CN102691532A - System for regulating a cooling fluid within a turbomachine - Google Patents
System for regulating a cooling fluid within a turbomachine Download PDFInfo
- Publication number
- CN102691532A CN102691532A CN2012100896833A CN201210089683A CN102691532A CN 102691532 A CN102691532 A CN 102691532A CN 2012100896833 A CN2012100896833 A CN 2012100896833A CN 201210089683 A CN201210089683 A CN 201210089683A CN 102691532 A CN102691532 A CN 102691532A
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- China
- Prior art keywords
- cooling fluid
- collector
- fixed component
- cooling
- adjusting plug
- 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.)
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Classifications
-
- 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
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
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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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/127—Vortex generators, turbulators, or the like, for mixing
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Embodiments of the present invention provide a system for regulating a cooling fluid within a turbomachine. The system may include a plurality of bypass chambers, wherein each of the plurality of bypass chambers allows for the cooling fluid to pass from the compressor section to a wheelspace area. The system includes a plurality of angular passages that aid in the mixing of a cooling fluid with a working fluid in the wheelspace area.
Description
This is the part continuation application; Require to submit on May 1st, 2007, name is called the preference of U.S. Patent application 11/799,162 [GE file number 208397-1] of the co-assigned of " system (System For Regulating A Cooling Fluid Within A Turbomachine) that is used to regulate the cooling fluid in the turbine machine "; Above-mentioned application way of reference is in full incorporated in this specification.
Technical field
Present invention relates in general to the cooling system on a kind of turbine machine; And relate more particularly to the system of the cooling fluid in a kind of zone, wheel space that is used to regulate the turbine machine.
Background technique
In some the turbine machines such as combustion gas turbine, typically being shifted from burning by the part of air of compressor compresses is the chamber in the various fixed components of cooling and rotary component or the purge combustion gas turbine.The air-flow that shifts (below be called " cooling fluid ") consumes the considerable amount by the total air flow of compressor compresses.The cooling fluid that shifts does not burn, and has reduced the performance of combustion gas turbine.Regulate and control the performance that cooling fluid can increase turbo machine greatly.
Typically, cooling fluid from compressor extract, bypass is through combustion system and flow and pass through cooling circuit.Cooling circuit typically is positioned at various turbine components and near various the wheel zone, space that comprises rotor compressor-turbo machine joint (below be called " cooperation joint ").Cooling circuit typically is integrally formed with sealing system.The gap possibly be present between sealing system parts and the gas turbine machine rotor relatively closely.
Sealing system can comprise the labyrinth seal spare between rotary component and fixed component.Maybe through the typical case that the labyrinth seal gap takes place leak be generally used for cooling off or purge in the zone in the downstream of Sealing.For example, high pressure packing seal system (HPPS) can comprise Qu Lu and brush seal arrangement, wherein comprises the components downstream in zone, wheel space through the leakage flow cooling of HPPS.The validity of cooling circuit depends on the performance of HPPS to a great extent.
The configuration of cooling circuit determines whether that enough cooling fluids flow to aforementioned turbine components.Cooling circuit can comprise the chamber that chilled fluid flow is directed to the particular wheel area of space.
Possibly there are several problems in known sealing system at present.Wearing and tearing may enlarge the sealing system gap.Sealing maybe wearing and tearing during " tripping operation (trip) " (emergency shutdown of turbine machine).And Sealing is along with the time is worn and torn by the gas turbine machine operation gradually.Wearing and tearing can allow excessive cooling fluid to flow to the downstream of Sealing, thereby can reduce the total efficiency of combustion gas turbine.The unpredictability that the sealing system wearing and tearing take place does not allow the circulation supercooling loop of confirming of cooling fluid.In addition, known sealing system uncompensation sealing system is worn and torn.So known sealing system does not provide a kind of mode to regulate and flow to the amount of taking turns the regional cooling fluid in space.
For above-mentioned reasons, i.e. expectation has a kind of system, and said system allows to regulate the cooling fluid in the zone, wheel space that flows into combustion gas turbine.Said system should cool off fully, improves the gas turbine engine efficiency simultaneously.Said system also should provide the stream of confirming through cooling circuit.
Summary of the invention
Outlined on scope some embodiment suitable with original invention required for protection.These embodiments are not intended to limit scope of invention required for protection, but these embodiments only aim to provide the simplified summary of possibility form of the present invention.In fact, the present invention can be contained the various forms that can be similar to or be different from embodiment described below.
