CN104807042A - Combustion chamber - Google Patents
Combustion chamber Download PDFInfo
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- CN104807042A CN104807042A CN201510250468.0A CN201510250468A CN104807042A CN 104807042 A CN104807042 A CN 104807042A CN 201510250468 A CN201510250468 A CN 201510250468A CN 104807042 A CN104807042 A CN 104807042A
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- combustion chamber
- cooling
- wall
- downstream
- venturi tube
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Abstract
The invention relates to the design of a dry-low-emission combustion chamber of a heavy gas turbine, in particular to a combustion chamber. The combustion chamber provided by the invention comprises a center body, a combustion chamber outer wall and a Venturi tube, wherein an annular cooling air channel is formed in the Venturi tube; a downstream air inlet is formed in the outer annular wall of the downstream section of the Venturi tube; a corresponding through hole is formed in the outer wall of the combustion chamber; the downstream outlet of the cooling air channel is closed; an upstream air outlet is formed in the inner annular wall of an upstream section; cooling air enters the cooling air channel from the downstream air inlet to perform impingement cooling on the inner annular wall of the downstream section, then flows out from the upstream air outlet, and enters an annular premixing area to participating premixing after cooling a wall surface. According to the combustion chamber provided by the invention, a relatively high outlet temperature of the combustion chamber can be met, and simultaneously, the emission of NOx is reduced; the generating amount of CO of the downstream of the Venturi tube is reduced; the conflict between the Venturi cooling air amount and the flame temperature of a combustion area is solved; the service life of a Venturi tube part of the combustion chamber is prolonged.
Description
Technical field
The present invention relates to the dry low emission combustor design of heavy combustion engine, be specifically related to a kind of combustion chamber.
Background technology
The inlet temperature of turbine is a key factor of the efficiency affecting gas-turbine unit, therefore along with gas-turbine unit power, the improving constantly of efficiency requirements, turbine inlet temperature (TIT) requires also to raise gradually, causes the increase of the increase of turbine heat load and combustion chamber NOx emission.
In recent years, country controls more to pay attention to air-polluting, and the NOx emission restriction of national legislation to gas turbine is also further strict.The NOx emission controlling gas turbine is crucial, be the flame temperature in control combustion district, along with combustion engine development, combustor exit temperature improves constantly, contradiction between premixed gas and cooling-air is difficult to balance more, needs more excellent combustion air flow organization mode.
Publication number is CN101349425B Chinese patent, relate to the apparatus/method for cooling the combustion chamber/venturi in low-NOx combustor, in that patent, this device sucks air from secondary-air passage, impinging cooling is formed in the convergence of Venturi tube internal face and expansion segment, then cooling-air flow further downstream, is interacted by multiple turbulator in downstream and cooling-air and produces turbulent cooling effect.But this device forms district of topical hypothermia at Venturi exit place, causes CO discharge capacity to increase; Downstream turbulence cooling effect is weaker than impinging cooling, causes Venturi tube internal face flat segments wall temperature higher; In addition, Venturi tube cooling-air directly drains into combustion zone downstream, can not act on premix air and make for adjustment combustion zone premix equivalent proportion.
Summary of the invention
The object of this invention is to provide a kind of combustion chamber, to solve at least one technical problem above-mentioned.
Technical scheme of the present invention is:
A kind of combustion chamber, comprise centerbody, outer wall of combustion chamber and Venturi tube, described Venturi tube comprises the Upstream section, converging portion, expansion segment and the tract that connect successively to downstream from upstream, and forms the cooling air channels of ring-type in the inside of described Venturi tube;
The inner annular wall of described Upstream section has upstream air outlet, be communicated with described cooling air channels; The annular wall of described tract has air downstream import, be communicated with described cooling air channels; Described cooling air channels is closed at lower exit place; Described outer wall of combustion chamber has the through hole corresponding with described air downstream import.
Alternatively, the profile of the inner annular wall of described Upstream section is column.
Alternatively, the diameter of the inner annular wall of described Upstream section is reduced to downstream gradually by upstream.
