CN100443805C - Evaporation pipe type miniature-small-sized engine combustion chamber - Google Patents
Evaporation pipe type miniature-small-sized engine combustion chamber Download PDFInfo
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- CN100443805C CN100443805C CNB2005100865394A CN200510086539A CN100443805C CN 100443805 C CN100443805 C CN 100443805C CN B2005100865394 A CNB2005100865394 A CN B2005100865394A CN 200510086539 A CN200510086539 A CN 200510086539A CN 100443805 C CN100443805 C CN 100443805C
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- evaporation tube
- sized engine
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Abstract
The present invention relates to an evaporation tube type miniature-small-sized engine combustion chamber. The present invention is composed of the inner wall and the outer wall of a flame tube of the combustion chamber, T-shaped evaporation tubes of which the number is 3 to 12, a fuel nozzle. The T-shaped evaporation tubes of which the number is 3 to 12 are uniform arranged along the front end wall of the flame tube of the combustion chamber in a peripheral direction. The fuel nozzles of which the number is 3 to 12 are inserted into the T-shaped evaporating tubes of which the number is 3 to 12 along a radial direction. A plurality of holes are arranged on the inner wall, the outer wall and the front end wall of the flame tube of the combustion chamber. Air goes into the combustion chamber from the inner wall, the outer wall and the front end wall of the flame tube. Tangential air intake is used to form a large stable vortex at the head part of the flame tube. The present invention makes air more uniformly mixed and combustion more stable, and adopts a stable big vortex flame. The combustion organization of a main combustion region is limited by the size of a fine generating combustion chamber. The overall design of the present invention makes the main combustion region of the combustion chamber ahead to shorten the length of the combustion chamber.
Description
Affiliated technical field
The present invention relates to a kind of microminiature aeroengine combustor buring system, particularly evaporation pipe type miniature-small-sized engine combustion chamber.
Background technology
At present, carried out number of research projects for the microminiature engine abroad, and obtained a large amount of achievements, the corresponding ripe model that produces each magnitude has formed suitable military affairs, commercial market.Holland AMT, Britain Rolls-Royce, Artesjet etc. have a series of product, as Mercury HP and the Pegasus HP of AMT, and the KJ66 of Artesjet etc.The structure of the small engine chamber of certain type as shown in Figure 1, form by chamber front end wall 1, burner inner liner inwall 4, wall burner inner liner outer wall 3, evaporation tube 2 and fuel nozzle 5, wherein evaporation tube 2 is positioned at the middle part of combustion chamber flame drum by a plurality of Γ type evaporation tubes, fuel nozzle 5 adopts direct-injection type, from the air inlet of burner inner liner front end, adopt the little jet of multiply with the retention flame at the burner inner liner head.A plurality of Γ type evaporation tubes are welded in the burner inner liner front bulkhead, and the direct-injection type fuel nozzle sprays into fuel oil in the Γ type evaporation tube vertically, and axially nearly gas is adopted in this combustion chamber, and the evaporation rate of evaporation tube is low, causes this combustion chambers burn efficient low; After this primary zone, combustion chamber was leaned on, the retention flame mode of the little jet of multiply caused flame long partially.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of tissue burning efficient, stable in limited space is provided, solve the evaporation pipe type miniature-small-sized engine combustion chamber of the contradiction between labyrinth and chamber performance.
Technical solution of the present invention: evaporation pipe type miniature-small-sized engine combustion chamber, its characteristics are: it is by the combustion chamber flame drum inner and outer wall, 3-12 T type evaporation tube, fuel nozzle is formed, 3-12 T type evaporation tube is circumferentially evenly distributed along the front bulkhead of combustion chamber flame drum, 3-12 fuel nozzle radially is inserted in 3-12 the T type evaporation tube, at the combustion chamber flame drum inwall, (number in the hole of burner inner liner outer wall is 50-70 to be equipped with a plurality of holes on outer wall and the front bulkhead, the number of front end cinclides is 50-70), air is from the combustion chamber flame drum inwall, outer wall and front bulkhead enter the combustion chamber, utilize tangential admission to form at the burner inner liner head and stablize big whirlpool.
Slight curving crosspiece that described T type evaporation tube joins by the inducer that is positioned at the middle part, with inducer and two outlets and the structure that is positioned at two outlet section formed shapes similar " T " at two ends, external diameter is identical in each section, two outlet section exit portion bands close up, and crosspiece forms an angle for cooperating primary zone two parts.
