turbine models are based on performance maps as a general representation of the characteristics. In addition, a shaft model which incorporates moment of inertia is included to account for gas turbine transients.The SOFC model is calibrated against experimentally obtained data from a single-cell experiment performed on a Siemens Westinghouse tubular SOFC. The agreement between the model and the experimental results is good. The sensitivity study revealed that the degree of prereforming is of great importance with respect to the axial temperature distribution of the fuel cell.Types of malfunctions are discussed prior to the dynamic behaviour study. The dynamic study of the SOFC/GT process is performed by simulating small and large load changes according to three different strategies;• Load change at constant mean fuel cell temperature• Load change at constant turbine inlet temperature• Load change at constant shaft speedOf these three strategies, the constant mean fuel cell temperature strategy appears to be the most rapid load change method. Furthermore, this strategy implies the lowest degree of thermal cycling, the smoothest fuel cell temperature distribution and the lowest current density at part-load. Thus, this strategy represents the overall lowest risk with respect to system malfunctions and degradation. In addition, the constant mean fuel cell temperature strategy facilitates high efficiency part-load operation. The constant turbine inlet temperature strategy proved to lead to unstable operation at low load, and thus it is considered to be the least adequate method for load change. For both the constant mean fuel cell temperature strategy and the constant TIT strategy, surge might be a problem for very large load reductions. The slowest response to load changes was found for the constant shaft speed strategy. Furthermore, this strategy leads to very low fuel cell temperatures at low loads. This in combination with a possible higher degradation rate makes the constant shaft speed strategy unsuited for large load variations. Nevertheless, operation at constant shaft speed may be facilitated by air bypass, VIGV or compressor blow off.

Device to feed air and fuel to burner ring in afterburner chamber

Abstract: PROBLEM TO BE SOLVED: To provide a method to solve a problem regarding an afterburner system for a turbojet in a simple, inexpensive, and effective manner. SOLUTION: A device to feed air and fuel to a burner ring in an afterburner chamber is provided with: a plurality of flame stabilizers radially extending from an outside casing to the surroundings of the axis of the afterburner chamber; a burner ring consisting of a ring sector mounted such that the one end is substantially attached to the other end by a flame stabilizer arm; and a means to feed air and fuel to the burner ring sector. The means is extended between the burner ring and the outside casing of the afterburner chamber situated at the inside of the flame stabilizer arm. COPYRIGHT: (C)2006,JPO&NCIPI

Device and method for providing ignition to a post-combustor for bypass gas turbine

Abstract: The method involves guiding a fraction of primary flow (10) in an ignition zone (34) of an afterburner in order to maintain the temperature in the zone at a value greater than value of secondary flow (20) in a manner to favor ignition of the afterburner. The primary flow is hot and the secondary flow is cool, where the fraction of primary flow is injected in an upstream part of the zone. An independent claim is also included for an afterburner device for a turbofan engine.