CN102444476A - Wave-shaped diffuser of gas turbine - Google Patents
Wave-shaped diffuser of gas turbine Download PDFInfo
- Publication number
- CN102444476A CN102444476A CN2011104216054A CN201110421605A CN102444476A CN 102444476 A CN102444476 A CN 102444476A CN 2011104216054 A CN2011104216054 A CN 2011104216054A CN 201110421605 A CN201110421605 A CN 201110421605A CN 102444476 A CN102444476 A CN 102444476A
- Authority
- CN
- China
- Prior art keywords
- diffuser
- wave
- gas turbine
- waveform
- changeover portion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
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 the gas turbine blower Diffuser, relate more specifically to be used to promote 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 the gas-turbine combustion chamber technical field.
Background technique
In the industry gas turbine, chamber structure commonly used is a can annular type combustor, and a plurality of burners are arranged with the mode of annular array around gas turbine rotor.The pressurized gas of blower outlet forms high-temperature fuel gas in burner inner liner and fuel mix after the ignition.High-temperature fuel gas in the burner inner liner gets into turbine subsequently, drives the turbine acting, and wherein the part merit is used to drive coaxial with it continuous gas compressor, and another part then drives generator for electricity generation.
High-temperature fuel gas in the firing chamber gets into turbine via changeover portion.Typically the burner inner liner outlet is circle, and the turbine import is a rectangle, and therefore, the cross section of changeover portion extremely exports by circular smooth transition to rectangle from import.Simultaneously, burner inner liner radius of living in is big usually, and the turbine radius is little, and also there is tangible radius change in changeover portion.Complicated geometrical construction and very high fuel gas temperature make the operating conditions in the changeover portion extremely complicated, burn because of overheated for preventing changeover portion, need cool off the surface of changeover portion.
Participation burning and cooled gas flow derive from the gas compressor at its upper reaches in the firing chamber; Diffuser is positioned at blower outlet; Its role is to reduce the interior speed of compressed air stream inflow burning chamber of blower outlet, can reduce the loss of high pressure draught in the chamber on the one hand, make the interior pressure of burning chamber even as far as possible simultaneously; Be convenient to the burner high temperature wall, especially the cooling of changeover portion.
Industry gas turbine for the advanced person; Have the air-flow of 1/2 entering firing chamber annular chamber to be used for participating in burning approximately, other has 1/4 air-flow then to be used to dilute combustion gas, regulates the burning indoor temperature distribution; To satisfy the requirement in turbine import stage efficiency and life-span; Some need be used to cool off the burner inner liner wall, therefore, only has a small amount of air-flow to can be used for the cooled transition section.Be to realize with the least possible cooling blast effective cooling of changeover portion, changeover portion has adopted such as impacting cooling, dispersing the type of cooling such as cooling in the comparatively advanced now gas turbine.The main mechanism of wherein impacting cooling is; The airflow strikes of diffuser exit is furnished with on the impact changeover portion cooling bushing of a plurality of cooling hole on the surface; Under the effect of inside and outside pressure reduction, jet impulse is quickened to form at the changeover portion wall in air communication supercooling hole, thereby reaches the purpose of cooled transition section.The diffusion cooling is similar with the impact cooling, just between changeover portion cooling bushing and changeover portion wall, is furnished with fin, is used to strengthen cooling effect.
Traditional diffuser exit radial height, angle all immobilize; Air-flow is concentrated the lower surface that impacts at the changeover portion cooling bushing; Stream subsequently to formed gap between adjacent two changeover portions, make to be flowing in the gap and quicken, cause shock point supercooling on every side; And the changeover portion both side surface of not impacted quickens to cause pressure reduction not enough because of air-flow, and cooling effect is poor.Because the changeover portion both side surface is the zone that temperature is higher, stress is concentrated, the cooling deficiency causes wall crackle to occur easily.Especially when blower outlet speed is big; During for example greater than 130m/s, the diffuser exit airspeed increases, and the mobile acceleration in the adjacent changeover portion gap is more obvious; Even the external pressure that causes cooling hole in this zone forms the refluence of cooling air less than internal pressure.At this moment, strengthen the cooling gas consumption, for example increase the diameter of cooling hole, perhaps be aided with the method for air film cooling, also be difficult to the cooling effect that reaches desirable.