When being distributed in conceptual design, burner inner liner tolerance vertically provides by empirical relation according to this combustion chamber each several part tolerance function, general rule is: it is 15-20% that tolerance is assigned as head tolerance, primary holes tolerance is 13-18%, interlude and blending section are 62-70%, head tolerance and the primary holes tolerance of half are participated in the primary zone burning directly, primary holes tolerance of half and interlude tolerance are the afterburning effect in addition, remaining tolerance blending combustion gas, make high-temperature fuel gas form suitable Temperature Distribution in the exit, the range of distribution of this tolerance is determined according to the design point fuel consumption, the size and the quantity in each round footpath of decision on this scope basis.
Described fuel nozzle is the little tubule of end sealing, opens the oil outlet of some on the distolateral wall of one, forms radial spray.
Operation principle of the present invention is: fuel oil is from fuel nozzle in the spirt T type evaporation tube, mix with the air in the T type evaporation tube, this gas mixture sprays in the combustion chamber flame drum, again and spray the air of coming in from the inside and outside wall of combustion chamber flame drum and front bulkhead and mix, the tissue burning forms single stable big whirlpool in the ring cavity that inside and outside wall forms.
The present invention's advantage compared with prior art is:
(1) front bulkhead at combustion chamber flame drum adopts the crooked T type evaporation tube annular array of a plurality of bands, with respect to Γ type evaporation tube, the spout quantity of T type evaporation tube has been Duoed one times than Γ type evaporation tube, makes the petroleum distribution of burner inner liner head even relatively, more helps igniting and burning; Moreover T type evaporation tube is also shorter relatively at axial length, makes the position, primary zone in advance, has reduced the engine overall axial length; And the front end air inlet can make the enough kinetic energy of evaporation tube inlet air acquisition head, the evaporation of acceleration fuel oil in pipe; This structure has also avoided evaporation tube to be directly exposed to terminal high-temperature region, primary zone, reduces the probability of ablating to a certain extent.
(2) punch on burner inner liner inside and outside wall and front bulkhead in the combustion chamber, utilizes tangential admission, cooperates the primary holes air inlet to form the single big whirlpool retention flame at the burner inner liner head again, and efficiency of combustion is improved greatly.
(3) fuel nozzle of combustion chamber adopts radial spray to T type evaporation tube inwall, and the cooperation air flows evaporation tube inside, has increased the turbulivity that fuel oil and air mix, and improves fuel oil evaporation rate in evaporation tube.
Description of drawings
Fig. 1 is a chamber structure schematic diagram of the prior art;
Fig. 2 is structure master's schematic diagram of the present invention;
Fig. 3 is the front bulkhead side view of Fig. 2;
Fig. 4 is a T type evaporation tube structure master cutaway view of the present invention;
Fig. 5 is that the B of Fig. 4 is to the structure cutaway view;
Fig. 6 is that the A-A of Fig. 4 is to the structure cutaway view;
Fig. 7 is the Γ type evaporation tube and the T type evaporation tube evaporation process schematic diagram of prior art, and wherein Fig. 7 a is a Γ type evaporation tube evaporation process schematic diagram of the prior art, and Fig. 7 b is a T type evaporation tube evaporation process schematic diagram of the present invention;
Fig. 8 is a fuel nozzle structural representation of the present invention.
The specific embodiment
As Fig. 2, shown in 3, the present invention is by combustion chamber flame drum inwall 4 and outer wall 3,3-12 T type evaporation tube 2, fuel nozzle 5 is formed, 3-12 T type evaporation tube 2 is circumferentially evenly distributed along the front bulkhead 1 of combustion chamber flame drum, 3-12 fuel nozzle 5 radially is inserted in 3-12 the T type evaporation tube, at combustion chamber flame drum inwall 4, be equipped with a plurality of holes 6 on outer wall 3 and the front bulkhead 1, decision is distributed by this ground, combustion chamber tolerance in hole count and aperture, circumferential size decision according to combustion chamber flame drum, if need the position of atm number, the aperture of beating is bigger, size just can be beaten much and what by the decision of burner inner liner girth, the ratio that this position perforated area sum accounts for total perforated area should be located tolerance with this and distribute consistently, and generally quantity sees Table 1.Fuel oil is from fuel nozzle 5 in the spirt T type evaporation tube 2, mix with the air in the T type evaporation tube 2, this gas mixture sprays in the combustion chamber flame drum, again and from the hole 6 of inwall 4, outer wall 3 and the front bulkhead 1 of combustion chamber flame drum, spray the air of coming in and mix, utilize tangential admission to form and stablize big whirlpool at the burner inner liner head.
