CN109140501B - Double-oil-way double-nozzle centrifugal nozzle structure with double-layer air hood - Google Patents
Double-oil-way double-nozzle centrifugal nozzle structure with double-layer air hood Download PDFInfo
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- CN109140501B CN109140501B CN201710504591.XA CN201710504591A CN109140501B CN 109140501 B CN109140501 B CN 109140501B CN 201710504591 A CN201710504591 A CN 201710504591A CN 109140501 B CN109140501 B CN 109140501B
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- gas hood
- oil filter
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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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- 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
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- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Abstract
The invention belongs to a double-oil-way double-nozzle centrifugal nozzle structure with a double-layer gas hood of an aircraft engine. The assembly relation is as follows: the nozzle shell is connected with the bushing with the threaded oil filter in a welding way, and the auxiliary oil filter is arranged in the bushing with the threaded oil filter; the swirler and the nozzle-swirler are connected into a whole through threads, and then are screwed into the bushing with the threaded oil filter through threads and are locked by a locking ring; the inner gas cover and the outer gas cover are welded into a whole and then welded with the main oil way nozzle to form the nozzle with the double-layer gas cover, and finally the component is welded with the nozzle shell. The nozzle structure is characterized by a double-layer gas hood structure which is formed by brazing an inner gas hood and an outer gas hood, wherein the outer gas hood is provided with a plurality of phi 0.7 uniformly distributed straight holes, the inner gas hood is provided with a plurality of phi 0.7 uniformly distributed straight holes, a plurality of phi 1.4 uniformly distributed inclined holes and a plurality of phi 1.2 uniformly distributed inclined holes.
Description
Technical Field
The invention belongs to a double-oil-way double-nozzle centrifugal nozzle structure with an air hood for a fuel main pipe of a combustion chamber of an aero-engine.
Background
An aircraft engine nozzle is one of the key components of a combustion chamber. When the engine works, fuel oil is conveyed to the nozzle through the fuel oil regulator, atomized through the nozzle and then enters the combustion chamber for combustion, and therefore chemical energy of the fuel oil is converted into heat energy.
During the operation of the engine, the fuel atomization quality and the fuel concentration distribution obviously affect the performance of the combustion chamber, and the combustion stability is related, so that the thrust, the fuel consumption rate and the safety and the economical efficiency of the operation of the engine are affected. Poor quality of fuel atomization, uneven spray concentration distribution, and improper spray cone angle, will directly affect the life of the combustion chamber and turbine, and pollutant emissions. The oil drops are large and hit the wall surface to cause overheating and coking of the oil drops, the combustion time is long, the efficiency is low, the ignition is difficult, the exhaust smoke is generated, the exhaust pollutants are increased, and the like. The spray cone angle is too large, and oil drops hit the wall surface of the head of the flame tube, so that local overheating and ablation of the wall surface can be caused; the spray cone angle is too small, so that more oil drops are concentrated in the center of the flame tube to burn, the center is too rich in oil, the burning is incomplete, the smoke is easy to generate, and the hot spot temperature of a temperature field is high. In addition, because the temperature of the working environment of the nozzle is very high, when the temperature of fuel oil exceeds 150 ℃, coking is easily formed on the inner surface of a pipeline and in a flow passage of the nozzle, which can cause the blockage of a fuel oil passage and influence the fluidity and the atomization quality of the nozzle, thereby influencing the combustion performance of a combustion chamber and the like.
Therefore, the advantages and disadvantages of the fuel nozzle structure directly affect the operating performance of the aircraft engine.
Disclosure of Invention
The purpose of the invention is:
because the temperature of the working environment of the nozzle is very high, when the temperature of fuel oil exceeds 150 ℃, coking is easily formed on the inner surface of a pipeline and in a flow passage of the nozzle, which can cause the blockage of a fuel oil passage, influence the fluidity and the atomization quality of the nozzle, and further influence the combustion performance of a combustion chamber and the like. Therefore, the nozzle is designed into a double-layer gas hood structure form, and the coking and carbon deposition phenomena are improved.
