CN101586496A - Systems and methods for cooling heated components in a turbine - Google Patents
Systems and methods for cooling heated components in a turbine Download PDFInfo
- Publication number
- CN101586496A CN101586496A CN200910202877.8A CN200910202877A CN101586496A CN 101586496 A CN101586496 A CN 101586496A CN 200910202877 A CN200910202877 A CN 200910202877A CN 101586496 A CN101586496 A CN 101586496A
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- Prior art keywords
- turbine
- cooling liquid
- heated
- components
- cooling
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
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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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/203—Heat transfer, e.g. cooling by transpiration cooling
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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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/207—Heat transfer, e.g. cooling using a phase changing mass, e.g. heat absorbing by melting or boiling
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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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
Abstract
Systems and methods for cooling heated components in a turbine are provided. According to one embodiment, a system for cooling a turbine is provided that may include at least one liquid source (116) which may include a coolant liquid. The system may also include at least one liquid nozzle (118) in fluid communication with the liquid source or sources (116) and operable to deliver the coolant liquid in an atomized form adjacent to at least one heated turbine component positioned in a hot gas path (216) of the turbine. Upon delivering the atomized coolant liquid adjacent to the heated turbine component or components, at least a portion of the coolant liquid substantially changes phase to a gas.
Description
Technical field
The present invention relates generally to turbo machine, and more specifically relates to the system and method for the heated components that is used for cooling turbomachine.
Background technique
In turbo machine, be positioned in the hot gas path and stand to be in hot gas under the temperature that is higher than one or more member fusing points in these members such as some member of nozzle, turbine, blade or guard shield such as gas turbine.In some contemporary gas turbine, the temperature of hot gas can be up to 1600 ℃.Therefore, in many cases, the member that is positioned in the hot gas path is cooled at the turbo machine run duration.In exemplary conventional system, the air that oozes out from the compressor of gas turbine is used to cool off these members.Yet this air has consumed the firing chamber that a large amount of merits or energy are walked around gas turbine.The air member that enters into turbine bucket for example or nozzle cools off them then, so they can survive in the hot gas path.Afterwards, air is released and gets back in the hot gas path.Because air gets around the firing chamber, its any fuel and do not obtain extra momentum of not burning.Therefore, this air can not be done useful work in other turbine stage.As a result, the efficient of gas turbine reduces.
In other exemplary conventional system, heated components can be by steam rather than the air cooling of taking out from compressor.Steam can extract and send into pipeline then the turbine components that is heated that is positioned in the hot gas path from steam turbine.This steam have usually higher heat-transfer coefficient and therefore the turbine components in the self-heating gas path absorb more heats.Therefore, steam cooling can provide the improvement that is better than air cooling solution solution.Steam can be taken from gas path and is incorporated into steam turbine once more then.Therefore, some heat energy in the heat energy that obtains of steam self-heating gas path can recover in steam turbine to produce extra useful work.Therefore, under exemplary cases, the efficient of the gas turbine of steam cooling can be greater than air cooled gas turbine.
But the system of conventional steam cooling can be very complicated.For example, steam is taken from fixing tube and must be led to the blade of rotation.Steam supply and recovery system must keep excellent sealing, because steam exists with very high pressure and otherwise will cause leakage in vapour system.In addition, because steam is advanced and got back to steam turbine, vapour system also should be sealed to keep purity.
Therefore, existence is for the needs of the system and method for the heated components that is used for cooling turbomachine.
Summary of the invention
Embodiments of the invention can solve some needs in the needs mentioned above or all need.Embodiments of the invention are by and large at the system and method for the turbine components that is heated that is used for cooling turbine engines.
According to one exemplary embodiment of the present invention, provide a kind of system of heated components of the hot gas path that is used for cooling turbomachine.This example system can comprise at least one fluid supply, and this at least one fluid supply comprises cooling liquid.This system also can comprise at least one fluid injector, and this at least one fluid injector is communicated with one or more fluid supply fluids and can operates with the cooling liquid that will be atomised form and is transported near at least one turbine components that is heated in the hot gas path that is positioned turbo machine.According to this exemplary embodiment, after atomized liquid coolant being transported near this be heated turbine components or these turbine components that is heated, at least a portion of cooling liquid becomes gas basically mutually.