Alternatively, described converging portion and described expansion segment carry out turbulent flow by turbulator and cool.
Alternatively, described turbulator is the multiple annular projections be coaxially arranged on the inner annular wall of described converging portion and described expansion segment.
Alternatively, the annular wall of described converging portion and described expansion segment offers multi-turn outer ring cinclides and arrange, described converging portion and described expansion segment are arranged by described outer ring cinclides and are formed impinging cooling.
Alternatively, described outer wall of combustion chamber arranges corresponding position with described outer ring cinclides and offer Venturi air inlet.
Beneficial effect of the present invention:
In combustion chamber of the present invention, cooling-air can enter cooling air channels from air downstream import, impinging cooling is carried out to the inner annular wall of tract, because venturi lower exit place closes, cooling-air meeting flow upstream, outflow is exported in the upstream air of the inner annular wall of Upstream section from cooling-air, main combustion zone is no longer directly entered after wall is cooled, but enter annular premixed district participation premix, combustion chamber can be made on the one hand while meeting higher combustor exit temperature to reduce NOx emission, the even quenching of main combustion zone partial flame temperature decrease can be prevented simultaneously, reduce the growing amount of CO, in addition, venturi cooling-air directly enters annular premixed district and participates in premix after cooling Venturi tube, can regulate flame temperature, successfully solve the contradiction between venturi cooling air volume and combustion zone flame temperature, further, Venturi tube tract belongs to the higher part of wall temperature in combustion chamber, uses the cooling effect of impinging cooling more obvious, can increase the life-span of combustion chamber Venturi tube parts.
Accompanying drawing explanation
Accompanying drawing to be herein merged in description and to form the part of this description, shows embodiment according to the invention, and is used from description one and explains principle of the present invention.
Fig. 1 is the simplification view in the cross section of prior art gas-turbine combustion chamber;
Fig. 2 is the simplification view in the cross section of gas-turbine combustion chamber of the present invention;
Fig. 3 is the view that Venturi tube converging portion in Fig. 2 and expansion segment adopt the cross section of turbulent flow cooling
Fig. 4 is the view that Venturi tube converging portion in Fig. 2 and expansion segment adopt the cross section of impinging cooling.
Reference numeral:
Combustion chamber 10,48;
Annular premixed district 11,49;
Main combustion zone 12,50;
Premixed district, center 13,51;
Secondary combustion zone 14,52;
Venturi tube 15,53;
Inner annular wall 16,54;
Annular wall 17,55;
Converging portion 18,56;
Expansion segment 19,57;
Venturi 20,58;
Tract 21,59;
Cooling air channels 22,60;
Lower exit 23,61;
Air downstream import 24;
Turbulator 25,62;
Outer ring cinclides row 26,63;
Upstream section 27;
Upstream air outlet 28;
Fuel nozzle 29,43;
Fuel 30,44;
Hole 31,45;
Head air inlet 32,46;
Venturi air inlet 33,47;
Outer wall of combustion chamber 34,42;
Through hole 41;
Centerbody 36,40.
Detailed description of the invention
Here will be described exemplary embodiment in detail, its sample table shows in the accompanying drawings.When description below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawing represents same or analogous key element.
As shown in Figure 1, show generally existing gas-turbine combustion chamber 10 structure.
This combustion chamber 10 comprises centerbody 36, outer wall of combustion chamber 34 and Venturi tube 15, forms the main combustion zone 12 after the annular premixed district 11 that is used for premixed fuel and air and premixed district, center 13, venturi and time combustion zone 14, center.
The shape of combustion chamber 10 is the substantial cylindrical around combustion chamber center line, and burned chamber outer wall 34 surrounded.Compressor (not shown) provides compressed air stream to combustion chamber 10, and Partial shrinkage air-flow enters annular premixed district 11 and premixed district, center 13 by multiple head air inlet 32; Another part compressed air stream enters annular premixed district 11 by one or more hole 31; Fuel 30 (in figure dotted line) sprays into annular premixed district 11 and premixed district, center 13 through one or more fuel nozzle 29, and flows into main combustion zone 12 after compressed air stream blending respectively and carries out premixed combustion with time combustion zone 14.
