EP0621920A1 - Kühlung des deckbandes einer turbinenschaufel. - Google Patents
Kühlung des deckbandes einer turbinenschaufel.Info
- Publication number
- EP0621920A1 EP0621920A1 EP94901787A EP94901787A EP0621920A1 EP 0621920 A1 EP0621920 A1 EP 0621920A1 EP 94901787 A EP94901787 A EP 94901787A EP 94901787 A EP94901787 A EP 94901787A EP 0621920 A1 EP0621920 A1 EP 0621920A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- cooling air
- cooling
- shroud segment
- duct
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- 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
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2240/00—Components
- F05B2240/80—Platforms for stationary or moving blades
- F05B2240/801—Platforms for stationary or moving blades cooled platforms
-
- 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
Definitions
- the invention relates to a turbine blade of a gas turbine with at least one cooling air duct running in the blade, and with a shroud segment arranged at the blade tip, which together with other segments of adjacent blades forms a blade reinforcement band, and with one in the shroud segment in the essentially vertical to the blade axis and connected to the blade cooling air duct located in the blade inflow region, from which cooling air bores lead to the surface of the shroud segment.
- Such a cooled gas turbine blade is shown in DE 39 30 324 AI.
- Such cooling not only of the blade, but also of the shroud segment, can result in the thermal loads and geometric deformations of the blade and segment being kept low by thermal influences.
- the thermal stress on a turbine blade is already considerably reduced, but further improved cooling measures are desirable, which the present invention has set out to demonstrate.
- at least one further cooling branch duct runs in the shroud segment, which is connected to a further blade cooling duct located in the blade outflow region or in the center of the blade, and from which cooling air Bores lead to the surface of the shroud segment.
- a shroud segment extends over the entire blade cross-section and can thus become relatively large, effective cooling with only a single cooling air branch duct and the cooling air bores branching therefrom cannot be sufficient.
- at least two, preferably essentially parallel, cooling air branch ducts are provided, each of which is supplied directly by its own blade cooling air duct and which in each case provides effective cooling of essentially the entire shroud, in particular via branching film cooling holes or convection cooling bores. Effect segment.
- both the cooling air branch duct and the cooling air bores which in comparison have a significantly smaller diameter, can be drilled into the shroud segment.
- the cooling air holes should open on the surfaces of the shroud segment and thereby form film cooling holes or convection cooling bores
- the cooling air branch channels should not open on the surface of the shroud segment, since relative to the respective one large cross-section cooling air branch duct, too large a cooling air partial flow would escape uselessly. Therefore, the ends of each cooling air branch duct, which preferably extends over the entire shroud segment, are closed on the end sides or on the surfaces of the shroud segment. This closing is preferably carried out by subsequent build-up welding.
- FIG. 1 shows a top view of a shroud segment of a turbine blade according to the invention
- FIG. 3 shows the view X from FIG. 1
- Fig. 4 shows the view Y of Fig. 3, as well
- FIG. 5 shows the view Z from FIG. 3.
- Reference number 1 denotes a cooled turbine blade of a gas turbine, of which only the blade tip is shown in FIGS. 2 to 5.
- This turbine blade 1 carries a shroud segment 2
- the shape of the edge surfaces 22, 23 creates a positive connection between these turbine blades or their shroud segments 2, so that a circumferential blade reinforcement strip is formed.
- This middle or rear cooling duct system consists of three meandering cooling air ducts 13.
- the cooling air duct 3 on the blade inflow side and the further system of cooling air ducts 13 work independently of one another, i. H. the cooling air channels 3, 13 are supplied with cooling air separately from one another.
- Two cooling air branch ducts 4, 14 and a parallel branch duct 15 are provided in the shroud segment 2.
- the branch channels 4, 14 and the parallel branch channel 15 run essentially parallel to one another and essentially vertically to the longitudinal axis of the turbine blade 1 and, as can be seen, are essentially in the circumferential direction of the one formed by a plurality of adjacent cover band segments 2 , not shown Strengthening band of a conventional turbine blade arrangement oriented.
