CN204851442U - A exhaust diffuser, turbine and combined cycle system for turbine - Google Patents
A exhaust diffuser, turbine and combined cycle system for turbine Download PDFInfo
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- CN204851442U CN204851442U CN201520116685.6U CN201520116685U CN204851442U CN 204851442 U CN204851442 U CN 204851442U CN 201520116685 U CN201520116685 U CN 201520116685U CN 204851442 U CN204851442 U CN 204851442U
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- 230000007704 transition Effects 0.000 claims abstract description 26
- 239000012530 fluid Substances 0.000 claims abstract description 8
- 238000011084 recovery Methods 0.000 claims description 10
- 230000008859 change Effects 0.000 claims description 6
- 230000000087 stabilizing effect Effects 0.000 abstract 3
- 239000007789 gas Substances 0.000 description 32
- 238000010438 heat treatment Methods 0.000 description 21
- 230000004087 circulation Effects 0.000 description 7
- 238000010248 power generation Methods 0.000 description 6
- 238000011144 upstream manufacturing Methods 0.000 description 6
- 239000007859 condensation product Substances 0.000 description 5
- 238000005452 bending Methods 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 4
- 239000006200 vaporizer Substances 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005381 potential energy Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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- 230000003068 static effect Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
- F01K23/00—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids
- F01K23/02—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled
- F01K23/06—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle
- F01K23/10—Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/32—Arrangement of components according to their shape
- F05D2250/324—Arrangement of components according to their shape divergent
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/16—Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The utility model relates to an exhaust diffuser, turbine and combined cycle system for turbine. The utility model discloses an exhaust diffuser of turbine including the supporting on the turbine rotor, with the diffuser of the axis alignment of turbine rotor. The diffuser is constructed into messenger's turbine exhaust phase and is reached roughly 90 degrees to the first mobile orientation redirecting along rotor axis. The pressure stabilizing chamber is in the fluid intercommunication with the exit end of diffuser, and surrounds the exit end of diffuser. The pressure stabilizing chamber is in the fluid intercommunication with the transition pipe, and the transition pipe is suitable for exhaust supply to another turbine. The volume of pressure stabilizing chamber is expanded between diffuser and transition pipe.
Description
Technical field
The utility model relates generally to and heat recovery steam generation (HRSG) system is combined with gas turbine exhaust component, more specifically, relates to turbine exhaust plenum, and it is designed to promote that combustion gas evenly flow into HRSG.
Background technique
In combined cycle power generation systems, the exhaust through heating of discharging from gas turbine can be used as thermal source by HRSG system, and thermal source can be passed to water source to generate superheated vapor.Superheated vapor can be used as power source again then in steamturbine.The exhaust through heating from gas turbine can be delivered to HRSG via exhaust plenum and diffuser etc., and this kinetic energy that can contribute to the exhaust through heating of the final stage by flowing out gas turbine converts the potential energy in the static pressure form increased to.Once be delivered to HRSG system, the exhaust through heating can cross a series of heat exchanger element, e.g., and superheater, reheater, vaporizer, vapor economizer etc.Heat exchanger element can be used for heat to be passed to water source to generate superheated vapor from the exhaust through heating.Design object is to promote through the equal uniform flow of exhaust plenum, and can not adversely affect diffuser performance, that is, allow stream diffusion, and do not have can loss of total pressure significantly.
Model utility content
In one embodiment, provide a kind of exhaust diffuser for turbo machine, it comprises and is bearing in diffuser in turbine rotor, that aim at the axis of turbine rotor, and diffuser is configured to make turbine exhaust change direction relative to the first flow direction along axis and reaches approximately ninety degrees; Be in fluid with the outlet end of diffuser to be communicated with and the plenum surrounding outlet end, plenum be suitable for being in fluid being communicated with being vented the transition duct being supplied to another turbo machine; Wherein the volume of plenum is expanded along the direction towards transition duct.
