WO1999045297A1 - Dispositif d'etancheite pour machines tournantes - Google Patents
Dispositif d'etancheite pour machines tournantes Download PDFInfo
- Publication number
- WO1999045297A1 WO1999045297A1 PCT/JP1999/000769 JP9900769W WO9945297A1 WO 1999045297 A1 WO1999045297 A1 WO 1999045297A1 JP 9900769 W JP9900769 W JP 9900769W WO 9945297 A1 WO9945297 A1 WO 9945297A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- seal plate
- seal
- plate
- sealing
- groove
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J9/00—Piston-rings, e.g. non-metallic piston-rings, seats therefor; Ring sealings of similar construction
- F16J9/12—Details
- F16J9/14—Joint-closures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/08—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing
- F16J15/0887—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing the sealing effect being obtained by elastic deformation of the packing
Definitions
- the present invention relates to a sealing device for performing gas sealing of a rotating machine through which a high-temperature gas flows, such as a gas turbine.
- Fig. 7 is a structural diagram of the main parts of the gas turbine.
- 1 is a evening bin disk fixed to the rotating shaft
- 10 is a rotor blade implanted on the outer periphery of the evening bin disk
- 1 1 is a stationary wing.
- a labyrinth seal 15 for providing a gas seal between the gas passage 12 and the cooling space 14 formed between the turbine disks 1 and 1 is provided on the inner periphery of the stator vane 11.
- I have. 13 is a cooling air passage for sending a cooling fluid to the cooling space.
- Reference numeral 2 denotes a seal plate provided inside the labyrinth seal 15. As shown in FIG. 8, the seal plate 2 is formed by dividing a thin metal ring into a plurality of pieces (two pieces in this example) in the circumferential direction, and the divided portions 2c are formed on the upper and lower surfaces of the gas ring. It has a stepped shape with a flat surface. Then, the sealing plate 2 is assembled in a groove la (see FIG.
- the seal plate 2 is circular. Since the fluid is divided into a plurality in the circumferential direction, the fluid easily enters from the divided portion 2c. Since the sealing plate 2 is pressed against the outer peripheral surface 1b of the groove 1a of the turbine disk 1 only by the centrifugal force, the pressing force is small, and the sealing plate 2 self-oscillates due to the intrusion of the fluid. Therefore, in the above-mentioned conventional seal structure, there is a problem that the self-excited vibration causes the seal plate 2 to be worn and reduced in thickness, thereby causing the occurrence of poor sealing.
- the purpose of this is to reduce the self-excited vibration of the seal plate by securely fixing the seal plate to the evening bin disk with a large mounting force, and to reduce the wear, thinning of the seal plate due to the self-excited vibration, and It is an object of the present invention to provide a sealing device for a rotary machine, which prevents the occurrence of defective sealing due to the above.
- the present invention solves the above-described problems.
- the first means is to provide a groove provided in a rotatably driven disk portion with a fluid passage on an outer peripheral side of the groove and an inner periphery in the groove.
- a rotary machine provided with a seal device provided with a seal plate for sealing a fluid between the fluid passage and a side fluid passage, the seal plate is divided into a plurality of pieces along a circumferential direction, and is divided into a plurality of grooves in the disk portion.
- a spring plate is inserted inside the seal plate, and the seal plate is pressed against the seal surface of the groove by the elastic force of the spring plate. In the device.
- the seal plate is pressed against the seal surface of the groove by the combined force of the elastic force of the spring plate and the centrifugal force of the spring plate itself in addition to the centrifugal force of the seal plate itself.
- the fluid is securely sealed on the sealing surface.
- the seal plate is pressed against the disk by a large pressing force due to the resultant force. Since it is pressed against the sealing surface of the groove, even if fluid enters the divided part of the seal plate, large self-excited vibration does not occur unlike the conventional one, and self-excited vibration is reduced, and The occurrence of wear and thinning of the seal plate is prevented.
- a second means is the same as the first means, wherein a plurality of the seal plates are overlapped and inserted into the groove, and the spring plate is inserted inside the seal plate.
- the centrifugal force of the seal plate itself is increased by stacking a plurality of seal plates, and the seal plate can be pressed against the seal surface in the groove with a larger pressing force, further improving the sealing performance. I do. Further, self-excited vibration is further reduced by friction at a contact portion between the seal plates.
