CN112963864A - Strong-mixing type main combustion hole of combustion chamber of gas turbine - Google Patents
Strong-mixing type main combustion hole of combustion chamber of gas turbine Download PDFInfo
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- CN112963864A CN112963864A CN202110325715.4A CN202110325715A CN112963864A CN 112963864 A CN112963864 A CN 112963864A CN 202110325715 A CN202110325715 A CN 202110325715A CN 112963864 A CN112963864 A CN 112963864A
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- main combustion
- bent pipe
- hole
- combustion hole
- channel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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
Technical Field
The invention belongs to the technical field of gas turbine combustion chambers, and particularly relates to a main combustion hole of a strong-mixing type gas turbine combustion chamber.
Background
At present, an aero-engine, as a pearl on an industrial crown, is a high-end technological technical embodiment in the aspects of materials, compact processing and control design in China. The focus of aircraft engines is on the development of a core engine, which consists of a compressor, a combustion chamber and a high-pressure turbine, the two combustion chambers being the main components in which power is produced. In the combustion chamber, high-pressure gas from the compressor and fuel in the combustion chamber are fully mixed and combusted, the temperature of moisture is increased by released heat energy, and high-temperature gas enters a rear turbine and a rear spray pipe to expand and do work, so that the whole power output process is completed.
Holes and seams on the flame tube of the gas turbine mainly comprise two types, one type is a large-size hole which is mainly used for distributing combustion and mixing gas; the other part is a small-size hole which is mainly used for cooling and protecting the flame tube wall surface and preventing the flame tube wall surface from being damaged by the high temperature. The air entering the flame tube is partially entered through the swirler, and the other part enters the flame tube through the holes and the slits. Therefore, the required air flow rate is ensured to enter the flame tube uniformly according to the design requirement. The large-size holes on the flame tube can be mainly divided into main combustion holes, afterburning holes and mixing holes. Wherein the air flow through the main burner orifices is relatively large so that the jet has sufficient plume intensity and penetration depth to enhance the combustion process. Generally, the flow distribution determines the open area of the liner, while the penetration depth determines the size of the bore, and hence the number of bores. And the margin and the number of rows of the holes are determined by the strength condition.
Disclosure of Invention
The invention mainly aims at a main combustion hole of a combustion chamber of a strong-mixing type gas turbine in the technical field of combustion chambers of aero-engines, and specifically comprises the following steps: the main combustion hole of the combustion chamber consists of a bent pipe gas path channel and a middle main combustion hole channel, a bent pipe type gas path channel is added, a certain angle is formed between the central axis of a connecting line of a turning part of a bent pipe and the middle main combustion hole channel, the central axis of the bent pipe and the central axis of the bent pipe gas path channel are both provided with certain angles, when a gas path flows through the bent pipe and is ejected out of the bent pipe, gas flow gives a reaction force to the bent pipe, under the condition of the reaction force, the main combustion hole bent pipe gas path pipe, a front ball baffle, a rear ball baffle and the pipe wall of the middle main combustion hole channel are connected into a whole to rotate, a rotating mechanism is connected with a radial control ball plate by balls, so that the gas flow ejected from the bent pipe rotates, the rotating gas flow is further and fully mixed with unburned or insufficiently combusted fuel oil in the main combustion chamber to carry out secondary combustion, and the combustion condition is also, the combustion efficiency is improved.
Technical scheme
The invention aims to realize a main combustion hole of a combustion chamber of a strong mixing type gas turbine.
The technical scheme of the invention is as follows:
the utility model provides a gas turbine combustion chamber main combustion hole of intensive mixing which characterized in that: the method is characterized in that: the gas path pipe comprises a main combustion hole bent pipe gas path pipe, a main combustion hole bent pipe gas path channel, a preposed ball baffle, a middle main combustion hole channel, a postposition ball baffle, a middle main combustion hole channel pipe wall, a radial control ball plate and balls, wherein a certain angle is formed between the central axis of a turning part of the bent pipe and the connecting line of the middle main combustion hole channel, and the bent pipe and the central axis of the bent pipe gas path channel have certain angles.