According to another exemplary embodiment of the present invention, provide a kind of method of heated components of the hot gas path that is used for cooling turbomachine.This illustrative methods can comprise provides at least one fluid supply, this at least one fluid supply comprises cooling liquid and is communicated with at least one fluid injector fluid that wherein this fluid injector or these fluid injectors are positioned near at least one turbine components that is heated in the hot gas path that is arranged in turbo machine.This method also can comprise making from the atomizing of the cooling liquid of this fluid supply or these fluid supplies and with atomized liquid coolant and is transported near this be heated turbine components or these turbine components that is heated.According to this exemplary embodiment, after atomized liquid coolant being transported near this be heated turbine components or these turbine components that is heated, at least a portion of this cooling liquid becomes gas basically mutually.
A kind of method of operating turbine is provided in accordance with a further exemplary embodiment of the present invention.This illustrative methods can comprise the startup turbo machine, increases turbine speed moving under predetermined load, and makes the cooling liquid atomizing.This method also can be included in and increase turbine speed with after the operation under predetermined load, atomized liquid coolant is transported near at least one turbine components that is heated in the hot gas path that is positioned turbo machine, wherein after carrying atomized liquid coolant, at least a portion of cooling liquid becomes gas basically mutually.This method also can comprise and reduce turbine speed being lower than predetermined load operation, and reduce turbine speed be lower than predetermined load after the self-heating gas path purge excess liquid.
In conjunction with the accompanying drawings, by following description, other embodiments of the invention and aspect will become apparent.
Description of drawings
Therefore briefly described embodiments of the invention, now referring to accompanying drawing, accompanying drawing is not proportionally drawn, and in the accompanying drawings:
Fig. 1 is the functional-block diagram of example system of turbine components of being heated that is used to cool off according to an embodiment of the invention;
Fig. 2 is a view according to an embodiment of the invention, that represent the turbine bucket of the exemplary turbine components that is heated;
Fig. 3 be according to an embodiment of the invention, the be heated flow chart of illustrative methods of turbine components of cooling has been described; And
Fig. 4 is a flow chart according to an embodiment of the invention, that the illustrative methods of operating turbine has been described.
List of parts
The 102-turbine bucket
The 104-turbomachine injection nozzle
The 106-compressor
108-inner space (in the turbomachine injection nozzle)
The 110-guide
The 112-root
The 114-pipeline
The 116-fluid supply
The 118-fluid injector
120-inner space (in the turbine bucket)
The 122-pipe-line system
124-purges the unit
The 202-turbine bucket
The 204-hole
The 206-bucket platform
The 208-inner space
The 210-mixture
The 212-root
The 214-gaseous mixture
216-hot gas path
218A-first side
218B-second side
The 300-method
The 302-segment
The 304-segment
The 306-segment
The 400-method
The 402-segment
The 404-segment
The 406-segment
The 408-segment
The 410-segment
The 412-segment
Embodiment
Now more fully describe exemplary embodiment of the present invention hereinafter, wherein show some but not all embodiments referring to accompanying drawing.In fact, the present invention can implement and should not be construed as to be limited to the embodiment that this paper is set forth with many different forms; Make present disclosure will satisfy suitable legal requiremnt and provide these embodiments.Similar reference character refers to similar element all the time.
The speed that starts turbo machine and increase turbo machine causes the burning in the turbine combustion chamber.During burning, the temperature of the hot gas that is produced can be far above the fusing point of the various turbine components that are arranged in the hot gas path.Therefore, for the turbine components that is heated in the hot gas path of cooling turbomachine, cooling liquid can be atomized and be transported to is heated near turbine components place or its.Since cooling liquid (such as: water for example) it absorbs more multipotency during liquid phase-change is gas, with only comparing in steam cooling or the only air cooled turbo machine, will more effectively cool off these members near atomized liquid coolant is supplied to be heated turbine components or its.In addition, cooling liquid is mixed into the cooling mechanism that has served as air in the air extraly, the air mixture is transported to the turbine components that is heated afterwards.