- the third means is a seal provided by providing a seal plate for sealing a fluid between a fluid passage on an outer peripheral side and a fluid passage on an inner peripheral side of the groove in a groove provided in the disk portion driven to rotate.
- the seal plate is divided into a plurality of pieces along the circumferential direction, a protrusion is formed on one side of the divided portion, and the protrusion is formed on the other side in the circumferential direction. And a groove that is fitted with a predetermined gap in the seal device.
- FIG. 1 is a partial front view of a gas turbine sealing device according to a first embodiment of the present invention.
- FIG. 2 is a cross-sectional view of a main part of the sealing device in the embodiment.
- FIG. 3 is a perspective view of the seal plate in the embodiment.
- FIG. 4 is a front sectional view of a main part showing a second embodiment of the present invention.
- FIG. 5 is a diagram corresponding to FIG. 2 in the second embodiment.
- FIGS. 6A and 6B are partial front views of a seal plate according to a third embodiment of the present invention, wherein FIG. 6A shows a state before assembling, and FIG. 6B shows a state after assembling.
- Figure 7 is a cross-sectional view of the main part of the gas bin.
- FIG. 8 is a perspective view of a conventional seal plate. BEST MODE FOR CARRYING OUT THE INVENTION
- the embodiment described below applies the present invention to a sealing device using a sealing plate 2 for gas sealing between a gas passage 12 and a cooling space 14 in the gas turbine shown in FIG. Applied.
- FIGS. 1 to 3 show the structure of a sealing plate 2 in a sealing device according to a first embodiment of the present invention and the manner of attachment thereof.
- the seal plate 2 is formed by dividing a thin metal ring into a plurality of pieces in the circumferential direction, and the divided portion 21 is formed in a stepped shape having upper and lower mating surfaces, that is, gas tight surfaces. Have been.
- a wavy spring plate 3 is provided on the inner peripheral side of the seal plate 2. As shown in FIGS. 1 and 3, the spring plate 3 is divided into a plurality of pieces in the circumferential direction, and fitting holes 3 a provided at appropriate locations project from the inner peripheral surface of the seal plate 2. The circumferential displacement is prevented by being fitted to the pin 4 thus set.
- FIG. 2 shows a state in which the seal plate 2 and the spring plate 3 are incorporated in the turbine disk 1.
- 1 and 1 are the evening bin disks of the adjacent paragraph
- a high-temperature working gas flows through the gas passage 12 of the evening bin, and the low-temperature cooling air flows into the cooling space 14 inside the seal plate 2 and the labyrinth seal 15.
- the sealing plate 2 incorporated in the groove 1a of the turbine disk 1, 1 being rotated at a high speed has the spring force of the spring plate 3 and the centrifugal force of the sealing plate 2 itself added with the centrifugal force of the spring plate 3.
- the resultant force is pressed against the outer peripheral surface 1 b of the groove 1 a, so that the cooling air due to the pressure difference between the high-temperature gas in the gas passage 12 and the cooling air in the cooling space 14 at this outer peripheral surface
- the seal plate 2 is securely mounted in the groove 1a by the elastic force of the spring plate 3 and the centrifugal force of the seal plate 2 as described above, so that the seal plate 2 and the spring plate 3 Is prevented from moving in the circumferential direction, and even if gas or cooling air enters from the divided portion 21 of the seal plate 2, large self-excited vibration unlike the conventional one does not occur.
- FIG. 4 is a partial sectional view of a sealing plate and a spring plate (a sectional view on the front side).
- FIG. 5 is a sectional view showing a mounting state of a sealing device. is there.
- two sealing plates 2 and 2 ' are provided in the radial direction (two or more sealing plates may be provided). That is, in FIGS. 4 and 5, 2 is an outer seal plate, 2 'is an inner seal plate, and both seal plates 2 and 2' are shown in FIG.
- the spring plates 3 are inserted in the grooves 1a of the turbine disks 1 and 1 in the radial direction, and the spring plate 3 similar to the first embodiment is inserted into the inner periphery of the inner seal plate 2 '.
- the outer seal plate 2 and the inner seal plate 2 ' are divided into a plurality of pieces in the circumferential direction.
- Reference numeral 22 denotes a divided portion of the seal plate 2
- reference numeral 23 denotes a divided portion of the seal plate 2 '.
