EP2426316A1 - Pale de turbine - Google Patents

Pale de turbine Download PDF

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Publication number
EP2426316A1
EP2426316A1 EP20100175230 EP10175230A EP2426316A1 EP 2426316 A1 EP2426316 A1 EP 2426316A1 EP 20100175230 EP20100175230 EP 20100175230 EP 10175230 A EP10175230 A EP 10175230A EP 2426316 A1 EP2426316 A1 EP 2426316A1
Authority
EP
European Patent Office
Prior art keywords
airfoil
tip
turbine blade
main body
shelf
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Withdrawn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
EP20100175230
Other languages
German (de)
English (en)
Inventor
Hans-Thomas Bolms
John J. Marra
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 EP20100175230 priority Critical patent/EP2426316A1/fr
Priority to PCT/EP2011/064827 priority patent/WO2012028584A1/fr
Publication of EP2426316A1 publication Critical patent/EP2426316A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/186—Film 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
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • 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
    • F05D2240/00—Components
    • F05D2240/40—Use of a multiplicity of similar components
    • 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
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the invention relates to a turbine blade comprising a root region for attaching the turbine blade to a carrier, a platform region and an airfoil attached to said platform region, the airfoil comprising integrally formed a suction side wall and a pressure side wall extending from a common leading edge to a trailing edge and transversely from said platform region to a tip region bordering at least one cavity, wherein the cavity is covered by an airfoil tip shelf.
  • Turbine blades which are exposed to the working fluid in order to absorb the kinetic energy of the latter are to be designed with regard to such loads.
  • a turbine blade may be designed in the form of a moving blade fastened to a rotor.
  • a turbine blade may be designed in the form of a guide blade firmly attached to the casing of a turbine. Equally, in both blade types, in particular the tip of the turbine blade is subjected to high thermal loads. In a moving blade, there is also the high mechanical load caused by the rotary movement.
  • the external contour of the airfoil tip shelf is primarily determined by an aerodynamic definition of the object. Furthermore, technical considerations relating to production are an important factor with regard to the shaping.
  • a cooling design is relevant to the further development of a turbine blade, and in this case in particular the airfoil tip, as a result of the high thermal loads. This is because the tip must be cooled in order to achieve a long service life. Without cooling of the airfoil tip, it would rapidly oxidize. Nonetheless, the service-life requirements imposed on guide blades and in particular on moving blades are constantly increasing. That is to say that the component temperature must be kept within readily acceptable limits through the use of a cooling fluid.
  • the use of cooling fluid must be arranged efficiently in order to increase the overall efficiency and the output of a gas turbine.
  • DE 198 131 15 A1 discloses a cooled turbine blade of a gas turbine, the airfoil of which has a multiplicity of webs in the hollow profile, these webs serving as swirl elements. Furthermore, a shroud or blade-stiffening band is arranged on the end of the turbine blade. A cooling-air opening and a cooling-air outlet are connected to the hollow profile around this shroud. Furthermore, the shroud is deformed and has a narrow central section, such that this shroud becomes a lightweight shroud. In a similar manner, a multiplicity of shroud cooling openings are formed parallel to one another in such a way that a form is provided which enables the cooling air to be discharged outwards from the cooling-air outlet.
  • US 6,164,914 shows a turbine blade having a squealer tip.
  • a turbine blade in which the use of cooling medium can be arranged as efficiently as possible and which is also easier to produce would be desirable.
  • the suction side wall of the airfoil main body and the pressure side wall of the airfoil main body both having a wall thickness along its span direction, which is in its tip region almost constant.
  • the airfoil main body does not have at its tip region any projections extending transversely to the side walls.
  • the invention is based on the knowledge, that the casting of the turbine blade or at least of its airfoil main body can be improved, if the outer end of the airfoil main body - the tip region - do not have any projections extending perpendicular to the pressure side wall and suction side wall. Due to the avoidance of the projections, the section side wall and the pressure side wall both having a wall thickness along its span direction, which in tip region is almost constant. This avoids an outer opening of the airfoil main body having a bottle neck - the outer opening of the airfoil main body is large as possible. Such an airfoil main body or a turbine blade having such an airfoil main body can be cast more easily with respect to precision, time and costs. Because of the big outer opening - also known as a core exit hole - in the blade tip region especially control of wall thickness and core position can be improved significantly.
