Gas-turbine engine afterburner

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed afterburner of gas-turbine engine contains prechamber and ring-type flame stabilizer installed in housing. Stabilizer is arranged coaxially relative to vibration absorber made in form perforated fairing. Fairing has two perforated sections. One section is located at outlet of fairing at a distance not exceeding 40% of length of fairing along its axis. Second section is provided with sleeveless perforation in beginning before flame stabilizer and is located at a distance from end of fairing not exceeding 50-59.9% of its length along axis. Fairing can be provided additionally with rim. Holes can be made in fairing and rim connected to fairing forming section with sleeveless perforation.

EFFECT: optimization of operation of afterburner owing to provision of frequency characteristics of oscillation process in inner spaces of afterburner and fairing and thus damping excess pressure fluctuations and velocity of gas.

4 cl, 3 dwg

 

The invention relates to aircraft engine, in particular to the afterburning chambers.

Known afterburning chamber of a gas turbine engine containing installed in the housing of the front device with a ring-shaped flame stabilizer and vibration-screen TV mounted on the body [1].

However, this afterburner camera has a lot of weight due to vibration of the screen, which is a cylindrical perforated shell made from a sheet of heat-resistant material, which is concentric to the outer walls of the afterburner.

Also known afterburning chamber of a gas turbine engine containing within the enclosure of the front device and the annular flame stabilizer located coaxially vibration absorber made in the form of fairing with perforations therein, the perforations on the fairing is made in two sections, one of which is arranged at the output of the fairing, and the perforation at the beginning of the fairing is made at a distance of 60-70% of its length along the axis from the end of the fairing and is provided with a cylindrical bushing [2].

However, in the known solution of one of the sections of the perforation at a distance of 60-70% of its length along the axis from the end of the fairing and the use of cylindrical bushings with channels of diameter d relative to the Bo is isoi length L=(1,25 0,5...) d protruding into the inner cavity of the fairing (as indicated on figure 1 and figure 2 above inventions), leads to the formation of eddy currents in the walls of the sleeves and to decrease the actual flow area of the channels in the sleeve, which will lead to the decrease in the gas flow through the sleeve.

The applicant theoretically and experimentally established that in order to ensure passage into the internal cavity of the fairing, the amount of gas required to ensure the health of the engine and the intensification of damping of the pressure and velocity of gas in the oscillatory process, you must change the location of one of the sites of perforation and to increase the coefficient of discharge and, consequently, to increase the area of the holes in the perforation and the area of the channels in the sleeve.

The technical result, which is aimed invention are optimization afterburners, by providing the necessary frequency characteristics of the vibrating process in internal cavities afterburners and fairing and thereby suppress the excessive pressure fluctuations and velocity of the gas.

This task is solved in that in the afterburner of a gas turbine engine containing within the enclosure of the front device and the annular flame stabilizer located coaxially vibration is th absorber, made in the form of fairing with perforations therein, the perforations on the fairing is made in two sections, one of which is arranged at the output of the fairing, and the second section is made with besuconas perforation in the beginning before the stabilizer is spaced from the end of the fairing at 50-59,9% of its length along the axis, with the first section of the perforation is made at the output of the fairing at a distance of not more than 40% of the length of the fairing on its axis.

However, in some cases, for example, in the case of small thickness of the fairing increase the area of the holes in the perforation will reduce stiffness and reliability of the fairing and afterburners in General.

Therefore, an additional technical result is also an increase in the rigidity and structural strength.

For this purpose, the fairing may further comprise a Hoop, with the fairing and attached to the Hoop can be made holes that make up the plot with besuconas perforation.

This fairing can be at least one shell and a bottom, and the first area of the perforations may be made in one of the shells in the bottom.

New here is that the second section is made with besuconas perforation in the beginning before the stabilizer is spaced from the end of the fairing at 50-59,9% of its length along the axis, and the first section of the perforation is made at the outlet MBT is katala at a distance of not more than 40% of the length of the fairing on its axis. This fairing may further comprise a Hoop, with the fairing and attached to the Hoop can be made holes that make up the plot with besuconas perforation.

This fairing can be at least one shell and a bottom, and the first area of the perforations may be made in one of the shells in the bottom.

The second plot with besuconas perforation in the beginning before the stabilizer is spaced from the end of the fairing at 50-59,9% of its length along the axis, and the execution of the first section of the perforation at the output of the fairing at a distance of not more than 40% of the length of the fairing on its axis to provide the required frequency response of the oscillatory process in internal cavities afterburners and fairing, and the use of Hoop attached to the fairing, made with education in the fairing holes, forming a perforation in the second section, provides high rigidity and structural strength.

