EP1256695A1 - Elément d'anneau de guidage de turbine à gaz, et turbine à gaz comportant ledit élément - Google Patents

Elément d'anneau de guidage de turbine à gaz, et turbine à gaz comportant ledit élément Download PDF

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Publication number
EP1256695A1
EP1256695A1 EP01111004A EP01111004A EP1256695A1 EP 1256695 A1 EP1256695 A1 EP 1256695A1 EP 01111004 A EP01111004 A EP 01111004A EP 01111004 A EP01111004 A EP 01111004A EP 1256695 A1 EP1256695 A1 EP 1256695A1
Authority
EP
European Patent Office
Prior art keywords
turbine
guide ring
gas turbine
guide
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.)
Withdrawn
Application number
EP01111004A
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 EP01111004A priority Critical patent/EP1256695A1/fr
Publication of EP1256695A1 publication Critical patent/EP1256695A1/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Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • 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
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • the invention relates to a molding for forming a Guide ring for a gas turbine.
  • Gas turbines are used to drive generators in many areas or used by work machines.
  • the Energy content of a fuel to generate a rotational movement a turbine shaft used.
  • the fuel will To do this, burned in a combustion chamber, using an air compressor compressed air is supplied. That in the combustion chamber generated by the combustion of the fuel, under high Pressure and high temperature working medium is via a turbine unit downstream of the combustion chamber managed where it relaxes while working.
  • a number of them usually in groups of blades or rows of blades grouped together arranged via a pulse transfer from the flow medium drive the turbine shaft.
  • For guiding the flow medium are also common in the turbine unit between adjacent rows of blades with the turbine housing connected rows of vanes arranged.
  • the guide vanes indicate the appropriate management of the working medium a shovel blade on the end for attachment the turbine blade on the respective carrier body also as Platform designated blade root is formed.
  • This Platform usually on an inner wall of the turbine unit attached or hooked, limited with her surface facing the interior of the turbine unit the flow area for that flowing through the turbine unit Working medium.
  • Flow channel with a comparatively smooth inner surface form are also usually in the turbine unit between the platforms of in the direction of flow of the working medium seen adjacent guide vane rows so-called guide rings arranged, which in the flow direction of the working medium seen from the platforms of adjacent guide vanes bridge the gap left.
  • the invention is therefore based on the object of a fitting to form a reliably coolable guide ring for specify a gas turbine that with particularly little effort can be produced.
  • a gas turbine with a reliable coolable, easy to manufacture Guide ring can be specified.
  • This object is achieved by a shaped piece with a curved jacket sheet, its in the axial direction seen edges of the guide ring one each have continuous end rib thickened on top.
  • “Upper side” takes on that side of the casing sheet reference that in the assembled state of the casing sheet from the flow space facing away from the working medium and the guide vane carrier faces the turbine unit.
  • the invention is based on the consideration that for a particular simple and therefore inexpensive version of the Guide ring the flow path of the cooling medium flowing through it or the cooling air can be kept particularly simple should. Deviating from the previously common concept that as little cooling air as possible is used to cool the guide ring and is strongly heated, so that it then in the Kind of an open cooling in the hot gas or working medium can be admixed to the turbine unit is provided the guide ring with a comparatively large Amount of cooling medium or cooling air to feed only heated up to a limited extent. That is heated up to such a limited extent Coolant is then closed in the manner of a Cooling is not added to the hot gas flow, but instead rather used for cooling other components.
  • the cooling concept forms the jacket sheet in cooperation with the Guide vane carrier a coolant channel.
  • the coolant channel, the one hand through the top of the jacket sheet and on the other hand formed by the inner wall of the guide vane carrier through the end ribs limited at which the incoming or outgoing cooling medium a deflection into or out of the coolant channel experiences.
  • the at the end or front edges of the jacket sheet molded end ribs also favor the reliable Cooling the guide ring even further by looking at them due to the redirection of the cooling medium flow in Impact cooling takes place in a particularly effective manner.
  • the jacket sheet has advantageously a number of essentially on the top extending in the axial direction of the guide ring Stiffening ribs on. These form essentially parallel switched flow channels for the cooling medium or the cooling air.
  • the gas turbine are advantageously each on one Number of adjacent stiffening ribs a number of Beam hooks forming through the cladding sheet, respectively two adjacent stiffening ribs and the respective support hook limited flow openings arranged.
  • the carrier hooks are thus in a stand-alone construction on each a number of stiffening ribs, for example two to four, put on, each below the carrier hook a number of passages or flow openings for the Cooling medium are formed.
  • the carrier hooks are thus from Coolant flows under, so that a particularly effective Cooling enables and thermal stresses kept particularly low are.
  • the jacket is advantageously on the cooling medium for a turbulence of the one running along it Cooling medium trained.
  • the casing sheet advantageously has a number of essentially transverse on the upper side turbolator ribs oriented to the direction of flow of the cooling medium on.
  • the stated task is solved, by placing one of a number in the interior of the turbine housing guide ring composed of the fittings mentioned is arranged.
  • the guide ring is advantageously in the flow direction of the working medium seen between the first row of guide vanes and the first row of blades of the gas turbine arranged. This is the position during operation the gas turbine the comparatively strongest thermal stress the guide rings.
  • the advantages achieved with the invention are in particular in that the cladding sheet provided with thickened end ribs essentially closed cooling of the guide ring allowed with a particularly simple construction.
  • the essentially closed cooling can act of the guide ring with a comparatively large one Amount of cooling air or cooling medium.
  • the one Such cooling only heated up comparatively little Coolant can then be used to cool other components be used so that a particularly effective use of the cooling medium is made possible.
  • the gas turbine 1 has a compressor 2 for Combustion air, a combustion chamber 4 and a turbine 6 for Drive the compressor 2 and a generator, not shown or a work machine.
  • a compressor 2 for Combustion air
  • a combustion chamber 4 for Driving the compressor 2 and a generator, not shown or a work machine.
  • the turbine 6 and the compressor 2 on a common, also as a turbine rotor designated turbine shaft 8 arranged with the the generator or the working machine is also connected, and which is mounted rotatably about its central axis 9.
  • the combustion chamber 4 is provided with a number of burners 10 Combustion of a liquid or gaseous fuel. It is still not closer to its inner wall provided heat shield elements.
  • the turbine 6 has a number of with the turbine shaft 8 connected, rotatable blades 12.
  • the blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of rows of blades.
  • the turbine 6 comprises a number of fixed guide vanes 14, which is also ring-shaped with the formation of Guide vane rows attached to an inner housing 16 of the turbine 6 are.
  • the blades 12 are used to drive the turbine shaft 8 by transfer of momentum from the turbine 6 working medium flowing through M.
  • the guide vanes 14 serve in contrast to the flow of the working medium M between seen two in the flow direction of the working medium M. successive rows of blades or blade rings.
  • a successive pair from a wreath of Guide vanes 14 or a row of guide vanes and from one Wreath of blades 12 or a row of blades is also referred to as the turbine stage.
  • Each guide vane 14 has one, also referred to as a blade root Platform 18 on which to fix the respective guide vane 14 on the inner housing 16 of the turbine 6 as a wall element is arranged.
  • the platform 18 is a thermally comparative heavily loaded component that the outer boundary a hot gas duct for the one flowing through the turbine 6 Working medium M forms.
  • Each blade 12 is analog Way over a platform 20 also referred to as a blade root attached to the turbine shaft 8.
  • each guide ring 20 is also hot, flowing through the turbine 6 Working medium M exposed and in the radial direction from the outer end 22 of the blade opposite to it 12 spaced apart by a gap.
  • the one between neighboring Guide rings 20 arranged guide vane rows serve in particular as cover elements covering the inner wall of the inner housing 16 or other housing installation parts a thermal overload caused by the turbine 6 flowing hot working medium M protects.
  • the gas turbine 1 for a comparatively high outlet temperature of the working medium emerging from the combustion chamber 4 M designed from about 1200 ° C to 1300 ° C.
  • the blades 12 and Guide vanes 14 designed to be coolable as cooling medium by cooling air.
  • the guide rings 21 are also through Cooling air designed to be coolable.
  • the guide ring 21 is in each case of a number of Fittings 30 assembled.
  • One to form the flow direction of the working medium M seen first guide ring 21 shaped piece 30 is in supervision in Figure 2, in Figure 3 in longitudinal section and in Figure 4 in cross section shown.
  • the shaped piece 30 comprises a jacket plate 32, the circumferential direction of the guide ring 21 to be formed is curved like a segment of a circle.
  • the jacket plate 32 At its in the axial direction x of the guide ring, shown in Figures 2, 4 by the arrow 34 is symbolized, front or end edges 36, 38 the jacket plate 32 has a continuous, to the top 40 of the cladding sheet 32 thickened end rib 42 or 44 on.
  • top 40 of the casing sheet 32 is like this that can be seen in particular from FIGS. 3 and 4
  • Side of the cladding sheet 32 to be understood in the assembled state of the guide ring 21 of the inner wall of the inner housing 16 faces the turbine 6.
  • the underside 46 of the cladding sheet 32 denotes the side that is in the assembled position State of the guide ring 21 the flowing working medium M faces and limits its flow channel.
  • the jacket plate 32 is for a particularly low cooling effort executed in a particularly small thickness. To nevertheless with comparatively high mechanical stress to ensure sufficient strength of the molding 30, the jacket plate 32 has a number on its upper side 40 of essentially in the axial direction x of the guide ring 21 extending stiffening ribs 50. These thus form a number of substantially parallel flow channels for the cooling medium. Between adjacent stiffening ribs 50 also has the jacket plate 32 essentially aligned transversely to the flow direction of the cooling medium Turbolator fins 52 through which a substantially wavy surface structure of the top 40 forms. Through the turbolator ribs 52 is in the by two stiffening ribs 50 flowing flow channels Swirling cooling medium, so that a particularly good mechanical contact and thus heat transfer with the jacket sheet 32 sets.
  • each carrier hook 54 extends seen in the transverse direction of the casing sheet 32 via a A plurality of the stiffening ribs 50.
  • each carrier hook 54 is on the respective Stiffening ribs 50 placed such that each two adjacent stiffening ribs 50 together with the casing sheet 32 and the respective carrier hook 54 a number of Form flow openings 56.
  • the carrier hook 54 are thus flows under the cooling medium, so that occurring thermal stresses in the fitting 30 even when subjected to comparatively high thermal load are kept particularly low.
  • the carrier hooks 54 are otherwise, as can be seen from Figure 4 is formed with molded carrier lugs and with corresponding support elements on the inner wall of the inner housing 16 of the turbine 6 can be brought into engagement.
  • Hot working medium flows through during operation of the gas turbine 1 M the turbine 6.
  • the cooling air L is like this is represented by the arrow 60 in FIG. 4, from the region the inner wall of the inner casing 16 of the turbine 6 Jacket sheet 32 supplied.
  • Cooling air L essentially along a flow path the top 40 of the jacket plate 32 deflected. there occurs in the area of the end rib 42 for cooling in particular favorable impact cooling effect.
  • the cooling air L flows through in the direction towards the turbine shaft 8 from the top 40 of the casing sheet 32 and towards the outside from the inside wall of the inner housing 16 of the turbine 6 limited coolant channel and cools the jacket sheet 32 in the area of Another end rib 44, the cooling air L is redirected and flows in the direction as indicated by arrow 62 on the inner wall of the inner housing 16 of the turbine 6. With the redirection there is again a cooling of the Jacket plate 32 particularly advantageous impact cooling effect.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01111004A 2001-05-07 2001-05-07 Elément d'anneau de guidage de turbine à gaz, et turbine à gaz comportant ledit élément Withdrawn EP1256695A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01111004A EP1256695A1 (fr) 2001-05-07 2001-05-07 Elément d'anneau de guidage de turbine à gaz, et turbine à gaz comportant ledit élément

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01111004A EP1256695A1 (fr) 2001-05-07 2001-05-07 Elément d'anneau de guidage de turbine à gaz, et turbine à gaz comportant ledit élément

Publications (1)

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EP1256695A1 true EP1256695A1 (fr) 2002-11-13

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10340670B4 (de) * 2003-04-08 2009-08-20 Valerij Albrandt Rotorenkolbenmotor
US8128344B2 (en) 2008-11-05 2012-03-06 General Electric Company Methods and apparatus involving shroud cooling

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5127793A (en) * 1990-05-31 1992-07-07 General Electric Company Turbine shroud clearance control assembly
EP0528520A1 (fr) * 1991-06-24 1993-02-24 General Electric Company Stator pour un compresseur
US5609469A (en) * 1995-11-22 1997-03-11 United Technologies Corporation Rotor assembly shroud
WO2000057033A1 (fr) * 1999-03-24 2000-09-28 Siemens Aktiengesellschaft Element de revetement et systeme comportant un element de revetement et une structure support
US6224329B1 (en) * 1999-01-07 2001-05-01 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5127793A (en) * 1990-05-31 1992-07-07 General Electric Company Turbine shroud clearance control assembly
EP0528520A1 (fr) * 1991-06-24 1993-02-24 General Electric Company Stator pour un compresseur
US5609469A (en) * 1995-11-22 1997-03-11 United Technologies Corporation Rotor assembly shroud
US6224329B1 (en) * 1999-01-07 2001-05-01 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine
WO2000057033A1 (fr) * 1999-03-24 2000-09-28 Siemens Aktiengesellschaft Element de revetement et systeme comportant un element de revetement et une structure support

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10340670B4 (de) * 2003-04-08 2009-08-20 Valerij Albrandt Rotorenkolbenmotor
US8128344B2 (en) 2008-11-05 2012-03-06 General Electric Company Methods and apparatus involving shroud cooling

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