CN204283516U - For housing and the temperature control fluid conduit thereof of turbogenerator - Google Patents
For housing and the temperature control fluid conduit thereof of turbogenerator Download PDFInfo
- Publication number
- CN204283516U CN204283516U CN201420119083.1U CN201420119083U CN204283516U CN 204283516 U CN204283516 U CN 204283516U CN 201420119083 U CN201420119083 U CN 201420119083U CN 204283516 U CN204283516 U CN 204283516U
- Authority
- CN
- China
- Prior art keywords
- inner passage
- temperature control
- control fluid
- conduit
- turbine
- 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.)
- Expired - Lifetime
Links
- 239000012530 fluid Substances 0.000 title claims abstract description 106
- 238000009434 installation Methods 0.000 claims abstract description 26
- 238000001816 cooling Methods 0.000 abstract description 6
- 230000002093 peripheral effect Effects 0.000 abstract description 2
- 238000000638 solvent extraction Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 230000007704 transition Effects 0.000 description 3
- 239000002826 coolant Substances 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 241001672694 Citrus reticulata Species 0.000 description 1
- 230000004087 circulation Effects 0.000 description 1
- 239000012809 cooling fluid Substances 0.000 description 1
- 230000003467 diminishing effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
Abstract
The utility model relates to a kind of housing for turbogenerator and temperature control fluid conduit thereof, comprises one or more installation groove, each installation groove containing fluid conduit.Temperature control fluid circulates optionally to heat by fluid conduit systems or peripheral part of cooling turbomachine inner casing, controls the heat growth of those parts of described inner turbine thus.This makes the gap optionally controlled between the tip of the turbine bucket rotated and the surrounding shield of turbo machine become possibility.
Description
Technical field
The utility model relates to turbogenerator correlation technique, particularly relates to the housing technologies of the turbogenerator with cooling unit (temperature control fluid conduit).
Industrial Turbine motor comprises compressor section, combustor section and turbine section.In turbine section, be arranged on epitrochanterian more lines blade (or bailing bucket) and rotate between respective column fixed nozzle.For each row turbine bucket, circumferential guard shield is installed on turbine cylinder, and this guard shield is just radially positioned at the most advanced and sophisticated outside of turbine bucket.
The tip friction guard shield of turbine bucket when must keep leaving gap to prevent in turbine blade rotation between the tip and guard shield of turbine bucket.But it is little of as far as possible to prevent motive gas from leaking from the most advanced and sophisticated of blade around that people expect to keep this gap.Typically, gap is less, and turbo machine is more effective.
Within the transitional period, such as when turbo machine starts, or when turbo machine increases or reduce load or rotating speed, the temperature of the various elements in turbine section may raise or reduce.Unfortunately, the temperature of various element does not trend towards raising with same speed and reducing.Such as, during start-up operation, the temperature of turbine bucket trends towards raising more rapidly than turbine cylinder, and this turbine cylinder holds the guard shield around the tip of turbine bucket.This turbine bucket is arranged on disk, and this disk also heating also radially expands outwardly.
When the temperature of a part for turbo machine raises faster than another part, heat the slower part of the comparable temperature of part faster rising and stand thermal expansion faster/heat growth.During start-up operation, if the temperature of turbine bucket raises the turbine cylinder faster than holding guard shield, the comparable turbine cylinder of this turbine bucket stands heat expansion faster in radial directions.
And the different piece of turbo machine is made up of the different materials with different thermal expansion coefficient.Even if the temperature of all elements raises with phase same rate, the difference of the thermal expansion coefficient of different materials will cause different elements relative to each other to grow different quantity.
Another factor is the load putting on different elements.Turbine bucket and be provided with the disk of these turbine buckets thereon, stands mechanical centripetal force due to blade and disk rotational.This also can cause disk and turbine bucket radially to grow.Under relatively low rotating speed, produce relatively little growth due to this mechanical load.But along with the increase of rotating speed, blade and disk trend towards becoming longer.On the contrary, the guard shield around turbine bucket does not rotate and can not stand the growth because centripetal force causes.
When determining the size of element of turbo machine, all of these factors taken together must all be taken into account to guarantee can not grow oversize in the radial direction at its guard shield that starts to rub at any given time point turbine bucket by artificer.But, when the element of turbo machine is designed to guarantee always to retain certain gap between the tip and guard shield of turbine bucket, this can cause this gap to be greater than gap required during steady state operation, and this can have a negative impact to the efficiency of turbogenerator.