In another embodiment, provide a kind of turbo machine, it comprises: gas turbine section, and it comprises turbine rotor; Along the radial diffuser that the first axle of turbine rotor is arranged; Exhaust plenum, it comprises the entrance of the part receiving radial diffuser, and exhaust plenum is along the second Axis Extension being approximately perpendicular to first axle, and the volume of plenum is expanded along the second axis.
In yet another embodiment, provide a kind of combined cycle system, it comprises: gas turbine, and it comprises the turbine rotor extended along first axle; Heat recovery steam generator; Be suitable for the steamturbine of the steam receiving heat recovery steam generator; Along the radial diffuser that first axle is arranged; And exhaust plenum, it comprises the entrance of the part receiving radial diffuser, and exhaust plenum is along the second Axis Extension being approximately perpendicular to first axle, and the volume of plenum is expanded along the second axis, and is communicated with heat recovery steam generator.
For an exhaust diffuser for turbo machine, comprising:
Be bearing in diffuser in turbine rotor, that aim at the axis of described turbine rotor, described diffuser is configured to make turbine exhaust change direction relative to the first flow direction along described axis and reaches approximately ninety degrees; Be in fluid with the outlet end of described diffuser to be communicated with and the plenum surrounding described outlet end, described plenum and transition duct are in fluid and are communicated with, and described transition duct is suitable for exhaust to be supplied to another turbo machine; The volume of wherein said plenum is expanded along the direction towards described transition duct.
In one embodiment, described plenum is partly made up of with the perimeter wall being connected described paired non-parallel side-walls paired non-parallel side-walls.
In one embodiment, the one in described paired non-parallel side-walls is approximately perpendicular to described axis.
In one embodiment, the another one in described paired non-parallel side-walls extends with the angle of 20 ° to 50 ° relative to the described one in described non-parallel side-walls.
In one embodiment, the another one in described paired non-parallel side-walls extends with the angle of 35 ° to 45 ° relative to the described one in described non-parallel side-walls.
In one embodiment, described perimeter wall comprises rounded end, and it is connected on paired straight almost parallel top wall portion and bottom wall portion.
In one embodiment, described rounded end is positioned at the side of described axis, and described paired straight almost parallel top wall portion and bottom wall portion stride across described axis, are connected in described transition duct at the opposite side of described axis.
In one embodiment, the another one in described paired non-parallel side-walls extends with the angle of 20 ° to 50 ° relative to the described one in described non-parallel side-walls.
In one embodiment, the another one in described paired non-parallel side-walls extends with the angle of 35 ° to 45 ° relative to the described one in described non-parallel side-walls.
A kind of turbo machine, comprising:
Comprise the gas turbine section of turbine rotor;
Along the radial diffuser that the first axle of described turbine rotor is arranged;
Exhaust plenum, it comprises the entrance of the part receiving described radial diffuser, and described exhaust plenum is along the second Axis Extension being approximately perpendicular to described first axle, and the volume of described plenum is along described second axis expansion.
In one embodiment, described plenum is partly made up of with the perimeter wall being connected described paired non-parallel side-walls paired non-parallel side-walls.
In one embodiment, the one in described paired non-parallel side-walls is approximately perpendicular to described axis.
In one embodiment, the another one in described paired non-parallel side-walls extends with the angle of 20 ° to 50 ° relative to the described one in described non-parallel side-walls.
In one embodiment, the another one in described paired non-parallel side-walls extends with the angle of 35 ° to 45 ° relative to the described one in described non-parallel side-walls.
In one embodiment, described perimeter wall comprises rounded end, and it is connected on paired straight almost parallel top wall portion and bottom wall portion.
In one embodiment, described rounded end is positioned at the side of described axis, and described paired straight almost parallel top wall portion and bottom wall portion stride across described axis, are connected in described transition duct at the opposite side of described axis.
A kind of combined cycle system, comprising: gas turbine, and it comprises the turbine rotor extended along first axle; Heat recovery steam generator; Be suitable for receiving the steamturbine from the steam of described heat recovery steam generator; Along the radial diffuser that described first axle is arranged; And
Exhaust plenum, it comprises the entrance of the part receiving described radial diffuser, described exhaust plenum is along the second Axis Extension being approximately perpendicular to described first axle, and the volume of described plenum along described second axis expansion, and is communicated with described heat recovery steam generator.
