GB2298246A - Turbine-blad-tip-sealing arrangement comprising a shroud band - Google Patents
Turbine-blad-tip-sealing arrangement comprising a shroud band Download PDFInfo
- Publication number
- GB2298246A GB2298246A GB9503575A GB9503575A GB2298246A GB 2298246 A GB2298246 A GB 2298246A GB 9503575 A GB9503575 A GB 9503575A GB 9503575 A GB9503575 A GB 9503575A GB 2298246 A GB2298246 A GB 2298246A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shroud band
- slot
- air
- turbine
- sealing rib
- 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
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
- F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
-
- 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
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
1 2298246 A turbine-blade arrangement comprising a shroud band The
invention relates to a turbine blade arrangement comprising a shroud band with at least one circumferential sealing rib, as known for example from WO 94/11616. The aim, by means of one or more circumferential sealing ribs on the shroud band, is greatly to reduce losses through leakage via the gap between the shroud banl and the wall of the casing or duct through which flow takes place.
The aim of the present invention is to disclose steps for still further reducing these leakage losses. To this end, the sealing rib has a circumferential slot, and a stream of air is supplied to the base of the slot and flows out at the top edge of the sealing rib. Advantageous other features are disclosed in the sub-claims.
According to the invention, the leakage flow is reduced by an air stream which flows substantially transversely with respect to the leakage flow between the wall of the casing or duct and the top edge of the sealing rib (s) and which f lows out of the aforementioned top edge. As a result, turbulence occurs in the gap between the casing or duct wall and the top edge of the sealing rib (s), and this turbulence hinders the leakage flow. Optionally the flow of air supplied to the bottom region of the slot can be branched off from the leakage flow upstream of the sealing rib(s), or alternatively the air flowing into the slot can be obtained from a cooling-air duct provided in the turbine blade, or preferably in the shroud band, for supplying air to cool these components.
The invention will now be explained in detail with reference to a preferred embodiment shown in the accompanying drawings, in which:
Figure 1 is a part section through a shroud band segment associated with a turbine blade in accordance with the invention; Figure 2 is a view X of Figure 1; and Figure 3 is a section taken on the line A-A in Figure 1.
Reference 1 denotes a turbine blade, more especially that used in a highpressure turbine or an aircraft gas turbine. The turbine blade carries a shroud-band segment 2, hereinafter also called a shroud band 2, and cooperates in a known manner with the other shroud-band segments of the adjacent blades to form a circumferential shroud band. At the top, the shroud band 2 has three sealing ribs 3, 4, 5 disposed one behind the other in the axial direction of the turbine. The ribs 3, 4, 5 are adapted to seal the gap on the side of the diagrammatically-indicated casing or duct wall 6 and thereby greatly reduce the leakage air flow represented by arrows 7. The sealing effect is improved by an additional air flow 8 from the top edge 5a of the sealing rib 5 into the gap between the sealing rib 5 and the wall 6. violent turbulence consequently occurs in the gap between the leakage air flow 7 and the air flow 8, thus further throttling the leakage air flow 7.
To obtain a uniform distribution of the air flow 8 around the entire periphery of the rotating shroud band 2 or of the likewise rotating sealing rib 5, the sealing rib 5 has - 3 a likewise circumferential slot 9 through which the sealing air flow 8 is guided. Consequently the air flow 8 from the slot 9 enters the gap between the tunnel wall 6 and the top edge Sa of the sealing ribs.
The air flow 8 can be supplied from various sources. A f irst embodiment is shown in Figures 1 to 3, in which a number of branch ducts 10 from a cooling-air duct 11 in the shroud band 2 open into the bottom region 9a of the slot 9. The shroud band in Figures 1 to 3 is provided with a cooling-air duct 11 and an entire cooling-air duct system 12 which supplies the cooling-air duct 11 and, in turn, is connected to a coolingair duct system (not shown) inside the air-cooled turbine blade 1. The air flow 8 is thus supplied from the flow of cooling air guided through the turbine blade 1 and the shroud band or segment 2.
