CN112963864B - A strong mixing type main combustion port of gas turbine combustor - Google Patents

Abstract

The invention relates to a strong mixed type combustion chamber main combustion hole of a gas turbine, which consists of a bent pipe gas path channel and a middle main combustion hole channel, and is additionally provided with a bent pipe type gas path channel, wherein a central axis between a bent part of a bent pipe and a connecting line of the middle main combustion hole channel has a certain angle, and the bent pipe and the central axis of the bent pipe gas path channel both have certain angles, so that the strong mixed type combustion chamber main combustion hole can be used for controlling the rotating strength and the area of the rotating airflow diffusion. When the gas path flows through the elbow and is ejected from the elbow, the airflow gives a reaction force to the elbow, the rotating mechanism is connected by the ball bearings and then rotates, so that the airflow ejected from the elbow rotates, the rotating airflow is further and fully mixed with the unburned or insufficiently combusted fuel oil in the main combustion chamber to carry out secondary combustion, simultaneously, the combustion condition is strengthened, and the combustion efficiency is improved.

Description

A strong mixing type gas turbine combustor main combustion hole

technical field

The invention belongs to the technical field of gas turbine combustion chambers, and in particular relates to a main combustion hole of a strongly mixed gas turbine combustion chamber.

Background technique

At present, aero-engines, as the crown jewel of the industry, are the embodiment of a country's high-end technology level in materials, tight processing, and control design. The key point of aero-engine lies in the research and development of the core engine, which consists of a compressor, a combustion chamber and a high-pressure turbine. The second combustion chamber is the main component for producing power. In the combustion chamber, the high-pressure gas from the compressor and the fuel in the combustion chamber are fully mixed and combusted, and the released heat can increase the temperature of the wet gas, and the high-temperature gas enters the turbine and the nozzle behind to expand and do work, thus completing the entire process. Power take off process.

The holes and slits on the gas turbine flame tube are mainly divided into two categories. One is large-sized holes, which are mainly used for distributing combustion and mixing gas; the other is small-sized holes, which are mainly used to cool and protect the wall of the flame tube and prevent heat and high temperature. Damage the wall of the flame tube. Part of the air entering the flame Jane enters through the cyclone, and the other part enters the flame Jane through these holes and slits. Therefore, it is necessary to ensure that the required air flow enters the flame tube uniformly according to the design requirements. The large-sized holes on the flame tube can be mainly divided into main combustion holes, supplementary combustion holes and mixing holes. Among them, the air flow through the main combustion hole is relatively large, so that the jet has sufficient turbulent intensity and penetration depth to strengthen the combustion process. Generally speaking, the flow distribution determines the opening area of the flame tube, and the penetration depth determines the size of the aperture, thereby determining the number of holes. And the margins and rows of holes are determined by the strength condition.

SUMMARY OF THE INVENTION

The present invention is mainly aimed at a strong-mixed gas turbine combustion chamber main combustion hole in the technical field of aero-engine combustion chambers, specifically: the combustion chamber main combustion hole is composed of a curved gas path channel and an intermediate main combustion hole channel, adding A kind of elbow-type air passage is developed. The central axis between the turning part of the elbow and the connecting line of the middle main combustion hole channel has a certain angle, and the central axis of the elbow and the gas passage of the elbow has a certain angle. When The air flow flows through the elbow and is ejected from it, and the airflow gives a reaction force to the elbow. The wall of the combustion hole channel rotates as a connected whole, and the rotating mechanism and the radial control ball plate are connected by balls, so the rotation occurs, so that the airflow ejected from the elbow rotates, and the rotating airflow is connected with the main combustion chamber. The unburned or insufficiently burned fuel is further fully mixed for secondary combustion, which also strengthens the combustion condition and improves the combustion efficiency.

Technical solutions

The purpose of the present invention is to realize the main combustion hole of a strongly mixed gas turbine combustion chamber.