In one embodiment, described plenum is partly made up of with the perimeter wall being connected described paired non-parallel side-walls paired non-parallel side-walls, and the one in wherein said paired non-parallel side-walls is approximately perpendicular to described axis.
In one embodiment, the another one in described paired non-parallel side-walls extends with the angle of 20 ° to 50 ° relative to the described one in described non-parallel side-walls.
In one embodiment, the another one in described paired non-parallel side-walls extends with the angle of 35 ° to 45 ° relative to the described one in described non-parallel side-walls.
Accompanying drawing explanation
When reading following detailed description in detail with reference to accompanying drawing, these and other feature of the present utility model, aspect and advantage will become better understood, and wherein, same-sign represents same parts in the drawings, wherein:
Fig. 1 is the indicative flowchart of the embodiment of the combined cycle power generation systems with gas turbine, steamturbine and HRSG;
Fig. 2 is the side cross-sectional view of the detailed of the embodiment of the gas turbine of Fig. 1 but local, and it makes the heat exchanger element of the HRSG of Fig. 1 combine with the component of the exhaust diffuser of gas turbine;
Fig. 3 is the sectional perspective view of the exhaust plenum of the type that can be used in the gas turbine of Fig. 2;
The broken section plan view that Fig. 4 is the exhaust plenum shown in Fig. 3;
Fig. 5 is according to the exemplary but perspective view of the exhaust diffuser of non-limiting example and plenum of the present utility model;
Another perspective view that Fig. 6 is the exhaust diffuser shown in Fig. 5 and plenum; And
The plan view from above that Fig. 7 is the exhaust diffuser shown in Fig. 5 and Fig. 6 and plenum;
Fig. 8 shows the HRSG entrance distributing line at the downstream edge place of plenum pelvic outlet plane place and transition zone.
List of parts:
10 systems
12 gas turbines
14 first loads
16 turbines
18 burners
20 compressors
22 steamturbines
24 second loads
26 low pressure sections (LPST)
Pressure section (IPST) in 28
30 high pressure section (HPST)
There is (HRSG) in 32 Multi-stage heat recovered steams
34 through heating exhaust
36 condensers
38 condensate pump
40 low pressure vapor economizers (LPECON)
42 low pressure evaporators (LPEVAP)
Vapor economizer (IPECON) is pressed in 44
Vaporizer (IPEVAP) is pressed in 46
48 high pressure vapor economizers (HPECON)
50 high pressure evaporators (HPEVAP)
52 main high-pressure superheaters
54 final high-pressure superheaters
56 inter-stage attemperator
58 main reheaters
60 secondary reheaters
62 inter-stage attemperator
64 air intlets
66 fuel nozzles
68 exhaust diffusers
70 exit guide blades
72 exhaust frame pillars
74 plenums
76 transition duct
78 angled end wall parts
80 roofs
82 sidewalls
84 upstream sides
86 downstream sides
88 diapires
90 dip members
100 through improvement plenum
101 radial diffusers
102 bending end walls
104 roofs
106 diapires
108 upstream sidewalls
110 downstream sidewalls
112 transition zones
114 turbine rotor axis (first axle)
116 plenum pelvic outlet planes (the second axis)
118 downstream edges.
Embodiment
To be described one or more specific embodiment of the present utility model below.In order to be devoted to provide the simple and clear description to these embodiments, may be described all features that reality realizes in the description.Be to be understood that, when such as develop in any engineering or design object any this actual realize time, many decisions proprietary for realization must be made to realize the objectives of developer, such as meet with system about and the constraint relevant with business, the objectives of developer can change each other to some extent according to different realizations.In addition, should be appreciated that this development may be complicated and consuming time, however, concerning the those of ordinary skill with benefit of the present disclosure, this development is by the routine mission being design, produce and manufacture.
