Showing papers on "Afterburner published in 2017"

Cooling design of an aero-engine fuel centrifugal pump at shut-off:

Abstract: Because of the problem of a high fuel temperature rise at shut-off, a conventional centrifugal pump could not be used as an aero-engine fuel pump for the afterburner fuel supply. In this study, a c...

On the Dominant Noise Components of Tactical Aircraft: Laboratory to Full Scale

Abstract: This paper investigates the dominant noise components of a full-scale high performance tactical aircraft The present study uses acoustic measurements of the exhaust jet from a single General Electric F414-400 turbofan engine installed in a Boeing F/A-18E Super Hornet aircraft operating from flight idle to maximum afterburner The full-scale measurements are to the ANSI S1275–2012 standard employing about 200 microphones By comparing measured noise spectra with those from hot supersonic jets observed in the laboratory, the dominant noise components specific to the F/A-18E aircraft at different operating power levels are identified At intermediate power, it is found that the dominant noise components of an F/A-18E aircraft are essentially the same as those of high temperature supersonic laboratory jets However, at military and afterburner powers, there are new dominant noise components Their characteristics are then documented and analyzed This is followed by an investigation of their origin and noise generation mechanisms

Integrated afterburner of supporting plate tail dual oil channels

Abstract: The invention provides an integrated afterburner of supporting plate tail dual oil channels. Fuel oil is supplied to the integrated afterburner through a hollow thrust augmentation inner cone, two supporting plates are installed on the two sides, close to the tail portion, of a whole flow supporting plate, and fuel oil channels are formed in the middles of the whole flow plate and the supporting plates on the two sides of the tail portion of the whole flow supporting plate correspondingly; and the fuel oil is sprayed out of the tail portion of the whole flow supporting plate and fuel oil spraying holes formed in the supporting plates on the two sides of the whole flow supporting plate. The integrated afterburner of the supporting plate tail dual oil channels has the advantages that by installing the hollow fuel oil channels of the thrust augmentation inner cone, the fuel oil in the thrust augmentation inner cone is preheated, and thus the fuel oil is subjected to pre-evaporation; by forming inclined-spraying fuel oil holes in the supporting plates on the two sides of the whole flow supporting plate, the fuel oil can reach the process of fuel oil primary atomization by hitting against the outer wall of the whole flow supporting plate; the pre-heated fuel oil is sprayed out of a spraying opening, and after hitting against the wall face, and the fuel oil basically is gas or a supercritical body; and viscidity is reduced, diffusivity is reinforced, the flowing ability is greatly improved, thus the fuel oil can be more evenly mixed with surrounding air, and burning efficiency of the afterburner is improved.

Heat-power coordinated supply system and method integrating fuel cell and carbon dioxide circulation

Abstract: The invention provides a heat-power coordinated supply system integrating a fuel cell and carbon dioxide circulation. The heat-power coordinated supply system comprises the solid oxide fuel cell and a power converter. An air preheater and a mixer are connected with the cathode and the anode of the solid oxide fuel cell correspondingly. A fuel preheater and a water supply preheater are connected with the mixer. Waste gas of the solid oxide fuel cell is connected with an afterburner. Part of heat of waste gas exhausted by the afterburner is used for supplying heat to thermal loads, part of heat of the waste gas exhausted by the afterburner is used for supplying heat to the air preheater, the fuel preheater and the water supply preheater, and another part of heat of the waste gas exhausted by the afterburner is used for being transferred to a carbon dioxide working medium of a supercritical carbon dioxide circulation loop, so that power is generated through supercritical carbon dioxide circulation. The invention further provides a heat-power coordinated supply method integrating the fuel cell and carbon dioxide circulation. According to the heat-power coordinated supply system and method, advantages of the solid oxide fuel cell and supercritical carbon dioxide circulation are combined, heat-power coordinated supply is achieved, the system is simple, the structure is compact, the energy utilization rate is high, cost is low, and the system and method are suitable for distributed energy sources.

