CN102444476B - Wave-shaped diffuser of gas turbine - Google Patents
Wave-shaped diffuser of gas turbine Download PDFInfo
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- CN102444476B CN102444476B CN201110421605.4A CN201110421605A CN102444476B CN 102444476 B CN102444476 B CN 102444476B CN 201110421605 A CN201110421605 A CN 201110421605A CN 102444476 B CN102444476 B CN 102444476B
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Abstract
The invention which relates to a design of the structure of a compressor diffuser of a gas turbine concretely relates to a wave-shaped diffuser of a gas turbine. The diffuser is characterized in that: the diffuser comprises an inner wall surface and an outer wall surface, and the inner wall surface and the outer wall surface respectively have a wave-shaped line in a circumferential direction around rotors of the gas turbine; a part of the wave-shaped line which has a smallest radius is positioned at the trough of the wave when the wave-shaped line is at a circumferential position corresponding with the center of transition sections, and a part of the wave-shaped line which has a biggest radius corresponds with the peak of the wave when the wave-shaped line is at a circumferential position corresponding with the center of narrow slits between all adjacent transition sections. The wave-shaped diffuser allows the airflow from the upstream compressor to be decelerated and a periodic variation of the cooperation of the radius and the radial angle with the position of a combustor to be formed at the outlet of the diffuser, so the distribution in the circumference and the impact position of the airflow are pertinently adjusted, and nonuniform degrees of the speed and the pressure of the airflow surrounding the transition sections are reduced, thereby the cooling efficiency of the transition sections can be effectively improved, and the flow resistance loss of the airflow in the chamber of the combustion chamber can be simultaneously reduced.
Description
Technical field
The present invention relates to gas turbine blower Diffuser, relate more specifically to for promoting industry gas turbine firing chamber changeover portion wall cooling effect, the diffuser structure of windage loss in the chamber that reduces to burn, belong to gas-turbine combustion chamber technical field.
Background technique
In industry gas turbine, conventional chamber structure is can annular type combustor, and multiple burners are arranged in the mode of annular array around gas turbine rotor.The pressurized gas of blower outlet in burner inner liner and fuel mix, forms high-temperature fuel gas after ignition.High-temperature fuel gas in burner inner liner enters turbine subsequently, drives turbine acting, and wherein part merit is for driving coaxial connected gas compressor with it, and another part drives generator generating.
High-temperature fuel gas in firing chamber enters turbine via changeover portion.Typically burner inner liner outlet is circle, and turbine import is rectangle, and therefore, the cross section of changeover portion is from import to exporting by circular smooth transition to rectangle.Meanwhile, burner inner liner radius of living in is large conventionally, and turbine radius is little, and changeover portion also exists obvious change in radius.Complicated geometrical construction and very high fuel gas temperature make the operating conditions in changeover portion extremely complicated, for preventing that changeover portion from burning because of overheated, need to carry out cooling to the surface of changeover portion.
In firing chamber, participate in the gas compressor that burning and cooling air-flow derive from its upstream, Diffuser is positioned at blower outlet, its role is to reduce the speed in the compressed air stream flowing in combustion chamber chamber of blower outlet, can reduce the loss of high pressure draught in chamber on the one hand, make the pressure burning in chamber try one's best evenly simultaneously, be convenient to burner high temperature wall, especially changeover portion is cooling.
For advanced industry gas turbine, approximately there is 1/2 the air-flow that enters firing chamber annular chamber for participating in burning, separately there is 1/4 air-flow for diluting combustion gas, regulate burning indoor temperature distribution, to meet the requirement in turbine import stage efficiency and life-span, some need be used for cooling flame tube wall surface, therefore, only has a small amount of air-flow to can be used for cooled transition section.For realize the effective cooling of changeover portion with the least possible cooling blast, now in comparatively advanced gas turbine changeover portion adopted cooling such as impacting, disperse the types of cooling such as cooling.Wherein impacting cooling main mechanism is, the airflow strikes of diffuser exit is furnished with on surface on the impulse transfer section cooling bushing of multiple Cooling Holes, under the effect of inside and outside pressure reduction, air-flow accelerates to form jet impulse at changeover portion wall by Cooling Holes, thereby reaches the object of cooled transition section.Spread cooling with impact cooling similar, just between changeover portion cooling bushing and changeover portion wall, be furnished with fin, for strengthening cooling effect.
