EP1706593A1 - Aube de turbine a gaz et turbine a gaz avec une telle aube - Google Patents

Aube de turbine a gaz et turbine a gaz avec une telle aube

Info

Publication number
EP1706593A1
EP1706593A1 EP05706868A EP05706868A EP1706593A1 EP 1706593 A1 EP1706593 A1 EP 1706593A1 EP 05706868 A EP05706868 A EP 05706868A EP 05706868 A EP05706868 A EP 05706868A EP 1706593 A1 EP1706593 A1 EP 1706593A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine
sheet metal
metal part
turbine blade
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
EP05706868A
Other languages
German (de)
English (en)
Other versions
EP1706593B1 (fr
Inventor
Stefan Baldauf
Hans-Thomas Bolms
Michael HÄNDLER
Christian Lerner
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
Siemens Corp
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 PL05706868T priority Critical patent/PL1706593T3/pl
Priority to EP05706868A priority patent/EP1706593B1/fr
Publication of EP1706593A1 publication Critical patent/EP1706593A1/fr
Application granted granted Critical
Publication of EP1706593B1 publication Critical patent/EP1706593B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the invention relates to a turbine blade with an airfoil arranged along a blade axis and with a platform region having at the foot of the airfoil a platform which extends transversely to the blade axis.
  • the invention further relates to a gas turbine having a flow channel with an annular cross-section for a working medium extending along an axis of the gas turbine, a second blade arranged behind a first blade stage arranged along the axis, wherein a blade stage arranged a number of annular, radially into the channel having extending turbine blades.
  • a gas turbine of this type occur in the flow channel after exposure to hot gas temperatures that can range between 1000 ° C and 1400 ° C.
  • the platform of the turbine bucket due to the annular arrangement of a number of such turbine buckets in a bucket stage, forms part of the flow passage for a gas turbine flowing working fluid in the form of hot gas, thus driving the axial turbine rotor via the turbine bucket.
  • Such a strong thermal stress on the boundary of the flow channel formed by the platforms is countered by cooling a platform from behind, that is to say from the base of a turbine blade arranged below the platform.
  • the foot and the platform region usually have a suitable sewer system for the application of a cooling medium.
  • DE 2 628 807 A1 discloses an impingement cooling system for a turbine blade of the type mentioned initially.
  • DE 2 628 807 A1 for cooling the platform in front of the side facing away from the hot gas of the platform, ie behind the platform, ie between a blade root and the platform form, a perforated wall element arranged. Cooling air strikes the side of the platform remote from the hot gas through the holes of the wall element under relatively high pressure, thereby achieving efficient impingement cooling.
  • EP 1 073 827 B1 discloses a new way of constructing the platform area of cast turbine blades.
  • the platform area is formed as a double platform of two opposing platform walls. This ensures that the flow channel and thus the
  • the flow channel limiting platform wall can be made thin.
  • the design in two platform walls results in a functional separation for the platform walls.
  • the platform wall bounding the flow channel is essentially responsible for the sewerage of the hot gas.
  • the opposite, not acted upon by the hot gas platform wall takes over the recording of the blade resulting from the blade loads. This function separation makes it possible to make the platform wall delimiting the flow channel so thin that hot gas channelisation is ensured without having to absorb significant loads.
  • sealing measures are necessary in a parting line between platforms of adjacent turbine blades of the same blade stage or adjacent turbine blades of successively arranged blade stages to prevent unwanted and excessive leakage of cooling medium in the acted upon hot gas flow channel.
  • the measures required for sealing can lead to structurally and cooling technically difficult situations on a thermally highly loaded platform wall and represent an increased failure potential for a turbine blade and thus for a gas turbine.
  • the sealing of such part joints is achieved by the installation of special sealing elements.
  • they must be flexible enough to permit simultaneous relative movements of adjacent parts, in particular of adjacent turbine blades and their platforms, and on the other hand, they nevertheless have to obtain a sealing effect.
  • the installation of such sealing elements leads to geometrically and structurally complicated components. As a result, special cooling measures are necessary to sufficiently cool hard to reach edges of a platform.
