CN101892867A - The control of turbine wheel space temperature - Google Patents
The control of turbine wheel space temperature Download PDFInfo
- Publication number
- CN101892867A CN101892867A CN2010101899134A CN201010189913A CN101892867A CN 101892867 A CN101892867 A CN 101892867A CN 2010101899134 A CN2010101899134 A CN 2010101899134A CN 201010189913 A CN201010189913 A CN 201010189913A CN 101892867 A CN101892867 A CN 101892867A
- Authority
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- China
- Prior art keywords
- cooling air
- actuator
- temperature
- impeller space
- control valve
- 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
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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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
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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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/11—Purpose of the control system to prolong engine life
- F05D2270/112—Purpose of the control system to prolong engine life by limiting temperatures
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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
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/303—Temperature
- F05D2270/3032—Temperature excessive temperatures, e.g. caused by overheating
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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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to the control of turbine wheel space temperature.Be used for the sensor (70) that the equipment of cooling air volume in impeller space (68) that control offers the turbine section (14) of gas turbine (10) comprises the temperature in sensing impeller space (68) and sensing temperature signal (52) is provided.This equipment also comprises processor (50), and its response sensing temperature signal (52) judges whether the temperature in impeller space (68) surpasses expected value.If the temperature of impeller space (68) surpasses expected value, then processor (50) triggers the motion of actuator control signal (54) with control cooling air control valve (82), in order to allow more substantial be derived from gas turbine (10) compressor section (12) or be derived from from the cooling air of the cooling air cooler (33) of compressor section (12) admission of air of gas turbine (10) flow to impeller space (68), thereby the temperature of cooling wheel space (68).
Description
Technical field
Theme disclosed herein relates to gas turbine, and relates to the temperature that the cooling blast that offers the impeller space by control is controlled the impeller space (wheelspace) of gas turbine turbine section particularly.
Background technique
The turbine wheel space is meant in corresponding in a row rotor disk of turbine blade of supporting or those cavitys or the zone in the gas turbine turbine section between the impeller.The impeller space is positioned at the inner radial through the main air flow of adjacent turbine stage.Usually, the wheel disc of inner radial heats by various effects, comprises that conduction, main air flow via rotor blade enters into the wind-force disturbance heating in impeller space cavity and the impeller space.
The function of the aging or set state of the actual normally turbine output of turbine wheel space temperature, ambient temperature and unit.Wheel space temperature carries out sensing or monitoring usually, and can report to the police and be higher than the signal that can accept temperature reading in order to transmission.This in order to prevent owing to the unacceptably warning of too high wheel space temperature, gas turbine operator cpable of lowering power.Yet this operating in caused revenue losses and limited total equipment output potentially in the higher weather of temperature.
Be used to realize that another kind of method that wheel space temperature descends comprises that gas turbine is shut down, change the orifice plate in the cooling supply loop, reset gas turbine then.Yet this process causes the delay of shutting down and starting, and need carry out frequent adjustment according to ambient temperature.
Another method that is used to regulate wheel space temperature comprises the minimizing cool stream, thereby has the effect of rising impeller temperature.Setting higher relatively wheel space temperature impels performance to improve; Yet, also can reduce the Life cycle of gas turbine.
It is also known that, provide cooling blast to the impeller space in series or in parallel simultaneously with the cooling blast of other member that offers gas turbine.Yet, even have variable cooling blast, but the problem for some embodiments of this operation is, if provide enough cooling blast to the impeller space, the cooling blast that then generally offers other gas turbine component (for example, turbine nozzle, dividing plate (diaphragm), guard shield) may be not enough to fully cool off these other members.
Summary of the invention
According to an aspect of the present invention, the equipment that is used to control the cooling air volume in the impeller space that offers the gas turbine turbine section comprises sensor, and the temperature in this sensor sensing impeller space also provides the sensing temperature signal.This equipment also comprises processor, and this processor response sensing temperature signal judges whether the temperature in impeller space surpasses expected value.If the temperature in impeller space surpasses expected value, then processor triggers the motion of actuator control signal with control cooling air control valve, in order to allow more substantial be derived from gas-turbine compressor portion section or be derived from from the cooling air of the cooling air cooler of gas-turbine compressor portion section admission of air flow to the impeller space, thereby the temperature in cooling wheel space.
According to a further aspect in the invention, the equipment that is used to control the cooling air volume in the impeller space that offers the gas turbine turbine section comprises sensor, and the temperature in this sensor sensing impeller space also provides the sensing temperature signal.This equipment also comprises processor, and this processor response sensing temperature signal judges whether the temperature in impeller space is lower than expected value.If the temperature in impeller space is lower than expected value, then processor triggers the motion of actuator control signal with control cooling air control valve, flow to the impeller space in order to allow the compressor section that is derived from gas turbine more in a small amount or to be derived from, thereby allow the temperature in impeller space to raise from the cooling air of the cooling air cooler of the compressor section admission of air of gas turbine.
According to the description below in conjunction with accompanying drawing, it is more obvious that these and other advantage and feature will become.
Description of drawings
Be considered as that theme of the present invention is specifically noted and claimed clearly in claims.According to the detailed description below in conjunction with accompanying drawing, above-mentioned and other feature and advantage of the present invention become obviously, in the accompanying drawings:
Fig. 1 has the block diagram that embodiments of the invention are positioned at gas turbine wherein;
Fig. 2 is the sectional view of a part of turbine section that comprises the gas turbine of one embodiment of the present of invention; And
Fig. 3 is the sectional view of a part of turbine section that comprises the gas turbine of another embodiment of the present invention.
Detailed description is for example understood embodiments of the invention, and advantage and feature.
List of parts
10 gas turbines
12 compressor section
14 turbine sections
16 center lines
18,20 ports
22,24,38,40 pipelines
26,28,30,32,42,44,46,48 inlet ports
33 air-coolers
34,36 ports
50 microprocessors
52,54 signal paths
60 turbine shells
62 bins
64 nozzles
66 dividing plates
68 impeller spaces
70 sensors
72 devices
74 outputs
76 synchronizing ring (synch ring)
78 actuators
80
82 valves
84,92 holes
86 linings
90 pipes
92,106 holes
100 linkages
102 valve collars
104 openings
Embodiment
In Fig. 1 is gas turbine 10, and it comprises provides compressed-air actuated compressor section 12.Compressor 12 can be aimed at the turbine section 14 of gas turbine 10 on by the single shaft of vertical center line 16 representatives vertically.Most of pressurized air can be supplied to turbine burner (not shown), but can extract some pressurized air to use it for anything else.For example, according to embodiments of the invention, cooling air can extract port one 8,20 places from compressor 12 extractions, and (for example by pipeline, pipe, pipeline etc.) 22,24 be fed to turbine section 14 selection areas and final by inlet ports 26,28,30,32 (for example, hole in the turbine shell) be fed to impeller space (Fig. 2-3) in the turbine section 14, as described in greater detail below and shown in Fig. 2-3.In an alternative, cooling air cooler 33 can be arranged in one of pipeline 24 and be positioned at gas turbine 10 outsides.The cooling air that is derived from compressor section 12 on the pipeline 24 can offer cooling air cooler 33, and its further cooling offers the pressurized air of respective input mouth 26,28 subsequently.In a similar fashion, equally according to embodiments of the invention, cooling air can and (for example pass through pipeline 38,40 from 34,36 extractions of compressor port, pipe, pipeline etc.) supply, and (for example by inlet ports 42,44,46,48, hole in the turbine shell) finally be supplied to impeller space in the turbine section 14, as described in greater detail below and shown in Fig. 2-3.
Embodiments of the invention can comprise feedback control loop, with on the lower limit that wheel space temperature is controlled at expectation respectively and the upper limit or lower limit and the CLV ceiling limit value or under (for example, in acceptable value scope).Therefore, embodiments of the invention can comprise processor, counting circuit or the logical circuit of microprocessor 50 or other adequate types.One or more signals on the microprocessor 50 response corresponding signal paths 52 are for example established at least one in the wired or wireless circuit etc. in each path 52, or its combination.Each signal on the corresponding signal path 52 is indicated directly or indirectly as the temperature by the suitable respective impeller space that temperature transducer provided that is arranged in impeller space (Fig. 2-3).Yet, also can use other suitable sensing signal of indicating wheel space temperature directly or indirectly.Seeing below Fig. 2-3 describes in more detail, microprocessor 50 responds the wheel space temperature signals and one or more actuator control signal is provided on corresponding signal path 54, for example establish at least one in the wired or wireless circuit etc. in each path 54, or its combination.Actuator control signal is used for controlling the amount from the cooling blast of compressor, so that the temperature of each in each impeller space is controlled to be expected value or acceptable value.
