CN111520749A - Preheating type double-oil-way opposite-impact type annular combustion chamber structure - Google Patents
Preheating type double-oil-way opposite-impact type annular combustion chamber structure Download PDFInfo
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- CN111520749A CN111520749A CN202010215626.XA CN202010215626A CN111520749A CN 111520749 A CN111520749 A CN 111520749A CN 202010215626 A CN202010215626 A CN 202010215626A CN 111520749 A CN111520749 A CN 111520749A
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- Prior art keywords
- oil
- combustion chamber
- fuel
- pipeline
- annular combustion
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
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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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/58—Cyclone or vortex type combustion chambers
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
- Spray-Type Burners (AREA)
Abstract
The invention discloses a preheating type double-oil-way opposite-flushing type annular combustion chamber structure, which can effectively improve the fuel atomization and evaporation effects of the annular combustion chamber.
Description
Technical Field
The invention relates to the field of combustion chambers of gas turbines, in particular to a preheating type double-oil-way opposite-impact type annular combustion chamber structure.
Background
In a gas turbine, a combustion chamber is provided between a compressor and a turbine, and fuel oil supplied to the combustion chamber is mixed with high-pressure air from the compressor to form a combustible mixture and is sufficiently and efficiently combusted. Through the combustion process, the chemical energy in the fuel is released and converted into heat energy, so that the temperature of the fuel gas is greatly increased. These high temperature, high pressure gases first flow through the turbine where they expand, pushing the turbine to do work, and then further expand and accelerate in the jet nozzle, thereby generating thrust.
There are three typical types of combustors, the combustor configuration chosen primarily from the two aspects of performance requirements and available port spacing for an aircraft gas turbine engine, and the three basic configurations being a single-tube combustor, a can-annular combustor, and an annular combustor, respectively. The annular combustion chamber is actually composed of 4 concentric circles, the innermost and outermost 2 cylinders are the inner and outer casings of the combustion chamber, and the middle 2 cylinders constitute the flame tube. The compact aerodynamic layout of the annular combustion chamber, in which not only two air flows are communicated but also one air flow for combustion, makes it possible to achieve a smaller pressure loss than other types of engines under the same geometrical and aerodynamic conditions. However, the annular combustion chamber was not used in early low pressure ratio engines because of the poor rigidity of the combustion chamber and the liner. By the 60's of the 20 th century, the predominant position of annular combustors was established and became a necessary choice for almost all aero gas turbines.
In order to improve the performance of a combustion chamber of a gas turbine, the internal fuel atomization effect is an important part, the fuel atomization effect determines the working performance of the combustion chamber, fuel and air are mixed completely, and the fuel is distributed uniformly in space, so that the research on fuel atomization is an important part in the research on the combustion chamber of an aeroengine. Based on the background, the invention provides a preheating type double-oil-way opposite-impact annular combustion chamber structure, which is characterized in that a fuel oil pipeline which surrounds the outer casing wall surface of a traditional annular combustion chamber for several circles is additionally arranged on the outer casing wall surface of the traditional annular combustion chamber, fuel oil flowing into the outer casing wall surface is preheated by high temperature generated by the annular combustion chamber, is primarily evaporated and then flows into a flame tube to be oppositely-impacted and mixed with fuel oil flowing into the flame tube from a nozzle at a mounting hole of a swirler, the fuel oil which is preheated and oppositely-impacted and mixed is basically a gas or supercritical body, the viscosity of the fuel oil is reduced, the diffusion capacity is enhanced, the flow capacity is greatly improved, and therefore the fuel oil can be more uniformly mixed with air flowing into the periphery of the flame tube, the fuel oil atomization effect is better, and the.
Disclosure of Invention
The invention aims to solve the technical problem of providing a preheating type double-oil-way opposite-flushing type annular combustion chamber structure, wherein a fuel oil pipeline which is wound by a plurality of circles is additionally arranged on the wall surface of an outer casing of a traditional annular combustion chamber, so that fuel oil flowing into the outer casing is preheated by high temperature generated by the annular combustion chamber, is preliminarily evaporated, then flows into a flame tube and is oppositely mixed with fuel oil flowing into the flame tube from a nozzle at a mounting hole of a swirler, and the aim of improving the combustion efficiency of the annular combustion chamber is fulfilled.
Technical scheme
The invention aims to provide a preheating type double-oil-way opposite-impact type annular combustion chamber structure.
The technical scheme of the invention is as follows:
the utility model provides a two oil circuit hedging formula annular combustion chamber structures of preheating-type which characterized in that: the annular combustion chamber comprises an outer casing, an inner casing, a flame tube, a fuel oil pipeline and a gas compressor guide vane; the fuel pipeline surrounds the surface of the outer box.
