EP2628900A1 - Turbinenleitschaufel mit einem Drosselelement - Google Patents

Turbinenleitschaufel mit einem Drosselelement Download PDF

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Publication number
EP2628900A1
EP2628900A1 EP12155394.5A EP12155394A EP2628900A1 EP 2628900 A1 EP2628900 A1 EP 2628900A1 EP 12155394 A EP12155394 A EP 12155394A EP 2628900 A1 EP2628900 A1 EP 2628900A1
Authority
EP
European Patent Office
Prior art keywords
turbine
throttle element
coolant
vane
region
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.)
Withdrawn
Application number
EP12155394.5A
Other languages
German (de)
English (en)
French (fr)
Inventor
Fathi Ahmad
Nihal Kurt
Mario Nitsche
Marco Schüler
Andreas Varnholt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP12155394.5A priority Critical patent/EP2628900A1/de
Priority to RU2014136803A priority patent/RU2615091C2/ru
Priority to CN201280069754.1A priority patent/CN104126054B/zh
Priority to PCT/EP2012/075256 priority patent/WO2013120560A1/de
Priority to EP12808764.0A priority patent/EP2788583B1/de
Priority to JP2014555956A priority patent/JP6005764B2/ja
Priority to IN5979DEN2014 priority patent/IN2014DN05979A/en
Priority to US14/376,428 priority patent/US9856738B2/en
Publication of EP2628900A1 publication Critical patent/EP2628900A1/de
Withdrawn legal-status Critical Current

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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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • 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
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer

Definitions

  • the invention relates to a turbine guide vane with an aerodynamically curved airfoil, which has a channel system equipped with a throttle element of channel sections for guiding coolant.
  • Such a turbine blade is for example from the WO 01/36790 A1 known.
  • the throttling of the cooling air consumption of the known turbine blade takes place with the aid of a plug, which is attached from outside into the turbine guide vanes at a reversal point of the cooling duct.
  • the flow-through cross section of the reversal point and thus the flow rate of cooling air can be easily adjusted to predetermined dimensions.
  • casting-related dimensional differences arising from the production of the turbine blade can be compensated by means of the plug, whereby an excessive consumption of cooling air can be avoided.
  • the object of the invention is to provide an alternative turbine vane, in which despite a present at the deflection point opening for the removal of coolant from the turbine blade a subsequent throttling is possible.
  • the invention is based on the finding that, in the case of a turbine guide vane with an aerodynamically curved airfoil, which has a duct system comprising duct sections for guiding coolant, equipped with a throttle element, the throttle element must be designed in such a way that it also permits the removal of coolant. Consequently, it should be equipped with an inflow opening, an outflow opening and a channel connecting the two openings.
  • the throttle element is now not alone for throttling. It is also used as a switch for splitting the coolant into two separate coolant streams. The first of the two coolant sub-streams continues to flow within the turbine vane and is used to cool the airfoil and its trailing edge.
  • the other of the two coolant sub-streams is led out of the turbine vane immediately.
  • the latter is particularly advantageous if at the end at which the coolant is led out of the turbine vane, further gas turbine components are arranged, which must either be cooled or with which the turbine vane (or other components) include gaps in which a hot gas could penetrate the gas turbine.
  • the respective gaps are blocked by outflowing coolant, so that the hot gas intrusion can be safely avoided.
  • the throttle element is inserted into the turbine guide vane and designed cup-shaped with a circumferentially arranged inflow opening for coolant, wherein the pot opening of the throttle element is disposed in the outer surface of the turbine vane.
  • the pot opening represents the outflow opening for the flow into the throttle element coolant partial flow.
  • Another advantage of this design is that with a single component inserted into the cast turbine vane - the throttle element - the distribution of the incoming coolant flow into two partial streams can take place.
  • the distribution of the coolant flow depends on the size of the inflow opening and on the remaining flow cross-section at the throttle point in the duct system.
  • turbine operating vanes which are already operational in the field can optionally be retrofitted with such a throttle device without the turbine vanes having to be machined, modified or prepared for this purpose.
  • the pot opening may still have a collar whose diameter is larger than the opening into which the throttle element is inserted. This prevents that when inserting the throttle element this fall into the channel sections and thus can be lost.
  • the turbine guide vane is a cast component, which is designed largely or completely monolithically.
  • the turbine vane includes a foot region and a head region for attachment. Both areas are arranged on both sides of the airfoil.
  • the throttle element may be arranged in the foot area and / or in the head area.
  • the root section of the turbine vane is used to attach the turbine vane on an annular vane carrier.
  • the blade area extends radially inward from the foot region, at the inner end of which the head region adjoins.
  • the foot area and head area generally each comprise a so-called platform for the local, radial delimitation of the hot gas channel of the gas turbine.
  • a low-pressure loss of coolant through the throttle element can take place when the inflow opening faces the incoming coolant flow.
  • the cross-sectional area of all through-flow openings is preferably substantially smaller than the cross-sectional area of the inflow opening.
  • the through-flow openings are located opposite the inflow opening and consequently on the side of the throttle element at which the coolant partial stream remaining in the turbine guide vane for the time being flows out. It is even conceivable that such flow openings are located even in throttle element, if this is not for the removal of cooling air - that is not partially tubular, but solid - configured.
  • the throttle element is arranged in that region which is opposite to the feed.
  • a turbine nozzle 10 for a stationary gas turbine is in FIG. 1 shown in perspective.
  • the turbine vane 10 comprises a foot region 12, an aerodynamically curved airfoil 14 and a head region 16, which follow one another along a longitudinal axis 18.
  • the foot region 12 is located radially outward and the head region 16 is located radially inwards.
  • Both foot region 12 and head region 16 each include a platform 20 which forms the local, radial boundary of the annular hot gas path of the gas turbine in the region of the respective turbine guide vane 10.
  • the airfoil 14 extends through the annular hot gas channel 22.
  • Both foot region 12 and head region 16 have on their sides facing away from the hot gas channel 22 a plurality of hooks 24 for attachment.
  • hooks 24 are used to attach the turbine vane 10 to an annular turbine vane carrier, not shown.
  • the hooks located in the head area 16 serve for fastening a so-called U-ring, which is also not shown here.
  • the airfoil 14 comprises a leading edge 17 and a trailing edge 19, between which a pressure-side and a suction-side airfoil wall 40, 42 extend.
  • FIG. 1 shown blade 14 is not completely perspective, but partially shown in longitudinal section.
  • the channel sections 26 of a channel system 28 present in the interior of the blade 14 are shown.
  • the channel system 28 with the channel sections 26 between the two walls 40, 42 (FIG. FIG. 2 ) arranged.
  • the channel system 28 is configured to guide coolant, which can be supplied via an opening 30 of the turbine guide vane 10 arranged on the base side.
  • three parallel juxtaposed channel portions 26 are provided, two of which are fluidically connected to one another at the head-side region via a deflection region 30.
  • the turbine guide vane 10 has an opening 31 into which a throttle element is connected from the outside 32 is inserted.
  • the throttle element 32 may be welded or soldered to the cast turbine vane 10 at points or peripherally.
  • the throttle element 32 is cup-shaped with a cylindrical shell and a bottom of the pot 34, which is a gap forming a the two channel sections 26 separating partition 36 opposite.
  • FIG. 2 shows the turbine vane 10 according to the section II-II in FIG. 1 with the head portion 16 and the hooks 24 arranged thereon in a perspective view.
  • the throttle element 32 inserted from the outside into the turbine guide vane 10 on the outside is shown in perspective and has an inflow opening 37 which faces one (26a) of the channel sections 26. Through the inflow opening 37 through a pot opening 38 can be seen.
  • the pot bottom 34 is the head-side end 39 ( Fig. 1 ) of the partition wall 36 gap forming opposite.
  • the throttle element 32 is formed cylindrically with a constant diameter.
  • the throttle element is also configured cylindrically with sections of different diameters or conical.
  • the inner surfaces of the airfoil walls 40 42 are spaced, so that the incoming from the channel portion 26 a coolant flow, usually cooling air, flows into two flow streams either into the inflow opening 37 or into the gaps between the blade wall inner surfaces or partition wall 36 and throttle element 32 , The latter partial flow then flows through the channel section 26b and remains in the turbine guide vane 10 for the time being.
  • the partial flow flowing into the inflow opening 37 flows out through the pot opening 38 and can be on the hub side be used for cooling the components located there or to block columns against hot gas intake.
  • one or more flow openings 41 can still be provided in the throttle element.
  • the invention relates to a turbine vane 10 with an aerodynamically curved airfoil 14, which has a equipped with a throttle element 32 channel system 28 of channel portions 26 for guiding coolant.
  • the throttle element 32 is designed for removal of coolant.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12155394.5A 2012-02-14 2012-02-14 Turbinenleitschaufel mit einem Drosselelement Withdrawn EP2628900A1 (de)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP12155394.5A EP2628900A1 (de) 2012-02-14 2012-02-14 Turbinenleitschaufel mit einem Drosselelement
RU2014136803A RU2615091C2 (ru) 2012-02-14 2012-12-12 Направляющая лопатка турбины, снабженная дроссельным элементом
CN201280069754.1A CN104126054B (zh) 2012-02-14 2012-12-12 具有节流元件的涡轮机导向叶片
PCT/EP2012/075256 WO2013120560A1 (de) 2012-02-14 2012-12-12 Turbinenleitschaufel mit einem drosselelement
EP12808764.0A EP2788583B1 (de) 2012-02-14 2012-12-12 Turbinenleitschaufel mit einem drosselelement
JP2014555956A JP6005764B2 (ja) 2012-02-14 2012-12-12 絞り要素を有するタービンガイド翼
IN5979DEN2014 IN2014DN05979A (ru) 2012-02-14 2012-12-12
US14/376,428 US9856738B2 (en) 2012-02-14 2012-12-12 Turbine guide vane with a throttle element

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12155394.5A EP2628900A1 (de) 2012-02-14 2012-02-14 Turbinenleitschaufel mit einem Drosselelement

Publications (1)

Publication Number Publication Date
EP2628900A1 true EP2628900A1 (de) 2013-08-21

Family

ID=47469943

Family Applications (2)

Application Number Title Priority Date Filing Date
EP12155394.5A Withdrawn EP2628900A1 (de) 2012-02-14 2012-02-14 Turbinenleitschaufel mit einem Drosselelement
EP12808764.0A Active EP2788583B1 (de) 2012-02-14 2012-12-12 Turbinenleitschaufel mit einem drosselelement

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP12808764.0A Active EP2788583B1 (de) 2012-02-14 2012-12-12 Turbinenleitschaufel mit einem drosselelement

Country Status (7)

Country Link
US (1) US9856738B2 (ru)
EP (2) EP2628900A1 (ru)
JP (1) JP6005764B2 (ru)
CN (1) CN104126054B (ru)
IN (1) IN2014DN05979A (ru)
RU (1) RU2615091C2 (ru)
WO (1) WO2013120560A1 (ru)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3147455A1 (de) 2015-09-23 2017-03-29 Siemens Aktiengesellschaft Turbinenleitschaufel mit einer drosseleinrichtung
EP3199760A1 (de) * 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Turbinenschaufel mit einem drosselelement

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104481927A (zh) * 2014-12-12 2015-04-01 常州环能涡轮动力股份有限公司 具有双面离心压轮微型涡轮喷气发动机的导流环
CN109374275A (zh) * 2018-11-13 2019-02-22 霍山嘉远智能制造有限公司 一种涡轮导向叶片的内部流道检测工装
KR102207971B1 (ko) * 2019-06-21 2021-01-26 두산중공업 주식회사 터빈 베인, 및 이를 포함하는 터빈
CN112539086A (zh) * 2020-10-27 2021-03-23 哈尔滨广瀚燃气轮机有限公司 涡轮动叶冷却空气分段旋转增压装置

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4526512A (en) * 1983-03-28 1985-07-02 General Electric Co. Cooling flow control device for turbine blades
EP1099825A1 (de) * 1999-11-12 2001-05-16 Siemens Aktiengesellschaft Turbinenschaufel und Verfahren zur Herstellung einer Turbinenschaufel
US20090185893A1 (en) * 2008-01-22 2009-07-23 United Technologies Corporation Radial inner diameter metering plate
WO2009118245A1 (de) * 2008-03-28 2009-10-01 Alstom Technology Ltd Leitschaufel für eine gasturbine sowie gasturbine mit einer solchen leitschaufel

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FR2468727A1 (fr) * 1979-10-26 1981-05-08 Snecma Perfectionnement aux aubes de turbine refroidies
US4526551A (en) * 1980-05-30 1985-07-02 Champion Spark Plug Company Production of electrodes
JPS57153903A (en) 1981-03-20 1982-09-22 Hitachi Ltd Cooling structure for turbing blade
DE3603350A1 (de) * 1986-02-04 1987-08-06 Walter Prof Dipl Ph Sibbertsen Verfahren zur kuehlung thermisch belasteter bauelemente von stroemungsmaschinen, vorrichtung zur durchfuehrung des verfahrens sowie ausbildung thermisch belasteter schaufeln
US4666368A (en) * 1986-05-01 1987-05-19 General Electric Company Swirl nozzle for a cooling system in gas turbine engines
JPH09303103A (ja) 1996-05-16 1997-11-25 Toshiba Corp 閉ループ冷却形タービン動翼
JPH10306701A (ja) 1997-05-08 1998-11-17 Toshiba Corp タービン動翼およびその製造方法
RU2159335C1 (ru) 1999-04-28 2000-11-20 Открытое акционерное общество "А.Люлька-Сатурн" Способ охлаждения рабочего колеса турбины многорежимного турбореактивного двигателя
US7185662B2 (en) * 2003-11-14 2007-03-06 United Technologies Corporation Methods of preparing, cleaning and repairing article and article repaired
EP1789654B1 (de) * 2004-09-16 2017-08-23 General Electric Technology GmbH Strömungsmaschinenschaufel mit fluidisch gekühltem deckband
RU2387846C1 (ru) 2008-10-29 2010-04-27 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Способ охлаждения рабочих лопаток турбины двухконтурного газотурбинного двигателя и устройство для его реализации

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4526512A (en) * 1983-03-28 1985-07-02 General Electric Co. Cooling flow control device for turbine blades
EP1099825A1 (de) * 1999-11-12 2001-05-16 Siemens Aktiengesellschaft Turbinenschaufel und Verfahren zur Herstellung einer Turbinenschaufel
WO2001036790A1 (de) 1999-11-12 2001-05-25 Siemens Aktiengesellschaft Turbinenschaufel und verfahren zur herstellung einer turbinenschaufel
US20090185893A1 (en) * 2008-01-22 2009-07-23 United Technologies Corporation Radial inner diameter metering plate
WO2009118245A1 (de) * 2008-03-28 2009-10-01 Alstom Technology Ltd Leitschaufel für eine gasturbine sowie gasturbine mit einer solchen leitschaufel

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3147455A1 (de) 2015-09-23 2017-03-29 Siemens Aktiengesellschaft Turbinenleitschaufel mit einer drosseleinrichtung
EP3199760A1 (de) * 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Turbinenschaufel mit einem drosselelement

Also Published As

Publication number Publication date
EP2788583B1 (de) 2016-03-02
JP2015507129A (ja) 2015-03-05
RU2014136803A (ru) 2016-04-10
JP6005764B2 (ja) 2016-10-12
US20140377058A1 (en) 2014-12-25
US9856738B2 (en) 2018-01-02
EP2788583A1 (de) 2014-10-15
WO2013120560A1 (de) 2013-08-22
CN104126054A (zh) 2014-10-29
IN2014DN05979A (ru) 2015-06-26
CN104126054B (zh) 2016-02-03
RU2615091C2 (ru) 2017-04-03

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