In an embodiment of the present invention, a kind of system that is used to regulate cooling fluid is provided, said system comprises: turbo machine, and said turbo machine comprises: compressor section, said compressor section comprises the inner core cover; The compressor air-discharging cover; And bypass chamber (bypass chambers), said bypass chamber allows cooling fluid to flow to said compressor air-discharging cover from said inner core cover; Turbine section, said turbine section comprises rotary component; Fixed component; With wheel space zone, wherein each is taken turns the zone, space and comprises rotary component and fixed component, and each bypass chamber allows cooling fluid to flow to the said zone, space of taking turns from said compressor section; And nozzle cooling circuit; Said nozzle cooling circuit comprises main passage and the collector (header) that all roughly is positioned at each fixed component; The first end of wherein said main passage receives cooling fluid; And the second end of said main passage is connected to said collector, makes cooling fluid flow to said collector from said main passage; Wherein said collector comprises upstream orifice and downstream orifice, and said aperture allows cooling fluid to discharge from said collector.
The downstream in each aperture is connected to adjusting plug, and said adjusting plug comprises said cooling fluid is directed to the opening outside the said nozzle cooling circuit; Said adjusting plug is confirmed the mechanical property of said cooling fluid.Said fixed component comprises a plurality of nozzle cooling circuits; Each of said a plurality of nozzle cooling circuits comprises: specify the main passage and specify collector.Each aperture is with the said collector of certain angle deviating, and said angle is with the mode that helps to mix with the working fluid said cooling fluid of prewhirling.Said angle the flowing of directed said cooling fluid on the direction that is similar to said working fluid and said rotary component.Said collector is the form in the hole that extends through said fixed component; Each end of said collector is by cap closure.
In alternative of the present invention, a kind of system that is used to regulate cooling fluid is provided, said system comprises: combustion gas turbine, said combustion gas turbine comprises: combustion system, said combustion system generates working fluid; Compressor section, said compressor section comprises the inner core cover; The compressor air-discharging cover; And bypass chamber (bypass chambers); Wherein cooling fluid flows to said compressor air-discharging cover through said inner core cover; Turbine section, said turbine section comprises rotation blade; Barrier film (diaphragms); Nozzle; With wheel space zone, wherein each is taken turns the zone, space and comprises a series of rotation blades, barrier film and nozzle, and each bypass chamber allows cooling fluid to flow to the said zone, space of taking turns from said compressor air-discharging cover; And nozzle cooling circuit; Said nozzle cooling circuit roughly is positioned at each fixed component; Wherein said nozzle cooling circuit comprises main passage and collector; The second end that the first end of wherein said main passage receives cooling fluid and said main passage is connected to said collector, and cooling fluid flows to said collector from said main passage; Wherein said collector comprises upstream orifice and downstream orifice, and said aperture allows cooling fluid to mix from said collector discharge and with working fluid.
Said system also comprises the adjusting plug in the downstream that are positioned at said collector, and said adjusting plug allows said cooling fluid to leave said nozzle cooling circuit.Each aperture and special-purpose adjusting plug are integrally formed; Said special-purpose adjusting plug comprises inside diameter-variable, and said cooling fluid is discharged said collector through said inside diameter-variable; And said special-purpose adjusting plug is confirmed at least a in the following character of said cooling fluid: speed, flow or pressure.Said fixed component comprises a plurality of nozzle cooling circuits.Each of said a plurality of nozzle cooling circuits comprises: specify the main passage and specify collector.Said special-purpose adjusting plug guides said cooling fluid towards the outer surface of said fixed component.Each aperture is with the said collector of certain angle deviating, and said angle is with the mode that helps to mix with the working fluid said cooling fluid of prewhirling; Said angle the flowing of directed said cooling fluid on the direction that is similar to said working fluid and said rotary component.The form of the rounded opening of said collector, said circular open extend through said fixed component on the direction in the upper reaches to downstream, and each end of said collector is by cap closure.
Description of drawings
When describing in detail below with reference to advantages, of the present invention these with the understanding that can improve of further feature, aspect and advantage, similar in the accompanying drawings reference character is represented similar elements/components all the time.
Fig. 1 is the schematic cross section of combustion gas turbine, shows embodiments of the invention and operates residing environment.
Fig. 2 is the guide wire of alternative shape of the combustion gas turbine shown in Fig. 1.
Fig. 3 is the schematic representation with the fixed component among Fig. 2 of known nozzle cooling circuit.