A two oil circuit offset ring combustion chamber structures of preheating-type, its characterized in that: 5-10 circles of fuel pipelines are wound around the outer box; the wall thickness of the pipeline is 10 mm-20 mm, the diameter is 30 mm-50 mm, and the fuel oil flows out from the fuel oil main pipe and flows into the fuel oil injection pipeline along the fuel oil pipeline.
A two oil circuit offset ring combustion chamber structures of preheating-type, its characterized in that: the inner diameter of the fuel injection pipeline is 30-50 mm, 12-18 oil injection holes are arranged on the pipeline, and the diameter of each oil injection hole is 5-8 mm; the number of the mounting holes of the swirler is 12-18, and the number of the mountable fuel nozzles is 12-18.
A two oil circuit offset ring combustion chamber structures of preheating-type, its characterized in that: the positions of the oil injection hole on the fuel injection pipeline and the mounting hole of the swirler are kept consistent, and no included angle exists.
The invention has the following beneficial effects:
compared with the traditional annular combustion chamber, the invention has the advantages that: the fuel oil pipeline is additionally arranged on the wall surface of an outer casing of a traditional annular combustion chamber for several circles, the fuel oil flowing into the outer casing is preheated by high temperature generated by the annular combustion chamber, is evaporated preliminarily, then flows into a flame tube and is mixed with the fuel oil flowing into the flame tube from a nozzle at a mounting hole of a swirler, the fuel oil mixed by the preheating and the opposite flushing is basically a gas or a supercritical body, the viscosity is reduced, the diffusion capacity is enhanced, the flow capacity is greatly improved, and therefore the fuel oil can be mixed with air flowing into the periphery of the flame tube through a guide vane of a gas compressor more uniformly, the fuel oil atomization effect is better, and the combustion efficiency of the annular combustion chamber is improved.
Drawings
FIG. 1: integral structure schematic diagram of preheating type double-oil-way opposite-impact type annular combustion chamber
FIG. 2: top view of preheating type double-oil-way opposite-impact type annular combustion chamber structure
FIG. 3: structure front view of preheating type double-oil-way opposite-impact type annular combustion chamber
In the figure: 1-combustion chamber outer casing, 2-combustion chamber inner casing, 3-flame tube, 4-compressor guide vane, 5-oil spray hole, 6-swirler mounting hole, 7-fuel oil main pipe, 8-fuel oil pipeline, 9-fuel oil pipeline switching part and 10-fuel oil injection pipeline
Detailed Description
The invention will now be further described with reference to the accompanying drawings in which:
referring to fig. 1, a preheating type double oil way opposite-impact annular combustion chamber structure.
The specific process comprises the following steps: the structure has two oil paths, a fuel oil pipeline (7 and 8 in figure 1) which is wound by a plurality of circles is additionally arranged on the wall surface of an outer casing (1 in figure 1) of a traditional annular combustion chamber, fuel oil flowing into the wall surface is preheated by high temperature generated by the annular combustion chamber, the fuel oil is evaporated preliminarily, flows through a transition part (9 in figure 1) of the fuel oil pipeline to enter a fuel oil injection pipeline (10 in figure 1), then flows into a flame tube (3 in figure 1) along an oil injection hole (5 in figure 1) and is mixed with fuel oil flowing into the flame tube from a nozzle at a swirler mounting hole (6 in figure 1) in an opposite-flushing manner, wherein the oil injection hole on the fuel oil injection pipeline is consistent with the position of the swirler mounting hole and has no included angle, so that the opposite-flushing mixing effect is maximized, the fuel oil mixed by preheating is basically gas or supercritical body, the viscosity is reduced, the diffusion capacity is enhanced, the flow capacity is greatly improved, and therefore, the opposite-flushing fuel oil can be mixed with air flowing into the periphery of the The fuel atomization effect is better due to the uniform addition, so that the combustion efficiency of the annular combustion chamber is improved.
Claims (4)
1. The utility model provides a two oil circuit hedging formula annular combustion chamber structures of preheating-type which characterized in that: the annular combustion chamber comprises an outer casing, an inner casing, a flame tube, a fuel oil pipeline and a gas compressor guide vane; the fuel pipeline surrounds the surface of the outer box.
2. The preheating type double-oil-way opposite-impact annular combustion chamber structure as claimed in claim 1, wherein: 5-10 circles of fuel pipelines are wound around the outer box; the wall thickness of the pipeline is 10 mm-20 mm, the diameter is 30 mm-50 mm, and the fuel oil flows out from the fuel oil main pipe and flows into the fuel oil injection pipeline along the fuel oil pipeline.
3. The preheating type double-oil-way opposite-impact annular combustion chamber structure as claimed in claim 1, wherein: the inner diameter of the fuel injection pipeline is 30-50 mm, 12-18 oil injection holes are arranged on the pipeline, and the diameter of each oil injection hole is 5-8 mm; the number of the mounting holes of the swirler is 12-18, and the number of the mountable fuel nozzles is 12-18.
