GB2223811A - Gas turbine having ring for sealing at rotor blade tips - Google Patents
Gas turbine having ring for sealing at rotor blade tips Download PDFInfo
- Publication number
- GB2223811A GB2223811A GB8920543A GB8920543A GB2223811A GB 2223811 A GB2223811 A GB 2223811A GB 8920543 A GB8920543 A GB 8920543A GB 8920543 A GB8920543 A GB 8920543A GB 2223811 A GB2223811 A GB 2223811A
- Authority
- GB
- United Kingdom
- Prior art keywords
- gas turbine
- bellows
- ring
- compressed air
- turbine device
- 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 description 7
- 239000000919 ceramic Substances 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 3
- 229910052751 metal Inorganic materials 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 229910000831 Steel Inorganic materials 0.000 claims description 2
- 239000010959 steel Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 claims 1
- 239000007789 gas Substances 0.000 description 9
- 238000001816 cooling Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000013021 overheating Methods 0.000 description 2
- 230000006399 behavior Effects 0.000 description 1
- VNNRSPGTAMTISX-UHFFFAOYSA-N chromium nickel Chemical compound [Cr].[Ni] VNNRSPGTAMTISX-UHFFFAOYSA-N 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 230000003068 static effect Effects 0.000 description 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
-
- 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
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
-
- 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
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Diaphragms And Bellows (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
k 2'19 L& 3 8 11 A gas turbine having a device for retaining a jacket ring
The invention relates to a gas turbine having a device for centrally retaining a jacket ring which encloses a gas turbine rotor in a turbine housing, forming a radial sealing gap.
Such devices are known and compensate for the geometric variations caused by different heat expansion behaviours of the rotor and the stator and help to keep the radial width of the circumferential sealing gap uniformly open under all operational conditions. For this purpose jacket rings are centrally suspended between the rotor and the stator, for example by means of spacers, which may be bimetallic, jointedly supported on the housing and on the jacket ring. However, it is difficult and expensive to produce joints on ceramic jacket rings. Other solutions involve metallic brush seals or metal felt inserts or metal meshes as an intermediate layer between the metallic housing and the ceramic jacket ring. These solutions have the disadvantage that the resilient action of these intermediate layers weakens over fairly long operation times and the jacket ring is set into rotation and consequently destroys the intermediate layer and the rotor blading.
According to the present invention there is provided a gas turbine having a device for centrally retaining a jacket ring surrounding the gas turbine rotor in the turbine housing with a radial sealing gap therebetween, comprising a bellows means distributed over the circumference between the turbine housing and the jacket ring, the bellows means being operable by compressed air so as to secure the ring in the radial direction in a set position.
Embodiments of the invention may thus provide 1 1 is a retaining means which supports a jacket ring with respect to the metallic housing so that a radial sealing gap is guaranteed for all operational conditions and long operational times without material fatigue endangering the operation and without structurally elaborate mechanical parts having to be provided.
An advantage of the central holding means of the invention lies in the fact that the clamping effect of the bellows means takes place not by spring action but by the effect of compressed air or other suitable fluid means. By 'bellows' a generally closed component is envisaged, capable of expansion and contraction. The supply of compressed air may be, for instance, from a compressor stage connected in series or from another compressed air source on the stator side. The compressed air is preferably taken from the high pressure compressor stage since this pressure is greater in all operational states than the static pressure on the high pressure side of the first turbine stage and hence is also higher than the ambient pressure in the region of the bellows means.
In order to position the jacket ring centrally, the bellows means would normally comprise at least three individual bellows, distributed around the circumference. These may take the shape of annular segments so that they take up a minimum amount of space between the housing and the jacket ring; alternatively, since flat cylindrical bellows can be produced costeffectively in large numbers and matched to or fitted around.the turbine housing curve, this embodiment may be preferred for large production quantities.
The bellows means in accordance with the invention are particularly suitable for holding g sintered ceramics closed jacket rings since these jacket rings can accept high pressure loads. Metallic materials have proved reliable for the bellows. A chromium nickel steel is preferably used since thinwalled and weight-saving bellows can be produced from this material. For heat insulaton between the bellows and the jacket ring the radially outer circumference of the jacket ring, or the bellows base, or both, is/are provided with a heat insulation layer.
The jacket ring is preferably held in the circumferential direction in force-fitting manner by the action of pressure from the bellows and is thus secured against rotation or rotary movements. In the axial direction devices are preferably provided which fix the jacket ring in form-fitting manner, via the bellows, in the turbine housing. For this purpose, for example, the metallic base of the bellows may have a generally circumferential ridge or groove mating with a corresponding groove or ridge in the jacket ring so as to form a snug fit.
The supply of compressed air for all the bellows of the bellows means is preferably effected by means of compressed air apertures in the bellows and an annular compressed air duct which encloses the bellows and is connected to the compressed air apertures. An arrangement of this type has the advantage that it can be made as an integral component and can be positioned on the jacket ring with a slight resilient pressure of the bellows.
Ceramic jacket rings are used in particular in turbines with a high turbine intake temperature (1000 to 1300C), and therefore it is advantageous to cool the bellows means. A constant cooling gas stream can preferably be supplied via the compressed air apertures of the compressed air duct and be drawn off via separate outlet apertures in the bellows, and advantageously the outlet apertures are directed towards the high pressure side of the turbine rotor so as to obtain an intensive cooling of the bellows in this high temperature area.
The cooling air flowing out under pressure can be used for the thermal matching of the rotor disc or for the gap sealing and in this connection the compressed air duct forming an integral component with the bellows should preferably be arranged on the low pressure side of a turbine stage and an outlet duct should be located on the high pressure side.
A further preferred construction of the invention consists in having the compressed air duct, the bellows and the outlet duct form an integral component which is easy to assemble.
The air cooling of the bellows should guarantee a high-temperatureresistant retaining of the hot jacket ring. A further preferred measure is to arrange between the jacket ring and the bellows a segmented insulating ring with lower heat conductivity than the jacket ring. The axial positioning can be ensured preferably on the one hand by the interlocking of circumferential guide grooves between the jacket ring and the insulating ring, and on the other haud mechanisms can be provided on the outer circumference of the insulating ring as mentioned above, for a formfitting connection to the bellows.
For a better understanding of the invention, embodiments will be explained below with reference to the accompanying drawings, in which:- Fig. 1 shows.the installation position of a jacket ring with a holding means in a hot gas turbine, Fig. 2 shows a cross section through a first embodiment of the invention; 1 Fig. 3 shows the end piece of a bellows ring segment in longitudinal section, elevation and plan view; Fig. 4 shows a cross section of a second embodiment of the invention, and Fig. 5 shows an embodiment having several flat cylindrical bellows adapted to the housing curve.
Fig. 1 shows the installation position of a jacket ring 1 having holding means 2 in accordance with the invention in a hot gas turbine in axial cross section. The jacket ring 1 encloses a rotor 3 and is held centrally to the rotor axis 5 in a turbine housing 6 by bellows means acted on by compressed 'air. The bellows means comprises several individual metallic bellows 4 which are protected by an insulating ring 8 against overheating by a hot gas stream 7 (see arrows) in a flow duct 9.
Fig. 2 shows a cross section through a bellows 4 having a welded-on compressed air duct 10 and an insulating ring 8 and a ceramic jacket ring 1 fitted to it. The compressed air, which is supplied from a high pressure compressor via the connecting flange 11 to the annular segmented compressed air duct 10 which encloses the bellows 4, reaches the bellows 4 via the compressed air aperture 12 causing it to expand. Thus the insulating ring 8 is secured with respect to the turbine housing 6. The insulating ring 8 is preferably segmented and is fixed in the axial direction with respect to the jacket ring 1 via a circumferential guide groove 13 on the jacket ring 1. Through the good heat insulation of the insulating ring 8 the thinwalled bellows 4 is prevented from overheating due to the hot gas in the flow duct. The compressed air duct 10 here forms an integral component with the bellows 4. The bellows 4 position the insulating ring 8 in the axial direction by means of a radially inwardly protruding curve or ridge 14 in the bellows base 15. A corresponding groove or recess forms a fit surface in the insulating ring 8. Rotation of the jacket ring 1 with respect to the insulating ring 8 and the bellows 4 and the turbine housing 6 is prevented by a forcelocking clamping of the bellows 4 by means of the compressed air action.