Traditional diffuser exit radial height, angle all immobilize, in air flow collection, impact the lower surface at changeover portion cooling bushing, stream subsequently to the gap forming between adjacent two changeover portions, make to be flowing in gap and accelerate, cause shock point supercooling around, and the changeover portion both side surface of not impacted because of air-flow accelerate cause pressure reduction deficiency, cooling effect is poor.Because changeover portion both side surface is the region that temperature is higher, stress is concentrated, cooling deficiency easily causes wall to occur crackle.Especially in the time that blower outlet speed is larger, for example, while being greater than 130m/s, diffuser exit airspeed increases, and the mobile acceleration in adjacent changeover portion gap is more obvious, even cause the external pressure of Cooling Holes in this region to be less than internal pressure, form the refluence of cooling air.Now, strengthen cooling gas consumption, for example, increase the diameter of Cooling Holes, or be aided with the cooling method of air film, be also difficult to the cooling effect that reaches desirable.
For avoiding flowing and excessively accelerate to affect cooling effect in the gap between adjacent changeover portion, control position and the velocity anomaly key of diffuser exit gas shock changeover portion.Increase simply the radial angle of diffuser exit, can make the position of gas shock changeover portion move toward combustor inlet, thereby reduce air flow rate and the speed of flowing through in adjacent changeover portion gap, but as easy as rolling off a log to cause participating in the cooling gas consumption of changeover portion inadequate.Also there is some Diffuser; outlet radial angle is larger; in order to take into account the cooling requirement of changeover portion; draw a part of air-flow to changeover portion in the perforate of Diffuser internal face; but be that the air-flow that Diffuser inwall face is drawn impacts changeover portion wall more equably; conventionally also need after inner wall hole, in certain distance, configure a kind of flat board with the hole of gathering, structure is comparatively complicated.In Diffuser, add guide plate, form two even three passages, also can effectively control gas shock point and striking velocity, but this need to increase guide plate and corresponding supporting structure in Diffuser, complex structure, also increased the loss of Diffuser, and this structure is on large scale gas turbine more than 150MW, just to reach good effect at power level.In disclosed patent documentation CN101839256A, adopt a kind of Diffuser of fluting, this Diffuser can be by part air-flow guiding changeover portion for cooled transition section, and another part is through the fluting of Diffuser outer wall, directly enter the passage between water conservancy diversion lining and burner inner liner, thereby to a certain extent balance changeover portion cooling and burning chamber in flow losses, its shortcoming is that Diffuser outer wall groove is blunt form structure, and flow velocity is higher at fluting place, cause thus extraneoas loss.
Summary of the invention
The object of this invention is to provide a kind of Wave-shaped diffuser of gas turbine, make it not only simple in structure, and can take into account preferably the flow losses that changeover portion is cooling and minimizing is burnt in chamber.
Technological scheme of the present invention is as follows:
A kind of Wave-shaped diffuser of gas turbine, the upstream of this Diffuser is axial-flow compressor, downstream, for burning chamber, comprises the burner that several are arranged with annular array around gas turbine rotor in this burning chamber, between the burner inner liner of this burner and turbine import, be connected by changeover portion; The entrance point of described Diffuser is connected with the outlet of gas compressor, outlet end is connected with burning chamber, Diffuser comprises internal face and outer wall, it is characterized in that: described internal face and outer wall have waveform molded line on the circumferencial direction around gas turbine rotor, this waveform molded line is the periodicity curve that is smoothly connected crest and trough, at circumferential position corresponding to changeover portion center, it is minimum that radius reaches, in the trough of wave, at circumferential position corresponding to the center in gap that adjacent changeover portion forms, it is maximum that radius reaches, the crest of corresponding wave; The periodicity of wave is identical with the number of burner.
The amplitude of waveform molded line increases to outlet linearly from the import of Diffuser, and outlet port amplitude A is 0.05～0.4 times of wavelength L, and its medium wavelength L is the occupied circumferential arc length in each wave mean radius position.
Described periodicity curve is preferably sinusoidal curve.