Fig. 4 is the schematic representation of the fixed component of Fig. 2 of having the nozzle cooling circuit according to an embodiment of the invention.
Fig. 5 is the decomposing schematic representation according to fixed component among Fig. 4 of the embodiment of the invention.
Fig. 6 is the schematic representation of the fixed component that is in use among the Fig. 4 according to the embodiment of the invention.
Embodiment
The one or more specific embodiments of various details.For these embodiments' succinct description is provided, all characteristics of actual implementation possibly described in specification not.Be to be understood that in the development of any actual implementation like this; As such in engineering or the design planning; Made the system relevant and/or business-related constraints of the specific decision of many implementations to obtain specific objective, for example to meet between implementation, to differ from one another.And it possibly be complicated and consuming time should understanding such trial, but the routine work that for utilizing those skilled in the art of the present invention, remains design, assembling and make.
Concrete exemplary embodiment is disclosed in this manual.Yet concrete structure disclosed herein and function detail only are representational, and purpose is to describe exemplary embodiment.Yet embodiments of the invention embody with many alterative version, and are not appreciated that the embodiment who only is confined among this paper to be set forth.
Therefore, although exemplary embodiment can have various modifications and alterative version, their embodiment illustrates in the drawings as an example and will be described in detail in this manual.Yet be to be understood that not to be to want exemplary embodiment is restricted to particular forms disclosed, but on the contrary, exemplary embodiment will contain all modifications, equivalent and the substitute that belongs in the scope of the present invention.
Term as used in this specification only is in order to describe specific embodiment rather than to be intended to limit exemplary embodiment.When using in this manual, singulative " " and " said one " also are intended to comprise plural form, only if context is clearly pointed out in addition.When using in this manual; Term " comprises " and/or " comprising " expression exists said characteristic, integer, step, operation, element and/or parts, but does not get rid of existence or increase one or more further features, integer, step, operation, element, parts and/or their group.
Although first, second grade of term can be used to describe various elements in this manual, these elements should be by these term restrictions.These terms only are used for element is distinguished from each other out.For example, first element can be called as second element, and similarly, second element can be called as first element, and this does not break away from the scope of exemplary embodiment.When using in this manual, term " and/or " comprise one or more relevant Listed Items arbitrarily and all combinations.
Some term only is reader and using for ease in this manual, and should not be regarded as restriction scope of the present invention.For example, such as " on ", the word of D score, " left side ", " right side ", " just ", " back of the body ", " top ", " end ", " level ", " vertically ", " upper reaches ", " downstream ", " preceding ", " back " etc. only describes the configuration shown in the figure.In fact, an element of embodiments of the invention or a plurality of element can go up directed in any direction and therefore term be appreciated that and comprise such variation, only if point out in addition.
The present invention can be applied to various air intake type turbine machines.This can change formula turbo machine (aero-derivative) etc. including, but not limited to heavy duty gas turbines, boat.Although following argumentation relates to the combustion gas turbine shown in Fig. 1, embodiments of the invention can be applied to have the combustion gas turbine of different configurations.For example but non-exclusively, the present invention can be applied to have the combustion gas turbine that is different from the parts shown in Fig. 1 or has optional feature.
With reference now to accompanying drawing,, wherein various reference characters are represented similar parts in some views, and Fig. 1 is the schematic cross section of the part of combustion gas turbine, show embodiments of the invention and operate residing environment.In Fig. 1, combustion gas turbine 100 comprises: compressor section 105; Combustion sec-tion 150; With turbine section 180.
Generally speaking, compressor section 105 comprises a plurality of rotation blades 110 and fixed tab 115 that are configured to compressed fluid.Compressor section 105 also can comprise to be extracted mouth 120, inner core 125, compressor air-discharging cover 130, cooperate joint (marriage joint) 135 and cooperates track bolt 137.
Combustion sec-tion 150 comprises a plurality of explosion chamber 155, a plurality of fuel nozzle 160 and a plurality of transition part section 165 substantially.A plurality of explosion chambers 155 can be connected to fuel source.In each explosion chamber 155, pressurized air from compressor section 105 receive and with the fuel mix that receives from fuel source.Working fluid is lighted and produced to air and fuel mixture.Working fluid is advanced from the rear end of a plurality of fuel nozzles 160 substantially towards downstream, gets into turbine section 180 through transition part section 165.
Typically, in the operation period of combustion gas turbine 100, a plurality of parts experience high temperature and possibly need cooling or purge.These parts can comprise a part, cooperation joint 135 and a plurality of zone, space 195 of taking turns of compressor section 105.
Extract the cooling fluid of mouthful 120 extractions from compressor section 105.The cooling fluid bypass is through (bypasses) combustion sec-tion 150, and the mobile cooling circuit 200 (shown in Fig. 2) that passes through, and is used for cooling or the various parts of purge, comprises cooperating joint 135 and a plurality of spaces regional 195 of taking turns.
With reference now to Fig. 2,, Fig. 2 is the close-up view of the combustion gas turbine shown in Fig. 1.Fig. 2 shows the embodiment's of cooling circuit 200 indefiniteness example.The stream of cooling circuit 200 can start from extracting mouthful 120 (shown in Fig. 1), flow through compressor air-discharging cover 130 a part, inner core cover 125 and flow to chamber then in the rear end of compressor section 105.Then, cooling circuit 200 can be oppositely, flow through cooperating joint 135, sealing system parts 140, until zone, wheel space 195.
Fig. 3 shows the schematic representation of the fixed component 190 of the Fig. 2 with known nozzle cooling circuit.Fixed component 190 comprises the nozzle cooling circuit 300 that is positioned at inside.Nozzle cooling circuit 300 allows cooling fluid to cool off fixed component 190 internally.Nozzle cooling circuit 300 receives in the drawings by the cooling fluid shown in the arrow.Current known loop 300 comprises can the path of direct cooled fluid to discharge at the upstream side of fixed component 190.After leaving fixed component 190, cooling fluid can flow through sealing system parts 140 towards downstream and engage the downstream side of fixed component 190 then.
Fig. 4 shows the schematic representation of the fixed component that has the nozzle cooling circuit among Fig. 2 according to embodiments of the invention.Fixed component 190 comprises the nozzle cooling circuit 400 that is positioned at inside.Nozzle cooling circuit 400 allow cooling fluids with more controlled and efficiently mode cool off fixed component 190.Nozzle cooling circuit 400 receives in the drawings by the cooling fluid shown in the arrow.Through comparison diagram 3 and Fig. 4, shown the benefit of embodiments of the invention.Here, cooling fluid 405 flows to collector 410 from the main passage; Said collector allows cooling fluid on the upstream and downstream both direction, to discharge from fixed component 190.This allows the cooling more efficiently of the downstream of fixed component 190.
Fig. 5 shows the decomposing schematic representation of the fixed component of Fig. 4 according to embodiments of the invention.The embodiment of nozzle cooling circuit 400 can comprise main passage 405, collector 410, aperture 415 and adjusting plug 420.
The embodiment of main passage 405 can comprise first end and the second end.First end can be oriented to receive cooling fluid.The second end is positioned at the opposed end of main passage 405.The second end can be connected to collector 410 with the mode that allows cooling fluid to get into.Nozzle cooling circuit 400 can comprise a main passage 405 in an embodiment of the present invention.In alternative of the present invention, nozzle cooling circuit 400 can comprise a plurality of main passages 405.Here, each main passage 405 can comprise special-purpose collector 410.
The embodiment of collector 410 can have the form of through hole etc.Each end of collector 410 can be via cap 425 sealings, for example as shown in Figure 5.Cap 425 can be via welding, be threaded or other connection means are connected to collector 410.
The embodiment of adjusting plug 420 can comprise and allows to be threaded with the part in aperture 415 cooperates.The alternative of adjusting plug 420 can be press fit in the aperture 415.Another alternative of adjusting plug 420 can comprise inside diameter-variable, and cooling fluid is discharged from collector 410 through said inside diameter-variable, and the more controls to aforesaid properties are provided.
Fig. 6 shows the schematic representation of the fixed component 190 in using among Fig. 4 according to embodiments of the invention.In use, embodiments of the invention can be worked as follows.Nozzle cooling circuit 400 is received in the cooling fluid of being represented by arrow among Fig. 4.Then, cooling fluid can flow through main passage 405.Then cooling fluid can get into collector 410.Here, flowing of cooling fluid can bifurcated.A part can flow towards upstream orifice 415, discharges via the adjusting plug that is connected 420.Remaining part can flow towards downstream orifice 415, discharges via the adjusting plug that is connected 420.
