By-pass engine afterburner

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

 

The invention relates to aircraft engine industry, in particular, to the afterburning chambers bypass gas turbine engines.

Known afterburner chamber bypass gas turbine engine described in U.S. patent No. 3.485.045 "Afterburner chamber bypass gas turbine engine", MCL: F02C 3/00, from 23.10.69. This camera contains Saturninus and fan input channels, an annular split ring between them, building with heat-shielding screen, the collectors of the fuel injector and a flame stabilizer located in the housing cavity. The area of the body cavity to the place of installation of the collectors and the stabilizer is a mixing cone. The purpose of the diffuser is to provide a partial mixing of the flow of relatively cold air from the fan channel with a stream of high temperature gas from securinega channel with the aim of improving the combustion characteristics. In addition, the diffuser allows you to brake blending streams to reduce losses of total pressure at the flow around them stabilizer flame.

The disadvantage of this design of the camera is its great length (and therefore mass), because the camera includes a sufficiently long mixing cone. Streams of fan air and securinega gas is first decelerated in the diffuser, and the Les it accelerated again around the flame stabilizer, installed at the outlet of the diffuser. Inhibition of threads and their subsequent acceleration, of course, involve a loss of the total pressure flows. The next disadvantage is the location of the heat shield at the end of the mixing cone, resulting in the channel between the screen and the case can get a high-temperature gas from securinega channel, which reduces the cooling efficiency of the housing. In addition, in this construction it is practically impossible to arrange the cooling elements of the stabilizer and the fuel reservoir, located in high-temperature flow securinega gas, air from the fan duct, because the collectors and the stabilizer are at a great distance from the output section of the specified channel.

Closest to the technical nature of the claimed afterburner is the camera described in UK patent No. 1.127.651 "flame Stabilizer for afterburners bypass gas turbine engine", ..F 1 L, from 1.4.66. This camera contains Saturninus and fan input channels, an annular split ring between them, a Central body, a rack connecting the Central body to the separating drum, a casing in heat-insulating screen, the collectors of the fuel injectors and radial-annular flame stabilizer in the body.

The however is that what is the distance between the end face of the separator shell and the tail is relatively small, i.e. the mixing cone is made short with a low degree of mixing of flows, space of characteristic cross-sections (flow part) are selected in the camera according to the standard scheme. The inlet area of the chamber, the so-called cross-section of the mixing - end separation of the shell is determined by the relation

Fcm=(μ F)1+(μ F)2+FCT, (1)

where space flows at the outlet of securinega and fan channels, i.e. in the mixing section, (μ F)1and (μ F)2are based engine, and the area of the Central body in the specified section, FCTturns out in the profiling process of the body from the condition of unseparated flow in saturnina input channel. The area of the midship afterburners achieved at the outlet of the mixing cone, is selected by value

Fm(μ F)1+(μ F)2+Farticle, (2)

where Farticle- the area of the flame stabilizer in the projection on the fuselage mid-section. The value of Farticleis selected in the range

Farticle/Fm=0,3...0,4. (3)

In a mixing cone streams of fan air and securinega gas are inhibited. The degree of inhibition is approximately equal to the degree of expansion of the cone

After the diffuser flows are accelerated again when you wrap them of the flame stabilizer (placed in the midsection of the camera) with a maximum velocity of the edges of the stabilizer. The degree of acceleration, i.e. the degree of confusingly flow in the flame stabilizer is determined by the ratio

Comparing equations (5) and (4), it can be seen that the degree of inhibition in the mixing cone is approximately equal extent further acceleration in the stabilizer flame. This means that the flow rate in the cross section of the edges of the stabilizer flame that represents the parameter that limits the fuel combustion in the chamber, it turns out, in the first approximation, the same as the velocity in the mixing section (i.e. at the output of securinega and fan channels), the area of which is equal to the sum of the living sections of streams (μ F)1and (μ F)2set of the calculation engine. Between these two distinctive sections is intermediate braking flows, which requires the extension length.