In order to address this problem, the selected portion of turbine cylinder can during transition or be heated and/or be cooled, to control guard shield position in radial directions during steady state operation.Correspondingly, this controls the gap between turbine bucket and guard shield.The optionally heating during transition of the part of turbine cylinder or cooling can be guaranteed during transition between the tip and guard shield of turbine bucket, to retain certain gap.Gap between the tip of turbine bucket and guard shield can be reduced to minimum required size by turbine cylinder optionally heating and/or cooling during steady state operation, makes the efficiency of turbogenerator maximum thus.
The trial of optionally heating and/or the cooling turbine engine housing of prior art requires the select location place in turbine cylinder, such as in radial directions just outside guard shield, forms coolant channel.Manufacture turbine cylinder possibility by this way expensive and difficult.Further, it is impossible for this design being attached in existing turbogenerator.Turbine cylinder must manufacture and comprise coolant channel from the beginning.
Model utility content
In a first aspect, the utility model can be presented as the inner casing comprising multiple arc housing parts of the turbine section at turbogenerator, and described multiple arc housing parts is configured to the inner casing being attached to one another to be formed general cylindrical.Each arc shell body divides the guard shield hook portion comprising at least one and extend in circumferential direction along the inner side of arc housing parts, and at least one installation groove extended in circumferential direction along arc housing parts.Each at least one installation groove described is positioned to adjacent with at least one guard shield hook portion described.The conduit had at least one inner passage of temperature control fluid is arranged at least one installation groove described.At least one catheter configurations described is installed in groove for slipping in circumferential direction.
In one aspect of the method, the utility model can be presented as temperature control fluid conduit, and described temperature control fluid catheter configurations is on the arcuate section of the inner casing of the turbine section being arranged on turbogenerator.Described fluid conduit systems comprises elongated, the arcuate main body of the inner passage had for temperature control fluid, and at least one is configured to allowable temperature and controls flow of fluid enter and enter hole in inner passage.
Accompanying drawing explanation
Fig. 1 shows the schematic diagram of the interface between the turbine bucket of the rotation of the turbine section of turbogenerator and peripheral part of turbine cylinder;
Fig. 2 shows the schematic diagram that part slides into the fluid conduit systems in the installation groove of inner turbine;
Fig. 3 shows the schematic diagram of the fluid conduit systems be installed to completely in the installation groove of inner turbine;
Fig. 4 is mounted in the sectional view of the first embodiment of the fluid conduit systems in the installation groove of inner turbine;
Fig. 5 is mounted in the sectional view of the second embodiment of the fluid conduit systems in the installation groove of inner turbine;
Fig. 6 is the fragmentary, perspective view of the first embodiment's of the bossed temperature control fluid conduit of a tool on the outer surface part;
Fig. 7 is the fragmentary, perspective view of the second embodiment's of the bossed temperature control fluid conduit of a tool on the outer surface part; With
Fig. 8 is mounted in the sectional view of the third embodiment of the fluid conduit systems in the installation groove of inner turbine.
Embodiment
Fig. 1 shows the schematic diagram of a part for the turbine section of turbogenerator.Fig. 1 shows turbine casing 100 and inner turbine 110.There is shown the tip of two row turbine buckets 122 and 124.Turbine bucket 122,124 row are installed on the rotor of turbo machine, and this turbine bucket rotates relative to the internal surface of inner turbine 110.Fixed nozzle row 130 are installed in the inner turbine 110 between two turbine buckets 122,124 row.
The guard shield 142,144 that circumference extends is installed in inner turbine 110 in the position relative with the tip of the turbine bucket 122,124 rotated.Guard shield 142,144 is installed on the guard shield hook of inner turbine 110.As illustrated in the background section, between the tip and secure shroud 142,144 of the turbine bucket 122,124 rotated, retain certain gap is necessary.But it is minimum to make the efficiency of turbogenerator maximum that people also expect to make this gap.