Although illustrate and described specific embodiment in this manual, those skilled in the art can understand, and specific embodiment and the present invention shown in any layout that can obtain identical purpose can replace have other application in other environment.The application is intended to contain any change of the present invention or modification.Following claim is in no way intended to limit the scope of the invention to the specific embodiment described in this specification.
Those skilled in the art will understand, and the characteristic of many variations of describing about some embodiments above can also optionally be used to form other possible embodiment of the present invention with configuration.Those skilled in the art also will understand, and all possible repetition the of the present invention do not provided in detail or discuss, although by following some claims or otherwise contain all the combination and possible embodiment be intended to a part for the application.In addition, those skilled in the art will expect improving, change and revise from some embodiments' of the present invention above description.Such improvement, variation and modification that those skilled in the art carry out also are intended to contained by accompanying claims.In addition, what it should be obvious that is, preceding text only relate to said embodiment of the present invention and can carry out many variations and modification in this manual and do not break away from the spirit and scope of the present invention that limited following claim and equivalent thereof.
Claims (10)
1. system that is used to regulate cooling fluid, said system comprises:
Combustion gas turbine (100), said combustion gas turbine comprises:
Combustion system (150), said combustion system generates working fluid;
Compressor section (105), said compressor section comprise inner core cover (125); Compressor air-discharging cover (130); And bypass chamber; Wherein said cooling fluid flow to said compressor air-discharging cover (130) through said inner core cover (125);
Turbine section (180), said turbine section comprise rotary component (185); Fixed component (190); With wheel space zone (195), wherein each is taken turns zone, space (195) and comprises rotary component (185) and fixed component (190), and each bypass chamber allows said cooling fluid to pass to the said zone, space (195) of taking turns from said compressor section (150); And
Nozzle cooling circuit (400), said nozzle cooling circuit roughly is positioned at each fixed component (190), and wherein said nozzle cooling circuit (400) comprises main passage (405) and collector (410); The second end that the first end of wherein said main passage (405) receives said cooling fluid and said main passage (405) is connected to said collector (410), and said cooling fluid flow to said collector (410) from said main passage (405); Wherein said collector (410) comprises upstream orifice and downstream orifice, and said aperture allows said cooling fluid to mix from said collector (410) discharge and with said working fluid.
2. system according to claim 1 is characterized in that, also comprises the adjusting plug (420) in the downstream that are positioned at said collector (410), and said adjusting plug allows said cooling fluid to leave said nozzle cooling circuit (400).
3. system according to claim 2 is characterized in that, each aperture and special-purpose adjusting plug (420) are integrally formed.
4. system according to claim 2 is characterized in that, said special-purpose adjusting plug (420) comprises inside diameter-variable, and said cooling fluid is discharged said collector (410) through said inside diameter-variable.
5. system according to claim 4 is characterized in that, said special-purpose adjusting plug (420) is confirmed at least a in the following character of said cooling fluid: speed, flow or pressure.
6. system according to claim 1 is characterized in that, said fixed component (190) comprises a plurality of nozzle cooling circuits (400).
7. system according to claim 2 is characterized in that, said special-purpose adjusting plug (420) guides said cooling fluid towards the outer surface of said fixed component (190).
8. system according to claim 1 is characterized in that, said collector (410) is departed from certain angle (430) in each aperture, and said angle is with the mode that helps to mix with the said working fluid said cooling fluid of prewhirling.
9. system according to claim 8 is characterized in that, said angle (430) the flowing of directed said cooling fluid on the direction that is similar to said working fluid and said rotary component (185).