An integrated afterburner with supporting plate jet flow structures

Abstract: The invention provides an integrated afterburner with support plate jet flow structures. Support plate jet flow structures are added to the two sides of a fairing support plate flame stabilizer of an integrated afterburner. Compared with the prior art, the fuel jet mode is changed; the fuel jet mode is changed to fuel jet at the two sides and the tail of a fairing support plate: fuel jet at the two sides of the support plate are atomized secondarily through collision and breaking of support plates on the two sides; fuel is jet at the central position of the tail of the fairing support plate flame stabilizer, and the atomizing and evaporating effects of fuel are improved by the action of shearing force of high temperature air flow. With the cooperative action of the two fuel jet modes, the combustion efficiency of the afterburner is greatly improved. Moreover, with the support plates added to the two sides of the fairing support plate flame stabilizer, a backflow area with a certain range can be formed, so that high temperature air flow can be reduced and the combustion stability of the afterburner can be improved. A thrust augmentation inner cone transmits much heat to low temperature fuel, so that the temperature of the thrust augmentation inner cone itself is reduced and the infrared stealth performance is improved.

Operation-Related Failures of Aircraft Turbine Engines

Abstract: The paper is intended to draw attention to the most frequent reasons that lead to initiation of failures to components of flame tubes incorporated into combustion chambers and turbine units during the operation lifetime of aircraft turbine engines. These failures are illustrated by means of numerous examples that disclose gradual deterioration of components and subassemblies detected on their surfaces during endoscopic inspections carried out on various types of components and subassemblies of aircraft engines. The mentioned deterioration process affecting blade surfaces of turbine blade rims is analyzed on the basis of continuous monitoring that has been carried out to date. Attention is also paid to the way how aircraft engines have been so far and keep being evaluated whether or not they suit for further operation with consideration to specific features of service.

Integrated afterburner with double oil-way injection and strut jet flows

Abstract: The invention provides an integrated afterburner with double oil-way injection and strut jet flows. In the integrated afterburner, a double oil-way injection mode. Fuel oil is injected at two sides, the central position of the tail and the central position of an afterburning inner core of a fairing strut flame holder. Meanwhile, two sides of the fairing strut flame holder are additionally provided with strut jet flow structures. The integrated afterburner with double oil-way injection and strut jet flows has following advantages: a part of fuel oil enters an oil channel of the fairing strut flame holder through an oil cavity of the afterburning inner core; fuel oil is injected out from a direct-injection type or an eccentric nozzle on two sides or the central position of the tail; the other part of fuel oil is injected to the integrated afterburner through the central position of the afterburning inner core; due to the interplay between double oil ways, fuel oil is better mixed with air; two sides of the fairing strut flame holder are additionally provided with strut structures; fuel oil is injected on two sides of the fairing strut flame holder; fuel oil collides with the inside of a strut so that the atomization-vaporization effect of fuel oil in the afterburner is effectively improved; meanwhile, struts on two sides help decrease airflow velocity and stabilize airflow; combination effect of these aspects helps effectively increase burning efficiency and burning stability of the afterburner; and due to the fact that a lot of heat of the afterburning inner core is transferred to low-temperature fuel oil, the temperature of the afterburning inner core decreases and infrared stealth performance is improved.

Afterburner annular flame tube structure with cyclones

Abstract: The invention provides an afterburner annular flame tube structure with cyclones According to the structure, the six cyclones are additionally mounted in the middle of an afterburner, a wide-range recirculation zone can be generated in the afterburner, and therefore the air flow speed can be reduced to the largest degree, and stable burning of the afterburner can be guaranteed Meanwhile, an expansion air inlet segment is arranged at the tail of an afterburning tail cone, expansion air inlet holes are formed in the centers of the cyclones, the internal air flow flowing speed can be greatly reduced after afterburning through multiple ways, and space is provided for stable burning After air flow passes through the cyclones, a shearing function can be generated on fuel oil, fuel oil atomization is more thorough, and therefore burning can be more sufficient After the air flow passes through the expansion air inlet segment, part of the air flow passes through a channel between the inner wall and the outer wall of the afterburner, the wall temperature of the afterburner can be effectively reduced, and the infrared stealth performance of an airplane can be improved

Gas-turbine engine with afterburner operation mode and its actualization system

Abstract: FIELD: engine devices and pumps.SUBSTANCE: to create the set value of distributing valve position, a regulator with proportional-integral control law and with variable gain factor, depending on the specific speed of turbocharger rotor, is used. On the modes of starting the afterburner, regulator gain factor is increased and value, accumulated by integrator, is reset. Control system for gas turbine engine with afterburner is also described.EFFECT: improving the quality of control of the gas turbine engine with afterburner by increasing the speed of system by switching the structure of regulator and changing regulator gain factor depending on operating mode of gas turbine engine.2 cl, 2 dwg