Fig. 1 shows temperature control fluid passage 150,152 and is formed in inner turbine 110.The fluid heated can circulate to make the temperature of inner turbine to raise in this temperature control fluid passage 150,152, and this will cause inner casing 110 radial outward expansion, thus increases the gap between guard shield 142,144 and the tip of turbine bucket 122,124.Meanwhile, the temperature of guard shield raises and trends towards causing the heat of guard shield to grow, and this trends towards reducing this gap.These factors must be balanced to guarantee that suitable temperature fluid is used to adjust gap by rights.
Result, cooling fluid carries out the temperature circulating to reduce inner turbine 110 by temperature control fluid passage 150,152, this will cause inner turbine 110 radially-inwardly to be shunk, thus the gap between the tip reducing guard shield 142,144 and turbine bucket 122,124.Meanwhile, guard shield is cooled and causes guard shield to shrink, this trends towards increasing this gap.Here, the temperature of fluid must be controlled carefully to guarantee to retain suitable gap.
In the different time, it can be favourable for using suitable temperature fluid to increase or reduce gap.But the design shown in Fig. 1 needs fluid passage to be formed in inner turbine, this may be expensive.
Fig. 2 shows design the utility model being embodied as the inner turbine 110 for turbogenerator, and inner turbine 110 comprises and can control the fluid conduit systems 200 of fluid stream by delivery temperature.The inner turbine of turbogenerator generally includes two or more arcuate segments, and these arcuate segments are bolted together to be formed the inner turbine of general cylindrical.Fig. 2 shows a part for an arcuate segments of inner turbine 110.Fig. 2 also show be formed at this inner turbine 110 inner radial surface on some guard shield hooks 114.Will be installed on guard shield hook 114 in the face of the guard shield at the tip of the turbine bucket of rotation.
Groove 120 is installed be formed in inner turbine 110, and is arranged in one group of direct neighbor of multiple guard shield hold-down hook 114 groups and in the position of radial outside.Elongated, arcuate conduit 200 is installed on installs in groove 120.Fig. 2 shows fluid conduit systems 200 and is inserted partially in installation groove 120.Fig. 3 shows fluid conduit systems 200 and is inserted into completely in installation groove 120.Fig. 2 and Fig. 3 also show the mounting blocks portion 240 when fluid conduit systems 200 is inserted in inner turbine 110 completely on fluid conduit systems and aims at the mounting blocks portion 112 of inner turbine 110.
Fig. 4 shows the sectional view of the first embodiment of the fluid conduit systems 200 be arranged in the installation groove 120 of inner turbine 110.This fluid conduit systems 200 has lower surface portion 210, and this lower surface portion 210 abuts with wall 116, and the position that installation groove 120 and guard shield are installed on guard shield hook 114 separates by this wall 116.
Fluid conduit systems 200 is in stepped shape, and it comprises and has small cross sections and amass and surround the top 230 of the first inner passage 232 and have larger sectional area and surround the bottom of the second inner passage 220.First inner passage 232 and the second inner passage 220 separate by the partitioning wall 222 with multiple hole 234.
Top 230 is also for this architecture provides hardness and rigidity, and this contributes to bottom and keeps its shape.Correspondingly, this contributes to preventing the random variation of bottom from affecting shape and the position of lower floor's guard shield.
Supply pipeline 250 is attached to the top 230 of fluid circuit 200.Temperature control fluid stream is transported in the first inner passage 232 by this supply pipeline 250.This temperature control fluid can flow in circumferential direction along the first inner passage 232.This temperature control fluid also enters the second inner passage 220 by the hole 234 in partitioning wall 222.Partitioning wall 222 with hole 234 contributes to before temperature control fluid enters the second inner passage 220 via hole 234, the temperature control fluid stream be transported in the first inner passage 232 being uniformly distributed circumferentially around inner turbine 110.
The temperature control fluid stream entering the second inner passage 220 flows out from fluid conduit systems 200 through multiple holes 212 of the lower wall 210 of fluid conduit systems 200.As by illustrating in further detail hereinafter, the outer wall of fluid conduit systems 200 is opened with the internal wall separates installing groove 120.As a result, temperature control fluid can pass through along the space between the outer wall of fluid conduit systems 200 and the inwall installing groove 120, and finally flows out to the position at the radial outside place being positioned at inner turbine 110.Arrow in Fig. 4 shows temperature control fluid stream and flows in the first inner passage 232 from supply pipeline 250, the second inner passage 220 is flow to from the first inner passage 232, by hole 212, flow in the outer periphery of fluid conduit systems 200, and flow out to the position at the radial outside place being positioned at inner turbine 110.