Excessively quicken to influence cooling effect for avoiding flowing in the gap between the adjacent changeover portion, the position and the velocity anomaly of control diffuser exit gas shock changeover portion are crucial.Increase the radial angle of diffuser exit simply, move toward combustor inlet the position that can make the gas shock changeover portion, thus air flow rate and speed in the adjacent changeover portion gap that reduces to flow through, but as easy as rolling off a log to cause participating in the gas consumption that changeover portion cools off not enough.Some Diffuser is also arranged; The outlet radial angle is bigger; 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, yet be that the air-flow that Diffuser inwall face is drawn impacts the changeover portion wall more equably; Usually also need behind interior cinclides, to dispose a kind of flat board that has the hole of gathering in the certain distance, structure is comparatively complicated.In Diffuser, add guide plate; Form two even three passages; Also can control gas shock point and striking velocity effectively, but this need increase guide plate and corresponding supporting structure, complex structure in Diffuser; Also increased the loss of Diffuser, and this structure is just can reach effect preferably on the large scale gas turbine more than the 150MW at power level.In disclosed patent documentation CN101839256A; Adopted a kind of Diffuser of fluting; This Diffuser can be used for the cooled transition section with part air-flow guiding changeover portion, and another part directly gets into the passage between water conservancy diversion lining and the burner inner liner through the fluting of Diffuser outer wall; Thereby to a certain extent balance flow losses in changeover portion cooling and the burning chamber; Its shortcoming is that Diffuser outer wall groove is the blunt form structure, and flow velocity is higher at the fluting place, has caused extraneoas loss thus.
Summary of the invention
The purpose of this invention is to provide a kind of gas turbine waveform Diffuser, make it not only simple in structure, and can take into account the changeover portion cooling preferably and reduce the flow losses in the burning chamber.
Technological scheme of the present invention is following:
A kind of gas turbine waveform Diffuser; The upper reaches of this Diffuser are axial-flow compressor; Downstream are the burning chamber, comprise several in this burning chamber around the burner of gas turbine rotor with annular array layout, are connected through changeover portion between the burner inner liner of this burner and the turbine import; The entrance point of said Diffuser links to each other with the outlet of gas compressor, and outlet end links to each other with the burning chamber, and Diffuser comprises internal face and outer wall; It is characterized in that: said internal face and outer wall have the waveform molded lines on the circumferencial direction of gas turbine rotor; This waveform molded lines is the periodicity curve of smooth connection crest and trough, and at the circumferential position of changeover portion center correspondence, it is minimum that radius reaches; Be in the trough of wave; The corresponding circumferential position at the center in gap that adjacent changeover portion forms, radius reach maximum, the crest of corresponding wave; The periodicity of wave is identical with the number of burner.
The amplitude of waveform molded lines increases to outlet from the import of Diffuser linearly, 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.
Said periodicity curve is preferably sinusoidal curve.
The internal face of said Diffuser and outer wall molded lines vertically is a straight line; Also can be that outer wall molded lines vertically is the curve that slope increases gradually, internal face molded lines vertically be the curve that straight line or slope increase gradually.
The present invention compared with prior art; Have the following advantages and the high-lighting effect: gas turbine waveform Diffuser provided by the present invention; Can the air-flow from its upper reaches gas compressor be slowed down, the cyclically-varying that formation radius, radial angle match with the burner position at the diffuser exit place can be according to the cooling requirement of firing chamber different parts; Regulate air-flow pointedly at distribution that makes progress in week and impact position; Thereby reduce the nonuniformity of airspeed and pressure around the changeover portion, for the different changeover portion types of cooling, for example impact cooling, disperse cooling, air film cools off or convection current cooling etc.; All can improve the cooling of changeover portion effectively, reduce the flow losses of air-flow in the burning chamber simultaneously.