Fig. 1 is the functional-block diagram of system 100 of turbine components of being heated that is used to cool off according to an embodiment of the invention.In the exemplary embodiment, the turbine components that is heated can be turbine bucket 102, such as first order turbine bucket 102.But, will be appreciated that other turbine components also can be cooled off by system and method as herein described such as turbine wheel, turbomachine injection nozzle, turbomachine shroud or its any combination.In gas turbine, hot gas produces in the firing chamber, forms to be in about 1000 ℃ of hot gas temperatures to about 1600 ℃ of scopes.After leaving the firing chamber, hot gas can pass the first order turbomachine injection nozzle 104 of gas turbine at first, and it is communicated with the turbine components that is heated such as turbine bucket 102.Will be appreciated that, for purposes of illustration, in Fig. 1, only show a first order turbomachine injection nozzle 104, and other exemplary turbo machine can comprise a plurality of nozzles, blade etc.Therefore, turbomachine injection nozzle 104 and turbine bucket 102 or other turbine components are exposed to the hot gas that is under the very high temperature.Therefore, these turbine components may stand the temperature far above the construction material melting point.
For cooling turbomachine blade 102, carry air from the compressor 106 of gas turbine.Air can at first pass the inner space 108 of turbomachine injection nozzle 104.After leaving turbomachine injection nozzle 104, air passes guide 110, and guide 110 further releases air near the root 112 of turbine bucket 102.Root 112 is the radially penetralia part of turbine bucket 102.Root 112 has attachment feature (as shown in Figure 2) usually, this attachment feature is shaped such that turbine bucket 102 is attachable on the turbine wheel, in addition, guide 110 discharging air make air be directed to and guide to enter turbine bucket 102 through root 112.Fig. 1 also shows pipeline 114, and this pipeline 114 makes cooling liquid pass turbomachine injection nozzle 104.In the exemplary embodiment, cooling liquid is from fluid supply 116.In an exemplary embodiment, cooling liquid can be essentially water, but should be appreciated that in other embodiments, and fluid supply 116 can be carried the cooling liquid except water.After passing pipeline 114, cooling liquid is passed fluid injector 118.Fluid injector 118 is transported to cooling liquid near be heated turbine components or its.For example, as shown in Figure 1, fluid injector can be transported to cooling liquid near the root 112 of turbine bucket 102.Should be appreciated that in other exemplary embodiment fluid injector 118 can be transported to cooling liquid other turbine components, for example, such as turbine wheel, turbomachine injection nozzle, turbomachine shroud or its any combination.
In various exemplary embodiments, fluid injector 118 can be positioned at turbine wheel inside or turbomachine shroud outside.The determining positions of fluid injector 118 is being heated near turbine components 102 places or discharge the position of cooling liquid it.In various exemplary embodiments, fluid injector 118 can be ejector type, Venturi type etc.
If the cooling liquid of carrying from fluid injector 118 directly contacts the turbine components that is heated, such as turbine bucket 102, cooling liquid can cause the significantly reduction of temperature at the regional area that cooling liquid contacted.This may cause high-temperature gradient in construction material, thereby may cause high stress gradients in the heated components material, makes to produce cracking at the some place that cooling liquid contacted.For fear of this damage to the turbine components that is heated, in one exemplary embodiment, cooling liquid is discharged in the air with atomised form and at least a portion of this cooling liquid is being a gas from liquid phase-change with air mixing and when being exposed to high temperature.Avoided certain the some place on heated components directly to contact to the phase transformation of gas by the cooling liquid of liquid form.
In some cases, the cooling liquid of leaving fluid supply 116 can be in the pressure lower than the pressure of the air that leaves compressor 106.In this case, cooling liquid can not be discharged in the air with atomised form and therefore may not can evenly distributes by air dielectric.Therefore, cooling liquid can be in it be released to air dielectric before supercharging.Therefore, in one exemplary embodiment, can use suction booster to come, make cooling liquid to leave with atomised form basically and arrive air dielectric and near be heated turbine components or its, evenly distribute by air dielectric to the cooling liquid supercharging.For example, cooling liquid can be supercharged to about 2.8 * 10
6N/m
2(400psi) or higher pressure.
