EP2418355A1 - Gasturbinenschaufel - Google Patents

Gasturbinenschaufel Download PDF

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Publication number
EP2418355A1
EP2418355A1 EP10172775A EP10172775A EP2418355A1 EP 2418355 A1 EP2418355 A1 EP 2418355A1 EP 10172775 A EP10172775 A EP 10172775A EP 10172775 A EP10172775 A EP 10172775A EP 2418355 A1 EP2418355 A1 EP 2418355A1
Authority
EP
European Patent Office
Prior art keywords
insert
airfoil
basic body
transition portion
gtv
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Withdrawn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
EP10172775A
Other languages
English (en)
French (fr)
Inventor
Janos Szijarto
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 EP10172775A priority Critical patent/EP2418355A1/de
Priority to PCT/EP2011/063557 priority patent/WO2012019975A1/en
Publication of EP2418355A1 publication Critical patent/EP2418355A1/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Withdrawn legal-status Critical Current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
    • 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

Definitions

  • the invention relates to a gas turbine vane comprising an airfoil extending along a central axis from a bottom to a top, a top platform and a bottom platform of a basic body, wherein said top platform and said bottom platform are both attached to said airfoil through a transition portion respectively, a top transition portion and a bottom transition portion, wherein said top platform and said bottom platform are both provided with a cavity connected by an airfoil cavity provided in said airfoil, wherein said cavities are supplied with cooling air for cooling said basic body, wherein an airfoil insert is provided in the airfoil cavity, said airfoil insert channels at least a portion of the cooling air basically along said central axis and is furnished with holes facing an inner surface of the basic body to cool said basic body by jets of cooling air.
  • a gas turbine vane of the incipiently design-type is for example disclosed in US 7,674,092 B2 , which document relates to the cooling of a gas turbine blade or vane by means of specific cooling channel geometry in the airfoil.
  • Modern gas turbines are aiming for increasing efficiency also by increased hot gas temperature.
  • Hot gas, generated by a combustor of a gas turbine is discharged into a hot gas path of an aerodynamics turbine section of the gas turbine provided with vanes and blades to transfer the thermodynamic energy into a kinetic momentum.
  • An essential perception is that an increased hot gas temperature leads to a higher efficiency according to thermodynamic principals.
  • the limiting factors to an umlimited temperature increase are the material properties of components exposed to the hot gas in the hot gas path.
  • Modern gas turbines are operated with hot gas temperatures, which already exceed the material capabilities, which is made possible by extensive cooling of the hot gas components.
  • the thermal capability of the hot gas components is increased by film cooling using cooling air, which is also sometimes called "secondary air".
  • the secondary air enables operation at higher temperatures but on the other hand the efficiency is lowered since the temperature is decreased by the desired cooling effect because the film cooling secondary air is injected into the hot gas path and therefore mixes with the combustion hot gas.
  • a gas turbine vane of the incipiently defined type which is characterized in that said inner surface of said basic body is provided with a defined convex radius in at least one of said top transition portion or bottom transition portion, and that said insert extends along said inner surface of said transition portion provided with the insert and that said insert is provided with impingement holes facing said inner surface to cool said basic body by a jet of cooling air.
  • the defined radius according to the invention of convex shape follows the outer contour of the basic body in the transition portion, which leads to a defined wall thickness in the transition portion, which is significantly thinner than the wall thickness in this area of the conventional blade according to the above US document. Further the extension of the insert along this part of the inner surface in combination with the impingement holes leads to a concentrated cooling, where conventionally heat concentrations occurred.
  • the distribution of the impingement holes can be adjusted to the temperature profile to be expected in the transition portion. Since according to improved distribution of cooling the temperature distribution in the basic body is more uniform and thermal stresses are reduced, which increases the expected lifetime of the component.
  • a preferred embodiment of the invention is provided by a gas turbine vane, wherein a ratio of wall thicknesses of the basic body between the transition portion (top transition portion or bottom transition portion) and the airfoil along said central axis at the same circumferential position with regard to said central axis is below to point 2.0.
  • This design rule leads to an optimized stress distribution with regard to thermally induced stress and mechanically induced stress in the whole basic body.
