EP1918523B1 - Laufschaufel und zugehöriges turbinentriebwerk - Google Patents

Laufschaufel und zugehöriges turbinentriebwerk Download PDF

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Publication number
EP1918523B1
EP1918523B1 EP07254135.2A EP07254135A EP1918523B1 EP 1918523 B1 EP1918523 B1 EP 1918523B1 EP 07254135 A EP07254135 A EP 07254135A EP 1918523 B1 EP1918523 B1 EP 1918523B1
Authority
EP
European Patent Office
Prior art keywords
land
blade
disk
seal
rotor
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.)
Ceased
Application number
EP07254135.2A
Other languages
English (en)
French (fr)
Other versions
EP1918523A3 (de
EP1918523A2 (de
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/de
Publication of EP1918523A3 publication Critical patent/EP1918523A3/de
Application granted granted Critical
Publication of EP1918523B1 publication Critical patent/EP1918523B1/de
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

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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

Definitions

  • the invention generally relates to an arrangement for fluid seals within a gas turbine engine.
  • Turbine engines include high and low pressure rotor spools comprising multiple rotor disks. Fluid seals are formed integrally into each rotor disk to contact stator components, such as a tangential on-board injector. The seals restrict leakage of compressed air from between the stator component and the rotor disks and separate the lower pressure gaspath air from high pressure air used for cooling.
  • the fluid seal Due to the rotor disk geometry, multiple machining passes are required to produce the thin sectional area required for the fluid seal. This is unduly complex. Also, during operation of the engine, the fluid seal may contact an abradable material on the stationary components, causing wear. Because the fluid seal is integrally formed with the rotor disk of the compressor, the entire rotor disk must be repaired or replaced when the fluid seal has worn.
  • US 4218189 discloses a rotor blade comprising: a blade platform having a blade root extending from the blade platform for receiving in a blade slot of a rotor disk; and a blade land segment extending from the blade root, wherein the blade land segment defines a seal land for contacting a brush seal extending from a stationary turbine engine component.
  • a similar form of rotor blade is disclosed in US 4685863 .
  • a rotor blade as defined by claim 1.
  • the invention also extends to a turbine engine as defined by claim 3.
  • the interlocking feature reduces circumferential and radial fluid leaks.
  • Figure 1 is a schematic view of a turbine engine 10. Air is pulled into the turbine engine 10 by a fan 12 and flows through a low pressure compressor 14 and a high pressure compressor 16. Fuel is mixed with the air, and combustion occurs within the combustor 18. Exhaust from combustion flows through a high pressure turbine 20 and a low pressure turbine 22 prior to leaving the engine through an exhaust nozzle 24.
  • FIG. 2 illustrates a portion of a cross-section of a typical turbine engine turbine, showing a rotor disk 26, which is one of several defining a rotor.
  • a rotor disk 26 rotates about an axis A located along the longitudinal centerline of the turbine engine 10.
  • a plurality of rotor blades 28 are mounted about the circumference of each rotor disk 26.
  • a plurality of stator vanes 30 extend between the rotor blades 28 of axially adjacent rotor disks 26, as shown.
  • Each rotor disk 26 includes a disk rim 32.
  • the disk rim 32 secures the rotor blades 28.
  • a fluid seal 34 is located between the rotor disk 26 and a stationary part of the turbine, such as a stator vane, a support or a tangential on-board injector (TOBI) 36.
  • the fluid seal 34 defines a cavity 38 located axially above the fluid seal 34 and further defined by the stator vane 30 and the rotor blade 28. Air within the cavity 38 is flowing circumferentially about the axis A of rotation for the rotor disk 26.
  • An interior cavity 40 is located axially below the fluid seal 34 and defined by the rotor disk 26 and the stationary component 36.
  • a nozzle 42 leading from the TOBI 36 allows high pressure cooling air to reach the interior cavity 40 to cool the rotor disk 26.
  • Figure 3 illustrates an enlarged view of the example fluid seal 34.
  • the fluid seal 34 includes a segmented seal land 44 and a brush seal 46.
  • the seal land 44 extends about the circumference of the disk rim 32.
  • the seal land 44 is preferably formed of the same material as the rotor disk 26, such as any ferrous, nickel, or ceramic materials.
  • the seal land 44 may also be coated with a wear resistant hard facing or coating to reduce wear.
  • the seal land 44 is in contact with the brush seal 46 extending from the stationary component 36.
  • the seal land 44 is illustrated as extending axially toward the stationary component 36 along the axis A of the turbine engine 10. However, the seal land 44 can extend toward any stationary component of the turbine engine 10.
  • the brush seal 46 includes an axial locking feature 48 to retain the brush seal 46 to the stationary component 36 and to prevent axial movement of the brush seal 46 along the axis A of the turbine engine 10.
