GB2453231A - Sealing rings - Google Patents
Sealing rings Download PDFInfo
- Publication number
- GB2453231A GB2453231A GB0817380A GB0817380A GB2453231A GB 2453231 A GB2453231 A GB 2453231A GB 0817380 A GB0817380 A GB 0817380A GB 0817380 A GB0817380 A GB 0817380A GB 2453231 A GB2453231 A GB 2453231A
- Authority
- GB
- United Kingdom
- Prior art keywords
- ring
- coating
- sealing
- thickness
- forming
- 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
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 33
- 238000000576 coating method Methods 0.000 claims abstract description 23
- 239000011248 coating agent Substances 0.000 claims abstract description 22
- 238000000034 method Methods 0.000 claims abstract description 12
- 238000003754 machining Methods 0.000 claims abstract description 9
- 238000000151 deposition Methods 0.000 claims abstract description 6
- UONOETXJSWQNOL-UHFFFAOYSA-N tungsten carbide Chemical compound [W+]#[C-] UONOETXJSWQNOL-UHFFFAOYSA-N 0.000 claims abstract description 5
- 238000005480 shot peening Methods 0.000 claims description 5
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 238000005755 formation reaction Methods 0.000 claims description 3
- 230000008021 deposition Effects 0.000 abstract description 2
- 239000012530 fluid Substances 0.000 description 6
- 239000011247 coating layer Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J9/00—Piston-rings, e.g. non-metallic piston-rings, seats therefor; Ring sealings of similar construction
- F16J9/26—Piston-rings, e.g. non-metallic piston-rings, seats therefor; Ring sealings of similar construction characterised by the use of particular materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
-
- 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
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/08—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing
- F16J15/0806—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with exclusively metal packing characterised by material or surface treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3268—Mounting of sealing rings
- F16J15/3272—Mounting of sealing rings the rings having a break or opening, e.g. to enable mounting on a shaft otherwise than from a shaft end
-
- 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
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
This invention relates to sealing rings and specifically a sealing split ring 10 for use in gas turbines, the sealing ring 10 being dimensioned to in use dimensions wherein its sealing surfaces 13, 14 are shot peen hardened and/or coated with a wear resistant coating 15 typically of tungsten carbide, the thickness of the coating being in the range of 0.125mm to 0.077mm. Also disclosed is a method of forming the sealing ring, the method including: forming the sealing ring to the in use dimensions less the coating thickness of the ring; and depositing a coating having a thickness in the range of 0.125mm to 0.077mm, the ring requiring no further machining after the deposition of the coating. Alternatively a shot peened sealing surface may be used.
Description
END3OGB 1 Sealing Rings This invention relates to sealing rings for use in gas turbines.
In aerospace gas turbines in particular, fuel is fed radially through the outer "shell" of the engine into the combustion can. Typically there may be twenty holes in the shell arranged evenly around the engine. The fluid feed conveyors positioned in these holes may be in a high and varying temperature environment and need to be flexibly mounted in order to accommodate the movements due to thermal expansion of the components. Piston ring type seals are therefore used to maintain a good seal and yet allow for some relative movement of the cooperating components at high temperatures. There may be as many as forty of these rings on a single gas turbine and so cost and service life are both very important. The relative movements of these components produce wear which can be a substantial problem.
The current practice is to use an out-springing, split ring, which is made undersized relative to the in use dimensions and to deposit a hard and relatively thick coating layer on the sealing surfaces of the rings at least, so as to provide long wear life. Typically, such coatings are 0.3810 mm (0.01 50 inches).
However, the dimension tolerances involved are very tight and it is difficult to deposit a film of that thickness and still keep within the ring tolerances required. Post deposition machining therefore has to take place and this adds *.:.* significantly to the cost of the sealing rings. Despite this problem having existed S...
for some decades, no satisfactory solution has been found.
From one aspect the present invention consists in a sealing split ring for S. * use in a gas turbine dimensioned to in use dimensions wherein its sealing * S * *.. S. * S* * S.
END.3OGB 2 surfaces are shot peen hardened and/or coated with a wear resistant coating of thickness in the range about 0.125mm to about 0.077mm.
It is particularly preferred that the coating thickness is in the range 0.1270 to 0.076mm (0.0050 to 0.0030 inches) The Applicants have determined that, contrary to the genera! prejudice in the industry, by making the ring to its in use dimensions less the coating thickness and putting on a relatively thin coating, one achieves superior sealing and satisfactory wear characteristics without needing post-deposition machining to obtain the required ring dimension tolerances.
In this process the mid-tolerance coating thickness will normally be in the region of 0.1000 mm (0.0039 inches) and the coating may be of tungsten carbide.
