EP1245792A1 - Virole de turbine refroidie et procédé pour sa fabrication - Google Patents

Virole de turbine refroidie et procédé pour sa fabrication Download PDF

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Publication number
EP1245792A1
EP1245792A1 EP01108171A EP01108171A EP1245792A1 EP 1245792 A1 EP1245792 A1 EP 1245792A1 EP 01108171 A EP01108171 A EP 01108171A EP 01108171 A EP01108171 A EP 01108171A EP 1245792 A1 EP1245792 A1 EP 1245792A1
Authority
EP
European Patent Office
Prior art keywords
guide ring
wall
cavity
thickness
core
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Withdrawn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
EP01108171A
Other languages
German (de)
English (en)
Inventor
Hans-Thomas Dr. Bolms
Peter 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 EP01108171A priority Critical patent/EP1245792A1/fr
Publication of EP1245792A1 publication Critical patent/EP1245792A1/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Withdrawn legal-status Critical Current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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C21/00—Flasks; Accessories therefor
    • B22C21/12—Accessories
    • B22C21/14—Accessories for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Definitions

  • the present invention relates to a guide ring for a Turbine, especially for a gas turbine, which has a housing with multiple rows of vanes and a rotor with has several rows of blades, being on the housing in the axial direction between two rows of guide vanes a guide ring is provided. It also concerns a procedure for the production of a guide ring.
  • Such a guide ring is known from EP 0 709 550 A1.
  • This guide ring is with a to the housing Baffle plate covered so that a cavity is created.
  • the Cooling fluid is introduced on the housing side of the baffle plate, passes through holes in the baffle plate and hits then essentially perpendicular to the guide ring.
  • At the A channel is provided from the front edge of the guide ring which the coolant can leak. There is no channel in this channel Connection between an inner wall and an outer wall the guide ring.
  • a disadvantage of this known guide ring is that the inner wall and the other area of the guide ring comparatively must be made thick. Only through this thick one Training the required mechanical stability is achieved.
  • the guide ring may, for example, occasionally occurring brushing of the tips of the rotor blades don't fail. Even cracking without one Touching must be avoided.
  • the well-known guide ring and also its only partially provided inner wall are therefore formed thick, resulting in poor cooling efficiency leads.
  • the object of the present invention is therefore a guide ring with improved cooling without deterioration of the to provide mechanical properties.
  • this task is performed with a guide ring solved type in that the guide ring an outer wall facing the housing and one facing the rotor Has inner wall that have a cavity to each other spaced and with a number of support elements are interconnected.
  • the outer wall, the inner wall and the support elements are advantageous integrally connected with each other.
  • the Guide ring can then be made in one piece using a suitable one Core are poured. Manufacturing and assembly simplified, and assembly tolerances become complete locked out.
  • the thickness is Outer wall is a multiple of the thickness of the inner wall and is special two to seven times as large.
  • the exact thickness ratio depends on the respective boundary conditions.
  • Number, shape and arrangement of the support elements are chosen such that the inner wall on the much thicker External wall is supported and thus the mechanical stability is guaranteed.
  • the height of the cavity can be less than the thickness of the outer wall, but larger than the thickness of the inner wall. Since the Cavity essentially only for the distribution of the cooling medium serves the entire surface of the inner wall, its height can be reduced, so that overall a compact structure results in low material requirements.
  • the support elements are advantageously designed as pins, the distance between the central axes of the pins is one and a half up to two and a half times the diameter of the Pens is. With this arrangement, there is sufficient Support and stability of the inner wall, while at the same time a large area of the inner wall is exposed to the cooling medium can be.