- the cooling air is via a connecting channel 6 -Stichkanal 4 connected to the blade cooling air duct 3, d. H.
- the cooling air branch duct 4 is supplied with cooling air from the blade cooling air duct 3.
- a multiplicity of cooling air bores 7 branch off from the cooling air branch duct 4, which lead to the surface of the shroud segment 2 and open at this surface and thereby form so-called film cooling holes 8 or convection cooling bores 8. This enables convection cooling in the front region of the shroud segment 2 and additionally film cooling of the sealing edge 21 of this shroud segment.
- the mutually adjacent edge surfaces 22, 23 of the individual shroud segments of mutually adjacent turbine blades are cooled in particular by the cooling air stream emerging via the film cooling holes 8.
- the second cooling air branch duct 14 is connected to the blade cooling air duct 13 via a connecting duct 16. Cooling air bores 9 also branch off from the second cooling air branch duct 14 and also open on the surface of the shroud segment 2 as film cooling holes 10 or as convection cooling bores 10. At the same time, the parallel branch duct 15, which brings about an improved distribution of cooling air, is supplied with cooling air via these cooling air bores 9, which ensure cooling of the shroud segment 2 over a large area. In this case, only a part of the cooling air bores 9 extends from the surface of the shroud segment 2 beyond the parallel branch duct 15 to the cooling branch duct 14. The cooling air flow entering the parallel branch duct 15 can be determined via the number of these cooling air bores 9 connecting the cooling branch duct 14 to the parallel branch duct 15.
- the cooling air branch channels 4, 14 and the parallel branch channel 15 are of relatively large cross section and are produced by drilling. These channels are closed on the end sides of the shroud segment 2, for example by welding. With the two cooling air branch ducts 4, 14 and the additional parallel branch duct 15 as well as with the film cooling holes 8 and the additional convection cooling holes or film cooling holes 10, uniform, effective cooling results not only of the shroud segment 2, but also of the latter Edge surfaces 22, 23 and its sealing edge 21. However, a large number of details can be designed quite differently from the exemplary embodiment shown, without departing from the content of the claims.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB929224241A GB9224241D0 (en) | 1992-11-19 | 1992-11-19 | A turbine blade arrangement |
GB9224241 | 1992-11-19 | ||
PCT/EP1993/003146 WO1994011616A1 (de) | 1992-11-19 | 1993-11-10 | Kühlung des deckbandes einer turbinenschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0621920A1 true EP0621920A1 (de) | 1994-11-02 |
EP0621920B1 EP0621920B1 (de) | 1996-03-20 |
Family
ID=10725339
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP94901787A Expired - Lifetime EP0621920B1 (de) | 1992-11-19 | 1993-11-10 | Kühlung des deckbandes einer turbinenschaufel |
Country Status (5)
Country | Link |
---|---|
US (1) | US5460486A (de) |
EP (1) | EP0621920B1 (de) |
DE (1) | DE59301968D1 (de) |
GB (1) | GB9224241D0 (de) |
WO (1) | WO1994011616A1 (de) |
Families Citing this family (41)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2290833B (en) * | 1994-07-02 | 1998-08-05 | Rolls Royce Plc | Turbine blade |