The internal face of described Diffuser and outer wall molded line is vertically straight line; Also can be that outer wall molded line is vertically the curve that slope increases gradually, internal face molded line be vertically the curve that straight line or slope increase gradually.
The present invention compared with prior art, have the following advantages and high-lighting effect: Wave-shaped diffuser of gas turbine provided by the present invention, air-flow from its upstream gas compressor can be slowed down, at diffuser exit place forming radius, the cyclically-varying that radial angle matches with burner position, can be according to the cooling requirement of firing chamber different parts, regulate pointedly air-flow at week distribution and impact position upwards, thereby reduce the changeover portion nonuniformity of airspeed and pressure around, for the different changeover portion types of cooling, for example impact cooling, disperse cooling, cooling or the convection current of air film is cooling etc., all can effectively improve the cooling of changeover portion, reduce the flow losses of air-flow in burning chamber simultaneously.
Accompanying drawing explanation
Fig. 1 is the structural principle schematic diagram of existing gas-turbine combustion chamber.
Fig. 2 is the gas-turbine combustion chamber structural principle schematic diagram with Wave-shaped diffuser.
Fig. 3 is the structural representation of Wave-shaped diffuser provided by the invention.
Fig. 4 is the I-I cross-sectional view in Fig. 2.
Fig. 5 is the three-dimensional side view of Wave-shaped diffuser and firing chamber.
List of parts: 10-burner; 11-burner inner liner; 12-water conservancy diversion lining; 13-changeover portion; 14-changeover portion cooling bushing; 15-Cooling Holes; 16-firing chamber; The 17-chamber of burning; 18-Diffuser; 19-internal face; 20-outer wall; 21-gas compressor; 22-turbine; 23-gas turbine rotor; Narrow slit between the adjacent changeover portion of 28-.
Embodiment
Below in conjunction with accompanying drawing, structure of the present invention, principle and working procedure are described further.
Fig. 2 is the gas-turbine combustion chamber 16 structural principle schematic diagram with Wave-shaped diffuser 18, the upstream of this Diffuser is axial-flow compressor 21, downstream is burning chamber 17, burning comprise in chamber 17 several around gas turbine rotor 23 burner 10 with annular array arranged in form; The entrance point of Wave-shaped diffuser 18 is connected with the outlet of gas compressor 21, and outlet end is connected with burning chamber 17, and changeover portion 13 is the subassembly of burner 10, for connecting burner inner liner 11 outlet and turbine 22 imports.There is certain height difference from import to outlet in changeover portion 13, and its cross section transits to rectangle from import to outlet gradually by circle.The high pressure draught that gas compressor 21 exports is after Wave-shaped diffuser 18 deceleration diffusions, enter in burning chamber 17, be divided into two strands, wherein a part of air-flow directly enters burner 10 front ends by the annular pass between burner inner liner 11 and water conservancy diversion lining 12, with fuel blending after-combustion.Another part air-flow is under the effect of pressure reduction, via the Cooling Holes 15 on changeover portion cooling bushing 14, form the wall of jet impulse at changeover portion 13, realization is cooling to changeover portion 13 walls, and this part air-flow also enters the annular pass between burner inner liner 11 and water conservancy diversion lining 12 subsequently.
Fig. 3 is the structural representation of Wave-shaped diffuser, and Diffuser 18 comprises internal face 19 and outer wall 20, and internal face 19 and outer wall 20 have waveform molded line on the circumferencial direction around gas turbine rotor 23; Waveform molded line is circumferential position corresponding to narrow slit 28 center between adjacent changeover portion, it is maximum that the radius of internal face 19 and outer wall 20 and radial angle all reach, be positioned at the peak value of wave, thereby by the close burner of air-flow guiding 10 front end places, more easily enter the annular pass between burner inner liner 11 and water conservancy diversion lining 12, shorten the flow process of fluid in burning chamber 17, flow resistance loss can significantly reduce.Simultaneously, also reduced by the air flow rate at narrow slit 28 places between adjacent changeover portion, air-flow acceleration in narrow slit 28 between adjacent changeover portion is weakened, and at circumferential position corresponding to changeover portion 13 centers, the radius of internal face 19 and outer wall 20 and radial angle all reach minimum, in the trough of wave, thereby by enough air-flow guiding changeover portions 13, first this strand of air-flow strike the lower surface of changeover portion cooling bushing 14, wherein part air-flow forms jet impulse to changeover portion 13 by the Cooling Holes 15 of changeover portion cooling bushing 14 under the effect of inside and outside differential pressure, realization is cooling to changeover portion 13 bottoms, another part streams to narrow slit 28 between adjacent changeover portion, be used for the cooling of changeover portion 13 both side surface.Owing to only there being part air-flow to be directed to changeover portion 13, so air-flow is the acceleration in narrow slit 28 not obvious between adjacent changeover portion, make the pressure distribution of changeover portion cooling bushing 14 both side surface more even, effectively improved the cooling effect of changeover portion 13 bi-side.