  • the cavity extends over at least half the axial length of the guide ring, especially over at least 80 percent of the axial Length.
  • the guide ring Only in the peripheral areas where the Guide ring in the axial direction with the rows of guide vanes is connected, there is a small area reduced Cooling. If the guide ring consists of several segments exists, which are arranged side by side in the circumferential direction are, is a similar in the peripheral region in the circumferential direction Construction as intended in the axial direction.
  • the inner wall can face at least one from the cavity have recess running to the rotor. This recess is created during use in the bus process of a core with protrusions for support is provided on the inside of the mold. Through these projections can have a defined thickness of the inner wall as well as, if necessary the outer wall can be ensured. A possible shift of the core during casting, the influence on the Thicknesses of the inner wall and outer wall could be reliably avoided.
  • the cavity via at least one feed is advantageous can be charged with a cooling medium. It can also at least a removal should be provided.
  • the cooling medium can then be inserted directly into the cavity. A contribution it coolant into a space radially outside the outer wall and a passage through correspondingly provided recesses in the outer wall to act on the inner surface is then no longer necessary.
  • the exhaustion itself can towards the housing or in the axial direction towards the front edge and / or rear edge of the guide ring for gap sealing respectively.
  • the invention further relates to a method of manufacture a guide ring for a turbine, especially for manufacturing a guide ring described above. It will be first a core for forming the cavity of the guide ring placed in a mold, the mold closed and with filled with the material of the guide ring. After cooling the mold is opened and the guide ring together with the Core removed. The core is then removed, for example drained so that the cavity is released becomes. It will be a one-piece production of the guide ring enables so that the assembly is significantly simplified.
  • the core is here with one or more projections Support on the mold to a defined thickness of the ensure the cavity-bounding walls of the guide ring.
  • the support can be on one or both sides. Through the projections that lead to the inner wall, to the outer wall or facing both walls will be displacements of the core avoided during casting. Unwanted variations in the wall thickness are reliably prevented.
  • Figure 1 shows a schematic longitudinal section through a gas turbine 10 with a housing 11 and a rotor 12. On the housing 11 are several rows of guide vanes 13 and on the rotor 12 several rows of blades 14 are provided.
  • the turbine 10 is flowed through by hot gas according to arrow direction 15, that the rotor 12 in rotation according to arrow direction 17 by one Axis of rotation 16 offset.
  • guide rings 18 are arranged on the housing. This Guide rings 18 are arranged on the left in FIG. 1 in particular Entry area of the gas turbine 10 cooled.
  • FIG Figures 2 and 3 The construction of a guide ring 18 according to the invention is shown in FIG Figures 2 and 3 shown in more detail. He has a comparative thick outer wall 19 facing the housing 11 is. On the side facing the hot gas flow is one relatively thin inner wall 20 is provided. The two walls 19, 20 are spaced apart from one another via a cavity 21. To Support of the inner wall 20 are support elements in the form of Pins 22 provided. The attachment to the housing 11 is carried out by means of schematically represented hooks 23. The outer wall 19, the inner wall 20 and the pins 22 are made of one piece of material connected with each other.
  • the guide ring 18 For sealing in the axial direction, the guide ring 18 is included Provide grooves 24 in the appropriate, not shown Crack plates can be used. There are further approaches 25 provided for the formation of press seals.
  • the cavity 21 has a feed 37 and a drain 38 for a cooling medium, especially cooling air.
  • the cooling medium enters through feed 37 as shown schematically into the cavity 21, flows around the pins 22 and cools the inner wall 20 and then passes through the outlet 38 again out. Since the thickness of the inner wall 20 is very small, lets achieve high cooling efficiency.
  • the cavity 21 extends essentially over the entire available area of the guide ring 18. It is not provided only in edge areas of the guide ring 18. In the exemplary embodiment shown extends the cavity 21 over about 75 percent of the axial length of the Guide ring 18. It can thus the maximum possible range of the guide ring 18 are cooled.
  • the thickness d 1 of the outer wall 19 is approximately 3 to 5 mm, the height of the h of the cavity 21 is between 1 and 2 mm.
  • the thickness d 2 of the inner wall is approximately 0.7 to 1.2 mm.
  • the diameter E of the pins is between 1 and 3 mm, the distance A between the central axes of the pins being about one and a half to two and a half times the diameter D. Since the inner wall 20 is connected to the outer wall 19 via the pins 22, their thickness d 2 can be significantly reduced. The required mechanical stability is ensured by the thickness d 1 of the outer wall 19 and the pins 22.
  • the thickness d 1 of the outer wall 19 is a multiple of the thickness d 2 of the inner wall 20 and is in particular two to seven times as large. In the exemplary embodiment shown, the thickness d 1 of the outer wall 19 is approximately three times the thickness d 2 of the inner wall 20.
  • the inner wall 20 is provided with a plurality of recesses 27, which extend from the cavity 21 towards the rotor 12. These recesses 27 are conical and leave behind in an inner surface exposed to the hot gas flow 26 of the inner wall 20 small holes. Since the inner surface 26 is provided with a coating 28 in many cases, these holes are closed and are not critical. The coating 28 increases heat resistance.
  • the recesses 27 arise during the manufacture of the guide ring 18, which is shown schematically in Figure 4. It is a form 29 with an upper part 30 and a lower part 31 intended. The two parts 30, 31 are in the direction of the arrow 32 movable to each other.
  • the shape division is schematic indicated by line 39.
  • a core 33 which is introduced into the mold 29, is used to form the cavity 21.
  • the core 33 has recesses 35 for producing the pins 22. It is further provided with a plurality of projections 36 for support on the mold 29. Such projections, which are indicated schematically by the broken line 40, can also be provided on the opposite side of the core 33.
  • the projections 36, 40 hold the core together with schematically illustrated hooks 34 in a defined position in the form 29.
  • a displacement of the core 33 in the direction of the arrow 32 which would lead to a change in the thicknesses d 1 , d 2 of the walls 19, 20 is reliably avoided. Defined thicknesses d 1 , d 2 can thus be specified for the outer wall 19 and the inner wall 20. Manufacturing tolerances are reduced to a minimum.
  • the mold 29 is closed and with the material for forming the guide ring 18 filled. After cooling, the mold 29 is opened again, the cast guide ring 18 is removed together with the core 33 and then the core 33 removed. For example by leaching. The hook 34 then left openings form the feed 37 and discharge 38 for the cooling medium.
  • Figures 5 and 6 show schematic plan views of two different embodiments of a core 33.
  • the recesses 35 are vertical and horizontal Arranged rows.
  • the distance A between each Recesses 35 is approximately twice as large as their diameter D.
  • the recesses 35 are in contrast offset laterally and vertically to each other.
  • the distance A is about one and a half times the diameter D.
  • the diameter of the pins 22 is therefore also reduced.
  • the distance A is therefore reduced so that the Pins 22 are packed more densely overall.
  • the diameter D, the distance A and the arrangement of the pins 22 respectively Recesses 35 is determined depending on the individual case.
  • the guide ring according to the invention enables the inner wall 20 to be supported on the outer wall 19.
  • the thickness d 2 of the inner wall 20 can therefore be significantly reduced, so that the cooling efficiency increases. Because of this support, the desired mechanical properties are reliably ensured despite the reduction in the thickness d 2 of the inner wall 20.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01108171A 2001-03-30 2001-03-30 Virole de turbine refroidie et procédé pour sa fabrication Withdrawn EP1245792A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01108171A EP1245792A1 (fr) 2001-03-30 2001-03-30 Virole de turbine refroidie et procédé pour sa fabrication

