EP3124744A1 - Aube directrice avec plateforme refroidie par impact - Google Patents

Aube directrice avec plateforme refroidie par impact Download PDF

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Publication number
EP3124744A1
EP3124744A1 EP15178804.9A EP15178804A EP3124744A1 EP 3124744 A1 EP3124744 A1 EP 3124744A1 EP 15178804 A EP15178804 A EP 15178804A EP 3124744 A1 EP3124744 A1 EP 3124744A1
Authority
EP
European Patent Office
Prior art keywords
impingement cooling
cooling
guide vane
impingement
vane according
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Withdrawn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
EP15178804.9A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Daniela Koch
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
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP15178804.9A priority Critical patent/EP3124744A1/fr
Publication of EP3124744A1 publication Critical patent/EP3124744A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/13—Manufacture by removing material using lasers
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2250/19—Two-dimensional machined; miscellaneous
    • F05D2250/191—Two-dimensional machined; miscellaneous perforated
    • 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

Definitions

  • Such guide vanes are known in the prior art in different configurations and are used in turbomachines to make the enthalpy contained in a hot gas usable.
  • the guide vanes are usually arranged in the form of a blade ring and held on a blade carrier, which is provided in a housing of the turbomachine and fixedly connected thereto.
  • a turbine is provided within the housing adjacent to the vanes.
  • the turbine comprises moving blades, which usually also form a blade ring and are held on a further blade carrier.
  • the further blade carrier is rotatably connected to a housing passing through and rotatably mounted turbine shaft, which is coupled to a drive shaft of a working machine, such as a generator.
  • the enthalpy contained in the hot gas is completely or partially converted into flow energy by the guide vanes.
  • the flowing hot gas is then deflected on the blades, thereby exerting a circumferential force on them.
  • the turbine shaft is activated by the circumferential force acting on the blades Rotation displaces and finally drives the work machine.
  • Such a vane includes a vane platform and an airfoil and blade root projecting from the vane platform on opposite sides.
  • the blade root serves to secure the vane to the blade carrier while the airfoil is formed so that a directional flow can form in the expanding hot gas.
  • the vanes are exposed to a high thermal load due to the high temperature of the hot gas.
  • the concomitant temperature-induced wear of the guide vanes can be reduced for example by a heat-resistant coating of the outer surface.
  • a cavity can be formed within a guide vane, through which a cooling fluid, for example compressed air, can flow.
  • the EP 0 789 806 B1 proposes an improved guide vane whose vane platform is cooled by impingement cooling.
  • a baffle plate is associated with a wall portion, which is arranged within the blade platform spaced from the wall portion to form a baffle cooling space.
  • the impingement cooling plate is penetrated by impingement cooling bores, through which the cooling fluid can be fed to the impingement cooling chamber.
  • the cooling fluid flows through the baffle cooling bores into the baffle cooling chamber, bounces substantially perpendicularly from the inside to the wall section the blade platform, absorbing heat from the wall section. Finally, the heated cooling fluid leaves the impingement cooling chamber, whereby the absorbed heat is removed from the guide vane.
  • the cooling performance of the cooling fluid flowing into the impingement cooling space through the impingement cooling holes may be insufficient.
  • transverse secondary flows of the cooling fluid can be formed, which reduce the achievable cooling capacity, for example by causing a deflection of the cooling fluid flowing through the impingement cooling bores before it impacts on the wall section from the inside.
  • the present invention provides a guide vane of the type mentioned in the introduction, in which the impact cooling openings comprise at least one oblong impingement cooling slot and preferably additionally impact cooling bores.
  • the invention is based on the idea of forming the baffle cooling openings at least partially slit-shaped. Since the cooling fluid flow through a baffle cooling slot is more extensive than that through an impingement cooling bore, a corresponding improvement in the area-related baffle cooling performance is achieved.
  • baffle cooling slots can direct the cooling fluid flowing through it more precisely than baffle cooling bores, so that particularly hot areas of the wall section can be specifically cooled.
  • the cooling fluid walls created by the impingement cooling slots in the impingement cooling space can favorably influence the secondary flow of the cooling fluid in the impingement cooling space.