Alternatively, the Applicants have determined that it is equally sufficient simply to shot peen the sealing surfaces of a ring which has already been made to its in use dimensions. This process hardens the surfaces without changing the ring dimensions sufficiently so that they fall outside the required tolerances and again good wear and sealing characteristics are obtained without the need for a post-hardening machining operations. It is possible to combine both these alternative techniques in order to obtain additional enhanced wear properties.
The free ends of the ring may have overlapping formations which may be scarf cut in order to further improve the sealing properties in the region of the S... * . ***.
ring gap.
The ring may in particular form a gas turbine burner seal.
** S...
* From a further aspect the invention consists in a method of forming a *S * S * ... S* * * S* S **
END3OGB 3 sealing ring for a gas turbine including: (a) forming a ring to the in use dimensions less a coating thickness of the ring; and (b) depositing a coating having a thickness between about 0.125mm and 0.077mm.
wherein the ring requires no further machining after step (b).
From a still further aspect the invention consists in a method of forming a sealing ring for a gas turbine including: (a) forming a ring having sealing surfaces, to the in use dimensions of the ring; and (b) shot peening the sealing surfaces wherein the ring requires no further machining after step (b).
Although the invention has been defined above it must be understood that it includes any inventive combination of the features set out above or in the
following description.
The invention may be performed in various ways and specific embodiments will now be described by way of example, with reference to the accompanying drawings in which: Figure 1 is a schematic cross-sectional view showing a sealing ring which in use separates two fluid spaces such that different fluid pressures may exist in S...
the said spaces with minimum fluid flow occurring between them.
Figure 2 is a cross section through one part of a sealing ring embodiment * of the invention; S. * . * *.S * * * S * ..
END.3008 4 Figure 3 is a corresponding view of an alternative embodiment of the invention; Figure 4 is a pictorial view of the ring sections in the region of the ring gap and illustrates one design of a scarf cut abutment used to reduce fluid leakage; and Figure 5 shows a cross section of the scarf abutment when the two ends of the gapped ring are engaged in the in use position.
In Figure 1 a sealing ring 10 seals between a first part 11 and a second part 12 in order to define high pressure and tow pressure regions, annotated HP and LP respectively. It will be seen that the ring seals on its outer diameter surface 13 in contact with the hole diameter 19 and on a side surface 14 which is in contact with the low pressure side of the groove in part 11.
In the arrangement shown in Figure 2 the surfaces 13 and 14 are coated with a tungsten carbide coating 15 of a thickness in the region of 0.1000 mm (0.0039 inches). For drawing clarity this thickness has been shown enlarged in Figure 2. The reason for using this relatively thin wearing coating is to enable the in use dimensions of the ring to be held within the tight dimensional tolerances required in gas turbine engines as previously described.
In an alternative embodiment, shown in Figure 3, the two wearing surfaces 13 and 14 at least are subjected to a shot peening operation, the at least region being designated by 20 in the drawing. The dimensions of the ring S...
are made initially to the in use dimensions and no further machining is required following the shot peening treatment. The use of shot peening is counter * intuitive, because one would expect.such a treatment to provide a slightly *. * * * ..* S. *
SS S.
END.30 GB 5 roughened surface, which would be inappropriate for sealing purposes.
As is shown in Figures 4 and 5, the respective free ends 16, 17 of the split or gapped ring can be in use overlapping and scarf cut to maintain a fluid seal in the gap region of the ring 10. * ** * * * * ** * * S...
*5S*** * * *..S*. * S *S * S * I*. *. * * S * * S.
Claims (11)
- END.30 GB 6 Claims 1. A sealing split ring for use in a gas turbine dimensioned to in use dimensions wherein its sealing surfaces are shot peen hardened and/or coated with a wear resistant coating of thickness in the range about 0.125mm to about 0.077mm.
- 2. A ring as claimed in claim I wherein the coating is about 0.100mm thick.
- 3. A nng as claimed in claim I or claim 2 wherein the coating is tungsten carbide.
- 4. A ring as claimed in any one of the preceding claims wherein the free ends of the ring have overlapping formations.
- 5. A ring as claimed in claim 4 wherein the formations are scarf cut.
- 6. A gas turbine burner seal constituted by a ring as claimed in any one of the preceding claims.
- 7. A method of forming a sealing ring fora gas turbine including: (a) forming a ring to the in use dimensions less a coating thickness of the ring; and (b) depositing a coating having a thickness between abput 0.125mm and 0.077mm.wherein the ring requires no further machining after step (b).
- 8. A method as claimed in claim 7, wherein step (b) also includes shot * S. peening the sealing surface. S... * . S...
- 9. A method as claimed in claim 7 or claim 8, wherein the thickness of theS *..* : coating is about 0.100mm.S.....
- 10. A method as claimed in any one of claims 7 to 9, wherein the coating is END3OGB 7 tungsten carbide.
- 11. A method of forming a sealing ring for a gas turbine including: (a) forming a ring having sealing surfaces, to the in use dimensions of the ring; and (b) shot peening the sealing surfaces wherein the ring requires no further machining after step (b). * S. * S * * .. **.S * I S...II..... * *I*51I5I * I I. * I * SIISI S * I I * II
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GBGB0718799.0A GB0718799D0 (en) | 2007-09-26 | 2007-09-26 | Sealing rings |
Publications (3)
Publication Number | Publication Date |
---|---|
GB0817380D0 GB0817380D0 (en) | 2008-10-29 |
GB2453231A true GB2453231A (en) | 2009-04-01 |
GB2453231B GB2453231B (en) | 2012-02-01 |
Family
ID=38701699
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GBGB0718799.0A Ceased GB0718799D0 (en) | 2007-09-26 | 2007-09-26 | Sealing rings |
GB0817380.9A Expired - Fee Related GB2453231B (en) | 2007-09-26 | 2008-09-23 | Sealing rings |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GBGB0718799.0A Ceased GB0718799D0 (en) | 2007-09-26 | 2007-09-26 | Sealing rings |
Country Status (1)
Country | Link |
---|---|
GB (2) | GB0718799D0 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2453150A1 (en) * | 2010-11-10 | 2012-05-16 | United Technologies Corporation | Seal assembly |
EP2442912A4 (en) * | 2009-06-17 | 2017-11-22 | Spray Nozzle Engineering Pty. Limited | Spray nozzle seal means |
US9995397B2 (en) | 2016-07-12 | 2018-06-12 | United Technologies Corporation | Coated seal housing |
GB2578782A (en) * | 2018-11-09 | 2020-05-27 | Ingles Mood Geoffrey | A split gasket |
EP3885535A1 (en) * | 2020-03-24 | 2021-09-29 | Siemens Aktiengesellschaft | Sealing ring for a rotor and rotor with such a sealing ring |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1291294A (en) * | 1969-10-20 | 1972-10-04 | Ramsey Corp | Improvements in or relating to piston rings |
US5794943A (en) * | 1995-08-16 | 1998-08-18 | Northrop Grumman Corporation | Piston rings particularly suited for use with ceramic matrix composite pistons and cylinders |
EP1132663A2 (en) * | 2000-03-11 | 2001-09-12 | Federal-Mogul Burscheid GmbH | Piston ring with wear resistant layer and wear resistant layer for piston ring |
JP2006125530A (en) * | 2004-10-29 | 2006-05-18 | Kanai Hiroaki | Piston ring and method of manufacturing the same |
-
2007
- 2007-09-26 GB GBGB0718799.0A patent/GB0718799D0/en not_active Ceased
-
2008
- 2008-09-23 GB GB0817380.9A patent/GB2453231B/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1291294A (en) * | 1969-10-20 | 1972-10-04 | Ramsey Corp | Improvements in or relating to piston rings |
US5794943A (en) * | 1995-08-16 | 1998-08-18 | Northrop Grumman Corporation | Piston rings particularly suited for use with ceramic matrix composite pistons and cylinders |
EP1132663A2 (en) * | 2000-03-11 | 2001-09-12 | Federal-Mogul Burscheid GmbH | Piston ring with wear resistant layer and wear resistant layer for piston ring |
JP2006125530A (en) * | 2004-10-29 | 2006-05-18 | Kanai Hiroaki | Piston ring and method of manufacturing the same |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2442912A4 (en) * | 2009-06-17 | 2017-11-22 | Spray Nozzle Engineering Pty. Limited | Spray nozzle seal means |
EP2453150A1 (en) * | 2010-11-10 | 2012-05-16 | United Technologies Corporation | Seal assembly |
EP2453150B1 (en) | 2010-11-10 | 2016-05-11 | United Technologies Corporation | Seal assembly |
US9995397B2 (en) | 2016-07-12 | 2018-06-12 | United Technologies Corporation | Coated seal housing |
GB2578782A (en) * | 2018-11-09 | 2020-05-27 | Ingles Mood Geoffrey | A split gasket |
EP3885535A1 (en) * | 2020-03-24 | 2021-09-29 | Siemens Aktiengesellschaft | Sealing ring for a rotor and rotor with such a sealing ring |
US11365639B2 (en) | 2020-03-24 | 2022-06-21 | Siemens Energy Global GmbH & Co. KG | Sealing washer for a rotor, and rotor with such a washer |
Also Published As
Publication number | Publication date |
---|---|
GB0817380D0 (en) | 2008-10-29 |
GB0718799D0 (en) | 2007-11-07 |
GB2453231B (en) | 2012-02-01 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20130923 |