WO2005103452A1 - Turbinenschaufel mit einem prallkühleinsatz - Google Patents
Turbinenschaufel mit einem prallkühleinsatz Download PDFInfo
- Publication number
- WO2005103452A1 WO2005103452A1 PCT/EP2005/051487 EP2005051487W WO2005103452A1 WO 2005103452 A1 WO2005103452 A1 WO 2005103452A1 EP 2005051487 W EP2005051487 W EP 2005051487W WO 2005103452 A1 WO2005103452 A1 WO 2005103452A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- blade
- turbine blade
- sections
- cooling insert
- waveform
- Prior art date
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
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
-
- 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
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/184—Two-dimensional patterned sinusoidal
-
- 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
- F05D2250/00—Geometry
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
Definitions
- the invention relates to a cooled turbine blade, which successively comprises a blade root, a platform area and a hollow blade blade for receiving a sheet-metal impact cooling insert, which has at least two overlapping sections which overlap in an overlap area and which form a gap with a gap opening.
- the invention further relates to a gas turbine according to claim 6.
- a cooled gas turbine blade with sheet-shaped impingement cooling inserts is known.
- a baffle cooling insert which is triangular in cross section in the region of the blade rear edge of the turbine blade, is spaced from the inner surface of the outer wall and is provided with baffle cooling openings.
- US Pat. No. 6,439,847 discloses a turbine blade with an insert made of a shape memory alloy, which increases the size of a cooling system by contraction to improve the cooling of the turbine blade after a threshold temperature has been exceeded.
- the insert which changes in cross-sectional shape, has two overlapping sheet ends that are parallel to
- US 6,439,847 also shows a wave-shaped insert made of a shape memory alloy.
- impingement cooling inserts consist of two separate parts which are pushed one after the other into the cavity of a turbine blade. The first part is fixed gas-tight on the radially inner platform and the second part on the radially outer platform in order to avoid losses in the feed area. The two parts lie against each other in an overlapping, flat sliding seat in order to enable a relative movement during operation of the gas turbine.
- Impact cooling insert can escape unused as leakage.
- the object of the invention is therefore to provide a turbine blade which saves cooling medium. Furthermore, it is an object of the invention to provide a correspondingly improved gas turbine.
- the solution to the problem directed at the turbine blade suggests that, in order to seal the overlap region, the two sections have a wavy cross section and, with respect to the gap opening, are parallel to the latter.
- the solution is based on the knowledge that the wave-shaped overlap of the two sections enlarges the overlap area formed between them and specifically creates a contact area at which the two sections seal against the gap they enclose.
- the waveform has a rising flank between a wave trough and a wave crest and a falling flank between a wave crest and a wave trough.
- the wave form of the two overlapping sections formed by the wave troughs and by the wave crests run approximately parallel, so that contact surfaces are formed between adjacent rising flanks and / or between adjacent falling flanks, which prevent the leakage flow. This leads to a saving of cooling medium.
- the use of such a turbine blade in a gas turbine leads to an increase in efficiency during operation.
- the frequency and / or the amplitude of the waveform of the first element deviates from the second frequency or amplitude of the waveform of the second element. This will surely avoid that the waveform of the two sections in the overlap area is parallel, i.e. towards the
- the frequencies and the amplitudes are to be chosen so that the heat-related
- the installation space required for the overlap area can be particularly space-saving if the overlap area has no more than five oscillation periods in cross section.
- Impact cooling insert made of several parts.
- the parts forming the impingement cooling insert can thus be inserted one after the other into the hollow airfoil from an open blade tip. Then the sections of the individual parts are in one
- FIG. 1 is a perspective view of a turbine blade with an impact cooling insert
- FIG. 2 shows the detailed view of an overlap area of the impact cooling insert of the turbine blade according to FIG. 1 and
- FIG. 3 shows the detailed view of an alternative overlap region of the impact cooling insert of the turbine blade according to FIG. 1.