As shown in the direction of arrow in Fig. 1, fuel-air mixture is swum downwards and is moved to main combustion zone 12.Inner annular wall 16 and the annular wall 17 of Venturi tube 15 are coaxially placed, and use rivet interlacement with outer wall of combustion chamber 34.Venturi tube converging portion 18 and expansion segment 19 form venturi 20, and fuel-air mixture accelerates at venturi 20 place, prevents tempering.
Compressor provides cooling-air by Venturi air inlet 33 to Venturi tube 15, cooling-air enters cooling air channels 22 by outer ring cinclides row 26, and impinging cooling is carried out to the converging portion 18 of inner annular wall 16 and expansion segment 19, afterwards along cooling air channels 22 flow further downstream, carry out turbulent flow cooling by turbulator 25 pairs of tracts 21, entered in gas-turbine combustion chamber 10 by lower exit 23.
As shown in Figure 2, be that the gas-turbine combustion chamber of the embodiment of the present invention shows to be 48.
Combustion chamber 48 comprises centerbody 40, outer wall of combustion chamber 42 and Venturi tube 53, forms the main combustion zone 50 after the annular premixed district 49 that is used for premixed fuel and air and premixed district, center 51, venturi and time combustion zone 52, center.
Premixed district 49 is for realizing the even blending of annulus fuel and air; Main combustion zone 50 is for the premixed combustion of fuel and air; Premixed district, center 51 is for realizing the even blending of center fuel and air; With the premixed combustion of secondary combustion zone 52 for fuel and air.
Venturi tube 53 is arranged on downstream, annular premixed district 49, can comprise from upstream to Upstream section 27, converging portion 56, expansion segment 57 and the tract 59 that downstream (view direction shown in Fig. 2 from left to right) connects successively.This Venturi tube 53 also has inner annular wall 54 and the annular wall 55 of coaxial placement, is fastenedly connected, and forms cooling air channels 60 between inner annular wall 54 and annular wall 55 between both and outer wall of combustion chamber 42.
The shape of combustion chamber 48 is the substantial cylindrical around combustion chamber center line, and burned chamber outer wall 42 surrounded.Compressor (not shown) provides compressed air stream to combustion chamber 48, and Partial shrinkage air-flow enters annular premixed district 49 and premixed district, center 51 by multiple head air inlet 46; Another part compressed air stream enters annular premixed district 49 by one or more hole 45; Fuel 44 sprays into annular premixed district 49 and premixed district, center 51 through one or more fuel nozzle 43, and flows into main combustion zone 50 after compressed air stream blending respectively and carries out premixed combustion with time combustion zone 52.
As shown in the direction of arrow in Fig. 2, fuel-air mixture is swum downwards and is moved to main combustion zone 50.Inner annular wall 54 and the annular wall 55 of Venturi tube 53 are coaxially placed, and use rivet interlacement with outer wall of combustion chamber 42.Converging portion 56 and the expansion segment 57 of Venturi tube 53 form venturi 58, and fuel-air mixture accelerates at venturi 58 place, prevents tempering.
Further, the inner annular wall 54 of the Upstream section 27 of Venturi tube 53 has upstream air outlet 28, be communicated with cooling air channels 60.Wherein, the profile of the inner annular wall 54 of Upstream section 27 can be column, or the diameter of the inner annular wall 54 of Upstream section 27 is reduced to downstream gradually by upstream, and its profile can be similar " horn-like ".
Compressor provides cooling-air by Venturi air inlet 47 and air downstream import 24 to Venturi tube 53, and Venturi air inlet 47 and air downstream import 24 are one or more through hole.Part cooling-air enters cooling air channels 60 by air downstream import 24, carries out impinging cooling to tract 59; All the other cooling-airs enter cooling air channels 60 by outer ring cinclides row 63.Wherein, especially as shown in Figure 4, outer ring cinclides row 63 is the hole that many rows arrange in the form of a ring, and carries out impinging cooling to the converging portion 56 of inner annular wall 54 and expansion segment 57.