  • the insert comprises an airfoil insert and a bottom transition portion insert, which are aligned to each other, wherein the airfoil insert extends along the airfoil and the bottom transition portion insert extends along the bottom transition portion.
  • the airfoil insert is basically of cylindrical shape, while the bottom transition portion insert is of a complex geometry similar to a rotation of a progressivly inclining polynomial.
  • a further preferred embodiment of the gas turbine vane provides an insert comprising a top transition portion insert, which extends along the top transition portion and is aligned to the airfoil insert.
  • the provision of the top transition portion insert goes along with the same advantages as the bottom transition portion insert.
  • the basic body maybe provided with holes connecting the airfoil cavity with a hot gas path. These holes should not face the holes of the airfoil insert directly opposing to increase cooling efficiency of the basic body due to the jet of cooling air first hitting the inner surface of the basic body and downstream discharging through holes into the hot gas path for the purpose of film cooling.
  • Figure 1 shows a vane GTV of a gas turbine in a longitudinal cross section along a central axis X.
  • To one end of the vane GTV is assigned the attribute "top” T and to the opposite and of the GTV is assigned the attribute "bottom” B, which attribute is not referred necessarily to the direction of gravity and could also be named differently.
  • the vane GTV comprises a top platform PLT, a top transition portion TTR an airfoil AF, a bottom transition portion BTA, and a bottom platform PLB.
  • the transition portions TR, the airfoil RF and the platform PLT, PLB belong to a basic body BB of the vane GTV.
  • the basic body BB is preferably made of casted steel alloy.
  • the airfoil RF of the basic body BB comprises a trailing edge TE and a leading edge LE is near the location, which is indicated in figure 1 but is not depicted correctly in figure 1 due to the cross section, which cuts away the real leading edge LE.
  • Both platforms PLT, PLB are provided with a cavity CV, a top cavity TCV and a bottom cavity BCV.
  • the top cavity TCV is connected with the bottom cavity BCV by an airfoil cavity AFCV.
  • cooling purpose cooling air A which often is also named secondary air, enters the top cavity TCV, passes the airfoil cavity AFCV and enters the bottom cavity BCV while during the passage through these cavities CV a part of the airflow is consumed for being discharged into a hot gas path AGP surrounding the airfoil AF for the purpose of film cooling through holes not shown in the figure 1 of the basic body BB.
  • the invention focusses on the cooling air A distribution in the cavity CV to cool the basic body BB from the inside.
  • the cooling air A is directed by means of inserts INS directly on the inner surface IS of the basic body BB.
  • An insert INS extends basically along the central axis X from the top cavity TCV through the airfoil cavity AFCV down to the bottom cavity BCV.
  • This insert INS is devided into three parts, a top transition portion insert TTRINS an airfoil insert AFINS and a bottom transition portion insert BTRINS.
  • the top transition portion insert TTRINS is fixed to the inner surface IS of the top cavity TCV of the top platform TCV, wherein it is aligned with the adjacent end of the airfoil insert AFINS.
  • both inserts INS are fixedly connected to the basic body by means of a protrusion on the inner surface IS of the basic body BB.
  • the airfoil insert AFINS is slidingly connected to the bottom transition portion insert BTRINS by means of a sliding connection SLC, which gives the airfoil insert AFINS freedom to move basically in the direction of the central axis X. This freedom of relative movement allows different thermal expansion between the basic body BB and the insert INS.
  • the sliding connection SLC allows relative movement between the airfoil insert AFINS and the basic body and the bottom transition portion insert BTRINS, which is fixedly connected to the basic body BB in the area of the transition portion BTR.
  • Both transition portions TR are provided with a concave radius at the outer surface of the vane GTV and a convex radius on the inner surface IS of the basic body.
  • Said radii are designed in such a way that following a path along the central axis X at the leading edge LE of the vane GTV the wall thickness in the area of the radii does not increase more than double of the wall thickness of the airfoil along its extension in direction of the central axis X.
  • the airfoil insert AFINS is provided with impingement holes IH facing the inner surface IS of the basic body.
  • said top transition portion insert TTRINS and the bottom transition portion insert BTRINS provided with impingement holes IH to provide a jet of cooling air to the inner surface IS of the basic body in this area.
  • a gap GA is provided between the insert INS and the inner surface IS of the basic body BB.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP10172775A 2010-08-13 2010-08-13 Gasturbinenschaufel Withdrawn EP2418355A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP10172775A EP2418355A1 (de) 2010-08-13 2010-08-13 Gasturbinenschaufel
PCT/EP2011/063557 WO2012019975A1 (en) 2010-08-13 2011-08-05 Gas turbine vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10172775A EP2418355A1 (de) 2010-08-13 2010-08-13 Gasturbinenschaufel

Publications (1)

Publication Number Publication Date
EP2418355A1 true EP2418355A1 (de) 2012-02-15

Family

ID=43479594

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10172775A Withdrawn EP2418355A1 (de) 2010-08-13 2010-08-13 Gasturbinenschaufel

Country Status (2)

Country Link
EP (1) EP2418355A1 (de)
WO (1) WO2012019975A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104929698A (zh) * 2014-03-20 2015-09-23 阿尔斯通技术有限公司 具有受冷却圆角的涡轮导叶
EP3495623A1 (de) * 2017-12-11 2019-06-12 United Technologies Corporation Statorschaufel, zugehöriges gasturbinentriebwerk und turbine
EP3656986A1 (de) * 2018-11-23 2020-05-27 United Technologies Corporation Schaufelprofil, zugehörige hüllenanordnung und gasturbinentriebwerk

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10450881B2 (en) 2014-05-08 2019-10-22 Siemens Aktiengesellschaft Turbine assembly and corresponding method of operation

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1452695A1 (de) * 2003-02-18 2004-09-01 Snecma Moteurs Mit verringertem Kühlluftdurchstrom gekühlte Turbinenschaufel
EP1626162A1 (de) * 2004-08-11 2006-02-15 United Technologies Corporation Temperaturtolerante Leitschaufelanordnung
EP1659265A1 (de) * 2004-10-29 2006-05-24 Snecma Gasturbine Leitschaufelträger mit Kühlluftzufuhrsystem
EP1674660A2 (de) * 2004-12-21 2006-06-28 United Technologies Corporation Turbinenkomponente mit Aufprallkühlung und Schmutztrennung
EP1908921A2 (de) * 2006-09-28 2008-04-09 United Technologies Corporation Verfahren zur Prallkühlung einer Turbinenschaufel mit grossem Übergangsradius zwischen Plattform und Schaufelprofil, sowie entsprechendes System und Turbinenschaufel
US7674092B2 (en) 2004-02-27 2010-03-09 Siemens Aktiengesellschaft Blade or vane for a turbomachine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1452695A1 (de) * 2003-02-18 2004-09-01 Snecma Moteurs Mit verringertem Kühlluftdurchstrom gekühlte Turbinenschaufel
US7674092B2 (en) 2004-02-27 2010-03-09 Siemens Aktiengesellschaft Blade or vane for a turbomachine
EP1626162A1 (de) * 2004-08-11 2006-02-15 United Technologies Corporation Temperaturtolerante Leitschaufelanordnung
EP1659265A1 (de) * 2004-10-29 2006-05-24 Snecma Gasturbine Leitschaufelträger mit Kühlluftzufuhrsystem
EP1674660A2 (de) * 2004-12-21 2006-06-28 United Technologies Corporation Turbinenkomponente mit Aufprallkühlung und Schmutztrennung
EP1908921A2 (de) * 2006-09-28 2008-04-09 United Technologies Corporation Verfahren zur Prallkühlung einer Turbinenschaufel mit grossem Übergangsradius zwischen Plattform und Schaufelprofil, sowie entsprechendes System und Turbinenschaufel

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104929698A (zh) * 2014-03-20 2015-09-23 阿尔斯通技术有限公司 具有受冷却圆角的涡轮导叶
US20150267549A1 (en) * 2014-03-20 2015-09-24 Alstom Technology Ltd. Turbine vane with cooled fillet
US9896951B2 (en) * 2014-03-20 2018-02-20 Ansaldo Energia Switzerland AG Turbine vane with cooled fillet
EP3495623A1 (de) * 2017-12-11 2019-06-12 United Technologies Corporation Statorschaufel, zugehöriges gasturbinentriebwerk und turbine
US10619492B2 (en) 2017-12-11 2020-04-14 United Technologies Corporation Vane air inlet with fillet
EP3656986A1 (de) * 2018-11-23 2020-05-27 United Technologies Corporation Schaufelprofil, zugehörige hüllenanordnung und gasturbinentriebwerk

Also Published As

Publication number Publication date
WO2012019975A1 (en) 2012-02-16

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