  • the airfoil tip shelf is a cast and/or machine part preferable from the same base material like the airfoil main body or the turbine blade.
  • the bonding surfaces of the airfoil main body and the airfoil tip shelf are machined to allow a sufficient bonding and to stand up the thermal as well mechanical loadings.
  • the casting process for manufacturing the airfoil main body is improved due to the totally open design of the tip region.
  • the whole airfoil surface will be finished to prepare for metallic and/or ceramic oxidation and thermal protection coatings.
  • the main advantage is the decreased complexity of casting, which improves the precision of the cast turbine blade with regard to wall thickness.
  • the scrap rate can be lowered, which save time and costs.
  • the free arrangement of film cooling holes in the airfoil tip shelf using established bonding technologies improves the service-lifetime.
  • an efficient tip cooling can be applied due to an easy access of the cavity. This can lead to a reduced thermal loading and less mass at the airfoil tip. The latter is mostly reached due to the avoidance of said perpendicular projections.
  • the airfoil tip shelf comprises a shelf bottom, projections extending transversely from the shelf bottom and parallel to the side walls into the cavity and an impingement cooling plate spaced apart from said shelf bottom by said projections attached to the shelf bottom.
  • the Projections arranged on the cold side of the shelf bottom acting as distance elements which will prevent buckling of the impingement cooling plate due to the centrifugal force.
  • the shelf bottom is cooled by impingement cooling air which is flowing through the impingement cooling openings arranged in the impingement cooling blade to the hot shelf bottom.
  • the airfoil tip shelf is joined to the airfoil main body, the airfoil main body and the airfoil tip shelf being brazed or welded in place.
  • the airfoil tip shelf comprises at least one squealer tip extending outwardly from the shelf bottom.
  • the squealer tip has a wall thickness thinner than the thickness of the pressure side wall or/and suction side wall. This leads to a reduced centrifugal loading in comparison to conventional one-piece-casted airfoils.
  • an impingement cooling plate has the advantage that the mass of the airfoil tip shelf can be kept as small as possible. Furthermore, it is possible to produce the airfoil and the airfoil tip shelf from different materials or same materials in order to be able to realize at the same time special advantages, such as, for example, low weight or high thermal conductivity of the airfoil tip shelf or, for example, high strength of the airfoil.
  • the airfoil tip shelf and/or the tip region of the airfoil main body contain a number of cooling openings.
  • the cooling openings are advantageously formed and/or arranged as film cooling openings, which, in cooling fluid is admitted to the turbine blade, enable a film of cooling fluid to be produced on the outer surface of the turbine blade. This allows additional cooling of thermal high loaded areas.
  • the arrangement of the film cooling holes is very flexible, since the holes can be drilled from both the hot side as well as cold side of the shelf.
  • Figure 1 shows a turbine blade 1 fastened to a rotor 3 of a gas turbine (not described in any more detail).
  • the turbine blade 1 in this case is one of a number of moving blades which are arranged in an annular manner extend radially in a flow duct 5 of the gas turbine and which in their entirety form a blade ring which extends into the annular cross section of the flow duct 5.
  • a multiplicity of such annular blade rings are arranged along an axis 7 of the gas turbine (not described in any more detail) in the same way as the flow duct.
  • a working fluid 9 in the form of a hot-gas mixture is admitted to the flow duct 5 and this hot-gas mixture expands, with the turbine blade 1 being driven, and thus delivers its kinetic energy, with the rotor rotating for driving a generator (not described in any more detail).
  • the turbine blade 1 has - along a blade axis 11 arranged one after the other towards a turbine blade tip 29 - at least a platform region 13 and an airfoil 15.
  • the airfoil 15 comprises an airfoil main body 12 arranged in the form of a hollow profile and an airfoil tip shelf 17 also arranged in the form of a hollow profile.
  • the platform region 13 surrounds a blade platform for delimiting the flow duct 5 and a blade root, which are not shown in detail.
  • the airfoil 15 comprises a suction side wall 14 and a pressure side wall 16 ( FIG 2 ). Both suction side wall 14 and pressure side wall 16 extend from a common leading edge 18 to a trailing edge 20 while surrounding a cavity 22 containing a passage system 19. As indicated schematically, a cooling fluid 21 can be admitted to the turbine blade 1 via a passage system 19.
  • the cooling of the turbine blade 1 also extends in this case in particular to the airfoil main body 12 and the airfoil tip shelf 17.
  • Figure 2 shows in a perspective sectional view the embodiment according to the invention with regard to a tip region 27 of the turbine blade 1.
  • the airfoil main body 12 and the airfoil tip shelf 17 being produced separately.
  • the airfoil main body 12 is usually produced by casting and designed as a hollow profile.
  • the airfoil tip shelf 17 is - with regard to its cross-section - designed with shelf bottom 31, shoulders 33, spacers 34 and an impingement cooling plate 35.