  • the invention is based, whose task is to provide a turbine blade with a platform that is simultaneously simple and also satisfies the geometrical-structural and cooling requirements within a flow channel limitation of a gas turbine advantageous. Furthermore, the sealing of the part joints between adjacent turbine blades should be particularly simple and inexpensive.
  • the object is achieved by the invention with the turbine blade mentioned above, wherein according to the invention the platform is at least partially formed by a first elastic sheet-metal part fixed to the airfoil, which can be applied to an adjacent turbine blade.
  • the invention is based on the consideration that the use of a non-load-bearing platform for representing the boundary of a hot gas flow channel of a gas turbine is fundamentally suitable for cooling the platform, and thus the boundary of the flow channel, as effectively as possible.
  • the essential income knowledge of the invention in that it is possible to equip the platform itself with an increased sealing effect, namely by the platform is designed so thin-walled that it is formed by a voltage applied to the airfoil sheet metal part.
  • the platform as a part of the hot gas acted upon flow-limiting part meets all requirements with respect to the cooling and also a sealing element.
  • Sheet metal part the platform as such, namely sufficiently flexible to allow simultaneous relative movements of adjacent airfoils and other parts and still receives the sealing effect. This eliminates the need for a special sealing element. This simplifies the
  • the first resilient sheet metal part is provided as a non-load-bearing platform wall which at least partially defines the hot-gas-charged flow channel.
  • the platform thus consists at least partially of the first spring-elastic sheet-metal part fixed to the blade.
  • the platform is formed by the first fixed to a first stop on one side of the airfoil elastic sheet metal part and is formed by a second at a second stop on the other side of the airfoil fixed sheet metal part.
  • two sheet metal parts are expediently provided, which form the platform, which thus extend on both sides on one side and the other side of the airfoil transversely to the blade axis.
  • the second sheet metal part resting against the blade leaf assumes the function of a first platform wall which does not carry the blade leaf, and the platform furthermore has a second platform wall carrying the blade leaf.
  • a corresponding cooling space for acting on a cooling medium is formed between the first non-load-bearing platform wall of the second sheet-metal part and the second thicker supporting platform wall as a special load-bearing structure.
  • each stop can be designed in the form of a groove or edge. This allows a particularly reliable and aerodynamically favorable attachment of the sheet metal part at the foot of the airfoil.
  • the sheet metal parts in particular the first, is held on a further stop of an adjacent turbine blade.
  • this further stop in the form of a support formed his.
  • a support may be formed by a formed between the blade root and foot of the airfoil step.
  • the first sheet metal part of a first turbine blade engages behind the bearing of the adjacent turbine blade sealing.
  • the second sheet metal part can advantageously engage behind the support arranged on the same turbine blade or, in addition or as an alternative, be attached to the step.
  • the first resilient sheet metal part in the rest state is loosely against the further stop of the adjacent turbine blade.
  • the sheet metal part there results a still to be explained sufficient attachment of the sheet metal part from the movement or fluidic connection of the turbine blade in the operating state of a gas turbine.
  • the sealing effect of the first resilient sheet metal part on the further stop can be further improved if the first resilient sheet metal part rests under a self-generated bias on the other stop.
  • a blade stage comprises a number of annularly arranged radially in the flow channel extending turbine blades, wherein according to the invention a turbine blade is designed according to one of the above type.
  • the turbine blade is a rotor blade.
  • Such a run is at one attached axially rotating turbine rotor and rotates when operating the gas turbine with the turbine rotor.
  • a centrifugal force acting in the direction of the blade blade as a result of the rotation from the foot of the blade blade is produced.
  • the development provides that the first resilient sheet metal part reaches a sufficient sealing effect between two adjacent sheet metal parts of two adjacent blades. Due to the centrifugal force, the first resilient sheet metal part of a first blade is pressed against a further stop of the second blade and thereby applied centrifugally mounted.
  • the first resilient sheet metal part When operating the rotor blade of the gas turbine, the first resilient sheet metal part also has the function of a sealing element.
  • the contact surface of the first resilient sheet metal part acts on the further stop of the adjacent blade in the form of a support as a sealing abutment for the first sheet metal part.
  • the turbine blade is provided as a guide vane on a peripheral turbine housing.
  • a pressure gradient from the foot of the airfoil is produced in the direction of the airfoil by means of a cooling medium.
  • the alternative development provides that the first resilient sheet metal part of a first vane through the Pressure gradient is pressed against the further stop a second vane and thereby pressure-fastened. The pressure gradient is thus generated by the fact that the first resilient sheet metal part is acted upon from the back with cooling medium and is thereby pressed against the other stop.
  • the first resilient sheet metal part has the function of a sealing element.
  • the contact surfaces of the first resilient sheet metal part act on a stop described above as sufficient sealing surfaces and the stop as an abutment for the first resilient sheet metal part.
  • a boundary of the flow channel is formed, which is continuous.
  • a continuous axial boundary of the flow channel is advantageously formed.
  • it is in the Vane stages around vanes and turbine blades around vanes.
  • FIG. 1 shows a particularly preferred embodiment of a gas turbine with a flow channel and a preferred embodiment of the guide and blading in a schematic form in a cross-sectional view;
  • FIG. 2 shows a platform region of a particularly preferred embodiment of a first turbine blade of a first blade stage and a second turbine blade adjacent to the first turbine blade. Bell bucket of a second blade stage in perspective view.
  • FIG. 1 shows a gas turbine 1 with a flow channel 5 extending along an axis 3 with an annular cross-section for a working medium M.
  • a number of blade stages are arranged in the flow channel 5.
  • a second vane stage 9 is arranged behind a first vane stage 7 along the axis 3.
  • a second blade stage 13 is behind a first one
  • Blade stage 11 is arranged.
  • the guide blade stages 7, 9 have a number of guide vanes 21, which are arranged annularly on a peripheral turbine housing 15 and extend radially into the flow channel 5.
  • a blade stage 11, 13 in this case has a number of annular blades 23 arranged on an axial turbine rotor 19 and extending radially into the flow channel 5.
  • the flow of a working medium M is generated in the form of a hot gas from a burner 17.
  • a number of such burners 17 are arranged around the axis 3 in an annular space, not shown in the cross-sectional drawing of FIG.
  • a vane 21 and a rotor blade 23 are shown schematically in FIG.
  • a guide blade 21 has a blade tip 27 arranged along a blade axis 25, an airfoil 29 and a platform region 31.
  • the platform region 31 has a platform 33 extending transversely to the blade axis 25 and a blade root 35.
  • a rotor blade 23 has a blade tip 37 arranged along a blade axis, an airfoil 39 and a platform region 41.
  • the platform region 41 has a platform 43 extending transversely to the blade axis 45 and a blade root 47.
  • the platform 33 of a guide blade 21 and the platform 43 of a rotor blade 23 each form part of a boundary 49, 51 of the flow channel 5 for the working medium M, which flows through the gas turbine 1.
  • the peripheral boundary 49 is part of the peripheral turbine housing 15.
  • the rotor-side boundary 51 is part of the turbine rotor 19 rotating in the operating state of the gas turbine 1.
  • the platform 33 of a guide blade 21 and the platform 43 of a rotor blade 23 are formed by sheet metal parts fixed to the blade blade 29, 39.
  • FIG 2 shows a representative of a platform area
  • the first turbine blade 63 and second turbine blade 65 shown in FIG. 2 are shown as representative of a first stator blade 21 of a first stator blade stage 7 and a second stator blade 21 of a second stator blade stage 9 arranged axially directly behind it.
  • the first turbine blade 63 and the second turbine blade 65 are also shown as representative of a first blade 23 of the first blade stage 11 shown in FIG. 1 and a second rotor blade 23 of the second blade stage 13 arranged axially directly behind it.
  • the turbine blades 63, 65 are vanes.
  • the first turbine blade 63 has an airfoil 69 drawn in demolition.
  • Turbine blade 65 in this case has an airfoil 67 drawn in demolition.
  • a platform 71 which extends transversely to the blade axis 73, 75, is formed in the platform region 61 at the foot of the blade leaf 67, 69.
  • the platform 71 is on the one hand by a first spring-elastic sheet metal part 79 shown in the first blade 63 and the others are formed by a second sheet metal part 77 shown in the second blade 65.
