MX174048B - Metodo mejorado de recubrimiento preliminar de un sistema de sello desgastable de turbina de gas - Google Patents

Metodo mejorado de recubrimiento preliminar de un sistema de sello desgastable de turbina de gas

Info

Publication number
MX174048B
MX174048B MX018857A MX1885789A MX174048B MX 174048 B MX174048 B MX 174048B MX 018857 A MX018857 A MX 018857A MX 1885789 A MX1885789 A MX 1885789A MX 174048 B MX174048 B MX 174048B
Authority
MX
Mexico
Prior art keywords
coating method
gas turbine
seal system
preliminary coating
wearable seal
Prior art date
Application number
MX018857A
Other languages
English (en)
Inventor
Charles Carter Mccomas
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of MX174048B publication Critical patent/MX174048B/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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)

Abstract

La presente invención se refiere a en el método de recubrimiento preliminar de un sistema de sello desgastable, del tipo que incluye un sello desgastable ubicado y adaptado para interactuar con un componente de máquina relativamente en movimiento, la mejora caracterizada porque comprende: aplicar una capa delgada de partículas coloidales de cerámica al componente en movimiento, siendo dichos componentes de cerámica no humedecibles por los constituyentes del sello desgastable mediante lo cual las interacciones adversas entre el sello y el componente en movimiento son reducidas al mínimo durante el funcionamiento inicial de la máquina.
MX018857A 1988-12-21 1989-12-21 Metodo mejorado de recubrimiento preliminar de un sistema de sello desgastable de turbina de gas MX174048B (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/287,221 US5017402A (en) 1988-12-21 1988-12-21 Method of coating abradable seal assembly

Publications (1)

Publication Number Publication Date
MX174048B true MX174048B (es) 1994-04-18

Family

ID=23101962

Family Applications (1)

Application Number Title Priority Date Filing Date
MX018857A MX174048B (es) 1988-12-21 1989-12-21 Metodo mejorado de recubrimiento preliminar de un sistema de sello desgastable de turbina de gas

Country Status (10)

Country Link
US (1) US5017402A (es)
EP (1) EP0382993B1 (es)
JP (1) JPH02211304A (es)
CN (1) CN1021843C (es)
AU (1) AU623459B2 (es)
BR (1) BR8906606A (es)
DE (1) DE68906780T2 (es)
IL (1) IL92722A (es)
MX (1) MX174048B (es)
RU (1) RU1799424C (es)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5932356A (en) * 1996-03-21 1999-08-03 United Technologies Corporation Abrasive/abradable gas path seal system
US5951892A (en) * 1996-12-10 1999-09-14 Chromalloy Gas Turbine Corporation Method of making an abradable seal by laser cutting
EP1152124A1 (de) * 2000-05-04 2001-11-07 Siemens Aktiengesellschaft Dichtungsanordnung
US20020139741A1 (en) * 2001-03-27 2002-10-03 Henry Kopf Integral gasketed filtration cassette article and method of making the same
US6688867B2 (en) 2001-10-04 2004-02-10 Eaton Corporation Rotary blower with an abradable coating
CH696854A5 (de) 2003-04-14 2007-12-31 Alstom Technology Ltd Thermische Turbomaschine.
US7732058B2 (en) * 2005-03-16 2010-06-08 Diamond Innovations, Inc. Lubricious coatings
US8017240B2 (en) * 2006-09-28 2011-09-13 United Technologies Corporation Ternary carbide and nitride thermal spray abradable seal material
US20080260523A1 (en) * 2007-04-18 2008-10-23 Ioannis Alvanos Gas turbine engine with integrated abradable seal
US20080260522A1 (en) * 2007-04-18 2008-10-23 Ioannis Alvanos Gas turbine engine with integrated abradable seal and mount plate
DE102007024591B4 (de) 2007-05-25 2012-10-18 Mtu Aero Engines Gmbh Gasturbine mit einem Stator, einem Rotor sowie einer Dichteinrichtung
US20130236302A1 (en) * 2012-03-12 2013-09-12 Charles Alexander Smith In-situ gas turbine rotor blade and casing clearance control
FR2994397B1 (fr) 2012-08-07 2014-08-01 Snecma Revetement en materiau abradable a faible rugosite de surface
US20150078900A1 (en) * 2013-09-19 2015-03-19 David B. Allen Turbine blade with airfoil tip having cutting tips
EP3068997B1 (en) 2013-11-11 2021-12-29 Raytheon Technologies Corporation Segmented seal for gas turbine engine
US10634055B2 (en) 2015-02-05 2020-04-28 United Technologies Corporation Gas turbine engine having section with thermally isolated area
US9920652B2 (en) 2015-02-09 2018-03-20 United Technologies Corporation Gas turbine engine having section with thermally isolated area

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4424001A (en) * 1981-12-04 1984-01-03 Westinghouse Electric Corp. Tip structure for cooled turbine rotor blade
EP0187612B1 (en) * 1984-12-24 1990-09-12 United Technologies Corporation Abradable seal having particulate erosion resistance
US4884820A (en) * 1987-05-19 1989-12-05 Union Carbide Corporation Wear resistant, abrasive laser-engraved ceramic or metallic carbide surfaces for rotary labyrinth seal members

Also Published As

Publication number Publication date
US5017402A (en) 1991-05-21
JPH02211304A (ja) 1990-08-22
IL92722A0 (en) 1990-09-17
BR8906606A (pt) 1990-09-04
EP0382993B1 (en) 1993-05-26
CN1043773A (zh) 1990-07-11
EP0382993A1 (en) 1990-08-22
DE68906780T2 (de) 1993-09-02
DE68906780D1 (de) 1993-07-01
CN1021843C (zh) 1993-08-18
IL92722A (en) 1992-09-06
AU623459B2 (en) 1992-05-14
RU1799424C (ru) 1993-02-28
AU4615889A (en) 1990-06-28

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