In substituting embodiment, the fluid through the first and second inner passage circulations need not flow to the position at the radial outside place being positioned at inner casing 110.On the contrary, this fluid can be collected and for other objects in inner turbine 110.
Structure shown in Fig. 4 causes temperature control fluid to impact the wall 116 adjacent with guard shield hold-down hook 114.As a result, this temperature control fluid can heat or the part directly relative with the tip of the turbine bucket rotated of cooling turbomachine inner casing and guard shield.This provide the heat of these parts of turbo machine is grown, thus to the gap between turbine bucket and guard shield fast and effectively control.
The installation step shape of groove 120 and the corresponding step shape of fluid conduit systems 200 make fluid conduit systems 200 can be easily mounted in inner turbine 110.Radially outer has the step shape of the sectional shape less than inner radial, guarantees when not using and installing hardware, fluid conduit systems to be trapped in inner turbine 110.Other shapes of installing groove 120 and fluid conduit systems 200 can realize similar function.Such as, installation groove 120 and fluid conduit systems 200 can be trapezoidal or triangle, and wherein, radially outer has the size less than inner radial.Further, in certain embodiments, the shape of installing groove need not mate the shape of fluid conduit systems.
Fig. 5 shows the substituting configuration of fluid conduit systems 200.In this embodiment, between first fluid passage 232 and second fluid passage 220, partitioning wall is not set.In various embodiments, to be to guarantee that temperature control fluid circumferentially distributes so unimportant for the favourable part of this embodiment.Partitioning wall is not had to reduce flow restriction.
Fig. 6 show multiple projection 242,244,246 can be formed at implement fluid conduit systems 200 of the present utility model outer wall on.Projection 242,244,246 for separating the outer wall of fluid conduit systems 200 and the inwall installing groove 120 in inner turbine 110.Retaining certain interval makes temperature control fluid can pass along the space between the outer wall of fluid conduit systems 200 and the inwall installing groove 120, as in figures 4 and 5.Although not shown in figure 6, similar projection can be formed on the diapire of fluid conduit systems 200.
In the embodiment shown in fig. 6, projection 242,244,246 is elongate on the length direction of fluid conduit systems 200.Further, the leading edge of projection and trailing edge are in diminishing gradually.The elongate of being out of shape gradually of projection 242,244,246 is designed to facilitate fluid conduit systems 200 to slide in the installation groove 120 of inner turbine 110.
Fig. 7 shows the alternate embodiment of fluid conduit systems 200.In such an embodiment, the spine 248 that the outer wall that projection is formed as being centered around fluid conduit systems 200 extends.Although illustrate only single spine 248 in the figure 7, multiple spine 248 will locate along the length of fluid conduit systems 200.Spine 248 extends along the direction substantially identical along the direction of the flows outside of fluid conduit systems 200 with temperature control fluid.Therefore, spine 248 can not hinder this fluid stream, and can be used for guiding this temperature control fluid stream.
Fig. 8 shows another embodiment of the fluid conduit systems 300 be arranged in the installation groove 320 of inner turbine 110.In this embodiment, on the outer wall of fluid conduit systems 300, projection is not formed.As a result, the diapire 310 of fluid conduit systems 300 directly can contact with the inwall installing groove 320 with side outer wall.
When the embodiment of the fluid conduit systems shown in Fig. 8 is used in inner turbine 110, the stream that enters be used to temperature control fluid is delivered in inner passage 320 by the one or more pipelines being connected to the inner passage 320 of fluid conduit systems 300, and the one or more pipelines being connected to inner passage 320 will remove temperature control fluid stream.For being delivered into the pipeline that becomes a mandarin and the pipeline for regaining output stream will be positioned in around fluid conduit systems to make predetermined flow pattern through the inner passage 320 of fluid conduit systems 300.
Fluid conduit systems as above can be easily mounted to inner turbine to help to control the gap between the tip of turbine bucket and surrounding shield.When each section of inner turbine is separated so that when carrying out maintenance and repair, this fluid conduit systems can be easily inserted into be installed accordingly in groove and removes from this installation groove.And, the above-mentioned installation groove for fluid conduit systems can be machined into existing inner turbine, thus make this fluid conduit systems to be attached to can realize the gap between the tip of ACTIVE CONTROL turbine bucket and surrounding shield without any mode existing turbo machine on become possibility.