  • the shoulders 33 and spacers 34 are projections extending transversely from the shelf bottom 31 into the cavity 22.
  • the impingement cooling plate 35 is spaced apart from the shelf bottom 31 by said shoulders 33 and spacers 34.
  • the impingement cooling plate 35 is fixed to the shoulders 33 located close to the side walls 14, 16.
  • the spacers 34 located between the shoulders 33 prevent buckling of the impingement cooling plate 35 due to centrifugal forces occurring during operation of the turbine blade 1.
  • the hollow profile of the airfoil 15 contains the cavity 22 and the airfoil tip shelf 17 has a another cavity 37, which both are part of the cooling system 19 shown in Figure 1 and to which cooling fluid can be admitted.
  • the airfoil main body 12 On its side facing the turbine blade tip 29, shown in Figure 1 , the airfoil main body 12 has in its tip region 27 - in contrast to the turbine blade known from prior art - no wall running transversely to the blade axis 11.
  • both the suction side wall 14 and the pressure side wall 16 having a wall thickness t along their span direction 11, which is also in the tip region 27 of the airfoil main body 12 almost constant.
  • the impingement cooling plate 35 and the shelf bottom 31 are opposite to one another forming a raised floor 45.
  • the other cavity 37 is formed between the impingement cooling plate 35 and the shelf bottom 31, which both extend horizontally over the entire cross section of the hollow airfoil main body 12. This leads to a reduced mass in comparison to known turbine blades, which having impingement cooling plates being at least partially casted together with the airfoil main body.
  • the thickness of the shelf bottom 31 is larger than the thickness of the impingement cooling plate, since the shelf bottom 31 has not only the objection to cover the cavity 22. Besides this, the shelf bottom 31 shall also enhance the mechanical rigidity of the airfoil 15. Due to this, the shelf bottom 31 is firmly connected by bonding, welding or brazing to the airfoil main body 12 directly and not via the impingement cooling plate 35.
  • the raised floor 45 has cooling means, which are explained in detail below.
  • impingement-cooling openings 43 are arranged in the impingement cooling plate 35.
  • the impingement cooling plate 35 is arranged so close to the shelf bottom 31 that an appropriately pressurized cooling medium impinges on the shelf bottom 31 via the impingement-cooling openings 43 and effectively cools the airfoil tip shelf 17 in the course of impingement cooling.
  • This impingement cooling explained could be intensified further by swirl elements (not shown) in the form of nipples and/or dimples arranged on the inner surface of the shelf bottom 31. That is to say that heat absorbed in the airfoil tip shelf is effectively dissipated by the cooling fluid as a result.
  • the shelf bottom 31 has advantageously a number of first cooling openings 39 and second cooling openings 41, through which the cooling medium entered the other cavity 37 can be discharged out of the turbine blade 1.
  • the first cooling openings 39 are inclined relative to the blade axis 11 to lead transversely cooling medium onto a surface of squealer tips 47 extending perpendicular from the shelf bottom 31 outwardly.
  • the shelf bottom 31 has a number of inclined second cooling openings 41 to enable a suitably film-cooling along the outer surfaces of the airfoil 15.
  • the squealer tips 47 and the shelf bottom 31 of the airfoil tip shelf 17 may be cast thinner than conventional one-piece casting practice would allow, providing reduced centrifugals loading on the airfoil walls 14, 16.
  • the wall thickness 63 is smaller than the wall thickness t of the pressure side wall 16 and suction side wall 14.
  • the wall structure of the airfoil tip shelf 17 can have higher porosity (not illustrated) than the wall structure of the airfoil 15.
  • the turbine blade 1 shown provides a core exit hole 77 between the suction side wall 14 and the pressure side wall 16, which in this case is as large as possible. Since the demanding tip geometry, explained here, of the airfoil tip does not have to be cast together with the airfoil main body 12, the casting of the turbine blade 1 is simplified saving both time and cost.
  • connection between airfoil tip shelf 17 and airfoil main body 12 is produced in the joining region 60 in this case by an especially suitable welding, brazing or bonding process.
  • the connecting surfaces between airfoil tip shelf 17 and airfoil main body 12 in the joining region 60 can be produced in an especially simple and precise manner.
  • the core exit hole 77 is closed in the course of a specifically sized fitting of the airfoil tip shelf 17 onto the core exit hole 77.
  • the contact area of the connection can then be further extended, when the projection 34 contacts the inner surfaces of their side walls 14, 16 respectively.
  • the invention relates to a turbine blade (1) for a gas turbine, comprising one after the other along a blade axis (11) towards a turbine blade tip (29), a platform region (13) and a airfoil (15) attached to said platform region, the airfoil (15) comprising an airfoil main body (12) and an airfoil tip shelf (17), the airfoil main body (12) comprises integrally formed a suction side wall (14) and a pressure side wall (16) bordering at least one cavity (37), wherein the cavity (37) is covered by said airfoil tip shelf (17), which is separately manufactured from the airfoil main body (12).