US5482435A (en) * | 1994-10-26 | 1996-01-09 | Westinghouse Electric Corporation | Gas turbine blade having a cooled shroud |
GB2298246B (en) * | 1995-02-23 | 1998-10-28 | Bmw Rolls Royce Gmbh | A turbine-blade arrangement comprising a shroud band |
GB2298245B (en) * | 1995-02-23 | 1998-10-28 | Bmw Rolls Royce Gmbh | A turbine-blade arrangement comprising a cooled shroud band |
JP3178327B2 (ja) * | 1996-01-31 | 2001-06-18 | 株式会社日立製作所 | 蒸気タービン |
US5785496A (en) * | 1997-02-24 | 1998-07-28 | Mitsubishi Heavy Industries, Ltd. | Gas turbine rotor |
JPH1113402A (ja) * | 1997-06-23 | 1999-01-19 | Mitsubishi Heavy Ind Ltd | ガスタービン冷却翼チップシュラウド |
JP2955252B2 (ja) * | 1997-06-26 | 1999-10-04 | 三菱重工業株式会社 | ガスタービン動翼チップシュラウド |
JP3510467B2 (ja) * | 1998-01-13 | 2004-03-29 | 三菱重工業株式会社 | ガスタービンの動翼 |
EP1391581B1 (de) * | 1998-02-04 | 2013-04-17 | Mitsubishi Heavy Industries, Ltd. | Rotorblatt für Gasturbinen |
EP1013884B1 (de) | 1998-12-24 | 2005-07-27 | ALSTOM Technology Ltd | Turbinenschaufel mit aktiv gekühltem Deckbandelememt |
DE19904229A1 (de) * | 1999-02-03 | 2000-08-10 | Asea Brown Boveri | Gekühlte Turbinenschaufel |
EP1041247B1 (de) * | 1999-04-01 | 2012-08-01 | General Electric Company | Gasturbinenschaufel mit einem offenen Kühlkreislauf |
US6761534B1 (en) | 1999-04-05 | 2004-07-13 | General Electric Company | Cooling circuit for a gas turbine bucket and tip shroud |
DE19963377A1 (de) * | 1999-12-28 | 2001-07-12 | Abb Alstom Power Ch Ag | Turbinenschaufel mit aktiv gekühltem Deckbandelement |
DE10016081A1 (de) * | 2000-03-31 | 2001-10-04 | Alstom Power Nv | Plattenförmiger, auskragender Bauteilabschnitt einer Gasturbine |
DE10064265A1 (de) | 2000-12-22 | 2002-07-04 | Alstom Switzerland Ltd | Vorrichtung und Verfahren zur Kühlung einer Plattform einer Turbinenschaufel |
JP2002201913A (ja) * | 2001-01-09 | 2002-07-19 | Mitsubishi Heavy Ind Ltd | ガスタービンの分割壁およびシュラウド |
US6506022B2 (en) * | 2001-04-27 | 2003-01-14 | General Electric Company | Turbine blade having a cooled tip shroud |
US6887033B1 (en) * | 2003-11-10 | 2005-05-03 | General Electric Company | Cooling system for nozzle segment platform edges |
EP1591626A1 (de) * | 2004-04-30 | 2005-11-02 | Alstom Technology Ltd | Schaufel für Gasturbine |
EP1591625A1 (de) * | 2004-04-30 | 2005-11-02 | ALSTOM Technology Ltd | Deckband für eine Gasturbinenschaufel |
US7442008B2 (en) | 2004-08-25 | 2008-10-28 | Rolls-Royce Plc | Cooled gas turbine aerofoil |
US7686581B2 (en) * | 2006-06-07 | 2010-03-30 | General Electric Company | Serpentine cooling circuit and method for cooling tip shroud |
US7762773B2 (en) * | 2006-09-22 | 2010-07-27 | Siemens Energy, Inc. | Turbine airfoil cooling system with platform edge cooling channels |
US7611324B2 (en) * | 2006-11-30 | 2009-11-03 | General Electric Company | Method and system to facilitate enhanced local cooling of turbine engines |
CH699593A1 (de) * | 2008-09-25 | 2010-03-31 | Alstom Technology Ltd | Schaufel für eine gasturbine. |
GB0901129D0 (en) * | 2009-01-26 | 2009-03-11 | Rolls Royce Plc | Rotor blade |
CH700686A1 (de) * | 2009-03-30 | 2010-09-30 | Alstom Technology Ltd | Schaufel für eine gasturbine. |
US8356978B2 (en) * | 2009-11-23 | 2013-01-22 | United Technologies Corporation | Turbine airfoil platform cooling core |
