EP1126134A1 - Aube de turbine à refroidissement à air et à vapeur - Google Patents

Aube de turbine à refroidissement à air et à vapeur Download PDF

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Publication number
EP1126134A1
EP1126134A1 EP00103261A EP00103261A EP1126134A1 EP 1126134 A1 EP1126134 A1 EP 1126134A1 EP 00103261 A EP00103261 A EP 00103261A EP 00103261 A EP00103261 A EP 00103261A EP 1126134 A1 EP1126134 A1 EP 1126134A1
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EP
European Patent Office
Prior art keywords
gas turbine
blade
turbine blade
cavity
steam
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Withdrawn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
EP00103261A
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German (de)
English (en)
Inventor
Peter Dipl.-Ing. Tiemann
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 EP00103261A priority Critical patent/EP1126134A1/fr
Publication of EP1126134A1 publication Critical patent/EP1126134A1/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Withdrawn legal-status Critical Current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
    • F01D5/187—Convection cooling

Definitions

  • the invention relates to a gas turbine blade that is hollow executed and can be cooled by a cooling medium.
  • U.S. Patent 5,320,483 discloses how cooling fluid for cooling a Gas turbine blade in the form of cooling steam in a closed Circuit initiated in a gas turbine blade and after flowing through one with different flow chambers and interior walls equipped, interior Cavity of the turbine blade is brought out again.
  • the Cavity is surrounded by the outer wall of the turbine blade, which is flown by a hot action fluid of the gas turbine is.
  • the outer wall has a substantially constant thickness by considering a cross section through the airfoil area on.
  • Cast gas turbine blades result in over the boundary conditions of the casting process also certain minimum thicknesses.
  • the inevitably relatively thick trailing edges but run the aerodynamic requirements of the gas turbine blade contrary.
  • a loss-free outflow hot gas is only guaranteed with a thin trailing edge. Thick trailing edges in turn impair the efficiency of the gas turbine.
  • the object of the invention is accordingly a gas turbine blade and specify a gas turbine where one efficient cooling with high efficiency is ensured.
  • Another object of the invention is Specification of a method for cooling a Gas turbine blade.
  • a gas turbine blade with a blade wall which is an airfoil with an airfoil surface having, the blade wall a first cavity and a second completely separate from the first cavity Cavity limited, and wherein the first cavity opposite the Blade surface closed and the second cavity is open to the airfoil surface.
  • the first cavity is opposite the hot gas duct in the the gas turbine blade can be installed, is completely closed.
  • the second cavity opens in the hot gas duct.
  • the first cavity is used to guide Steam.
  • the second cavity is used to guide cooling air.
  • the part of the blade wall that delimits the first cavity can thus be cooled by steam cooling.
  • the second part the blade wall that delimits the second cavity cooled by cooling air.
  • the first cavity is part of the Blade wall bounded by a leading edge of the gas turbine blade forms.
  • the thermal load is particularly high Part of the gas turbine blade, namely the leading edge, Can be cooled particularly efficiently by steam cooling.
  • the second cavity is preferably formed by a part the blade wall delimits a trailing edge of the gas turbine blade forms. This is the trailing edge of the gas turbine blade Coolable by cooling air through the opening of the second cavity to the airfoil surface in the Hot gas duct emerges.
  • the second cavity is further preferred in the area of the trailing edge to the airfoil surface open. This has the particular advantage that the trailing edge can be made thin. Especially for Cast gas turbine blades are particularly thin trailing edges producible.
  • the opening of the second cavity the possibility of an additional bracket of the casting core in the casting process. This will in particular bending of the core during casting is reduced.
  • Gas turbine blades which are exclusively steam cooled are in the Usually only pourable so that the casting core in the head and foot area is held. In the middle is by necessity the production of closed cavities no bracket possible.
  • the cast core is bent straight in the Middle of the gas turbine blade may be so significant that caused by the wall thickness fluctuations set the minimum wall thickness for the gas turbine blade becomes.
  • With the additional bracket over an open trailing edge can keep wall thickness fluctuation less and thus, if necessary, the blade wall thickness is made thinner become. At the same time, however, it is still becoming significant Part of the gas turbine blade through steam cooling coolable.
  • the gas turbine blade is directed along a blade axis and has a suction side and a pressure side of the Blade on.
  • the first cavity is preferably through along a connecting the suction side and the pressure side inner rib directed towards the blade axis into second partial cavities divided. The separation of the two cavities is thus realized by an inner stiffening rib. she closes the first cavity completely from the second Cavity. An escape of cooling steam into the hot gas duct therefore does not take place.
  • the air-cooled part of the airfoil preferably extends just so far that the execution of a thin trailing edge is made possible.
  • the gas turbine blade is preferably like a guide blade, further preferred for a first gas turbine stage, educated.
  • a guide vane there is steam cooling easier to implement than with a moving blade because the steam can be supplied via the fixed housing of the guide vane is.
  • the guide vanes of a first gas turbine stage are exposed to high temperatures and must be cooled efficiently.
  • the object directed to a gas turbine is achieved according to the invention solved by a gas turbine with a gas turbine blade according to one of the versions described above, where the first cavity with a steam supply and the second cavity is connected to an air supply.
  • the object directed to a method is achieved according to the invention solved by a method for cooling one in a hot gas duct a gas turbine blade arranged in a gas turbine, where air and steam flow through the gas turbine blade at the same time is directed.
  • the steam is preferably without contact with the hot gas duct passed through the gas turbine blade while the air at least partially escapes into the hot gas duct.