Be assigned as 18.97% in head tolerance in the present embodiment, primary holes tolerance is assigned as 15.86%, and interlude and blending section are under 65.26% the situation, the quantity of punching, aperture and list of locations such as following table 1.
Table 1
Shown in Fig. 4,5,6, the T type evaporation tube that the present invention adopts is by the structure of an inducer 2-1, slight curving crosspiece 2-2 and two outlet section 2-3 formed shapes similar " T ", external diameter is identical in each section, two outlet section 2-3 exit portion bands close up, crosspiece 2-2 is generally 150 °～180 ° for cooperating primary zone two parts θ in a certain angle, at the straight section end of inducer 2-1 one contraction mouth is arranged, can smash adherent oil film, promote EVAP; Crosspiece 2-2 is slight curving, is in order to allow evaporation tube cooperate the burning tissue in primary zone.Fuel oil sprays into evaporation tube import 2-1, mixes the air blending of coming in from import 2-1 equally, and fuel oil evaporates through the crosspiece 2-2 of evaporation tube, and then is ejected into burner inner liner ring cavity participation burning from 2 two outlet section 2-3 of evaporation tube.
As shown in Figure 7,7a, 7b are respectively the work schematic diagram of Γ type and T type evaporation tube, and both principles are identical, and the course of work is the structure difference as mentioned above, and T type evaporation tube size of the present invention is littler than Γ type evaporation tube, many one times of outlet, and evaporation rate is higher.
As shown in Figure 8, fuel nozzle 5 is by the little tubule 5-1 of end sealing, on the distolateral wall of one, open 4 oil outlet 5-2, adopt the inwall of radial spray to T type evaporation tube 2, cooperate air flowing in evaporation tube inside, increase the turbulivity that fuel oil and air mix, improved fuel oil evaporation rate in evaporation tube.
Claims (5)
1, evaporation pipe type miniature-small-sized engine combustion chamber, it is characterized in that: it is made up of combustion chamber flame drum inner and outer wall, a 3-12 T type evaporation tube, fuel nozzle, 3-12 T type evaporation tube is circumferentially evenly distributed along the front bulkhead of combustion chamber flame drum, 3-12 fuel nozzle radially is inserted in 3-12 the T type evaporation tube, on combustion chamber flame drum inwall, outer wall and front bulkhead, be equipped with the hole respectively, air enters the combustion chamber from combustion chamber flame drum inwall, outer wall and front bulkhead, utilizes tangential admission to form at the burner inner liner head and stablizes single big whirlpool.
2, evaporation pipe type miniature-small-sized engine combustion chamber according to claim 1, it is characterized in that: slight curving crosspiece that described T type evaporation tube joins by the inducer that is positioned at the middle part, with inducer and two outlets and the structure that is positioned at two outlet section formed shapes similar " T " at two ends, external diameter is identical in each section, two outlet section exit portion bands close up, crosspiece is for cooperating main combustion zone, and two parts of crosspiece form angle.
3, evaporation pipe type miniature-small-sized engine combustion chamber according to claim 1, it is characterized in that: the tolerance of described tangential admission is assigned as head tolerance, comprise the front-seat 15-20% of being of burner inner liner inwall, primary holes tolerance is 13-18%, and interlude and blending section are 62-70%.
4, evaporation pipe type miniature-small-sized engine combustion chamber according to claim 1 is characterized in that: described fuel nozzle is the tubule of end sealing, seals on the distolateral wall at it and has oil outlet, forms radial spray.
