JPH04116316A - Swirler of combustion apparatus - Google Patents

Abstract

PURPOSE:To obtain a swirler for a combustion apparatus excellent in reliability and durability by a method wherein a first ring with upstream blades around the circumference and a second ring with downstream blades around the circumference are relatively turned. CONSTITUTION:During low output period from ignition to idling periods, a stationary ring 15 provided with a group of upstream blades 11 around the circumference and a rotary ring 16 provided with a group of down stream blades 12 around the circumference are relatively rotated by an input rod 18, and the positional relationship between air inlets 13 determined by the group of upstream blades 11 and air outlets 14 determined by the group of downstream blades 12 is changed, and a primary swirler 6 and a secondary swirler 7 are rotated in the same direction. During high output period, the positional relationship between the air inlets 13 determined by the group of upstream blades 11 and the air outlets 14 determined by the group of downstream blades 12 is changed, and a primary swirler 6 and a secondary swirler 7 are turned in the opposite directions. Thus, when the rotary ring 16 is simply turned against the stationary ring 15, the turning direction of the secondary swirler 7 and the passing air flow rate can be changed corresponding to the output of an engine.

Description

[Detailed description of the invention] U industrial use! iI'i'] The present invention is directed to a swirler installed in a combustor such as a jet engine or a cast turbine engine for land and ships.
In particular, the present invention relates to a combustor swirler with excellent thermal durability that controls both the swirling direction of combustion air and the amount of air passing through the swirler.

[Prior Art] As shown in Fig. 8, a cast turbine engine such as a jet engine is mainly composed of a compressor a, a combustor, and a turbine C. Air is combusted together with fuel in the combustor, and the combustion residue drives a turn C that is linked to a compressor a.

The flow velocity of combustion air within the combustor is generally greater than the flame propagation velocity. Therefore, in order to prevent the flame from blowing out and to maintain stable flame stability, a combustion air circulation region (combustion region) is created on the first flow side of each combustor. in particular,
A swirler e that gives a swirl to the combustion air is provided at the air intake port C1 of the combustor. This swirler e consists of a plurality of vanes f arranged in a spiral 4-S pattern as shown in FIG.

In order to enhance the swirling effect of the swirler C, the present inventors installed two (14) swirlers e in the air intake section of the combustor as shown in FIG. Develop a technology to change the rotation direction of each swirler e according to the required specifications.

For example, in the case of specifications that emphasize performance on the low output side, such as from ignition to idle, the two swirlers C are designed to rotate in the same direction. Then, when the combustion air mixes with the fuel from the fuel injector g, it double swirls, the swirl becomes stronger, and the residence time in the combustion region becomes longer. Therefore, combustion is promoted and unburned hydrocarbons and carbon monoxide (hereinafter referred to as Tl-IC, C) in the exhaust gas are
(denoted as o) is reduced, and stable combustion without blow-off is achieved at low compressive forces.

On the other hand, when placing more emphasis on performance on the high output side, the two swirlers e are designed to rotate in opposite directions. Then,
Combustion air undergoes a square counter-rotation swirl to be intensively mixed with the fuel, and this counter-rotation swirl cancels out the macroscopic swirl of the combustion air, shortening the residence time in the combustion region. Therefore, nitrogen oxides (hereinafter referred to as NOx) in exhaust gas
), and the generation of smoke is also suppressed.

Problems to be Solved by the Invention] According to this technique, the design of the two water heaters e changes greatly depending on which performance is given more weight, the low-output side or the high-output side. If you place more weight on the low output side and shift the setting J1, smoke and NOx will be generated more at high output.
If you change the design by adding one weight to 11, THC on the low output side
, Co increases, and stable combustion (such as blowout) occurs.

As a countermeasure against this, the vanes f of the swara e (not shown in Fig. 9) are designed to be rotatable for each vane f as shown by the broken line 1 in the figure, and the rotation angle of each vane f is adjusted according to the output of the engine. It is possible to consider a technology that changes these in conjunction with each other. However, with this technology, interlocking means for each vane f must be installed in the combustor of the Custer pin engine, which generates heat at high temperatures (over 1000'C), making reliability and durability difficult. This is virtually impossible when considering the nature of the project. Therefore, I with excellent thermal durability
It was hoped that JJ Hentai Swara would be developed.

The purpose of the present invention, which was created in view of the above circumstances, is to control the swirling flow of combustion air with a simple structure in a swirler installed in the combustor of a cast turbine engine such as a jet engine, thereby improving reliability and This provides a combustor swirler with excellent durability.

[Means for Solving the Problems] In order to achieve the above object, a swirler of a combustor according to the present invention has a plurality of guide vanes arranged in a ring shape to give a swirling flow to combustion air, and each guide vane is arranged in a ring shape to give a swirling flow to combustion air. The upstream blade is divided into an upstream blade that determines the inlet and an upstream blade that determines the air outlet. and are relatively rotatable in order to switch the direction of rotation and change the amount of air passing through.

1 Action 1 When the first ring around which the upstream blade is circumferentially rotates and the second ring around which the upstream blade is circumferentially rotated, the air inlet determined for the upstream blade and the upstream blade The positional relationship with the air outlet determined in is changed. Thereby, the swirling direction of the combustion air can be reversed.

At this time, there is no need for interlocking means for interlocking the individual blades, and the turning direction can be reversed with an extremely simple structure of relatively rotating the first ring and the second ring. Therefore, it is a highly reliable variable swirler with excellent thermal durability and 19g.

Also, depending on the shape of the upstream blade and the upstream blade, the area of the air inlet and air outlet can be changed by relative rotation of the first ring and the second ring, thereby adjusting the air flow rate passing through the swirler. I'll come.

[Example] An example of the present invention will be described below based on the accompanying drawings.

FIG. 4 shows a jet engine combustor 1 equipped with a swirler according to this embodiment. This combustor 1 is provided between a compressor and a turbine of a jet engine. As shown in the figure, a combustor liner 3 is provided in a combustor cooling sink 2, and an air intake port 4 for taking air into the liner 3 is opened in the liner 3.

This air intake 4 is provided with a slanted fuel injection valve 5 for mixing fuel with combustion air. According to this configuration, a part of the air compressed by the compressor and flowing into the combustor goosen 2 enters the liner 3 from the air intake port 4 and is mixed with the fuel from the fuel injection valve 5 and combusted. The remainder flows between the liner 3 and the gauging 2 to cool the combustor liner 3, which generates heat at a high temperature.

The air intake port 4 is provided with a secondary air swirler 6 and a secondary air swirler 7 for giving a swirling flow to the combustion air flowing into the liner 3. Details of these primary and secondary air swirlers 6.7 are shown in FIG.

As shown in the figure, the pressure distributing air swirler 6 is formed into a ring shape to be installed around the cylindrical fuel injection valve 5, and has a plurality of vanes (
(not shown) is provided to provide a swirling flow in a fixed direction to the primary air flowing into the liner 3.

On the other hand, the secondary air swirler 7 is the secondary air swirler 6.
A ring diameter larger than that of the primary air swirler 6 is formed on the downstream side of the primary air swirler 6. As shown in FIG. 2, this secondary air swirler 7 has a plurality of guide vanes 8 arranged in a ring shape in the same direction so as to give a swirling flow to the secondary air flowing into the liner 3.

In the state shown in FIG. 2, this secondary air swirler 7 is configured to introduce combustion air from its outer circumferential side, swirl it counterclockwise, and blow it out toward its inner circumferential side. There is.

The guide blade 8 of the secondary air swirler 7 is divided into a downstream blade 11 and a downstream blade 12 by a dividing line 10 substantially perpendicular to the swirling flow 9 of the secondary air. Above downstream blade 1
1 determines the position of the air inlet 13 of the swirler 7, while the downstream blade 12 determines the position of the air outlet 14 of the swirler 7.
It determines the position.

As shown in FIG. 1, the downstream blade 12 is disposed around a first ring ]-5 (hereinafter referred to as fixed ring 1-5) fixed to the liner 3 side. This fixing ring 15 is a member fixed to the liner 3 side to support the swirlers 6 and 7. On the other hand, the downstream blade 11- is disposed around a rotatable second ring 16 (hereinafter referred to as the rotary ring 16). Therefore, when the rotary ring 1-6 is rotated with respect to the fixed ring 15, the 11 groups of upstream blades are integrated with the 12 groups of downstream blades, as shown in FIGS. 2 and 3. Rotate in a comradely manner. In this way, when the upstream blade 11 group and the downstream blade 12 group rotate relative to each other, the air inflow 1113
The positional relationship between the combustion air and the air outlet 14 is shifted, and the swirling direction of the combustion air is reversed.

That is, the secondary air swirler 7 has the function of swirling the secondary air flowing into the liner 3 in the same direction as the swirling direction of the primary air by the secondary air swirler 6, or in the opposite direction. have.

As shown in FIG. 1, the rotating ring 16 can be rotated from outside the combustor casing 2 via a ring mechanism 17. Details of the ring mechanism 17 will be described below. As shown in FIG. 1, an input rod 18 is provided in the combustor casing 2 through the gauging hole 2 so as to be rotatable around its axis. A first arm is attached to the end of the manual lot 18 in the game sink at right angles to the input lot 18. An engagement hole 20 is bored at the tip of one of the first arms. This engagement hole 20 has
A liner outer portion 23 of the second arm 22 supported by the combustor liner 3 via a pole joint 21 is loosely fitted.

A third arm 25 is connected to the inner liner portion 24 of the second arm 22 . This third arm 25 is
A second flow blade 11 is fixed to a rotating ring 16 surrounding it.

According to this configuration, when the input rod 18 is rotated around its axis, one first arm rotates in the direction of the front and back sides of the paper, and thereby the second arm 22 rotates about the ball joint 21 as a fulcrum. 3 arm 25 is rotated, and rotation ring 1
6 will rotate relative to the fixed ring 15. As a result, as shown in FIGS. 2 and 3, the second flow blade 11 group rotates integrally with respect to the downstream blade 12 group.