  • a leading edge of the gas turbine blade is preferred with the steam and a trailing edge of the gas turbine blade cooled with the air. At least more are preferred three quarters of the blade wall of a blade of the gas turbine blade cooled with steam.
  • FIG. 1 shows a purely steam-cooled gas turbine blade 1 According to the state of the art.
  • the gas turbine blade 1 is directed along a blade axis 2.
  • the gas turbine blade 1 has a blade wall 3.
  • the blade wall 3 forms an airfoil 4.
  • a gas turbine blade 1 usually also a head and a foot part, which here for clarity are not shown for the sake of it.
  • the airfoil 4 has one Suction side 5 and a pressure side 7.
  • the Blade 4 has a leading edge 9 and a trailing edge 11 on.
  • the blade wall 3 delimits an inner cavity 13.
  • Flow channels 15 arranged.
  • Such a gas turbine blade 1 is one in the hot gas duct Arranged gas turbine and is surrounded by very hot gas.
  • the gas turbine blade is used to protect against damage 1 chilled. This happens through a closed Steam cooling.
  • steam 17 is injected into the inner cavity 13 passed and returned via the flow channels 15.
  • the steam 17 cools the blade wall very efficiently 3. As a result, the temperature of the blade wall 3 remains below a critical melting point.
  • FIG. 2 shows steam-cooled gas turbine blade 1.
  • the inner cavity 13 in Partial cavities 13A, 13B, 13C, 13D divided. This subdivision is directed along the blade axis 2, the Stiffening ribs connecting suction side 5 with pressure side 7 19 reached.
  • the cooling steam 17 now becomes like a serpentine through the partial cavities 13A, 13B, 13C, 13D and cools the gas turbine blade 1.
  • the gas turbine blades according to FIG. 1 and FIG. 2 show both a closed cooling system, i.e. Cooling steam 17 occurs nowhere in the hot gas duct over the surface of the Blade 4 on.
  • Cooling steam 17 occurs nowhere in the hot gas duct over the surface of the Blade 4 on.
  • the trailing edge 11 a certain Do not fall below the minimum thickness.
  • one Minimum wall thickness of 1.6 mm and a minimum cavity diameter of 1.6 mm are provided, so that a minimum thickness of approx. 5 mm also follows in the area of the trailing edge 11.
  • Hot gas duct closed cooling system With air-cooled turbine blades, there is no need for this Hot gas duct closed cooling system can be provided. This leads to a simplification of the manufacturing process especially with cast turbine blades, as well Possibility of designing relatively thin trailing edges. The resulting benefits in terms of efficiency due to the aerodynamically more favorable design however compensated for by the loss of combustion air sufficient pressure.
  • the cooling air must namely from Compressor of the gas turbine are branched off and is thus no longer with sufficiently high combustion pressure Available.
  • the gas turbine blade 1 from FIG. 3 shows those described above Disadvantages of purely steam-cooled blades on the one hand and purely air-cooled blades, on the other hand, do not more.
  • the gas turbine blade 1 has a first cavity 21, which corresponds to the inner cavity of the gas turbine blade 1 of Figure 2 divided into two part cavities 21A, 21B is. The division is made by an inner rib 22 causes that directed along the blade axis 2 Connects suction side 5 with the pressure side 7.
  • the shovel wall 3 of the gas turbine blade is partially double-walled.
  • a cooling chamber 27 lying in the blade wall 3 extends itself from the leading edge 9 to the end of the first Cavity 21, both on the suction side 5 and on the pressure side 7.
  • the cooling chamber 27 communicates with openings 29 with the first cavity 21.
  • a second cavity 23 is in the region of the trailing edge 11 of the gas turbine blade 1 arranged and partially bordered by the blade wall 3. For Trailing edge 11 is the second cavity 23 to the airfoil surface of the airf
  • the cooling of the gas turbine blades 1 works as follows:
  • the cooling steam 17 is conducted into the first partial cavity 21A.
  • the cooling steam 17 passes out of the partial cavity 21A the openings 29 into the cooling chamber 27 and flows in there Direction to the trailing edge 11. Via further openings 29 the cooling steam 17 again enters the first cavity 21, namely in the second partial cavity 21B.
  • Cooling air 25 is in the second cavity 23 initiated. This flows through the opening of the second cavity 23 past the trailing edge 11 into the hot gas duct. The rear part of the gas turbine blade 1 is thus through the cooling air 25 cooled.
  • the trailing edge 11 can now be thin be executed since no closed ram as with the Steam cooling of the front area must be provided.
  • This thin trailing edge 11 makes it aerodynamically very good reached favorable values so that the efficiency of a gas turbine, in which the gas turbine blade 1 is installed, increases.
  • the opening of the second cavity 23 a cast core also in the area between the head and the Foot side of the gas turbine blade 1 are held.
  • In order to bends of the casting core are significantly reduced and it can have a smaller wall thickness for the gas turbine blade 1 can be achieved.
  • With a smaller wall thickness of the blade wall 3 is a significantly better cooling of the gas turbine blade 1 reachable.
  • the combination of a simultaneous Air and steam cooling of the gas turbine blade 1 enables thus efficient cooling with high efficiency.
  • FIG. 4 schematically shows a gas turbine in a longitudinal section 31.
  • a gas turbine shaft 33 On a gas turbine shaft 33 are in a row arranged a compressor 35, a combustion chamber 39 and a Turbine part 37.
  • the turbine part 37 has a hot gas channel 38 on.
  • Gas turbine blades 1 are arranged in the hot gas duct 38. Vane rings are alternating in succession and blade rings are provided.
  • the in the direction of flow first gas turbine blades 1 belong to a guide vane ring a first stage of the gas turbine 31. This first stage is particularly high temperatures from out of the combustion chamber 39 escaping hot gas exposed.
  • the gas turbine blades 1 are - as explained above - via a combined air and cooled by steam cooling.
  • the compressor is 35 compressor air removed and via an air supply 45 to the gas turbine blades 1 fed.
  • Via a steam supply 43 steam is also supplied to the gas turbine blades 1.
  • this steam comes from a steam turbine one combined gas and steam process.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00103261A 2000-02-17 2000-02-17 Aube de turbine à refroidissement à air et à vapeur Withdrawn EP1126134A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP00103261A EP1126134A1 (fr) 2000-02-17 2000-02-17 Aube de turbine à refroidissement à air et à vapeur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00103261A EP1126134A1 (fr) 2000-02-17 2000-02-17 Aube de turbine à refroidissement à air et à vapeur

Publications (1)

Publication Number Publication Date
EP1126134A1 true EP1126134A1 (fr) 2001-08-22

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EP00103261A Withdrawn EP1126134A1 (fr) 2000-02-17 2000-02-17 Aube de turbine à refroidissement à air et à vapeur

Country Status (1)

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EP (1) EP1126134A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1321627A1 (fr) * 2001-12-21 2003-06-25 Siemens Aktiengesellschaft Aube de turbine à refroidissement à air et à vapeur et procédé de refroidissement
EP1355040A2 (fr) * 2002-04-18 2003-10-22 Siemens Aktiengesellschaft Plate-forme d'aube de turbine avec refroidissement à air et à vapeur
EP1655452A3 (fr) * 2004-11-09 2009-09-16 United Technologies Corporation Configuration pour le refroidissement d'une aube d'une turbomachine
CN102953767A (zh) * 2012-11-05 2013-03-06 西安交通大学 一种高温透平叶片冷却系统
WO2015181488A1 (fr) * 2014-05-28 2015-12-03 Snecma Aube de turbine a refroidissement optimise au niveau de son bord de fuite comprenant des conduits amont et aval et des cavités latérales internes
WO2015181497A1 (fr) * 2014-05-28 2015-12-03 Snecma Aube de turbine a refroidissement optimise
US10570751B2 (en) 2017-11-22 2020-02-25 General Electric Company Turbine engine airfoil assembly