  • the brush seal 46 extends in a radially inward direction from the stationary component 36 and has bristles 50 which contact a radial face 52 of the seal land 44.
  • the bristles 50 are wire bristles or the like to provide radial resilience and reduce wear on the seal land 44.
  • the segmented seal land 44 includes a plurality of disk land segments 54 and a plurality of blade land segments 56. Spaced around the circumference of the disk rim 32, segments 54 and 56 fit together to form a segmented, ring-like seal land about the disk rim 32.
  • the disk land segments 54 are integrally formed with the disk rim 32 between the rotor blades 28.
  • the blade land segments 56 are integrally formed with the rotor blades 28.
  • the rotor blade 28 has a root 57 contoured to fit into a complementary contoured blade slot 58 in the disk rim 32. Walls 59 in the disk rim 32 define the individual blade slots 58.
  • the rotor blade 28 is loaded in the blade slot 58, and each disk land segment 54 and blade land segment 56 mate with a circumferentially adjacent land segment 54 or 56 to provide a rigid structure.
  • the individual rotor blades 28 and blade land segments 56 can be repaired or replaced.
  • use of the brush seal 46 reduces wear on the seal land 44, extending the life of the fluid seal 34 compared to the prior art abradable material.
  • each disk land segment 54 has a first interlocking feature 62
  • each blade land segment 56 has a second interlocking feature 60.
  • the first interlocking feature 62 and the second interlocking feature 60 interfit to align the disk land segments 54, with the blade land segments 56.
  • the first interlocking feature 62 is a protrusion extending from the disk land segment 54
  • the second interlocking feature 60 is a protrusion extending from the blade land segment 56.
  • first interlocking feature 62and the second interlocking feature can be tongue and groove or other interfitting elements.
  • Figure 5 illustrates a portion of a cross-section of another example embodiment of a turbine including a rotor disk 26 defining a turbine rotor.
  • a fluid seal 102 is located between the rotor disk 26 and a stationary component 36.
  • the fluid seal 102 defines a cavity 38 located axially above the fluid seal 102 and further defined by the stator vane 30 and the rotor blade 28.
  • An interior cavity 40 is located axially below the fluid seal 102 and defined by the rotor disk 26 and the stationary component 36.
  • a nozzle 42 leading from the stationary component 36 allows high pressure cooling air to reach the interior cavity 40 to cool the rotor disk 26.
  • Figure 6 illustrates an enlarged view of the example fluid seal 102.
  • the fluid seal 102 includes a seal land 104 and a brush seal 106.
  • the seal land 104 extends about the circumference of the disk rim 32.
  • the seal land 104 is preferably formed of the same material as the rotor disk 26, such as any ferrous or nickel materials.
  • the seal land 104 may also be coated with a wear resistant hard facing or coating to reduce wear.
  • the seal land 104 is in contact with the brush seal 106 extending axially from the stationary component 36.
  • the seal land 104 is illustrated as extending axially toward the stationary component 36 along the axis A of the turbine engine 10.
  • the brush seal 106 includes an axial locking feature 108 to retain the brush seal 106 to the stationary component 36 and to prevent axial movement of the brush seal 106 along the axis A of the turbine engine 10.
  • the brush seal 106 extends in an axial direction from the stationary component 36 and has bristles 110 which contact a radial face 112 of the seal land 104.
  • the bristles 110 are wire bristles or the like to provide radial resilience and to reduce wear on the seal land 104.
  • the seal land 104 includes a plurality of disk land segments 114 and a plurality of blade land segments 116 spaced around the circumference of the disk rim 32 and fitting together to form a solid seal land 104 about the disk rim 32.
  • the disk land segments 114 are integrally formed with the disk rim 32 between the rotor blades 28.
  • the blade land segments 116 are integrally formed with the rotor blades 28.
  • the rotor blade 28 is loaded into a blade slot 58 in the disk rim 32. Walls 59 in the disk rim 32 define the individual blade slots 58.
  • each disk land segment 114 and blade land segment 116 mate with a circumferentially adjacent land segment 114 or 116 to provide a rigid structure.
  • the individual rotor blades 28 and blade land segments 116 can be repaired or replaced.
  • the brush seal 106 reduces wear on the seal land 104 extending the life of the fluid seal 102.
  • each disk land segment 114 can have a first interlocking feature 62, and each blade land segment 116 can have a second interlocking feature 60 as illustrated in Figure 4 of the previous example.
  • the first interlocking feature and the second interlocking feature interfit to align the disk land segments 114 with the blade land segments 116.
  • the first interlocking feature and the second interlocking feature can be a ship lap, a tongue and a groove or other interfitting elements.
  • the example embodiment discloses an arrangement of assembling fluid seal segments onto a rotor disk for a turbine, the arrangement may be used for any rotor and seal assembly.