Thus, this camera is an intermediate deceleration of the flow is not caused by the needs of the organization workflow, which requires an incremental length, i.e. increases the weight of the camera and the loss of total pressure in it.

Real from what Britanie solves the problem of minimizing the length and weight afterburners while reducing loss of the total pressure and the efficiency of the cooling elements.

This object is achieved in that in the afterburner bypass gas turbine engine containing Saturninus and fan input channels, an annular split ring between them, a Central body, a rack connecting the Central body to the separating drum, a casing in heat-insulating screen, the flame stabilizer and the collectors of the fuel injector, a flame stabilizer is installed in the end of the barrier ribs, and the collectors of the fuel injectors are located in saturnina and fan input channels before the stabilizer flame.

Figure 1 shows schematically a longitudinal section of the head part afterburners bypass gas turbine engine with a stabilizer flame at the end of the separator shell and reservoir of the fuel injectors in the input channels, figure 2 - view of the stabilizer and fuel manifolds in the cross section of the camera, figure 3 - view of the rack in cross section.

Offer afterburner chamber bypass gas turbine engine consists of input securinega channel 1 input of the fan channel 2, the annular shell 3, dividing the input channels 1 and 2, the Central body 4, the rack 5 connecting the Central body 4 with the separation drum 3, the housing 6 by a thermal shield 7, collectors 8 and 9 of the fuel injector and the article is of bilister 10. The stabilizer 10 is located in the end face of the barrier ribs 3, at least one fuel manifold 8 is installed in saturnina channel 1 and at least one fuel manifold 9 - in ventilation channel 2 front stabilizer 10.

Over the air (gas) and combustion of fuel in the proposed afterburner is organized differently than in known afterburning chambers bypass gas turbine engines. Because the stabilizer 10 is installed in the camera at the end of the barrier ribs 3, i.e. directly in the mixing section, the area of this section of the mixing is determined not by the usual relation (1), and ratio

Fcm=(μ F)1+(μ F)2+Farticle+FCT. (6)

Thus, the calculated flow rate corresponding to the specified space (μ F)1and (μ F)2are implemented directly on the edges of the stabilizer 10, the intermediate braking flows and required for him mixing cone is missing. The fuel is injected before the stabilizer 10 collectors 8 and 9 in Saturninus and fan input channels 1 and 2. Ignition of the fuel (source of ignition of any type) is provided in the circulation flow for the stabilizer 10. In this area there is also a mixture of air from the fan channel 2 and the high-temperature gas from the ZAT is seated channel 1, that promotes sustainable and efficient combustion ignited fuel and is equivalent to a partial mixing of the fan air and securinega gas, which is known in the afterburning chambers is provided with a mixing cone. The heat shield 7 is installed as in conventional afterburning chambers, before the fuel manifold 8 that this camera ensures the selection of the channel between the screen 7 and the camera body only 6 cold fan air, It guarantees the efficiency of the cooling screen 7, which protects the body 6 from contact with high-temperature combustion products, extending from the stabilizer 10 flame on the entire flow of the fuel-air mixture generated by the collectors 8 and 9 in the afterburner. The proposed location of the stabilizer 10 in the end face of the barrier ribs 3 and the fuel reservoir 8 and 9 in the input channels 1 and 2 makes it possible to arrange the cooling fan air collectors 8 and 9 and the elements of the stabilizer 10 in contact with the high temperature gas.

Offer afterburner chamber bypass gas turbine engine ensures minimization of length and weight, reduced losses of total pressure, increasing the cooling efficiency of the design elements. This allows us to improve master data dvuhkonturny the th gas turbine engine, and when you install this engine on an aircraft is to improve flight and tactical characteristics of the device.

Afterburner chamber bypass gas turbine engine containing Saturninus and fan input channels, dividing the annular shell between them, a Central body, a rack connecting the Central body to the separating drum, a casing in heat-insulating screen, the collectors of the fuel injector and a flame stabilizer, wherein the stabilizer flame is installed at the end of the barrier ribs, and the collectors of the fuel injectors are located in saturnina and fan input channels before the stabilizer flame.



 

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