MXPA05007887A - Estructura de pared para restringir una trayectoria de gas caliente. - Google Patents

Estructura de pared para restringir una trayectoria de gas caliente.

Info

Publication number
MXPA05007887A
MXPA05007887A MXPA05007887A MXPA05007887A MXPA05007887A MX PA05007887 A MXPA05007887 A MX PA05007887A MX PA05007887 A MXPA05007887 A MX PA05007887A MX PA05007887 A MXPA05007887 A MX PA05007887A MX PA05007887 A MXPA05007887 A MX PA05007887A
Authority
MX
Mexico
Prior art keywords
flow path
gas flow
hot gas
wall structure
channel
Prior art date
Application number
MXPA05007887A
Other languages
English (en)
Inventor
Ulrich Rathmann
Original Assignee
Alstom Technology Ltd
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=34981354&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=MXPA05007887(A) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Alstom Technology Ltd filed Critical Alstom Technology Ltd
Publication of MXPA05007887A publication Critical patent/MXPA05007887A/es

Links

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)

Abstract

La invencion se refiere a una estructura (1) de pared para restringir una trayectoria (4) de gas caliente en una turbina de gas o una camara de combustion, con al menos dos segmentos de pared que en una zona de union se disponen adyacentes uno a otro, siendo que - en la zona (5) de union, una cara (6) frontal de uno de los segmentos (2) de pared se dispone opuesta a una cara (7) frontal del otro segmento (3) de pared, - que las caras (6, 7) frontales estan espaciadas una de otra, y forman entre ellas un intersticio (8) que conduce de un lado (9) interior de los segmentos (2, 3) de pared orientado hacia la trayectoria (4) de gas caliente a un lado (10) exterior de los segmentos (2, 3) de pared alejado de la trayectoria (4) de gas caliente, - que las caras (6, 7) frontales tienen en cada caso una ranura (11) de recepcion abierta en direccion al intersticio (8), - que en las ranuras (11) de recepcion se inserta un elemento (15) de obturacion que puentea el intersticio (8). Para permitir diferentes posiciones relativas entre los segmentos (2, 3) de pared, la relacion de la distancia (A) entre dos paredes (14) de ranura con respecto al grosor (S) del elemento (15) de obturacion es superior o igual a 1:1.
MXPA05007887A 2004-07-30 2005-07-25 Estructura de pared para restringir una trayectoria de gas caliente. MXPA05007887A (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102004037356.6A DE102004037356B4 (de) 2004-07-30 2004-07-30 Wandstruktur zur Begrenzung eines Heißgaspfads

Publications (1)

Publication Number Publication Date
MXPA05007887A true MXPA05007887A (es) 2006-03-02

Family

ID=34981354

Family Applications (1)

Application Number Title Priority Date Filing Date
MXPA05007887A MXPA05007887A (es) 2004-07-30 2005-07-25 Estructura de pared para restringir una trayectoria de gas caliente.

Country Status (6)

Country Link
US (2) US20060137351A1 (es)
EP (1) EP1621736B2 (es)
KR (1) KR101259179B1 (es)
DE (1) DE102004037356B4 (es)
ES (1) ES2421907T5 (es)
MX (1) MXPA05007887A (es)

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US7377742B2 (en) * 2005-10-14 2008-05-27 General Electric Company Turbine shroud assembly and method for assembling a gas turbine engine
CH698921B1 (de) * 2006-11-10 2009-12-15 Alstom Technology Ltd Strömungsmaschine.
ATE537333T1 (de) * 2009-01-28 2011-12-15 Alstom Technology Ltd Streifendichtung und verfahren zum entwurf einer streifendichtung
US8287234B1 (en) * 2009-08-20 2012-10-16 Florida Turbine Technologies, Inc. Turbine inter-segment mate-face cooling design
US8215115B2 (en) * 2009-09-28 2012-07-10 Hamilton Sundstrand Corporation Combustor interface sealing arrangement
US8371800B2 (en) * 2010-03-03 2013-02-12 General Electric Company Cooling gas turbine components with seal slot channels
FR2974839B1 (fr) * 2011-05-04 2015-08-14 Snecma Anneau sectorise de turbine a orifices de ventilation, et turbomachine equipee d'un tel anneau
US9534783B2 (en) * 2011-07-21 2017-01-03 United Technologies Corporation Insert adjacent to a heat shield element for a gas turbine engine combustor
US8845285B2 (en) * 2012-01-10 2014-09-30 General Electric Company Gas turbine stator assembly
US8905708B2 (en) * 2012-01-10 2014-12-09 General Electric Company Turbine assembly and method for controlling a temperature of an assembly
US10472981B2 (en) 2013-02-26 2019-11-12 United Technologies Corporation Edge treatment for gas turbine engine component
EP3042045A4 (en) * 2013-09-06 2017-06-14 United Technologies Corporation Canted boas intersegment geometry
US10934871B2 (en) 2015-02-20 2021-03-02 Rolls-Royce North American Technologies Inc. Segmented turbine shroud with sealing features
US10808576B2 (en) 2017-02-06 2020-10-20 General Electric Company Methods of replacing seals in exhaust frames of turbine systems and related components
GB2559804A (en) * 2017-02-21 2018-08-22 Siemens Ag Heatshield for a gas turbine
US10815807B2 (en) * 2018-05-31 2020-10-27 General Electric Company Shroud and seal for gas turbine engine
US11852018B1 (en) * 2022-08-10 2023-12-26 General Electric Company Turbine nozzle with planar surface adjacent side slash face

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US3752598A (en) * 1971-11-17 1973-08-14 United Aircraft Corp Segmented duct seal
GB2076071B (en) * 1980-05-16 1983-11-02 United Technologies Corp Flow directing assembly for a gas turbine engine
IT1164225B (it) * 1983-05-13 1987-04-08 Anic Spa Analoghi retro-invertiti del pentapeptide potenziante la bradichina bpp5a e metodi per la loro preparazione
US4650394A (en) * 1984-11-13 1987-03-17 United Technologies Corporation Coolable seal assembly for a gas turbine engine
US5154577A (en) * 1991-01-17 1992-10-13 General Electric Company Flexible three-piece seal assembly
US5375973A (en) * 1992-12-23 1994-12-27 United Technologies Corporation Turbine blade outer air seal with optimized cooling
US5476363A (en) * 1993-10-15 1995-12-19 Charles E. Sohl Method and apparatus for reducing stress on the tips of turbine or compressor blades
US5374161A (en) * 1993-12-13 1994-12-20 United Technologies Corporation Blade outer air seal cooling enhanced with inter-segment film slot
DE69802848T2 (de) * 1997-01-30 2002-08-08 Snecma Moteurs, Paris Dichtung bestehend aus in einem Schlitz gestapelten Gleitstreifen
JP3999395B2 (ja) * 1999-03-03 2007-10-31 三菱重工業株式会社 ガスタービン分割環
GB2356022B (en) † 1999-11-02 2003-12-10 Rolls Royce Plc Gas turbine engines
US6702549B2 (en) * 2000-03-02 2004-03-09 Siemens Aktiengesellschaft Turbine installation
EP1286021B1 (de) * 2001-08-21 2010-10-27 Alstom Technology Ltd Verfahren zur Herstellung einer nutförmigen Ausnehmung sowie eine diesbezügliche nutförmigen Ausnehmung
US6722846B2 (en) * 2002-07-30 2004-04-20 General Electric Company Endface gap sealing of steam turbine bucket tip static seal segments and retrofitting thereof
US7033138B2 (en) * 2002-09-06 2006-04-25 Mitsubishi Heavy Industries, Ltd. Ring segment of gas turbine
US6910854B2 (en) † 2002-10-08 2005-06-28 United Technologies Corporation Leak resistant vane cluster
ES2289256T3 (es) * 2003-02-19 2008-02-01 Alstom Technology Ltd Sistema de estanqueidad, particularmente para los segmentos de alabes de turbinas de gas.
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Also Published As

Publication number Publication date
EP1621736B1 (de) 2013-04-17
KR101259179B1 (ko) 2013-04-29
EP1621736B2 (de) 2017-08-16
EP1621736A3 (de) 2012-02-22
KR20060048985A (ko) 2006-05-18
US9353638B2 (en) 2016-05-31
EP1621736A2 (de) 2006-02-01
DE102004037356A1 (de) 2006-03-23
US20060137351A1 (en) 2006-06-29
US20090155054A1 (en) 2009-06-18
DE102004037356B4 (de) 2017-11-23
ES2421907T3 (es) 2013-09-06
ES2421907T5 (es) 2018-01-09

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