When introducing the element of various embodiment of the present utility model, there is this element one or more in article " ", " one ", the expression of " being somebody's turn to do " and " described " intention.Term " comprises ", " comprising " and " having " be intended to comprising property, and represent except the element listed, and can there is other element.Any example of operating parameter does not all get rid of other parameter of disclosed embodiment.
Fig. 1 is the indicative flowchart of the embodiment of the combined cycle power generation systems 10 with gas turbine, steamturbine and HRSG.Specifically, system 10 can comprise the gas turbine 12 for driving the first load 14.Such as, the first load 14 can be the generator for generation of electric power.Gas turbine 12 can comprise turbine 16, burner 18 and compressor 20.System 10 also can comprise the steamturbine 22 for driving the second load 24.Second load 24 also can be the generator for generating electric power.But, will be appreciated that both the first load 14 and the second load 24 can be the load of other type that can be driven by gas turbine 12 and steamturbine 22.In addition, although gas turbine 12 and steamturbine 22 such shown in as directed embodiment can drive independent load 14 and 24, gas turbine 12 and steamturbine 22 also can be connected in series and make for driving single load via single axle.In an illustrated embodiment, steamturbine 22 can comprise a low pressure section 26 (LPST), a middle pressure section 28 (IPST), and a high pressure section 30 (HPST).But it is distinctive that the particular configuration of steamturbine 22 and gas turbine 12 can be mode of execution, and can comprise any combination of section and/or level.
System 10 also can comprise multistage HRSG32.The simplification of HRSG32 and component thereof describes and is not intended to as restrictive.On the contrary, shown HRSG32 shows the general arrangement for expressing this type systematic.The exhaust 34 through heating from gas turbine 12 can be transported in HRSG32, and for heating for the steam to steamturbine 22 energy supply.Exhaust from the low pressure section 26 of steamturbine 22 can be directed in condenser 36.The condensation product carrying out condenser 36 can be directed in the low pressure section of HRSG32 by means of condensate pump 38 again then.
Then condensation product can flow through low pressure vapor economizer 40 (LPECON), and it is be configured to the device with gas-heated feedwater, can be used for heating-condensing thing.Condensation product can be directed into low pressure evaporator 42 (LPEVAP) or middle pressure vapor economizer 44 (IPECON) from low pressure vapor economizer 40.Steam from low pressure evaporator 42 can return the low pressure section 26 of steamturbine 22.Equally, condensation product can therefrom press vapor economizer 44 to be directed into middle pressure vaporizer 46 (IPEVAP) or high pressure vapor economizer 48 (HPECON).In addition, the steam from middle pressure vapor economizer 44 can be sent to fuel gas heater (not shown), and wherein steam can be used for heating fuel gas, to use in the burner 18 of gas turbine 12.Steam from middle pressure vaporizer 46 can be sent to pressure section 28 in steamturbine 22.
Finally, the condensation product from high pressure vapor economizer 48 can be directed in high pressure evaporator 50 (HPEVAP).The steam flowing out high pressure evaporator 50 is bootable to main high-pressure superheater 52 and final high-pressure superheater 54, and wherein steam is overheated, and is finally sent to the high pressure section 30 of steamturbine 22.Exhaust from the high pressure section 30 of steamturbine 22 can be directed in steamturbine 22 in pressure section 28 again then, and can be directed in the low pressure section 26 of steamturbine 22 from the exhaust of pressure section 28 in steamturbine 22.
Inter-stage attemperator 56 can between main high-pressure superheater 52 and final high-pressure superheater 54.Inter-stage attemperator 56 can allow to carry out more reliable and more stable control to the delivery temperature of the steam from final high-pressure superheater 54.
In addition, the exhaust from the high pressure section 30 of steamturbine 22 can be directed in main reheater 58 and secondary reheater 60, and wherein it can heat before being directed in steamturbine 22 in pressure section 28 again.Main reheater 58 and secondary reheater 60 also can be associated with inter-stage attemperator 62, for the exhaust steam temperature controlled from reheater.