Fig. 3 shows the end piece 17 of a bellows in the form of a ring segment 16 in longitudinal section, elevation and plan view. For a satisfactory clamping function of the bellows 4 it is necessary for them to match the turbine housing curve 18, and in their end area they have an end piece 17 which has the same elasticity as the remainder of the bellows ring segment 16.
Fig. 4 shows a cross-section similar to Fig. 2 but of an integral component comprising a bellows ring segment 16, a compressed air duct 10 and an outlet duct 19. The compressed air flows via the connecting flange 11 into the annular compressed air duct 10 and, by means of the compressed air apertures 12 of the bellows ring segment 16 on the low pressure side of the turbine, reaches the bellows 4. It cools the bellows 4 and flows out over the outlet apertures. 20 on the high pressure side of the turbine stage. It is collected in the outlet duct _19 and is conveyed over the flange 21 to a further load.
Fig. 5 shows a radial section through part of jacket ring and turbine housing, having the shape of circular segment.- Several flat cylindrical bellows 4 are matched or adapted to the turbine housing curve 18. The bellows 4 form an integral component with a segmented compressed air duct 10 as before and clamp the turbine housing 6 to the jacket ring 1 of ceramics.
A 1 Three insulating ring segments 22 are shown, positioned between the jacket ring 1 and the bellows 4 and having a lower heat conductivity than the ceramic jacket ring 1. This arrangement is a preferred embodiment of the invention since a holding means 2 of this type is particularly suitable for mass production.
X
Claims (18)
1. A gas turbine having a device for centrally retaining a jacket ring surrounding the gas turbine rotor in the turbine housing with a radial sealing gap therebetween, comprising a bellows means distributed over the circumference between the turbine housing and the jacket ring, the bellows means being operable by compressed air so as to secure the ring in the radial direction in a set position.
2. A gas turbine device according to claim 1, wherein the jacket ring is made of a sintered ceramics material.
3. A gas turbine device according to claim 1 or 2, wherein the bellows means is made of metal, preferably chromium-nickel-steel.
4. A gas turbine device according to any preceding claim, wherein the jacket ring carries a heat-insulating layer on its outer circumference.
5. A gas turbine device according to claim 4, wherein the heat-insulating layer is a segmented insulating ring of lower heat conductivity than the jacket ring.
6. A gas turbine device according to claim 5, wherein the jacket ring and the insulating ring interlock by means of a circumferential guide groove for axial positioning.
7. A gas turbine device according to any preceding claim, wherein the part of the bellows means adjacent to the jacket ring has a heat- insulating layer.
8. A gas turbine device according to any preceding claim, wherein the bellows means comprises several individual bellows having the shape of annular segments uniformly circumferentially distributed about z 1.1 the jacket ring.
9. A gas turbine device according to any of claims 1 to 7, wherein the bellows means comprises several individual bellows each having a flat cylindrical shape and matched to the turbine housing curve, arranged about the circumference of the ring.
10. A gas turbine device according to any preceding claim, wherein the bellows means holds the jacket ring in the circumferential direction in forcefitting manner in the turbine housing.
11. A gas turbine device according to any preceding claim, wherein the bellows means has means which fix the jacket ring, or its insulating ring as the case may be, in the axial direction in form-fitting manner.
12. A gas turbine device according to any preceding claim and having a compressed air duct to which the bellows means is connected by means of compressed air apertures.
13. A gas turbine device according to claim 12, wherein the compressed air duct and the bellows means form an integral component.
14. A gas turbine device according to claim 12 or 13, wherein the compressed air duct surrounds the bellows means.
15. A gas turbine device according to any of claims 12 to 14, wherein the bellows means has outlet apertures for compressed air which are connected to an annular outlet duct.
16. A gas turbine device according to claim 15, wherein the compressed air duct is arranged axially on the low pressure side of the turbine stage and the outlet duct is arranged on the high pressure side of the turbine stage.
17. A gas turbine device according to claim 1 16, wherein the compressed air duct, bellows means and outlet duct form an integral component.
18. A gas turbine, substantially as described herein with reference to any of the accompanying drawings.
Published 1990 atThe Patent Office. State House, 6671 High Holborn, LondonWCIR4TP. Further copies maybeobtainedfroin The Patent Office. Wes Branch, St Mary Cray. Orpington, Kent BR5 3RD. Printed by Multiplex techniques ltd, St Mary Cray. Kent. Can. 1187
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE3830762A DE3830762C2 (en) | 1988-09-09 | 1988-09-09 | Device for holding a jacket ring in gas turbines |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB8920543D0 GB8920543D0 (en) | 1989-10-25 |
| GB2223811A true GB2223811A (en) | 1990-04-18 |
| GB2223811B GB2223811B (en) | 1992-12-16 |
Family
ID=6362666
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8920543A Expired GB2223811B (en) | 1988-09-09 | 1989-09-11 | A gas turbine having a device for retaining a shroud ring. |
Country Status (4)
| Country | Link |
|---|---|
| DE (1) | DE3830762C2 (en) |
| FR (1) | FR2636373B1 (en) |
| GB (1) | GB2223811B (en) |
| IT (1) | IT1231406B (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6048170A (en) * | 1997-12-19 | 2000-04-11 | Rolls-Royce Plc | Turbine shroud ring |
| JP2014015927A (en) * | 2012-07-06 | 2014-01-30 | General Electric Co <Ge> | Aerodynamic seals for rotary machine |
| US8894349B2 (en) | 2009-08-20 | 2014-11-25 | Rolls-Royce Plc | Turbomachine casing assembly |
| CN105840549A (en) * | 2016-03-30 | 2016-08-10 | 中国科学院工程热物理研究所 | Mechanism for active control over blade top gap and case shape of air compressor within full working condition range |
| CN106150571A (en) * | 2015-05-11 | 2016-11-23 | 通用电气公司 | There is the guard shield retention system of fixing spring |
| RU2613104C1 (en) * | 2015-09-18 | 2017-03-15 | Михаил Александрович Щербаков | Gas turbine engine axial flow turbine |
| RU2620883C2 (en) * | 2011-03-03 | 2017-05-30 | Сафран Аэро Бустерс Са | Outer segmented shell adapted to correct rotor offset as the stator |
| WO2018174739A1 (en) * | 2017-03-21 | 2018-09-27 | Siemens Aktiengesellschaft | A system of providing mobility of a stator shroud in a turbine stage |
| US20180371997A1 (en) * | 2017-06-27 | 2018-12-27 | General Electric Company | Clearance control device |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6671938B2 (en) * | 2000-12-27 | 2004-01-06 | United Technologies Corporation | Pneumatic press vane lift installation tool |
| DE10117231A1 (en) * | 2001-04-06 | 2002-10-31 | Hodson Howard | Rotor gap control module |
| DE102006052786B4 (en) * | 2006-11-09 | 2011-06-30 | MTU Aero Engines GmbH, 80995 | turbomachinery |
| DE102009006029A1 (en) * | 2009-01-24 | 2010-07-29 | Mtu Aero Engines Gmbh | turbomachinery |
| DE102010031124A1 (en) * | 2010-07-08 | 2012-01-12 | Man Diesel & Turbo Se | flow machine |
| US11933226B2 (en) * | 2022-05-13 | 2024-03-19 | Rtx Corporation | Heat shield and method of installing the same |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2103294A (en) * | 1981-07-11 | 1983-02-16 | Rolls Royce | Shroud assembly for a gas turbine engine |
| US4596116A (en) * | 1983-02-10 | 1986-06-24 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Sealing ring for a turbine rotor of a turbo machine and turbo machine installations provided with such rings |
| GB2195715A (en) * | 1986-10-08 | 1988-04-13 | Rolls Royce Plc | Rotor blade tip-shroud |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2922835C2 (en) * | 1979-06-06 | 1985-06-05 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Circumferential gap seal on axial flow machines |
| DE2931766C2 (en) * | 1979-08-04 | 1982-08-05 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Sealing device for the free blade ends of an adjustable diffuser of a gas turbine |
| US4269903A (en) * | 1979-09-06 | 1981-05-26 | General Motors Corporation | Abradable ceramic seal and method of making same |
| JPS59185804A (en) * | 1983-04-08 | 1984-10-22 | Agency Of Ind Science & Technol | Gas turbine |
| FR2574473B1 (en) * | 1984-11-22 | 1987-03-20 | Snecma | TURBINE RING FOR A GAS TURBOMACHINE |
-
1988
- 1988-09-09 DE DE3830762A patent/DE3830762C2/en not_active Expired - Fee Related
-
1989
- 1989-09-04 IT IT8921603A patent/IT1231406B/en active
- 1989-09-07 FR FR8911723A patent/FR2636373B1/en not_active Expired - Fee Related
- 1989-09-11 GB GB8920543A patent/GB2223811B/en not_active Expired
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2103294A (en) * | 1981-07-11 | 1983-02-16 | Rolls Royce | Shroud assembly for a gas turbine engine |
| US4596116A (en) * | 1983-02-10 | 1986-06-24 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Sealing ring for a turbine rotor of a turbo machine and turbo machine installations provided with such rings |
| GB2195715A (en) * | 1986-10-08 | 1988-04-13 | Rolls Royce Plc | Rotor blade tip-shroud |
| US4844688A (en) * | 1986-10-08 | 1989-07-04 | Rolls-Royce Plc | Gas turbine engine control system |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6048170A (en) * | 1997-12-19 | 2000-04-11 | Rolls-Royce Plc | Turbine shroud ring |
| US8894349B2 (en) | 2009-08-20 | 2014-11-25 | Rolls-Royce Plc | Turbomachine casing assembly |
| RU2620883C2 (en) * | 2011-03-03 | 2017-05-30 | Сафран Аэро Бустерс Са | Outer segmented shell adapted to correct rotor offset as the stator |
| JP2014015927A (en) * | 2012-07-06 | 2014-01-30 | General Electric Co <Ge> | Aerodynamic seals for rotary machine |
| CN106150571B (en) * | 2015-05-11 | 2018-09-21 | 通用电气公司 | Shield retention system with fixing spring |
| CN106150571A (en) * | 2015-05-11 | 2016-11-23 | 通用电气公司 | There is the guard shield retention system of fixing spring |
| RU2613104C1 (en) * | 2015-09-18 | 2017-03-15 | Михаил Александрович Щербаков | Gas turbine engine axial flow turbine |
| CN105840549A (en) * | 2016-03-30 | 2016-08-10 | 中国科学院工程热物理研究所 | Mechanism for active control over blade top gap and case shape of air compressor within full working condition range |
| WO2018174739A1 (en) * | 2017-03-21 | 2018-09-27 | Siemens Aktiengesellschaft | A system of providing mobility of a stator shroud in a turbine stage |
| US20180371997A1 (en) * | 2017-06-27 | 2018-12-27 | General Electric Company | Clearance control device |
| CN109139129A (en) * | 2017-06-27 | 2019-01-04 | 通用电气公司 | Gap control device |
| US10851712B2 (en) | 2017-06-27 | 2020-12-01 | General Electric Company | Clearance control device |
| CN109139129B (en) * | 2017-06-27 | 2021-07-06 | 通用电气公司 | Gap control device |
Also Published As
| Publication number | Publication date |
|---|---|
| IT8921603A0 (en) | 1989-09-04 |
| DE3830762A1 (en) | 1990-03-15 |
| DE3830762C2 (en) | 1994-08-18 |
| GB2223811B (en) | 1992-12-16 |
| FR2636373B1 (en) | 1994-04-29 |
| IT1231406B (en) | 1991-12-02 |
| FR2636373A1 (en) | 1990-03-16 |
| GB8920543D0 (en) | 1989-10-25 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 19960911 |