EP3158168A1 - Turbine blade and turbine - Google Patents
Turbine blade and turbineInfo
- Publication number
- EP3158168A1 EP3158168A1 EP15756631.6A EP15756631A EP3158168A1 EP 3158168 A1 EP3158168 A1 EP 3158168A1 EP 15756631 A EP15756631 A EP 15756631A EP 3158168 A1 EP3158168 A1 EP 3158168A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine blade
- turbine
- material recess
- rib
- wall
- 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
- 239000000463 material Substances 0.000 claims abstract description 54
- 238000001816 cooling Methods 0.000 claims abstract description 33
- 230000007613 environmental effect Effects 0.000 claims description 5
- 239000002826 coolant Substances 0.000 abstract description 6
- 239000011796 hollow space material Substances 0.000 abstract 1
- 230000036961 partial effect Effects 0.000 description 5
- 230000000930 thermomechanical effect Effects 0.000 description 5
- 230000007704 transition Effects 0.000 description 4
- 230000003014 reinforcing effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000007373 indentation Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000005266 casting Methods 0.000 description 1
- 150000001768 cations Chemical class 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000001186 cumulative effect Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000002028 premature Effects 0.000 description 1
- 238000005050 thermomechanical fatigue Methods 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
- 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
-
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
-
- 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
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Definitions
- the invention relates to a turbine blade with an internally cooled ⁇ turbine blade, in which a cavity is divided by rib elements in at least one coolant cooling channel and wherein the Rippenele ⁇ ment element extends longitudinally to a free end in the cooling channel fin element.
- the invention further relates to a turbine, re insbesonde ⁇ a gas turbine, with at least one turbine stage umfas ⁇ transmitting a plurality of turbine blades.
- a turbine blade of this type is equipped with an internally cooled turbine blade in order to withstand even high temperatures prevailing in the turbine, especially in a hot gas turbine, thermally and mechanically.
- the turbine blades are often thermally and mechanically loaded higher, in which case it hardly plays a role, whether it is in the
- Turbine blade is a guide vane or a run show ⁇ fel the turbine.
- such innenge ⁇ -cooled turbine airfoil having a cavity can be through which a cooling medium passed therethrough.
- a fin element or a plurality of rib elements is often additionally arranged to form in the cavity at least one cooling channel with an often meandering cooling channel profile.
- the object of the invention is achieved by a turbine blade with an internally cooled turbine blade, in which a cavity is divided by at least one rib element in at least one coolant-carrying cooling channel,
- the rib member in question up to a freely ending in the cooling channel rib member end extending longitudinally, wherein on an inner side of a turbine blade wall ei ⁇ ne arranged next to the rib member end of the relevant Rippenele ⁇ ments material recess is designed in such a way that occurring within the turbine blade clamping ⁇ voltages in a surrounding region the at least one rib element can be reduced.
- thermo-mechanically induced stresses are significantly reduced, whereby material fatigue can be correspondingly well delayed in critical areas in this respect.
- pre- ⁇ called thermo-mechanical stresses are reduced significantly in critical areas of the turbine blade forth by temperature differences between the suction side and the pressure side of the turbine airfoil.
- the present material recess is designed in such a way that they division improvedchrosver- within the fin member, enable in transition areas between the actual rib member and the front side wall of the turbine blade and / or the back wall of the turbine blade, but also in the actual Au ⁇ hstructuren of the turbine airfoil.
- the fin member end around aponsreduzie ⁇ time of at least 10% or preferably greater than 20% or 25%.
- fatigue in particular a fatigue cracking in the sense of the invention detects, which is specific ⁇ ell caused by a thermo-mechanical fatigue of the blade ⁇ materials.
- the LCF-fatigue low cycle fatigue
- the possible number of load cycles to be increased by more than two times, in particular by more than three times, previ- engined usual load cycles.
- a preferred embodiment provides that the mate ⁇ rialauslangung is disposed in an environmental region of a free end in the cooling channel fin element end. Spezi ⁇ ell in an environmental region of a fin element end wel ⁇ ches exposed in a turbine blade leaf cavity en ⁇ det, increased and / or increased thermo-mechanical stresses can occur and cause a faster material fatigue there.
- a particularly preferred embodiment provides that the material recess is arranged axially in front of a head side of a free end in the cooling channel fin element end on a turbine blade blade wall.
- the material recess in different ⁇ union intervals away from the rib element, in particular of the rib element end, can be arranged, especially in view of different designs of various turbine shoveling.
