BR8906606A - Revestimento preliminar de vedacao abrasivel para turbina a gas - Google Patents

Revestimento preliminar de vedacao abrasivel para turbina a gas

Info

Publication number
BR8906606A
BR8906606A BR898906606A BR8906606A BR8906606A BR 8906606 A BR8906606 A BR 8906606A BR 898906606 A BR898906606 A BR 898906606A BR 8906606 A BR8906606 A BR 8906606A BR 8906606 A BR8906606 A BR 8906606A
Authority
BR
Brazil
Prior art keywords
abrasively
preliminary
gas turbine
seal coating
seal
Prior art date
Application number
BR898906606A
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 BR8906606A publication Critical patent/BR8906606A/pt

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)
BR898906606A 1988-12-21 1989-12-20 Revestimento preliminar de vedacao abrasivel para turbina a gas BR8906606A (pt)

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
BR8906606A true BR8906606A (pt) 1990-09-04

Family

ID=23101962

Family Applications (1)

Application Number Title Priority Date Filing Date
BR898906606A BR8906606A (pt) 1988-12-21 1989-12-20 Revestimento preliminar de vedacao abrasivel para turbina a gas

Country Status (10)

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

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
US20080260522A1 (en) * 2007-04-18 2008-10-23 Ioannis Alvanos Gas turbine engine with integrated abradable seal and mount plate
US20080260523A1 (en) * 2007-04-18 2008-10-23 Ioannis Alvanos Gas turbine engine with integrated abradable seal
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
WO2015119687A2 (en) 2013-11-11 2015-08-13 United 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
DE3579684D1 (de) * 1984-12-24 1990-10-18 United Technologies Corp Abschleifbare dichtung mit besonderem erosionswiderstand.
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
IL92722A (en) 1992-09-06
DE68906780D1 (de) 1993-07-01
JPH02211304A (ja) 1990-08-22
RU1799424C (ru) 1993-02-28
US5017402A (en) 1991-05-21
EP0382993B1 (en) 1993-05-26
EP0382993A1 (en) 1990-08-22
MX174048B (es) 1994-04-18
AU623459B2 (en) 1992-05-14
AU4615889A (en) 1990-06-28
IL92722A0 (en) 1990-09-17
CN1043773A (zh) 1990-07-11
DE68906780T2 (de) 1993-09-02
CN1021843C (zh) 1993-08-18

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Legal Events

Date Code Title Description
FF Decision: intention to grant
KD Notifcation of receipt (letter patent)
FG Letter patent granted
B21A Patent or certificate of addition expired [chapter 21.1 patent gazette]

Free format text: PATENTE EXTINTA EM 20/12/2004