Mixer of afterburner of double-flow turbojet engine

FIELD: mechanical engineering; turbojet engines.

SUBSTANCE: mixer of afterburner of turbojet engine relaters to members of afterburners making it possible to increase margin of vibratory combustion. Mixer 4 distributes air of outer loop and behind-the-turbine gas which pass through pockets 6 with lobes 5 and mix on section between end face edges 7 of mixer 4 and flame stabilizers 3. Fuel is delivered to gas through manifolds 2. Fuel-air mixture burn out behind flame stabilizers 3. Each portion of fuel from manifold 2 gets into air flow, each element of which has its momentum and direction. Thanks to it each portion of fuel from manifolds 2 has its own time for preparation to combustion and its own burnout time, so afterburner of double-flow turbojet engine has low tendency to vibratory combustion.

EFFECT: increased margin of vibratory combustion.

 

The invention relates to aviadvigatelestroenii, namely, the design elements of the afterburning chambers turbofan engines (turbofan).

Known mixer afterburner turbofan, containing corrugations forming alternating channels of internal and external contours, the output edges of which are at an angle to the longitudinal axis of the mixer (patent Germany N 2650373, MKI F 02 To 3/10).

The disadvantage of this device is that the passage of high-speed air flow external circuit, having a low temperature on the periphery of the chamber, leads to disruption of stabilization of the flame in this area, especially at high flight speeds and, as a consequence, the emergence of it vibrating burning.

Of the known devices is the closest in technical essence to the present invention is a turbofan mixer containing corrugations forming alternating channels of internal and external contours, the output edges through which one is inclined to the longitudinal axis of the mixer at different angles (USSR author's certificate N 1813906, MKI F 02 To 3/10, Appl. 1983). This device though and extends the range of stability with respect to vibrocoring work afterburners, but fibrogene still occurs at the maximum speed of flight.

The objective of the invention is to improve stability margin to shaking is ogrenew.

This task is achieved by the fact that in the mixer afterburner turbofan engine, containing corrugations forming alternating channels of internal and external contours, the output edges of which are inclined to the longitudinal axis of the mixer at different angles, the angle of each successive edges of the corrugations differs from the previous one on the corner in 4-90 degree. The proposed location of the output edges of all of the corrugation leads to the fact that at each point of the chamber, where the mixture of fuel and air due to the difference in the amount of motion and direction of the jet of air each portion of the combustible mixture is prepared for combustion and burns on its own, will brissim only this portion of the law. Therefore, each portion of the mixture has its own individual preparation for combustion and individual time burnout. Afterburner chamber turbofan engines with such an organization supplying air to the front of the device is less prone to vibrocoring compared to a camera, in which the mixer has only two output channels from an external circuit.

Figure 1 shows a longitudinal section of the front element of the device afterburner turbofan;

figure 2 shows the rear view of the motor on the mixer;

figure 3 shows the dependence function of burnup ϕ(t) servings fuel flowing to different streams of air from BP is like t where τ1- preparation portion of fuel to burn, τ2the time of burning of portions of the fuel mixture.

The device includes a housing 1, a fuel reservoir 2, stabilizers, flame 3 and the mixer 4 with petals 5 for supplying a gas of an internal contour pockets and 6 for the supply of air. End edges 7 of the mixer 4 is performed at different angles to the axis of the engine β1that β2that β3that β4... and so on, and

β122334...=4°-19°, 41°-90°

The device operates as follows. Mixer 4 distributes the air to the outer contour and Saturninus gas that pass through the pockets 6 and petals 5, are mixed in the area between the end edges of the mixer 4 and stabilizers flame 3. In the gas flow is supplied fuel through the reservoir 2. An air-fuel mixture is burned with the flame stabilizers 3. Execution end edges 7 of the mixer 4 different angles leads to the fact that each portion of fuel from reservoir 2 is adjudged to be in an air stream, each element of which has its own momentum and its direction of motion. Due to this, each portion of the fuel from the reservoir 2 has its own preparation for combustion and their individual time of burnout. The nature of you is orania these portions is shown in figure 3 - positions a, b, C, d and so on. Due to the fact that each portion of the combustible mixture has its own character preparation for combustion and burnout, afterburning chamber turbofan engines, which includes the proposed mixer, less prone to vibrocoring than the camera, in which the mixer has only two output channels from an external circuit.

The invention improves the reliability of operation of afterburners and engine in General.

Mixer afterburner turbofan engine, containing corrugations forming alternating channels of internal and external contours, the output edges of which are inclined to the longitudinal axis of the mixer at different angles, wherein the angle of each successive edges of the corrugations differs from the previous one on the corner of 4°-19°, 41°-90°.



 

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The invention relates to aircraft engine industry, namely to design afterburners GTE

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