Because the lower exit 61 of Venturi tube 53 is closed; cooling-air can along cooling air channels 60 flow upstream; flowed out by the upstream air outlet 28 of Venturi tube 53; form cooling air film; the Upstream section 27 of Venturi tube 53 is protected; enter annular premixed district 49 simultaneously, continue blending with fuel-air mixture.Upstream air outlet 28 be the hole differed in many rounds footpath, and less hole, aperture is for the formation of cooling air film protective bulkhead face, and larger hole, aperture is for strengthening mixing effect.
Venturi tube 53 of the present invention, except the type of cooling shown in above-mentioned Fig. 4, can also adopt the type of cooling that other are applicable to.As shown in Figure 3, turbulator 62 can be adopted to carry out turbulent flow cooling, and the Venturi air inlet 47 now in the above-mentioned type of cooling can be cancelled.Turbulator 62 can be the multiple annular projections (or annular plate) for being coaxially arranged on the inner annular wall 54 of converging portion 56 and expansion segment 57.Particularly, cooling-air is along cooling air channels 60 flow upstream, carry out turbulent flow by the converging portion 56 of turbulator 62 pairs of Venturi tubes 53 and expansion segment 57 to cool, cooling-air is more contacted with annular wall 55 with the inner annular wall 54 of Venturi tube 53, promotes the heat exchange between cooling-air and metal wall.Now, the tract 59 of Venturi tube 53 adopts impinging cooling, and upstream portion adopts turbulent flow cooling, can enhanced heat exchange effect.
The above; be only the specific embodiment of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.
Claims (7)
1. a combustion chamber, comprise centerbody (40), outer wall of combustion chamber (42) and Venturi tube (53), it is characterized in that, described Venturi tube (53) comprises the Upstream section (27), converging portion (56), expansion segment (57) and the tract (59) that connect successively to downstream from upstream, and forms the cooling air channels (60) of ring-type in the inside of described Venturi tube (53);
The inner annular wall (54) of described Upstream section (27) has upstream air outlet (28), be communicated with described cooling air channels (60);
The annular wall (55) of described tract (59) has air downstream import (24), is communicated with described cooling air channels (60);
Described cooling air channels (60) is closed at lower exit (61) place;
Described outer wall of combustion chamber (42) has the through hole (41) corresponding with described air downstream import (24).
2. combustion chamber according to claim 1, is characterized in that, the profile of the inner annular wall (54) of described Upstream section (27) is column.
3. combustion chamber according to claim 1, is characterized in that, the diameter of the inner annular wall (54) of described Upstream section (27) is reduced to downstream gradually by upstream.
4. combustion chamber according to claim 1, is characterized in that, described converging portion (56) and described expansion segment (57) carry out turbulent flow by turbulator (62) and cool.
5. combustion chamber according to claim 4, it is characterized in that, described turbulator (62) is the multiple annular projections be coaxially arranged on the inner annular wall (54) of described converging portion (56) and described expansion segment (57).
6. combustion chamber according to claim 1, it is characterized in that, the annular wall (55) of described converging portion (56) and described expansion segment (57) offers multi-turn outer ring cinclides arrange (63), described converging portion (56) and described expansion segment (57) are arranged (63) by described outer ring cinclides and are formed impinging cooling.