In the combined cycle system of such as system 10, thermal exhaust can flow out from gas turbine 12, and through HRSG32, and can be used for generating high-pressure and high-temperature steam.The steam produced by HRSG32 then can through steamturbine 22 for generation of power.In addition, the steam of generation also can be supplied to other process any that can use superheated vapor.The generation circulation of gas turbine 12 is commonly referred to " top circulation ", and the generation of steamturbine 22 circulation is commonly referred to " end circulation ".By combining these two circulations as shown in Figure 1, combined cycle power generation systems 10 has higher efficiency during two can be caused to circulate.Specifically, from top circulation exhaust heat can be captured and for be created on the end circulation in use steam.
Therefore, an aspect of combined cycle power generation systems 10 is to use HRSG32 to trap heat again from the exhaust 34 of heating.As shown in fig. 1, the component of gas turbine 12 and HRSG32 can be divided into independent functional unit.In other words, gas turbine 12 can generate the exhaust 34 through heating, and guides the exhaust 34, HRSG32 through heating can trap heat by generating superheated vapor again from the exhaust 34 through heating by primary responsibility towards HRSG32.Superheated vapor can be used as power source by steamturbine 22 again then.Exhaust 34 through heating can be passed to HRSG32 via pipeline, and pipeline can change based on the particular design of combined cycle power generation systems 10.
The more detailed diagram how gas turbine 12 works can contribute to illustrating how the exhaust 34 through heating can be passed to HRSG32 from gas turbine 12.Therefore, Fig. 2 is the detailed side view of the embodiment of the gas turbine 12 of Fig. 1, and it makes the heat exchanger element of the HRSG32 of Fig. 1 combine with the component of the exhaust diffuser of gas turbine 12.As described with reference to FIG. 1, gas turbine 12 can comprise turbine 16, burner 18 and compressor 20.Air can enter via air intlet 64, and is compressed by compressor 20.Next, the pressurized air from compressor 20 can be directed in burner 18, and wherein pressurized air can mix with fuel gas.Fuel can be ejected in burner 18 via multiple fuel nozzle 66.The mixture of pressurized air and fuel gas, substantially in the firing chamber combustion of burner 18, is used in the interior High Temperature High Pressure combustion gas generating torque of turbine 16 to generate.The rotor of turbine 16 can be connected on the rotor of compressor 20, makes the rotation of turbine rotor also can cause the rotation of compressor 20.In this way, turbine 16 drives compressor 20 and load 14 (not shown in Fig. 2).Exhaust from the turbine 16 of gas turbine 12 can be directed in exhaust diffuser 68.In the embodiment of fig. 2, exhaust diffuser 68 can be radial exhaust diffuser, exhaust can change direction by exit guide blade 70 thus, with by 90 degree outside (namely, radially) turn to and flow out exhaust diffuser 68, arriving HRSG32 through exhaust plenum (not shown) and transition entrance.
Except guiding to except HRSG32 by the exhaust 34 through heating, the another aspect of some component of exhaust diffuser 68 can be some the aerodynamic force character guaranteeing the exhaust 34 realized through heating.Such as, exhaust frame pillar 72 shown in Fig. 2 can be curved surface, and airfoil is enclosed in around it.Exhaust frame pillar 72 is also rotatable, and the vortex of exhaust 34 through heating can be minimized, and character is comparatively axial substantially, until flow through exit guide blade 70 through the flowing of the exhaust 34 of heating.In addition, exit guide blade 70 can also be designed so that, when turning to the angle of 90 degree through the exhaust 34 of heating towards exhaust plenum, exit guide blade 70 reduces to greatest extent and stream is radially rotated 90 degree of aerodynamic losses caused in one way.Therefore, the aerodynamic design be applicable to of other component of exhaust frame pillar 72, exit guide blade 70 and the exhaust diffuser 68 in the flow passage of the exhaust 34 of heating can be design consideration.
Fig. 3 is the sectional perspective view of the embodiment of diffuser, and it can be similar to the diffuser 68 in Fig. 2, but conveniently, will recognize diffuser not to illustrate with the same ratio of Fig. 2.Diffuser 68 is connected on plenum 74, and exhaust is changed direction and reaches roughly nine ten (90) and spend by plenum 74 together with stator 46, and makes it enter in transition duct 76, and transition duct 76 is connected on HRSG entrance (not shown).Radial stator 46 can be circle (such as, conical ring or conical structure), and is arranged to around x-axis line 31 concentric.Then plenum 74 little by little guides combustion gas to enter expansion transition zone 76 along z-axis line 35, and transition zone 76 is connected on the entrance of HRSG.
The plenum 74 of the known configuration shown in Fig. 3 and 4 is substantially square or rectangle, but the end wall portion 78 of its medium dip extends to sidewall 82 from roof 80.Wall 80 and 82 is approximately perpendicular to each other, and upstream side 84 is parallel like that as best seen in fig. 4 respectively with downstream side 86 simultaneously.Diapire 88 is parallel to roof 80, but can have dip member 90 between diapire 88 and sidewall 82.
Fig. 5-7 shows according to the exemplary but plenum 100 of the improvement of nonrestrictive embodiment of the present utility model.Radial diffuser 101 is received in plenum entrance, concentric with turbine rotor axis 114 (Fig. 7).In this example, plenum 100 is formed with fillet (radiused) end, and it is limited by the bending end wall 102 converged with roof 104 and diapire 106.Bending end wall 102 and roof 104 and diapire 106 form perimeter wall upstream sidewall 108 and downstream sidewall 110 jointly, and it extends to expansion transition zone 112 from fillet end wall 102.Bending end wall 102 is plotted in (here not proportional drafting again) on the central axis 114 of diffuser 101, and roof 104 and diapire 106 tangentially extend abreast from the opposite end of fillet end wall.Note, flat roof 104 and diapire 106 stride across the axis 114 of diffuser/turbine rotor.
Will be appreciated that the inside stator component of diffuser can be similar to the layout shown in Fig. 3.
Be apparent that, upstream sidewall 108 and downstream sidewall 110 not parallel.As best seen in figure 7, downstream sidewall 110 is perpendicular to central axis 114, but upstream sidewall 108 extends with the angle of (and preferably between 35 to 45 degree) between about 20 to 50 degree relative to downstream sidewall 110.Flow passage facilitates uniform air-flow from plenum 100 to this expansion of transition zone 112 and is redistributed to HRSG entrance, and does not affect diffuser performance.In fact, uniform stream is not only of value to HRSG performance, but also simplifies the design of the HRSG baffler being arranged in HRSG entrance.Plenum design as herein described also achieves relatively flat entrance distribution in operation conditions and in the final stage turbine vane outlet distribution of certain limit.
Fig. 8 shows the HRSG entrance distributing line at downstream edge 118 place of plenum pelvic outlet plane 116 place and transition zone 112.Y-axis line " % span " refers to the height from bottom to top of plenum.It is seen that the height that " Sum velocity " that pass the air stream of plenum strides across plenum is relatively consistent.
Although in conjunction with current thought the most practical and preferred embodiment describes the utility model, but will be appreciated that, the utility model is not limited to disclosed embodiment, and on the contrary, intention covers various remodeling included in the spirit and scope of the appended claims and equivalent arrangements.
Claims (20)
1., for an exhaust diffuser for turbo machine, comprising:
Be bearing in diffuser in turbine rotor, that aim at the axis of described turbine rotor, described diffuser is configured to make turbine exhaust change direction relative to the first flow direction along described axis and reaches approximately ninety degrees; Be in fluid with the outlet end of described diffuser to be communicated with and the plenum surrounding described outlet end, described plenum and transition duct are in fluid and are communicated with, and described transition duct is suitable for exhaust to be supplied to another turbo machine; The volume of wherein said plenum is expanded along the direction towards described transition duct.
