Ring combustion chamber for gas-turbine engine

FIELD: gas-turbine engine engineering.

SUBSTANCE: ring combustion chamber comprises fire tube and vortex burners arranged over periphery of its face and made of fuel-air scroll and air swirlers with outlet conical branch pipe having cylindrical section. The shell is secured to the face coaxially to each branch pipe defining a ring space. The outer side of the end cylindrical section or inner side of the shell located above it is provided with longitudinal ribs distributed uniformly over periphery and defining insulated passages. The through openings connected with the ring space are made in the face of the fire tube under the shell.

EFFECT: enhanced reliability and expanded functional capabilities.

2 cl, 2 dwg

 

The invention relates to the field of aircraft gas turbine engines, mainly to annular combustion chambers.

Known annular combustion chamber containing a heating pipe and located around the circumference of the wall of the burner (see RF Patent №2164323, IPC 7 F 23 R 3/46,, 20.03.1999). In the known technical solution in the burner unit has a combination of centrifugal nozzle with axial air swirler and the exit of the burner channel with a bell that does not provide the required length of the air-fuel mixture burning in the specified length of the flame tube. While the spray mixture will be directed to the inner surface of the walls of the flame tube, which in turn will lead to the interaction of the hot wall with the air-fuel mixture and cause gas corrosion and micropackage combustion, and the combustion efficiency bude less 0,98.

Also known annular combustion chamber, which also has a combination of centrifugal nozzle with an axial swirler (see RF Patent №2039323, IPC 7 F 23 R 3/42, 04.03.1993 year). In a known camera output from the burner is made in the form of an inverted cone, i.e. forms a centrifugal chamber of the spin of the air traversed by the spray of fuel centrifugal atomizer. This scheme is spraying fuel gives a complete transformation in g is megenney mixture and, accordingly, the combustion efficiency. However, this device has a fan spray at the exit, where the angle of promotion more than 120°. There is a hit of a mixture of ceramic inserts, which do not let the temperature drop, as it causes the spalling of fragments, and in the case of using the metal walls of their gas corrosion and micropackage burning.

The objective of the invention is to improve the reliability and extend the range of stable operation by reducing the cone of spray mix fuel with air at the outlet of the burner and the establishment of the zone reverse currents.

The technical result is achieved in that the annular combustor of a gas turbine engine includes heating pipe and evenly spaced around the circumference of its end wall vortex burner comprising a fuel snail and air swirlers, with the output conical nozzle having a cylindrical end section, while the outside coaxial to each nozzle to the end wall of the flame tube attached shell, forming with him a ring cavity and the outer surface of the cylindrical end section or on the inner surface of the shell above him, evenly spaced around the circumference is made of longitudinal ribs forming isolated channels, but in the end wall of the flame Trou what s under cowling is a through hole, communicated with the annular cavity. In addition, the number of edges is equal to at least three or a multiple of it, the thickness of each of the ribs has a size of from 1.2 to 1.6 mm, and a height of 0.6 to 0.8 mm, while the total area of the through holes at the entrance to the channels 1.2...1.4 times larger than the total area of the channels. The internal diameter of the cylindrical end section perform equal to from 1.8 to 1.85 internal nozzle diameter of the swirler, the length of the shell from the end nozzle of swirlers perform equal to the internal diameter of the nozzle, and the distance from the end of the nozzle to the end of the end cylindrical section of pipe perform equal to 0.65 from the inner nozzle diameter of the swirler.

The invention is illustrated by drawings.

Figure 1 shows a longitudinal section of the head part of the combustion chamber.

Figure 2 presents the cross-section A-a in figure 1.

The combustion chamber of a gas turbine engine includes heating pipe 1 and evenly spaced around the circumference of its end wall 2 of the vortex burner 3, which consists of the air-fuel snail 4 and air 5 of swirlers, with the output conical pipe 6 having a cylindrical end section 7. Outside coaxially to each pipe 6 to the end wall 2 of the flame tube attached shell 8, forming with it an annular chamber 9. On the inner surface of the shell 8 is equal to the RNO circumference made ribs 10, forming isolated channels 11. In the end wall 2 of the heating pipe under the shell 8 is a through hole 12, is in communication with the annular cavity 9. Number of ribs 10 is at least three or a multiple of it. The thickness of each rib 10 has a size of from 1.2 to 1.6 mm, and a height of 0.6 to 0.8 mm, while the total area of the through holes 12 1.2...1.4 times larger than the total area of the channels 11. The internal diameter of the cylindrical end section 7 is made equal to 1.8...1,85 inner diameter of the nozzle 13 of the swirler. The length of the shell 8 from the end of the nozzle 13 of swirlers perform equal to its internal diameter, and the distance from the end of the nozzle 13 to the end of the cylindrical section 7 of the pipe 6 perform equal to 0.65 from the inner diameter of the nozzle 13 of the swirler. The combustion chamber also has an inlet fuel injector 14, which is installed in the sleeve with a radial movement 15.