Cooling liquid and air mixing also can be of value to cool off the turbine components that is heated, because compare with the gaseous form of cooling liquid and cooling liquid and the specific heat of air, the latent heat of vaporization of cooling liquid is very high.For example, if cooling liquid is a water, the specific heat of the latent heat of vaporization of water, specific heat of water and steam is respectively about 2.26 * 10 so
2J/kg, 4.184J/kg-℃ and 2J/kg-℃.Therefore, in the turbo machine of steam cooling, for every kilogram of steam, about 1 ℃ increase can absorb 2 joules heat, and in water-cooled turbo machine, for every kilogram water, about 1 ℃ increase can absorb 4.184 joules heat.But water is transformed in the system (such as system 100) of steam therein, and every kilogram water can absorb 2.26 * 10 when being transformed into steam
2The heat of joule.In addition, this betides big under the steady temperature of water boiling point.Water is with 2.26 * 10
2J/kg-℃ of heat absorption is transformed into steam up to all basically water.This provides very strong hot scoopability for cooling liquid.In addition, cooling liquid is served as the cooling mechanism of air to the transformation of gas subsequently to airborne mixing and its, and air and gaseous mixture are transported near the turbine components that is heated (such as turbine bucket 102) afterwards.In the exemplary embodiment of at least one turbine bucket 102 of cooling, in case cooling liquid is phase-changed into gaseous medium, gas and air mixture just can enter the inner space 120 of turbine bucket 102 through root 112.
In one exemplary embodiment, can provide pipe-line system 122 alternatively, fluid supply 116 be connected to fluid injector 118 and guarantee the correct conveying of cooling liquid from fluid supply 116 and fluid injector 118.In addition, pipe-line system 122 can be in that wherein temperature is high in fact to cooling liquid is phase-changed in the environment of gaseous form.This makes cooling liquid lose some hot scoopability, and it is kept better to be used to the turbine components 102 that is heated.Phase transformation for fear of cooling liquid to gas, pipe-line system 122 also can be isolated with its surrounding environment heat.In addition, pipe-line system 122 can be corroded owing to the corrosive action of cooling liquid.Therefore, in one exemplary embodiment, pipe-line system 122 can be provided with corrosion resistant coating.
In some cases, at system's 100 run durations, the speed that reduces gas turbine is no longer moved gas turbine with predetermined load.Gas turbine can need the self-heating gas path to purge the excessive cooling liquid that is not transformed into gas phase.Therefore, in one exemplary embodiment, in gas turbine, provide purging unit 124 alternatively.Yet exemplary gas turbine engine can generally include the discharge system that discharges unburned fuel in gas turbine.Therefore, in one exemplary embodiment, fuel is discharged system can be along with extending in order to the purging unit 124 that purges any excessive cooling liquid residual in the path.
Fig. 2 is the view of exemplary turbine bucket 202 according to an embodiment of the invention, and it has represented the example of at least one turbine components that is heated in the hot gas path 216 of turbo machine.Turbine bucket 202 has the first side 218A and the second side 218B, and the first side 218A and the second side 218B are the relative wall of turbine bucket 202 and form inner space 208 in the turbine bucket 202.Turbine bucket 202 can comprise a plurality of holes 204 and bucket platform 206.Hole 204 extends through the first side 218A and the second side 218B of turbine bucket 202.Cooling liquid and AIR MIXTURES 210 can be transported near the root 212 of turbine bucket 202 or its, and at this point, mixture 210 enters turbine bucket 202 by bucket platform 206.Mixture 210 further passes inner space 208.Because air has been in about 750 ℃ high temperature and cooling liquid evenly distributes in air with atomised form, cooling liquid is from the air heat absorption and become basic gas phase.Because the cooling liquid of mixture 210 is transformed into gas, has formed gaseous mixture 214.Then, gaseous mixture 214 can leave hole 204 at least in part and enters in the hot gas path 216.
Should be appreciated that only provides turbine bucket 202 for purpose of explanation, and other turbine components that is heated in hot gas path 216 can cool off to be similar to mode described herein.In various exemplary embodiment, the turbine components that is heated can be (but being not limited to) turbomachine injection nozzle, turbine bucket, turbine wheel, turbomachine shroud or its combination.
Fig. 3 has illustrated the illustrative methods that can operate one embodiment of the present of invention by it.Flow chart 300 is provided, and it has illustrated illustrative methods according to an embodiment of the invention, as to be used for the turbine components that is heated in cooling turbomachine hot gas path.
This illustrative methods starts from segment 302.At segment 302, provide at least one fluid supply with near one or more be heated turbine components or its or nearby with cooling fluid supply.In various exemplary embodiment, the turbine components that is heated can be (but being not limited to) turbomachine injection nozzle, turbine bucket, turbine wheel, turbomachine shroud or its combination.In one exemplary embodiment, cooling liquid can be water, but also can supply other freezing mixture.Fluid supply and vicinity or be heated turbine components and at least one fluid injector fluid of locating is communicated with near these be heated turbine components or these.Therefore, these one or more fluid injectors can be operated, with will be from the cooling fluid supply of fluid supply near one or more be heated turbine components place or its.This fluid injector or these fluid injectors can be ejector type, Venturi type etc.
In an example, the pipe-line system to fluid injector can provide fluid therebetween to be communicated with from fluid supply.In the exemplary embodiment, pipe-line system can stand quite high temperature, and such as at the turbo machine run duration, it can cause cooling liquid to carry out phase transformation at least in part in pipe-line system.Therefore, in one exemplary embodiment, this method can comprise that also to make pipe-line system heat insulation to avoid heat to be delivered to cooling liquid in it from the surrounding environment of pipe-line system.
After the segment 302 is segment 304, and wherein the cooling liquid from fluid supply is atomized basically.Fluid injector can be exercisable, so that cooling liquid atomizes basically.In addition, in other exemplary embodiment, turbo machine can comprise suction booster, with the atomizing that is used to make the cooling liquid supercharging that receives from fluid supply and also is used for auxiliary cooling liquid.
Be segment 306 after segment 304, wherein fluid injector is transported to atomized liquid coolant near this be heated turbine components or these turbine components that is heated or air nearby.Basically equably atomized liquid coolant is transported to the air of carrying from compressor and allows cooling liquid and air mixing, become gas when being exposed to higher temperature in the hot gas path basically mutually with box lunch.
In one exemplary embodiment, be lower than predetermined load if the speed of turbo machine is reduced to, this method can comprise provides the purging unit to come to remove cooling liquid from the hot gas path.In an example, self-heating gas path purging cooling liquid can be carried out before the startup next time of turbo machine.In another example, turbo machine post-purge cooling liquid can closed.
Fig. 4 has illustrated another illustrative methods that can operate one embodiment of the present of invention by it.Flow chart 400 is provided, and it has illustrated the illustrative methods that is used for operating turbine according to an embodiment of the invention.
This illustrative methods starts from segment 402.At segment 402, start turbo machine.Be segment 404 after segment 402, wherein the speed of turbo machine increases with operating turbine under predetermined load.The speed that starts gas turbine and increase gas turbine causes the combustion process in the gas-turbine combustion chamber.In the exemplary embodiment, the temperature of the hot gas that is produced can be far above the fusing point of the various turbine components that are arranged in the hot gas path.
After the segment 404 be segment 406, and wherein the cooling liquid from the fluid supply reception is atomized, and it can be used for the one or more turbine components that are heated in the hot gas path of cooling turbomachine.In an illustrative methods, the fluid injector that is in fluid connection with fluid supply is atomized liquid coolant basically.In the exemplary embodiment, cooling liquid can be water, but also can supply other freezing mixture.
Be segment 408 after segment 406, wherein atomized liquid coolant is transported near this turbine components or these turbine components or nearby.In this illustrative methods, owing to cooling liquid is carried with atomised form, and be transported to the air that has the temperature that is higher than the cooling liquid boiling point in the hot gas path, at least a portion of this cooling liquid experiences phase transformation and is transformed into gas phase.In the exemplary embodiment, this be heated turbine components or these turbine components that is heated can comprise turbine bucket, turbomachine injection nozzle, turbine wheel, turbomachine shroud etc.