In Fig. 2 is one embodiment of the present of invention, and wherein, hole shape becomes (for example, cast iron) the turbine shell 60 that passes entity and enters internal cavities or bin 62.Be provided with one of pipeline (pipe, pipeline etc.) 22,24,38,40 via this hole, it will be provided in the bin 62 of open region from the pressurized air of compressor 12 (Fig. 1).Pressurized air in the bin 62 flows to downwards in Fig. 2 in the hollow nozzle 64 without restriction, and this nozzle can be air foil shape as known in the art.This identical pressurized air also can flow to downwards in the dividing plate 66 of open region without restriction.As described in greater detail below, according to one embodiment of present invention, the pressurized air that enters bin 62 is used for controlling in the turbine section 14 (Fig. 1) temperature in respective impeller space 68 shown in figure 2.
One or more temperature transducers 70 can be positioned at each impeller space 68.Each impeller space 68 all can be the circumferential cavity of continual 360 degree of the turbine section 14 (Fig. 1) that is arranged in gas turbine 10.Because turbine section 14 (Fig. 1) has many row's turbine blades usually, so there is the impeller space 68 of numerous quantity between blade in a row.Sensor 70 can be the sensor of any adequate types, its directly or indirectly sensing impeller space 68 temperature and the wheel space temperature signal on the signal path 52 offered microprocessor 50.According to one embodiment of present invention, the temperature at that time of judging any one or a plurality of particular impeller space 68 when microprocessor 50 during greater than expected value or acceptable CLV ceiling limit value (for example, by the wheel space temperature of institute's sensing is compared with one or more expected values in for example being stored in the storage relevant with microprocessor 50), actuator control signal on the microprocessor 50 trigger signal paths 54 is reduced to expected value in order to the temperature in this particular impeller space 68 the most at last.
Embodiments of the invention also can have microprocessor 50, and it for example uses similar method of comparison to judge that whether the temperature at that time in any one or a plurality of particular impeller space 68 is less than expected value or acceptable lower limit.If institute's sensed temperature is less than expected value, but the actuator control signal on the microprocessor trigger signal path 54 then is elevated to expected value in order to the temperature that finally makes this particular impeller space 68.
Actuator control signal on the signal path 54 can be connected to device 72, for example electromechanical assembly (for example, motor), hydraulic actuator or other suitable device.Device 72 output 74 can be connected to optional synchronizing ring 76, and this synchronizing ring can be contiguous and around the whole circumference of the turbine section 14 (Fig. 1) of gas turbine 10.If adopt, synchronizing ring 76 is connected on each of a plurality of actuators 78 of being arranged in turbine shell 60 outsides.Such actuator 78 has been shown among Fig. 2.The output shaft of actuator 78, it can rotate or be movable with certain other suitable manner, be connected to also can rotate or with certain other suitable manner movable the axle 80 on.Axle 80 is connected on the cooling air control valve 82 with one or more ellipses (or other is suitable) shaped aperture 84 at the place, bottom (as shown in FIG. 2) that it is positioned at bin 62.Valve 82, it can be positioned at bin 62, can rotate or movable with certain other suitable manner.Cooling air control valve 82 also can comprise the valve of other adequate types, for example disc valve, gate valve or ball valve.Sealing and/or lining 86 are set in order to the seal shaft 80 suitably in the output joint of axle 80 and actuator 78.Lining 86 also passes the hole of formation (for example, drilling) in turbine shell 60 and is placed in order to provide sealing around axle 80.Sealing and/or lining 86 have reduced the pressurized air gas from turbine shell 60 inner side leakage to shell 60 outsides.
In operation, the temperature at that time of judging particular impeller spaces 68 when microprocessor 50 is during greater than expected value or acceptable CLV ceiling limit value, actuator control signal on the microprocessor trigger signal path 54, it finally causes the hole 84 in the cooling air control valve 82 to be alignd with the hole 92 (wholly or in part) in pipe 90 the top.When alignment like this, in a certain amount of pressurized air intake channel 90, flow downward by managing 90, and finally flow in the impeller space 68 in this permission bin 62.This pressurized air is usually than surpassing CLV ceiling limit value and making the pressurized air of cooling flow to the colder than hot air of 68 sensings in impeller space in the impeller space 68, thus the temperature in reduction impeller space 68.In case microprocessor 50 judges that wheel space temperature is equal to or less than CLV ceiling limit value, therefore and be in acceptable value, then microprocessor just the actuator control signal on the trigger signal path 54 and therefore make hole 92 misalignment in the top of hole 84 and pipe 90 in the valve 82 or only partly aim at so that cooling air control valve 82 moves.This prevention or the pressurized air that has reduced cooling flow to impeller space 68 by managing 90.