Landscapes

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

Claims (10)

  1. Laufschaufel (28), umfassend:
    eine Schaufelplattform, die einen Schaufelfuß (57), der sich von der Schaufelplattform erstreckt, zum Aufnehmen in einer Schaufelnut (58) einer Rotorscheibe (26) aufweist; und
    ein Schaufelstegsegment (56, 116), das sich von dem Schaufelfuß (57) erstreckt, wobei das Schaufelstegsegment (56, 116) einen Dichtungssteg zum Berühren einer Bürstendichtung (46, 106) definiert, die sich von einer stationären Turbinentriebwerkskomponente (36) erstreckt,
    wobei das Schaufelstegsegment (56, 116) zwei erste Verriegelungsmerkmale (62) jeweils zum Verriegeln mit jeweiligen zweiten Verriegelungsmerkmalen (60) eines jeweiligen Scheibenstegsegments (54; 114) der Rotorscheibe (26) beinhaltet, wobei mindestens ein Abschnitt jedes ersten Verriegelungsmerkmals (62) sich mit mindestens einem Abschnitt des jeweiligen zweiten Verriegelungsmerkmals (60) überschneidet, und dadurch gekennzeichnet, dass das Schaufelstegsegment in Bezug auf eine radiale Achse, die sich im Wesentlichen entlang der Spanne der Laufschaufel (28) erstreckt, nicht symmetrisch ist.
  2. Laufschaufel nach Anspruch 1, wobei das Schaufelstegsegment (56; 116) mit der Laufschaufel (28) einstückig ausgebildet ist.
  3. Turbinentriebwerk (10), umfassend:
    eine Rotorscheibe (26) zum Rotieren um eine Achse, die einen Scheibenrand (32) definiert und die eine Vielzahl von Laufschaufeln (28) gemäß einem der vorhergehenden Ansprüche aufweist, die an dem Scheibenrand (32) angebracht sind;
    eine Vielzahl von Scheibenstegsegmenten (54; 114), die sich von dem Scheibenrand (32) zwischen jeder der Vielzahl von Laufschaufeln (28) erstrecken; und
    wobei die Vielzahl von Scheibenstegsegmenten (54; 114) und von Schaufelstegsegmenten (56; 116) der Vielzahl von Laufschaufeln einen Dichtungssteg (44; 104) bilden, der um einen Umfang des Scheibenrands (32) gelegen ist; und
    eine Bürstendichtung (46; 106), die sich von einer stationären Komponente (36) des Turbinentriebwerks (10) erstreckt und den Dichtungssteg (44; 104) berührt.
  4. Turbinentriebwerk nach Anspruch 3, wobei die Vielzahl von Scheibenstegsegmenten (54; 114) einstückig mit der Rotorscheibe (26) ausgebildet sind.
  5. Turbinentriebwerk nach einem der Ansprüche 3 und 4, wobei der Dichtungssteg (104) eine radiale Fläche (112) umfasst und sich die Bürstendichtung (106) axial erstreckt, um die radiale Fläche (112) zu berühren.
  6. Turbinentriebwerk nach einem der Ansprüche 3 und 4, wobei der Dichtungssteg (44) eine axiale Fläche (52) umfasst und sich die Bürstendichtung (46) radial nach innen erstreckt, um die axiale Fläche (52) zu berühren.
  7. Turbinentriebwerk nach einem der Ansprüche 3 bis 6, wobei die stationäre Komponente (36) eine tangentiale integrierte Einspritzvorrichtung ist.
  8. Turbinentriebwerk nach einem der Ansprüche 3 bis 6, wobei die Bürstendichtung (46; 106) ferner ein axiales Verriegelungsmerkmal (48; 108) zum Verhindern einer axialen Bewegung der Bürstendichtung (46; 106) umfasst.
  9. Turbinentriebwerk nach einem der Ansprüche 3 bis 8, wobei die Verriegelungsmerkmale (60, 62) auf den Scheibenstegsegmenten (54; 114) und den Schaufelstegsegmenten (56; 116) die Scheibenstegsegmente (54; 114) und die Schaufelstegsegmente (56; 116) ausrichten.
  10. Turbinentriebwerk nach Anspruch 3, wobei der Dichtungssteg (104) eine axiale Dichtung bereitstellt.
EP07254135.2A 2006-10-20 2007-10-18 Laufschaufel und zugehöriges turbinentriebwerk Ceased EP1918523B1 (de)