- FIG. 1 shows a perspective view of a turbine blade 1 according to the invention with a
- the airfoil 2b has at least one cavity 3 in which an impact cooling insert 5 is provided. Furthermore, the airfoil 2b has a front edge 9 of the blade that can be flowed by a hot gas 7 of the gas turbine, from which a suction side wall 11 and a pressure side wall 13 extend to a rear edge 15 of the blade.
- the turbine blade 1 can be both a guide blade and a rotating blade.
- the inner surfaces 19 of the side walls 11, 13 enclose the cavity 3. To form an intermediate space 22, the surface 19 is spaced from the impingement cooling insert 5 by means of a plurality of rib-shaped or circular spacer elements 21.
- a coolant can flow through the coolant channel 23 enclosed in the interior of the impact cooling inserts 5.
- Impingement cooling inserts 5 also have impingement cooling openings 25, through which the cooling medium flowing in the coolant channel 23 can flow and then impact perpendicularly onto the surfaces 19 of the side walls 11, 13 in order to cool them.
- the impact cooling insert 27 is formed in the direction of the blade axis 2a from two separate parts 29, 31, each of which overlaps one another with a section 30, 32 in an overlap region 33, 35.
- the overlap area 33, 35 lies outside the middle blade height.
- the lower part 31 of the impact cooling insert shown in FIG. 1 is fixed gas-tight on the lower platform and the upper part 29 on an upper platform (not shown) in the connection area in order to avoid leaks.
- the hot airfoil 2b expands more in the direction of the airfoil axis 2a than the cool impingement cooling insert 27, it is necessary to move the two fixed parts 29, 31 in the overlap region 33, 35 along the airfoil axis 2a.
- FIGS. 2 and 3 each show an alternative embodiment of the overlap area 33, 35 in a detailed view.
- the impingement cooling insert 5 is spaced from the inner surface 19 to form the intermediate space 22.
- the hot gas 7 flows around the suction side wall 11.
- the cooling medium 36 flows out of the coolant channel 23 through the impingement cooling openings 25 and impinges coolingly on the inner surface 19.
- the two sections 30, 32 are formed with an identical waveform, ie the waveforms of the two sections 30, 32 of the parts 29, 31 have an identical frequency f and an identical amplitude A.
- the wave shape forms between the two sections 30, 32 a meandering gap 37 with a rectilinear gap opening 38 parallel to the wave propagation, from which a leakage reduced by turbulence flows out compared to a leakage in a flat overlap area according to the prior art.
- a position of the sections 30, 32 which is shifted to the left or right relative to one another with respect to FIG falling flanks 40 of the adjacent sections 30, 32 but also lie close together to form a contact surface. A displacement of the two parts 29, 31 perpendicular to it is not possible due to the given geometry of the airfoil 2b and the impact cooling insert 5.
- the contact surface 43 shifts within the overlap region 33, 35 from one period to an adjacent period. Therefore, a minimum number of two periods is expediently provided in the overlap region 33, 35 in order to achieve a particularly secure seal of the coolant channel 23 with respect to the intermediate space 22.
- impingement cooling openings 25 can also be provided in the overlap area 33, 35 for more uniform cooling of the side walls 11, 13, in particular in the area of the wave troughs or wave crests of the sections 30, 32.
- the waveform is not necessarily sinusoidal. The same effect can also be achieved with a waveform consisting of successive semi-circles or semi-ellipses. In addition, a triangular shape, a sawtooth shape or a rectangular shape is also conceivable.
- the improved sealing effect of the impingement cooling insert 5 compared to the flat contact surfaces from the prior art enables cooling air to be achieved, which leads to an increase in efficiency when the turbine blade is used in a gas turbine.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/578,920 US8137055B2 (en) | 2004-04-20 | 2005-04-01 | Turbine blade with an impingement cooling insert |
EP05731679A EP1738060B1 (de) | 2004-04-20 | 2005-04-01 | Turbinenschaufel mit einem prallkühleinsatz |
DE502005004644T DE502005004644D1 (de) | 2004-04-20 | 2005-04-01 | Turbinenschaufel mit einem prallkühleinsatz |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04009326.2 | 2004-04-20 | ||
EP04009326A EP1589192A1 (de) | 2004-04-20 | 2004-04-20 | Turbinenschaufel mit einem Prallkühleinsatz |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005103452A1 true WO2005103452A1 (de) | 2005-11-03 |
Family
ID=34924665
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2005/051487 WO2005103452A1 (de) | 2004-04-20 | 2005-04-01 | Turbinenschaufel mit einem prallkühleinsatz |
Country Status (5)
Country | Link |
---|---|
US (1) | US8137055B2 (de) |
EP (2) | EP1589192A1 (de) |
DE (1) | DE502005004644D1 (de) |
ES (1) | ES2308476T3 (de) |
WO (1) | WO2005103452A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102016207162A1 (de) | 2016-04-27 | 2017-11-02 | Siemens Aktiengesellschaft | Kühlfluidverteiler für eine Schaufel aus mehreren Teileinsätzen |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN100420542C (zh) * | 2006-06-22 | 2008-09-24 | 上海电气电站设备有限公司 | 镶入式焊接隔板的装配工艺 |
JP2010515850A (ja) * | 2007-01-04 | 2010-05-13 | アンサルド エネルジア エス.ピー.エー. | ガスタービンブレード・インサート用スペーサ |
US8206109B2 (en) * | 2009-03-30 | 2012-06-26 | General Electric Company | Turbine blade assemblies with thermal insulation |
US8777569B1 (en) * | 2011-03-16 | 2014-07-15 | Florida Turbine Technologies, Inc. | Turbine vane with impingement cooling insert |
US9719372B2 (en) | 2012-05-01 | 2017-08-01 | General Electric Company | Gas turbomachine including a counter-flow cooling system and method |
US10100659B2 (en) | 2014-12-16 | 2018-10-16 | Rolls-Royce North American Technologies Inc. | Hanger system for a turbine engine component |
US9879554B2 (en) | 2015-01-09 | 2018-01-30 | Solar Turbines Incorporated | Crimped insert for improved turbine vane internal cooling |
PL232314B1 (pl) | 2016-05-06 | 2019-06-28 | Gen Electric | Maszyna przepływowa zawierająca system regulacji luzu |
US10309246B2 (en) | 2016-06-07 | 2019-06-04 | General Electric Company | Passive clearance control system for gas turbomachine |
US10392944B2 (en) | 2016-07-12 | 2019-08-27 | General Electric Company | Turbomachine component having impingement heat transfer feature, related turbomachine and storage medium |
US10605093B2 (en) | 2016-07-12 | 2020-03-31 | General Electric Company | Heat transfer device and related turbine airfoil |
DE102016216858A1 (de) * | 2016-09-06 | 2018-03-08 | Rolls-Royce Deutschland Ltd & Co Kg | Laufschaufel für eine Turbomaschine und Verfahren für den Zusammenbau einer Laufschaufel für eine Turbomaschine |
US10767487B2 (en) * | 2016-11-17 | 2020-09-08 | Raytheon Technologies Corporation | Airfoil with panel having flow guide |
JP6655589B2 (ja) * | 2017-11-29 | 2020-02-26 | 三菱重工業株式会社 | 計測システム、加工システム、計測方法及びプログラム |
CN111764967B (zh) * | 2020-07-06 | 2022-10-14 | 中国航发湖南动力机械研究所 | 涡轮叶片尾缘冷却结构 |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2888241A (en) * | 1954-06-09 | 1959-05-26 | Stalker Corp | Fabricated cooled turbine blades |