  • baffle cooling slots can direct the cooling fluid in the impingement cooling space such that a reduction in the achievable cooling capacity due to unfavorable secondary flow is largely avoided.
  • the wall portion is penetrated by film cooling channels, through which the cooling fluid flows from an inner surface to an outer surface of the wall portion.
  • the film cooling causes an immediate cooling of the outer surface of the wall portion and protects the wall portion from the overflowing hot gas, which further increases the thermal load capacity of the blade platform.
  • a closed cooling film along the outer surface of the wall section requires a favorable distribution of the cooling fluid to the film cooling channels.
  • impingement cooling slots direct the cooling fluid in the impingement cooling chamber such that an unfavorable distribution of the cooling fluid is counteracted to the film cooling channels.
  • a plurality of impingement cooling slots is provided. With a suitable arrangement of a plurality of impingement cooling slots, even more expansive areas of the wall section can be efficiently cooled if necessary and / or complex complex secondary flows of the cooling fluid in the impingement cooling compartment can be modeled.
  • a plurality of impingement cooling slots are arranged behind one another in the impingement cooling plate in such a way that they lie on a line.
  • a wall-shaped cooling fluid flow with even greater effective length expansion and / or steering effect can be produced from a plurality of impact cooling slots.
  • a plurality of impingement cooling openings and in particular a plurality of impingement cooling slots are arranged behind one another in the impingement cooling plate such that they lie on a plurality of lines.
  • Multiple lines in the impingement cooling plate allow for differentiated modeling of the secondary flow of cooling fluid in the impingement refrigerator when a single line does not perform the intended or sufficient effect.
  • a plurality of impingement cooling openings / impingement cooling slots are arranged one behind the other in the impingement cooling plate in such a way that they lie on at least two lines extending substantially parallel. Impact cooling slots arranged on parallel lines can produce channel-like structures in the impingement cooling chamber for the precise steering of the secondary flow.
  • impingement cooling bores and impingement cooling slots are arranged alternately on at least one line.
  • the alternating arrangement of impingement cooling bores and impingement cooling slots makes it possible to combine the respective advantages of both opening forms in the impingement cooling plate.
  • At least one line has a straight shape.
  • a straight-shaped line may result in a straight secondary flow of the cooling fluid in the impingement refrigerator.
  • At least one line has a curved shape.
  • a curved line may cause a correspondingly curved secondary flow of the cooling fluid in the impingement cooling space.
  • At least one line has a kinked shape. With a kinked line, abrupt changes of direction in the secondary flow of the cooling fluid can be produced.
  • At least one impingement cooling slot and in particular each impingement cooling slot has a width between 0.1 mm and 0.3 mm, preferably a width of 0.2 mm. Impingement cooling slots of this small width ensure that a sufficient pressure difference is maintained on both sides of the impingement cooling plate, which causes the cooling fluid to flow through the impingement cooling plate into the impingement cooling space.
  • At least one impingement cooling slot and in particular each impingement cooling slot may have a length between 15 mm and 25 mm, preferably a length of 20 mm. Impingement cooling slots of this length produce sufficiently extensive wall-like flow patterns to affect the direction of secondary flows in the impingement cooling space.
  • the impact cooling bores have a diameter between 0.2 mm and 0.8 mm, preferably a diameter of 0.5 mm. Impact cooling bores of this diameter can on the one hand maintain the required pressure difference on both sides of the impingement cooling plate, but on the other hand allow sufficient cooling fluid flow to cool a certain point of the wall section of the blade platform.
  • the impingement cooling bores and / or the at least one impingement cooling slot are introduced into the wall section by means of a laser. This fabrication process is easy to apply and provides the precision needed to produce small diameter baffles and / or baffles.
  • separating elements are provided in the impingement cooling space, which segment the impingement cooling space.
  • solid walls may also be arranged in the impingement cooling space between the wall section of the blade platform and the impingement cooling plate in order to prevent undesired secondary flow progressions.
  • the separating elements are held on the baffle cooling plates.
  • the separating elements can be provided on the baffle cooling plates by embossing. Separating elements held on the baffle plates offer the advantage that they are automatically positioned correctly when the baffle plates are inserted.
  • FIGS. 1 to 4 show a guide vane 1 of a gas turbine according to an embodiment of the present invention.
  • the guide vane 1 can be used in other turbomachinery without further ado.
  • several guide vanes 1 are arranged in the form of a blade ring, which is held on a fixedly connected to a housing of the gas turbine blade carrier.
  • a cavity is formed for cooling in each case, to which a cooling fluid such as compressed air can be supplied.
  • the vane 1 comprises a blade platform 2 and an airfoil 3 and a blade root 4, which protrude from the blade platform 2 on opposite sides.
  • the blade platform 2 has a wall section 5, whose Outside surface 6 is covered by a hot gas, and an inner surface 7, which is covered by a cooling fluid on.
  • the wall portion 5 is penetrated by film cooling channels 8, through which the cooling fluid from the inner surface 7 of the wall portion 5 can flow to the outer surface 6 to cool the outer surface 6 and to protect against the overflowing hot gas.
  • the wall section 5 of the blade platform 2 is associated with an impingement cooling plate 9, which is arranged within the blade platform 2 spaced from the wall section 5 to form an impingement cooling chamber 10.
  • the impingement cooling plate 9 is penetrated by a plurality of impingement cooling bores 11 and elongate impingement cooling slots 12, through which the cooling fluid can be fed to the impingement cooling chamber 10.
  • the impingement cooling holes 11 have a diameter of 0.5 mm.
  • the diameter of the impingement cooling bores 11 can also be between 0.2 mm and 0.8 mm.
  • the impingement cooling slots 12 have a width of 0.2 mm and a length of 20 mm.
  • the width of the baffle cooling slots 12 may be between 0.1 mm and 0.3 mm, the length between 15 mm and 25 mm.
  • the impingement cooling bores 11 and impingement cooling slots 12 are introduced into the impingement cooling plate 9 by means of a laser in the embodiment described here. But you can also in an alternative manner, for example, by drilling or cutting or milling in the impingement cooling plate 9 bring.
  • the impingement cooling bores 11 and impingement cooling slots 12 are arranged one behind the other in such a way that they lie on two lines 13.
  • the two lines 13 extend parallel to each other and have a bent shape.
  • the impingement cooling bores 11 and impingement cooling slots 12 are arranged alternately.
  • the number and shapes of the lines 13 may vary depending on the blade platform 2 and the particular cooling demand. For example, straight and / or curved lines 13 are possible.
  • an arbitrary sequence of Impeller cooling bores 11 and impingement cooling slots 12 may be arranged, in particular, only impingement cooling bores 11 or impingement cooling slots 12 may be provided.
  • separating elements 14 are provided, which are held on the impingement cooling plate 9 and segment the impingement cooling chamber 10.
  • the cooling fluid first flows through the impingement cooling bores 11 and the impingement cooling slots 12 of the impingement cooling plate 9 into the impingement cooling chamber 10 and collides against the inner surface 7 of the wall section 5, absorbing heat of the wall section 5. From the impingement cooling chamber 10, the heated cooling fluid flows through the film cooling channels 8 provided in the wall section 5 onto the outer surface 6 of the blade platform 2. On the outer surface 6, the cooling fluid forms a cooling film that cools the outer surface 6 of the wall section 5 and the outer surface 6 of the wall section 5 protects the overflowing hot gas.
  • FIG. 3 can be achieved by the illustrated kinked shape of the lines 13 indicated by arrows kinking secondary flow of the cooling fluid in the impingement cooling chamber 10. But other directions of flow can be achieved by appropriate arrangement and shaping of the lines 13.
  • An advantage of the guide blade 1 according to the invention lies in an improved cooling of the wall section 5 of the blade platform 2.
  • a strong flow of cooling fluid which can be directed specifically to particularly hot regions of the wall section 5, onto the inner surface 7 of the wall section 5 can be provided by the cooling slots 12 be directed.
  • the cooling fluid in the impingement cooling chamber 10 can be influenced by the relative arrangement of the impingement cooling bores 11 and the impingement cooling slots 12 in such a way that no secondary flow reducing the cooling capacity in the impingement cooling chamber 10 the cooling fluid is formed.
  • the impingement cooling slots 12 generate wall-like cooling fluid streams which segment the impingement cooling chamber 10 like dividing elements 14.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15178804.9A 2015-07-29 2015-07-29 Aube directrice avec plateforme refroidie par impact Withdrawn EP3124744A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15178804.9A EP3124744A1 (fr) 2015-07-29 2015-07-29 Aube directrice avec plateforme refroidie par impact

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15178804.9A EP3124744A1 (fr) 2015-07-29 2015-07-29 Aube directrice avec plateforme refroidie par impact

Publications (1)

Publication Number Publication Date
EP3124744A1 true EP3124744A1 (fr) 2017-02-01

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EP15178804.9A Withdrawn EP3124744A1 (fr) 2015-07-29 2015-07-29 Aube directrice avec plateforme refroidie par impact

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EP (1) EP3124744A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3581762A3 (fr) * 2018-06-14 2020-11-04 United Technologies Corporation Agencement de refroidissement de plateforme pour moteur à turbine à gaz

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6235001A (ja) * 1985-08-09 1987-02-16 Toshiba Corp ガスタ−ビン空気冷却翼
EP0416542A1 (fr) * 1989-09-04 1991-03-13 Hitachi, Ltd. Aube de turbine
EP0789806B1 (fr) 1994-10-31 1998-07-29 Westinghouse Electric Corporation Pale de turbine a gaz avec plateforme refroidie
EP1088964A2 (fr) * 1999-09-30 2001-04-04 General Electric Company Fente pour le refroidissement par impact du bord d'attaque d'une aube pour une turbomachine
US20020076324A1 (en) * 2000-12-19 2002-06-20 Nesim Abuaf Bucket platform cooling scheme and related method
EP1647672A2 (fr) * 2004-10-18 2006-04-19 United Technologies Corporation Ailette ayant un raccordement à grand rayon de courbure refroidi par impact
US20130205794A1 (en) * 2012-02-15 2013-08-15 United Technologies Corporation Gas turbine engine component with impingement and lobed cooling hole
EP2778369A1 (fr) * 2011-11-08 2014-09-17 IHI Corporation Mécanisme de refroidissement par impact de jets, aube de turbine et chambre de combustion

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6235001A (ja) * 1985-08-09 1987-02-16 Toshiba Corp ガスタ−ビン空気冷却翼
EP0416542A1 (fr) * 1989-09-04 1991-03-13 Hitachi, Ltd. Aube de turbine
EP0789806B1 (fr) 1994-10-31 1998-07-29 Westinghouse Electric Corporation Pale de turbine a gaz avec plateforme refroidie
EP1088964A2 (fr) * 1999-09-30 2001-04-04 General Electric Company Fente pour le refroidissement par impact du bord d'attaque d'une aube pour une turbomachine
US20020076324A1 (en) * 2000-12-19 2002-06-20 Nesim Abuaf Bucket platform cooling scheme and related method
EP1647672A2 (fr) * 2004-10-18 2006-04-19 United Technologies Corporation Ailette ayant un raccordement à grand rayon de courbure refroidi par impact
EP2778369A1 (fr) * 2011-11-08 2014-09-17 IHI Corporation Mécanisme de refroidissement par impact de jets, aube de turbine et chambre de combustion
US20130205794A1 (en) * 2012-02-15 2013-08-15 United Technologies Corporation Gas turbine engine component with impingement and lobed cooling hole

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3581762A3 (fr) * 2018-06-14 2020-11-04 United Technologies Corporation Agencement de refroidissement de plateforme pour moteur à turbine à gaz
US10975702B2 (en) 2018-06-14 2021-04-13 Raytheon Technologies Corporation Platform cooling arrangement for a gas turbine engine

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