As can be seen from Figure 3, internal face 19 and outer wall 20, in the concave, convex layout of different circumferential positions, have been formed naturally wave molded line very much, and this waveform molded line can be sinusoidal curve, or other is smoothly connected the periodicity curve of crest and trough.At whole circumferencial direction, the periodicity of wave should be identical with the number of burner 10, and wavelength L is the occupied circumferential arc length in each wave mean radius position.The amplitude of waveform molded line is the important parameter that affects Diffuser 18 exit flow impulse transfer section 13 positions and speed, its numerical value can regulate according to the cooling requirement of the structure of firing chamber 16 and changeover portion 13, and the amplitude of internal face 19 and outer wall 20 can be divided other optimization.When amplitude is too small, Diffuser 18 regulates the DeGrain of exit flow impact position and changeover portion 13 cooling assignment of traffic, and amplitude is when excessive, will increase the flow losses in Diffuser 18.Amplitude increases gradually from Diffuser 18 imports to outlet.Conventionally Diffuser 18 outlet port amplitude A value between 0.05～0.4 times of wavelength L.
The internal face of Diffuser 18 and outer wall vertically molded line can be straight line, can be also curve, adopt curve can make outlet obtain larger radial angle, for example, adopt bell line, and radial angle obviously increases in outlet.The axial molded line of internal face 19 and outer wall 20, according to the needs of design, can have different combining forms, and for example, internal face 19 and outer wall 20 are straight line; Or internal face 19 and outer wall 20 are curve; Also can internal face 19 be straight line, outer wall 20 be curve.Because internal face 20 is curve, and the combining form that outer wall 20 is straight line cannot form appropriate assignment of traffic, does not adopt.As an exemplary embodiment, the wall of Diffuser 18 shown in Fig. 3 vertically molded line is straight line.
Fig. 4 is a preferred embodiment of the present invention.In this embodiment, have six burners 10 and be evenly arranged with annular array form around gas turbine rotor 23, the wave molded line of Diffuser 18 has adopted sinusoidal curve, and its periodicity is six, identical with the number of burner 10, the axial molded line of Diffuser 18 has adopted the simplest straight line.From Diffuser 18 imports to outlet, the amplitude of internal face 19 and outer wall 20 waves increases linearly.The amplitude A of Diffuser 18 outlet port waves chooses according to mobile being optimized in burning chamber 17, in the present embodiment, when the amplitude of internal face 19 outlet port waves is 0.18 times of its wavelength L, and the amplitude of outer wall 20 outlet port waves is while being 0.15 times of its wavelength L, can make changeover portion 13 ambient pressures distribute and reach better balance with the interior flow resistance loss of burning chamber 17, be optimal magnitude value.
Fig. 5 is the three-dimensional side view of Wave-shaped diffuser 18 and firing chamber 16, has illustrated spatial relation between Wave-shaped diffuser, burner 10 and changeover portion cooling bushing 14 (or changeover portion 13).
Although the present invention thinks that practicality the most and preferred embodiment describe at present, should know, the present invention is not limited to the disclosed embodiments, and should cover the various modifications and the equivalent arrangements that are comprised within the protection domain that claims limit.