5, evaporation pipe type miniature-small-sized engine combustion chamber according to claim 1 is characterized in that: the number in the hole of described burner inner liner outer wall is 50-70, and the number of front end cinclides is 50-70.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005100865394A CN100443805C (en) | 2005-09-29 | 2005-09-29 | Evaporation pipe type miniature-small-sized engine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005100865394A CN100443805C (en) | 2005-09-29 | 2005-09-29 | Evaporation pipe type miniature-small-sized engine combustion chamber |
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| Publication Number | Publication Date |
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| CN1743735A CN1743735A (en) | 2006-03-08 |
| CN100443805C true CN100443805C (en) | 2008-12-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB2005100865394A Expired - Fee Related CN100443805C (en) | 2005-09-29 | 2005-09-29 | Evaporation pipe type miniature-small-sized engine combustion chamber |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107763668A (en) * | 2017-11-01 | 2018-03-06 | 中国科学院工程热物理研究所 | A kind of subregion burning high stability vaporizer tube combustor |
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| CN100436945C (en) * | 2006-08-23 | 2008-11-26 | 北京航空航天大学 | Fuel pre-evaporation and premix perforated pipe |
| CN102607025A (en) * | 2011-12-06 | 2012-07-25 | 上海诺特飞博燃烧设备有限公司 | Gas back-jetting pre-mixing low-NOx combustion apparatus and combustion method of combustion apparatus |
| CN102889615A (en) * | 2012-10-24 | 2013-01-23 | 哈尔滨东安发动机（集团）有限公司 | Fuel oil atomizing device |
| CN105627365A (en) * | 2016-01-19 | 2016-06-01 | 西北工业大学 | Micro combustion chamber punching type evaporation pipe |
| CN105716120B (en) * | 2016-02-22 | 2018-02-16 | 中国科学院工程热物理研究所 | A kind of fuel oil cooled evaporates tubular construction |
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| CN107726364B (en) * | 2017-09-26 | 2020-08-14 | 中国科学院工程热物理研究所 | Evaporation tube combustion chamber |
| CN108131685A (en) * | 2017-12-14 | 2018-06-08 | 西北工业大学 | Tiny engine combustion chamber multi-point injection evaporation tube |
| CN108151065A (en) * | 2017-12-21 | 2018-06-12 | 西北工业大学 | Tiny engine combustion chamber is to spraying formula evaporation tube |
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| CN108534180B (en) * | 2018-05-02 | 2023-08-15 | 中国科学院工程热物理研究所 | Combustion chamber for engine |
| CN108758689B (en) * | 2018-07-09 | 2024-04-09 | 西安空天能源动力智能制造研究院有限公司 | Combustion chamber of miniature turbine engine |
| CN109469922B (en) * | 2018-11-09 | 2020-07-03 | 四川航天中天动力装备有限责任公司 | Miniature engine combustion chamber |
| CN109595592B (en) * | 2018-12-06 | 2020-04-10 | 西北工业大学 | Pre-evaporation type flame tube |
| CN112815355B (en) * | 2021-01-19 | 2023-02-28 | 重庆交通大学绿色航空技术研究院 | Flame stabilizing device of small turbine engine and turbine engine |
| CN114110659B (en) * | 2021-11-30 | 2023-04-25 | 中国航发湖南动力机械研究所 | Evaporation pipe atomizing device and combustion chamber |
| CN114234237B (en) * | 2021-12-20 | 2023-03-31 | 中国人民解放军总参谋部第六十研究所 | Head preparation method for wide-envelope starting of evaporating tube combustion chamber |
| CN115143490B (en) * | 2022-06-15 | 2023-08-01 | 南京航空航天大学 | Combustion chamber with circumferential staggered opposite flushing jet flow and full-ring large-scale rotational flow coupling |
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| JPH10160162A (en) * | 1996-11-22 | 1998-06-19 | Ishikawajima Harima Heavy Ind Co Ltd | Nitrogen oxide reduction structure of gas turbine combustor |
| WO2004015332A1 (en) * | 2002-08-12 | 2004-02-19 | Alstom Technology Ltd | Premixed exit ring pilot burner |
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2005
- 2005-09-29 CN CNB2005100865394A patent/CN100443805C/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5027603A (en) * | 1988-12-28 | 1991-07-02 | Sundstrand Corporation | Turbine engine with start injector |
| JPH10160162A (en) * | 1996-11-22 | 1998-06-19 | Ishikawajima Harima Heavy Ind Co Ltd | Nitrogen oxide reduction structure of gas turbine combustor |
| WO2004015332A1 (en) * | 2002-08-12 | 2004-02-19 | Alstom Technology Ltd | Premixed exit ring pilot burner |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107763668A (en) * | 2017-11-01 | 2018-03-06 | 中国科学院工程热物理研究所 | A kind of subregion burning high stability vaporizer tube combustor |
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| CN1743735A (en) | 2006-03-08 |
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Granted publication date: 20081217 Termination date: 20110929 |