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EP1267041B1 - Aube de turbine refroidie - Google Patents

Aube de turbine refroidie Download PDF

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Publication number
EP1267041B1
EP1267041B1 EP02405389A EP02405389A EP1267041B1 EP 1267041 B1 EP1267041 B1 EP 1267041B1 EP 02405389 A EP02405389 A EP 02405389A EP 02405389 A EP02405389 A EP 02405389A EP 1267041 B1 EP1267041 B1 EP 1267041B1
Authority
EP
European Patent Office
Prior art keywords
tip
blade
cavity
squealer
cooling
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.)
Expired - Lifetime
Application number
EP02405389A
Other languages
German (de)
English (en)
Other versions
EP1267041A2 (fr
EP1267041A3 (fr
Inventor
Norman Roeloffs
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.)
GE Vernova GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1267041A2 publication Critical patent/EP1267041A2/fr
Publication of EP1267041A3 publication Critical patent/EP1267041A3/fr
Application granted granted Critical
Publication of EP1267041B1 publication Critical patent/EP1267041B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • 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

  • This invention relates to internally cooled blades for gas turbines, and more particularly to a cooling structure for the tip portion of the blade.
  • Gas turbine blades are typically cooled to protect the material of the blades from the high gas temperatures and to prevent their oxidation.
  • the cooling effectively increases the durability of the blades and prolongs their service life.
  • a proven and successful cooling design for turbine blades is the internal cooling.
  • a liquid or gaseous cooling fluid - usually air which is taken from the compressor of the turbine - flows through channels into a cavity between the pressure-side wall of the blade, the suction-side wall and a tip cap.
  • the tip region typically includes the tip cap and a squeal edge extending radially along the pressure and suction side walls.
  • the squeal edge has relatively thin walls and is relatively far away from the cooling air inside the blade. For this reason, it is particularly susceptible to the high temperatures of the gas stream.
  • the cooling of this tip area is particularly important.
  • the cooling channels lead from the cavity within the blade either through the tip cap to a half space enclosed by the squeal edge or through the squeal edge to the crown of that squeal edge.
  • the liquid or gaseous Cooling fluid flows through these channels, cools the half-space and the squealer edge from the inside and - after exiting the outlet openings on the outer surface and finally mixes in the leakage current of the gas turbine.
  • a typical problem encountered with the operation of turbines is occasional, intentional or unintentional rubbing of the blade tip against the outer heat shield or against other components mounted on the turbine housing.
  • the rubbing of the blade tip leads to a smearing of material on the blade tip and to a clogging or even to a complete blocking of the outlet openings of the cooling channels on the blade tip.
  • the cooling of the blade tip is then reduced or even completely interrupted and may result in significant blade damage due to overheating.
  • European Patent Application EP 816 636 discloses a gas turbine blade having a typical squealer tip squealer and cooling channels designed to cool the squealer edge.
  • the channels extend from a cavity within the blade to the pressure side of the blade and through the tip cap to the hemisphere enclosed by the squealer. If the squeal edge rubs against an outer heat shield or other component of the gas turbine, material may fall into the exit openings on the tip cap and clog the channel for the liquid or gaseous cooling fluid.
  • the arrangement of the cooling channels does not ensure optimum cooling of the outermost tip of the squealer.
  • the cooling structure includes cooling channels that extend from a cavity within the blade through the squealer edge on the suction side to the crown of the squealer edge on the suction side. This ensures efficient cooling of the outermost tip area. However, there is a high risk that abraded material will smear and clog the exit holes of the cooling channels.
  • a blade for a turbomachine has a cavity 38 for a cooling fluid, which is closed by an end cap 46. At its tip, the blade has two radially extending side walls 42, 44. From the cavity of the blade, cooling channels pass through the side walls to exit openings at the radial ends of the side walls. These outlets are exposed there abraded material, which could get into the channels and close them.
  • US Pat. No. 5,476,364 discloses a turbine blade without a squeal edge at the tip and with cooling channels extending from an inner cooling channel to the pressure side of the blade tip.
  • the cooling channels are arranged at a specific angle to the tip surface of the blade.
  • the outlet openings of the cooling channels in particular comprise a cavity, which runs through a side wall parallel to the surface of the blade and is formed by the side wall of the outlet opening. This cavity is intended to prevent the exit port from being clogged with material that is being abraded by an annular shroud over the paddles. Instead, the abraded material is intended to divert the flow of coolant in a direction that is more beneficial to the performance of the turbine.
  • This cooling design should work as long as the abraded material particles are small. However, if the particles are larger than the cooling channel, it will likely clog.
  • the object of this invention is to provide a gas turbine blade having a squeal edge and a cooling structure for that squeal edge that allows the cooling fluid to reach the outermost edge of the squeal edge.
  • Cooling construction also provide for sufficient cooling after an intentional or unintentional rubbing with the outer heat shield or other turbine component has occurred and the cooling channels have been blocked or polluted by abraded particles of different sizes.
  • a turbine blade for a gas turbine that extends from a root to a tip and has a pressure side and a suction side includes a pressure side wall, a suction side wall, and a tip cap.
  • the tip of the blade includes the tip cap and a squeal edge extending radially from the pressure side and suction side walls to a tip crown on the pressure and suction sides. Together with the outer surface of the tip cap, the squeal edge forms a half space.
  • the squealer edge comprises a cavity which extends from the half-space into the squealer edge. This cavity extends into the cooling channels, which extend from the cavity within the blade to the tip crown, so that these cooling channels are divided into a first and a second part. The first part leads from the cavity to an exit opening in the cavity and the second part leads from the cavity to an exit opening on the tip crown.
  • the concavity in the squealer provides an additional exit port for the cooling fluid to enter Direction of the tip area can escape.
  • the squeegee edge with the second portion of the cooling channel protects the cavity and the additional exit opening from contact with the outer heat shield or other components and material that is rubbed off on such contact.
  • the exit openings on the tip crown are partially or completely blocked by the abraded material, and the cooling fluid can no longer flow through the second area of the cooling channel to the tip crown to cool the squeal edge from the inside. Instead, the cooling fluid exits through the additional exit opening in the cavity, flows into the half space and from there around the squealer edge to the tip crown.
  • the liquid or gaseous cooling fluid can flow unhindered through the first region into the cavity and thence through the second region of the cooling channel to the tip crown, cooling the squealer edge from the inside by convection.
  • the cooling structure according to the invention thus provides cooling even if the outlet has been smeared.
  • the cooling fluid reaches the outermost edge of the squealer edge both in the cases where the exit openings are free and in the cases where the exit openings are blocked.
  • the cooling design provides cooling regardless of the size of the abraded material particles.
  • the concavity in the squealer edge is provided on both the pressure side and the suction side of the blade.
  • This solution is particularly suitable for blades having outlet openings on the tip crown on both the pressure side and the suction side of the blade.
  • the cavity in the rubbing edge is provided only on the suction side.
  • the exit ports of the cooling channels are located on the pressure side of the tip section below the tip crown. For these discharge ports, the problem of blocking is not as severe as with the discharge ports on the tip crown of the suction side, and accordingly, measures to protect the discharge ports are not absolutely necessary.
  • the cavity according to the invention has a first sidewall which lies substantially in the plane of the outer surface of the tip cap.
  • a second side wall of the cavity extends from said first sidewall of the cavity to a third sidewall substantially parallel to the crown of the squealer edge.
  • the second sidewall of the cavity is either curved or straight, with sharp corners to the first and third sidewalls of the cavity.
  • a cavity with curved or rounded sidewalls is most conveniently made by casting.
  • a cavity with a straight sidewall and sharp corners is more conveniently made by other methods, such as by electrochemical ablation techniques.
  • the squeal edge comprises rounded corners or sharp, for example rectangular, corners. Sharp corners on the squeal edge are advantageous in terms of the leakage current at the blade head, as the sharp corners ensure a higher flow rate.
  • Figure 1 shows a perspective view of the radially outer portion of a rotor blade 1 for a gas turbine according to the invention with a pressure-side wall 2, a suction-side wall 3 and a tip cap 4 at the radial end of the blade.
  • a cooling fluid - usually air, which is taken from the compressor of the turbine - circulates within the cavity 5 and cools the pressure - and suction wall from the inside by convection.
  • the figure shows the tip area of the blade, which includes a squeal edge 6 and protects the tip area of the blade from damage in the event of contact with the housing of the gas turbine.
  • the squealer extends radially from the pressure and The squealer 6 forms together with the tip cap 4 a half space 9.
  • the cooling channels extend from the cavity 5 within the blade through the squealer edge 6 to the tip portion of the blade , The cooling fluid flows through these cooling channels and cools the squealer by cooling from the inside. The cooling fluid then exits the channels through the exit ports, cools the squealer edge by flowing around the crown, and eventually mixes with the leakage flow of the gas turbine.
  • On the pressure side of the blade 1 a plurality of outlet openings 10 of cooling channels on the squealer and slightly below the tip crown 7 are arranged. Several additional outlet openings 11 of the cooling channels are arranged on the tip crown of the suction side 8.
  • the squealer edge comprises a cavity which extends from the tip cap 4 into the squealer edge 6.
  • the cavity divides the cooling channels in the vicinity of the suction side into a first part which extends from the cavity 5 to the outlet openings 11 'in the cavity, and into a second part which extends from the cavity to the outlet openings 11 on the tip crown 8 the suction side extends.
  • Figure 2 shows the cross-section along the line II-II of the tip portion of the blade 1 with the pressure side wall 2 and the suction side wall 3.
  • the cavity 5 is defined by the inner surface 12 and the inner surface 13 of the pressure and the suction side wall and the inner surface 14 of the tip cap 4 is formed.
  • a cooling channel 15 extends in a first part 17 from the cavity 5 through the tip cap 4 to the outlet 11 'and into the cavity 16.
  • the second part 18 of the channel 15 extends from the cavity 16 through the squealer 6 to the outlet 11 on the tip crown 8 the suction side.
  • the cooling fluid 20 can flow freely to the outermost edge of the squealer and mix in the leakage flow 22.
  • the cooling fluid will travel a distance 23 from the cavity 16 into the half space 9 and around the squeal edge to the tip crown 8. In both cases sufficient cooling of the squealer including its outermost edge reached, regardless of the extent to which the second part 18 of the cooling channel is clogged.
  • the cavity 16 is here formed with a rounded or curved side wall which is most conveniently made by casting.
  • a rectangular cavity is most economically produced by a machining design. Both forms are suitable from the standpoint of coolant flow and the effectiveness of the cooling.
  • the squealer 6 has a shape with either sharp, such as rectangular, corners or rounded corners. Concerning the blade tip leakage current, sharp corners result in a better flow rate.
  • a further cooling channel 25 extends from the cavity 5 to the pressure side of the blade 1.
  • the channel 25 leads to an outlet opening 10 which is arranged on the pressure side of the blade and below the tip crown 7 of the pressure side.
  • the cooling fluid 26, which flows through this outlet opening 10 flows around the squealer 6 around, over the top crown 7 of the pressure side in the half-space 9 and from there into the leakage stream 22. Since the outlet openings 10 below the tip crown are arranged, they are not so prone to clogging with abraded material as the outlet openings on the tip crown of the suction side and therefore need no protection.
  • the cooling channels extend on the pressure side all the way to the tip crown, as is the case along the suction side of the blade.
  • the squeal edge Similar to the cooling structure on the suction side, which is indicated in the figure, the squeal edge also includes a cavity on the pressure side, which divides the cooling channel into two parts in the same way as on the suction side of the blade.
  • cooling channels leading to the pressure side provide sufficient cooling of the squealer edge, so that a construction with a cavity on that side is not necessary.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (6)

  1. Aube (1) pour une turbine à gaz, constituée d'une paroi côté pression (2) et d'une paroi côté aspiration (3), d'un capuchon en pointe (4), d'un espace creux (5), qui est formé par la surface interne (12, 13, 14) de la paroi côté pression (2), de la paroi côté aspiration (3) et du capuchon en pointe (4), d'une arête de frottement (6) s'étendant radialement depuis la paroi côté pression et la paroi côté aspiration (2, 3), qui présente une couronne en pointe (7, 8), d'un demi-espace (9) qui est formé par la surface extérieure du capuchon en pointe (4) et l'arête de frottement (6) et de canaux de refroidissement (15), qui conduisent de l'espace creux (5) à l'arête de frottement (6) et qui débouchent sur la couronne en pointe (7, 8) de l'arête de frottement (6) dans une ouverture de sortie,
    caractérisée en ce que
    l'arête de frottement (6) présente un évidement (16) qui s'étend depuis le demi-espace (9) dans l'arête de frottement (6), de sorte que l'évidement (16) divise les canaux de refroidissement (15) à chaque fois en une première partie (17) et une deuxième partie (18), la première partie (17) présentant une ouverture de sortie (11') dans l'évidement (16) de sorte qu'un fluide de refroidissement (20, 23) puisse s'écouler dans le demi-espace (9) et autour de l'arête de frottement (6), et la deuxième partie (18) conduisant à l'ouverture de sortie (11) sur la couronne en pointe (8) de l'arête de frottement (6) .
  2. Aube (1) selon la revendication 1,
    caractérisée en ce que
    l'évidement s'étend dans l'arête de frottement (6) à la fois le long du côté pression et le long du côté aspiration de l'aube (1).
  3. Aube (1) selon la revendication 1,
    caractérisée en ce que
    l'évidement (16) s'étend dans l'arête de frottement (6) le long du côté d'aspiration de l'aube (1).
  4. Aube (1) selon l'une quelconque des revendications précédentes,
    caractérisée en ce que
    l'évidement (16) présente une première paroi latérale qui se situe essentiellement dans le plan de la surface extérieure du capuchon en pointe (4), et une deuxième paroi latérale qui s'étend depuis la première paroi latérale jusqu'à une troisième paroi latérale, la troisième paroi latérale s'étendant essentiellement parallèlement à la couronne en pointe (8) de l'arête de frottement.
  5. Aube (1) selon la revendication 4,
    caractérisée en ce que
    la deuxième paroi latérale de l'évidement (16) s'étend soit en courbe soit en ligne droite et présente des coins pointus avec la première et la troisième paroi latérale.
  6. Aube (1) selon l'une quelconque des revendications précédentes,
    caractérisée en ce que
    l'arête de frottement (6) présente des coins arrondis, ou des coins pointus, par exemple à angle droit.
EP02405389A 2001-06-11 2002-05-14 Aube de turbine refroidie Expired - Lifetime EP1267041B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US877083 1997-06-17
US09/877,083 US6527514B2 (en) 2001-06-11 2001-06-11 Turbine blade with rub tolerant cooling construction

Publications (3)

Publication Number Publication Date
EP1267041A2 EP1267041A2 (fr) 2002-12-18
EP1267041A3 EP1267041A3 (fr) 2004-09-29
EP1267041B1 true EP1267041B1 (fr) 2006-06-28

Family

ID=25369214

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02405389A Expired - Lifetime EP1267041B1 (fr) 2001-06-11 2002-05-14 Aube de turbine refroidie

Country Status (3)

Country Link
US (1) US6527514B2 (fr)
EP (1) EP1267041B1 (fr)
DE (1) DE50207362D1 (fr)

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EP3088673A1 (fr) 2015-04-28 2016-11-02 Siemens Aktiengesellschaft Aube rotorique de turbine à gaz, rotor, turbine à gaz et moteur associés

Also Published As

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US6527514B2 (en) 2003-03-04
EP1267041A2 (fr) 2002-12-18
US20020197159A1 (en) 2002-12-26
DE50207362D1 (de) 2006-08-10
EP1267041A3 (fr) 2004-09-29

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