CN111520755A - Low-pollution combustor head swirler structure - Google Patents
Low-pollution combustor head swirler structure Download PDFInfo
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- CN111520755A CN111520755A CN202010184717.1A CN202010184717A CN111520755A CN 111520755 A CN111520755 A CN 111520755A CN 202010184717 A CN202010184717 A CN 202010184717A CN 111520755 A CN111520755 A CN 111520755A
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- swirler
- vane
- fuel oil
- oil
- low
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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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The invention provides a low-pollution combustor head swirler structure, which comprises: single stage axial swirler and its internal structure. The fuel cavity is arranged inside the single-stage axial swirler blade, the fuel injection groove is arranged at the tail part of the swirler blade, the fuel passage is connected with the fuel injection groove at the tail part of the blade, fuel enters the fuel passage inside the swirler blade from the oil inlet groove on the wall surface of the nozzle mounting hole at the center of the swirler, and then the fuel is sprayed out from the convergent-divergent fuel injection groove at the tail part of the swirler blade.
Description
Technical Field
The invention belongs to the field of gas turbine engines, and particularly relates to a low-pollution combustor head swirler structure.
Background
In the design of the combustion chamber of the aero-engine, the main combustion chamber is the heart of the engine and is one of three large core components of the aero-engine, and the performance of the main combustion chamber directly determines the overall performance of the aero-engine. In response to the development of the performance of the future aircraft, the modern aircraft engine needs to have a higher thrust-weight ratio, a lower fuel consumption, a higher reliability and a lower life-cycle cost, and therefore, a high-pressure high-performance combustion chamber with high combustion efficiency, small pressure loss, reliable ignition and combustion stability, long service life, low emission, high outlet temperature and uniform distribution is urgently required to be designed and developed.
At present, in order to improve the combustion performance of an engine combustion chamber and increase the stable working range of the engine combustion chamber, and enable the combustion chamber to have the characteristics of efficient combustion, small pressure loss, good atomization and mixing characteristics and the like, the key point is how to improve the head combustion organization structure of the combustion chamber, and the head structure and the fuel atomization mode of the combustion chamber have decisive effects on fuel atomization, oil-gas mixing and combustion processes. Swirl combustion technology is widely used in gas turbine combustors to establish proper flow structure and achieve good organization of the combustion process and combustor performance. A staged and zoned combustion scheme is widely adopted in the current high-performance gas turbine combustion chamber, so that high-performance combustion and low-pollution emission under different powers are realized.
In addition to meeting the requirements of combustion performance and low pollution emission, the combustion chamber of the aircraft engine is in a high-temperature and high-pressure working state for a long time, and the severe working environment can generate great harm to structures such as a fuel nozzle, a venturi and the like, such as nozzle overheating ablation and venturi carbon deposition. Therefore, a new type of combustion chamber head is needed, which can achieve the required combustion state, and simultaneously has a certain protection effect on each part structure of the combustion chamber head and reduces the emission of pollutants.
Disclosure of Invention
The invention aims to solve the technical problem of providing a low-pollution combustor head swirler structure, and compared with the prior art, the scheme has the advantages that the mixing degree of a swirler for fuel oil and incoming gas is further enhanced through the targeted design of the combustor head swirler structure, so that the fuel oil atomization effect is enhanced, the combustion efficiency is improved, the fuel oil flow channel design is carried out in the swirler, and the combustion efficiency is improved, the combustion temperature is reduced, and the pollution emission is reduced through the mode that the fuel oil is sprayed out from the swirler vanes.
Technical scheme
The invention aims to provide a low-pollution combustor head swirler structure.
The technical scheme of the invention is as follows:
a low pollution combustor head swirler structure comprising: single stage axial swirler and its internal structure. The method is characterized in that: the fuel oil enters the fuel oil channel inside the swirler vane from the oil inlet groove on the wall surface of the nozzle mounting hole in the center of the swirler and then is sprayed out from the oil spraying groove.
The low-pollution combustor head swirler structure is characterized in that: the swirler is a single-stage axial swirler, the mounting angle of the swirler vanes is 30 degrees to 60 degrees, the number of the vanes is 8 to 24, the thickness of the vanes is 0.7 to 1.5mm, and the swirl strength is 0.7 to 1.5.
The low-pollution combustor head swirler structure is characterized in that: the cross section of the oil inlet groove on the wall surface of the mounting hole of the central nozzle of the swirler is the same as that of the swirler vane, the oil inlet groove is connected with a fuel oil cavity inside the vane, the cross section width of the oil inlet groove is 1/3-2/3 of the vane width, the cross section length is 1/5-1/4 of the axial length of the swirler vane, and the depth of the oil inlet groove is 1/6-1/4 of the radial length of the swirler vane.
The low-pollution combustor head swirler structure is characterized in that: the width of a fuel oil cavity in the swirler vane is the same as that of the oil inlet groove, the axial length of the fuel oil cavity is 2/3-3/4 of the axial length of the swirler vane, the radial length of the fuel oil cavity is 1/2-3/4 of the radial length of the swirler vane, and the tail of the fuel oil cavity is connected with the oil spray groove.
The low-pollution combustor head swirler structure is characterized in that: the oil injection groove is positioned at the tail part of the swirler vane, the cross section of the passage of the oil injection groove is in a convergent-divergent shape and is connected with a fuel oil cavity in the swirler vane, the radial length of the oil injection groove is the same as that of the fuel oil cavity, and the width of the outlet of the oil injection groove is 1/4-1/3 of the width of the swirler vane.
The invention has the following beneficial effects:
according to the low-pollution combustor head swirler structure, fuel oil enters the swirler and is sprayed out through the convergent-divergent oil spraying grooves at the tail parts of the swirler vanes, the structure can greatly reduce the weight of the combustor head swirler, has a larger fuel oil spraying range, can improve the mixing degree of the fuel oil and incoming gas, improves the fuel oil combustion efficiency, reduces the combustion temperature, reduces the pollution emission of a combustion chamber, and enables an airplane to be suitable for a large flight envelope range.
Drawings
FIG. 1: low-pollution combustor head swirler structure overall structure sketch map
FIG. 2: low-pollution combustor head swirler structure swirler vane internal structure sketch map
In the figure: 1-cyclone, 2-oil inlet groove, 3-fuel oil cavity, 4-oil spray groove
Detailed Description
The invention will now be further described with reference to the accompanying drawings in which:
with reference to fig. 1 and 2, the present invention provides a low pollution combustor head swirler structure. Fig. 1 is a schematic structural diagram of an overall structure of a head swirler of a low-pollution combustion chamber, and fig. 2 is a schematic structural diagram of an internal structure of a swirler vane of the head swirler of the low-pollution combustion chamber.
As shown in figures 1 and 2, fuel oil enters a fuel oil cavity (3) in the swirler through an oil inlet groove (2) on the central side wall surface of the swirler (1), and in the fuel oil cavity (3), the fuel oil is preheated by high-temperature fuel gas and then is sprayed into a combustion chamber through a convergent-divergent oil spraying groove (4) connected with the tail part of the fuel oil cavity (3) to participate in combustion. The structure greatly increases the space range of fuel oil participating in combustion, improves the mixing degree of the fuel oil and the incoming air, can effectively improve the combustion efficiency of the fuel oil, enables the engine to adapt to a larger airplane flight envelope, and improves the performance of the engine.
Claims (5)
1. A low pollution combustor head swirler structure comprising: single-stage axial swirler and inner structure thereof, its characterized in that: the fuel oil enters the fuel oil channel inside the swirler vane from the oil inlet groove on the wall surface of the nozzle mounting hole in the center of the swirler and then is sprayed out from the oil spraying groove.