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 (de) 2008-05-07
EP1918523A3 EP1918523A3 (de) 2011-02-23
EP1918523B1 true EP1918523B1 (de) 2019-07-24

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ID=38710451

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Application Number Title Priority Date Filing Date
EP07254135.2A Ceased EP1918523B1 (de) 2006-10-20 2007-10-18 Laufschaufel und zugehöriges turbinentriebwerk

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US (1) US20080095616A1 (de)
EP (1) EP1918523B1 (de)

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 (de) 2011-09-30 2013-04-04 Mtu Aero Engines Gmbh Segmentiertes Bauteil
FR2988129B1 (fr) * 2012-03-15 2015-12-25 Snecma Systeme d'etancheite pour un distributeur d'une turbine de turbomachine, turbine et turbomachine correspondantes.
US9097129B2 (en) * 2012-05-31 2015-08-04 United Technologies Corporation Segmented seal with ship lap ends
AT13415U1 (de) * 2012-12-11 2013-12-15 Mtu Aero Engines Gmbh Dichtelement mit Bürsten und Haken
US10458266B2 (en) 2017-04-18 2019-10-29 United Technologies Corporation Forward facing tangential onboard injectors for gas turbine engines
JP1604073S (de) * 2017-06-27 2018-05-21

Family Cites Families (10)

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Publication number Priority date Publication date Assignee Title
GB1450553A (en) * 1973-11-23 1976-09-22 Rolls Royce Seals and a 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
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
FR2691749B1 (fr) * 1992-05-27 1994-07-22 Snecma Dispositif d'etancheite entre des etages d'aubes et un tambour tournant notamment pour eviter les fuites autour des etages d'aubes de redresseur .
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
US6619030B1 (en) * 2002-03-01 2003-09-16 General Electric Company Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors
DE10318852A1 (de) * 2003-04-25 2004-11-11 Rolls-Royce Deutschland Ltd & Co Kg Hauptgaskanal-Innendichtung einer Hochdruckturbine

Non-Patent Citations (1)

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Title
None *

Also Published As

Publication number Publication date
EP1918523A3 (de) 2011-02-23
US20080095616A1 (en) 2008-04-24
EP1918523A2 (de) 2008-05-07

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