2. exhaust diffuser according to claim 1, is characterized in that, described plenum is partly made up of with the perimeter wall being connected described paired non-parallel side-walls paired non-parallel side-walls.
3. exhaust diffuser according to claim 2, is characterized in that, the one in described paired non-parallel side-walls is approximately perpendicular to described axis.
4. exhaust diffuser according to claim 3, is characterized in that, the another one in described paired non-parallel side-walls extends with the angle of 20 ° to 50 ° relative to the described one in described non-parallel side-walls.
5. exhaust diffuser according to claim 3, is characterized in that, the another one in described paired non-parallel side-walls extends with the angle of 35 ° to 45 ° relative to the described one in described non-parallel side-walls.
6. exhaust diffuser according to claim 2, is characterized in that, described perimeter wall comprises rounded end, and it is connected on paired straight almost parallel top wall portion and bottom wall portion.
7. exhaust diffuser according to claim 6, it is characterized in that, described rounded end is positioned at the side of described axis, and described paired straight almost parallel top wall portion and bottom wall portion stride across described axis, are connected in described transition duct at the opposite side of described axis.
8. exhaust diffuser according to claim 7, is characterized in that, the another one in described paired non-parallel side-walls extends with the angle of 20 ° to 50 ° relative to the described one in described non-parallel side-walls.
9. exhaust diffuser according to claim 7, is characterized in that, the another one in described paired non-parallel side-walls extends with the angle of 35 ° to 45 ° relative to the described one in described non-parallel side-walls.
10. a turbo machine, comprising:
Comprise the gas turbine section of turbine rotor;
Along the radial diffuser that the first axle of described turbine rotor is arranged;
Exhaust plenum, it comprises the entrance of the part receiving described radial diffuser, and described exhaust plenum is along the second Axis Extension being approximately perpendicular to described first axle, and the volume of described plenum is along described second axis expansion.
11. turbo machines according to claim 1, is characterized in that, described plenum is partly made up of with the perimeter wall being connected described paired non-parallel side-walls paired non-parallel side-walls.
12. turbo machines according to claim 11, is characterized in that, the one in described paired non-parallel side-walls is approximately perpendicular to described axis.
13. turbo machines according to claim 12, is characterized in that, the another one in described paired non-parallel side-walls extends with the angle of 20 ° to 50 ° relative to the described one in described non-parallel side-walls.
14. turbo machines according to claim 12, is characterized in that, the another one in described paired non-parallel side-walls extends with the angle of 35 ° to 45 ° relative to the described one in described non-parallel side-walls.
15. turbo machines according to claim 11, is characterized in that, described perimeter wall comprises rounded end, and it is connected on paired straight almost parallel top wall portion and bottom wall portion.
16. turbo machines according to claim 15, it is characterized in that, described rounded end is positioned at the side of described axis, and described paired straight almost parallel top wall portion and bottom wall portion stride across described axis, are connected in described transition duct at the opposite side of described axis.
17. 1 kinds of combined cycle systems, comprising: gas turbine, and it comprises the turbine rotor extended along first axle; Heat recovery steam generator; Be suitable for receiving the steamturbine from the steam of described heat recovery steam generator; Along the radial diffuser that described first axle is arranged; And
Exhaust plenum, it comprises the entrance of the part receiving described radial diffuser, described exhaust plenum is along the second Axis Extension being approximately perpendicular to described first axle, and the volume of described plenum along described second axis expansion, and is communicated with described heat recovery steam generator.
18. combined cycle systems according to claim 17, it is characterized in that, described plenum is partly made up of with the perimeter wall being connected described paired non-parallel side-walls paired non-parallel side-walls, and the one in wherein said paired non-parallel side-walls is approximately perpendicular to described axis.
19. combined cycle systems according to claim 18, is characterized in that, the another one in described paired non-parallel side-walls extends with the angle of 20 ° to 50 ° relative to the described one in described non-parallel side-walls.