Description of drawings
Fig. 1 is the structural principle schematic representation of existing gas-turbine combustion chamber.
Fig. 2 is the gas-turbine combustion chamber structural principle schematic representation that has the waveform Diffuser.
Fig. 3 is the structural representation of waveform Diffuser provided by the invention.
Fig. 4 is the I-I cross-sectional view among Fig. 2.
Fig. 5 is the three-dimensional side view of waveform Diffuser and firing chamber.
List of parts: 10-burner; The 11-burner inner liner; 12-water conservancy diversion lining; The 13-changeover portion; 14-changeover portion cooling bushing; The 15-cooling hole; The 16-firing chamber; The 17-chamber of burning; The 18-Diffuser; The 19-internal face; The 20-outer wall; The 21-gas compressor; The 22-turbine; The 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 done further explanation.
Fig. 2 is the gas-turbine combustion chamber 16 structural principle schematic representation that have waveform Diffuser 18; The upper reaches of this Diffuser are axial-flow compressor 21; Downstream are burning chamber 17, comprise several in the burning chamber 17 around the burner 10 of gas turbine rotor 23 with the annular array arranged in form; The entrance point of waveform Diffuser 18 links to each other with the outlet of gas compressor 21, and outlet end links to each other with burning chamber 17, and changeover portion 13 is the subassembly of burner 10, is used to connect burner inner liner 11 outlet and turbine 22 imports.Changeover portion 13 exists certain height poor from import to outlet, and its cross section transits to rectangle from import to outlet by circle gradually.Behind the high pressure draught process waveform Diffuser 18 deceleration diffusions of gas compressor 21 outlets; Get in the burning chamber 17; Be divided into two strands, wherein a part of air-flow directly gets into burner 10 front ends through the annular pass between burner inner liner 11 and the water conservancy diversion lining 12, with the fuel blending after-combustion.Another part air-flow is under the effect of pressure reduction; Via the cooling hole on the changeover portion cooling bushing 14 15; Form the wall of jet impulse at changeover portion 13, realize the cooling to changeover portion 13 walls, this part air-flow also gets into the annular pass between burner inner liner 11 and the water conservancy diversion lining 12 subsequently.
Fig. 3 is the structural representation of waveform Diffuser, and Diffuser 18 comprises internal face 19 and outer wall 20, and internal face 19 has the waveform molded lines with outer wall 20 on the circumferencial direction of gas turbine rotor 23; The circumferential position that the center of waveform molded lines narrow slit 28 between adjacent changeover portion is corresponding; 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 air-flow is led near burner 10 front end places, more be prone to get into the annular pass between burner inner liner 11 and the water conservancy diversion lining 12; Shorten the flow process of fluid in burning chamber 17, flow resistance loss can significantly reduce.Simultaneously; Also reduced air flow rate, air-flow acceleration narrow slit 28 between adjacent changeover portion weakened through narrow slit 28 places between the adjacent changeover portion, and at the circumferential position of changeover portion 13 centers correspondence; The radius and the radial angle of internal face 19 and outer wall 20 all reach minimum; Be in the trough of wave, thereby with enough air-flow guiding changeover portions 13, this strand air-flow at first strikes the lower surface of changeover portion cooling bushing 14; Wherein part air-flow cooling hole 15 through changeover portion cooling bushing 14 under the effect of inside and outside differential pressure forms jet impulse to changeover portion 13; Realization is to the cooling of changeover portion 13 bottoms, and another part then streams to narrow slit 28 between the adjacent changeover portion, is used for the cooling of changeover portion 13 both side surface.Owing to only have the part air-flow to be directed to changeover portion 13; So air-flow is the acceleration in the narrow slit 28 and not obvious between adjacent changeover portion; Make the pressure distribution of changeover portion cooling bushing 14 both side surface more even, improved the cooling effect of changeover portion 13 bi-side effectively.