2. The swirler structure of a low-pollution combustion chamber as claimed in claim 1, wherein: the swirler is a single-stage axial swirler, the mounting angle of the swirler vanes is 30 degrees to 60 degrees, the number of the vanes is 8 to 24, the thickness of the vanes is 0.7 to 1.5mm, and the swirl strength is 0.7 to 1.5.
3. The swirler structure of a low-pollution combustion chamber as claimed in claim 1, wherein: the cross section of the oil inlet groove on the wall surface of the mounting hole of the central nozzle of the swirler is the same as that of the swirler vane, the oil inlet groove is connected with a fuel oil cavity inside the vane, the cross section width of the oil inlet groove is 1/3-2/3 of the vane width, the cross section length is 1/5-1/4 of the axial length of the swirler vane, and the depth of the oil inlet groove is 1/6-1/4 of the radial length of the swirler vane.
4. The low pollution combustor head swirler structure of claim 1, wherein: the width of a fuel oil cavity in the swirler vane is the same as that of the oil inlet groove, the axial length of the fuel oil cavity is 2/3-3/4 of the axial length of the swirler vane, the radial length of the fuel oil cavity is 1/2-3/4 of the radial length of the swirler vane, and the tail of the fuel oil cavity is connected with the oil spray groove.
5. The swirler structure of a low-pollution combustion chamber as claimed in claim 1, wherein: the oil injection groove is positioned at the tail part of the swirler vane, the cross section of the passage of the oil injection groove is in a convergent-divergent shape and is connected with a fuel oil cavity in the swirler vane, the radial length of the oil injection groove is the same as that of the fuel oil cavity, and the width of the outlet of the oil injection groove is 1/4-1/3 of the width of the swirler vane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010184717.1A CN111520755A (en) | 2020-03-17 | 2020-03-17 | Low-pollution combustor head swirler structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010184717.1A CN111520755A (en) | 2020-03-17 | 2020-03-17 | Low-pollution combustor head swirler structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111520755A true CN111520755A (en) | 2020-08-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010184717.1A Pending CN111520755A (en) | 2020-03-17 | 2020-03-17 | Low-pollution combustor head swirler structure |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5122033A (en) * | 1990-11-16 | 1992-06-16 | Paul Marius A | Turbine blade unit |
| CN105066173A (en) * | 2015-06-18 | 2015-11-18 | 上海发电设备成套设计研究院 | Axial swirler with fuel injection hole |
| CN106322436A (en) * | 2016-11-11 | 2017-01-11 | 厦门大学 | Micro-channel regenerative cooling micro-combustor |
| CN109539311A (en) * | 2018-11-13 | 2019-03-29 | 西北工业大学 | A kind of axial swirler structure with oil injection structure blade |
| CN109539313A (en) * | 2018-11-08 | 2019-03-29 | 西北工业大学 | A kind of head of combustion chamber that V-shaped groove is matched with cyclone |
| CN109539314A (en) * | 2018-11-14 | 2019-03-29 | 西北工业大学 | A kind of novel radial swirler with wave blade |
-
2020
- 2020-03-17 CN CN202010184717.1A patent/CN111520755A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5122033A (en) * | 1990-11-16 | 1992-06-16 | Paul Marius A | Turbine blade unit |
| CN105066173A (en) * | 2015-06-18 | 2015-11-18 | 上海发电设备成套设计研究院 | Axial swirler with fuel injection hole |
| CN106322436A (en) * | 2016-11-11 | 2017-01-11 | 厦门大学 | Micro-channel regenerative cooling micro-combustor |
| CN109539313A (en) * | 2018-11-08 | 2019-03-29 | 西北工业大学 | A kind of head of combustion chamber that V-shaped groove is matched with cyclone |
| CN109539311A (en) * | 2018-11-13 | 2019-03-29 | 西北工业大学 | A kind of axial swirler structure with oil injection structure blade |
| CN109539314A (en) * | 2018-11-14 | 2019-03-29 | 西北工业大学 | A kind of novel radial swirler with wave blade |
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Application publication date: 20200811 |