Although combined and be considered to the most practical at present and most preferred embodiment describes the utility model, be to be understood that, the utility model is not limited to the disclosed embodiments, and on the contrary, it is intended to cover various modification included in the spirit and scope of the appended claims and equivalent device.
Claims (19)
1., for a housing for turbogenerator, described housing comprises:
Multiple arc housing parts, described multiple arc shell body is configured to the inner casing being attached to one another to be formed general cylindrical, and wherein, each arc shell body comprises:
At least one guard shield hook portion, at least one guard shield hook portion described extends in circumferential direction along the inner side of described arc shell body, and
At least one installs groove, and at least one installation groove described extends in circumferential direction along described arc shell body, and wherein, at least one installation groove each is orientated as adjacent with at least one guard shield hook portion described; And
At least one conduit, described conduit has at least one inner passage for temperature control fluid, and each conduit is arranged at least one one of installing in groove described, and wherein, at least one catheter configurations described is installed in groove for being inserted into.
2. housing according to claim 1, is characterized in that, the radially inner side of at least one installation groove described has the width larger than the radial outside of at least one installation groove described.
3. housing according to claim 1, is characterized in that, described at least one installation groove each is positioned on the radial outside of at least one guard shield hook portion described.
4. housing according to claim 1, is characterized in that, the described inner passage of at least one conduit each extends along the length direction of described conduit.
5. housing according to claim 4, is characterized in that, at least one conduit each comprises the multiple holes extending to the outside of described conduit from described inner passage.
6. housing according to claim 5, is characterized in that, described multiple hole be formed at described conduit towards on the side of at least one guard shield hook portion described.
7. housing according to claim 5, is characterized in that, at least one conduit each comprise be formed at described conduit outer surface on multiple projections.
8. housing according to claim 7, is characterized in that, described multiple pop-up structure is the outer surface of described conduit and at least one internal surface installing groove described are separated.
9. housing according to claim 1, is characterized in that, at least one conduit each comprises:
First inner passage, described first inner passage extends along the length direction of described conduit;
Second inner passage, described second inner passage extends along the length direction of described conduit, and described first inner passage is positioned on the radial outside of described second inner passage; With
The radial multiple holes extended, described hole extends between described first inner passage and described second inner passage.
10. housing according to claim 1, is characterized in that, at least one conduit each also comprises at least one and enters hole, described in enter hole and be configured to allowable temperature and control fluid stream and flow in described inner passage.
11. housings according to claim 1, is characterized in that, at least one catheter configurations described is that circumferentially direction is slipped in installation groove.
12. 1 kinds of temperature control fluid conduits, described temperature control fluid catheter configurations is on the arcuate section of the inner casing of the turbine section being installed to turbogenerator, and described temperature control fluid conduit comprises:
Elongate arcuate main body, described elongate arcuate main body has the inner passage for temperature control fluid; And
At least one enters hole, described at least one enter hole and be configured to allowable temperature and control flow of fluid enter in described inner passage.
13. temperature control fluid conduits according to claim 12, is characterized in that, the radially inner side of described elongate body has the width larger than the radial outside of described elongate body.
14. temperature control fluid conduits according to claim 12, is characterized in that, described at least one enter hole and be positioned on the radial outside of described elongate arcuate main body.
15. temperature control fluid conduits according to claim 12, is characterized in that, described inner passage extends along the length direction of described elongated arcuate main body.
16. temperature control fluid conduits according to claim 15, is characterized in that, described multiple hole extends to the outside of described main body from inner passage by described elongate arcuate main body.
17. temperature control fluid conduits according to claim 16, is characterized in that, described multiple hole is formed at the radially inner side of described elongate arcuate main body.
18. temperature control fluid conduits according to claim 16, is characterized in that, described multiple projection is formed at least one outer surface of described elongate arcuate main body.