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP20100175230 2010-09-03 2010-09-03 Pale de turbine Withdrawn EP2426316A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP20100175230 EP2426316A1 (fr) 2010-09-03 2010-09-03 Pale de turbine
PCT/EP2011/064827 WO2012028584A1 (fr) 2010-09-03 2011-08-29 Aube de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20100175230 EP2426316A1 (fr) 2010-09-03 2010-09-03 Pale de turbine

Publications (1)

Publication Number Publication Date
EP2426316A1 true EP2426316A1 (fr) 2012-03-07

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP20100175230 Withdrawn EP2426316A1 (fr) 2010-09-03 2010-09-03 Pale de turbine

Country Status (2)

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EP (1) EP2426316A1 (fr)
WO (1) WO2012028584A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3623577A1 (fr) * 2018-09-12 2020-03-18 United Technologies Corporation Agencement de refroidissement d'extrémité d'aube de turbine avec séparation de purge

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170370232A1 (en) * 2015-01-22 2017-12-28 Siemens Energy, Inc. Turbine airfoil cooling system with chordwise extending squealer tip cooling channel
EP3765714B1 (fr) 2018-03-14 2024-01-03 General Electric Technology GmbH Ensemble refroidissement pour ensemble turbine
CN111852575A (zh) * 2020-07-27 2020-10-30 北京全四维动力科技有限公司 涡轮转子叶片及包括其的燃气轮机

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2502242A1 (fr) * 1981-03-20 1982-09-24 Gen Electric Embout rapporte pour aube de rotor
JPS59231102A (ja) * 1983-06-15 1984-12-25 Toshiba Corp ガスタ−ビンの翼
US4519745A (en) 1980-09-19 1985-05-28 Rockwell International Corporation Rotor blade and stator vane using ceramic shell
DE19813115A1 (de) 1997-04-11 1998-10-29 Mangar International Ltd Klosett-Hilfseinrichtung für behinderte und gebrechliche Personen
US6164914A (en) 1999-08-23 2000-12-26 General Electric Company Cool tip blade
US20050091848A1 (en) * 2003-11-03 2005-05-05 Nenov Krassimir P. Turbine blade and a method of manufacturing and repairing a turbine blade
EP1557533A1 (fr) * 2004-01-23 2005-07-27 Siemens Aktiengesellschaft Refroidissement d'une aube de turbine avec faux-plancher entre l'aube et son extrémité
EP1659263A2 (fr) * 2004-11-18 2006-05-24 General Electric Company Système de refroidissement pour une aube de turbine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4519745A (en) 1980-09-19 1985-05-28 Rockwell International Corporation Rotor blade and stator vane using ceramic shell
FR2502242A1 (fr) * 1981-03-20 1982-09-24 Gen Electric Embout rapporte pour aube de rotor
JPS59231102A (ja) * 1983-06-15 1984-12-25 Toshiba Corp ガスタ−ビンの翼
DE19813115A1 (de) 1997-04-11 1998-10-29 Mangar International Ltd Klosett-Hilfseinrichtung für behinderte und gebrechliche Personen
US6164914A (en) 1999-08-23 2000-12-26 General Electric Company Cool tip blade
US20050091848A1 (en) * 2003-11-03 2005-05-05 Nenov Krassimir P. Turbine blade and a method of manufacturing and repairing a turbine blade
EP1557533A1 (fr) * 2004-01-23 2005-07-27 Siemens Aktiengesellschaft Refroidissement d'une aube de turbine avec faux-plancher entre l'aube et son extrémité
EP1659263A2 (fr) * 2004-11-18 2006-05-24 General Electric Company Système de refroidissement pour une aube de turbine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3623577A1 (fr) * 2018-09-12 2020-03-18 United Technologies Corporation Agencement de refroidissement d'extrémité d'aube de turbine avec séparation de purge
US10801334B2 (en) 2018-09-12 2020-10-13 Raytheon Technologies Corporation Cooling arrangement with purge partition

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