Claims (4)
1. a Wave-shaped diffuser of gas turbine, the upstream of this Diffuser is axial-flow compressor (21), downstream is burning chamber (17), in this burning chamber (17), comprise the burner (10) that several are arranged with annular array around gas turbine rotor (23), between the burner inner liner (11) of this burner (10) and turbine (22) import, be connected by changeover portion (13), changeover portion is the subassembly of burner (10), be used for connecting burner inner liner outlet and turbine import, changeover portion transits to rectangle from import to outlet gradually by circle; The entrance point of described Diffuser (18) is connected with the outlet of gas compressor (21), and the outlet end of Diffuser is connected with burning chamber (17); The high pressure draught of blower outlet, after Diffuser deceleration diffusion, enters in burning chamber and is divided into two-part, and wherein a part of air-flow directly enters burner front end by the annular pass between burner inner liner and water conservancy diversion lining (12), with fuel blending after-combustion; Another part air-flow, via the Cooling Holes (15) on changeover portion cooling bushing (14), forms the wall of jet impulse at changeover portion, and realization is cooling to changeover portion wall, and this part air-flow also enters the annular pass between burner inner liner and water conservancy diversion lining subsequently; Described Diffuser comprises internal face (19) and outer wall (20), it is characterized in that: described internal face (19) and outer wall (20) have waveform molded line on the circumferencial direction around gas turbine rotor (23); Described waveform molded line is the periodicity curve that is smoothly connected crest and trough, this waveform molded line is at circumferential position corresponding to changeover portion (13) center, it is minimum that radius reaches, in the trough of wave, the circumferential position corresponding to center of narrow slit between adjacent changeover portion (28), it is maximum that radius reaches, the crest of corresponding wave; The periodicity of wave is identical with the number of burner (10); The amplitude of waveform molded line increases to outlet linearly from the import of Diffuser (18), and outlet port amplitude A is 0.05～0.4 times of wavelength L, and its medium wavelength L is the occupied circumferential arc length in each wave mean radius position.
2. a kind of Wave-shaped diffuser of gas turbine according to claim 1, is characterized in that: described periodicity curve is sinusoidal curve.
3. a kind of Wave-shaped diffuser of gas turbine according to claim 1, is characterized in that: described internal face (19) and outer wall (20) molded line are vertically straight line.
4. a kind of Wave-shaped diffuser of gas turbine device according to claim 1, it is characterized in that: described outer wall (20) molded line is vertically the curve that slope increases gradually, internal face (19) molded line is vertically the curve that straight line or slope increase gradually.
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| CN201110421605.4A CN102444476B (en) | 2011-12-15 | 2011-12-15 | Wave-shaped diffuser of gas turbine |
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| CN201110421605.4A CN102444476B (en) | 2011-12-15 | 2011-12-15 | Wave-shaped diffuser of gas turbine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110388335A (en) * | 2018-04-18 | 2019-10-29 | 三菱重工业株式会社 | Compressor diffuser, gas turbine |
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| CN103870620B (en) * | 2012-12-14 | 2017-08-11 | 中国航发商用航空发动机有限责任公司 | Parametric modeling method for diffuser and exit guide blade Combined design |
| CN104596723B (en) * | 2015-01-28 | 2017-06-16 | 中誉远发国际建设集团有限公司 | The manufacture method of aerodynamic experiment diffuser |
| CN104864416A (en) * | 2015-04-22 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Connecting structure of combustion liner and transition section |
| CN109139262A (en) * | 2017-06-28 | 2019-01-04 | 中国航发贵阳发动机设计研究所 | A kind of aeroengine combustor buring room diffuser |
| KR102377720B1 (en) | 2019-04-10 | 2022-03-23 | 두산중공업 주식회사 | Liner cooling structure with improved pressure losses and combustor for gas turbine having the same |
| CN113983494B (en) * | 2021-09-22 | 2022-10-21 | 南京航空航天大学 | Diffusion ratio intelligent adjustable gas turbine main combustion chamber multi-channel diffuser |
| CN115342078B (en) * | 2022-10-20 | 2023-03-24 | 杭州顿力电器有限公司 | High-efficiency centrifugal fan with module diffusion structure |
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Denomination of invention: Wave-shaped diffuser of gas turbine Effective date of registration: 20161104 Granted publication date: 20140514 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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Date of cancellation: 20191211 Granted publication date: 20140514 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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Effective date of registration: 20191225 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: China United heavy-duty gas turbine technology Co., Ltd. Address before: 100084 No. 8, building 1, No. 1001, Zhongguancun East Road, Beijing, Haidian District Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |