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WO1997001695A1 - Disque de turbine dont les pales sont dotees de plaques d'etancheite - Google Patents

Disque de turbine dont les pales sont dotees de plaques d'etancheite Download PDF

Info

Publication number
WO1997001695A1
WO1997001695A1 PCT/EP1996/002375 EP9602375W WO9701695A1 WO 1997001695 A1 WO1997001695 A1 WO 1997001695A1 EP 9602375 W EP9602375 W EP 9602375W WO 9701695 A1 WO9701695 A1 WO 9701695A1
Authority
WO
WIPO (PCT)
Prior art keywords
seal plates
turbine disc
turbine
seal
disc
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
PCT/EP1996/002375
Other languages
English (en)
Inventor
Neil Milner Evans
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
BMW Rolls Royce GmbH
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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
Publication of WO1997001695A1 publication Critical patent/WO1997001695A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades 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
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • the invention relates to a turbine disc with a large number of inset blades, whose root sections are held and sealed by means of several inset seal plates inserted between the disc and blade root flanges in the direction of the circumference.
  • DE 41 10 214A1 gives an example of the previously proposed state of the technology.
  • the seal plates mentioned above are set particularly into slots in the blade root flanges and into the turbine disc and act, since they are pressed by the fluid-pressure conditions within the turbine against the slot walls, especially as the sealing of the blade root sections. Any fluid leakage flow over the blade root sections on the turbine blades should thereby be avoided. However a small leakage flow can still arise and especially through the gaps between the individual seal plates. It is therefore attempted to make these gaps as small as possible, on the other hand however account must be taken of their heat expansion behaviour in the dimensioning of the individual components. Further the seal plates can deform to a small extent due to the load or stress conditions present, so that for this reason an unwanted increase of the gap size between individual seal plates can arise.
  • the seal plates are cast in such a manner that they exhibit a directionally soldified crystal structure in the circumferential direction.
  • the casting technique for directionally solidified casting is known in turbine blades.
  • An example is described in DE-OS 29 01 724. If then this known casting technique is applied to the seal plates in the manner described, then this results in a reduced modulus of elasticity (Young's Modulus), due to the crystal grains being oriented in the circumferential direction. Because of this lower peripheral loads or stresses are set up in the annularly adjacent seal plates, which again generate the radial loads or stresses explained above in the blade root flanges, the blade root sections and the turbine disc itself only to a reduced extent. The reduced peripheral load or stress again results in lower plastic deformation of the seal plates, so that an improved sealing is thus set up, since the increase in the gaps between the seal plates now occurs to a lesser extent.
  • FIG 1 a turbine disc 1 is shown in section.
  • this turbine disc 1 distributed around the circumference, several blades 2 are assembled, as is known.
  • the root section 3 of the blade 2 shown exhibits a fir tree profile.
  • the blades are held using several seal plates 4, which are assembled similarly in a circumferential direction between the turbine dire 1 and the blade root flanges 5 and thus form an essentially closed ring.
  • Figure 2 shows the elevation X from Figure 1 of an individual seal plate 4.
  • each seal plate On both edges 6a, 6b of each seal plate lie the neighbouring seal plates 4, which are not shown, so that, however, a narrow gap appears between neighbouring seal plates, which was explained fully in the introductory description and via which a leakage air flow can penetrate the necessary fluid in the turbine.
  • the seal plates are cast in such a manner that they exhibit a directionally solidified crystal structure, i.e. in the direction of the arrow 7.
  • the sealing effect is noticeably increased thereby, and the stress loading on the individual components noticeably reduced. An increased lifetime for these components results.
  • protective strips 9 can be provided to prevent friction wear. These protective strips 9 are preferably provided between the rear side of each seal plate 4 and the corresponding slot wall, since the chief pressure conditions arise on this side of every seal plate 4. These protective strips 9 can be renewed at a drive unit overhaul, however these as well as other details can be formed deviating completely from the example of embodiment shown, without abandoning the scope of the claim.