This embodiment of the sites allows you to optimize the afterburners by providing the necessary frequency characteristics of the vibrating process in internal cavities afterburners and fairing and thereby suppress the excessive pressure fluctuations and velocity of the gas, and the use of Hoop attached to the fairing, made with the education in the fairing holes, forming a perforation in the second section, allows to increase the rigidity and structural strength.

Figure 1 shows the longitudinal section of the afterburner.

Figure 2 presents the node I in an enlarged scale.

Figure 3 presents the node II in an enlarged scale.

Afterburning chamber of the gas turbine engine contains installed in the front housing 1 device 2 and the annular flame stabilizer 3. The annular flame stabilizer 3 is coaxially vibration absorber made in the form of fairing with 4 perforations (5, 6) on it. Perforation (5, 6) on the fairing 4 made in the form of two sections. One plot is made at the output of the fairing 4 at a distance of not more than 40% of the length of the fairing on its axis. The second section is made with besuconas perforation in the beginning before the flame stabilizer 3, spaced from the end of the fairing 4 50-59,9% of its length along the axis.

This fairing may further comprise a Hoop 7, and the fairing 4 and attached to the Hoop 7 holes, forming a plot with besuconas perforation.

This fairing can be at least one shell (8, 9) and the bottom 10, and the first area of the perforations may be made in one of the shells 8 and in the bottom 10.

When working afterburners is the burnup of the fuel-air mixture for stabilizatio the Ohm flame 3. Upon receipt of the mode of vibration of the combustion in the afterburner arise periodic fluctuations in pressure and gas velocity. Acoustic vibrations cause gas gas oscillations in the perforation holes 5 and 6 of the nacelle 4. The punched deflector 4 is the effect on the oscillations of a gas in the afterburner as a resonant absorber (Helmholtz resonator).

The second plot with besuconas perforation in the beginning before the stabilizer is spaced from the end of the fairing at 50-59,9% of its length along the axis, and the execution of the first section of the perforation at the output of the fairing at a distance of not more than 40% of the length of the fairing on its axis to provide the required frequency response of the oscillatory process in internal cavities afterburners and fairing, and the use of Hoop attached to the fairing, made with education in the fairing holes, forming a perforation in the second section, provides high rigidity and structural strength.

The applicant determined that the execution of the fairing perforation at the site in the beginning before the stabilizer is spaced from the end of the fairing 60% or more of its length along the axis, or run it at a distance of less than 50% of its length along the axis leads to a decrease in the intensity of damping pressure and gas velocity not less than 5%, which means the flax worsen the performance of the engine during its operation.

Here is an example of a specific implementation of the fairing.

Example: Consider the afterburning chamber of the gas turbine engine fairing, the length of which is L=716 mm

The distance from the end of the fairing to the stabilizer chosen equal to 400 mm, which is 55.9 percent. This distance is in the range of 50-59,9%.

The first section of the perforation is made at the output of the fairing chosen equal to 215 mm, which is 30%. This distance does not exceed 40% of the length of the fairing on its axis.

Experiments have shown that the above implementation of the fairing allows you to optimize the afterburners by providing the necessary frequency characteristics of the vibrating process in internal cavities afterburners and fairing and thereby extinguish the excess fluctuations of the pressure and velocity of gas, as well as to increase the rigidity and reliability of a design.

Sources of information

1. Skubachevskii G.S. "Aircraft gas turbine engines. Design and calculation details". M: "engineering", 1969, s).

2. Patent document EN 2117806, F 02 K 3/10, publ. 20.08.1998,

1. Afterburning chamber of a gas turbine engine containing within the enclosure of the front device and the annular flame stabilizer located coaxially vibration absorber made in the form of fairing with perforation on it, while airforce on the fairing is made in the form of two sections, one of which is executed on the output of the fairing, characterized in that the second section is made with besuconas perforation in the beginning before the stabilizer is spaced from the end of the fairing at 50-59,9% of its length along the axis, and the first section of the perforation is made at the output of the fairing at a distance of not more than 40% of the length of the fairing on its axis.

2. Afterburning chamber of the gas turbine engine according to claim 1, characterized in that the fairing further comprises a Hoop, with the fairing and attached to the Hoop with holes that make up the plot with besuconas perforation.

3. Afterburning chamber of the gas turbine engine according to claim 1, wherein the fairing comprises at least one shell and a bottom.

4. Afterburning chamber of the gas turbine engine according to claim 3, characterized in that the first area of the perforation is made in one of the shells in the bottom.



 

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