CN104564174B - 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
- CN104564174B CN104564174B CN201410838152.9A CN201410838152A CN104564174B CN 104564174 B CN104564174 B CN 104564174B CN 201410838152 A CN201410838152 A CN 201410838152A CN 104564174 B CN104564174 B CN 104564174B
- Authority
- CN
- China
- Prior art keywords
- elastic sealing
- piece
- turbine
- elasticity
- stator blade
- 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
- 238000007789 sealing Methods 0.000 title claims abstract description 42
- 238000005452 bending Methods 0.000 claims description 18
- 230000003044 adaptive effect Effects 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 19
- 239000000112 cooling gas Substances 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
- 238000009434 installation Methods 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
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 structure of gas turbine turbine stator blade, belong to gas turbine structure designing technique neck
Domain.
Background technology
During gas turbine work, turbine blade is operated in high-temperature fuel gas, is entered using introducing cooling gas from other positions
Enter blade, and then reduce leaf temperature it is ensured that the safe and reliable work of blade, improve leaf longevity.Stator blade lower end is using knot of obturaging
Structure, bootable cooling gas enter the rotor disk chamber specified it is ensured that wheel disc operating temperature, improve structural reliability and use the longevity
Life.When turbine stator part is heated, produce radial displacement, stator blade lower end and seal structure have the relative motion of radial direction, obturage
Structure and stator blade lower end can be effectively ensured sealing effectiveness in turbine axial compression.
Traditional industry gas turbine stator blade sealing structure adds spring structure using baffle plate, using axial pin by baffle plate,
Spring and pad link together, and are threaded connection between pin and stator blade sealing ring.Along the circumferential direction, baffle plate is divided into a lot
Sector, each section is added spring to realize axially position by a pin, this complex structure and install inconvenience, close in stator blade during installation
At seal ring horizontal flange, the presence of pin can lead to the installation and removal of split bolt difficult.Operationally, due to thermal deformation
The stator blade lower end leading to moves up and down, and baffle plate can be brought to wear and tear, lead to seal failure, structural life-time shortens.
Content of the invention
It is an object of the invention to provide a kind of gas turbine turbine stator blade elastic sealing structure is so as to work can preferably be solved
The dismounting inconvenience of industry gas turbine stator blade sealing ring baffle plate, service wear problem, improve gas turbine turbine stator blade sealing structure
Functional reliability, stability and service life.
Technical scheme is as follows:
A kind of gas turbine turbine stator blade elastic sealing structure it is characterised in that: this elastic sealing structure contains front elasticity
Piece, the rear elasticity of obturaging is obturaged piece, pressing plate and bolt；Described front elasticity obturages piece and rear elasticity is obturaged, and piece all includes bending
Section and straight section, front elasticity obturages piece and rear elasticity is obturaged, and piece is radially arranged symmetrically, and forms a cavity between two bending sections,
Turbine stator blade lower end is stretched in the cavity that two bending sections are formed, turbine stator blade lower end and front elasticity obturage piece and rear elasticity is obturaged piece
It is being axially formed a contact or face contact；Two straight sections below bending section are in close contact, and will with pressing plate and bolt
Front elasticity obturages piece and rear elasticity is obturaged, and piece is axially fixed on stator blade sealing ring.
Described bending section of the present invention is in wave Curved, or by one section or several sections of circular arc be formed by connecting curved
Curved shape.
The present invention compared with prior art, has advantages below and high-lighting effect: gas turbine provided by the present invention
Turbine stator blade elastic sealing structure, structure is simple, and easy accessibility is reliable, when gas turbine works, adapts to turbine stator heat
Deform the stator blade bringing to move radially, be always ensured that piece of obturaging is contacted with turbine stator blade lower end and obturage, using the bullet of piece of obturaging
Property deformation reducing the frictional force of obturage piece and turbine stator blade lower end, obturaging and wearing and tearing less thus can guarantee that when working, working
Reliability and increasing the service life it is ensured that gas turbine is reliable, stably work.
Brief description
Fig. 1 is existing gas turbine turbine stator blade sealing structure enlarged drawing.
Fig. 2 is existing gas turbine turbine stator blade sealing structure profile.
Fig. 3 is the gas turbine turbine stator blade elastic sealing structure schematic diagram that the present invention provides.
Fig. 4 is the gas turbine turbine stator blade elastic sealing structure enlarged drawing that the present invention provides.
Fig. 5 is the gas turbine turbine stator blade elastic packing knot three dimensional sectional view that the present invention provides.
List of parts: 1- turbine held in ring；2- turbine stator blade；3- rotor assembly；4- stator blade sealing ring；Before 5-, elasticity is obturaged
Piece；After 6-, elasticity is obturaged piece；7- pressing plate；8- bolt；9- baffle plate；10- pin；11- spring；12- pad.
Specific embodiment
Below in conjunction with the accompanying drawings the structure of the present invention, principle and the course of work are described further.
Fig. 3, Fig. 4 are the gas turbine turbine stator blade elastic sealing structure schematic diagrames that the present invention provides, with sprue combustion gas
Flow direction is turbine axial direction, and stator blade lower end is provided with stator blade sealing ring 4, and seal structure thereon is used for guiding and flows from stator blade
The cooling gas going out, make it to reach the rotor disk chamber specified, and cool down rotor disk.Described gas turbine turbine stator blade elasticity
Sealing structure contains obturage piece 5, rear elasticity of front elasticity obturages piece 6, pressing plate 7 and bolt 8；Described front elasticity is obturaged piece 5
All include bending section and straight section with rear elasticity piece 6 of obturaging, front elasticity obturages piece 5 and rear elasticity is obturaged, and piece 6 is radially arranged symmetrically,
The diametrically opposite bending of bending section, forms a cavity, turbine stator blade 2 lower end is stretched into two bending sections and formed between two bending sections
Cavity in, turbine stator blade 2 lower end and front elasticity obturage piece 5 and rear elasticity is obturaged piece 6 contacts or face contact being axially formed；
Front elasticity obturage piece and rear elasticity obturage piece bending section curved shape identical, can with undulate bending or by
The curved shape that one section or several sections of circular arc are formed by connecting.Two straight sections below bending section are in close contact, and with pressing plate 7 He
Front elasticity is obturaged piece 5 by bolt 8 and rear elasticity is obturaged, and piece 6 is axially fixed on stator blade sealing ring 4.
After turbine stator blade 2 lower end is installed in this chamber, move down in radial direction with turbine stator blade 2 position, front elasticity is obturaged
Piece 5 and rear elasticity piece 6 of obturaging produces corresponding deformation, adapts to the movement of turbine stator blade 2, and in the course of work, front elasticity is obturaged piece
5 and rear elasticity obturage piece 6 all the time with turbine stator blade 2 lower end keep axially contact, realize sealing.As shown in figure 5, in straight section
On, with pressing plate 7, front elasticity is obturaged piece 5 and rear elasticity is obturaged piece 6 axial compression, and fixed using multiple identical bolts 8
Three is fixed on stator blade sealing ring 4 for position, and structure is simple, easy accessibility.
Claims (2)
1. a kind of gas turbine turbine stator blade elastic sealing structure it is characterised in that: this elastic sealing structure contain before elasticity envelope
Tight piece (5), rear elasticity are obturaged piece (6), pressing plate (7) and bolt (8)；Described front elasticity obturage piece (5) and rear elasticity envelope
Tight piece (6) all includes bending section and straight section, and front elasticity obturages piece (5) and rear elasticity is obturaged, and piece (6) is radially arranged symmetrically, two
Form a cavity, turbine stator blade (2) lower end is stretched in the cavity that two bending sections are formed, under turbine stator blade (2) between bending section
Piece (5) is obturaged at end respectively with front elasticity and rear elasticity is obturaged piece (6) contacts or face contacts being axially formed；Under bending section
Two straight sections in face are in close contact, and with pressing plate (7) and bolt (8), front elasticity are obturaged piece (5) and rear elasticity is obturaged piece (6)
It is axially fixed on stator blade sealing ring (4).
2. as claimed in claim 1 a kind of gas turbine turbine stator blade elastic sealing structure it is characterised in that: described bending
Section is in wave Curved.
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 CN104564174A (en) | 2015-04-29 |
| CN104564174B true CN104564174B (en) | 2017-01-18 |
Family
ID=53081146
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) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (9)
| 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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8079803B2 (en) * | 2008-06-30 | 2011-12-20 | Mitsubishi Heavy Industries, Ltd. | Gas turbine and cooling air supply structure thereof |
-
2014
- 2014-12-29 CN CN201410838152.9A patent/CN104564174B/en active Active
Patent Citations (9)
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104564174A (en) | 2015-04-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106536867B (en) | Stator blade, gas turbine, the remodeling method for splitting ring, the remodeling method of stator blade and segmentation ring | |
| WO2009022448A1 (en) | Turbo charger | |
| JP2013139814A (en) | System and method for sealing gas path in turbine | |
| US10393025B2 (en) | Sealing arrangement at the interface between a combustor and a turbine of a gas turbine and gas turbine with such a sealing arrangement | |
| CN105041460A (en) | Turbocharger with variable-vane turbine nozzle | |
| CN204716307U (en) | Air seal structure between gas turbine turbine wheel disc and turbine stator blade | |
| CN204402578U (en) | A kind of gas turbine turbine stator blade elastic sealing structure | |
| CN104564174B (en) | Elastic sealing structure for turbine fixed blades of gas turbine | |
| CN103541776B (en) | Axial seal structure between a kind of gas turbine wheel disk | |
| US9829007B2 (en) | Turbine sealing system | |
| CN102330819B (en) | Mechanical sealing device | |
| CN205297656U (en) | Combined type atmoseal device | |
| CN204705173U (en) | Seal of rotary kiln structure | |
| CN203533606U (en) | Novel center cylinder sealing device of air preheater | |
| CN201706524U (en) | Sealing device for preventing air preheater from air leakage | |
| CN204113352U (en) | A kind of turbosupercharger nozzle ring capable of changing cross sections | |
| CN204609955U (en) | A kind of Multi-tooth corrugated sheet elastic sealing device | |
| CN203413127U (en) | Dry gas seal device of pump double-end-face corrugated pipe | |
| CN103982248B (en) | There is the vane sealing device of gap control function | |
| CN103075204B (en) | Back steam seal device of steam turbine | |
| CN202812206U (en) | Novel flexible sheet tooth sealing ring | |
| CN203515684U (en) | Axial sealing structure among wheel discs of gas turbine | |
| CN202733008U (en) | Motor-driven vacuum butterfly valve | |
| CN205858419U (en) | A kind of sealing retaining ring being applied to combustion engine | |
| CN206246156U (en) | A kind of floating tooth Honeycomb steam seal |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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 |
|
| PP01 | Preservation of patent right | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20190820 Granted publication date: 20170118 |
|
| 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 |
|
| PD01 | Discharge of preservation of patent | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20191230 Granted publication date: 20170118 |
|
| 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. |