CN105114983A - Omega-shaped flame tube - Google Patents
Omega-shaped flame tube Download PDFInfo
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- CN105114983A CN105114983A CN201510616565.7A CN201510616565A CN105114983A CN 105114983 A CN105114983 A CN 105114983A CN 201510616565 A CN201510616565 A CN 201510616565A CN 105114983 A CN105114983 A CN 105114983A
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- cambered surface
- inner ring
- outer shroud
- inner liner
- fuel oil
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- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The invention belongs to the technical field of turbine engines, and particularly relates to an omega-shaped flame tube. The omega-shaped flame tube comprises an outer ring 3, an outer ring air hole 4, an inner ring 9, an inner ring air hole 10, a sleeve 7, a combustor box 1 and an annular gap 2, wherein a cambered surface structure a is formed on the side, facing the front end face of a combustor, of the outer ring 3, the cambered surface of the inner ring 9 is composed of a cambered surface b and a cambered surface c, and an inner ring protrusion 6 is formed between the cambered surface b and the cambered surface c; an omega-shaped structure is formed by the cambered surface a, the cambered surface b and the cambered surface c. According to the technical scheme, the omega-shaped flame tube is simple and compact in structure, good in fuel oil atomization effect and high in combustion efficiency, heat discharge intensity is over 6500 kJ/h.m<3>.Pa, and the temperature inside the flame tube is uniform. Overall tests show that a turbine engine adopting the omega-shaped flame tube has a good ignition property and a good acceleration property, and reliable and quick ignition and acceleration to the highest design point can be achieved under a wide working condition.
Description
Technical field
The invention belongs to turbogenerator technical field, be specifically related to a kind of ω type burner inner liner.
Background technology
In the annular radial axial combustor of micro turbine engine, operation principle is that the fuel oil of air and atomization enters burner inner liner, and fuel oil in burner inner liner and air burning, releases heat.Existing annular radial axial combustor is made up of casing, burner inner liner, sleeve, disc, structure as shown in Figure 1: burner inner liner is made up of outer shroud 103 and inner ring 105; Casing 101 and outer shroud 103 form outer ring cavity, and the air in outer ring cavity enters burner inner liner by the hole on outer shroud; Sleeve 106 and inner ring 105 form interior ring cavity, and the hole of air in inner ring enters burner inner liner; Fuel oil throws away from discrete oilhole by disc 102, enter burner inner liner inner region 104 be atomized and and air burning, release heat.
Existing annular radial axial combustor burner inner liner can not meet the demand of micro turbine engine.Micro turbine engine has the feature that compact conformation, low cost, part are few.Owing to limiting by complete machine structure size, existing burner inner liner can not ensure combustion oil atomization, evaporation and burn fully in very little space, cause burner efficiency low.Existing annular radial axial combustor uses discrete oilhole on disc to get rid of oil in burner inner liner, and in burner inner liner, formation temperature height point, have impact on the uniformity in temperature field in burner inner liner.
Summary of the invention
(1) technical problem that will solve
The technical problem to be solved in the present invention is: how for micro turbine engine annular radial axial combustor designs a kind of ω type burner inner liner, ensures to ensure fuel-oil atmozation quality in very little space; Ensure that fuel oil can rapid evaporation Thorough combustion in burner inner liner, ensure efficiency of combustion; Ensure the uniformity in temperature field in burner inner liner.
(2) technical scheme
In order to solve the problems of the technologies described above, the invention provides a kind of ω type burner inner liner, it comprises: outer shroud 3, outer shroud pore 4, inner ring 9, inner ring pore 10, sleeve 7, combustion box 1, annulus 2;
Wherein, combustion box 1 and outer shroud 3 form outer shroud air cavity, and sleeve 7 and inner ring 9 form inner ring air cavity; Outer shroud 3 and inner ring 9 form burner inner liner; Outer shroud 3 is distributed with outer shroud pore 4, inner ring 9 is distributed with inner ring pore 10; Air in outer shroud air cavity and inner ring air cavity enters burner inner liner by outer shroud pore 4 and inner ring pore 10, and fuel oil enters burner inner liner by annulus 2; Fuel oil and air are in burner inner liner combustion; Outer shroud 3 is formed with a globoidal structure towards direction, chamber front end face; Inner ring 9 cambered surface is made up of b cambered surface, c cambered surface, and is formed with inner ring projection 6 between b cambered surface and c cambered surface; Described a cambered surface, b cambered surface, c cambered surface form ω type structure;
Wherein, a cambered surface of outer shroud 3 and b cambered surface, the c cambered surface formation ω type structure of inner ring 9; The radian of a cambered surface is between 0.4 π-0.5 π, and radius is between 60mm-70mm, and the distance of a cambered surface left-hand point and combustion box 1 is between 100mm-110mm, and the distance of a cambered surface right-hand point and combustion box 1 is between 10mm-15mm; The radian of b cambered surface is between 0.3 π-0.4 π, and radius is between 50mm-60mm, and b cambered surface left-hand point is identical with a cambered surface left-hand point height, and horizontal range is between 50mm-60mm, and the distance of b cambered surface right-hand point and combustion box 1 is between 40mm-50mm; The radian of c cambered surface is between 0.9 π-π, and radius is between 50mm-60mm, and c cambered surface left-hand point is identical with b cambered surface right-hand point height, and horizontal range is between 10mm-15mm, and the distance of c cambered surface right-hand point and combustion box 1 is between 30mm-40mm;
This ω type structure is used for extending the time of staying in fuel oil burner inner liner, ensures that fuel oil has time enough to evaporate and burning; In ω type structure, due to the existence of inner ring projection 6, burner inner liner is divided into the primary zone 5 be made up of a cambered surface and b cambered surface and the afterburning district 8 be made up of c cambered surface, fuel oil is first in primary zone 5 combustion, then flow into afterburning district 8 and carry out afterburning, be conducive to improving efficiency of combustion; Inner ring b cambered surface and the inner ring projection 6 of c cambered surface height of formation between 20mm-30mm, inner ring projection 6 is conducive to the blending strengthening air and fuel oil, is conducive to homogeneous temperature in burner inner liner.
