EP2853690A1 - Insert pour le refroidissement d'une aube de turbine constituée de plusieurs pièces partielles - Google Patents

Insert pour le refroidissement d'une aube de turbine constituée de plusieurs pièces partielles Download PDF

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Publication number
EP2853690A1
EP2853690A1 EP13186304.5A EP13186304A EP2853690A1 EP 2853690 A1 EP2853690 A1 EP 2853690A1 EP 13186304 A EP13186304 A EP 13186304A EP 2853690 A1 EP2853690 A1 EP 2853690A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
sections
wall
section
insert 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Withdrawn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
EP13186304.5A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Tobias Dr. Buchal
Daniela Koch
Marco Schüler
Nihal Kurt
Radan Dr. Radulovic
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 EP13186304.5A priority Critical patent/EP2853690A1/fr
Priority to PCT/EP2014/069751 priority patent/WO2015044008A1/fr
Publication of EP2853690A1 publication Critical patent/EP2853690A1/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins

Definitions

  • Turbine blades in particular blades of gas turbines, are thermally highly stressed components.
  • very high mechanical loads occur due to the rotation.
  • the gas or gas mixture flowing at high speed and high pressure which is intended to drive the turbine, causes a considerable mechanical load.
  • very high temperatures especially in gas turbine blades in operation very high temperatures. It generally applies that higher temperatures of the turbine blades driving gas mixture have a favorable effect on the efficiency of the gas turbine. To prevent too high temperatures in turbine blades, the turbine blades are cooled.
  • the perforated plates are designed as a box-shaped body of developable and welded together sheet metal pieces. This is the shape of the turbine blades, more precisely the inner spaces of the turbine blades, because the profiles are identical or only slightly scaled at all radial heights. These limitations make it difficult to create turbine blades that allow the most favorable flow possible.
  • the object of the invention is to reduce the difficulties.
  • an insert for the distribution of cooling fluid in a turbine blade which is constructed from at least three sections, which are successively inserted into an interior of the turbine blade.
  • at least the last introduced section acts as a wedge, which presses other sections so with a suitable distance to a wall of the turbine blade, that an impingement cooling can take place.
  • turbine blades are normally castings.
  • At least a selection of sections have surfaces which are installed at a low distance from an inner wall of the turbine blade, and the surfaces have holes, so that cooling fluid through the holes substantially perpendicular to the inner wall of the turbine blade can be performed.
  • the holes can have different shape and size. It is crucial that the cooling fluid flows reasonably evenly and perpendicularly to the inner wall of the turbine blade. This achieves the known and efficient impingement cooling.
  • At least one of the sections is constructed from a plurality of ventilation channels. These are mostly round or square ventilation ducts, the walls of which have holes.
  • the ventilation ducts can be connected for example by connecting webs to a section.
  • An essential embodiment of this embodiment are adjacent ventilation ducts, which in the inserted insert extend in the radial direction, that is, essentially from the blade root to the blade tip. As far as radial direction is concerned, it should be noted that due to the sometimes given curvature of the turbine blade this curvature is to follow.
  • a ventilation duct extending in the radial direction can thus have a corresponding curvature.
  • the sections are arranged one behind the other and / or next to one another in the radial direction. If the sections are arranged one behind the other, it is clear that an order must be observed during insertion. If the sections are introduced from the blade root, first the sections are to be introduced, which are closer to the blade tip. Since the cross section of the turbine blade usually changes from the blade root to the blade tip, the sections which are provided for different regions in the turbine blade are usually not identical. In this respect, the sequence plays a role especially in the radial direction to be introduced successively sections.
  • the sections are inserted partially overlapping. This results in areas within the turbine blade, in which there are two sections.
  • that portion which is inserted into another portion acts as a wedge, which presses the other portion with a suitable distance to a wall of the turbine blade, that an impingement cooling can take place.
  • a selection of sections is insertable simultaneously. So it is conceivable, for example, all parts that should rest against a wall, first introduce together in one step. In the next step, then at least one wedge-acting portion is introduced, whereby the insert is formed. This makes it possible already outside the turbine blade to create a connection between the sections that should rest against the wall. In this case, the connection can be designed so that even a movement between the connected sections is possible, which is caused approximately by the last introduced section.
  • the portions introduced first are only partially parallel to an inner wall of the turbine blade.
  • the inserts known in the prior art which are prefabricated and are introduced as prefabricated inserts into the turbine blade, the insert must be largely adapted to the inner walls of the turbine blade.
  • the now provided sections must be largely adapted to the shape of the inner wall only in the area covered by the individual sections.
  • a wedge effect is achieved by rotation of the inserted sections.
  • rotation is only to be carried out until a sufficient wedge effect is achieved.
  • At least the last introduced section does not rest on the wall of the turbine blade.
  • the last introduced section sometimes has only the function of a wedge and must not rest against the wall.
  • At least the last introduced section can not be flowed through.
  • this section does not have to abut against a wall of the turbine blade and does not have to fulfill the task of guiding cooling fluid perpendicular to the inner wall and causing impingement cooling. It is therefore not necessary to design this section throughflow.
  • these sections can, as it were, form cooling channels within the turbine blade and accordingly influence the flow of cooling fluid in a suitable manner.
  • the invention also provides a method of manufacturing an insert for distributing cooling fluid in a turbine blade by inserting at least three sections sequentially into an interior of the turbine blade, at least the last inserted section acting as a wedge, the other sections as a suitable one Distance to a wall of the turbine blade expresses that an impact cooling can take place.
  • This method and its embodiments are particularly suitable for the production of an insert described above.
  • FIG. 1 is a cross section of a turbine blade 1 in a plane on the blade root shown. It can be seen a circumferential wall 2 of the turbine blade 1. In one of the wall 2 surrounded interior 3, a portion 4 can be seen.
  • the section 4 comprises four ventilation channels.
  • a first, round running ventilation duct 6 can be seen.
  • This is followed by a connecting web 7, through which the ventilation duct 6 is connected to a further ventilation duct 8.
  • the largely angular running ventilation duct 8 is connected via a connecting web 9 with a further largely angular running ventilation duct 10.
  • a connecting web 11 connects the ventilation duct 10 with a fourth Ventilation channel 12.
  • the ventilation channel 12 has a flat, the connecting web 11 facing side and is otherwise oval designed to be adapted to the course of the wall 2 in the region of a trailing edge 13.
  • the walls of the ventilation channels 6, 8, 10 and 12 have holes, so that an air flow shown by arrows results from the ventilation channels 6, 8, 10 and 12 to the wall 2 of the turbine blade 1. This achieves the known impingement cooling.
  • FIG. 2 is a side view of the turbine blade 1 can be seen.
  • the section 4 can be seen, with the ventilation channels 6, 8, 10 and 12 and the connecting webs 7, 9 and 11 connecting them.
  • the section 4 extends in the radial direction up to a boundary 14.
  • a further section 15 is arranged, which extends from a boundary 16 to a boundary 17.
  • the section 15 and the section 4 are constructed in the same way.
  • the section 4 projects into the section 15 and acts as a wedge.
  • a further section 21 extends from a boundary 19 to a blade tip 20. Between the boundary 19 and the boundary 17, an overlapping area 22 again results. In the overlapping area 22, the section 15 protrudes into the section 21 and acts as a wedge.
  • section 4 acts as a wedge for the section 15 and this as a wedge for the section 21, a stable arrangement with suitable distances of the ventilation ducts reached from the wall 2 of the turbine blade 1. This achieves optimal impingement cooling.
EP13186304.5A 2013-09-27 2013-09-27 Insert pour le refroidissement d'une aube de turbine constituée de plusieurs pièces partielles Withdrawn EP2853690A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP13186304.5A EP2853690A1 (fr) 2013-09-27 2013-09-27 Insert pour le refroidissement d'une aube de turbine constituée de plusieurs pièces partielles
PCT/EP2014/069751 WO2015044008A1 (fr) 2013-09-27 2014-09-17 Élément rapporté permettant de refroidir une aube de turbine, constitué de plusieurs parties

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13186304.5A EP2853690A1 (fr) 2013-09-27 2013-09-27 Insert pour le refroidissement d'une aube de turbine constituée de plusieurs pièces partielles

Publications (1)

Publication Number Publication Date
EP2853690A1 true EP2853690A1 (fr) 2015-04-01

Family

ID=49293484

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13186304.5A Withdrawn EP2853690A1 (fr) 2013-09-27 2013-09-27 Insert pour le refroidissement d'une aube de turbine constituée de plusieurs pièces partielles

Country Status (2)

Country Link
EP (1) EP2853690A1 (fr)
WO (1) WO2015044008A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9581028B1 (en) * 2014-02-24 2017-02-28 Florida Turbine Technologies, Inc. Small turbine stator vane with impingement cooling insert

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4257734A (en) * 1978-03-22 1981-03-24 Rolls-Royce Limited Guide vanes for gas turbine engines
US4798515A (en) * 1986-05-19 1989-01-17 The United States Of America As Represented By The Secretary Of The Air Force Variable nozzle area turbine vane cooling
EP1233146A2 (fr) * 2001-02-16 2002-08-21 General Electric Company Insert pour une aube statorique d'une turbine à gaz et son montage
EP2628901A1 (fr) * 2012-02-15 2013-08-21 Siemens Aktiengesellschaft Aube de turbine à gaz avec refroidissement par impact

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8322988B1 (en) * 2009-01-09 2012-12-04 Florida Turbine Technologies, Inc. Air cooled turbine airfoil with sequential impingement cooling

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4257734A (en) * 1978-03-22 1981-03-24 Rolls-Royce Limited Guide vanes for gas turbine engines
US4798515A (en) * 1986-05-19 1989-01-17 The United States Of America As Represented By The Secretary Of The Air Force Variable nozzle area turbine vane cooling
EP1233146A2 (fr) * 2001-02-16 2002-08-21 General Electric Company Insert pour une aube statorique d'une turbine à gaz et son montage
EP2628901A1 (fr) * 2012-02-15 2013-08-21 Siemens Aktiengesellschaft Aube de turbine à gaz avec refroidissement par impact

Also Published As

Publication number Publication date
WO2015044008A1 (fr) 2015-04-02

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