Double-oil-way jet integrated afterburner

Abstract: The invention provides a double-oil-way jet integrated afterburner. A double-oil-way jet mode is adopted in the integrated afterburner. Jet positions for fuel oil jetting are the central position of the tail of a fairing spoke flameholder and the central position of a thrust augmentation inner cone. Compared with the prior art, the fuel oil jetting mode is changed, and as for an outer oil way, the jetted fuel oil is mixed with high-temperature mixed gas, and the atomizing effect is improved under the effect of the shear force of the high-temperature mixed gas; and as for a central oil way, since the thrust augmentation inner cone enables a wide low-speed backflow area to be formed behind the afterburner, the jetted fuel oil of the part is fully mixed with high-temperature mixed gas in the low-speed area, and the premixing effect is enhanced. Combustion is jointly conducted through the two oil ways in the afterburner, so that the combustion efficiency of the afterburner is improved, and the combustion stability is good. Meanwhile, the fuel oil can effectively decrease the temperature of the thrust augmentation inner cone to improve the infrared stealth performance of an engine.

Afterburner double-layer rectification supporting plates

Abstract: The invention provides an air inlet structure of afterburner double-layer rectification supporting plates. By means of the air inlet structure, air flow can be decelerated twice, the area of low-speed air flow can be effectively increased in an afterburner, and accordingly stable operation of flames in the afterburner can be ensured. The two layers of rectification supporting plates are arranged at an inlet of the afterburner and on the tail portion of a thrust augmentation caudal vertebra respectively, an inner sleeve arranged on the tail portion of the thrust augmentation caudal vertebra divides the air flow into an inner part and an outer part, outer air is used for combustion compensation and cooling, inner air is used for primary combustion, and accordingly the air flow is fully used. Meanwhile, a gradually-expanded inlet of the inner sleeve can further decelerate the air flow to guarantee stable and sufficient combustion of an inner air primary combustion area.

Twin-stage aero-engine strut used for integral afterburner

Abstract: The invention provides a twin-stage aero-engine strut used for an integral afterburner The range of a recirculation zone can be effectively enlarged, the swirling intensity of the recirculation zone is increased, the fuel oil atomizing and mixing effects are improved, and thus the burning efficiency and burning stability are improved A backward turning-direction combined twin-stage aero-engine strut flame holder is adopted, on the one hand, the turning directions of flue gas flowing through the twin-stage aero-engine strut are opposite, a shearing function is achieved on oil films, and crushing and atomizing of fuel oil are accelerated; on the other hand, the stable recirculation zone with the certain fuel gas recirculation volume and the proper size is formed on the downstream part of the twin-stage aero-engine strut, mixing of burnt high-temperature air and outside air is promoted, and stable burning is facilitated The twin-stage aero-engine strut has the advantages that the aero-engine strut flame holder adopts the twin-stage backward turning-direction combination structure design on the original basis of the integral afterburner, the mixing degree of the fuel oil and the air can be effectively increased, the ignition ability under the oil rich condition and the high altitude condition is improved, and the good burning stability and burning efficiency are ensured

Method of increasing combustion efficiency of solid and liquid rocket engine in afterburner

Abstract: The invention discloses a method of increasing combustion efficiency of a solid and liquid rocket engine in an afterburner. A secondary jet channel is formed in the circumferential direction of a housing of the afterburner and a secondary injection welding head communicating with the secondary injection channel is mounted. The axis of the secondary injection channel is designed to be vertical to the axial direction of the afterburner, and meanwhile, the pore diameter of the injection end of the secondary injection channel is designed at 7mm and the secondary injection flow ratio is 0.75. The method disclosed by the invention can effectively increase disturbance of the afterburner, so that an antioxidant and a fuel are fully mixed and a combustion reaction is performed near the optimum oxygen combustion ratio, and finally, the solid and liquid rocket engine achieves the highest combustion efficiency.

Integrated fuel cell and carbon dioxide cycle's heat and electricity co -generation system

Abstract: The utility model provides an integrated fuel cell and carbon dioxide cycle's heat and electricity co -generation system, including solid oxide fuel cell and electric power converter, air heater, blender are extremely continuous with solid oxide fuel cell's yin, yang respectively, preheating of fuel ware, continuous for water preheater and blender, and the afterburner is connected to solid oxide fuel cell's waste gas, the partial heat of afterburner combustion gas is used for for the heating load heat supply, and partial heat is used for for air heater, preheating of fuel ware, gives the water preheater heat supply, and another part heat is used for transfering super supercritical carbon dioxide circulation circuit's carbon dioxide working medium, through super supercritical carbon dioxide circulation electricity generation. The utility model discloses combining solid oxide fuel cell and super supercritical carbon dioxide endless advantage, realizing the cogeneration, overall generating efficiency is high, and the system is simple, compact structure, and energy utilization is high, and is reliably good, with low costs, is applicable to the distributed energy.