(3) beneficial effect
Technical solution of the present invention structure is simple, compact, and fuel atomization effect is good, and efficiency of combustion is high, and intensity reaches more than 6500kJ/hm3Pa, homogeneous temperature in burner inner liner.Overall test shows, the turbogenerator adopting this to invent has good igniting, accelerating performance, reliable under very wide operating mode, Quick-Point can fight and accelerate to the highest design point.
Accompanying drawing explanation
Fig. 1 is the structural representation of prior art.
Fig. 2 is ω type flame tube structure figure provided by the present invention.
Detailed description of the invention
For making object of the present invention, content and advantage clearly, below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.
In order to solve prior art problem, the invention provides a kind of ω type burner inner liner, it comprises: outer shroud 3, outer shroud pore 4, inner ring 9, inner ring pore 10, sleeve 7, combustion box 1, annulus;
Wherein, as shown in Figure 2, combustion box 1 and outer shroud 3 form outer shroud air cavity, and sleeve 7 and inner ring 9 form inner ring air cavity; Outer shroud 3 and inner ring 9 form burner inner liner; Outer shroud 3 is distributed with outer shroud pore 4, inner ring 9 is distributed with inner ring pore 10; Air in outer shroud air cavity and inner ring air cavity enters burner inner liner by outer shroud pore 4 and inner ring pore 10, and fuel oil enters burner inner liner by annulus 2; Fuel oil and air are in burner inner liner combustion; Outer shroud 3 is formed with a globoidal structure towards direction, chamber front end face; Inner ring 9 cambered surface is made up of b cambered surface, c cambered surface, and is formed with inner ring projection 6 between b cambered surface and c cambered surface; Described a cambered surface, b cambered surface, c cambered surface form ω type structure;
Wherein, a cambered surface of outer shroud 3 and b cambered surface, the c cambered surface formation ω type structure of inner ring 9; The radian of a cambered surface is between 0.4 π-0.5 π, and radius is between 60mm-70mm, and the distance of a cambered surface left-hand point and combustion box 1 is between 100mm-110mm, and the distance of a cambered surface right-hand point and combustion box 1 is between 10mm-15mm; The radian of b cambered surface is between 0.3 π-0.4 π, and radius is between 50mm-60mm, and b cambered surface left-hand point is identical with a cambered surface left-hand point height, and horizontal range is between 50mm-60mm, and the distance of b cambered surface right-hand point and combustion box 1 is between 40mm-50mm; The radian of c cambered surface is between 0.9 π-π, and radius is between 50mm-60mm, and c cambered surface left-hand point is identical with b cambered surface right-hand point height, and horizontal range is between 10mm-15mm, and the distance of c cambered surface right-hand point and combustion box 1 is between 30mm-40mm;
This ω type structure is used for extending the time of staying in fuel oil burner inner liner, ensures that fuel oil has time enough to evaporate and burning; In ω type structure, due to the existence of inner ring projection 6, burner inner liner is divided into the primary zone 5 be made up of a cambered surface and b cambered surface and the afterburning district 8 be made up of c cambered surface, fuel oil is first in primary zone 5 combustion, then flow into afterburning district 8 and carry out afterburning, be conducive to improving efficiency of combustion; A low speed recirculating zone can be formed in afterburning district 8, in order to stabilize the flame, prevent from stopping working; Inner ring b cambered surface and the inner ring projection 6 of c cambered surface height of formation between 20mm-30mm, inner ring projection 6 is conducive to the blending strengthening air and fuel oil, is conducive to homogeneous temperature in burner inner liner; Fuel oil enters burner inner liner by annulus 2, and annulus 2 is continuous print annulars, is conducive to temperature homogeneity in burner inner liner.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the technology of the present invention principle; can also make some improvement and distortion, these improve and distortion also should be considered as protection scope of the present invention.