US9759070B2 (en) * | 2013-08-28 | 2017-09-12 | General Electric Company | Turbine bucket tip shroud |
EP3329100B1 (de) * | 2015-07-31 | 2022-12-14 | General Electric Company | Kühlanordnungen bei turbinenlaufschaufeln |
US9885243B2 (en) | 2015-10-27 | 2018-02-06 | General Electric Company | Turbine bucket having outlet path in shroud |
US10156145B2 (en) | 2015-10-27 | 2018-12-18 | General Electric Company | Turbine bucket having cooling passageway |
US10508554B2 (en) | 2015-10-27 | 2019-12-17 | General Electric Company | Turbine bucket having outlet path in shroud |
US10202852B2 (en) | 2015-11-16 | 2019-02-12 | General Electric Company | Rotor blade with tip shroud cooling passages and method of making same |
US10301945B2 (en) * | 2015-12-18 | 2019-05-28 | General Electric Company | Interior cooling configurations in turbine rotor blades |
US10184342B2 (en) * | 2016-04-14 | 2019-01-22 | General Electric Company | System for cooling seal rails of tip shroud of turbine blade |
US10502069B2 (en) * | 2017-06-07 | 2019-12-10 | General Electric Company | Turbomachine rotor blade |
US10577945B2 (en) * | 2017-06-30 | 2020-03-03 | General Electric Company | Turbomachine rotor blade |
US20190085706A1 (en) * | 2017-09-18 | 2019-03-21 | General Electric Company | Turbine engine airfoil assembly |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1245518A (fr) * | 1957-04-19 | 1960-11-10 | Perfectionnements apportés aux turbines à fluide gazeux chaud | |
US3529902A (en) * | 1968-05-22 | 1970-09-22 | Gen Motors Corp | Turbine vane |
BE755567A (fr) * | 1969-12-01 | 1971-02-15 | Gen Electric | Structure d'aube fixe, pour moteur a turbines a gaz et arrangement de reglage de temperature associe |
GB1605335A (en) * | 1975-08-23 | 1991-12-18 | Rolls Royce | A rotor blade for a gas turbine engine |
US4017213A (en) * | 1975-10-14 | 1977-04-12 | United Technologies Corporation | Turbomachinery vane or blade with cooled platforms |
GB1514613A (en) * | 1976-04-08 | 1978-06-14 | Rolls Royce | Blade or vane for a gas turbine engine |
US4353679A (en) * | 1976-07-29 | 1982-10-12 | General Electric Company | Fluid-cooled element |
JP2862536B2 (ja) * | 1987-09-25 | 1999-03-03 | 株式会社東芝 | ガスタービンの翼 |
GB2223276B (en) * | 1988-09-30 | 1992-09-02 | Rolls Royce Plc | Turbine aerofoil blade |
GB2228540B (en) * | 1988-12-07 | 1993-03-31 | Rolls Royce Plc | Cooling of turbine blades |
GB2250548A (en) * | 1990-12-06 | 1992-06-10 | Rolls Royce Plc | Cooled turbine aerofoil blade |
US5344283A (en) * | 1993-01-21 | 1994-09-06 | United Technologies Corporation | Turbine vane having dedicated inner platform cooling |
-
1992
- 1992-11-19 GB GB929224241A patent/GB9224241D0/en active Pending
-
1993
- 1993-11-10 DE DE59301968T patent/DE59301968D1/de not_active Expired - Fee Related
- 1993-11-10 US US08/256,647 patent/US5460486A/en not_active Expired - Fee Related
- 1993-11-10 EP EP94901787A patent/EP0621920B1/de not_active Expired - Lifetime
- 1993-11-10 WO PCT/EP1993/003146 patent/WO1994011616A1/de active IP Right Grant
Non-Patent Citations (1)
Title |
---|
See references of WO9411616A1 * |
Also Published As
Publication number | Publication date |
---|---|
GB9224241D0 (en) | 1993-01-06 |
EP0621920B1 (de) | 1996-03-20 |
WO1994011616A1 (de) | 1994-05-26 |
DE59301968D1 (de) | 1996-04-25 |
US5460486A (en) | 1995-10-24 |
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