CN103485844B - Turbine and method for mitigating out of roundness effects of turbine - Google Patents
Turbine and method for mitigating out of roundness effects of turbine Download PDFInfo
- Publication number
- CN103485844B CN103485844B CN201310230832.8A CN201310230832A CN103485844B CN 103485844 B CN103485844 B CN 103485844B CN 201310230832 A CN201310230832 A CN 201310230832A CN 103485844 B CN103485844 B CN 103485844B
- Authority
- CN
- China
- Prior art keywords
- turbine casing
- interior
- ring insert
- degree
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 17
- 230000000694 effects Effects 0.000 title abstract description 7
- 230000000116 mitigating effect Effects 0.000 title abstract 2
- 238000005259 measurement Methods 0.000 claims description 6
- 230000008646 thermal stress Effects 0.000 claims description 4
- 238000003780 insertion Methods 0.000 claims 1
- 230000037431 insertion Effects 0.000 claims 1
- 238000012546 transfer Methods 0.000 abstract description 2
- 230000004087 circulation Effects 0.000 description 7
- 239000007789 gas Substances 0.000 description 3
- 230000002123 temporal effect Effects 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000011218 segmentation Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 238000012360 testing method Methods 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
-
- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49229—Prime mover or fluid pump making
- Y10T29/49231—I.C. [internal combustion] engine making
- Y10T29/49234—Rotary or radial engine making
Landscapes
- 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
A turbine and a method of mitigating out-of-roundness effects at a turbine are disclosed. An inner turbine shell and an outer turbine shell of the turbine are provided. The inner turbine shell is coupled to the outer turbine shell by using a ring insert. The ring insert is segmented into a plurality of ring insert segments (302) that reduce a transfer of load from the outer turbine shell to the inner turbine shell to mitigate out-of-roundness of the inner turbine shell.
Description
Technical field
The present invention relates to a kind of apparatus and method for reducing mistake circle impact in the inner turbine of combustion gas turbine.
Background technology
Some turbine portion designs include：Interior turbine casing, the interior turbine casing provides stream so that working gas is worn
Cross the turbine；And outer turbine casing, the outer turbine casing is around the interior turbine casing.In general, with many
The rotor of individual blade is arranged in the interior turbine casing, and is rotated because the working gas passes through the turbine.
Interval between the interior turbine casing and the plurality of turbine blade determines turbine efficiency and power generation, and may
Circular cross-section deviation effects are produced by the interior turbine casing, this deviation also referred to as loses circle.Due to interior turbine casing with it is outer
Connection between turbine casing, the load that various operational stresses induceds are caused generally is delivered to the interior turbine from the outer turbine casing
Casing and cause the interior turbine casing distortion, this distortion is a kind of situation for referred to as losing circle.Therefore, it is intended that designing drop
It is low to lose the turbine casing that circle affects.The present invention provides a kind of reduction load and transmits to come between outer turbine casing and interior turbine casing
Reduce the method and apparatus for losing circle effect.
The content of the invention
According to one side, the present invention provides a kind of reduction on turbine and loses the method that circle affects, and methods described includes：
The interior turbine casing of the turbine is provided in the outer turbine casing of the turbine；And will be described interior using ring insert
Turbine casing is connected to the outer turbine casing, and the ring insert is divided into multiple ring insert sections, to reduce from institute
State outer turbine casing to transmit to the load of the interior turbine casing, so as to the mistake for slowing down the interior turbine casing is justified.
According on the other hand, the present invention provides a kind of turbine, and the turbine includes：Outer turbine casing；Interior turbine
Shell；And ring insert, the ring insert is configured for for the interior turbine casing being connected to the outer turbine
Shell, and it is divided into multiple ring insert sections, pass to reduce from the outer turbine casing to the load of the interior turbine casing
Pass.
These and other advantages and features will be clearer from the following description for combine accompanying drawing.
Description of the drawings
The above and other feature and excellent of the present invention can be understood that by the detailed description below in conjunction with accompanying drawing
Point, in the accompanying drawings：
Fig. 1 illustrates the side cross-sectional of the exemplary interior turbine casing of the turbogenerator in one embodiment of the present invention
Figure；
The section of interior turbine casing shown in Fig. 1 that Fig. 2 illustrates including thrust ring；
Fig. 3 illustrates the sectional view of the exemplary shell sector in an exemplary embodiment；And
Figure 4 and 5 illustrate the exemplary interior turbine of each temporal present invention during exemplary turbine operation circulation
The plotting of the circumference of casing.
Specific embodiment refer to the attached drawing introduces by way of example every embodiment and advantages and features of the present invention.
Specific embodiment
Fig. 1 illustrates the side-looking of the exemplary interior turbine casing 100 of the combustion gas turbine in one embodiment of the present invention
Sectional view.The exemplary interior turbine casing 100 provides hollow shell, and the hollow shell extends along longitudinal axis 102, and
And the outlet 106 with the entrance 104 in the first end of the longitudinal axis and on the second end of the longitudinal axis.Institute
It is generally rotational symmetric around its longitudinal axis 102 to state turbine casing.Turning with multiple turbine blade (not shown)
Son is arranged in the interior turbine casing 100 generally along the longitudinal axis 102.It is expelled at entrance 104 in described
Working gas in turbine casing 100 causes the turbine blade displacement, so as to cause the turbine blade to rotate, thus
Cause the rotor rotary electrification.In every embodiment, the interior turbine casing 100 is made up of two or more parts,
These parts are also referred to as in this manual shell sector, described to be fit partially within together to constitute the interior turbine casing 100.Show
Selected azimuth is crossed in example property shell sector generally surround the longitudinal axis 102.Two or more shell sectors are via bolt
112 are combined together on interface 110.The shell sector of cooperation provides the Cooling Holes or air through the interior turbine casing 100
Passage 114, air is provided to the nozzle (not shown) being assembled on the interior turbine casing.The interior turbine casing is in institute
State and the outer turbine casing is connected at the thrust ring 116 of interior turbine casing 100.The interior turbine casing includes thrust ring 116.
The section of interior turbine casing shown in Fig. 1 that Fig. 2 illustrates including thrust ring 116.In every embodiment, the thrust
Ring 116 is segmentation.The thrust ring 116 of the segmentation of the interior turbine casing includes groove 118, and ring insert is inserted into institute
In stating groove.The interior turbine casing is connected to the outer turbine casing by the ring insert, to support the interior turbine
Casing.The ring insert provides contact area between the interior turbine casing and the outer turbine casing.Show at one
In example property embodiment, the ring insert is divided into multiple ring insert sections, and the plurality of ring insert section is separated
Open, circumferentially to provide gap between these sections.Therefore, the plurality of ring insert section is little as the child's hair twisted in a knot-childhood of opposite side
In 360 degree.
Fig. 3 illustrates the section view of the shell sector in an exemplary embodiment of the present invention.Exemplary interior turbine casing by
Four shell sector compositions, four shell sectors each constitute a quarter of the interior turbine casing 300.It is illustrated that example
Property shell sector 315.It is illustrated that ring insert section 302 on the exemplary shell sector 315.The ring insert section
302 extend to second orientation position 306 along the circumference of sector 315 from first orientation position 304, so as to as the right of angle 320
Side.In one embodiment, angle 320 is less than 90 degree.In another embodiment, angle 320 is between about 15 degree and 85 degree.Again
In one embodiment, angle 320 is between about 30 degree and about 70 degree.In an exemplary embodiment, the ring insert section
302 are uniformly arranged between the first coordinates interface 310 of shell sector 315 and the second coordinates interface 312, so that described
The distance between one position of orientation 304 and described first coordinates interface 310 with the second orientation position 306 and described second
The distance between coordinates interface 312 is substantially the same.Therefore, connecing between the outer turbine casing and the interior turbine casing
Tactile region is less than 360 degree.The contact area of this reduction is caused between the outer turbine casing and the interior turbine casing
Load transfer region reduces.In alternative embodiments, the exemplary shell sector 315 can include be spaced apart from each other two or
More ring segments.
On the one hand, the length of the ring insert section can be determined using processor.Example processor can
To be simulated, to determine the length of the ring insert section when the mistake circle of the interior turbine casing meets selected standard
Degree.The processor can simulate the various operation circulations of turbine, and determine the interior turbine during the circulation
Shell is justified in each temporal mistake.
Or, can construct and operate the turbine with example annular insert section.Sensor can be arranged
On each position of the interior turbine casing, and institute can be observed when turbine operation is by various operation circulations
State the mistake circle of interior turbine casing.Therefore, it can lose what circle affected relative to reduction by observing various ring insert segment length
Effect is determining ring insert segment length and interval.
On the one hand, select in the length for losing ring segment when circle meets selected standard.In every embodiment, in the ring
When the length of shape section causes the mistake circle of the interior turbine casing in acceptable tolerance levels, suitable section is selected.At another
In embodiment, the selected standard can be the mistake circle tolerance in selected time frame.
Fig. 4 is illustrated during exemplary turbine is operated in each temporal exemplary interior turbine casing of the invention
The plotting of circumference.From the analysis model in terms of the radial displacement measurement of the circumference, this measurement surrounds institute for the plotting output of Fig. 4
State circumference is being carried out once every about 5 degree.Or, generally can be come using about 10 sensors placed around the circumference
Marked and drawed, so as to test configuration into shell, radial measurement is obtained on each time, described each time is by reference number
401 (upon actuation 1654 seconds), 402 (2374 seconds), 403 (2874 seconds), 404 (4174 seconds), 405 (100000 seconds) and 406
Indicate within (100967 seconds).Fig. 5 illustrates the plotting of the circumference of the exemplary interior turbine casings of the Fig. 4 on later time.At each
Between it is upper obtain radial measurement, described each time by 501 (105618 seconds), 502 (114400 seconds), 503 (116055 seconds), 504
(116271 seconds), 505 (116775 seconds) and 506 instructions in (214400 seconds).The exemplary interior turbine casing generally runs
By one or more increases and the circulation of reduction electric power output.The circumference of the interior turbine casing is generally through being heated
Increase and reduced by cooling down.More early time (i.e. time 401) illustrates the interior turbine casing with substantially circular section.With
Will illustrate in the turbine of height output level (i.e. time 404,405 and 406) operation.Specifically, the time 404 show
Go out and there is the larger interior turbine casing for losing circle effect in height output level.The circumference is shown as into the time of operation circulation
503 and 504 are reduced to relatively low output level.Various degrees of mistake circle will be illustrated.The circumference is shown as into operation circulation
Time 506 is lifted again to height output level.As shown in figure 5, on the time 506, the mistake circle degree of the shell is relatively light.When
When the mistake circle effect is in acceptable tolerance, operator can select ring segment to use in the turbine.
Therefore, on the one hand, the present invention provides a kind of reduction on turbine and loses the method that circle affects, methods described bag
Include：The interior turbine casing of the turbine is provided in the outer turbine casing of the turbine；And will using ring insert
The interior turbine casing is connected to the outer turbine casing, and the ring insert is divided into multiple ring insert sections, to subtract
It is few to transmit from the outer turbine casing to the load of the interior turbine casing, so as to the mistake for slowing down the interior turbine casing is justified.