Similarly be, the temperature at that time of judging particular impeller spaces 68 when microprocessor 50 is during less than expected value or acceptable lower limit, actuator control signal on the microprocessor trigger signal path 54, it finally makes the hole 84 in the valve 82 align with the hole 92 (partially or completely not) in pipe 90 the top.When alignment like this, this allows not have in bin 62 pressurized air or only in a small amount the pressurized air intake channel 90, flows downward by managing 90, and finally flow in the impeller space 68.The cooling air volume that this minimizing offers impeller space 68 allows the temperature in impeller space 68 owing to previous reasons raises.
According to embodiments of the invention, each impeller space 68 can be adopted as shown in Figure 2 and the combination of a plurality of actuators as indicated above 78 and valve 82.Therefore, if adopt, synchronizing ring 76 can be used to make around the whole circumference of turbine section 14 (Fig. 1) and corresponding to a plurality of actuators 78 in single impeller space 68 and the combination of valve 82 and triggers simultaneously, thereby the temperature in this impeller space 68 suitably is controlled to be expected value.Each impeller space 68 all can have the synchronizing ring 76 of himself special use.
In Fig. 3 is another embodiment of the present invention, and it is similar to the embodiment of Fig. 2 to a certain extent.Therefore, shown between Fig. 2 and Fig. 3, similar reference number is represented similar components.In Fig. 3, replace pipe 90,80 a whole height downward (as shown in FIG. 3) that pass hollow nozzle 64 extends and enters in the dividing plate 66.Place, bottom at axle 80 is movable (for example, rotatable) linkage 100, and it is connected on the cooling air control valve 102 of form for the rotation valve collar, and this rotary valve endless belt has one or more isolated openings 104 that are formed on wherein.Be similar to the embodiment of Fig. 2, cooling air control valve 102 can comprise the valve of other adequate types, for example disc valve, gate valve or ball valve.The rotation valve collar can be around the whole circumference of the turbine section 14 (Fig. 1) of gas turbine 10.Each opening 104 all is communicated with by forming 68 one-tenth fluids of (for example, drilling) respective aperture 106 in the entity metalwork of dividing plate 66 and impeller space.
In operation, the temperature at that time of judging particular impeller spaces 68 when microprocessor 50 is during greater than expected value or acceptable CLV ceiling limit value, actuator control signal on the microprocessor trigger signal path 54, it (for example finally makes axle 80 motions, rotate) and (for example make linkage 100 motions, rotation), up to rotation each opening 104 in the valve collar 102 with till aliging in a corresponding hole 106 (wholly or in part).When opening 104 so aligns, this allows the flow through opening 104 of alignment of a certain amount of cooled compressed air in dividing plate 66 to go forward side by side in the hand-hole 106, flow downward (as shown in FIG. 3) by hole 106, and finally flow in the impeller space 68, thereby the temperature in impeller space 68 is reduced to acceptable value.Be similar to the embodiment of Fig. 2, in case microprocessor 50 judges that wheel space temperature is lower than CLV ceiling limit value, microprocessor is the actuator control signal on the trigger signal path 54 just, so that 102 motions of cooling air control valve (for example, rotation), and therefore make opening 104 in the rotation valve collar 102 with respective aperture 106 misalignment or only partly aim at.This prevention or the pressurized air that has reduced cooling flow to impeller space 68.
Equally, the temperature at that time of judging particular impeller spaces 68 when microprocessor 50 is during less than expected value or acceptable lower limit, actuator control signal on the microprocessor trigger signal path 54, it (for example finally makes axle 80 motions, rotate) and (for example make linkage 100 motions, rotation), in rotation valve collar 102 each opening 104 not with till aliging in the corresponding hole (wholly or in part) in the hole 106.When opening 104 so aligns, this allow no cooled compressed air or only in a small amount cooled compressed air enter in the dividing plate 66 and the opening 104 of flowing through and aliging, enter in the hole 106 and and flow downward (as shown in FIG. 3), and finally flow in the impeller space 68 by hole 106.This temperature that allows impeller space 68 is owing to previous reasons is elevated to expected value or acceptable value
Embodiments of the invention offer the cooled compressed air in impeller space 68 and separate and separate the control that improves the turbine wheel space temperature with the cooling blast that is sent to other gas turbine component to a great extent by control.Therefore, embodiments of the invention do not have negative effect to cooling blast and the relative any leakage that offers these other gas turbine components discretely, and not influenced by it.Embodiments of the invention can be used as remodeling (transformation) or are applied to the impeller space of gas turbine as the part of original design.
Embodiments of the invention also reduce the parasitic secondary gas flow of use, thereby increase gas turbine proficiency and power output.By using the compressor that links with microprocessor 50 to extract Flow-rate adjustment as the part of feedback control system, the compressed air require that reduces can be sent to impeller space 68, no matter and the variation aspect leakage flow is how between the variation of environmental conditions, load and the machine-machine.
Although described the present invention in detail in conjunction with the embodiment of limited quantity only, should be understood that easily that the present invention is not limited to these disclosed embodiments.Exactly, can make amendment with in conjunction with non-previously described but modification, remodeling, replacement or the equivalent arrangements of arbitrary quantity that match with the spirit and scope of the present invention to the present invention.In addition, though described various embodiment of the present invention, it should be understood that aspect of the present invention can only comprise described embodiment's a part.Therefore, the present invention should not be considered as being limited by aforementioned description, but is only limited by the scope of claims.
Claims (10)
1. one kind is used for the equipment of cooling air volume in impeller space (68) that control offers the turbine section (14) of gas turbine (10), and described equipment comprises:
Sensor (70), the temperature in the described impeller of its sensing space (68) and the signal (52) that sensing temperature is provided;
Processor (50), its signal (52) that responds described sensing temperature judge whether the temperature in described impeller space (68) surpasses expected value; And
If the temperature in described impeller space (68) surpasses described expected value, then described processor (50) triggers actuator control signal (54) with control cooling air control valve (82,102) motion, in order to allow more substantial be derived from the compressor section (12) of described gas turbine (10) or be derived from from the cooling air of the cooling air cooler (33) of described compressor section (12) admission of air of described gas turbine (10) flow to described impeller space (68), thereby cool off the temperature in described impeller space (68).
2. equipment according to claim 1 is characterized in that, described cooling air is provided for described cooling air control valve (82) and is positioned at wherein bin (62).
3. equipment according to claim 1, it is characterized in that, described actuator control signal (54) offers first actuator (78), described first actuator (78) responds the motion of the output shaft (80) of described actuator control signal (54) described first actuator of control (78), the output shaft (80) of described first actuator (78) and described cooling air control valve (82,102) connect, the described cooling air control valve (82 of the motion control of the output shaft of described first actuator (80), 102) motion flows to described impeller space (68) in order to allow described cooling air.
4. equipment according to claim 3, it is characterized in that, described cooling air control valve (82) is connected with pipe (90), described pipe (90) has one or more openings (92) of aiming at the one or more openings (84) in the described cooling air control valve (82), allows described cooling air to flow to described impeller space (68) when surpassing described expected value in order to the temperature when described impeller space (68).
5. equipment according to claim 3 is characterized in that, output shaft of described first actuator (80) and described cooling air control valve (82) are rotatable.
6. equipment according to claim 1, it is characterized in that, described second actuator (72) connects described actuator control signal (54), described second actuator (72) has the output that connects described first actuator (78), described first actuator (78) responds the motion of the output shaft of described actuator control signal (54) described second actuator of control (72), the output shaft (80) of described first actuator (78) is connected with described cooling air control valve (82), the motion of the described cooling air control valve of the motion control of the output shaft of described first actuator (80) (82) flows to described impeller space (68) in order to allow described cooling air.
7. equipment according to claim 6 is characterized in that, described second actuator (72) comprises one of motor or hydraulic actuator.
8. equipment according to claim 1 is characterized in that, described cooling air offers described cooling air control valve (82) by pipe, pipeline or hole and is positioned at wherein bin (62).
9. equipment according to claim 1, it is characterized in that, a plurality of first actuators (78) connect described actuator control signal (54), each first actuator in described a plurality of first actuators (78) all has the output of connection synchronizing ring (76), described synchronizing ring (76) responds described actuator control signal (54) and controls the motion of the output shaft (80) of each first actuator in described a plurality of first actuators (78) simultaneously, the output shaft (80) of each first actuator in described a plurality of first actuators (78) is connected to the corresponding cooling air control valve in a plurality of described cooling air control valves (82), the motion of the corresponding cooling air control valve of the motion control of each output shaft in the output shaft of described first actuator (80) (82) flows to described impeller space (68) in order to allow described cooling air.
