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GB839915A - Labyrinth seals - Google Patents

Labyrinth seals

Info

Publication number
GB839915A
GB839915A GB193758A GB193758A GB839915A GB 839915 A GB839915 A GB 839915A GB 193758 A GB193758 A GB 193758A GB 193758 A GB193758 A GB 193758A GB 839915 A GB839915 A GB 839915A
Authority
GB
United Kingdom
Prior art keywords
annuli
dimples
ring
adjacent
annulus
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.)
Expired
Application number
GB193758A
Inventor
Frederick William Walto Morley
Wilfred Henry Wilkinson
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 PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB193758A priority Critical patent/GB839915A/en
Publication of GB839915A publication Critical patent/GB839915A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12Preventing 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
    • F01D11/127Preventing 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 a deformable or crushable structure, e.g. honeycomb

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Abstract

839,915. Stuffing-box substitutes. ROLLSROYCE Ltd. Jan. 20, 1959 [Jan. 20, 1958], No. 1937/58. Class 122 (5). Also in Group XXII] A labyrinth seal comprises a sealing member 11 formed by a number of metal strip annuli 19, adjacent annuli being axially spaced apart at their peripheral sealing edges 19b, and cooperating with at least one rib 10b which cuts its own path in the annuli if rubbing therebetween occurs. The annuli may be either initially separate and mounted as a stack or in the form of a continuous helix. The invention is shown in Fig. 1 applied to sealing gas turbine blades 10, ribs 10b on the blade shrouds 10a co-operating with spaced sealing members 11 in a ring 12 secured to the turbine stator 14 and cooled by cooling air circulated through a chamber 16. Preferably the metal of the annuli 19 is softer or has a lower melting point than that of the projections 10b. In the embodiment shown in Fig. 2 each annulus has an outer enlarged V-section portion 19a received in the corresponding portion of the adjacent annulus and a thin sealing portion 19b of, for example <6>/1000 inch thickness. The annuli are clamped between a shoulder 12c on the ring 12 and a ring 13. In a modification, the annuli are of constant thickness metal and have circumferential corrugations at their outer peripheries engaging corresponding corrugations on adjacent annuli. In another modification, Fig. 5, the annuli are spaced by dimples 23, 24 formed on alternate annuli and spot-welded at their troughs to adjacent non-dimpled annuli. In a further modification, Fig. 6, each annulus is formed with dimples 25, the dimples on alternate annuli being circumferentially staggered with respect to those on adjacent annuli. The portions of flanges 26 in the region of the dimples are bent radially outwards to form tangs 27 protruding through slots 28 in a ring 29, the tangs 27, the flanges 26 and also end plates 30, 31 being welded to the ring 29. In yet another modification, the annuli are spaced by dimples formed on one side only of each annulus. The annuli may be made by forming a continuous strip of the metal to the desired cross-section by drawing, rolling or extruding and then winding the formed strip around a mandrel to provide a helically coiled strip from which separate annuli may be cut.
GB193758A 1958-01-20 1958-01-20 Labyrinth seals Expired GB839915A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB193758A GB839915A (en) 1958-01-20 1958-01-20 Labyrinth seals

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB193758A GB839915A (en) 1958-01-20 1958-01-20 Labyrinth seals

Publications (1)

Publication Number Publication Date
GB839915A true GB839915A (en) 1960-06-29

Family

ID=9730656

Family Applications (1)

Application Number Title Priority Date Filing Date
GB193758A Expired GB839915A (en) 1958-01-20 1958-01-20 Labyrinth seals

Country Status (1)

Country Link
GB (1) GB839915A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2432105A1 (en) * 1978-06-26 1980-02-22 United Technologies Corp BANDAGE FOR BLADE HEADS OF THE COMPRESSION STAGE OF A GAS TURBINE
US4466772A (en) * 1977-07-14 1984-08-21 Okapuu Uelo Circumferentially grooved shroud liner
GB2145478A (en) * 1983-08-26 1985-03-27 Gen Electric Resilient seal between relatively moveable members
FR2635562A1 (en) * 1988-08-18 1990-02-23 Snecma TURBINE STATOR RING ASSOCIATED WITH A TURBINE HOUSING BINDING SUPPORT
GB2420830A (en) * 2004-12-01 2006-06-07 Rolls Royce Plc Casing arrangement
US20150104306A1 (en) * 2013-10-15 2015-04-16 Rolls-Royce Plc Fan casing arrangement for a gas turbine engine and related method

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4466772A (en) * 1977-07-14 1984-08-21 Okapuu Uelo Circumferentially grooved shroud liner
FR2432105A1 (en) * 1978-06-26 1980-02-22 United Technologies Corp BANDAGE FOR BLADE HEADS OF THE COMPRESSION STAGE OF A GAS TURBINE
GB2145478A (en) * 1983-08-26 1985-03-27 Gen Electric Resilient seal between relatively moveable members
FR2635562A1 (en) * 1988-08-18 1990-02-23 Snecma TURBINE STATOR RING ASSOCIATED WITH A TURBINE HOUSING BINDING SUPPORT
EP0356305A1 (en) * 1988-08-18 1990-02-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine stator ring held by a turbine casing
US4925365A (en) * 1988-08-18 1990-05-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine stator ring assembly
GB2420830A (en) * 2004-12-01 2006-06-07 Rolls Royce Plc Casing arrangement
US7140836B2 (en) 2004-12-01 2006-11-28 Rolls Royce Plc Casing arrangement
GB2420830B (en) * 2004-12-01 2007-01-03 Rolls Royce Plc Improved casing arrangement
US20150104306A1 (en) * 2013-10-15 2015-04-16 Rolls-Royce Plc Fan casing arrangement for a gas turbine engine and related method
EP2865852A1 (en) * 2013-10-15 2015-04-29 Rolls-Royce plc A fan casing arrangement for a gas turbine engine and related method
US9777599B2 (en) * 2013-10-15 2017-10-03 Rolls-Royce Plc Fan casing arrangement for a gas turbine engine and related method

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