- the material recess angeord less than 30 mm or less than 20 mm, preferably less than 10 mm, spaced from the Rippenele ⁇ ment on a turbine airfoil wall ⁇ net is.
- the material recess can hereby reach as far as the rib element or even be worked into the rib element.
- the rib element may have the material recess at least partially.
- the material recess is preferably arranged more than 1 mm or 5 mm away from the rib element.
- the material recess is designed as at least one par tial ⁇ wall thickness reduction of a turbine airfoil wall.
- the material recess is designed scha ⁇ lenförmig.
- the present material ⁇ recess is arranged, for example, as a concave dent in the turbine ⁇ blade outer wall.
- the material recess can be designed differently. It is particularly advantageous if the material recess is designed as at least one concave cavity on a turbine blade leaf wall. A concavely shaped cavity has very little, if any, effect on the aerodynamics of the turbine blade.
- the Materialausneh ⁇ tion is designed on the inside of a turbine blade blade wall. Specifically, by means of a concave Materialausneh ⁇ tion thermo-mechanical stresses in the surrounding area of the rib member, in particular within the turbine blade outer blade wall advantageously be redirected. In addition makes Fluidic at least at a noticeable at a matrialaus foundedung provided on an inner side of the turbine blade outer wall facing the cavity or the cooling channel.
- the material recess is arranged on the rear wall of the turbine blade.
- present material recess can be produced with different geometrical base shapes.
- the material recess has a circular or oval base surface shape.
- differently configured base shapes may be advantageous.
- the material ⁇ recess has a straight elongated or a curved längli ⁇ che base surface shape.
- Materi ⁇ alausNFung therefrom also have a combined base surface shape or a completely different base area shape.
- the material recess is characterized by an indentation that is trough-shaped or cup-shaped and forms an indentation on the inside of the turbine blade outer wall.
- the turning area of the coolant channel here corresponds ei ⁇ ner curve of the meandering cooling channel profile of thedemit ⁇ telkanals.
- the object of the invention is also achieved by a turbine, in particular ⁇ sondere a gas turbine, with at least one turbine stage comprising a plurality of turbine blades, wherein the at least one turbine stage with a plurality of Turbi ⁇ nenlaufschaufeln and / or Turbinenleitschaufein in accordance with a turbine blade according to one of here includes features described.
- a turbine the turbine blades are less affected by material fatigue or at risk can be operated not only operationally safe and requires less maintenance, but it furthermore has a total of a higher life ⁇ duration, and can thus be operated more economically.
- FIG. 1 schematically shows a partial view of l jossgeoncee ⁇ NEN turbine blade with a cooling channel begren ⁇ a collapsing rib member, prior to its end a rib member Mate Rialaus principleung is formed on the inside of the turbine blade;
- FIG. 2 schematically shows a cross section of the turbine blade shown in FIG.
- each turbine blade 1 is a run ⁇ blade 2 of a hot gas turbine, not shown here.
- the turbine blade 1 has an internally cooled turbine blade leaf 3, wherein the inside 4 of the present Before ⁇ side wall 5 of the turbine blade 3 is shown (Fi gur ⁇ 1).
- Trailing edge region 7 is shown only partially in particular in FIG.
- the turbine blade 3 has a cavity 10, wherein in the present case, this cavity 10 is only partially illustrated by the inside 4 with respect to FIG.
- two rib elements 11 and 12 are located in the cavity 10, by means of which a plurality of spiral elements
- Cooling channel 13 is designed with a meandering cooling passage inside ⁇ half of the cavity 10. Along the wound ⁇ nen cooling channel 13 and its meandering cooling channel course cooling air can be passed as a coolant through the turbine blade 3 through to cool it from the inside.
- cooling channel 13 flows through from a foot area and thus from the direction of an opening fourteenth (see only FIG. 2) of a turbine blade root 15 coming cooling air essentially directly to the leading edge region 6 facing first cooling channel section 16 and the rear edge region 7 facing another cooling channel section 17th
- the meandering cooling channel during the convoluted cooling passage 13 is at least designed in the region of the partial view shown in particular ⁇ sondere by the two rib elements 11 and 12, wherein the first rib member 11, the twodekanalab ⁇ sections 16 and 17 are spatially separated from each other.
- the first rib element 11 terminates freely in the cooling channel 13 with its rib element end 24 defined by its head side 23, specifically in the turning region 19.
- a material recess 29 is formed on the inner side 4 in order to achieve an advantageous stress reduction in this surrounding region 28 of the rib element end 24.