- the above-mentioned seal plates 2, 2 ′ and the spring plate 3 are connected to the pin 4 fixed in place in the circumferential direction of the outer seal plate 2 with the hole 2 a of the inner seal plate 2 ′ and the hole 3 a of the spring plate 3. By fitting into a, the circumferential displacement of the above three members is prevented.
- FIG. 6A and 6B show a seal plate used in a sealing device according to a third embodiment of the present invention, wherein FIG. 6A shows a state before the seal plate is assembled, and FIG. The state after assembly is shown, respectively.
- a projection 5 is provided on the inner periphery of the gas tight surface on one side of the sealing plates 2 and 2 ′ divided along the circumferential direction, and the gas seal on the other side is provided.
- a groove 6 is recessed in the outer periphery of the seat surface. The groove 6 is formed so that its circumferential width is larger than the width of the protrusion 5.
- both seal plates 2, 2 ′ are overlapped on the gas night surface to form a turbine disk.
- the seal plate in addition to the centrifugal force of the seal plate itself, the elasticity of the spring plate, The seal plate is pressed against the seal surface by a strong force due to the centrifugal force of the seal plate itself and the seal plate. Vibration is suppressed. As a result, it is possible to prevent the occurrence of poor sealing due to wear and thinning of the seal plate.
- the centrifugal force of the seal plates increases, the pressing force of the seal surface increases, and the sealing performance is further improved.
- the self-excited vibration is further suppressed by the vibration damping effect due to the contact of.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE69931113T DE69931113T2 (de) | 1998-03-02 | 1999-02-22 | Dichtungsvorrichtung für drehende maschinen |
US09/423,003 US6315301B1 (en) | 1998-03-02 | 1999-02-22 | Seal apparatus for rotary machines |
EP99906454A EP0979961B1 (en) | 1998-03-02 | 1999-02-22 | Seal apparatus for rotary machines |
CA002287509A CA2287509C (en) | 1998-03-02 | 1999-02-22 | Rotating machine seal device |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP10/49441 | 1998-03-02 | ||
JP04944198A JP3643692B2 (ja) | 1998-03-02 | 1998-03-02 | 回転機械のシール装置 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1999045297A1 true WO1999045297A1 (fr) | 1999-09-10 |
Family
ID=12831218
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP1999/000769 WO1999045297A1 (fr) | 1998-03-02 | 1999-02-22 | Dispositif d'etancheite pour machines tournantes |
Country Status (6)
Country | Link |
---|---|
US (1) | US6315301B1 (ja) |
EP (1) | EP0979961B1 (ja) |
JP (1) | JP3643692B2 (ja) |
CA (1) | CA2287509C (ja) |
DE (1) | DE69931113T2 (ja) |
WO (1) | WO1999045297A1 (ja) |
Families Citing this family (43)
Publication number | Priority date | Publication date | Assignee | Title |
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DE60102217T2 (de) * | 2001-05-30 | 2005-01-13 | Techspace Aero, Milmort | Dichtende Verbindungsplatte |
US6612809B2 (en) * | 2001-11-28 | 2003-09-02 | General Electric Company | Thermally compliant discourager seal |
US6733234B2 (en) * | 2002-09-13 | 2004-05-11 | Siemens Westinghouse Power Corporation | Biased wear resistant turbine seal assembly |
US7562880B2 (en) * | 2004-02-09 | 2009-07-21 | Siemens Energy, Inc. | Seal usable between thermally movable components |
US7234918B2 (en) * | 2004-12-16 | 2007-06-26 | Siemens Power Generation, Inc. | Gap control system for turbine engines |
JP4822716B2 (ja) * | 2005-02-07 | 2011-11-24 | 三菱重工業株式会社 | シール構造を備えたガスタービン |
EP1918549B1 (en) * | 2005-08-23 | 2010-12-29 | Mitsubishi Heavy Industries, Ltd. | Seal structure of gas turbine combustor |
US7581931B2 (en) * | 2006-10-13 | 2009-09-01 | Siemens Energy, Inc. | Gas turbine belly band seal anti-rotation structure |
US20090108538A1 (en) * | 2007-10-24 | 2009-04-30 | Freudenberg-Nok General Partnership | Two-Component Seal With Integral Locking Feature To Prevent Relative Rotation |
US20090191050A1 (en) * | 2008-01-24 | 2009-07-30 | Siemens Power Generation, Inc. | Sealing band having bendable tang with anti-rotation in a turbine and associated methods |
US8821114B2 (en) | 2010-06-04 | 2014-09-02 | Siemens Energy, Inc. | Gas turbine engine sealing structure |
US8602737B2 (en) | 2010-06-25 | 2013-12-10 | General Electric Company | Sealing device |
JP5493233B2 (ja) * | 2010-11-19 | 2014-05-14 | イーグル工業株式会社 | シール装置 |
JP5631182B2 (ja) * | 2010-12-03 | 2014-11-26 | 三菱重工業株式会社 | ガスタービンのシール構造 |
US9200527B2 (en) * | 2011-01-04 | 2015-12-01 | General Electric Company | Systems, methods, and apparatus for a turbine interstage rim seal |
JP5769469B2 (ja) * | 2011-03-30 | 2015-08-26 | 三菱重工業株式会社 | シール構造 |
JP5134703B2 (ja) * | 2011-04-27 | 2013-01-30 | 三菱重工業株式会社 | シール構造を備えたガスタービン |
GB201109143D0 (en) * | 2011-06-01 | 2011-07-13 | Rolls Royce Plc | Flap seal spring and sealing apparatus |
US8956120B2 (en) * | 2011-09-08 | 2015-02-17 | General Electric Company | Non-continuous ring seal |
US9017015B2 (en) * | 2011-10-27 | 2015-04-28 | General Electric Company | Turbomachine including an inner-to-outer turbine casing seal assembly and method |
JP5785056B2 (ja) * | 2011-11-08 | 2015-09-24 | 三菱日立パワーシステムズ株式会社 | ガスタービン |
US8570505B2 (en) | 2012-03-06 | 2013-10-29 | Siemens Energy, Inc. | One-dimensional coherent fiber array for inspecting components in a gas turbine engine |
US9206705B2 (en) * | 2012-03-07 | 2015-12-08 | Mitsubishi Hitachi Power Systems, Ltd. | Sealing device and gas turbine having the same |
WO2013139837A1 (en) | 2012-03-21 | 2013-09-26 | Alstom Technology Ltd | Strip seal and method for designing a strip seal |
US9181810B2 (en) | 2012-04-16 | 2015-11-10 | General Electric Company | System and method for covering a blade mounting region of turbine blades |
US9366151B2 (en) | 2012-05-07 | 2016-06-14 | General Electric Company | System and method for covering a blade mounting region of turbine blades |
US9334738B2 (en) | 2012-10-23 | 2016-05-10 | Siemens Aktiengesellschaft | Gas turbine including belly band seal anti-rotation device |
US9347322B2 (en) | 2012-11-01 | 2016-05-24 | Siemens Aktiengesellschaft | Gas turbine including belly band seal anti-rotation device |
US9200519B2 (en) * | 2012-11-01 | 2015-12-01 | Siemens Aktiengesellschaft | Belly band seal with underlapping ends |
US10208612B2 (en) * | 2013-03-08 | 2019-02-19 | Siemens Energy, Inc. | Gas turbine sealing band arrangement having an underlap seal |
US9291065B2 (en) | 2013-03-08 | 2016-03-22 | Siemens Aktiengesellschaft | Gas turbine including bellyband seal anti-rotation device |
US9808889B2 (en) | 2014-01-15 | 2017-11-07 | Siemens Energy, Inc. | Gas turbine including sealing band and anti-rotation device |
US9790863B2 (en) | 2013-04-05 | 2017-10-17 | Honeywell International Inc. | Fluid transfer seal assemblies, fluid transfer systems, and methods for transferring process fluid between stationary and rotating components using the same |
US9399926B2 (en) * | 2013-08-23 | 2016-07-26 | Siemens Energy, Inc. | Belly band seal with circumferential spacer |
US9759081B2 (en) * | 2013-10-08 | 2017-09-12 | General Electric Company | Method and system to facilitate sealing in gas turbines |
EP2907977A1 (de) * | 2014-02-14 | 2015-08-19 | Siemens Aktiengesellschaft | Heißgasbeaufschlagbares Bauteil für eine Gasturbine sowie Dichtungsanordnung mit einem derartigen Bauteil |
US9631507B2 (en) * | 2014-07-14 | 2017-04-25 | Siemens Energy, Inc. | Gas turbine sealing band arrangement having a locking pin |
CN104196636B (zh) * | 2014-07-31 | 2017-12-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | 具有密封结构的燃气轮机 |
DE102016215983A1 (de) | 2016-08-25 | 2018-03-01 | Siemens Aktiengesellschaft | Rotor mit geteiltem Dichtungsring |
KR101877170B1 (ko) * | 2017-04-11 | 2018-08-07 | 두산중공업 주식회사 | 로터 디스크 실링장치와 이를 구비하는 로터 조립체 및 가스터빈 |
EP3409898B1 (en) | 2017-06-02 | 2020-05-13 | General Electric Technology GmbH | Belly band seals and method |
DE102018204521A1 (de) * | 2018-03-23 | 2019-09-26 | MTU Aero Engines AG | Turbomaschinenbauteilanordnung |
KR102612564B1 (ko) * | 2023-07-14 | 2023-12-11 | 한국중부발전(주) | 가스 터빈 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
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JPH03141804A (ja) * | 1989-09-08 | 1991-06-17 | General Electric Co <Ge> | クリアランス制御装置 |
JPH09133005A (ja) * | 1995-11-10 | 1997-05-20 | Mitsubishi Heavy Ind Ltd | ガスタービンロータ |
JPH102203A (ja) * | 1996-06-17 | 1998-01-06 | Mitsubishi Heavy Ind Ltd | ガスタービン冷却静翼 |
Family Cites Families (8)
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US1353082A (en) * | 1920-06-11 | 1920-09-14 | Frank K Stehle | Piston-ring |
US2638390A (en) * | 1950-08-02 | 1953-05-12 | Johannes E Neeme | Piston and ring |
US4537024A (en) * | 1979-04-23 | 1985-08-27 | Solar Turbines, Incorporated | Turbine engines |
US4251083A (en) * | 1979-05-15 | 1981-02-17 | Adriel Montes | Piston ring with tongue and groove joint |
JPS5896105A (ja) | 1981-12-03 | 1983-06-08 | Hitachi Ltd | スペ−サ先端空気漏洩防止ロ−タ |
US5221096A (en) * | 1990-10-19 | 1993-06-22 | Allied-Signal Inc. | Stator and multiple piece seal |
JPH09242505A (ja) | 1996-03-11 | 1997-09-16 | Hitachi Ltd | タービン構造 |
FR2758856B1 (fr) * | 1997-01-30 | 1999-02-26 | Snecma | Joint d'etancheite a plaquettes empilees glissant dans des fentes de reception |
-
1998
- 1998-03-02 JP JP04944198A patent/JP3643692B2/ja not_active Expired - Lifetime
-
1999
- 1999-02-22 EP EP99906454A patent/EP0979961B1/en not_active Expired - Lifetime
- 1999-02-22 US US09/423,003 patent/US6315301B1/en not_active Expired - Lifetime
- 1999-02-22 DE DE69931113T patent/DE69931113T2/de not_active Expired - Lifetime
- 1999-02-22 WO PCT/JP1999/000769 patent/WO1999045297A1/ja active IP Right Grant
- 1999-02-22 CA CA002287509A patent/CA2287509C/en not_active Expired - Lifetime
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH03141804A (ja) * | 1989-09-08 | 1991-06-17 | General Electric Co <Ge> | クリアランス制御装置 |
JPH09133005A (ja) * | 1995-11-10 | 1997-05-20 | Mitsubishi Heavy Ind Ltd | ガスタービンロータ |
JPH102203A (ja) * | 1996-06-17 | 1998-01-06 | Mitsubishi Heavy Ind Ltd | ガスタービン冷却静翼 |
Also Published As
Publication number | Publication date |
---|---|
JP3643692B2 (ja) | 2005-04-27 |
DE69931113D1 (de) | 2006-06-08 |
CA2287509C (en) | 2003-11-11 |
EP0979961B1 (en) | 2006-05-03 |
EP0979961A4 (en) | 2004-09-08 |
US6315301B1 (en) | 2001-11-13 |
JPH11247999A (ja) | 1999-09-14 |
CA2287509A1 (en) | 1999-09-10 |
DE69931113T2 (de) | 2006-11-30 |
EP0979961A1 (en) | 2000-02-16 |
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