CN104564174A - Elastic sealing structure for turbine fixed blades of gas turbine - Google Patents
Elastic sealing structure for turbine fixed blades of gas turbine Download PDFInfo
- Publication number
- CN104564174A CN104564174A CN201410838152.9A CN201410838152A CN104564174A CN 104564174 A CN104564174 A CN 104564174A CN 201410838152 A CN201410838152 A CN 201410838152A CN 104564174 A CN104564174 A CN 104564174A
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- China
- Prior art keywords
- elastic sealing
- sheet
- turbine
- stator blade
- obturaging
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- Granted
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 34
- 238000005452 bending Methods 0.000 claims description 16
- 230000003044 adaptive effect Effects 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 22
- 238000000034 method Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
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- Gasket Seals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an elastic sealing structure for turbine fixed blades of a gas turbine, and relates to structural designs of gas turbines. The elastic sealing structure for the turbine fixed blades comprises a front elastic sealing sheet, a rear elastic sealing sheet, a pressure plate and positioning bolts. The front elastic sealing sheet and the rear elastic sealing sheet comprise bent sections and straight sections and are radially symmetrically arranged, a cavity is formed between the two bent sections, and the lower ends of the turbine fixed blades extend into the cavity formed by the two bent sections and are axially in point contact or surface contact with the front elastic sealing sheet and the rear elastic sealing sheet; the two straight sections which are positioned on the lower surfaces of the bent sections are in close contact with each other and are axially fixed onto a fixed blade sealing ring. The elastic sealing structure has the advantages that the sealing sheets can elastically deform, so that friction force between the sealing sheets and the lower ends of the fixed blades can be reduced, the elastic sealing structure is adaptive to radial movement of the fixed blades due to thermal deformation of turbine stators, the sealing sheets and the lower ends of the fixed blades can be assuredly constantly sealed in a contact manner, and the gas turbine can assuredly reliably and stably work.
Description
Technical field
The present invention relates to a kind of sealing configuration of gas turbine turbine stator blade, belong to gas turbine structure design field.
Background technique
During gas turbine work, turbine blade is operated in high-temperature fuel gas, adopts and enters blade from other position introducing cooled gas, and then reduce leaf temperature, ensure the safe and reliable work of blade, improve leaf longevity.Stator blade lower end adopts seal structure, and bootable cooled gas enters the rotor disk chamber of specifying, and ensures wheel disc operating temperature, improves structural reliability and working life.When turbine stator part is heated, produce radial displacement, there is radial relative movement in stator blade lower end and seal structure, seal structure and stator blade lower end effectively can ensure sealing effect in turbine axial compression.
Traditional industry gas turbine stator blade sealing configuration adopts baffle plate to add spring structure, adopts axial pin baffle plate, spring and pad to be linked together, is threaded connection between pin and stator blade seal ring.Along the circumferential direction, baffle plate is divided into a lot of sector, and each section adds spring to realize axially locating by a pin, this complex structure and install inconvenience, and at stator blade seal ring horizontal flange place during installation, the existence of pin can cause split bolt to mount and dismount difficulty.Operationally, the stator blade lower end caused due to thermal distortion moves up and down, and baffle plate can be brought to wear and tear, cause seal failure, and structural life-time shortens.
Summary of the invention
The object of this invention is to provide a kind of gas turbine turbine stator blade elastic sealing structure, industry gas turbine stator blade seal ring baffle plate dismounting inconvenience, service wear problem can be solved preferably, improve the functional reliability of gas turbine turbine stator blade sealing configuration, stability and working life.
Technological scheme of the present invention is as follows:
A kind of gas turbine turbine stator blade elastic sealing structure, is characterized in that: this elastic sealing structure contains obturage sheet, rear elasticity of front elasticity to be obturaged sheet, pressing plate and holding down bolt; Described front elasticity sheet and rear elasticity sheet of obturaging of obturaging includes bending section and straight section, front elasticity sheet and rear elasticity sheet of obturaging of obturaging radially is arranged symmetrically with, a cavity is formed between two bending sections, turbine stator blade lower end is stretched in the cavity that two bending sections are formed, and turbine stator blade lower end and front elasticity sheet and rear elasticity sheet of obturaging of obturaging forms point cantact or face contacts in axis; Be positioned at two straight section close contacts below bending section, and be axially fixed on stator blade seal ring with pressing plate and holding down bolt front elasticity obturaged sheet and rear elasticity sheet of obturaging.
Described bending section of the present invention is wave Curved, or the curved shape be formed by connecting by a section or several sections of circular arc.
The present invention compared with prior art, have the following advantages and high-lighting effect: gas turbine turbine stator blade elastic sealing structure provided by the present invention, structure is simple, easy accessibility is reliable, when gas turbine works, the stator blade that the thermal distortion of turbine stator brings can be adapted to move radially, all the time the sheet that ensures to obturage contacts with turbine stator blade lower end and obturages, the resiliently deformable of sheet of obturaging is utilized to reduce to obturage the frictional force of sheet and turbine stator blade lower end, thus can ensure obturage and wear and tear less during work, reliable operation and increasing the service life, guarantee gas turbine is reliable, stably work.
Accompanying drawing explanation
Fig. 1 is existing gas turbine turbine stator blade sealing configuration enlarged view.
Fig. 2 is existing gas turbine turbine stator blade sealing configuration sectional drawing.
Fig. 3 is gas turbine turbine stator blade elastic sealing structure schematic diagram provided by the invention.
Fig. 4 is gas turbine turbine stator blade elastic sealing structure enlarged view provided by the invention.
Fig. 5 is gas turbine turbine stator blade elastic packing provided by the invention knot three dimensional sectional view.
List of parts: ring held by 1-turbine; 2-turbine stator blade; 3-rotor assembly; 4-stator blade seal ring; Before 5-, elasticity is obturaged sheet; After 6-, elasticity is obturaged sheet; 7-pressing plate; 8-holding down bolt; 9-baffle plate; 10-pin; 11-spring; 12-pad.
Embodiment
Below in conjunction with accompanying drawing, structure of the present invention, principle and working procedure are described further.
Fig. 3, Fig. 4 are gas turbine turbine stator blade elastic sealing structure schematic diagram provided by the invention, with sprue fuel gas flow direction for turbine spindle to, stator blade lower end is provided with stator blade seal ring 4, seal structure on it is for guiding the cooled gas flowed out from stator blade, make it to arrive the rotor disk chamber of specifying, cooled rotor wheel disc.Described gas turbine turbine stator blade elastic sealing structure contains obturage sheet 5, rear elasticity of front elasticity to be obturaged sheet 6, pressing plate 7 and holding down bolt 8; Described front elasticity sheet 5 and rear elasticity sheet 6 of obturaging of obturaging includes bending section and straight section, front elasticity sheet 5 and rear elasticity sheet 6 of obturaging of obturaging radially is arranged symmetrically with, bending section is local inclination radially, a cavity is formed between two bending sections, turbine stator blade 2 lower end is stretched in the cavity that two bending sections are formed, and turbine stator blade 2 lower end and front elasticity sheet 5 and rear elasticity sheet 6 of obturaging of obturaging forms point cantact or face contacts in axis; Front elasticity the obturage curved shape of bending section of sheet of sheet and rear elasticity of obturaging is identical, and can bend by undulate, also can be the curved shape be formed by connecting by a section or several sections of circular arc.Be positioned at two straight section close contacts below bending section, and be axially fixed on stator blade seal ring 4 with pressing plate 7 and holding down bolt 8 front elasticity obturaged sheet 5 and rear elasticity sheet 6 of obturaging.
Be installed to after in this chamber in turbine stator blade 2 lower end, along with turbine stator blade 2 position moves down in radial direction, front elasticity sheet 5 and rear elasticity sheet 6 of obturaging of obturaging produces corresponding distortion, the movement of turbine stator blade 2 can be adapted to, in working procedure front elasticity obturage sheet 5 and rear elasticity obturage sheet 6 all the time with turbine stator blade 2 lower end retainer shaft to contacting, realize sealing.As shown in Figure 5, on straight section, to obturage sheet 6 axial compression by front elasticity to be obturaged sheet 5 and rear elasticity of pressing plate 7, and adopt multiple identical holding down bolt 8 to locate to be fixed on stator blade seal ring 4 by three, structure is simple, easy accessibility.
Claims (2)
1. a gas turbine turbine stator blade elastic sealing structure, is characterized in that: this elastic sealing structure contains obturage sheet (5), rear elasticity of front elasticity to be obturaged sheet (6), pressing plate (7) and holding down bolt (8); Described front elasticity sheet (5) and rear elasticity sheet (6) of obturaging of obturaging includes bending section and straight section, front elasticity sheet (5) and rear elasticity sheet (6) of obturaging of obturaging radially is arranged symmetrically with, a cavity is formed between two bending sections, turbine stator blade (2) lower end is stretched in the cavity that two bending sections are formed, and turbine stator blade (2) lower end and front elasticity sheet (5) and rear elasticity sheet (6) of obturaging of obturaging forms point cantact or face contacts in axis; Be positioned at two straight section close contacts below bending section, and be axially fixed on stator blade seal ring (4) with pressing plate (7) and holding down bolt (8) front elasticity obturaged sheet (5) and rear elasticity sheet (6) of obturaging.
2. a kind of gas turbine turbine stator blade elastic sealing structure as claimed in claim 1, is characterized in that: described bending section is wave Curved, or the curved shape be formed by connecting by a section or several sections of circular arc.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410838152.9A CN104564174B (en) | 2014-12-29 | 2014-12-29 | Elastic sealing structure for turbine fixed blades of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410838152.9A CN104564174B (en) | 2014-12-29 | 2014-12-29 | Elastic sealing structure for turbine fixed blades of gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104564174A true CN104564174A (en) | 2015-04-29 |
| CN104564174B CN104564174B (en) | 2017-01-18 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410838152.9A Active CN104564174B (en) | 2014-12-29 | 2014-12-29 | Elastic sealing structure for turbine fixed blades of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104564174B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112610336A (en) * | 2020-12-21 | 2021-04-06 | 杭州汽轮动力集团有限公司 | Interstage seal ring sealing structure |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1239889B (en) * | 1963-06-28 | 1967-05-03 | Licentia Gmbh | Inlet guide vane ring for axial turbines, in particular axial gas turbines, with radially resiliently pressed ring segments |
| US3829233A (en) * | 1973-06-27 | 1974-08-13 | Westinghouse Electric Corp | Turbine diaphragm seal structure |
| CN1192513A (en) * | 1997-01-29 | 1998-09-09 | 亚瑞亚·勃朗勃威力有限公司 | Exhaust-gas turbine of turbocharger |
| US6217279B1 (en) * | 1997-06-19 | 2001-04-17 | Mitsubishi Heavy Industries, Ltd. | Device for sealing gas turbine stator blades |
| CN1441149A (en) * | 2002-02-27 | 2003-09-10 | 通用电气公司 | Sheet seal support part for turbine inner belt of gas turbine engine |
| CN1682012A (en) * | 2002-09-11 | 2005-10-12 | 三菱重工业株式会社 | Gas turbine pressurizing air supply system |
| CN101424196A (en) * | 2007-10-31 | 2009-05-06 | 通用电气公司 | Gas turbines having flexible chordal hinge seals |
| US20090324388A1 (en) * | 2008-06-30 | 2009-12-31 | Mitsubishi Heavy Industries, Ltd. | Gas turbine and cooling air supply structure thereof |
| CN102926972A (en) * | 2011-08-08 | 2013-02-13 | 通用电气公司 | Seal assembly and method for flowing hot gas in a turbine |
| CN204402578U (en) * | 2014-12-29 | 2015-06-17 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine turbine stator blade elastic sealing structure |
-
2014
- 2014-12-29 CN CN201410838152.9A patent/CN104564174B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1239889B (en) * | 1963-06-28 | 1967-05-03 | Licentia Gmbh | Inlet guide vane ring for axial turbines, in particular axial gas turbines, with radially resiliently pressed ring segments |
| US3829233A (en) * | 1973-06-27 | 1974-08-13 | Westinghouse Electric Corp | Turbine diaphragm seal structure |
| CN1192513A (en) * | 1997-01-29 | 1998-09-09 | 亚瑞亚·勃朗勃威力有限公司 | Exhaust-gas turbine of turbocharger |
| US6217279B1 (en) * | 1997-06-19 | 2001-04-17 | Mitsubishi Heavy Industries, Ltd. | Device for sealing gas turbine stator blades |
| CN1441149A (en) * | 2002-02-27 | 2003-09-10 | 通用电气公司 | Sheet seal support part for turbine inner belt of gas turbine engine |
| CN1682012A (en) * | 2002-09-11 | 2005-10-12 | 三菱重工业株式会社 | Gas turbine pressurizing air supply system |
| CN101424196A (en) * | 2007-10-31 | 2009-05-06 | 通用电气公司 | Gas turbines having flexible chordal hinge seals |
| US20090324388A1 (en) * | 2008-06-30 | 2009-12-31 | Mitsubishi Heavy Industries, Ltd. | Gas turbine and cooling air supply structure thereof |
| CN102926972A (en) * | 2011-08-08 | 2013-02-13 | 通用电气公司 | Seal assembly and method for flowing hot gas in a turbine |
| CN204402578U (en) * | 2014-12-29 | 2015-06-17 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine turbine stator blade elastic sealing structure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112610336A (en) * | 2020-12-21 | 2021-04-06 | 杭州汽轮动力集团有限公司 | Interstage seal ring sealing structure |
| CN112610336B (en) * | 2020-12-21 | 2021-11-12 | 杭州汽轮动力集团有限公司 | Interstage seal ring sealing structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104564174B (en) | 2017-01-18 |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: Elastic sealing structure for turbine fixed blades of gas turbine Effective date of registration: 20171115 Granted publication date: 20170118 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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Effective date of registration: 20190820 Granted publication date: 20170118 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20170118 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
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| PD01 | Discharge of preservation of patent | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20191230 Granted publication date: 20170118 |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20200115 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: China United heavy-duty gas turbine technology Co., Ltd. Address before: 100084 No. 8, building 1, No. 1001, Zhongguancun East Road, Beijing, Haidian District Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |