EP2158381A2 - Aube directrice pour turbine à gaz - Google Patents

Aube directrice pour turbine à gaz

Info

Publication number
EP2158381A2
EP2158381A2 EP08761302A EP08761302A EP2158381A2 EP 2158381 A2 EP2158381 A2 EP 2158381A2 EP 08761302 A EP08761302 A EP 08761302A EP 08761302 A EP08761302 A EP 08761302A EP 2158381 A2 EP2158381 A2 EP 2158381A2
Authority
EP
European Patent Office
Prior art keywords
cover plate
recess
guide vane
trailing edge
groove
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.)
Granted
Application number
EP08761302A
Other languages
German (de)
English (en)
Other versions
EP2158381B1 (fr
Inventor
Alexander Khanin
Igor Kurganov
Sergey Vorontsov
Victor Odinokov
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to SI200830147T priority Critical patent/SI2158381T1/sl
Publication of EP2158381A2 publication Critical patent/EP2158381A2/fr
Application granted granted Critical
Publication of EP2158381B1 publication Critical patent/EP2158381B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • 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
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals
    • 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
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous

Definitions

  • the invention relates to a guide blade for a gas turbine, in particular a guide blade with a cover plate, according to the preamble of claim 1.
  • a plurality of stationary vanes are used, which are arranged in a turbine part along the circumference in rows. Since such guide vanes are exposed to the action of the hot gas flowing out of the combustion part and high pressure, high voltages can be generated in the guide vanes and in the cover plates during operation.
  • the cover plate is located between a hot gas flow and a space filled with cooling air. In order to seal this space from the hot gas stream, usually the cover plate has side walls which are each provided with a groove extending in the longitudinal direction of the cover plate. The grooves of two circumferentially adjacent cover plates receive a sealing plate extending between the cover plates.
  • the present invention has for its object to provide a guide vane for a gas turbine with a cover plate with an improved construction, which avoids the problems mentioned, that is, a construction that the stress concentrations in the trailing edge of the guide vane and in the cover plate in the region of the trailing edge of the Guide vane reduced.
  • a vane has a leading edge and a trailing edge and a cover plate extending at least between the leading edge and the trailing edge.
  • the cover plate has extending in the longitudinal direction of the gas turbine and extending substantially radially first and second side walls.
  • the first side wall is provided, at least in the region of the rear edge, with a groove extending in the longitudinal direction of the cover plate for receiving a sealing plate, the first side wall of the cover plate having a recess extending from the groove in the region of the rear edge.
  • the recess in the cover plate in the region of the trailing edge of the vane reduces the stress concentrations in the trailing edge of the vane and in the cover plate in the region of the trailing edge of the vane. This reduces the fatigue of the material at low load cycles and the creep speed in these areas.
  • the depth of the recess in the circumferential direction of the gas turbine is substantially equal to the depth of the groove.
  • FIG. 1 shows a perspective view of a guide blade with a cover plate according to an advantageous embodiment of the invention
  • FIG. 2 shows a side view of a guide blade with a cover plate according to an advantageous embodiment of the invention
  • Figure 3 shows the relationship between the vane trailing edge and the
  • FIG. 4 shows a section through the cover plate in FIG. 2 along the line A--
  • Figure 5 is a side view of a vane with a cover plate after the
  • Figure 6 shows the relationship between the vane trailing edge and the groove in the prior art cover plate.
  • FIGS. 5 and 6 show a guide blade 1 with a cover plate 2 according to the prior art.
  • a plurality of such stationary vanes 1 are used, which are arranged in a turbine part along the circumference in rows.
  • the vane 1 has a front edge 12 and a rear edge 8, wherein the cover plate 2 extends at least between the front edge 12 and the rear edge 8.
  • the cover plate 2 extends in the longitudinal direction of the gas turbine and extending substantially radially extending first and second side walls 5, 6.
  • the cover plate 2 is located in the radial direction between a hot gas stream 3 and a space filled with cooling air 4.
  • the side walls 5, 6 are each provided with a groove 7 extending in the longitudinal direction of the cover plate.
  • the grooves 7 of two circumferentially adjacent cover plates 2 receive a sealing plate extending between the cover plates 2.
  • a groove 7 extends in the longitudinal direction of the gas turbine at least in the region of a trailing edge 8 of the guide vane 1 and the distance in the circumferential direction of the gas turbine between the trailing edge 8 of the guide vane 1 and the groove 7 may be very small, which is apparent from the Figure 6, the a section through a radially outer portion of the blade portion and a partial view in the region of the groove 7 shows simultaneously.
  • a guide blade 1 In operation, since the guide blade 1 is exposed to the action of the hot gas 3 flowing out of the combustion chamber and high pressure, stress concentrations occur in the trailing edge region of the guide blade 1 and in the cover plate 2 in the region of the trailing edge of the guide blade. These stress concentrations in the region within the circle 9 in Figure 6, the life of the vane 1 is considerably shortened.
  • a guide blade 1 In FIGS. 5 and 6, a guide blade 1 is provided with a radially outer cover plate 2.
  • the guide vane 1 can also have a radially inner cover plate, which is provided in a similar manner with a provided in the longitudinal direction of the cover plate groove, wherein in operation stress concentrations in the trailing edge region of the guide vane 1 and in the radially inner cover plate in the region of the trailing edge 8 of the guide vane 1 may also arise.
  • FIG. 1 shows a guide blade 1 with a cover plate 2 according to a preferred embodiment of the invention. Identical components are provided with the same reference numerals. According to the invention, a first side wall 5 of the cover plate 2 in the region of a trailing edge 8 has a recess 10 extending from a groove 7.
  • the recess 10 is located in the longitudinal direction of the cover plate 2 substantially opposite to the trailing edge 8.
  • the recess 10 extends substantially at right angles to the groove 7 radially outwardly. In particular, therefore, only the first side wall 5 has such a recess 10.
  • the recess 10 in the radial direction opposite side of the cover plate 2 may be provided with an increase 1 1, wherein the recess 10 is provided in the longitudinal direction of the cover plate 2 in the region of the increase 1 1.
  • the recess 10 can be in the longitudinal direction of the cover plate 2 in the region of the downstream end of the elevation 1 1.
  • the distance between the trailing edge 8 and the recess 10 in the circumferential direction of the gas turbine can be less than the depth of the groove 7 or the depth of the groove 7 same.
  • the recess 10 but the stress concentrations are reduced in this area and reduces the fatigue of the material at low load cycles and creeping speed.
  • the depth of the recess 10 in the circumferential direction of the gas turbine is substantially equal to the depth of the groove 7, as shown in FIG is.
  • the width of the recess 10 in the longitudinal direction of the cover plate 2 is advantageously between once to three times their depth and the profile of the recess is preferably formed substantially rectangular.
  • the profile can take a different shape, for example, with side walls which extend obliquely to the longitudinal direction of the cover plate 2.
  • the guide vane is provided with a radially outer cover plate 2.
  • the vane can also have a radially inner cover plate (not shown) similarly provided with a groove 7 provided in the longitudinal direction of the cover plate, with stress concentrations in the trailing edge region of the vane and in the radially inner cover plate in the region of the trailing edge of the vane in operation Guide vane can also arise.
  • a first side wall of the radially inner cover plate in the region of the trailing edge 8 may have a recess extending radially inward from the groove 7.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
  • Valve-Gear Or Valve Arrangements (AREA)
EP08761302A 2007-06-28 2008-06-23 Aube directrice pour turbine à gaz Not-in-force EP2158381B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SI200830147T SI2158381T1 (sl) 2007-06-28 2008-06-23 Vodilna lopatica za plinsko turbino

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH10442007 2007-06-28
PCT/EP2008/057947 WO2009000802A2 (fr) 2007-06-28 2008-06-23 Aube directrice pour turbine à gaz

Publications (2)

Publication Number Publication Date
EP2158381A2 true EP2158381A2 (fr) 2010-03-03
EP2158381B1 EP2158381B1 (fr) 2010-11-03

Family

ID=38566219

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08761302A Not-in-force EP2158381B1 (fr) 2007-06-28 2008-06-23 Aube directrice pour turbine à gaz

Country Status (8)

Country Link
US (1) US8152454B2 (fr)
EP (1) EP2158381B1 (fr)
AT (1) ATE487025T1 (fr)
CA (1) CA2691186C (fr)
DE (1) DE502008001731D1 (fr)
SI (1) SI2158381T1 (fr)
TW (1) TWI440768B (fr)
WO (1) WO2009000802A2 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8376705B1 (en) 2011-09-09 2013-02-19 Siemens Energy, Inc. Turbine endwall with grooved recess cavity
US9840917B2 (en) * 2011-12-13 2017-12-12 United Technologies Corporation Stator vane shroud having an offset
US9683446B2 (en) * 2013-03-07 2017-06-20 Rolls-Royce Energy Systems, Inc. Gas turbine engine shrouded blade
EP2964934B1 (fr) * 2013-03-08 2018-10-03 United Technologies Corporation Composant de moteur à turbine à gaz ayant une fente de joint à couvre-joint à largeur variable
EP2811118B1 (fr) * 2013-06-06 2018-03-14 MTU Aero Engines GmbH Segment d'aube directrice d'une turbomachine et turbine
US10352180B2 (en) 2013-10-23 2019-07-16 General Electric Company Gas turbine nozzle trailing edge fillet
EP2985419B1 (fr) * 2014-08-13 2020-01-08 United Technologies Corporation Ensemble de pales de turbomachines avec étanchéités de pied d'aube
US10329931B2 (en) * 2014-10-01 2019-06-25 United Technologies Corporation Stator assembly for a gas turbine engine
US10876417B2 (en) 2017-08-17 2020-12-29 Raytheon Technologies Corporation Tuned airfoil assembly
US11506129B2 (en) 2020-04-24 2022-11-22 Raytheon Technologies Corporation Feather seal mateface cooling pockets

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3542483A (en) * 1968-07-17 1970-11-24 Westinghouse Electric Corp Turbine stator structure
US3938906A (en) * 1974-10-07 1976-02-17 Westinghouse Electric Corporation Slidable stator seal
US4524980A (en) * 1983-12-05 1985-06-25 United Technologies Corporation Intersecting feather seals for interlocking gas turbine vanes
GB2195403A (en) * 1986-09-17 1988-04-07 Rolls Royce Plc Improvements in or relating to sealing and cooling means
JP2001152804A (ja) * 1999-11-19 2001-06-05 Mitsubishi Heavy Ind Ltd ガスタービン設備及びタービン翼
US7625174B2 (en) * 2005-12-16 2009-12-01 General Electric Company Methods and apparatus for assembling gas turbine engine stator assemblies
US7922444B2 (en) * 2007-01-19 2011-04-12 United Technologies Corporation Chamfer rail pockets for turbine vane shrouds

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009000802A3 *

Also Published As

Publication number Publication date
WO2009000802A2 (fr) 2008-12-31
DE502008001731D1 (de) 2010-12-16
CA2691186A1 (fr) 2008-12-31
SI2158381T1 (sl) 2011-03-31
TWI440768B (zh) 2014-06-11
ATE487025T1 (de) 2010-11-15
TW200925390A (en) 2009-06-16
CA2691186C (fr) 2015-08-04
EP2158381B1 (fr) 2010-11-03
US8152454B2 (en) 2012-04-10
WO2009000802A3 (fr) 2009-03-19
US20100150710A1 (en) 2010-06-17

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