After the segment 408 is segment 410, and wherein the speed of turbo machine reduces to make turbo machine to be lower than the predetermined load operation, such as slowing down or the down periods.Feasible is, when reducing to load or temporarily stopping the turbo machine operation, some in this cooling liquid can not experience phase transformation.Remaining liq in the turbo machine can cause the corrosion of turbine components and finally can be owing to heavily stressed coefficient causes occurring in the turbine components crack.Therefore, after segment 410 segment 412, wherein the self-heating gas path purges any excessive this cooling liquid.In an example, self-heating gas path purging cooling liquid can be carried out before turbo machine startup next time.In another example, closing turbo machine post-purge cooling liquid.
In various turbo machines, turbine efficiency can be subjected to air is incorporated into influence in the hot gas path, and this is because during compressor stage, air has stood a large amount of merits.Cooling liquid is incorporated into (all situations as indicated above) improved cooling effectiveness in the air, and therefore helps to reduce to be used to cool off the air quantity of turbine components of being heated.
Benefit from the instruction of in the description of preamble and the accompanying drawing that is associated, being showed, can associate these many modifications of describing the relevant exemplary description that this paper stated and other embodiments.Therefore, should be appreciated that the present invention can implement and should not be limited to exemplary embodiment mentioned above with many forms.Therefore, should be appreciated that the present invention should not be limited to disclosed specific embodiment and modification and other embodiment intention and be included in the category of appended claims.Although adopted particular term in this article, they only use and are not limited to purpose with general and descriptive sense.
Claims (10)
1. the system (100) of the heated components in a hot gas path (216) that is used for cooling turbomachine (102), it comprises:
At least one fluid supply (116) that comprises cooling liquid; And
At least one fluid injector (118), it is communicated with described at least one fluid supply (116) fluid and can operates with the described cooling liquid that will be atomised form and is transported near at least one turbine components that is heated in the hot gas path (216) that is arranged in described turbo machine;
Wherein, after described atomized liquid coolant being transported near described at least one turbine components that is heated, at least a portion of described cooling liquid becomes gas basically mutually.
2. system according to claim 1 is characterized in that, described system also comprises at least one pump that is used to make from the cooling liquid supercharging of described at least one fluid supply (116).
3. system according to claim 1 is characterized in that, described system also comprises the pipe-line system (122) that connects described at least one fluid supply (116) and described at least one fluid injector (118).
4. system according to claim 3 is characterized in that, described pipe-line system (122) comprises heat insulator.
5. system according to claim 1 is characterized in that described cooling liquid comprises water.
6. system according to claim 1 is characterized in that, described at least one turbine components that is heated comprises at least a in turbine bucket (102), turbine wheel, turbomachine injection nozzle (104) or the turbomachine shroud.
7. system according to claim 1, it is characterized in that, described at least one turbine components that is heated comprises turbine bucket (102), described turbine bucket (102) comprises first side (218A) and second side (218B), described first side (218A) and second side (218B) form inner space (120) therein and comprise at least one a plurality of holes (204) of running through in described first side (218A) or described second side (218B), and wherein, after described atomized liquid coolant being transported near the described turbine bucket (202), at least a portion of described gas is passed described inner space (120) and is left described inner space (120) and pass at least a portion in described a plurality of hole (204) and arrive described hot gas path (216).
8. system according to claim 1 is characterized in that, described system comprises that also purging unit (124) is to purge excessive described cooling liquid from described hot gas path (216).
9. the method for the heated components in a hot gas path (216) that is used for cooling turbomachine, it comprises:
Provide (302) to comprise at least one fluid supply (116) cooling liquid, that be communicated with at least one fluid injector (118) fluid, wherein said at least one fluid injector (118) is positioned near at least one turbine components that is heated in the hot gas path (216) that is arranged in described turbo machine;
Make cooling liquid atomizing (304) from described at least one fluid supply (116); And
Carry (306) near described at least one turbine components that is heated described atomized liquid coolant;
Wherein, after described atomized liquid coolant being transported near described at least one turbine components that is heated, at least a portion of described cooling liquid becomes gas basically mutually.