The technical scheme is as follows:
through the conception, the technical scheme is obtained, and the double-oil-way double-nozzle centrifugal nozzle structure with the double-layer air hood is provided.
The nozzle structure includes: the nozzle comprises a nozzle shell (1), a bushing (2) with a threaded oil filter, an auxiliary oil filter (3), a swirler (4), a locking ring (5), a nozzle-swirler (6), a main oil way nozzle (7), an inner gas cover (8) and an outer gas cover (9).
The assembly relationship is as follows: the nozzle shell (1) is connected with the bushing (2) with the threaded oil filter in a welding manner, and the auxiliary oil filter (3) is arranged in the bushing (2) with the threaded oil filter; the swirler (4) and the nozzle-swirler (6) are connected into a whole through threads, and then are screwed into the bushing (2) with the threaded oil filter through threads and are locked by a locking ring (5); the inner gas cover (8) and the outer gas cover (9) are welded into a whole and then welded with the main oil way nozzle (7) to form a nozzle with a double-layer gas cover, and finally the assembly is welded with the nozzle shell (1). The outer gas hood is provided with a plurality of uniformly distributed straight holes, a plurality of uniformly distributed inclined holes are formed in the horizontal section of the inner gas hood, and a plurality of uniformly distributed inclined holes and a plurality of straight holes are formed in the outlet section of the inner gas hood. The size and the number of the uniformly distributed straight holes and the inclined holes are determined according to the size of the required air inflow.
Description of the drawings:
FIG. 1 is a nozzle structure of a double-oil-way double-nozzle centrifugal type with double-layer air hood
FIG. 2 is a schematic view of a double-layer gas hood
1-nozzle shell 2-bushing with thread oil filter 3-auxiliary oil filter 4-swirler 5-locking ring 6-nozzle-swirler 7-main oil way nozzle 8-inner air cover 9-outer air cover
Detailed Description
The present invention is described in further detail below.
The main parts of the double-oil-way double-nozzle centrifugal structure comprise a nozzle shell (1), a bushing (2) with a threaded oil filter, an auxiliary oil filter (3), a swirler (4), a locking ring (5), a nozzle-swirler (6), a main oil-way nozzle (7), an inner gas cover (8) and an outer gas cover (9). The path of the fuel through the primary and secondary fuel passages is shown in figure 1. When the fuel oil filter works, fuel oil in a main oil way firstly passes through the bushing (2) with the thread oil filter, is filtered through threads, then passes through a swirl groove on the nozzle-swirler (6), is swirled, and finally is sprayed out through the nozzle (7) of the main oil way; the fuel oil in the auxiliary oil way firstly passes through the auxiliary oil filter (3), is filtered through threads of the auxiliary oil filter, then passes through the swirl groove on the swirler (4) to swirl the fuel oil, and finally is sprayed out through the nozzle-swirler (6). The fuel oil of the main and auxiliary oil ways generates rotational flow under the centrifugal action of the rotational flow grooves, a hollow diffusion conical oil film is sprayed out in the convergence channel at an accelerated speed, and finally the fuel oil is crushed and atomized under the action of air for combustion.
The structure of the double-layer gas hood comprises an outer gas hood and an inner gas hood, wherein the outer gas hood is provided with a plurality of phi 0.7 uniformly distributed straight holes, the inner gas hood is provided with a plurality of phi 0.7 uniformly distributed straight holes, a plurality of phi 1.4 uniformly distributed inclined holes and a plurality of phi 1.2 uniformly distributed inclined holes, and the inner gas hood and the outer gas hood are formed in a brazing mode which is convenient to operate and can not cause deformation to small parts. The size and the number of the uniformly distributed straight holes and the uniformly distributed inclined holes are determined according to the size of the required air inflow.
