CN103485844A - Method and apparatus for mitigating out of roundness effects at turbine - Google Patents
Method and apparatus for mitigating out of roundness effects at turbine Download PDFInfo
- Publication number
- CN103485844A CN103485844A CN201310230832.8A CN201310230832A CN103485844A CN 103485844 A CN103485844 A CN 103485844A CN 201310230832 A CN201310230832 A CN 201310230832A CN 103485844 A CN103485844 A CN 103485844A
- Authority
- CN
- China
- Prior art keywords
- turbine casing
- ring insert
- turbo machine
- interior turbine
- described interior
- 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.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 18
- 230000000694 effects Effects 0.000 title abstract description 7
- 230000000116 mitigating effect Effects 0.000 title abstract 2
- 238000012546 transfer Methods 0.000 claims abstract description 8
- 230000008646 thermal stress Effects 0.000 claims description 4
- 238000005259 measurement Methods 0.000 description 4
- 230000002123 temporal effect Effects 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000011218 segmentation Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Images
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
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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
- 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 for reducing equipment and the method for losing the circle impact on the turbo machine inner casing at combustion gas turbine.
Background technique
Some turbine partial design comprise: interior turbine casing, and described interior turbine casing provides stream to pass described turbo machine for working gas; And outer turbine casing, described outer turbine casing is around described interior turbine casing.In general, the rotor with a plurality of blades is arranged in described interior turbine casing, and rotates because described working gas passes described turbo machine.Turbine efficiency and electrical production are determined in interval between described interior turbine casing and described a plurality of turbine bucket, and may be subject to described interior turbine casing generation circular cross-section deviation effects, and this deviation is also referred to as losing circle.Due to being connected between interior turbine casing and outer turbine casing, the load that various operational stresses induced cause usually from described turbine casing be delivered to described interior turbine casing and cause described interior turbine casing distortion, this distortion is a kind of situation of losing circle that is called.Therefore, wish to design the turbine casing that reduces the impact of mistake circle.The invention provides a kind of minimizing loads between outer turbine casing and interior turbine casing and to transmit the method and apparatus that reduces to lose round effect.
Summary of the invention
According on the one hand, the invention provides a kind of method of losing the circle impact that reduces on turbo machine, described method comprises: the interior turbine casing that described turbo machine is provided in the outer turbine casing of described turbo machine; And use ring insert that described interior turbine casing is connected to described outer turbine casing, described ring insert is divided into a plurality of ring insert sections, in order to reduce from described turbine casing to the load transfer of described interior turbine casing, thereby slow down the mistake circle of described interior turbine casing.
According on the other hand, the invention provides a kind of turbo machine, described turbo machine comprises: outer turbine casing; Interior turbine casing; And ring insert, described ring insert is configured for described interior turbine casing is connected to described outer turbine casing, and is divided into a plurality of ring insert sections, in order to reduce from described turbine casing to the load transfer of described interior turbine casing.
These and other advantage and feature will be clearer from following description by reference to the accompanying drawings.
The accompanying drawing explanation
Claims in the present patent application file are pointed out in detail and have clearly been advocated the present invention.Can be well understood to above and other feature of the present invention and advantage by the detailed description below in conjunction with accompanying drawing, in the accompanying drawings:
Fig. 1 is illustrated in the side cross-sectional, view of the exemplary interior turbine casing of the turbogenerator in one embodiment of the present invention;
Fig. 2 illustrates the cross section of interior turbine casing shown in the Fig. 1 that comprises thrust ring;
Fig. 3 is illustrated in the sectional view of the exemplary shell sector in an exemplary embodiment; And
Figure 4 and 5 are illustrated in the plotting of the circumference of each temporal exemplary interior turbine casing of the present invention during exemplary turbo machine operation cycle.
Embodiment is introduced every embodiment of the present invention and advantage and feature by way of example with reference to accompanying drawing.