In one embodiment, the plurality of ring insert section includes four ring insert sections.In the ring insert section extremely
The opposite side at the angle of the longitudinal axis measurement of interior turbine casing described in a few ring insert Duan Weicong, the angle selected from it is following its
In one：I () is less than 90 degree；(ii) between about 15 degree and about 85 degree；And (iii) is between about 30 degree and about 70 degree.Place
Reason device may be used to determine the interior turbine casing mistake circle meet selected standard when the ring insert section length and
Position.The length of ring insert section is passed through and selected, to reduce between the outer turbine casing and the interior turbine casing
Load paths.In every embodiment, thermal stress of the load on the outer turbine casing.The ring insert
Section is arranged on the thrust ring of the interior turbine casing, and the circumference around the interior turbine casing is on equidistant position.Each
In item embodiment, the interior turbine casing is made up of at least two orientation shell sectors.
A kind of turbine includes：Outer turbine casing；Interior turbine casing；And ring insert, the ring insert Jing
It is configured to for the interior turbine casing to be connected to the outer turbine casing, and is divided into multiple ring insert sections, to subtract
It is few to transmit from the outer turbine casing to the load of the interior turbine casing.In an exemplary embodiment, the annular is inserted
Enter part and be divided into four ring insert sections.Ring insert section described at least one is selected from following wherein one as the angle of its opposite side
：I () is less than 90 degree；(ii) between about 15 degree and 85 degree；And (iii) is between about 30 degree and about 70 degree.Operation is described
The processor of the program of the model of turbine may be used to determine the length of the ring insert.The ring insert section
The length substantially pass through selection, to reduce the load road between the outer turbine casing and the interior turbine casing
Footpath.The load relates generally to the thermal stress on the outer turbine casing.In an exemplary embodiment, the annular is inserted
The even circumferential for entering part section around the interior turbine casing is spaced apart.In every embodiment, the interior turbine casing is by institute
At least two shell sectors extended on azimuth are selected to constitute.
Although the present invention is only described in detail with reference to the embodiment of limited quantity, it should be readily understood that the present invention is not
It is limited to such disclosed embodiment.Conversely, the present invention can modify, so as to be incorporated to before this not description but with this
Any amount of change, change, replacement or equivalent arrangements that bright spirit and scope are consistent.Although additionally, the items of the present invention
Embodiment is described, it is to be understood that various aspects of the invention can only include some in the embodiment.Therefore,
The present invention shall not be considered limited to described above, and be limited only in the scope of the appended claims.
Claims (16)
1. it is a kind of to lose the method that circle affects for reducing turbine, including：
The interior turbine casing of the turbine is arranged in the outer turbine casing of the turbine, the interior turbine casing includes
Multiple shell sectors, the shell sector forms angle corresponding thereto and is connected at coordinates interface；And
The interior turbine casing is connected to into the outer turbine casing using multiple ring insert sections, to reduce from described outer
Turbine casing to the load of the interior turbine casing is transmitted, so as to reduce the mistake circularity of the interior turbine casing, one of ring
The shape insert Duan Yuyi shell sector is associated and the relative angle of the ring insert section is less than the shell sector institute
Relative angle.
2. the method for claim 1, wherein the plurality of ring insert section further includes four ring inserts
Section.
3. method as claimed in claim 2, interior turbine casing described in ring insert Duan Weicong described in wherein at least one
The opposite side at the angle of longitudinal axis measurement, the angle is selected from one of：I () is less than 90 degree；(ii) 15 degree with 85 degree it
Between；And (iii) is between 30 degree and 70 degree.
4. the method for claim 1, further includes to determine using processor when the mistake of the interior turbine casing is justified
Degree meets the length of ring insert section during selected standard.
5. the length of the method for claim 1, wherein ring insert section through selecting, to reduce in the outer whirlpool
Load paths between wheel casing and the interior turbine casing.
6. the method for claim 1, wherein the load transmitted is caused by the thermal stress on the outer turbine casing
's.
7. the method for claim 1, wherein the ring insert section is equidistant around the circumference of the interior turbine casing
It is liftoff to be arranged on the thrust ring of the interior turbine casing.
8. the method for claim 1, wherein the interior turbine casing is made up of at least two orientation shell sectors.
9. a kind of turbine, including：
Outer turbine casing；
Interior turbine casing, it is arranged in the outer turbine casing, and the interior turbine casing includes multiple shell sectors, the shell fan
Area forms angle corresponding thereto and is connected at coordinates interface；And
Multiple ring insert sections, the plurality of ring insert section is configured to that the interior turbine casing is connected to outside described
Turbine casing, transmits to reduce from the outer turbine casing to the load of the interior turbine casing, one of annular insertion
The part Duan Yuyi shell sector is associated and the relative angle of the ring insert section is relative less than the shell sector
Angle.
10. turbine as claimed in claim 9, wherein the plurality of ring insert section is divided into four ring insert sections.
11. turbines as claimed in claim 10, ring insert section described in wherein at least one is selected as the angle of its opposite side
From following one of which：I () is less than 90 degree；(ii) between 15 degree and 85 degree；And (iii) is between 30 degree and 70 degree.
12. turbines as claimed in claim 9, wherein being determined using the processor of the model program for running the turbine
The length of the ring insert section.
13. turbines as claimed in claim 9, wherein the length of the ring insert section is through selecting, to reduce
Load paths between the outer turbine casing and the interior turbine casing.
14. turbines as claimed in claim 9, wherein the load is related to the thermal stress on the outer turbine casing.
15. turbines as claimed in claim 9, wherein the ring insert section is equal around the circumference of the interior turbine casing
It is even to separate.
16. turbines as claimed in claim 9, wherein the interior turbine casing is by least two extended on selected azimuth
Individual shell sector is constituted.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/493,435 US20130330187A1 (en) | 2012-06-11 | 2012-06-11 | Method and apparatus for mitigating out of roundness effects at a turbine |
| US13/493435 | 2012-06-11 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103485844A CN103485844A (en) | 2014-01-01 |
| CN103485844B true CN103485844B (en) | 2017-04-12 |
Family
ID=48578858
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310230832.8A Active CN103485844B (en) | 2012-06-11 | 2013-06-09 | Turbine and method for mitigating out of roundness effects of turbine |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20130330187A1 (en) |
| EP (1) | EP2674580A1 (en) |
| JP (1) | JP2013256945A (en) |
| CN (1) | CN103485844B (en) |
| RU (1) | RU2013126491A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1076991A (en) * | 1991-11-05 | 1993-10-06 | 西门子公司 | The structure for heat displacement of gap seal of turbine |
| US6733233B2 (en) * | 2002-04-26 | 2004-05-11 | Pratt & Whitney Canada Corp. | Attachment of a ceramic shroud in a metal housing |
| CN101382087A (en) * | 2007-08-23 | 2009-03-11 | 通用电气公司 | Apparatus and method for reducing eccentricity and out-of-roundness in turbines |
| CN101892875A (en) * | 2009-05-22 | 2010-11-24 | 通用电气公司 | Active housing track control system and method |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB229627A (en) * | 1924-02-19 | 1926-01-14 | Jan Kieswetter | Improvements relating to turbine casings having transverse partitions and the like therein |
| US1873743A (en) * | 1930-11-15 | 1932-08-23 | Gen Electric | Elastic fluid turbine |
| US3892497A (en) * | 1974-05-14 | 1975-07-01 | Westinghouse Electric Corp | Axial flow turbine stationary blade and blade ring locking arrangement |
| CH592262A5 (en) * | 1975-07-04 | 1977-10-14 | Bbc Brown Boveri & Cie | |
| US7617602B2 (en) * | 2005-08-18 | 2009-11-17 | General Electric Company | Method of servicing a turbine |
| US7686575B2 (en) * | 2006-08-17 | 2010-03-30 | Siemens Energy, Inc. | Inner ring with independent thermal expansion for mounting gas turbine flow path components |
| US20110255959A1 (en) * | 2010-04-15 | 2011-10-20 | General Electric Company | Turbine alignment control system and method |
-
2012
- 2012-06-11 US US13/493,435 patent/US20130330187A1/en not_active Abandoned
-
2013
- 2013-06-06 JP JP2013119358A patent/JP2013256945A/en active Pending
- 2013-06-09 CN CN201310230832.8A patent/CN103485844B/en active Active
- 2013-06-10 RU RU2013126491/06A patent/RU2013126491A/en not_active Application Discontinuation
- 2013-06-10 EP EP13171178.0A patent/EP2674580A1/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1076991A (en) * | 1991-11-05 | 1993-10-06 | 西门子公司 | The structure for heat displacement of gap seal of turbine |
| US6733233B2 (en) * | 2002-04-26 | 2004-05-11 | Pratt & Whitney Canada Corp. | Attachment of a ceramic shroud in a metal housing |
| CN101382087A (en) * | 2007-08-23 | 2009-03-11 | 通用电气公司 | Apparatus and method for reducing eccentricity and out-of-roundness in turbines |
| CN101892875A (en) * | 2009-05-22 | 2010-11-24 | 通用电气公司 | Active housing track control system and method |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2013256945A (en) | 2013-12-26 |
| EP2674580A1 (en) | 2013-12-18 |
| US20130330187A1 (en) | 2013-12-12 |
| CN103485844A (en) | 2014-01-01 |
| RU2013126491A (en) | 2014-12-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP6335252B2 (en) | System and method for locating a probe in a gas turbine engine | |
| CN102444437B (en) | For the device of the turbine cylinder that aligns | |
| CN108252748A (en) | Turbogenerator induces device assembly | |
| AU2011250787B2 (en) | Gas turbine of the axial flow type | |
| CA3142741A1 (en) | Low hub-to-tip ratio fan for a turbofan gas turbine engine | |
| WO2009041460A1 (en) | Compressor | |
| EP2372105A3 (en) | Rotor blade tip clearance control | |
| CN102252642A (en) | Methods, systems and apparatus relating to tip clearance calculations in turbine engines | |
| US20220106907A1 (en) | Turbine engine with struts | |
| CN107829958A (en) | Aircraft fan with lower part span solidity | |
| RU2014114054A (en) | A CENTRIFUGAL COMPRESSOR WITH A WEAR MEASUREMENT MARKER AND A WEAR MONITORING METHOD USING THIS MARKER | |
| EP2803820A3 (en) | Impingement-cooled integral turbine rotor | |
| KR20110050738A (en) | Gas turbine | |
| CN104279008B (en) | The stator vane sector with double fixing devices of axial flow turbo-machine | |
| GB2498256A (en) | Method and Apparatus for Obtaining Discrete Axial Clearance Data Using Radial Clearance Sensors | |
| CN102597426A (en) | Rotor of a turbomachine | |
| RU2562928C2 (en) | Determination of impeller machine vaned rotor diameter | |
| BR102016027237A2 (en) | ENGINE COMPONENT FOR GAS TURBINE ENGINE | |
| CN103485844B (en) | Turbine and method for mitigating out of roundness effects of turbine | |
| CN104727856B (en) | The method of turbine vane and turbine vane for cooling combustion turbine engine | |
| CN108339941B (en) | Investment casting core, method of casting airfoil, and turbine blade assembly | |
| EP3018358A1 (en) | Centrifugal compressor apparatus | |
| CN109632276A (en) | One kind subtracting whirlpool device experimental rig | |
| CN107762564A (en) | The airfoil for turbogenerator with porous flank | |
| US20180223672A1 (en) | Investment casting core |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20240105 Address after: Swiss Baden Patentee after: GENERAL ELECTRIC CO. LTD. Address before: New York, United States Patentee before: General Electric Co. |