Turboram air-jet engine

Abstract: FIELD: engines and pumps.SUBSTANCE: turboram air-jet engine comprises a turbojet engine with an afterburner and a jet nozzle (ATE), gas temperature measurement system behind the main combustion chamber of the turbojet engine, as well as direct-flow circuit positioned coaxially to the turbojet engine. The direct-flow circuit is connected to the air intake of the aircraft via the shut-off device, comprising a diffuser, a jet nozzle and a combustion chamber. The internal channel of the turbojet engine afterburner is connected to the internal cavity of the direct-flow circuit combustion chamber via the radial flame stabilizers of V-shaped profile for the supply of combustion products from the afterburner to the direct-flow circuit combustion chamber channel.EFFECT: higher efficiency of the aircraft ducted jet engine intended to fly in a wide range of flight velocity from subsonic to Mach equal to 4 or higher.6 cl, 1 dwg

Afterburner outlet ultra-high temperature measurement sensing part

Abstract: The invention relates to an afterburner outlet ultra-high temperature measurement sensing part, which belongs to direct measurement on the afterburner outlet temperature in a full afterburner state of an afterburner aeroengine. The ultra-high temperature measurement sensing part comprises a dual platinum-rhodium thermocouple (1), a tail packaging lug (2), a fixed clamping piece (3), a high-temperature composite skeleton (4), a high temperature-resisting adhesive (5), a high-temperature alloy pipe (6), a tungsten pipe (7), a corundum sleeve (8), a measurement channel (9), a thermocouple measurement point (10) and a thermocouple arrangement channel (11). The high-temperature composite material is firstly applied to design of the ultra-high temperature measurement sensing part, the product is portable and can be maintained, the mounting is convenient, direct measurement on the afterburner outlet temperature in the full afterburner state of the engine can be realized, the technical problem of direct measurement on the afterburner outlet temperature can be solved, and technical support is provided for technical development of design of the aeroengine.

Control method of aircraft jet turbine engine

Abstract: FIELD: engine devices and pumps.SUBSTANCE: expected technical result is achieved by the fact that in the known method of controlling the aircraft jet turbine engine, which includes maintaining the preset rotational speeds and gas temperature behind the turbine by means of a regulator, depending on the air inlet temperature, according to the present invention, the regular regulation program conducts its tests in full afterburner mode (engine operation mode with maximum fuel consumption through afterburner collectors) with thrust measurement, then the regulator is adjusted to increase the rotors rotation speed and the gas temperature behind the turbine, not exceeding the maximum permissible values for this type of engine, until a predetermined thrust gain is reached, and regulator values are fixed, and if the predetermined thrust gain is not attained, the values of the regulator are also fixed for the maximum thrust gain, then, on the basis of the obtained data, an additional regulation program for rotors rotation frequencies and the gases temperature behind the turbine is made, it is installed into the engine regulator, then during engine operation, if it is necessary to increase the thrust in excess of the nominal modes, involve an additional program for regulating the rotors rotation frequencies and the gases temperature behind the turbine.EFFECT: possibility of increasing the thrust beyond the normal modes during the engine operation.2 tbl, 2 ex

Nozzles for Airbreathing Engines

Abstract: Nozzle characteristics and the simplifying assumptions used in their analysis are introduced. The effects of friction and heat release are treated and the properties of isentropic flow in nozzles in which only the cross-sectional area changes are covered in detail. Calculation of the mass flow in such nozzles and the conditions for maximum mass flow are presented. Nozzle operation as controlled by the nozzle pressure ratio, including the presence of shocks, is discussed. Two-dimensional considerations in nozzle flows and illustrative cases of overexpanded nozzles and underexpanded nozzles are presented. The use of afterburning for increased thrust is covered and different nozzle configurations for subsonic and supersonic flight are discussed. Thrust-vectoring nozzles and practical nozzle losses are considered.