10. equipment according to claim 1 is characterized in that, described cooling air control valve (82) comprises the rotation valve collar (102) that is positioned at dividing plate (66), and described cooling air offers described rotation valve collar (102) and is positioned at wherein described dividing plate (66).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/467,378 US20100290889A1 (en) | 2009-05-18 | 2009-05-18 | Turbine wheelspace temperature control |
| US12/467,378 | 2009-05-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101892867A true CN101892867A (en) | 2010-11-24 |
Family
ID=43028719
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010101899134A Pending CN101892867A (en) | 2009-05-18 | 2010-05-18 | The control of turbine wheel space temperature |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20100290889A1 (en) |
| JP (1) | JP2010265901A (en) |
| CN (1) | CN101892867A (en) |
| CH (1) | CH701139A2 (en) |
| DE (1) | DE102010016828A1 (en) |
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| CN112832909A (en) * | 2021-03-23 | 2021-05-25 | 中国航发沈阳发动机研究所 | Aeroengine flight envelope control method |
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| ITCO20120008A1 (en) | 2012-03-01 | 2013-09-02 | Nuovo Pignone Srl | METHOD AND SYSTEM FOR MONITORING THE CONDITION OF A GROUP OF PLANTS |
| US9670797B2 (en) * | 2012-09-28 | 2017-06-06 | United Technologies Corporation | Modulated turbine vane cooling |
| JP6320063B2 (en) | 2014-02-03 | 2018-05-09 | 三菱日立パワーシステムズ株式会社 | Gas turbine, gas turbine control device, and gas turbine cooling method |
| JP5897180B2 (en) * | 2015-04-03 | 2016-03-30 | 三菱日立パワーシステムズ株式会社 | gas turbine |
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| US10514065B2 (en) * | 2015-12-14 | 2019-12-24 | Hamilton Sundstrand Corporation | Bearing thermal management system and method |
| US10619509B2 (en) * | 2018-04-27 | 2020-04-14 | United Technologies Corporation | Gas turbine engine flow modulation in a rotating vane |
| US11047313B2 (en) * | 2018-12-10 | 2021-06-29 | Bell Helicopter Textron Inc. | System and method for selectively modulating the flow of bleed air used for high pressure turbine stage cooling in a power turbine engine |
| US20220136404A1 (en) * | 2020-10-29 | 2022-05-05 | General Electric Company | Gas turbine mass differential determination system and method |
| US12116898B2 (en) * | 2023-01-26 | 2024-10-15 | Pratt & Whitney Canada Corp. | Ram air driven blade tip clearance control system for turboprop engines |
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| US6523346B1 (en) * | 2001-11-02 | 2003-02-25 | Alstom (Switzerland) Ltd | Process for controlling the cooling air mass flow of a gas turbine set |
| US20070137213A1 (en) * | 2005-12-19 | 2007-06-21 | General Electric Company | Turbine wheelspace temperature control |
-
2009
- 2009-05-18 US US12/467,378 patent/US20100290889A1/en not_active Abandoned
-
2010
- 2010-05-06 DE DE102010016828A patent/DE102010016828A1/en not_active Withdrawn
- 2010-05-17 CH CH00769/10A patent/CH701139A2/en not_active Application Discontinuation
- 2010-05-18 JP JP2010114150A patent/JP2010265901A/en not_active Withdrawn
- 2010-05-18 CN CN2010101899134A patent/CN101892867A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4117669A (en) * | 1977-03-04 | 1978-10-03 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Apparatus and method for reducing thermal stress in a turbine rotor |
| US4893983A (en) * | 1988-04-07 | 1990-01-16 | General Electric Company | Clearance control system |
| US5224332A (en) * | 1990-12-27 | 1993-07-06 | Schwarz Frederick M | Modulated gas turbine cooling air |
| US6067792A (en) * | 1996-11-12 | 2000-05-30 | Rolls-Royce Plc | Apparatus for controlling cooling air in gas turbine engine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112832909A (en) * | 2021-03-23 | 2021-05-25 | 中国航发沈阳发动机研究所 | Aeroengine flight envelope control method |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2010265901A (en) | 2010-11-25 |
| US20100290889A1 (en) | 2010-11-18 |
| CH701139A2 (en) | 2010-11-30 |
| DE102010016828A1 (en) | 2010-12-02 |
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Application publication date: 20101124 |