19. temperature control fluid conduits according to claim 12, it is characterized in that, described inner passage comprises:
First inner passage, described first inner passage extends along the length direction of described elongate arcuate main body;
Second inner passage, described second inner passage extends along the length direction of described elongate arcuate main body, and described first inner passage is positioned on the radial outside of described second inner passage; And
The radial multiple holes extended, described hole extends between described first inner passage and described second inner passage.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/828081 | 2013-03-14 | ||
| US13/828,081 US20140271154A1 (en) | 2013-03-14 | 2013-03-14 | Casing for turbine engine having a cooling unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204283516U true CN204283516U (en) | 2015-04-22 |
Family
ID=51419070
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420119083.1U Expired - Lifetime CN204283516U (en) | 2013-03-14 | 2014-03-14 | For housing and the temperature control fluid conduit thereof of turbogenerator |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20140271154A1 (en) |
| JP (1) | JP2014177937A (en) |
| CN (1) | CN204283516U (en) |
| CH (1) | CH707767A8 (en) |
| DE (1) | DE102014103009A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106224021A (en) * | 2015-05-11 | 2016-12-14 | 通用电气公司 | There is the turbine shroud bay assemblies of expansion pipe |
| CN108266275A (en) * | 2016-12-30 | 2018-07-10 | 安萨尔多能源英国知识产权有限公司 | Gas turbine with secondary air system |
| CN108506053A (en) * | 2017-02-28 | 2018-09-07 | 和谐工业有限责任公司 | Fan guard and mounting bracket for oil cooler |
| CN110494632A (en) * | 2017-03-30 | 2019-11-22 | 通用电气公司 | The machanical fastener of increasing material manufacturing with cooling channels |
| CN114026314A (en) * | 2019-07-04 | 2022-02-08 | 赛峰飞机发动机公司 | Improved aircraft turbine shroud cooling arrangement |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3023600B1 (en) * | 2014-11-24 | 2018-01-03 | Ansaldo Energia IP UK Limited | Engine casing element |
| GB201521937D0 (en) * | 2015-12-14 | 2016-01-27 | Rolls Royce Plc | Gas turbine engine turbine cooling system |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4513567A (en) * | 1981-11-02 | 1985-04-30 | United Technologies Corporation | Gas turbine engine active clearance control |
| FR2540939A1 (en) * | 1983-02-10 | 1984-08-17 | Snecma | SEALING RING FOR A TURBINE ROTOR OF A TURBOMACHINE AND TURBOMACHINE INSTALLATION PROVIDED WITH SUCH RINGS |
| US5116199A (en) * | 1990-12-20 | 1992-05-26 | General Electric Company | Blade tip clearance control apparatus using shroud segment annular support ring thermal expansion |
| US5281085A (en) * | 1990-12-21 | 1994-01-25 | General Electric Company | Clearance control system for separately expanding or contracting individual portions of an annular shroud |
| US5273396A (en) * | 1992-06-22 | 1993-12-28 | General Electric Company | Arrangement for defining improved cooling airflow supply path through clearance control ring and shroud |
| FR2766517B1 (en) * | 1997-07-24 | 1999-09-03 | Snecma | DEVICE FOR VENTILATION OF A TURBOMACHINE RING |
| US6702550B2 (en) * | 2002-01-16 | 2004-03-09 | General Electric Company | Turbine shroud segment and shroud assembly |
| FR2852053B1 (en) * | 2003-03-06 | 2007-12-28 | Snecma Moteurs | HIGH PRESSURE TURBINE FOR TURBOMACHINE |
| US6997673B2 (en) * | 2003-12-11 | 2006-02-14 | Honeywell International, Inc. | Gas turbine high temperature turbine blade outer air seal assembly |
| US7165937B2 (en) * | 2004-12-06 | 2007-01-23 | General Electric Company | Methods and apparatus for maintaining rotor assembly tip clearances |
| US20070009349A1 (en) * | 2005-07-11 | 2007-01-11 | General Electric Company | Impingement box for gas turbine shroud |
| FR2907841B1 (en) * | 2006-10-30 | 2011-04-15 | Snecma | TURBINE MACHINE RING SECTOR |
| GB0703827D0 (en) * | 2007-02-28 | 2007-04-11 | Rolls Royce Plc | Rotor seal segment |
