GB839915A - Labyrinth seals - Google Patents
Labyrinth sealsInfo
- 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
Links
- 238000007789 sealing Methods 0.000 abstract 5
- 239000002184 metal Substances 0.000 abstract 4
- 230000004048 modification Effects 0.000 abstract 4
- 238000012986 modification Methods 0.000 abstract 4
- 238000001816 cooling Methods 0.000 abstract 1
- 238000002844 melting Methods 0.000 abstract 1
- 230000008018 melting Effects 0.000 abstract 1
- 230000002093 peripheral effect Effects 0.000 abstract 1
- 238000005096 rolling process Methods 0.000 abstract 1
- 238000004804 winding Methods 0.000 abstract 1
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
- F01D11/127—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 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.
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)
| 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 |
-
1958
- 1958-01-20 GB GB193758A patent/GB839915A/en not_active Expired
Cited By (12)
| 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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