7. combustion chamber according to claim 6, is characterized in that, above arrange (63) corresponding position with described outer ring cinclides offers Venturi air inlet (47) to described outer wall of combustion chamber (42).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510250468.0A CN104807042A (en) | 2015-05-15 | 2015-05-15 | Combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510250468.0A CN104807042A (en) | 2015-05-15 | 2015-05-15 | Combustion chamber |
Publications (1)
| Publication Number | Publication Date |
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| CN104807042A true CN104807042A (en) | 2015-07-29 |
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ID=53692110
Family Applications (1)
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| CN201510250468.0A Pending CN104807042A (en) | 2015-05-15 | 2015-05-15 | Combustion chamber |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105042587A (en) * | 2015-08-28 | 2015-11-11 | 深圳华琰科技有限公司 | Methanol hydrogenation burner |
| CN105240872A (en) * | 2015-09-17 | 2016-01-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Combustion chamber head assembly |
| CN107525097A (en) * | 2017-09-26 | 2017-12-29 | 大连派思透平动力科技有限公司 | Vertical cylinder dual fuel burner |
| CN108775601A (en) * | 2018-07-04 | 2018-11-09 | 大连派思透平动力科技有限公司 | A kind of inner tube structure suitable for gas turbine reflux tube-type combustion chamber |
| CN109654538A (en) * | 2018-12-07 | 2019-04-19 | 中国航发沈阳发动机研究所 | A kind of Venturi tube conducive to reduction Calculating Wall Temperature of Flame Tube |
| CN109654540A (en) * | 2018-12-16 | 2019-04-19 | 中国航发沈阳发动机研究所 | A kind of head of combustion chamber exchanging structure |
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| CN1582365A (en) * | 2001-11-30 | 2005-02-16 | 动力体系制造有限公司 | Combustion chamber/venturi cooling apparatus and method for low nox emission combustor |
| CN1818362A (en) * | 2005-01-31 | 2006-08-16 | 通用电气公司 | Inboard radial dump venturi for combustion chamber of a gas turbine |
| US20090019854A1 (en) * | 2007-07-16 | 2009-01-22 | General Electric Company | APPARATUS/METHOD FOR COOLING COMBUSTION CHAMBER/VENTURI IN A LOW NOx COMBUSTOR |
| CN101782232A (en) * | 2009-01-21 | 2010-07-21 | 燃气涡轮机效率瑞典公司 | Venturi cooling system |
| CN102192510A (en) * | 2010-03-02 | 2011-09-21 | 通用电气公司 | Hybrid venturi cooling system |
| CN204611837U (en) * | 2015-05-15 | 2015-09-02 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of combustion chamber |
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Patent Citations (6)
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| CN1582365A (en) * | 2001-11-30 | 2005-02-16 | 动力体系制造有限公司 | Combustion chamber/venturi cooling apparatus and method for low nox emission combustor |
| CN1818362A (en) * | 2005-01-31 | 2006-08-16 | 通用电气公司 | Inboard radial dump venturi for combustion chamber of a gas turbine |
| US20090019854A1 (en) * | 2007-07-16 | 2009-01-22 | General Electric Company | APPARATUS/METHOD FOR COOLING COMBUSTION CHAMBER/VENTURI IN A LOW NOx COMBUSTOR |
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| CN102192510A (en) * | 2010-03-02 | 2011-09-21 | 通用电气公司 | Hybrid venturi cooling system |
| CN204611837U (en) * | 2015-05-15 | 2015-09-02 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of combustion chamber |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105042587A (en) * | 2015-08-28 | 2015-11-11 | 深圳华琰科技有限公司 | Methanol hydrogenation burner |
| CN105240872A (en) * | 2015-09-17 | 2016-01-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Combustion chamber head assembly |
| CN105240872B (en) * | 2015-09-17 | 2018-05-25 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of chamber head parts |
| CN107525097A (en) * | 2017-09-26 | 2017-12-29 | 大连派思透平动力科技有限公司 | Vertical cylinder dual fuel burner |
| CN108775601A (en) * | 2018-07-04 | 2018-11-09 | 大连派思透平动力科技有限公司 | A kind of inner tube structure suitable for gas turbine reflux tube-type combustion chamber |
| CN108775601B (en) * | 2018-07-04 | 2024-05-10 | 大连欧谱纳透平动力科技有限公司 | Inner cylinder structure suitable for gas turbine backflow cylinder type combustion chamber |
| CN109654538A (en) * | 2018-12-07 | 2019-04-19 | 中国航发沈阳发动机研究所 | A kind of Venturi tube conducive to reduction Calculating Wall Temperature of Flame Tube |
| CN109654540A (en) * | 2018-12-16 | 2019-04-19 | 中国航发沈阳发动机研究所 | A kind of head of combustion chamber exchanging structure |
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Application publication date: 20150729 |