| US20090053042A1 (en) * | 2007-08-22 | 2009-02-26 | General Electric Company | Method and apparatus for clearance control of turbine blade tip |
-
2013
- 2013-03-14 US US13/828,081 patent/US20140271154A1/en not_active Abandoned
-
2014
- 2014-03-06 DE DE102014103009.5A patent/DE102014103009A1/en not_active Withdrawn
- 2014-03-10 JP JP2014045805A patent/JP2014177937A/en active Pending
- 2014-03-10 CH CH00354/14A patent/CH707767A8/en not_active Application Discontinuation
- 2014-03-14 CN CN201420119083.1U patent/CN204283516U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106224021A (en) * | 2015-05-11 | 2016-12-14 | 通用电气公司 | There is the turbine shroud bay assemblies of expansion pipe |
| US9915153B2 (en) | 2015-05-11 | 2018-03-13 | General Electric Company | Turbine shroud segment assembly with expansion joints |
| CN108266275A (en) * | 2016-12-30 | 2018-07-10 | 安萨尔多能源英国知识产权有限公司 | Gas turbine with secondary air system |
| CN108506053A (en) * | 2017-02-28 | 2018-09-07 | 和谐工业有限责任公司 | Fan guard and mounting bracket for oil cooler |
| US11466700B2 (en) | 2017-02-28 | 2022-10-11 | Unison Industries, Llc | Fan casing and mount bracket for oil cooler |
| CN110494632A (en) * | 2017-03-30 | 2019-11-22 | 通用电气公司 | The machanical fastener of increasing material manufacturing with cooling channels |
| CN114026314A (en) * | 2019-07-04 | 2022-02-08 | 赛峰飞机发动机公司 | Improved aircraft turbine shroud cooling arrangement |
Also Published As
| Publication number | Publication date |
|---|---|
| US20140271154A1 (en) | 2014-09-18 |
| DE102014103009A1 (en) | 2014-09-18 |
| CH707767A8 (en) | 2015-01-15 |
| CH707767A2 (en) | 2014-09-15 |
| JP2014177937A (en) | 2014-09-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204283516U (en) | For housing and the temperature control fluid conduit thereof of turbogenerator | |
| CN101333937B (en) | Device for cooling the cavities of a turbomachine rotor disc | |
| EP2236747B1 (en) | Systems, methods, and apparatus for passive purge flow control in a turbine | |
| EP3092373B1 (en) | System comprising a meter plate and a blade outer air seal | |
| CN101230800B (en) | Holding device and system for turbine rotor | |
| EP1630385B1 (en) | Method and apparatus for maintaining rotor assembly tip clearances | |
| JP6126438B2 (en) | Gas turbine clearance control system | |
| EP2886801B1 (en) | Seal system for a gas turbine and corresponding gas turbine | |
| CN102046926B (en) | High pressure turbine of a turbomachine with improved assembly of the mobile blade radial clearance control box | |
| JP6334123B2 (en) | Rotor blade and rotor blade cooling method | |
| JP6888907B2 (en) | gas turbine | |
| EP2539546B1 (en) | Turbine shroud support thermal shield | |
| CN105402028A (en) | Rib plate eddy flow control structure, rotation disk cavity system and gas turbine | |
| EP3569825B1 (en) | Electric heating for turbomachinery clearance control | |
| EP2924238B1 (en) | Turbine sections of gas turbine engines with dual use of cooling air | |
| JP2008088978A (en) | Stator/rotor assembly with surface characteristic for confining gas flow, and related process | |
| EP3168427B1 (en) | Gas turbine engine stage provided with a labyrinth seal | |
| EP2505781A2 (en) | Stator-rotor assemblies with features for enhanced containment of gas flow, and related processes | |
| JP2010084762A (en) | Method and apparatus for matching thermal mass and stiffness of bolted split rings | |
| US10329940B2 (en) | Method and system for passive clearance control in a gas turbine engine | |
| JP2013151936A (en) | Retrofittable interstage angled seal | |
| US10655481B2 (en) | Cover plate for rotor assembly of a gas turbine engine | |
| US20060285971A1 (en) | Shroud tip clearance control ring | |
| EP2378088A2 (en) | Turbine with a double casing | |
| JP2015525853A (en) | Turbine blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231227 Address after: Swiss Baden Patentee after: GENERAL ELECTRIC CO. LTD. Address before: New York, United States Patentee before: General Electric Co. |
|
| TR01 | Transfer of patent right | ||
| CX01 | Expiry of patent term |
Granted publication date: 20150422 |
|
| CX01 | Expiry of patent term |