The detailed manufacturing process can be as follows: firstly, the slot 9 is formed in a sealing rib 5, which is made wider than a conventional sealing rib without a slot. Next, the branch ducts 10 are manufactured, e. g. by drilling or electro-erosion. Preferably the branch ducts 10 enter the slot 9 at an inclined angle, as shown especially in Figure 3. By this means, the air flow 8 exhausts in the peripheral direction, i.e. opposing the direction of the rotating shroud band 2, imposing additional torque to the rotating stage to that of the blades in the neighbourhood of the top edge 5a of the sealing rib 5 so that the desired turbulence of the two air flows 7 and 8 is reliably produced in the gap between the top edge 5a and the tunnel wall 6. Finally, in the turbine-blade 4 arrangement shown in Figures 1 to 3, the cooling-air supply duct 13, which for manufacturing reasons extends through the cooling-air duct 11, is closed by welding on the trailing edge 2a of the shroud band 2 so that substantially the entire cooling-air flow is available as the air flow 8.
In the previously-explained embodiment, the sealing rib 5 formed with the circumferential slot 9 is on the trailing-edge side 2a of the cover shroud 2, since the leakage air flow 7 here has already been throttled by the upstream sealing ribs 3 and 4. The additional sealing effect is thus intensified by the air 8 flowing transversely into the gap.
The disclosed steps are a simple method of increasing the sealing effect in the gapregion between a turbine-blade shroud band 2 and the adjacent casing or duct wall 6. The additional expense is kept relatively low, and of course a number of details, particularly constructional, can deviate from the embodiment shown without departing from the scope of the claims.
4
Claims (3)
1. A turbine blade arrangement comprising a shroud band (2) with at least one circumferential sealing rib (5), characterised in that the sealing rib (5) has a circumferential slot (9), whereby a stream of air (8) supplied to the base (9a) of the slot (9) is able to flow. out at the top edge (5a) of the sealing rib (5).
2. A turbine blade arrangement according to claim 1, having at least one cooling-air duct (11) in the shroud band (2), characterised in that branch ducts (10) extend from the cooling-air duct (11) and open into the bottom region (9a) of the slot (9).
3. A turbine blade arrangement according to claim 1 or claim 2, characterised in that the branch ducts (10) open into the slot (9) at an inclined angle.
A turbine blade arrangement according to any one of the preceding claims, characterised in that a number of circumferential sealing ribs (3, 4, 5) are disposed on the shroud band (2), and the sealing rib (5) formed with the circumferential slot (9) is situated on the trailing edge (2a) of the shroud band (2).
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9503575A GB2298246B (en) | 1995-02-23 | 1995-02-23 | A turbine-blade arrangement comprising a shroud band |
DE19601818A DE19601818C2 (en) | 1995-02-23 | 1996-01-19 | Turbine blade arrangement with a shroud |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9503575A GB2298246B (en) | 1995-02-23 | 1995-02-23 | A turbine-blade arrangement comprising a shroud band |
Publications (3)
Publication Number | Publication Date |
---|---|
GB9503575D0 GB9503575D0 (en) | 1995-04-12 |
GB2298246A true GB2298246A (en) | 1996-08-28 |
GB2298246B GB2298246B (en) | 1998-10-28 |
Family
ID=10770086
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB9503575A Expired - Fee Related GB2298246B (en) | 1995-02-23 | 1995-02-23 | A turbine-blade arrangement comprising a shroud band |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE19601818C2 (en) |
GB (1) | GB2298246B (en) |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2322167A (en) * | 1996-12-17 | 1998-08-19 | Gen Electric | Turbine blade with squealer tip cooling |
GB2413160A (en) * | 2004-04-17 | 2005-10-19 | Rolls Royce Plc | A rotor blade tip cooling arrangement |
GB2434842A (en) * | 2006-02-02 | 2007-08-08 | Rolls Royce Plc | Cooling arrangement for a turbine blade shroud |
GB2451568A (en) * | 2007-07-31 | 2009-02-04 | Gen Electric | Seal tooth arrangement for gas turbine engine rotor blade tip shroud |
CH699593A1 (en) * | 2008-09-25 | 2010-03-31 | Alstom Technology Ltd | Blade for a gas turbine. |
EP1793086A3 (en) * | 2005-12-03 | 2012-04-25 | Rolls-Royce plc | Turbine blade |
AU2010230482B2 (en) * | 2009-03-30 | 2014-12-04 | Ansaldo Energia Ip Uk Limited | Blade for a gas turbine |
RU2541078C2 (en) * | 2010-05-05 | 2015-02-10 | Альстом Текнолоджи Лтд | Turbine blade and procedure for its manufacture |
WO2017023258A1 (en) * | 2015-07-31 | 2017-02-09 | General Electric Company | Cooling arrangements in turbine blades |
EP3168423A1 (en) * | 2015-11-16 | 2017-05-17 | General Electric Company | Rotor blade with tip shroud cooling passages and method of making same |
JP2017115716A (en) * | 2015-12-24 | 2017-06-29 | 三菱日立パワーシステムズ株式会社 | Seal device |
US9777577B2 (en) | 2012-02-17 | 2017-10-03 | Ansaldo Energia Ip Uk Limited | Component for a thermal machine, in particular a gas turbine |
EP3412869A1 (en) * | 2017-06-07 | 2018-12-12 | General Electric Company | Turbomachine rotor blade |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1013884B1 (en) * | 1998-12-24 | 2005-07-27 | ALSTOM Technology Ltd | Turbine blade with actively cooled head platform |
DE19904229A1 (en) * | 1999-02-03 | 2000-08-10 | Asea Brown Boveri | Cooled turbine blade has shroud formed by sealing rib with integrated cooling channels connected to coolant channel in blade |
EP1041247B1 (en) * | 1999-04-01 | 2012-08-01 | General Electric Company | Gas turbine airfoil comprising an open cooling circuit |
DE10336863A1 (en) * | 2002-09-17 | 2004-03-25 | Alstom (Switzerland) Ltd. | Thermal turbo-machine e.g. gas turbine, has at least two adjacent turbine vanes, and continuous cover band that extends in rear part of vane to smallest cross-section region of maximum plus/minus 3 per cent of chord length |
US6887033B1 (en) * | 2003-11-10 | 2005-05-03 | General Electric Company | Cooling system for nozzle segment platform edges |
DE102007037855A1 (en) * | 2007-08-10 | 2009-02-12 | Rolls-Royce Deutschland Ltd & Co Kg | Vane cover tape with blocking jet generation |
US20140023497A1 (en) * | 2012-07-19 | 2014-01-23 | General Electric Company | Cooled turbine blade tip shroud with film/purge holes |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB855058A (en) * | 1957-02-22 | 1960-11-30 | Rolls Royce | Improvements in or relating to bladed rotor or stator constructions for axial-flow fluid machines for example for compressors or turbines of gas-turbine engines |
GB895615A (en) * | 1960-02-05 | 1962-05-02 | Rolls Royce | A method and apparatus for forming non-circular holes |
GB1437617A (en) * | 1972-09-01 | 1976-06-03 | Gen Electric | Gas turbine |
GB2075129A (en) * | 1980-05-01 | 1981-11-11 | Gen Electric | Tip cap for a rotor blade and method of replacement |
GB2228540A (en) * | 1988-12-07 | 1990-08-29 | Rolls Royce Plc | Cooling of turbine blades |
WO1994011616A1 (en) * | 1992-11-19 | 1994-05-26 | Bmw Rolls-Royce Gmbh | Cooling of the shroud of a turbine blade |
-
1995
- 1995-02-23 GB GB9503575A patent/GB2298246B/en not_active Expired - Fee Related
-
1996
- 1996-01-19 DE DE19601818A patent/DE19601818C2/en not_active Expired - Fee Related
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB855058A (en) * | 1957-02-22 | 1960-11-30 | Rolls Royce | Improvements in or relating to bladed rotor or stator constructions for axial-flow fluid machines for example for compressors or turbines of gas-turbine engines |
GB895615A (en) * | 1960-02-05 | 1962-05-02 | Rolls Royce | A method and apparatus for forming non-circular holes |
GB1437617A (en) * | 1972-09-01 | 1976-06-03 | Gen Electric | Gas turbine |
GB2075129A (en) * | 1980-05-01 | 1981-11-11 | Gen Electric | Tip cap for a rotor blade and method of replacement |
GB2228540A (en) * | 1988-12-07 | 1990-08-29 | Rolls Royce Plc | Cooling of turbine blades |
WO1994011616A1 (en) * | 1992-11-19 | 1994-05-26 | Bmw Rolls-Royce Gmbh | Cooling of the shroud of a turbine blade |
Cited By (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2322167A (en) * | 1996-12-17 | 1998-08-19 | Gen Electric | Turbine blade with squealer tip cooling |
GB2322167B (en) * | 1996-12-17 | 2001-02-07 | Gen Electric | Turbine blade |
GB2413160A (en) * | 2004-04-17 | 2005-10-19 | Rolls Royce Plc | A rotor blade tip cooling arrangement |
GB2413160B (en) * | 2004-04-17 | 2006-08-09 | Rolls Royce Plc | Turbine rotor blades |
US7632062B2 (en) | 2004-04-17 | 2009-12-15 | Rolls-Royce Plc | Turbine rotor blades |
EP1793086A3 (en) * | 2005-12-03 | 2012-04-25 | Rolls-Royce plc | Turbine blade |
GB2434842A (en) * | 2006-02-02 | 2007-08-08 | Rolls Royce Plc | Cooling arrangement for a turbine blade shroud |
GB2451568A (en) * | 2007-07-31 | 2009-02-04 | Gen Electric | Seal tooth arrangement for gas turbine engine rotor blade tip shroud |
GB2451568B (en) * | 2007-07-31 | 2012-06-27 | Gen Electric | Rotor blade |
CH699593A1 (en) * | 2008-09-25 | 2010-03-31 | Alstom Technology Ltd | Blade for a gas turbine. |
WO2010034669A1 (en) * | 2008-09-25 | 2010-04-01 | Alstom Technology Ltd. | Vane for a gas turbine |
US8764395B2 (en) | 2008-09-25 | 2014-07-01 | Alstom Technology Ltd. | Blade for a gas turbine |
AU2010230482B2 (en) * | 2009-03-30 | 2014-12-04 | Ansaldo Energia Ip Uk Limited | Blade for a gas turbine |
RU2543641C2 (en) * | 2009-03-30 | 2015-03-10 | Альстом Текнолоджи Лтд. | Gas turbine blade |
US9464529B2 (en) | 2009-03-30 | 2016-10-11 | General Electric Technology Gmbh | Blade for a gas turbine |
RU2541078C2 (en) * | 2010-05-05 | 2015-02-10 | Альстом Текнолоджи Лтд | Turbine blade and procedure for its manufacture |
US9777577B2 (en) | 2012-02-17 | 2017-10-03 | Ansaldo Energia Ip Uk Limited | Component for a thermal machine, in particular a gas turbine |
WO2017023258A1 (en) * | 2015-07-31 | 2017-02-09 | General Electric Company | Cooling arrangements in turbine blades |
US10605099B2 (en) | 2015-07-31 | 2020-03-31 | General Electric Company | Cooling arrangements in turbine blades |
EP3168423A1 (en) * | 2015-11-16 | 2017-05-17 | General Electric Company | Rotor blade with tip shroud cooling passages and method of making same |
US10202852B2 (en) | 2015-11-16 | 2019-02-12 | General Electric Company | Rotor blade with tip shroud cooling passages and method of making same |
JP2017115716A (en) * | 2015-12-24 | 2017-06-29 | 三菱日立パワーシステムズ株式会社 | Seal device |
EP3412869A1 (en) * | 2017-06-07 | 2018-12-12 | General Electric Company | Turbomachine rotor blade |
US10502069B2 (en) | 2017-06-07 | 2019-12-10 | General Electric Company | Turbomachine rotor blade |
Also Published As
Publication number | Publication date |
---|---|
GB9503575D0 (en) | 1995-04-12 |
GB2298246B (en) | 1998-10-28 |
DE19601818A1 (en) | 1996-08-29 |
DE19601818C2 (en) | 2003-06-18 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20100223 |