The double-layer gas hood structure not only optimizes the airflow channel, but also strengthens the effect of blowing off the carbon deposit, solves the problem that the fuel oil is easy to form coking on the inner surface of the pipeline and in the flow channel of the nozzle at high temperature, and improves the fluidity, the atomization quality and the combustion performance of the nozzle.
Claims (1)
1. A double-oil-way double-nozzle centrifugal nozzle structure with a double-layer air cover comprises: the oil filter comprises a nozzle shell (1), a bushing (2) with a threaded oil filter, an auxiliary oil filter (3), a swirler (4), a locking ring (5), a nozzle-swirler (6), a main oil way nozzle (7), an inner gas cover (8) and an outer gas cover (9); the nozzle shell (1) is connected with the bushing (2) with the threaded oil filter in a welding manner, and the auxiliary oil filter (3) is arranged in the bushing (2) with the threaded oil filter; the swirler (4) and the nozzle-swirler (6) are connected into an integral structure through threads, and the integral structure is screwed into the bushing (2) with the threaded oil filter through threads and is locked by a locking ring (5); the method is characterized in that: the inner gas hood (8) and the outer gas hood (9) are welded into a whole and then welded with the main oil way nozzle (7) to form a nozzle with a double-layer gas hood, and finally the nozzle of the double-layer gas hood is welded with the nozzle shell (1); the outer gas hood (9) is provided with a plurality of uniformly distributed straight holes, a plurality of uniformly distributed inclined holes are formed in the horizontal section of the inner gas hood (8), and a plurality of uniformly distributed inclined holes and a plurality of uniformly distributed straight holes are formed in the outlet section of the inner gas hood (8); the size and the number of the uniformly distributed straight holes and the inclined holes are determined by the size of the required air inflow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710504591.XA CN109140501B (en) | 2017-06-28 | 2017-06-28 | Double-oil-way double-nozzle centrifugal nozzle structure with double-layer air hood |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710504591.XA CN109140501B (en) | 2017-06-28 | 2017-06-28 | Double-oil-way double-nozzle centrifugal nozzle structure with double-layer air hood |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109140501A CN109140501A (en) | 2019-01-04 |
| CN109140501B true CN109140501B (en) | 2021-04-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710504591.XA Active CN109140501B (en) | 2017-06-28 | 2017-06-28 | Double-oil-way double-nozzle centrifugal nozzle structure with double-layer air hood |
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| CN (1) | CN109140501B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111055051A (en) * | 2019-12-27 | 2020-04-24 | 成立航空技术有限公司 | Device and method for debugging flow of multi-nozzle welding assembly |
| CN111828963B (en) * | 2020-06-05 | 2022-11-22 | 安徽工程大学 | Fuel nozzle mechanism with double-channel rotational flow structure |
| CN111828962B (en) * | 2020-06-05 | 2022-11-22 | 安徽工程大学 | Double-channel rotational flow fuel nozzle with carbon deposition prevention function |
| CN111829010B (en) * | 2020-06-05 | 2022-03-08 | 安徽工程大学 | Carbon deposition prevention fuel spray cap |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2390150A (en) * | 2002-06-26 | 2003-12-31 | Alstom | Reheat combustion system for a gas turbine including an accoustic screen |
| CN201697162U (en) * | 2010-05-05 | 2011-01-05 | 中国航空工业集团公司沈阳发动机设计研究所 | Carbon deposit prevention liquid fuel nozzle for gas turbine |
| CN103134079B (en) * | 2011-11-30 | 2014-12-17 | 贵州航空发动机研究所 | Double-oil-circuit fuel nozzle |
| CN204513465U (en) * | 2015-03-27 | 2015-07-29 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of head of combustion chamber structure strengthening cooling |
| CN105783032A (en) * | 2016-05-18 | 2016-07-20 | 贵州航空发动机研究所 | Wide-range fuel oil nozzle suitable for overhead work |
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- 2017-06-28 CN CN201710504591.XA patent/CN109140501B/en active Active
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| CN109140501A (en) | 2019-01-04 |
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