RU98108420A - SEALING ELEMENT FOR SEALING THE GAP AND ALSO THE GAS TURBINE INSTALLATION - Google Patents

SEALING ELEMENT FOR SEALING THE GAP AND ALSO THE GAS TURBINE INSTALLATION

Info

Publication number
RU98108420A
RU98108420A RU98108420/06A RU98108420A RU98108420A RU 98108420 A RU98108420 A RU 98108420A RU 98108420/06 A RU98108420/06 A RU 98108420/06A RU 98108420 A RU98108420 A RU 98108420A RU 98108420 A RU98108420 A RU 98108420A
Authority
RU
Russia
Prior art keywords
sealing element
gap
sealing
groove
region
Prior art date
Application number
RU98108420/06A
Other languages
Russian (ru)
Other versions
RU2162556C2 (en
Inventor
Милазар Мирко
Тершюрен Фридхельм
Линерт Альфред
Original Assignee
Сименс Акциенгезелльшафт
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Сименс Акциенгезелльшафт filed Critical Сименс Акциенгезелльшафт
Publication of RU98108420A publication Critical patent/RU98108420A/en
Application granted granted Critical
Publication of RU2162556C2 publication Critical patent/RU2162556C2/en

Links

Claims (12)

1. Уплотняющий элемент (1) для уплотнения зазора (5), который образован между двумя термично подвижными относительно друг друга деталями (2a, 2b), каждая из которых содержит канавку детали (3a, 3b), который направлен вдоль главной линии (21) и имеет в основном перпендикулярном к главной линии (21) поперечном сечении расположенную между первым концом (6a) и вторым концом (6b) среднюю область (10), причем средняя область (10) имеет первую поверхность (9a), которая снабжена зубьями.1. A sealing element (1) for sealing the gap (5), which is formed between two thermally movable relative to each other parts (2a, 2b), each of which contains a groove of the part (3a, 3b), which is directed along the main line (21) and has a generally middle region (10) located between the first end (6a) and the second end (6b), generally perpendicular to the main line (21), and the middle region (10) has a first surface (9a) that is provided with teeth. 2. Уплотняющий элемент (1) по п.1, со второй поверхностью (9b), которая относительно средней линии (4) лежит противоположно первой поверхности (9a) и является гладкой. 2. The sealing element (1) according to claim 1, with a second surface (9b), which relative to the midline (4) lies opposite to the first surface (9a) and is smooth. 3. Уплотняющий элемент (1) по п.1 или 2, с множеством уплотняющих канавок (7), которые наклонены относительно средней линии (4) на угол наклона (α) 50 - 90o.3. The sealing element (1) according to claim 1 or 2, with many sealing grooves (7), which are inclined relative to the midline (4) by an angle of inclination (α) of 50 - 90 o . 4. Уплотняющий элемент (1) по п.3, в котором уплотняющие канавки (7) наклонены с подъемом к средней области (10). 4. The sealing element (1) according to claim 3, in which the sealing grooves (7) are inclined to rise to the middle region (10). 5. Уплотняющий элемент (1) по п.3 или 4, в котором уплотняющие канавки (7) имеют на концах (6a, 6b) меньший угол наклона (α), чем в средней области (10), причем угол наклона (α) в средней области составляет в частности 90o.5. The sealing element (1) according to claim 3 or 4, in which the sealing grooves (7) have at the ends (6a, 6b) a smaller angle of inclination (α) than in the middle region (10), and the angle of inclination (α) in the middle region is in particular 90 o . 6. Уплотняющий элемент (1) по любому из предыдущих пунктов, который сужается в направлении от средней области (10) к концам (6a, 6b). 6. A sealing element (1) according to any one of the preceding paragraphs, which tapers in the direction from the middle region (10) to the ends (6a, 6b). 7. Уплотняющий элемент (1) по любому из предыдущих пунктов, в газотурбинной установке (22) с областью горячего газа (11) и подлежащей уплотнению от нее областью охлаждающего газа (8) для охлаждения направляющих лопаток (12) газотурбинной установки (22), который входит в канавку детали (3a) первой детали (2a), в частности направляющей лопатки (12) или детали стенки (13), и в канавку детали (3b) второй детали (2b), граничащей с первой деталью (2a), в частности направляющей лопатки (12) или детали стенки (13), причем между деталями (2a, 2b) образован зазор (5). 