As can be seen from Figure 3, internal face 19 arranges that at the concave, convex of different circumferential positions be formed naturally very much the wave molded lines, this waveform molded lines can be sinusoidal curve, or the periodicity curve of other smooth connection crest and trough with outer wall 20.In the whole circumference direction, the number of the periodicity of wave and burner 10 should be identical, and wavelength L is the occupied circumferential arc length in each wave mean radius position.The amplitude of waveform molded lines is to influence the important parameter that Diffuser 18 exit flows impact changeover portion 13 positions and speed; Its numerical value can be regulated according to the structure of firing chamber 16 and the cooling requirement of changeover portion 13, and the amplitude of internal face 19 and outer wall 20 can be divided other optimization.When amplitude was too small, Diffuser 18 was regulated the DeGrain of exit flow impact positions and changeover portion 13 cooling assignment of traffic, and amplitude is when excessive, will increase the interior flow losses of Diffuser 18.Amplitude increases from Diffuser 18 imports to outlet gradually.Usually, 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 molded lines vertically can be straight line, also can be curve, adopt curve can make outlet obtain bigger radial angle, for example, adopt the bell line, and radial angle obviously increases in outlet.The axial molded lines of internal face 19 and outer wall 20 can have various combination forms according to the needs of design, and for example, internal face 19 is straight line with outer wall 20; Perhaps internal face 19 is curve with outer wall 20; Can internal face 19 be straight line also, outer wall 20 be a curve.Because internal face 20 is a curve, and outer wall 20 can't form appropriate assignment of traffic for the combining form of straight line, does not adopt.As an exemplary embodiment, Diffuser 18 walls shown in Figure 3 molded lines vertically are straight line.
Fig. 4 is a preferred embodiment of the present invention.Among this embodiment; Have six burners 10 and evenly arrange with the annular array form that around gas turbine rotor 23 the wave molded lines of Diffuser 18 has adopted sinusoidal curve, its periodicity is six; Identical with the number of burner 10, the axial molded lines of Diffuser 18 has adopted the simplest straight line.To outlet, the amplitude of internal face 19 and outer wall 20 waves increases linearly from Diffuser 18 imports.The amplitude A of Diffuser 18 outlet port waves chooses according to mobile being optimized in the burning chamber 17; In the present embodiment; It when the amplitude of internal face 19 outlet port waves 0.18 times of its wavelength L; And the amplitude of outer wall 20 outlet port waves is when being 0.15 times of its wavelength L, can make changeover portion 13 ambient pressures distribute with burning chamber 17 in flow resistance losses reach better balance, be the optimal magnitude value.
Fig. 5 is the three-dimensional side view of waveform Diffuser 18 and firing chamber 16, has illustrated spatial relation between waveform Diffuser, burner 10 and the changeover portion cooling bushing 14 (or changeover portion 13).
Though the present invention thinks that practicality the most and preferred embodiment describe at present, should know that the present invention is not limited to the disclosed embodiments, and should cover various modifications and the equivalent arrangements that is comprised within the protection domain that claims limit.
Claims (5)
1. gas turbine waveform Diffuser; The upper reaches of this Diffuser are axial-flow compressor (21); Downstream are burning chamber (17); Comprise the burner (10) that several are arranged with annular array around gas turbine rotor (23) in this burning chamber (17), be connected through changeover portion (13) between the burner inner liner (11) of this burner (10) and turbine (22) import; The entrance point of said Diffuser (18) links to each other with the outlet of gas compressor (21); Outlet end links to each other with burning chamber (17); Diffuser comprises internal face (19) and outer wall (20), it is characterized in that: said internal face (19) and outer wall (20) have the waveform molded lines on the circumferencial direction of gas turbine rotor (23); Described waveform molded lines is the periodicity curve of smooth connection crest and trough; The circumferential position that this waveform molded lines is corresponding at changeover portion (13) center; It is minimum that radius reaches, and is in the trough of wave, the circumferential position that the center of narrow slit between adjacent changeover portion (28) is corresponding; It is maximum that radius reaches, the crest of corresponding wave; The periodicity of wave is identical with the number of burner (10).
2. gas turbine waveform Diffuser according to claim 1; It is characterized in that: the amplitude of waveform molded lines increases from import to the outlet of Diffuser (18) linearly; 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.
3. a kind of gas turbine waveform Diffuser according to claim 1, it is characterized in that: said periodicity curve is a sinusoidal curve.
4. a kind of gas turbine waveform Diffuser according to claim 1 is characterized in that: said internal face (19) and outer wall (20) molded lines vertically are straight line.
5. a kind of gas turbine waveform Diffuser device according to claim 1, it is characterized in that: said outer wall (20) molded lines vertically is the curve that slope increases gradually, internal face (19) molded lines vertically is the curve that straight line or slope increase gradually.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110421605.4A CN102444476B (en) | 2011-12-15 | 2011-12-15 | Wave-shaped diffuser of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110421605.4A CN102444476B (en) | 2011-12-15 | 2011-12-15 | Wave-shaped diffuser of gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102444476A true CN102444476A (en) | 2012-05-09 |
| CN102444476B CN102444476B (en) | 2014-05-14 |
Family
ID=46007341
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110421605.4A Active CN102444476B (en) | 2011-12-15 | 2011-12-15 | Wave-shaped diffuser of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102444476B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103870620A (en) * | 2012-12-14 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Parameterization modeling method for fusion design of diffuser and outlet guide vane |
| CN104596723A (en) * | 2015-01-28 | 2015-05-06 | 中誉远发国际建设集团有限公司 | Production method of diffuser used in aerodynamic experiments |
| 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 |
| CN113983494A (en) * | 2021-09-22 | 2022-01-28 | 南京航空航天大学 | Diffusion ratio intelligent adjustable gas turbine main combustion chamber multi-channel diffuser |
| US11242990B2 (en) | 2019-04-10 | 2022-02-08 | Doosan Heavy Industries & Construction Co., Ltd. | Liner cooling structure with reduced pressure losses and gas turbine combustor having same |
| CN114412594A (en) * | 2022-01-25 | 2022-04-29 | 中国联合重型燃气轮机技术有限公司 | Gas turbine |
| CN115342078A (en) * | 2022-10-20 | 2022-11-15 | 杭州顿力电器有限公司 | High-efficiency centrifugal fan with module diffusion structure |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6978976B2 (en) * | 2018-04-18 | 2021-12-08 | 三菱重工業株式会社 | Compressor diffuser, gas turbine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6153330A (en) * | 1995-09-01 | 2000-11-28 | Rayovac Corporation | Alkaline manganese dioxide electrochemical cell having coated can treated with silicon compounds |
| US20050138915A1 (en) * | 2003-05-28 | 2005-06-30 | Snecma Moteurs | Turbomachine nozzle with noise reduction |
| CN101315071A (en) * | 2007-06-01 | 2008-12-03 | 刘友宏 | Shock absorption energy-saving device of reciprocating compressor |
| CN101839256A (en) * | 2009-03-19 | 2010-09-22 | 通用电气公司 | Compressor diffuser |
| CN202360225U (en) * | 2011-12-15 | 2012-08-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Wave-type diffuser of combustion gas turbine |
-
2011
- 2011-12-15 CN CN201110421605.4A patent/CN102444476B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6153330A (en) * | 1995-09-01 | 2000-11-28 | Rayovac Corporation | Alkaline manganese dioxide electrochemical cell having coated can treated with silicon compounds |
| US20050138915A1 (en) * | 2003-05-28 | 2005-06-30 | Snecma Moteurs | Turbomachine nozzle with noise reduction |
| CN101315071A (en) * | 2007-06-01 | 2008-12-03 | 刘友宏 | Shock absorption energy-saving device of reciprocating compressor |
| CN101839256A (en) * | 2009-03-19 | 2010-09-22 | 通用电气公司 | Compressor diffuser |
| CN202360225U (en) * | 2011-12-15 | 2012-08-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Wave-type diffuser of combustion gas turbine |
Non-Patent Citations (1)
| Title |
|---|
| 焦树建: "《燃气轮机燃烧室》", 30 June 1981, article "《环管型燃烧室的典型结构》", pages: 151 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103870620A (en) * | 2012-12-14 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Parameterization modeling method for fusion design of diffuser and outlet guide vane |
| CN104596723A (en) * | 2015-01-28 | 2015-05-06 | 中誉远发国际建设集团有限公司 | Production method of diffuser used in aerodynamic experiments |
| 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 |
| US11242990B2 (en) | 2019-04-10 | 2022-02-08 | Doosan Heavy Industries & Construction Co., Ltd. | Liner cooling structure with reduced pressure losses and gas turbine combustor having same |
| CN113983494A (en) * | 2021-09-22 | 2022-01-28 | 南京航空航天大学 | Diffusion ratio intelligent adjustable gas turbine main combustion chamber multi-channel diffuser |
| 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 |
| CN114412594A (en) * | 2022-01-25 | 2022-04-29 | 中国联合重型燃气轮机技术有限公司 | Gas turbine |
| CN114412594B (en) * | 2022-01-25 | 2024-08-23 | 中国联合重型燃气轮机技术有限公司 | Heavy gas turbine shell structure |
| CN115342078A (en) * | 2022-10-20 | 2022-11-15 | 杭州顿力电器有限公司 | High-efficiency centrifugal fan with module diffusion structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102444476B (en) | 2014-05-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102444476B (en) | Wave-shaped diffuser of gas turbine | |
| CN104153884B (en) | A kind of rotation pinking gas turbine | |
| CN102959205B (en) | Insert the heat exchange structure in turbine engine exhaust device | |
| CN103185353B (en) | Burner assembly in turbogenerator and assemble method thereof | |
| CN102401397B (en) | Apparatus and method for mixing fuel in gas turbine nozzle | |
| JP5674336B2 (en) | Combustor can flow control device | |
| CN203757767U (en) | Floating wall type flame drum macropore structure with flow guide edge | |
| CN106958836A (en) | Bundle pipes fuel nozzle assembly with liquid fuel capacity | |
| CN202360225U (en) | Wave-type diffuser of combustion gas turbine | |
| CN101900340A (en) | Methods and systems to enhance flame holding in a gas turbine engine | |
| CN101625120A (en) | Combustor structure | |
| CN204082338U (en) | A kind of rotation pinking gas turbine | |
| CN106524152A (en) | Graded gas low-nitrogen burner | |
| CN103764953B (en) | The inner colded component of energy for gas turbine | |
| CN107709884A (en) | Fuel Nozzle Assembly | |
| CN207648852U (en) | A kind of combustion chamber and gas turbine | |
| CN107062306A (en) | A kind of combustion chamber and gas turbine | |
| CN102356279B (en) | Method for operating burner and burner, in particular for gas turbine | |
| CN102777934A (en) | Standing-vortex soft combustion chamber | |
| CN107796017A (en) | A kind of combustion chamber and gas turbine | |
| CN102297426A (en) | Hydrogen gas combustor | |
| CN206861592U (en) | A kind of combustion chamber and gas turbine | |
| CN202813440U (en) | Combustion chamber of small-sized turbine jet engine | |
| CN202544933U (en) | Gas diversion volute | |
| CN204611837U (en) | A kind of combustion chamber |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
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 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
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 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| TR01 | Transfer of patent right |
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. |
|
| TR01 | Transfer of patent right |