GB833770A (en) * | 1956-11-01 | 1960-04-27 | Havilland Engine Co Ltd | Hollow turbine or compressor blades |
GB1261765A (en) * | 1966-12-01 | 1972-01-26 | Gen Electric | Improvements in axial flow turbomachinery vanes |
US3707750A (en) * | 1968-11-14 | 1973-01-02 | Mtu Muenchen Gmbh | Method for manufacturing a turbine blade |
US4056332A (en) * | 1975-05-16 | 1977-11-01 | Bbc Brown Boveri & Company Limited | Cooled turbine blade |
US4403917A (en) * | 1980-01-10 | 1983-09-13 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Turbine distributor vane |
US6439847B2 (en) * | 2000-01-31 | 2002-08-27 | Alstom (Switzerland) Ltd. | Air-cooled turbine blade |
GB2386926A (en) * | 2002-03-27 | 2003-10-01 | Alstom | Two part impingement tube for a turbine blade or vane |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2873944A (en) * | 1952-09-10 | 1959-02-17 | Gen Motors Corp | Turbine blade cooling |
GB753224A (en) * | 1953-04-13 | 1956-07-18 | Rolls Royce | Improvements in or relating to blading for turbines or compressors |
US4257734A (en) * | 1978-03-22 | 1981-03-24 | Rolls-Royce Limited | Guide vanes for gas turbine engines |
JP2001140602A (ja) | 1999-11-12 | 2001-05-22 | Mitsubishi Heavy Ind Ltd | ガスタービン静翼 |
US7104756B2 (en) * | 2004-08-11 | 2006-09-12 | United Technologies Corporation | Temperature tolerant vane assembly |
-
2004
- 2004-04-20 EP EP04009326A patent/EP1589192A1/de not_active Withdrawn
-
2005
- 2005-04-01 WO PCT/EP2005/051487 patent/WO2005103452A1/de active IP Right Grant
- 2005-04-01 US US11/578,920 patent/US8137055B2/en not_active Expired - Fee Related
- 2005-04-01 EP EP05731679A patent/EP1738060B1/de not_active Expired - Fee Related
- 2005-04-01 ES ES05731679T patent/ES2308476T3/es active Active
- 2005-04-01 DE DE502005004644T patent/DE502005004644D1/de active Active
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2888241A (en) * | 1954-06-09 | 1959-05-26 | Stalker Corp | Fabricated cooled turbine blades |
GB833770A (en) * | 1956-11-01 | 1960-04-27 | Havilland Engine Co Ltd | Hollow turbine or compressor blades |
GB1261765A (en) * | 1966-12-01 | 1972-01-26 | Gen Electric | Improvements in axial flow turbomachinery vanes |
US3707750A (en) * | 1968-11-14 | 1973-01-02 | Mtu Muenchen Gmbh | Method for manufacturing a turbine blade |
US4056332A (en) * | 1975-05-16 | 1977-11-01 | Bbc Brown Boveri & Company Limited | Cooled turbine blade |
US4403917A (en) * | 1980-01-10 | 1983-09-13 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Turbine distributor vane |
US6439847B2 (en) * | 2000-01-31 | 2002-08-27 | Alstom (Switzerland) Ltd. | Air-cooled turbine blade |
GB2386926A (en) * | 2002-03-27 | 2003-10-01 | Alstom | Two part impingement tube for a turbine blade or vane |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102016207162A1 (de) | 2016-04-27 | 2017-11-02 | Siemens Aktiengesellschaft | Kühlfluidverteiler für eine Schaufel aus mehreren Teileinsätzen |
WO2017186481A1 (de) | 2016-04-27 | 2017-11-02 | Siemens Aktiengesellschaft | Kühlfluidverteiler, zugehörige schaufel,teileinsatz und verfahren |
Also Published As
Publication number | Publication date |
---|---|
EP1738060A1 (de) | 2007-01-03 |
US20080260537A1 (en) | 2008-10-23 |
EP1738060B1 (de) | 2008-07-09 |
EP1589192A1 (de) | 2005-10-26 |
DE502005004644D1 (de) | 2008-08-21 |
ES2308476T3 (es) | 2008-12-01 |
US8137055B2 (en) | 2012-03-20 |
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