7. A sealing element (1) according to any one of the preceding paragraphs, in a gas turbine installation (22) with a hot gas region (11) and a cooling gas region (8) to be sealed from it for cooling guide vanes (12) of a gas turbine installation (22), which enters the groove of the part (3a) of the first part (2a), in particular the guide vane (12) or the wall part (13), and the groove of the part (3b) of the second part (2b) bordering the first part (2a), in especially a guide vane (12) or a wall part (13), and a gap (5) is formed between the parts (2a, 2b). 8. Уплотняющий элемент (1) по п.7, в котором подлежащий введению в соответствующую канавку детали (3a, 3b) конец (6a, 6b) имеет незначительное повышение размера по сравнению с канавкой детали (3a, 3b). 8. The sealing element (1) according to claim 7, in which the end (6a, 6b) to be inserted into the corresponding groove of the part (3a, 3b) has a slight increase in size compared to the groove of the part (3a, 3b). 9. Уплотняющий элемент (1) по п.7 или 8, который входит в канавку детали (3a, 3b), сужающуюся в направлении от зазора (5) внутрь детали (12, 13). 9. The sealing element (1) according to claim 7 or 8, which is included in the groove of the part (3a, 3b), tapering in the direction from the gap (5) into the part (12, 13). 10. Уплотняющий элемент (1) по пп.7, 8 или 9, в котором первая поверхность (9a) обращена к области охлаждающего газа (8). 10. The sealing element (1) according to claims 7, 8 or 9, in which the first surface (9a) faces the region of the cooling gas (8). 11. Газотурбинная установка (22) с областью горячего газа (11) и подлежащей уплотнению относительно нее областью охлаждающего газа (8) для охлаждения направляющих лопаток (12), причем области (8, 11) разделены друг от друга за счет множества расположенных в направлении периметра и в осевом направлении деталей (2a, 2b) и по меньшей мере первая деталь (2a), в частности пластина направляющей лопатки (16) или деталь стенки (13), и вторая деталь (2b), в частности пластина направляющей лопатки (16), или деталь стенки (13), дистанционированы в направлении периметра за счет зазора (5) и имеют соответственно обращенную к зазору (5) канавку детали (3a, 3b), в которой расположен с уплотнением зазора снабженный зубьями уплотняющий элемент (1). 11. A gas turbine installation (22) with a hot gas region (11) and a cooling gas region (8) to be sealed relative to it for cooling guide vanes (12), the regions (8, 11) being separated from each other by a plurality of the perimeter and in the axial direction of the parts (2a, 2b) and at least the first part (2a), in particular the guide vane plate (16) or the wall part (13), and the second part (2b), in particular the guide vane plate (16 ), or a wall part (13), spaced in the direction of the perimeter at the expense of t of the gap (5) and respectively have a groove in the part (3a, 3b) facing the gap (5), in which the sealing element (1) equipped with teeth is located with the gap seal. 12. Газотурбинная установка (22) по п.11, в которой зазор (5) между двумя дистанционированными по оси деталями (2a, 2b) уплотнен посредством уплотняющего элемента (1), имеющего форму полого тела, в частности гантели или восьмерки. 12. A gas turbine installation (22) according to claim 11, in which the gap (5) between two axially spaced parts (2a, 2b) is sealed by means of a sealing element (1) having the shape of a hollow body, in particular a dumbbell or figure eight.
RU98108420/06A 1995-09-29 1996-09-27 Clearance packing member and gas-turbine unit RU2162556C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19536535 1995-09-29
DE19536535.6 1995-09-29

Publications (2)

Publication Number Publication Date
RU98108420A true RU98108420A (en) 2000-02-10
RU2162556C2 RU2162556C2 (en) 2001-01-27

Family

ID=7773719

Family Applications (1)

Application Number Title Priority Date Filing Date
RU98108420/06A RU2162556C2 (en) 1995-09-29 1996-09-27 Clearance packing member and gas-turbine unit

Country Status (6)

Country Link
US (1) US5975844A (en)
EP (1) EP0852659B1 (en)
JP (1) JP3898225B2 (en)
DE (1) DE59609029D1 (en)
RU (1) RU2162556C2 (en)
WO (1) WO1997012125A2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8561438B2 (en) 2006-12-08 2013-10-22 Lg Electronics Inc. Complex washing machine and controlling method for the same

Families Citing this family (55)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0921277B1 (en) * 1997-06-04 2003-09-24 Mitsubishi Heavy Industries, Ltd. Seal structure between gas turbine discs
JP4502517B2 (en) * 1999-03-24 2010-07-14 シーメンス アクチエンゲゼルシヤフト Guide vanes and guide vane rings of fluid machinery
EP1118806A1 (en) * 2000-01-20 2001-07-25 Siemens Aktiengesellschaft Thermally charged wall structure and method to seal gaps in such a structure
JP2002201913A (en) 2001-01-09 2002-07-19 Mitsubishi Heavy Ind Ltd Split wall of gas turbine and shroud
US6568692B2 (en) * 2001-03-02 2003-05-27 Honeywell International, Inc. Low stress seal
GB0108398D0 (en) * 2001-04-04 2001-05-23 Siemens Ag Seal element for sealing a gap and combustion turbine having a seal element
US7080513B2 (en) * 2001-08-04 2006-07-25 Siemens Aktiengesellschaft Seal element for sealing a gap and combustion turbine having a seal element
GB2385642B (en) * 2001-12-22 2004-01-14 Alstom Membrane seals
DE10209295B4 (en) 2002-03-01 2010-12-09 Alstom Technology Ltd. Gap seal in a gas turbine
US6733234B2 (en) 2002-09-13 2004-05-11 Siemens Westinghouse Power Corporation Biased wear resistant turbine seal assembly
US6883807B2 (en) 2002-09-13 2005-04-26 Seimens Westinghouse Power Corporation Multidirectional turbine shim seal
US7562880B2 (en) * 2004-02-09 2009-07-21 Siemens Energy, Inc. Seal usable between thermally movable components
JP4495481B2 (en) * 2004-02-18 2010-07-07 イーグル・エンジニアリング・エアロスペース株式会社 Sealing device
DE102004016467A1 (en) * 2004-03-31 2005-10-20 Alstom Technology Ltd Baden Gap seal for sealing a gap between two adjacent components
US20050242526A1 (en) * 2004-04-30 2005-11-03 Stefan Dahlke Hot gas seal
US8714565B1 (en) 2005-01-27 2014-05-06 Parker-Hannifim Corporation Seal
CA2598987C (en) * 2005-02-15 2014-05-27 Alstom Technology Ltd Sealing element for use in a fluid-flow machine
US7527472B2 (en) * 2006-08-24 2009-05-05 Siemens Energy, Inc. Thermally sprayed conformal seal
GB2449493B (en) * 2007-05-25 2009-08-12 Rolls Royce Plc Vibration damper assembly
US8206087B2 (en) 2008-04-11 2012-06-26 Siemens Energy, Inc. Sealing arrangement for turbine engine having ceramic components
US7824150B1 (en) * 2009-05-15 2010-11-02 Florida Turbine Technologies, Inc. Multiple piece turbine airfoil
US8322977B2 (en) * 2009-07-22 2012-12-04 Siemens Energy, Inc. Seal structure for preventing leakage of gases across a gap between two components in a turbine engine
US8585354B1 (en) * 2010-01-19 2013-11-19 Florida Turbine Technologies, Inc. Turbine ring segment with riffle seal
EP2407641A1 (en) 2010-07-13 2012-01-18 Siemens Aktiengesellschaft Sealing element for sealing a gap and sealing arrangement
US9534500B2 (en) * 2011-04-27 2017-01-03 Pratt & Whitney Canada Corp. Seal arrangement for segmented gas turbine engine components
US8562000B2 (en) * 2011-05-20 2013-10-22 Siemens Energy, Inc. Turbine combustion system transition piece side seals
EP2538031A1 (en) * 2011-06-22 2012-12-26 Siemens Aktiengesellschaft Rotor with sealing element for a stationary gas turbine
US20130028713A1 (en) * 2011-07-25 2013-01-31 General Electric Company Seal for turbomachine segments
GB201117084D0 (en) * 2011-10-05 2011-11-16 Rolls Royce Plc Strip seals
WO2014146866A1 (en) 2013-03-20 2014-09-25 Siemens Aktiengesellschaft Sealing element for sealing a gap and corresponding gas turbine
DE102013205028A1 (en) * 2013-03-21 2014-09-25 Siemens Aktiengesellschaft Sealing element for sealing a gap
DE102013205031A1 (en) 2013-03-21 2014-09-25 Siemens Aktiengesellschaft Sealing element for sealing a gap
DE102013205922B4 (en) * 2013-04-04 2016-09-29 MTU Aero Engines AG Apparatus and method for fastening sealing elements
US9581036B2 (en) 2013-05-14 2017-02-28 General Electric Company Seal system including angular features for rotary machine components
EP3025030B1 (en) 2013-07-24 2021-04-21 Raytheon Technologies Corporation Trough seal for gas turbine engine
EP3039269B1 (en) * 2013-08-29 2020-05-06 United Technologies Corporation Gas turbine engine and assembly method
US10253642B2 (en) 2013-09-16 2019-04-09 United Technologies Corporation Gas turbine engine with disk having periphery with protrusions
US10301958B2 (en) 2013-09-17 2019-05-28 United Technologies Corporation Gas turbine engine with seal having protrusions
WO2015088656A1 (en) * 2013-12-12 2015-06-18 United Technologies Corporation Wrapped dog bone seal
WO2015105654A1 (en) * 2014-01-08 2015-07-16 United Technologies Corporation Clamping seal for jet engine mid-turbine frame
US9719427B2 (en) * 2014-01-21 2017-08-01 Solar Turbines Incorporated Turbine blade platform seal assembly validation
US9416675B2 (en) * 2014-01-27 2016-08-16 General Electric Company Sealing device for providing a seal in a turbomachine
EP2907977A1 (en) * 2014-02-14 2015-08-19 Siemens Aktiengesellschaft Component that can be charged with hot gas for a gas turbine and sealing assembly with such a component
EP2915960A1 (en) * 2014-03-07 2015-09-09 Siemens Aktiengesellschaft Sealing assembly for sealing a gap between two components lying flat next to each other at room temperature
EP2915959A1 (en) 2014-03-07 2015-09-09 Siemens Aktiengesellschaft Sealing assembly for sealing a gap between two components lying flat next to each other at room temperature
EP3000983A1 (en) 2014-09-29 2016-03-30 Siemens Aktiengesellschaft Sealing assembly for sealing a gap between two components that lay flat next to each other at the gap at room temperature and method for mounting and dismantling the same
CN104929700B (en) * 2015-06-05 2016-03-16 赵军 The multi-section combined comb tooth of obturaging of a kind of screw type
US9810087B2 (en) 2015-06-24 2017-11-07 United Technologies Corporation Reversible blade rotor seal with protrusions
US10822988B2 (en) * 2015-12-21 2020-11-03 Pratt & Whitney Canada Corp. Method of sizing a cavity in a part
US10648479B2 (en) 2017-10-30 2020-05-12 United Technologies Corporation Stator segment circumferential gap seal
EP3667132A1 (en) * 2018-12-13 2020-06-17 Siemens Aktiengesellschaft Seal assembly for a split housing
FR3100274B1 (en) * 2019-09-04 2022-05-06 Safran Aircraft Engines Distributor for gas turbine
EP4074941A1 (en) 2021-04-13 2022-10-19 Siemens Energy Global GmbH & Co. KG Sealing strip element and sealing arrangement comprising said sealing strip element
EP4388179A1 (en) 2021-08-19 2024-06-26 Siemens Energy Global GmbH & Co. KG Sealing device with displaceable abutment
EP4137670A1 (en) 2021-08-19 2023-02-22 Siemens Energy Global GmbH & Co. KG Sealing device with displaceable abutment

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1816293A (en) * 1925-09-30 1931-07-28 William F Oberhuber Method of making high pressure steam joints
US2991045A (en) * 1958-07-10 1961-07-04 Westinghouse Electric Corp Sealing arrangement for a divided tubular casing
US3341172A (en) * 1965-06-24 1967-09-12 Westinghouse Electric Corp Fluid machine casing sealing structure
GB1493913A (en) * 1975-06-04 1977-11-30 Gen Motors Corp Turbomachine stator interstage seal
US4537024A (en) * 1979-04-23 1985-08-27 Solar Turbines, Incorporated Turbine engines
JPS58185903A (en) * 1982-04-23 1983-10-29 Hitachi Ltd Steam turbine casing
US4452462A (en) * 1983-10-06 1984-06-05 Gray Tool Company Temperature resistant joint packing with E-shaped spring seal
US5058906A (en) * 1989-01-19 1991-10-22 Vetco Gray Inc. Integrally redundant seal
US5158430A (en) * 1990-09-12 1992-10-27 United Technologies Corporation Segmented stator vane seal
US5221096A (en) * 1990-10-19 1993-06-22 Allied-Signal Inc. Stator and multiple piece seal
US5374161A (en) * 1993-12-13 1994-12-20 United Technologies Corporation Blade outer air seal cooling enhanced with inter-segment film slot
US5509669A (en) * 1995-06-19 1996-04-23 General Electric Company Gas-path leakage seal for a gas turbine
US5586773A (en) * 1995-06-19 1996-12-24 General Electric Company Gas-path leakage seal for a gas turbine made from metallic mesh

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8561438B2 (en) 2006-12-08 2013-10-22 Lg Electronics Inc. Complex washing machine and controlling method for the same

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