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01108171A EP1245792A1 (fr) 2001-03-30 2001-03-30 Virole de turbine refroidie et procédé pour sa fabrication

Publications (1)

Publication Number Publication Date
EP1245792A1 true EP1245792A1 (fr) 2002-10-02

Family

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Family Applications (1)

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EP01108171A Withdrawn EP1245792A1 (fr) 2001-03-30 2001-03-30 Virole de turbine refroidie et procédé pour sa fabrication

Country Status (1)

Country Link
EP (1) EP1245792A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1213444A2 (fr) * 2000-12-01 2002-06-12 ROLLS-ROYCE plc Segment de virole pour turbine
DE102008005482A1 (de) * 2008-01-23 2009-07-30 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit einem Verdichter mit selbstheilender Einlaufschicht
US8128344B2 (en) 2008-11-05 2012-03-06 General Electric Company Methods and apparatus involving shroud cooling
DE102010045712A1 (de) * 2010-09-16 2012-03-22 Mtu Aero Engines Gmbh Turbomaschinengehäuse
US8257016B2 (en) 2008-01-23 2012-09-04 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine with a compressor with self-healing abradable coating
EP3034808A3 (fr) * 2014-12-15 2016-08-24 United Technologies Corporation Noyau de coulée pour joint d'étanchéité à l'air externe d'aube

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2124527A (en) * 1979-06-08 1984-02-22 Foseco Int Cavity former for use in the production of a metal casting mould having a riser
US4573866A (en) * 1983-05-02 1986-03-04 United Technologies Corporation Sealed shroud for rotating body
US5374161A (en) * 1993-12-13 1994-12-20 United Technologies Corporation Blade outer air seal cooling enhanced with inter-segment film slot
US5375973A (en) * 1992-12-23 1994-12-27 United Technologies Corporation Turbine blade outer air seal with optimized cooling
EP0709550A1 (fr) 1994-10-31 1996-05-01 General Electric Company Virole réfroidi
WO1999006672A1 (fr) * 1997-07-29 1999-02-11 Siemens Aktiengesellschaft Aube de turbine et son procede de production
EP0974734A2 (fr) * 1998-07-18 2000-01-26 ROLLS-ROYCE plc Refroidissement d'une virole de turbine
US6047552A (en) * 1996-09-26 2000-04-11 Siemens Aktiengesellschaft Heat-shield component with cooling-fluid return and heat-shield configuration for a component directing hot gas

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2124527A (en) * 1979-06-08 1984-02-22 Foseco Int Cavity former for use in the production of a metal casting mould having a riser
US4573866A (en) * 1983-05-02 1986-03-04 United Technologies Corporation Sealed shroud for rotating body
US5375973A (en) * 1992-12-23 1994-12-27 United Technologies Corporation Turbine blade outer air seal with optimized cooling
US5374161A (en) * 1993-12-13 1994-12-20 United Technologies Corporation Blade outer air seal cooling enhanced with inter-segment film slot
EP0709550A1 (fr) 1994-10-31 1996-05-01 General Electric Company Virole réfroidi
US6047552A (en) * 1996-09-26 2000-04-11 Siemens Aktiengesellschaft Heat-shield component with cooling-fluid return and heat-shield configuration for a component directing hot gas
WO1999006672A1 (fr) * 1997-07-29 1999-02-11 Siemens Aktiengesellschaft Aube de turbine et son procede de production
EP0974734A2 (fr) * 1998-07-18 2000-01-26 ROLLS-ROYCE plc Refroidissement d'une virole de turbine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1213444A2 (fr) * 2000-12-01 2002-06-12 ROLLS-ROYCE plc Segment de virole pour turbine
EP1213444A3 (fr) * 2000-12-01 2004-02-04 ROLLS-ROYCE plc Segment de virole pour turbine
DE102008005482A1 (de) * 2008-01-23 2009-07-30 Rolls-Royce Deutschland Ltd & Co Kg Gasturbine mit einem Verdichter mit selbstheilender Einlaufschicht
US8257016B2 (en) 2008-01-23 2012-09-04 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine with a compressor with self-healing abradable coating
US8128344B2 (en) 2008-11-05 2012-03-06 General Electric Company Methods and apparatus involving shroud cooling
CN101737103B (zh) * 2008-11-05 2014-12-17 通用电气公司 关于护罩冷却的方法及设备
DE102010045712A1 (de) * 2010-09-16 2012-03-22 Mtu Aero Engines Gmbh Turbomaschinengehäuse
DE102010045712B4 (de) * 2010-09-16 2013-01-03 Mtu Aero Engines Gmbh Turbomaschinengehäuse
EP3034808A3 (fr) * 2014-12-15 2016-08-24 United Technologies Corporation Noyau de coulée pour joint d'étanchéité à l'air externe d'aube
US10329934B2 (en) 2014-12-15 2019-06-25 United Technologies Corporation Reversible flow blade outer air seal

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