Embodiment
Fig. 1 is illustrated in the side cross-sectional, view of the exemplary interior turbine casing 100 of the combustion gas turbine in one embodiment of the present invention.Described exemplary interior turbine casing 100 provides hollow shell, and described hollow shell axis 102 along the longitudinal extends, and has entrance 104 and the outlet 106 on the second end of described longitudinal axis on the first end of described longitudinal axis.Described turbine casing is rotational symmetric around its longitudinal axis 102 haply.Rotor with a plurality of turbine bucket (not shown) is arranged in described interior turbine casing 100 along described longitudinal axis 102 haply.The working gas be expelled in described interior turbine casing 100 at entrance 104 places makes described turbine bucket displacement, thereby causes described turbine bucket rotation, causes thus described rotor generating.In every embodiment, described interior turbine casing 100 is comprised of two or more parts, and these parts are in this manual also referred to as the shell sector, and described part is combined together to form described interior turbine casing 100.Selected azimythal angle is crossed over around described longitudinal axis 102 substantially in exemplary shell sector.Two or more shell sectors are combined together on interface 110 via bolt 112.The shell sector coordinated provides Cooling Holes or the air passageways 114 through described interior turbine casing 100, air is provided to the nozzle (not shown) be assembled on described interior turbine casing.Described interior turbine casing is connected to described outer turbine casing at thrust ring 116 places of described interior turbine casing 100.Described interior turbine casing comprises thrust ring 116.
Fig. 2 illustrates the cross section of interior turbine casing shown in the Fig. 1 that comprises thrust ring 116.In every embodiment, described thrust ring 116 is segmentations.The thrust ring 116 of the segmentation of described interior turbine casing comprises groove 118, and ring insert can be inserted in described groove.Described ring insert is connected to described outer turbine casing by described interior turbine casing, in order to support described interior turbine casing.Described ring insert provides contact area between described interior turbine casing and described outer turbine casing.In an exemplary embodiment, described ring insert is divided into a plurality of ring insert sections, and described a plurality of ring insert sections are separated from one another, in order to provide gap along circumference between these sections.Therefore, described a plurality of ring insert section is less than 360 degree as the child's hair twisted in a knot-childhood of opposite side.
Fig. 3 is illustrated in analysing and observe of shell sector in an exemplary embodiment of the present invention.Exemplary interior turbine casing is comprised of four shell sectors, and described four shell sectors form 1/4th of described interior turbine casing 300 separately.What illustrate is exemplary shell sector 315.What illustrate is that ring insert section 302 is on described exemplary shell sector 315.Along sector, 315 circumference extends to second orientation position 306 from first orientation position 304 to described ring insert section 302, thereby as the opposite side at angle 320.In an embodiment, angle 320 is less than 90 degree.In another embodiment, angle 320 is approximately between 15 degree and 85 degree.In another embodiment, angle 320 about 30 degree with approximately 70 spend between.In an exemplary embodiment, described ring insert section 302 evenly is arranged on first of shell sector 315 and coordinates interface 310 to coordinate between interface 312 with second, make like this between described first orientation position 304 and described the first cooperation interface 310 apart from in described second orientation position 306, with described second, coordinate between interface 312 apart from identical haply.Therefore, the contact area between described outer turbine casing and described interior turbine casing is less than 360 degree.This contact area reduced makes the load transfer zone between described outer turbine casing and described interior turbine casing reduce.In alternate embodiment, described exemplary shell sector 315 can comprise two or more ring segments that are spaced apart from each other.
On the one hand, the length of described ring insert section can be used processor to be determined.Example processor can be simulated, in order to determine the length of described ring insert section when the mistake circle of described interior turbine casing meets selected standard.Described processor can be simulated the various operation cycle of turbo machine, and determine described cycle period described interior turbine casing at each temporal mistake circle.
Perhaps, can construct and operate the turbo machine with example annular inserting member section.Can be by sensor setting on each position of described interior turbine casing, and the mistake that can observe in described turbo machine operation described interior turbine casing during by various operation cycle be justified.Therefore, can determine ring insert segment length and interval with respect to reducing the effect of losing the circle impact by observing various ring insert segment length.
On the one hand, be chosen in the length of ring segment when mistake is round meets selected standard.In every embodiment, the mistake circle that makes described interior turbine casing in the length of described ring segment, in the time can accepting in Tolerance level, is selected suitable section.In another embodiment, described selected standard can be the mistake circle tolerance on selected time frame.
Fig. 4 is illustrated in the plotting at the circumference of each temporal exemplary interior turbine casing of the present invention of exemplary turbo machine operation period.The plotting output of Fig. 4 is from the analytical model of the radial displacement measurement aspect of described circumference, and this measurement is carried out once at approximately every 5 degree around described circumference.Perhaps, can use substantially approximately 10 sensors of placing around described circumference to obtain plotting, so that the shell that test configuration becomes, obtain radial measurement on each time, described each time by reference number 401(latter 1654 seconds of startup), 402(2374 second), 403(2874 second), 404(4174 second), 405(100000 second) and 406(100967 second) indication.Fig. 5 is illustrated in the plotting of the circumference of the exemplary interior turbine casing of temporal Fig. 4 a little later.Obtain radial measurement on each time, described each time is by 501(105618 second), 502(114400 second), 503(116055 second), 504(116271 second), 505(116775 second) and 506(214400 second) indication.Described exemplary interior turbine casing moves substantially by one or more increases and reduces the circulation that electric power is exported.The described circumference of described interior turbine casing increases and reduces by cooling by being heated substantially.Early the time (being the time 401) illustrates and has the interior turbine casing of circular cross-section haply.With the described turbo machine in height output level (being the time 404,405 and 406) operation, will illustrate.Specifically, the time 404 is illustrated on high output level the interior turbine casing with larger mistake circle effect.The time 503 and 504 that described circumference is depicted as to operation cycle is reduced to low output level.The mistake circle of various degree will illustrate.The time 506 that described circumference is depicted as to operation cycle rises to high output level again.As shown in Figure 5, on the time 506, the mistake of described shell circle degree is relatively light.When described mistake circle effect, in the time can accepting in tolerance, the operator can select ring segment to use in turbo machine.
Therefore, on the one hand, the invention provides a kind of method of losing the circle impact that reduces on turbo machine, described method comprises: the interior turbine casing that described turbo machine is provided in the outer turbine casing of described turbo machine; And use ring insert that described interior turbine casing is connected to described outer turbine casing, described ring insert is divided into a plurality of ring insert sections, in order to reduce from described turbine casing to the load transfer of described interior turbine casing, thereby slow down the mistake circle of described interior turbine casing.In an embodiment, described a plurality of ring insert sections comprise four ring insert sections.The opposite side at the angle that the longitudinal axis of the described interior turbine casing of at least one ring insert Duan Weicong in described ring insert section is measured, described angle is selected from following wherein one: (i) be less than 90 degree; (ii) about 15 degree with approximately 85 spend between; And (iii) about 30 degree with approximately 70 spend between.Processor can be used for determining the length and location of described ring insert section when the mistake circle of described interior turbine casing meets selected standard.The length of ring insert section is through selecting, in order to reduce the load paths between described outer turbine casing and described interior turbine casing.In every embodiment, described load is from the thermal stress on described outer turbine casing.Described ring insert section is arranged on the thrust ring of described interior turbine casing, around the circumference of described interior turbine casing on equidistant position.In every embodiment, described interior turbine casing consists of shell sector, at least two orientation.
A kind of turbo machine comprises: outer turbine casing; Interior turbine casing; And ring insert, described ring insert is configured for described interior turbine casing is connected to described outer turbine casing, and is divided into a plurality of ring insert sections, in order to reduce from described turbine casing to the load transfer of described interior turbine casing.In an exemplary embodiment, described ring insert is divided into four ring insert sections.At least one described ring insert section is selected from following wherein one as the angle of its opposite side: (i) be less than 90 degree; (ii) approximately between 15 degree and 85 degree; And (iii) about 30 degree with approximately 70 spend between.The processor of program that moves the model of described turbo machine can be used for determining the length of described ring insert.The described length of described ring insert section is substantially through selecting, in order to reduce the load paths between described outer turbine casing and described interior turbine casing.Described load relates generally to the thermal stress on described outer turbine casing.In an exemplary embodiment, described ring insert section is spaced apart around the even circumferential of described interior turbine casing.In every embodiment, described interior turbine casing consists of at least two shell sectors of extending on selected azimythal angle.
Although the present invention only is described in detail in conjunction with the embodiment of limited quantity, should be easy to understand, the present invention is not limited to this type of disclosed embodiment.On the contrary, the present invention can modify, in order to be incorporated to any amount of variation, change, replacement or the equivalent arrangements of not describing before this but conforming to the spirit and scope of the present invention.In addition, although every embodiment of the present invention is described, be appreciated that All aspects of of the present invention can only include some in described embodiment.Therefore, the present invention should not be considered limited to aforementioned description, and only is limited to the scope of appended claims.
Claims (16)
1. one kind is lost for reducing turbo machine the method that circle affects, and comprising:
The interior turbine casing of described turbo machine is arranged in the outer turbine casing of described turbo machine; And
Use ring insert that described interior turbine casing is connected to described outer turbine casing, described ring insert is divided into a plurality of ring insert sections, in order to reduce from described turbine casing to the load transfer of described interior turbine casing, thereby reduce the mistake circularity of described interior turbine casing.
2. the method for claim 1, wherein said a plurality of ring insert sections further comprise four ring insert sections.
3. method as claimed in claim 2, the opposite side at the angle that wherein longitudinal axis of the described interior turbine casing of at least one described ring insert Duan Weicong is measured, described angle be selected from following one of them: (i) be less than 90 degree; (ii) about 15 degree with approximately 85 spend between; And (iii) about 30 degree with approximately 70 spend between.
4. the method for claim 1, further comprise the length of determining described ring insert section when the mistake circularity of described interior turbine casing meets selected standard with processor.
5. the method for claim 1, wherein the length of ring insert section is through selecting, in order to reduce the load paths between described outer turbine casing and described interior turbine casing.
6. the method for claim 1, wherein said load is to be caused by the thermal stress on described outer turbine casing.
7. the method for claim 1, wherein said ring insert section is arranged on the thrust ring of described interior turbine casing equidistantly around the circumference of described interior turbine casing.
8. the method for claim 1, wherein said interior turbine casing consists of shell sector, at least two orientation.
9. a turbo machine comprises:
Outer turbine casing;
Interior turbine casing; And
Ring insert, described ring insert is configured for described interior turbine casing is connected to described outer turbine casing, and is divided into a plurality of ring insert sections, in order to reduce from described turbine casing to the load transfer of described interior turbine casing.
10. turbo machine as claimed in claim 9, wherein said ring insert is divided into four ring insert sections.
11. turbo machine as claimed in claim 10, wherein at least one described ring insert section is selected from following wherein one as the angle of its opposite side: (i) be less than 90 degree; (ii) approximately between 15 degree and 85 degree; And (iii) about 30 degree with approximately 70 spend between.
12. turbo machine as claimed in claim 9, wherein determine the length of described ring insert section with the processor of model program of the described turbo machine of operation.
13. turbo machine as claimed in claim 9, the length of wherein said ring insert section is through selecting, in order to reduce the load paths between described outer turbine casing and described interior turbine casing.
14. turbo machine as claimed in claim 9, wherein said load relates to the thermal stress on described outer turbine casing.
15. turbo machine as claimed in claim 9, wherein said ring insert section separates around the even circumferential of described interior turbine casing.
16. turbo machine as claimed in claim 9, wherein said interior turbine casing consists of at least two shell sectors of extending on selected azimythal angle.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/493435 | 2012-06-11 | ||
| US13/493,435 US20130330187A1 (en) | 2012-06-11 | 2012-06-11 | Method and apparatus for mitigating out of roundness effects at a turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103485844A true CN103485844A (en) | 2014-01-01 |
| CN103485844B 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 (5)
| 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 |
| US20070041833A1 (en) * | 2005-08-18 | 2007-02-22 | General Electric Company | Fast temporary joint bolting system for turbine shells |
| 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 (6)
| 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 | |
| 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 (5)
| 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 |
| US20070041833A1 (en) * | 2005-08-18 | 2007-02-22 | General Electric Company | Fast temporary joint bolting system for turbine shells |
| 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 |
|---|---|
| CN103485844B (en) | 2017-04-12 |
| EP2674580A1 (en) | 2013-12-18 |
| US20130330187A1 (en) | 2013-12-12 |
| JP2013256945A (en) | 2013-12-26 |
| RU2013126491A (en) | 2014-12-20 |
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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. |
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