The strong mixed type main combustion hole of the combustion chamber of the gas turbine is characterized in that: the main burning hole bent pipe gas path pipe, the preposed ball baffle, the postposed ball baffle and the middle main burning hole channel pipe wall are connected into a whole.
The strong mixed type main combustion hole of the combustion chamber of the gas turbine is characterized in that: the sum of the gas channel area of the main combustion hole elbow and the middle main combustion hole channel area is larger than or equal to the area of the main combustion hole of the conventional gas turbine, but the sum of the total area of the main combustion hole and the area of the middle main combustion hole is ensured to be too large according to actual conditions.
The strong mixed type main combustion hole of the combustion chamber of the gas turbine is characterized in that: : the central axis between the turning part of the elbow and the connecting line of the middle main burning hole channel has a certain angle, and the included angle is between 30 and 60 degrees.
The strong-mixing type main combustion hole of the combustion chamber of the gas turbine is characterized in that: the bent pipe and the central axis of the air passage of the bent pipe are both provided with certain angles, and the included angle is 30-60 degrees.
The strong-mixing type main combustion hole of the combustion chamber of the gas turbine is characterized in that: the middle main combustion hole channel is positioned in the middle of the main combustion hole, the bent pipe gas path channels are circumferentially distributed around the middle main combustion hole, and the number of the bent pipe gas path channels can be determined according to actual conditions and the processing difficulty.
The invention has the following beneficial effects:
(1) the airflow ejected from the bent pipe rotates, and the rotating airflow is further fully mixed with the unburned or insufficiently combusted fuel oil in the main combustion chamber to perform secondary combustion, so that the combustion condition is enhanced, and the combustion efficiency is improved. (2) The ball joint can be lubricated in a convenient way, so that the structure can be widely used in other aspects. (3) Under the condition that the balls are blocked in an emergency, the smoothness of the air channel of the bent pipe of the main burning hole and the middle main burning hole channel can also ensure the function of the basic main burning hole. (4) The rotating strength and the area of the rotating airflow diffusion can be controlled by the included angle of the central axis between the connecting line of the turning part of the elbow and the middle main combustion hole channel and the included angle of the central axis of the elbow and the central axis of the elbow gas channel.
Drawings
FIG. 1: the overall appearance diagram of the main combustion hole of the combustion chamber of the strong mixing type gas turbine is shown;
FIG. 2: the main combustion hole of the combustion chamber of the gas turbine with strong mixing is partially enlarged (circle in figure 1);
FIG. 3: the back view of the main combustion hole of the combustion chamber of the gas turbine with strong mixing;
FIG. 4: the ball part of the main combustion hole of the combustion chamber of the gas turbine is a strong mixing type cross section;
FIG. 5: the angle diagram is formed by the main combustion hole bent pipe and the central axis of the bent pipe gas path channel of the combustion chamber of the strong mixing type gas turbine;
in the figure: 1. a main combustion hole bent pipe gas path pipe 2, a main combustion hole bent pipe gas path channel 3, a preposed ball baffle 4, a middle main combustion hole channel 5, a postposition ball baffle 6, a middle main combustion hole channel pipe wall 7, a radial control ball plate 8, balls P, and an included angle between a radial spray hole and an axial gas inlet
Detailed Description
The invention will now be further described with reference to the accompanying drawings in which:
referring to fig. 1, an overall appearance diagram of a main combustion hole of a strong mixing type gas turbine combustion chamber, fig. 2 is a partial enlarged view (circle in fig. 1) of the main combustion hole of the strong mixing type gas turbine combustion chamber, fig. 3 is a back view of the main combustion hole of the strong mixing type gas turbine combustion chamber, fig. 4 is a cross-sectional view of a ball part of the main combustion hole of the strong mixing type gas turbine combustion chamber, and fig. 5 is an angle formed by a bent pipe of the main combustion hole of the strong mixing type gas turbine combustion chamber and a central axis of a gas path channel of the bent pipe.