Claims (1)
1. a ω type burner inner liner, it is characterized in that, it comprises: outer shroud (3), outer shroud pore (4), inner ring (9), inner ring pore (10), sleeve (7), combustion box (1), annulus (2);
Wherein, combustion box (1) and outer shroud (3) form outer shroud air cavity, and sleeve (7) and inner ring (9) form inner ring air cavity; Outer shroud (3) and inner ring (9) composition burner inner liner; Outer shroud (3) is distributed with outer shroud pore (4), inner ring (9) is distributed with inner ring pore (10); Air in outer shroud air cavity and inner ring air cavity enters burner inner liner by outer shroud pore (4) and inner ring pore (10), and fuel oil passes through annulus (2) and enters burner inner liner; Fuel oil and air are in burner inner liner combustion; Outer shroud (3) is formed with a globoidal structure towards direction, chamber front end face; Inner ring (9) cambered surface is made up of b cambered surface, c cambered surface, and is formed with inner ring projection (6) between b cambered surface and c cambered surface; Described a cambered surface, b cambered surface, c cambered surface form ω type structure;
Wherein, a cambered surface of outer shroud (3) and b cambered surface, the c cambered surface formation ω type structure of inner ring (9); The radian of a cambered surface is between 0.4 π-0.5 π, radius is between 60mm-70mm, the distance of a cambered surface left-hand point and combustion box (1) is between 100mm-110mm, and the distance of a cambered surface right-hand point and combustion box (1) is between 10mm-15mm; The radian of b cambered surface is between 0.3 π-0.4 π, radius is between 50mm-60mm, b cambered surface left-hand point is identical with a cambered surface left-hand point height, and horizontal range is between 50mm-60mm, and the distance of b cambered surface right-hand point and combustion box (1) is between 40mm-50mm; The radian of c cambered surface is between 0.9 π-π, radius is between 50mm-60mm, c cambered surface left-hand point is identical with b cambered surface right-hand point height, and horizontal range is between 10mm-15mm, and the distance of c cambered surface right-hand point and combustion box (1) is between 30mm-40mm;
This ω type structure is used for extending the time of staying in fuel oil burner inner liner, ensures that fuel oil has time enough to evaporate and burning; In ω type structure, due to the existence of inner ring projection (6), burner inner liner is divided into the primary zone (5) be made up of a cambered surface and b cambered surface and the afterburning district (8) be made up of c cambered surface, fuel oil is first in primary zone (5) combustion, then flow into afterburning district (8) and carry out afterburning, be conducive to improving efficiency of combustion; Inner ring b cambered surface and the c cambered surface height of formation inner ring projection (6) between 20mm-30mm, inner ring projection (6) is conducive to the blending strengthening air and fuel oil, is conducive to homogeneous temperature in burner inner liner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510616565.7A CN105114983B (en) | 2015-09-24 | 2015-09-24 | A kind of ω types burner inner liner |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510616565.7A CN105114983B (en) | 2015-09-24 | 2015-09-24 | A kind of ω types burner inner liner |
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| CN105114983A true CN105114983A (en) | 2015-12-02 |
| CN105114983B CN105114983B (en) | 2017-12-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510616565.7A Active CN105114983B (en) | 2015-09-24 | 2015-09-24 | A kind of ω types burner inner liner |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108167864A (en) * | 2017-11-20 | 2018-06-15 | 北京动力机械研究所 | Burner inner liner and high-pressure turbine guider integral structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080019828A1 (en) * | 2006-07-19 | 2008-01-24 | Snecma | System for ventilating a combustion chamber wall in a turbomachine |
| CN201251198Y (en) * | 2008-07-03 | 2009-06-03 | 中国航空动力机械研究所 | Gas turbine combustor |
| CN102384489A (en) * | 2011-06-28 | 2012-03-21 | 北京动力机械研究所 | Small-sized annular combustion chamber with high-capacity heat intensity |
| CN102967465A (en) * | 2012-12-07 | 2013-03-13 | 北京动力机械研究所 | Fuel chamber virtual test method and system |
| CN104879324A (en) * | 2015-05-21 | 2015-09-02 | 中国南方航空工业(集团)有限公司 | Engine air cooling system |
-
2015
- 2015-09-24 CN CN201510616565.7A patent/CN105114983B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080019828A1 (en) * | 2006-07-19 | 2008-01-24 | Snecma | System for ventilating a combustion chamber wall in a turbomachine |
| CN201251198Y (en) * | 2008-07-03 | 2009-06-03 | 中国航空动力机械研究所 | Gas turbine combustor |
| CN102384489A (en) * | 2011-06-28 | 2012-03-21 | 北京动力机械研究所 | Small-sized annular combustion chamber with high-capacity heat intensity |
| CN102967465A (en) * | 2012-12-07 | 2013-03-13 | 北京动力机械研究所 | Fuel chamber virtual test method and system |
| CN104879324A (en) * | 2015-05-21 | 2015-09-02 | 中国南方航空工业(集团)有限公司 | Engine air cooling system |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108167864A (en) * | 2017-11-20 | 2018-06-15 | 北京动力机械研究所 | Burner inner liner and high-pressure turbine guider integral structure |
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| CN105114983B (en) | 2017-12-12 |
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