Camera of mixing afterburner

Abstract: FIELD: power industry.SUBSTANCE: afterburner mixing chamber is proposed. It includes an outer annular body, a kok-drainer and a shell on which are located radially directed pylon ducts fixed on the opposite side on a common divider that divides the inner contour into the central and vernal parts and also provides air supply of the external circuit, through the pylon cavity, directly to the central part of the internal circuit, thereby ensuring an even distribution of oxygen along the radius of the mixing chamber, one native temperature field at the outlet from the mixing chamber and effective cooling of the nozzle and afterburner stabiliser assemblies.EFFECT: invention makes it possible to create conditions in which a homogeneous temperature field at the exit from the mixing chamber was provided, a uniform distribution of oxygen along the radius of the afterburner, and effective cooling of the nozzle and stabiliser assemblies.9 dwg

Afterburner overall excess air coefficient design method

Abstract: The invention provides an afterburner overall excess air coefficient design method. The method comprises the following steps of: firstly defining a stress application stability parameter S according to an incoming flow parameter at an inlet of an afterburner and a groove width of a flameholder; drawing a relationship curve of the stability parameter S and an afterburner overall excess air coefficient ; and finally determining a stability parameter S of each state point according to a height H and a Mach number M of each state in a flight envelope, and connecting the points, the stability parameters of which are the same in the aspect of value, to obtain an equal S line. According to the design method provided by the invention, the stress application stability parameter S is adopted to correct the afterburner overall excess air coefficient ; and compared with the manner of correction the afterburner overall excess air coefficient by adoption of an engine inlet total temperature T1 in the prior art, the design method has the advantages of sufficiently giving full play to the potentials of engines and reducing the risk of instable combustion.

Method of fuel heating reduction in the fuel system of a gas turbine engine in deep choke modes

Abstract: FIELD: engines and pumps.SUBSTANCE: invention can be used in their fuel supply systems to reduce the heating of fuel delivered to the injectors of the main and/or afterburner combustion chambers in deep choke modes. Reduced fuel heating in the gas turbine engine fuel system is performed by controlling the parameters of the centrifugal pump of the fuel system, which is used as the number of impeller speed and position of the maximum efficiency of the pump on the pump pressure characteristics flow axis, wherein the transition of the pump to the deep throttling modes to reduce fuel preheating fuel discharge characteristic is changed from the impeller, which is carried out by shifting the maximum efficiency of the pump to the minimum fuel consumption field, leaving a constant number of revolutions of the pump impeller.EFFECT: invention makes it possible to increase the efficiency of fuel heating reduction in the fuel system of a GTE in deep choke modes.6 dwg

Wireless communication unmanned plane-based engine device

Abstract: The invention discloses a wireless communication unmanned plane-based engine device. The device comprises a gas compressor, a fuel oil tube, a burning chamber, a turbine, a pre-burning chamber, an afterburner and a jet tube which are sequentially connected, the afterburner and the jet tube are connected with rotating joints, rotating joints are connected with a controller and communicate with an unmanned plane control host, the rotating joints can rotate to any direction with an engine center shaft as a center, the rotating angle is 0-90 DEG, the pre-burning chamber is connected between the pre-burning chamber and the afterburner, and a pressure diffuser is connected between the pre-burning chamber and the turbine. The device is mainly characterized in that the rotating joints directly change the positions of the jet tube to control a direction, the host emits an instruction to the controller in order to rotate the direction of the jet tube, the jet tube position has faster response than a wing position in direction control to further improve the direction rotation, and a command code decoder in the controller is used for decoding the command code of the instruction to generate a corresponding control level in order to complete instruction analysis.

Fuel feed unit to the bypass turbojet engine afterburner

Abstract: FIELD: engines and pumps.SUBSTANCE: fuel feed unit to the afterburner of the bypass turbojet engine contains a fuel manifolds with the fuel feed fittings. The fuel manifolds are formed all-in-one with the housing, which by means of fixing elements is connected to the upper diffuser cowl and with the upper ring flame stabiliser fastener. At that the mentioned housing in the cross-section plane has a rectangular shape, and the fuel manifolds are made in the form of a ring.EFFECT: reduction of the full pressure loss in the afterburner flow section, thrust augmentation and reduction of coke formation in the fuel manifolds.3 cl, 3 dwg