The specific process comprises the following steps: air from the outer channel reaches the outer side of the outer main combustion hole of the combustion chamber of the gas turbine at a certain speed, one part of the air enters the combustion chamber from the middle main combustion hole channel (4 in figure 2) to be further fully mixed with unburned or insufficiently combusted fuel in the main combustion chamber to carry out secondary combustion, the basic function of the main combustion hole is realized, the other part of the air enters the combustion chamber from a gas channel (2 in figure 2) of a main combustion hole elbow which is circumferentially arranged, when the air is sprayed in the elbow (1 in figure 2), the gas channel flows through the elbow and is sprayed out from the elbow, the gas flow gives a reaction force to the elbow, the gas flow of the main combustion hole elbow gas channel pipe (2 in figure 2), the front ball baffle (3 in figure 2), the rear ball baffle (5 in figure 3) and the pipe wall (6 in figure 3) of the middle main combustion hole elbow rotate as a connected whole, the rotating mechanism and the radial control ball plate are connected by the balls (8 in figure 4) to rotate, so that the airflow ejected from the bent pipe rotates, the rotating airflow is further and fully mixed with the unburned or insufficiently combusted fuel oil in the main combustion chamber to perform secondary combustion, the combustion condition is strengthened, and the combustion efficiency is improved.
Claims (6)
1. The utility model provides a gas turbine combustion chamber main combustion hole of intensive mixing which characterized in that: the gas path pipe comprises a main combustion hole bent pipe gas path pipe, a main combustion hole bent pipe gas path channel, a preposed ball baffle, a middle main combustion hole channel, a postposition ball baffle, a middle main combustion hole channel pipe wall, a radial control ball plate and balls, wherein a certain angle is formed between the central axis of a turning part of the bent pipe and the connecting line of the middle main combustion hole channel, and the bent pipe and the central axis of the bent pipe gas path channel have certain angles.
2. The main burner of a highly mixed gas turbine combustor as set forth in claim 1, wherein: the main burning hole bent pipe gas path pipe, the preposed ball baffle, the postposed ball baffle and the middle main burning hole channel pipe wall are connected into a whole.
3. The main burner of a highly mixed gas turbine combustor as set forth in claim 1, wherein: the sum of the gas channel area of the main combustion hole elbow and the middle main combustion hole channel area is larger than or equal to the area of the main combustion hole of the conventional gas turbine, but the sum of the total area of the main combustion hole and the area of the middle main combustion hole is ensured to be too large according to actual conditions.
4. The main burner of a highly mixed gas turbine combustor as set forth in claim 1, wherein: the central axis between the turning part of the elbow and the connecting line of the middle main burning hole channel has a certain angle, and the included angle is between 30 and 60 degrees.
5. The main burner of a highly mixed gas turbine combustor as set forth in claim 1, wherein: the bent pipe and the central axis of the air passage of the bent pipe are both provided with certain angles, and the included angle is 30-60 degrees.
6. The main burner of a highly mixed gas turbine combustor as set forth in claim 1, wherein: the middle main combustion hole channel is positioned in the middle of the main combustion hole, the bent pipe gas path channels are circumferentially distributed around the middle main combustion hole, and the number of the bent pipe gas path channels can be determined according to actual conditions and the processing difficulty.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110325715.4A CN112963864B (en) | 2021-03-26 | 2021-03-26 | Strong-mixing type main combustion hole of combustion chamber of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110325715.4A CN112963864B (en) | 2021-03-26 | 2021-03-26 | Strong-mixing type main combustion hole of combustion chamber of gas turbine |
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| CN112963864A true CN112963864A (en) | 2021-06-15 |
| CN112963864B CN112963864B (en) | 2022-07-12 |
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| CN202110325715.4A Active CN112963864B (en) | 2021-03-26 | 2021-03-26 | Strong-mixing type main combustion hole of combustion chamber of gas turbine |
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| CN112963864B (en) | 2022-07-12 |
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