The technical scheme of the present invention is as follows:

A strong mixing type gas turbine combustion chamber main combustion hole is characterized in that: it is characterized in that: it comprises a main combustion hole elbow gas pipe, a main combustion hole elbow gas channel, a front ball baffle, a middle main combustion hole The channel, the rear ball baffle, the pipe wall of the middle main combustion hole channel, the radial control ball plate, the ball, the bending part of the elbow and the middle main combustion hole channel connection line has a certain angle, the elbow and the elbow have a certain angle. The central axis of the pipe and air passage has a certain angle.

The main combustion hole of the strong mixing type gas turbine combustion chamber is characterized in that: the main combustion hole elbow pipe, the front ball baffle, the rear ball baffle and the middle main combustion hole channel pipe wall are one connected whole.

The main combustion hole of the strong mixing type gas turbine combustion chamber is characterized in that: the sum of the area of the gas path channel of the main combustion hole elbow and the channel area of the intermediate main combustion hole is greater than or equal to the area of the main combustion hole of the conventional gas turbine, but It is necessary to ensure that the total main combustion hole area is too large according to the actual situation.

The main combustion hole of the strong mixing type gas turbine combustion chamber is characterized in that: there is a certain angle between the central axis between the turning part of the elbow and the connecting line of the middle main combustion hole passage, and the included angle is 30°～60° ° between.

The main combustion hole of the strong mixing type gas turbine combustion chamber is characterized in that: the elbow and the central axis of the gas passage of the elbow have a certain angle, and the included angle is between 30° and 60°.

The main combustion hole of the strong mixing type gas turbine combustion chamber is characterized in that: the middle main combustion hole channel is located in the middle of the main combustion hole, and the elbow gas passages are circumferentially arranged around the middle main combustion hole, and the number can be based on the actual situation. It depends on the situation and the difficulty of processing.

The present invention has the following beneficial effects:

(1) The airflow ejected from the elbow is rotated, and the rotating airflow is further fully mixed with the unburned or insufficiently burned fuel in the main combustion chamber for secondary combustion, which also strengthens the combustion condition and improves the combustion. efficiency. (2) The connection of the balls can be lubricated, and there is a very convenient treatment method, so that this structure can be widely used in other aspects. (3) In the event of an emergency situation where the balls are stuck, the smooth flow of the main combustion hole elbow air passage and the middle main combustion hole passage can also ensure the function of the basic main combustion hole. (4) The strength of the rotation and the area of the swirling airflow can pass through the angle between the center axis between the curved part of the elbow and the connecting line of the middle main combustion hole channel and the angle between the center axis of the elbow and the gas path of the elbow. controlled.

Description of drawings

Figure 1: It is an overall appearance view of the main combustion hole of a strongly mixed gas turbine combustion chamber;

Figure 2: is a partial enlarged view of the main combustion hole of a strongly mixed gas turbine combustor (circle in Figure 1);

Figure 3: It is a back view of the main combustion hole of a strongly mixed gas turbine combustion chamber;

Figure 4: is a cross-sectional view of the ball portion of the main combustion hole of a strongly mixed gas turbine combustion chamber;

Figure 5: It is an angle view formed by a strong mixing type gas turbine combustion chamber main combustion hole elbow and the central axis of the elbow gas path;

In the figure: 1. Main combustion hole elbow gas pipe 2, main combustion hole elbow gas channel 3, front ball baffle 4, middle main combustion hole channel 5, rear ball baffle 6, middle main combustion hole Channel wall 7, radial control ball plate 8, ball P, the angle between the radial injection hole and the axial air inlet

Detailed ways

Now in conjunction with the accompanying drawings, the present invention will be further described:

Combined with the overall appearance of the main combustion hole of a strongly mixed gas turbine combustor in Fig. 1, Fig. 2 is a partial enlarged view of the main combustion hole of a strongly mixed gas turbine combustor (circle in Fig. 1), Fig. 3 a strong The rear view of the main combustion hole of the hybrid gas turbine combustion chamber, Figure 4 is a cross-sectional view of the ball part of the main combustion hole of a strongly mixed gas turbine combustion chamber, and Figure 5 is a strongly mixed gas turbine combustion chamber Main combustion hole elbow and elbow gas The angle formed by the central axis of the road passage, the invention rotates the airflow ejected from the elbow, and the rotating airflow is further fully mixed with the unburned or insufficiently burned fuel in the main combustion chamber for secondary combustion, and at the same time It also strengthens the combustion condition and improves the combustion efficiency.

Specific process: the air from the external passage reaches the outer side of the outer main combustion hole of the gas turbine combustion chamber at a certain speed, and a part of it enters the combustion chamber from the middle main combustion hole passage (4 in Figure 2) and is connected with the air in the main combustion chamber. The fuel that burns or is not sufficiently burned is further fully mixed, and the secondary combustion is carried out to realize the basic function of the main combustion hole, while the other part of the air flows from the main combustion hole elbow air passages arranged in the circumferential direction (2 in Figure 2). ) into the combustion chamber, when the gas is ejected from the elbow (1 in Figure 2), the gas path flows through the elbow and is ejected from it, the airflow gives a reaction force to the elbow, and the main combustion hole elbow gas path The pipe (2 in Fig. 2), the front ball baffle (3 in Fig. 2), the rear ball baffle (5 in Fig. 3) and the pipe wall of the middle main combustion hole channel (6 in Fig. 3) are A coupled whole rotates, and the rotating mechanism and the radial control ball plate are connected with balls (8 in Figure 4) and then rotate, so that the airflow ejected from the elbow rotates, and the rotating airflow is connected with the main combustion chamber. The unburned or insufficiently burned fuel is further fully mixed for secondary combustion, which also strengthens the combustion condition and improves the combustion efficiency.

Claims (2)

1. The main combustion hole of a strongly mixed gas turbine combustion chamber is characterized in that: it comprises the main combustion hole elbow gas pipe, the main combustion hole elbow gas channel, the front ball baffle, the middle main combustion hole channel, The rear ball baffle, the pipe wall of the middle main combustion hole channel, the radial control ball plate, the balls; the included angle formed by the central axis between the turning part of the main combustion hole elbow and the connecting line of the middle main combustion hole channel is 30°～ 60°; the angle formed between the main combustion hole elbow and the central axis of the main combustion hole elbow is 30° to 60°; the middle main combustion hole channel is in the middle of the main combustion hole, and the main combustion hole elbow gas channel is around The air is arranged around the main combustion hole in the middle, and the number is determined according to the actual situation and the difficulty of processing; the air from the external channel reaches the outside of the main combustion hole, and part of it enters the interior of the combustion chamber and the air in the main combustion chamber from the middle main combustion hole channel. The unburned or insufficiently burned fuel is further fully mixed for secondary combustion to achieve the basic function of the main combustion hole, while another part of the air enters the combustion chamber from the circumferentially arranged main combustion hole elbow air passages , the airflow flows through the elbow and is ejected from it, the airflow gives a reaction force to the main combustion hole elbow, the main combustion hole elbow pipe, the front ball baffle, the rear ball baffle and the middle main combustion hole channel pipe The wall rotates as a connected whole, and the rotating mechanism and the radial control ball plate are connected by balls and then rotate, so that the airflow ejected from the elbow rotates, and the rotating airflow is connected with the unburned or unburned or unburned air in the main combustion chamber. Insufficiently burned fuel is further mixed thoroughly. 2. The main combustion hole of a strongly mixed gas turbine combustion chamber according to claim 1, characterized in that: the sum of the main combustion hole elbow gas path area and the intermediate main combustion hole channel area is equal to the total of the conventional gas turbine main combustion hole. area.

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