When the combustion air entering into the combustion chamber, is fed to the input vortex burner and forming the zone of reverse currents. Part of the air through the holes 12 is directed into the cavity 9, where air enters isolated from other channels 11, bypassing the output sections 7, forming an air curtain and participating in the spraying of residual fuel. The air incoming through the channels 11, performs the cooling of the shell 8 and the end portion 7, and that is also helps to reduce twist cone spray pattern of a homogeneous mixture at the outlet of the burner, creates a reduced area of the reverse currents, separating the area from the walls of the flame tube.

Longitudinal ribs 10 are performed on the inner surface of the shell 8 by the method of build-in scan of the workpiece, thus closing the seam should be sanded flush. Number of ribs 10 should choose the minimum or multiples of 3 (figure 2 shows the implementation with a number of edges equal to 3). Ribs 10 are used to provide stabilization of the height of the channels 11 and due to the fact that the shell 8 has a higher temperature than the end cylindrical section, the ribs 10 are not firmly connected with an end of the cylindrical section 7.

Fuel combined nozzle 14 is set in a floating sleeve 15, which provides temperature compensation of the hot header pipe 1 relative to the "cold" nozzle 14.

The width of the ribs 10 S=1,2...1,6 mm Ribs 10 with a width of S is less than 1.2 mm is complicated to manufacture and are deformed during rolling in the ring of the shell 8. If the width of edges S=1.6 mm strongly occlude the flow of air on channel 11, resulting in a trace of overheating of the material of the shell 8 at the outlet of a cylindrical section 7. Material for the manufacture of the ribs is alloy HNWT (residence permit-98). The use of other grades of materials is impractical, since most alloys - ageing, i.e. prone to cracking, such as alloy HNTB-VI (I-4).

Height Cana is offering 11 is selected within 0,6...0,8 mm to ensure that the air velocity in the channels 50-70 m/s, the total area of the holes 12 must be 1.2...1.4 times larger than the total area of the channels 11. Decreasing this ratio the speed of the air in the channels 11 is reduced, which in turn leads to reduced cooling shells and poor education of fuel-air mixture. The increase in the ratio over 1.4 leads to a drastic depletion of the air-fuel mixture and a waste of air.

The dimensions of the shell 8 and an end cylindrical section 7 are selected from the following ratios for the baseline nozzle size 13 Dc1:

- diameter end of the cylindrical section 7 (Darticle=(1,8...1,85) Dc1when Darticle≤5:1,8 Dc1decrease the size of the zone of reverse currents, which affects the combustion process; if Darticle>1,85 DC1dramatically increases the area of the reverse currents, which leads to burnout shell 8 and an end cylindrical section 7 due to the retraction of hot gases from the combustion zone in a vortex chamber;

- length of the shell 8 and an end cylindrical section 7 are selected from the relation l1=Dc1and l2=0,65 DC1. By reducing these ratios, the flame front approaches the wall 2 and causing it to overheat. The increase in these ratios above leads to the fact that the shell 8 and a cylindrical tail section 7 will thorat and length, we will have the specified outcome.

This embodiment of the combustion chamber reduces the temperature of the output sections of the shell and an end cylindrical section, in addition, to significantly improve the reliability of the combustion chamber, which, in turn, will lead to expansion of the range camera and the formation of a compact combustion zone and to obtain the maximum combustion efficiency with a reduced environmental emissions.

1. Annular combustion chamber of a gas turbine engine containing a heating pipe and evenly spaced around the circumference of its end wall vortex burner comprising a fuel snail and air swirlers, with the output conical nozzle having a cylindrical end section, while the outside coaxial to each nozzle to the end wall of the flame tube attached shell, forming with him a ring cavity and the outer surface of the cylindrical end section or on the inner surface of the shell above him, evenly spaced around the circumference is made of longitudinal ribs forming isolated channels, but in the end wall of the flame tube under the cowling is made of the through-hole communicated with ring cavity.

2. The combustion chamber according to claim 1, characterized in that the number of edges is equal to at least three or a multiple of it, the thickness of each rib is of the size of the p from 1.2 to 1.6 mm, and a height of 0.6 to 0.8 mm, while the total area of the through holes in the 1.2-1.4 times larger than the total area of the channels.

3. The combustion chamber according to claim 1 or 2, characterized in that the inner diameter of the cylindrical end section perform equal to from 1.8 to 1.85 internal nozzle diameter of the swirler, the length of the shell from the end nozzle of swirlers perform equal to its internal diameter, and the distance from the end of the nozzle to the end of the end cylindrical section of pipe perform equal to 0.65 from the inner nozzle diameter of the swirler.



 

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