Landscapes

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

Abstract

Les pales (2) d'un disque de turbine (1) sont maintenues dans le sens axial par des plaques d'étanchéité qui empêchent les pertes par fuite au niveau du pied (3) desdites pales. Ces plaques d'étanchéité (4) sont moulées de sorte qu'elles présentent une structure cristalline solidifiée dans le sens de la circonférence (7). Ainsi, la charge de contraintes sur les composants séparés est réduite ainsi que la déformation des plaques d'étanchéité dans le sens de la circonférence (7), l'espace entre les plaques d'étanchéité (4) restant faible pendant la durée de vie de la turbine.
PCT/EP1996/002375 1995-06-26 1996-06-01 Disque de turbine dont les pales sont dotees de plaques d'etancheite Ceased WO1997001695A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9512965.6 1995-06-26
GB9512965A GB2302711A (en) 1995-06-26 1995-06-26 A turbine disc with blade seal plates

Publications (1)

Publication Number Publication Date
WO1997001695A1 true WO1997001695A1 (fr) 1997-01-16

Family

ID=10776675

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP1996/002375 Ceased WO1997001695A1 (fr) 1995-06-26 1996-06-01 Disque de turbine dont les pales sont dotees de plaques d'etancheite

Country Status (2)

Country Link
GB (1) GB2302711A (fr)
WO (1) WO1997001695A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1371814A1 (fr) * 2002-06-11 2003-12-17 ALSTOM (Switzerland) Ltd Arrangement des joints d'étanchéité dans le rotor d'une turbine à gaz
WO2010088881A1 (fr) 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Dispositif d'étanchéité sur l'arbre à aubes d'un étage de rotor d'une turbomachine axiale

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2321862T3 (es) 2006-09-25 2009-06-12 Siemens Aktiengesellschaft Rotor de turbina con placas de bloqueo y correspondiente procedimiento de montaje.
EP2053285A1 (fr) * 2007-10-25 2009-04-29 Siemens Aktiengesellschaft Ensemble de pales de turbine
US8613599B2 (en) 2007-10-25 2013-12-24 Siemens Aktiengesellschaft Turbine blade assembly and seal strip

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2084523A5 (fr) * 1970-03-14 1971-12-17 Rolls Royce
GB1295003A (fr) * 1971-06-15 1972-11-01
GB1512882A (en) * 1976-02-11 1978-06-01 Rolls Royce Bladed rotor assembly for a gas turbine engine
US5211407A (en) * 1992-04-30 1993-05-18 General Electric Company Compressor rotor cross shank leak seal for axial dovetails
US5320487A (en) * 1993-01-19 1994-06-14 General Electric Company Spring clip made of a directionally solidified material for use in a gas turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2084523A5 (fr) * 1970-03-14 1971-12-17 Rolls Royce
GB1295003A (fr) * 1971-06-15 1972-11-01
GB1512882A (en) * 1976-02-11 1978-06-01 Rolls Royce Bladed rotor assembly for a gas turbine engine
US5211407A (en) * 1992-04-30 1993-05-18 General Electric Company Compressor rotor cross shank leak seal for axial dovetails
US5320487A (en) * 1993-01-19 1994-06-14 General Electric Company Spring clip made of a directionally solidified material for use in a gas turbine engine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1371814A1 (fr) * 2002-06-11 2003-12-17 ALSTOM (Switzerland) Ltd Arrangement des joints d'étanchéité dans le rotor d'une turbine à gaz
WO2003104617A1 (fr) * 2002-06-11 2003-12-18 Alstom (Switzerland) Ltd Dispositif d'etancheite pour rotor de turbomachine
US7220099B2 (en) 2002-06-11 2007-05-22 Alstom Technology Ltd. Sealing arrangement for a rotor of a turbo machine
WO2010088881A1 (fr) 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Dispositif d'étanchéité sur l'arbre à aubes d'un étage de rotor d'une turbomachine axiale
DE102009007664A1 (de) 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Abdichtvorrichtung an dem Schaufelschaft einer Rotorstufe einer axialen Strömungsmaschine
US8870542B2 (en) 2009-02-05 2014-10-28 Mtu Aero Engines Gmbh Sealing apparatus at the blade shaft of a rotor stage of an axial turbomachine

Also Published As

Publication number Publication date
GB9512965D0 (en) 1995-08-30
GB2302711A (en) 1997-01-29

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