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5320483A (en) 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
EP0894946A1 (fr) * 1997-02-04 1999-02-03 Mitsubishi Heavy Industries, Ltd. Pale fixe de refroidissement pour turbine a gaz
EP0955449A1 (fr) * 1998-03-12 1999-11-10 Mitsubishi Heavy Industries, Ltd. Aube pour turbine à gaz
US6019579A (en) * 1997-03-10 2000-02-01 Mitsubishi Heavy Industries, Ltd. Gas turbine rotating blade

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5320483A (en) 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
EP0894946A1 (fr) * 1997-02-04 1999-02-03 Mitsubishi Heavy Industries, Ltd. Pale fixe de refroidissement pour turbine a gaz
US6019579A (en) * 1997-03-10 2000-02-01 Mitsubishi Heavy Industries, Ltd. Gas turbine rotating blade
EP0955449A1 (fr) * 1998-03-12 1999-11-10 Mitsubishi Heavy Industries, Ltd. Aube pour turbine à gaz

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1321627A1 (fr) * 2001-12-21 2003-06-25 Siemens Aktiengesellschaft Aube de turbine à refroidissement à air et à vapeur et procédé de refroidissement
WO2003054357A2 (fr) * 2001-12-21 2003-07-03 Siemens Aktiengesellschaft Aube de turbine a refroidissement par l'air et la vapeur, et procede de refroidissement d'une aube de turbine
WO2003054357A3 (fr) * 2001-12-21 2003-09-25 Siemens Ag Aube de turbine a refroidissement par l'air et la vapeur, et procede de refroidissement d'une aube de turbine
EP1355040A2 (fr) * 2002-04-18 2003-10-22 Siemens Aktiengesellschaft Plate-forme d'aube de turbine avec refroidissement à air et à vapeur
EP1355040A3 (fr) * 2002-04-18 2005-04-06 Siemens Aktiengesellschaft Plate-forme d'aube de turbine avec refroidissement à air et à vapeur
EP1655452A3 (fr) * 2004-11-09 2009-09-16 United Technologies Corporation Configuration pour le refroidissement d'une aube d'une turbomachine
US7819169B2 (en) 2004-11-09 2010-10-26 United Technologies Corporation Heat transferring cooling features for an airfoil
CN102953767A (zh) * 2012-11-05 2013-03-06 西安交通大学 一种高温透平叶片冷却系统
WO2015181488A1 (fr) * 2014-05-28 2015-12-03 Snecma Aube de turbine a refroidissement optimise au niveau de son bord de fuite comprenant des conduits amont et aval et des cavités latérales internes
WO2015181497A1 (fr) * 2014-05-28 2015-12-03 Snecma Aube de turbine a refroidissement optimise
FR3021699A1 (fr) * 2014-05-28 2015-12-04 Snecma Aube de turbine a refroidissement optimise au niveau de son bord de fuite
FR3021697A1 (fr) * 2014-05-28 2015-12-04 Snecma Aube de turbine a refroidissement optimise
CN106470782A (zh) * 2014-05-28 2017-03-01 赛峰飞机发动机公司 包括上游管道和下游管道以及内侧部空腔的在后缘处具有优化的冷却的涡轮叶片
CN106470782B (zh) * 2014-05-28 2020-05-08 赛峰飞机发动机公司 叶片以及相关的模制装置、涡轮和涡轮机
US10662789B2 (en) 2014-05-28 2020-05-26 Safran Aircraft Engines Turbine blade with optimised cooling at the trailing edge of same comprising upstream and downstream ducts and inner side cavities
US10689985B2 (en) 2014-05-28 2020-06-23 Safran Aircraft Engines Turbine blade with optimised cooling
US10570751B2 (en) 2017-11-22 2020-02-25 General Electric Company Turbine engine airfoil assembly
US11359498B2 (en) 2017-11-22 2022-06-14 General Electric Company Turbine engine airfoil assembly

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