EP2260181A1 - Leitschaufel mit hakenförmigem befestigungselement für eine gasturbine - Google Patents
Leitschaufel mit hakenförmigem befestigungselement für eine gasturbineInfo
- Publication number
- EP2260181A1 EP2260181A1 EP09721575A EP09721575A EP2260181A1 EP 2260181 A1 EP2260181 A1 EP 2260181A1 EP 09721575 A EP09721575 A EP 09721575A EP 09721575 A EP09721575 A EP 09721575A EP 2260181 A1 EP2260181 A1 EP 2260181A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cover plate
- guide vane
- gas turbine
- trailing edge
- receiving groove
- 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
- 230000007704 transition Effects 0.000 claims abstract description 7
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 238000009825 accumulation Methods 0.000 abstract 1
- 239000000463 material Substances 0.000 description 9
- 230000035882 stress Effects 0.000 description 6
- 102100031118 Catenin delta-2 Human genes 0.000 description 2
- 101000922056 Homo sapiens Catenin delta-2 Proteins 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 241000124804 Sphyrna media Species 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000000930 thermomechanical 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- 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
- F05D2260/30—Retaining components in desired mutual position
Definitions
- the present invention relates to the field of gas turbines. It relates to a guide vane for a gas turbine according to the preamble of claim 1.
- Gas turbines with sequential combustion are known and have proven themselves in industrial use.
- Such a gas turbine which has become known in the art as GT24 / 26, for example, from an article by Joos, F. et al., "Field Experience of the Sequential Combustion System for the ABB GT24 / GT26 Gas Turbine Family", IGTI / ASME 98-GT-220, 1998 Sweden.
- the local Fig. 1 shows the basic structure of such a gas turbine, wherein the local Fig. 1 is reproduced in the present application as Fig. 1. Furthermore, such a gas turbine from EP-B1 - 0 620 362.
- the guide vanes 10 of FIG. 1 have a longitudinally extending airfoil 11 which is delimited in the flow direction of the hot gas (parallel arrows in FIG. 1) by a front edge 14 and a trailing edge 15.
- the blade 11 of a blade head 13 and an outer cover plate 12 (sometimes called shroud, this element is hereinafter referred to only cover plate) limited.
- the blade head 13 limits the annular hot gas channel of the turbine on the inside and usually comes through a not shown in detail
- the cover plate 12 defines with its inner side 19 the hot gas channel to the outside. 2 B07 / 106-0
- a front and rear hook-shaped fastening element 16 and 17 are formed, which serve on the one hand for attachment of the guide vane 10 on the inner housing of the turbine and on the other hand to Recording and fixation of adjacent in the flow direction
- a receiving groove 18 is provided on the rear fastening element 17 into which a heat recovery segment can be pushed in.
- the receiving groove 18 is directed toward the cover plate 12 by a horizontal groove Base 18 'limited, which forms a wedge-shaped portion 19', which is characterized by a large volume of material together with the oblique inner side 19 of the cover plate 12 in the region of the trailing edge 15.
- the transition 21 between the trailing edge 15 of the vane 10 and the cover plate 12 is a critical range for the life of the vane 10, since it sets a high thermal load resulting from a thermal-mechanical mismatch between the cover plate 12 and the blade 11 This results in a peak being superimposed on the stress resulting from the load of the airfoil 11 loaded by the hot gas flow.
- the above-mentioned large volume of material in the wedge-shaped portion 19 'above the trailing edge 15 now leads to a significant increase in the thermal stresses in this important for the life of the vane 10 area and thus to a reduction in the life itself, bearing in mind the fact that modern gas turbines high Require temperatures related to the working fluids, which are in many cases beyond the permissible material temperature economically useful materials.
- the invention aims to remedy this situation. It is therefore an object of the invention to provide a guide vane for gas turbines, which avoids the disadvantages of the previous vanes with extremely small and targeted changes in the design and is characterized by a significantly improved life.
- the object is solved by the entirety of the features of claim 1.
- Essential to the invention is that means are provided on the cover plate of the guide vane between the receiving groove and the trailing edge, which ensure a reduction of the thermal and mechanical stresses in the region of the transition between the trailing edge and cover plate. As a result of this engagement directly on the cover plate in the region of the trailing edge, the thermal and mechanical loads with regard to the service life of the blade can be sustainably improved there in a very simple and efficient manner.
- the cover plate has a reduced material thickness in the region between the trailing edge and the receiving groove. This material reduction effectively minimizes the stresses caused by thermal and mechanical stresses in this area.
- the means for reducing the thermal and mechanical stresses preferably comprise a groove formed between receiving groove and trailing edge in the cover plate, which groove is arranged substantially parallel to the inside of the cover plate and directed counter to the flow direction.
- the vane of the invention can be used to advantage in a gas turbine.
- Figure 1 is a side view of a vane, as has been installed in gas turbines.
- Fig. 2 in a comparable to Fig. 1 representation of a guide vane according to an embodiment of the invention
- Fig. 3 is an enlarged detail of Fig. 2 with the transition from the trailing edge of the airfoil to the rear fastener of the vane.
- FIG. 2 and 3 a guide blade according to an embodiment of the invention is shown in a comparable to FIG. 1 illustration.
- the guide vane 20 in turn comprises an airfoil 11 with leading edge 14 and trailing edge 15, the head in the longitudinal direction of a blade 13 and a cover plate 12 is limited.
- the cover plate 12 also here has an obliquely outwardly inclined inside in the flow direction 19.
- hook-shaped fasteners 16 and 17 are formed, wherein the 5 B07 / 106-0
- Rear fastening element 17 is formed on the rear side of a receiving groove 22 for an adjacent heat spreader 24.
- a substantially parallel to the inner side 19 extending groove 23 is provided, which leads to a significant reduction in the thickness and thus the material volume of the cover plate 12th in the area above the trailing edge 15 leads.
- the rear edge 15 is offset in the direction of flow with respect to the rear fastening element 17 at a distance a (FIG. 3) towards the rear, whereby a further thermal and mechanical decoupling is achieved.
- the groove 23 is disposed below the receiving groove 22.
- the rear edge 15 is set back relative to the fastening element 17 in order to reduce the thermal stress at the critical transition between the trailing edge and the cover plate 12.
- the groove 23 is dimensioned so that the reduction of the volume of material above the trailing edge 15 does not result in a loss of strength due to the intended use of the blade. 6 B07 / 106-0
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH4162008 | 2008-03-19 | ||
PCT/EP2009/051883 WO2009115384A1 (de) | 2008-03-19 | 2009-02-18 | Leitschaufel mit hakenförmigem befestigungselement für eine gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2260181A1 true EP2260181A1 (de) | 2010-12-15 |
EP2260181B1 EP2260181B1 (de) | 2016-08-17 |
Family
ID=39689493
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09721575.0A Active EP2260181B1 (de) | 2008-03-19 | 2009-02-18 | Leitschaufel mit hakenförmigem befestigungselement für eine gasturbine |
Country Status (3)
Country | Link |
---|---|
US (1) | US8147190B2 (de) |
EP (1) | EP2260181B1 (de) |
WO (1) | WO2009115384A1 (de) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2864599T3 (es) | 2011-09-30 | 2021-10-14 | Owens Corning Intellectual Capital Llc | Método de conformación de una malla a partir de materiales fibrosos |
US9371555B2 (en) * | 2012-06-01 | 2016-06-21 | Concordia Laboratories Inc. | Lighting systems and methods of using lighting systems for in vitro potency assay for photofrin |
US10619496B2 (en) | 2013-06-14 | 2020-04-14 | United Technologies Corporation | Turbine vane with variable trailing edge inner radius |
WO2014204608A1 (en) * | 2013-06-17 | 2014-12-24 | United Technologies Corporation | Turbine vane with platform pad |
FR3048015B1 (fr) * | 2016-02-19 | 2020-03-06 | Safran Aircraft Engines | Aube de turbomachine, comprenant un pied aux concentrations de contrainte reduites |
US20180340438A1 (en) * | 2017-05-01 | 2018-11-29 | General Electric Company | Turbine Nozzle-To-Shroud Interface |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
US4573865A (en) * | 1981-08-31 | 1986-03-04 | General Electric Company | Multiple-impingement cooled structure |
US4687413A (en) * | 1985-07-31 | 1987-08-18 | United Technologies Corporation | Gas turbine engine assembly |
US4820116A (en) * | 1987-09-18 | 1989-04-11 | United Technologies Corporation | Turbine cooling for gas turbine engine |
US5201846A (en) * | 1991-11-29 | 1993-04-13 | General Electric Company | Low-pressure turbine heat shield |
CH687269A5 (de) * | 1993-04-08 | 1996-10-31 | Abb Management Ag | Gasturbogruppe. |
EP0844369B1 (de) * | 1996-11-23 | 2002-01-30 | ROLLS-ROYCE plc | Zusammenbau eines Schaufelrotors und dessen Gehäuses |
JPH1150806A (ja) * | 1997-08-04 | 1999-02-23 | Ishikawajima Harima Heavy Ind Co Ltd | ガスタービンのノズル部材 |
US6761529B2 (en) | 2002-07-25 | 2004-07-13 | Mitshubishi Heavy Industries, Ltd. | Cooling structure of stationary blade, and gas turbine |
US7094029B2 (en) * | 2003-05-06 | 2006-08-22 | General Electric Company | Methods and apparatus for controlling gas turbine engine rotor tip clearances |
US6951447B2 (en) * | 2003-12-17 | 2005-10-04 | United Technologies Corporation | Turbine blade with trailing edge platform undercut |
DE102004004014A1 (de) * | 2004-01-27 | 2005-08-18 | Mtu Aero Engines Gmbh | Leitschaufel für eine Turbomaschine |
FR2896548B1 (fr) * | 2006-01-24 | 2011-05-27 | Snecma | Ensemble de redresseurs fixes sectorise pour un compresseur de turbomachine |
US7862300B2 (en) * | 2006-05-18 | 2011-01-04 | Wood Group Heavy Industrial Turbines Ag | Turbomachinery blade having a platform relief hole |
-
2009
- 2009-02-18 WO PCT/EP2009/051883 patent/WO2009115384A1/de active Application Filing
- 2009-02-18 EP EP09721575.0A patent/EP2260181B1/de active Active
-
2010
- 2010-09-17 US US12/884,875 patent/US8147190B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2009115384A1 * |
Also Published As
Publication number | Publication date |
---|---|
US20110016875A1 (en) | 2011-01-27 |
US8147190B2 (en) | 2012-04-03 |
WO2009115384A1 (de) | 2009-09-24 |
EP2260181B1 (de) | 2016-08-17 |
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