4. The preheating type double-oil-way opposite-impact annular combustion chamber structure as claimed in claim 1, wherein: the positions of the oil injection hole on the fuel injection pipeline and the mounting hole of the swirler are kept consistent, and no included angle exists.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010215626.XA CN111520749A (en) | 2020-03-25 | 2020-03-25 | Preheating type double-oil-way opposite-impact type annular combustion chamber structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010215626.XA CN111520749A (en) | 2020-03-25 | 2020-03-25 | Preheating type double-oil-way opposite-impact type annular combustion chamber structure |
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| CN111520749A true CN111520749A (en) | 2020-08-11 |
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| CN202010215626.XA Pending CN111520749A (en) | 2020-03-25 | 2020-03-25 | Preheating type double-oil-way opposite-impact type annular combustion chamber structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113154451A (en) * | 2021-04-27 | 2021-07-23 | 西北工业大学 | Guide spray pipe of rotary detonation combustion chamber |
| CN113864823A (en) * | 2021-11-09 | 2021-12-31 | 滨州学院 | Turbine engine cyclic heating multistage combustion system |
| CN114562742A (en) * | 2022-02-27 | 2022-05-31 | 西北工业大学 | Fuel preheating and oil-gas ratio regulation and control integrated annular combustion chamber wall surface |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59107119A (en) * | 1982-12-10 | 1984-06-21 | Toshiba Corp | Combustion of gas turbine |
| EP2136143A1 (en) * | 2007-04-13 | 2009-12-23 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| CN105042638A (en) * | 2015-06-25 | 2015-11-11 | 中国科学院工程热物理研究所 | Two-oil-way three-air-way multi-rotational-flow air atomizing nozzle structure |
| CN106969380A (en) * | 2017-03-22 | 2017-07-21 | 同济大学 | A kind of low-nitrogen discharged combustion chamber and the gas turbine containing the combustion chamber |
| CN206478680U (en) * | 2016-12-21 | 2017-09-08 | 中国燃气涡轮研究院 | A kind of lean premixed preevaporated head of combustion chamber |
| CN108131975A (en) * | 2017-12-21 | 2018-06-08 | 中国航发南方工业有限公司 | Heat exchange type jet pipe and high temperature combustion exhaust waste heat recycle method |
| CN108758693A (en) * | 2018-04-16 | 2018-11-06 | 西北工业大学 | A kind of integrated after-burner with double oil circuits and butt center wimble structure |
| CN110715323A (en) * | 2019-10-14 | 2020-01-21 | 哈尔滨工程大学 | Rotary detonation combustor for liquid fuel |
-
2020
- 2020-03-25 CN CN202010215626.XA patent/CN111520749A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59107119A (en) * | 1982-12-10 | 1984-06-21 | Toshiba Corp | Combustion of gas turbine |
| EP2136143A1 (en) * | 2007-04-13 | 2009-12-23 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
| CN105042638A (en) * | 2015-06-25 | 2015-11-11 | 中国科学院工程热物理研究所 | Two-oil-way three-air-way multi-rotational-flow air atomizing nozzle structure |
| CN206478680U (en) * | 2016-12-21 | 2017-09-08 | 中国燃气涡轮研究院 | A kind of lean premixed preevaporated head of combustion chamber |
| CN106969380A (en) * | 2017-03-22 | 2017-07-21 | 同济大学 | A kind of low-nitrogen discharged combustion chamber and the gas turbine containing the combustion chamber |
| CN108131975A (en) * | 2017-12-21 | 2018-06-08 | 中国航发南方工业有限公司 | Heat exchange type jet pipe and high temperature combustion exhaust waste heat recycle method |
| CN108758693A (en) * | 2018-04-16 | 2018-11-06 | 西北工业大学 | A kind of integrated after-burner with double oil circuits and butt center wimble structure |
| CN110715323A (en) * | 2019-10-14 | 2020-01-21 | 哈尔滨工程大学 | Rotary detonation combustor for liquid fuel |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113154451A (en) * | 2021-04-27 | 2021-07-23 | 西北工业大学 | Guide spray pipe of rotary detonation combustion chamber |
| CN113154451B (en) * | 2021-04-27 | 2022-09-06 | 西北工业大学 | Guide spray pipe of rotary detonation combustion chamber |
| CN113864823A (en) * | 2021-11-09 | 2021-12-31 | 滨州学院 | Turbine engine cyclic heating multistage combustion system |
| CN113864823B (en) * | 2021-11-09 | 2022-08-26 | 滨州学院 | Turbine engine cyclic heating multistage combustion system |
| CN114562742A (en) * | 2022-02-27 | 2022-05-31 | 西北工业大学 | Fuel preheating and oil-gas ratio regulation and control integrated annular combustion chamber wall surface |
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Application publication date: 20200811 |
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