10. system according to claim 2; It is characterized in that; The form of the rounded opening of said collector (410), said circular open extends through said fixed component (190) on the direction in the upper reaches to downstream, and each end of said collector (410) is sealed by cap (425).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/053,638 US20110189000A1 (en) | 2007-05-01 | 2011-03-22 | System for regulating a cooling fluid within a turbomachine |
| US13/053638 | 2011-03-22 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102691532A true CN102691532A (en) | 2012-09-26 |
Family
ID=45887981
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012100896833A Pending CN102691532A (en) | 2011-03-22 | 2012-03-22 | System for regulating a cooling fluid within a turbomachine |
Country Status (2)
| Country | Link |
|---|---|
| EP (1) | EP2503101A2 (en) |
| CN (1) | CN102691532A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105569750A (en) * | 2014-10-29 | 2016-05-11 | 通用电气公司 | Rotary machine, terminal for examining apparatus thereof, method for providing by-pass passange for cooling passage in casing |
| CN106438046A (en) * | 2015-08-13 | 2017-02-22 | A.S.En.安萨尔多开发能源有限责任公司 | Gas turbine unit with adaptive pre-swirler |
| CN106545364A (en) * | 2015-09-16 | 2017-03-29 | 通用电气公司 | For the mixing chamber of turbine wheel space cooling |
| CN108252748A (en) * | 2016-10-12 | 2018-07-06 | 通用电气公司 | Turbogenerator induces device assembly |
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| EP3068996B1 (en) | 2013-12-12 | 2019-01-02 | United Technologies Corporation | Multiple injector holes for gas turbine engine vane |
| US10125632B2 (en) | 2015-10-20 | 2018-11-13 | General Electric Company | Wheel space purge flow mixing chamber |
| US10132195B2 (en) * | 2015-10-20 | 2018-11-20 | General Electric Company | Wheel space purge flow mixing chamber |
| US10436050B2 (en) | 2017-04-11 | 2019-10-08 | United Technologies Corporation | Guide vane arrangement for gas turbine engine |
| KR102541933B1 (en) | 2018-08-21 | 2023-06-13 | 지멘스 에너지 글로벌 게엠베하 운트 코. 카게 | Modular casing manifolds for cooling fluids in gas turbine engines |
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| CN87101971A (en) * | 1986-05-01 | 1987-11-11 | 通用电气公司 | The turbine flow nozzle that is used for the gas turbine cooling system |
| CN1227619A (en) * | 1996-06-21 | 1999-09-01 | 西门子公司 | Turbomachine and process for cooling a turbomachine |
| CN1068409C (en) * | 1991-11-19 | 2001-07-11 | 通用电气公司 | Integrated steam/air cooling system for gas turbines |
| EP1988255A2 (en) * | 2007-05-01 | 2008-11-05 | General Electric Company | System for regulating a cooling fluid within a turbomachine |
| EP1988260A2 (en) * | 2007-05-01 | 2008-11-05 | General Electric Company | Method and system for regulating a cooling fluid within a turbomachine in real time |
-
2012
- 2012-03-19 EP EP12160035A patent/EP2503101A2/en not_active Withdrawn
- 2012-03-22 CN CN2012100896833A patent/CN102691532A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN87101971A (en) * | 1986-05-01 | 1987-11-11 | 通用电气公司 | The turbine flow nozzle that is used for the gas turbine cooling system |
| CN1068409C (en) * | 1991-11-19 | 2001-07-11 | 通用电气公司 | Integrated steam/air cooling system for gas turbines |
| CN1227619A (en) * | 1996-06-21 | 1999-09-01 | 西门子公司 | Turbomachine and process for cooling a turbomachine |
| EP1988255A2 (en) * | 2007-05-01 | 2008-11-05 | General Electric Company | System for regulating a cooling fluid within a turbomachine |
| EP1988260A2 (en) * | 2007-05-01 | 2008-11-05 | General Electric Company | Method and system for regulating a cooling fluid within a turbomachine in real time |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105569750A (en) * | 2014-10-29 | 2016-05-11 | 通用电气公司 | Rotary machine, terminal for examining apparatus thereof, method for providing by-pass passange for cooling passage in casing |
| CN106438046A (en) * | 2015-08-13 | 2017-02-22 | A.S.En.安萨尔多开发能源有限责任公司 | Gas turbine unit with adaptive pre-swirler |
| CN106438046B (en) * | 2015-08-13 | 2020-11-20 | A.S.En.安萨尔多开发能源有限责任公司 | Gas turbine unit with adaptive preswirler |
| CN106545364A (en) * | 2015-09-16 | 2017-03-29 | 通用电气公司 | For the mixing chamber of turbine wheel space cooling |
| CN106545364B (en) * | 2015-09-16 | 2021-01-05 | 通用电气公司 | Mixing chamber for turbine wheel space cooling |
| CN108252748A (en) * | 2016-10-12 | 2018-07-06 | 通用电气公司 | Turbogenerator induces device assembly |
| US10787920B2 (en) | 2016-10-12 | 2020-09-29 | General Electric Company | Turbine engine inducer assembly |
| US11466582B2 (en) | 2016-10-12 | 2022-10-11 | General Electric Company | Turbine engine inducer assembly |
| US11846209B2 (en) | 2016-10-12 | 2023-12-19 | General Electric Company | Turbine engine inducer assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2503101A2 (en) | 2012-09-26 |
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Application publication date: 20120926 |