10. method according to claim 9 is characterized in that, described method also comprises by at least one pump makes cooling liquid supercharging from described at least one fluid supply (116).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/123093 | 2008-05-19 | ||
| US12/123,093 US20090285677A1 (en) | 2008-05-19 | 2008-05-19 | Systems And Methods For Cooling Heated Components In A Turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101586496A true CN101586496A (en) | 2009-11-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910202877.8A Pending CN101586496A (en) | 2008-05-19 | 2009-05-19 | Systems and methods for cooling heated components in a turbine |
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|---|---|
| US (1) | US20090285677A1 (en) |
| JP (1) | JP2009281383A (en) |
| CN (1) | CN101586496A (en) |
| DE (1) | DE102009025803A1 (en) |
| FR (1) | FR2931193A1 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105386793A (en) * | 2014-11-12 | 2016-03-09 | 熵零股份有限公司 | Non-gas fluid backlash thermal dynamic conversion method and engine adopting method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8632297B2 (en) * | 2010-09-29 | 2014-01-21 | General Electric Company | Turbine airfoil and method for cooling a turbine airfoil |
| US20140123666A1 (en) * | 2012-11-07 | 2014-05-08 | General Electric Company | System to Improve Gas Turbine Output and Hot Gas Path Component Life Utilizing Humid Air for Nozzle Over Cooling |
| US20170107902A1 (en) * | 2015-10-19 | 2017-04-20 | General Electric Company | Systems and Methods for Wheel Space Temperature Management |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3446481A (en) * | 1967-03-24 | 1969-05-27 | Gen Electric | Liquid cooled turbine rotor |
| US3446482A (en) * | 1967-03-24 | 1969-05-27 | Gen Electric | Liquid cooled turbine rotor |
| JPS5572604A (en) * | 1978-11-29 | 1980-05-31 | Toshiba Corp | Cooling process of gas turbine rotor blade |
| JPS55104506A (en) * | 1979-02-02 | 1980-08-11 | Hitachi Ltd | Gas-turbine blade |
| JPS6056883B2 (en) * | 1979-02-28 | 1985-12-12 | 株式会社東芝 | gas turbine moving blades |
| US4283822A (en) * | 1979-12-26 | 1981-08-18 | General Electric Company | Method of fabricating composite nozzles for water cooled gas turbines |
| JPH0255837A (en) * | 1988-08-19 | 1990-02-26 | Jinichi Nishiwaki | Cooling method for gas turbine blade |
| US4948335A (en) * | 1988-12-30 | 1990-08-14 | Westinghouse Electric Corp. | Turbine moisture removal system |
| JPH03130503A (en) * | 1989-10-13 | 1991-06-04 | Jinichi Nishiwaki | Water-cooling method for high temperature part of gas turbine |
| JPH03189333A (en) * | 1989-12-18 | 1991-08-19 | Jinichi Nishiwaki | Water cooling type gas turbine unit |
| JPH1122406A (en) * | 1997-07-08 | 1999-01-26 | Mitsubishi Heavy Ind Ltd | Water cooled turbine blade |
| JP2000282810A (en) * | 1999-03-30 | 2000-10-10 | Toshiba Corp | Turbine plant |
| US7607307B2 (en) * | 2006-01-06 | 2009-10-27 | General Electric Company | Methods and apparatus for controlling cooling air temperature in gas turbine engines |
-
2008
- 2008-05-19 US US12/123,093 patent/US20090285677A1/en not_active Abandoned
-
2009
- 2009-05-11 FR FR0953105A patent/FR2931193A1/en not_active Withdrawn
- 2009-05-14 DE DE102009025803A patent/DE102009025803A1/en not_active Withdrawn
- 2009-05-14 JP JP2009117113A patent/JP2009281383A/en active Pending
- 2009-05-19 CN CN200910202877.8A patent/CN101586496A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105386793A (en) * | 2014-11-12 | 2016-03-09 | 熵零股份有限公司 | Non-gas fluid backlash thermal dynamic conversion method and engine adopting method |
| CN105386793B (en) * | 2014-11-12 | 2017-03-01 | 熵零股份有限公司 | A kind of non-air-flow body recoil heat moves conversion method and its electromotor |
Also Published As
| Publication number | Publication date |
|---|---|
| DE102009025803A1 (en) | 2009-11-26 |
| FR2931193A1 (en) | 2009-11-20 |
| US20090285677A1 (en) | 2009-11-19 |
| JP2009281383A (en) | 2009-12-03 |
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