- the material recess 29 is arranged at a distance of less than 10 mm from the head side 23 axially in front of the rib element end 24.
- the material recess 29 is present as a concave, trough-shaped cavity 30 having a substantially oval base surface (not explicitly numbered) on the inner side 4 of the front side wall 5 of the turbine blade 3 out processing ⁇ tet.
- the material recess 29 also embodies a partial wall thickness reduction on the front side wall 5 of the turbine blade 3.
- a reinforcing rib 40 provided with bores 39 is provided.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14182462.3A EP2990598A1 (en) | 2014-08-27 | 2014-08-27 | Turbine blade and turbine |
PCT/EP2015/069615 WO2016030449A1 (en) | 2014-08-27 | 2015-08-27 | Turbine blade and turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3158168A1 true EP3158168A1 (en) | 2017-04-26 |
EP3158168B1 EP3158168B1 (en) | 2023-05-17 |
Family
ID=51398570
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14182462.3A Withdrawn EP2990598A1 (en) | 2014-08-27 | 2014-08-27 | Turbine blade and turbine |
EP15756631.6A Active EP3158168B1 (en) | 2014-08-27 | 2015-08-27 | Turbine blade and turbine |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14182462.3A Withdrawn EP2990598A1 (en) | 2014-08-27 | 2014-08-27 | Turbine blade and turbine |
Country Status (4)
Country | Link |
---|---|
US (1) | US20170234136A1 (en) |
EP (2) | EP2990598A1 (en) |
CN (1) | CN106795770B (en) |
WO (1) | WO2016030449A1 (en) |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5296308A (en) * | 1992-08-10 | 1994-03-22 | Howmet Corporation | Investment casting using core with integral wall thickness control means |
US20040094287A1 (en) * | 2002-11-15 | 2004-05-20 | General Electric Company | Elliptical core support and plug for a turbine bucket |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5431537A (en) * | 1994-04-19 | 1995-07-11 | United Technologies Corporation | Cooled gas turbine blade |
US6142734A (en) * | 1999-04-06 | 2000-11-07 | General Electric Company | Internally grooved turbine wall |
US6390775B1 (en) * | 2000-12-27 | 2002-05-21 | General Electric Company | Gas turbine blade with platform undercut |
US6607355B2 (en) * | 2001-10-09 | 2003-08-19 | United Technologies Corporation | Turbine airfoil with enhanced heat transfer |
DE10217390A1 (en) * | 2002-04-18 | 2003-10-30 | Siemens Ag | turbine blade |
DE50306044D1 (en) * | 2003-09-05 | 2007-02-01 | Siemens Ag | Shovel of a turbine |
EP1757773B1 (en) * | 2005-08-26 | 2008-03-19 | Siemens Aktiengesellschaft | Hollow turbine airfoil |
US8579590B2 (en) * | 2006-05-18 | 2013-11-12 | Wood Group Heavy Industrial Turbines Ag | Turbomachinery blade having a platform relief hole, platform cooling holes, and trailing edge cutback |
FR2924156B1 (en) * | 2007-11-26 | 2014-02-14 | Snecma | TURBINE DAWN |
CH704616A1 (en) * | 2011-03-07 | 2012-09-14 | Alstom Technology Ltd | Turbomachinery component. |
-
2014
- 2014-08-27 EP EP14182462.3A patent/EP2990598A1/en not_active Withdrawn
-
2015
- 2015-08-27 EP EP15756631.6A patent/EP3158168B1/en active Active
- 2015-08-27 WO PCT/EP2015/069615 patent/WO2016030449A1/en active Application Filing
- 2015-08-27 US US15/504,361 patent/US20170234136A1/en not_active Abandoned
- 2015-08-27 CN CN201580045956.6A patent/CN106795770B/en active Active
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5296308A (en) * | 1992-08-10 | 1994-03-22 | Howmet Corporation | Investment casting using core with integral wall thickness control means |
US20040094287A1 (en) * | 2002-11-15 | 2004-05-20 | General Electric Company | Elliptical core support and plug for a turbine bucket |
Non-Patent Citations (1)
Title |
---|
See also references of WO2016030449A1 * |
Also Published As
Publication number | Publication date |
---|---|
EP2990598A1 (en) | 2016-03-02 |
CN106795770B (en) | 2018-12-11 |
WO2016030449A1 (en) | 2016-03-03 |
CN106795770A (en) | 2017-05-31 |
EP3158168B1 (en) | 2023-05-17 |
US20170234136A1 (en) | 2017-08-17 |
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