Four aeronautic/astronautic turbofan engines

Abstract: Four aeronautic/astronautic turbofan engines, which are respectively a turbofan engine comprising an air inlet for introduction of oxygen-enriched air, a turbofan engine comprising two oxygen-enriched air inlets, a turbofan engine free of oxygen-enriched air, and a turbofan engine comprising an afterburner for introduction of oxygen-enriched air. Regarding the limited working altitude of an aeronautic turbofan engine, by providing an air-inlet oxygen-enriched air injecting assembly (1) and continuing to use the main structure of an existing aeronautic turbofan engine, a slightly modified main structure (2) is formed; by utilizing two types of regenerative cooling afterburners (3, 4, 5) having acoustic cavities and baffle plates, the aeronautic turbofan engine can be changed into an aeronautic turbofan engine capable of working within various altitude ranges. The four aeronautic/astronautic turbofan engines belong to the same series of aeronautic/astronautic integrated engines which can make full use of oxygen in the air for combustion, and can propel an aircraft to reach a flight altitude of 20-50 km and a flight speed of 2-5 Mach, or even more. These turbofan engines are applicable to a variety of aeronautic/astronautic integrated vehicles capable of being used repeatedly.

Aircraft gas turbine engine combustion chamber

Abstract: FIELD: power industry.SUBSTANCE: aircraft gas turbine engine combustion chamber, where the combination of the main combustion chamber and afterburner into a single chamber is realized. The combustion chamber has two combustion areas: the main and the afterburner. The main area is permanent, the afterburner is for chamber working at the augmented rating. The positive result is due to the fact, that the combustion conditions in the main combustion chamber afterburner area of at the same values of the total air excess ratio is objectively better, than in the afterburners of similar gas turbine engines.EFFECT: invention allows to expand the operating modes range of the main combustion chambers according to the total air excess ratio.6 cl, 3 dwg

Rotational flow inner cone integrated afterburner

Abstract: The invention provides a rotational flow inner cone integrated afterburner. A hydrocyclone is arranged on a stress application inner cone, led-in cooling air forms a recirculation zone at the downstream through the hydrocyclone distributed on the stress application inner cone, formation of mixing gas is accelerated, the burning process is strengthened, a flame is stabilized, and meanwhile, the outlet temperature distribution is improved. A similar two-stage hydrocyclone device is formed through the hydrocyclone on the stress application inner cone and an external rectification support plate flame stabilizer, fuel pulverization and fuel space distribution uniformity are improved, burning is more sufficient, the total length of the afterburner is further decreased, the structure weight is decreased, the resistance loss is reduced, and the engine thrust-weight ratio has a very great promotion space.

Double-rotor gas turbine engine

Abstract: FIELD: engines.SUBSTANCE: invention relates to gas turbine engines, specifically to oil systems, their supercharge cavities and oil breathing devices. Double-rotor gas turbine engine is equipped with system of series-connected to each other by means of additional air ducts pre-oil cavities of low pressure compressor and pre-oil cavity of high-pressure compressor, simultaneously communicated with pre-oil cavity of turbine, ejector comprising ejected cavity, an ejection cavity and mixing chamber, pre-oil cavity of turbine is interconnected on one side, via air duct with breathing valve, and on other side, with inlet of ejected cavity of ejector whose output is connected to input of mixing chamber, wherein ejecting cavity is connected by its inlet to power supply, and by output to input of mixing chamber, mixing chamber outlet is communicated with inlet cavity of afterburner. Also, power supply can be secondary zone of combustion chamber or intermediate stage of high pressure compressor.EFFECT: technical result of invention is avoiding emissions into atmosphere on long-lasting cruising modes and maintaining optimum differential on movable seals of engine oil system at maximum and afterburner modes of engine operation.3 cl, 1 dwg

Method for controlling aircraft turbojet engine with afterburner combustion

Abstract: FIELD: airpower.SUBSTANCE: in the method for controlling the aircraft turbojet engine with the afterburner combustion, the engine is tested in the forced mode with the given altitude and the Mach number, for which the fuel flow through the fuel manifolds of the afterburner changes by the n-th number of times and forms the n-th number of programs for maintaining fuel consumption through the afterburner fuel manifolds. Then, for each program, the expansion ratio on the turbine is changed to achieve a thrust value corresponding to the specified altitude and the Mach number, and the total fuel consumption is measured. Further, the results are compared, the lowest total fuel consumption is extracted, then the program with the lowest total fuel consumption is used for the flight of the aircraft in the forced mode with the given altitude and the Mach number.EFFECT: invention allows to reduce fuel consumption on the forced mode of the engine operation.2 tbl