The operation of this embodiment having the above configuration will be described.

During low output, such as from ignition to idle, the input lot 18 is operated from outside the combustor casing 2 to bring the secondary air swirler 7 into the state shown in FIG. Make the turning direction with 7 the same.

That is, the fixed ring 15 surrounding the 11th group of downstream blades and the rotary ring 16 around the 12th group of downstream blades are determined by the input lot 18. The positional relationship between the air inlet 13 and the air outlet 1-4 determined in the downstream blade 12 group is set as shown in FIG. This causes the secondary air swirler 6 and the secondary air swirler 7 to rotate in the same direction.

Then, when the primary and secondary air passing through each swirler 6 and 7 mix with the fuel from the fuel injection valve 5, they double-swirl in the same direction and the swirl becomes stronger. The residence time becomes longer. Therefore, combustion is promoted, THC and Co in the exhaust gas are reduced, and stable combustion without blow-off is achieved at low output.

In addition, at this low output, as shown in Figure 3, the air passage 27 of the secondary air swirler 7 is narrowed to a tapered shape, which limits the amount of combustion air and causes the secondary air to swirl due to its nozzle effect. combustion is further promoted at low power. As a result, as shown in FIG. 5, the stable operating range at low power, where blow-out is likely to occur, becomes wider, and as shown in FIG. 6, THC and Co at low power are reduced.

On the other hand, at idle or above, the input lot 18 is operated at a predetermined rate so that the state shown in FIG. 3 gradually changes to the state shown in FIG. do it like this.

That is, at high output, the air inlet 13 is determined to be the downstream blade 11 group, and the air outlet 1 is determined to be the downstream blade 12 group.
/1 by changing the positional relationship with the secondary air swirler 7.
is brought into the state shown in Fig. 2, and the swirling directions of the primary air swirler 6 and the secondary air swirler 7 are reversed.Then, the primary and secondary air passing through each swirler 6 and 7 are counter-rotated with each other. In addition to swirling and intensively mixing with the fuel, this counter-rotating swirl cancels out the macroscopic swirl of the combustion air and shortens the residence time that the combustion air remains in the combustion zone, thus lowering the combustion temperature. As a result, NOx in the exhaust gas is reduced, and the generation of smoke gas is suppressed.

At this high output, a large amount of combustion air is supplied into the liner 3 because the air passage 28 of the secondary air swirler 7 is widened compared to the case at low output shown in FIG.
That dilution f! As a result of burning, the combustion temperature at high output is further reduced, as shown in Figure 7.
When changing the direction of rotation of the secondary air swirler 7 and the amount of air passing through it in accordance with the engine output so that x is reduced, the rotating ring 16 is moved relative to the fixed ring 1-5.

There is no need for an interlocking means for interlocking the individual downstream blades 11 and 12, and the rotation can be performed using an extremely simple structure. It is a variable swirler with excellent durability and reliability.According to Kome Swirler 7, it has a stable operating range over the entire operating range from engine ignition to maximum output (takeoff). Expansion, and purification of JF scum is achieved. In addition, since NOx is reduced during high output, the temperature of the combustor can be increased and the efficiency of the engine can be increased.

U Effects of the Invention] As explained above, the swirler of the combustor according to the present invention can exhibit the following excellent effects. (2) Simple structure with excellent thermal durability and extremely high reliability; (3) Low power consumption during high output. NOx conversion is achieved.

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[Brief explanation of the drawing]

FIG. 1 is a sectional side view of the main part of the combustor, which is a first embodiment of the present invention, and shows a jet in which the swirler of the combustor is shrunk to the engine.
Figure 2 is a front view of the secondary air swirler in Figure 1 at high output, Figure 3 is a front view of the secondary air swirler shown in Figure 1 at low power, and Figure 4 is shown in Figure 1. Overall side sectional view of the combustor, No. 5
7 to 7 are graphs showing a comparison between this embodiment and the conventional example,
Figure 8 is a schematic side view of the Je Soto engine, Figure 9 is a front view of a swirler showing a conventional example, and Figure 10 is a combustor of the Je Soto engine, which was developed by the present inventors. This is a side sectional view of main parts. In the figure, 1 is a combustor, 7 is a secondary air swirler, 8 is a guide blade, 11 is a downstream blade, 12 is a downstream blade, 13 is an air inlet,
14 is the air outlet, 15 is the second ring, which has a fixed ring, and 16 is the first ring, which has a rotating ring.

Claims (1)

[Claims] 1. A plurality of guide vanes are arranged in a ring shape to give a swirling flow to the combustion air, and each guide vane is divided into an upstream vane that determines the air inlet and a downstream vane that determines the air outlet. and downstream blades are disposed around the first ring and the second ring, respectively, and the first ring and the second ring are disposed so as to be rotatable with respect to each other in order to switch the direction of rotation and change the amount of air passing through. The swirler of the combustor is characterized by: