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EP1918523A3 - Turbine and rotor blade with brush seal - Google Patents

Turbine and rotor blade with brush seal Download PDF

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Publication number
EP1918523A3
EP1918523A3 EP07254135A EP07254135A EP1918523A3 EP 1918523 A3 EP1918523 A3 EP 1918523A3 EP 07254135 A EP07254135 A EP 07254135A EP 07254135 A EP07254135 A EP 07254135A EP 1918523 A3 EP1918523 A3 EP 1918523A3
Authority
EP
European Patent Office
Prior art keywords
rotor
disk
land
seal
segments
Prior art date
Legal status (The legal status 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 status listed.)
Granted
Application number
EP07254135A
Other languages
German (de)
French (fr)
Other versions
EP1918523B1 (en
EP1918523A2 (en
Inventor
Ioannis Alvanos
Jr. John P. Virtue
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
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 EP1918523A2 publication Critical patent/EP1918523A2/en
Publication of EP1918523A3 publication Critical patent/EP1918523A3/en
Application granted granted Critical
Publication of EP1918523B1 publication Critical patent/EP1918523B1/en
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F05D2240/56—Brush seals

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A turbine rotor for a turbine engine includes multiple rotor disks (26) having rotor blades (28) mounted about the circumference of each of the rotor disks (26). A fluid seal extends about the circumference of each rotor disk (26) in close proximity to a stationary component (36) of the rotor to separate the space between the rotor blades (28) and a stationary component (36) into separate cavities. The fluid seal includes a seal land (44) on the rotor disk (26) and a brush seal (46) extending from the stationary component (36). A plurality of disk land segments (54) and a plurality of blade land segments (56) form the seal land (44). The disk seal segments (54) are located on the rotor disk (26) between the rotor blades (28). The blade land segments (56) are located on the rotor blades (28). After the rotor blades (28) are assembled, the blade land segments (56) and the disk land segments (54) fit together to form a segmented ring-like seal land (44) around the circumference of the rotor disk (26).
Figure imgaf001
EP07254135.2A 2006-10-20 2007-10-18 Rotor blade and corresponding turbine engine Ceased EP1918523B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/584,062 US20080095616A1 (en) 2006-10-20 2006-10-20 Fluid brush seal with segment seal land

Publications (3)

Publication Number Publication Date
EP1918523A2 EP1918523A2 (en) 2008-05-07
EP1918523A3 true EP1918523A3 (en) 2011-02-23
EP1918523B1 EP1918523B1 (en) 2019-07-24

Family

ID=38710451

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07254135.2A Ceased EP1918523B1 (en) 2006-10-20 2007-10-18 Rotor blade and corresponding turbine engine

Country Status (2)

Country Link
US (1) US20080095616A1 (en)
EP (1) EP1918523B1 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8794918B2 (en) 2011-01-07 2014-08-05 General Electric Company System for adjusting brush seal segments in turbomachine
US9121297B2 (en) 2011-03-28 2015-09-01 General Electric Company Rotating brush seal
US9255486B2 (en) 2011-03-28 2016-02-09 General Electric Company Rotating brush seal
DE102011083814A1 (en) 2011-09-30 2013-04-04 Mtu Aero Engines Gmbh Segmented component
FR2988129B1 (en) * 2012-03-15 2015-12-25 Snecma SEALING SYSTEM FOR A DISTRIBUTOR OF A CORRESPONDING TURBOMACHINE, TURBINE AND TURBOMACHINE TURBINE.
US9097129B2 (en) * 2012-05-31 2015-08-04 United Technologies Corporation Segmented seal with ship lap ends
AT13415U1 (en) * 2012-12-11 2013-12-15 Mtu Aero Engines Gmbh Sealing element with brushes and hooks
US10458266B2 (en) 2017-04-18 2019-10-29 United Technologies Corporation Forward facing tangential onboard injectors for gas turbine engines
JP1604073S (en) * 2017-06-27 2018-05-21

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3917150A (en) * 1973-11-23 1975-11-04 Rolls Royce 1971 Ltd Seals and method of manufacture thereof
US4218189A (en) * 1977-08-09 1980-08-19 Rolls-Royce Limited Sealing means for bladed rotor for a gas turbine engine
US4685863A (en) * 1979-06-27 1987-08-11 United Technologies Corporation Turbine rotor assembly
EP0572312A1 (en) * 1992-05-27 1993-12-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Sealing arrangement between stator blade rows and a rotating rotor drum
EP1340902A2 (en) * 2002-03-01 2003-09-03 General Electric Company Gas turbine with frame supporting counter rotating low pressure turbine rotors

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4701105A (en) * 1986-03-10 1987-10-20 United Technologies Corporation Anti-rotation feature for a turbine rotor faceplate
US5622698A (en) * 1990-06-08 1997-04-22 Miami University Method and composition for increasing the supercooling point in invertebrates
US5310319A (en) * 1993-01-12 1994-05-10 United Technologies Corporation Free standing turbine disk sideplate assembly
US5522698A (en) * 1994-04-29 1996-06-04 United Technologies Corporation Brush seal support and vane assembly windage cover
DE10318852A1 (en) * 2003-04-25 2004-11-11 Rolls-Royce Deutschland Ltd & Co Kg Main gas duct inner seal of a high pressure turbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3917150A (en) * 1973-11-23 1975-11-04 Rolls Royce 1971 Ltd Seals and method of manufacture thereof
US4218189A (en) * 1977-08-09 1980-08-19 Rolls-Royce Limited Sealing means for bladed rotor for a gas turbine engine
US4685863A (en) * 1979-06-27 1987-08-11 United Technologies Corporation Turbine rotor assembly
EP0572312A1 (en) * 1992-05-27 1993-12-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Sealing arrangement between stator blade rows and a rotating rotor drum
EP1340902A2 (en) * 2002-03-01 2003-09-03 General Electric Company Gas turbine with frame supporting counter rotating low pressure turbine rotors

Also Published As

Publication number Publication date
EP1918523B1 (en) 2019-07-24
EP1918523A2 (en) 2008-05-07
US20080095616A1 (en) 2008-04-24

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