20. combined cycle systems according to claim 18, is characterized in that, the another one in described paired non-parallel side-walls extends with the angle of 35 ° to 45 ° relative to the described one in described non-parallel side-walls.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14/190902 | 2014-02-26 | ||
| US14/190,902 US20150240667A1 (en) | 2014-02-26 | 2014-02-26 | Exhaust plenum for radial diffuser |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204851442U true CN204851442U (en) | 2015-12-09 |
Family
ID=53782622
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520116685.6U Expired - Fee Related CN204851442U (en) | 2014-02-26 | 2015-02-26 | A exhaust diffuser, turbine and combined cycle system for turbine |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20150240667A1 (en) |
| JP (1) | JP2015161304A (en) |
| CN (1) | CN204851442U (en) |
| CH (1) | CH709269A2 (en) |
| DE (1) | DE102015102560A1 (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10563543B2 (en) | 2016-05-31 | 2020-02-18 | General Electric Company | Exhaust diffuser |
| JP6847673B2 (en) * | 2017-01-17 | 2021-03-24 | 株式会社東芝 | Turbine exhaust chamber |
| US11143058B2 (en) | 2017-12-20 | 2021-10-12 | General Electric Company | Exhaust device and an associated method thereof |
| JP7465650B2 (en) * | 2019-11-28 | 2024-04-11 | 三菱重工業株式会社 | Steam generators and waste heat recovery plants |
| US20230030721A1 (en) * | 2021-07-29 | 2023-02-02 | Solar Turbines Incorporated | Narrow, high performance collector design |
| US12253004B1 (en) * | 2024-02-28 | 2025-03-18 | Ge Infrastructure Technology Llc | Inlet duct system for a heat recovery steam generator |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3631672A (en) * | 1969-08-04 | 1972-01-04 | Gen Electric | Eductor cooled gas turbine casing |
| US3995432A (en) * | 1975-07-28 | 1976-12-07 | United Technologies Corporation | Collector |
| DE3206626A1 (en) * | 1982-02-24 | 1983-09-01 | Kraftwerk Union AG, 4330 Mülheim | EXHAUST CHANNEL FOR GAS TURBINES |
| US4473536A (en) * | 1982-12-27 | 1984-09-25 | General Electric Company | Catalytic pollution control system for gas turbine exhaust |
| US5851105A (en) * | 1995-06-28 | 1998-12-22 | General Electric Company | Tapered strut frame |
| WO2005017333A2 (en) * | 2002-12-10 | 2005-02-24 | Ingersoll-Rand Energy Systems Corporation | Wide-angle concentric diffuser |
| GB2440343B (en) * | 2006-07-25 | 2008-08-13 | Siemens Ag | A gas turbine arrangement |
| US8146341B2 (en) * | 2008-09-22 | 2012-04-03 | General Electric Company | Integrated gas turbine exhaust diffuser and heat recovery steam generation system |
| US8109720B2 (en) * | 2009-03-31 | 2012-02-07 | General Electric Company | Exhaust plenum for a turbine engine |
| US20110236201A1 (en) * | 2010-03-23 | 2011-09-29 | Sumedhkumar Vyankatesh Shende | Method and apparatus for radial exhaust gas turbine |
| ITFI20120221A1 (en) * | 2012-10-22 | 2014-04-23 | Nuovo Pignone Srl | "EXHAUST GAS COLLECTOR AND GAS TURBINE" |
-
2014
- 2014-02-26 US US14/190,902 patent/US20150240667A1/en not_active Abandoned
-
2015
- 2015-02-20 JP JP2015031185A patent/JP2015161304A/en active Pending
- 2015-02-23 DE DE102015102560.4A patent/DE102015102560A1/en not_active Withdrawn
- 2015-02-25 CH CH00255/15A patent/CH709269A2/en not_active Application Discontinuation
- 2015-02-26 CN CN201520116685.6U patent/CN204851442U/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| US20150240667A1 (en) | 2015-08-27 |
| DE102015102560A1 (en) | 2015-08-27 |
| CH709269A2 (en) | 2015-08-28 |
| JP2015161304A (en) | 2015-09-07 |
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