  • the first resilient sheet metal part 79 is attached to a first stop 83 on one side of the airfoil 69, which side is shown in the first turbine blade 63.
  • the second resilient sheet metal part 77 is fixed to a second stop 81 on the other side of the airfoil 67, which side is shown in the second turbine blade 65.
  • the attachment can be done for example by welding or soldering and is tight.
  • the first stop 83 and the second stop 81 are each formed in the form of a groove, in each of which the first resilient sheet metal part 79 and the second sheet metal part 77 each pierces with its end on the blade 69 and the blade 67 end edge.
  • the second resilient sheet metal part 77 is also held on a further stop 85 of the second turbine blade 65.
  • the second sheet metal part 77 is attached to the stopper 85.
  • the second sheet metal part 77 could also engage behind the further stop 85.
  • the latter is the case for the first resilient sheet metal part 79 of the first turbine blade 63, which is held together with the second sheet metal part 77 on the further stop 85 of the second turbine blade 67. To this end, the first resilient sheet metal part 79 loosely engages the further stop 85.
  • the further stop 85 is designed to hold the second sheet metal part 77 and the first resilient sheet metal part 79 in the form of a support and thus forms a side on its side facing the first resilient sheet metal part 79 Sealing surface which serves as an abutment for the first resilient sheet metal part 79.
  • the platform 71 comes on its rear side 89 largely without a support structure or a supporting platform wall. Rather, a first cooling space 93 and a second cooling roughness 91 are formed on the rear side 89, which make it possible to optimally cool the platform 71 in the area between the second turbine blade 65 and the first turbine blade 63. In this way, an otherwise usually complicated to design platform edge construction in connection with the further stopper 85 can be made easier and without thermally compromised area.
  • the support structure 95, 97 of the turbine blades 65, 63 extending from the foot of the blade leaf 67, 69 has been optimized in terms of shape to form the blade root 35, 47 in FIG.
  • the further stop 85 is provided Sealing action of the second sheet metal part 77 and the first resilient sheet metal part 79.
  • first resilient sheet metal part 79 by means of a self-generated by the first resilient sheet metal part 79 self-biasing abuts the other stop 85 sealingly. As a result, the contact pressure generated by the pressure gradient can be increased.
  • the sheet metal parts 77, 79 of the platform 71 are centrifugally mounted or pressure-mounted and simultaneously develop their sealing effect and separation effect between the H thoroughlygasbeetzmannten flow channel 5 and thedemediumbeaufschlagten back 89 of the platform 71st
  • a turbine blade 63, 65 has a blade blade 67, 69 arranged along a blade axis 73, 75 and a platform region 61 at the foot of the blade 67, 69 arranged a platform 71, which extends transversely to the blade axis 73, 75, proposed that the platform 71 is formed by a fixed to the blade plate 67, 69 sheet metal part 77, 79. This also leads to a gas turbine 1 with a along an axis 3 of the
  • Gas turbine 1 extending flow channel 5 with an annular cross-section for a working medium M, a second 9, 13 behind a first 7, 11 arranged along the axis 3 blade stage with a blade stage 7, 9, 11, 13 a number of annularly arranged, radially into the Channel 5 extending turbine blades 63, 65 according to the above concept.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Control Of Turbines (AREA)

Abstract

L'invention concerne une aube de turbine (63, 65) comprenant une pale (67, 69) qui s'étend le long d'un axe d'aube (73, 75) et une zone de plateforme (61) qui est disposée à la base de la pale (67, 69) et comporte une plateforme (71) qui s'étend transversalement à l'axe d'aube (73, 75). L'objectif de cette invention est de configurer la délimitation (87) d'un canal d'écoulement (5) d'une turbine à gaz (1) de la manière la plus simple possible. A cet effet, la plateforme (71) est formée par une pièce en tôle (77, 79) élastique à la manière d'un ressort qui repose contre la pale (67, 69). Cette pièce mène à une turbine à gaz (1) qui comporte un canal d'écoulement qui s'étend le long d'un axe (3) de la turbine à gaz (1), présente une section transversale annulaire pour une substance de travail (M), et qui comporte un deuxième (9, 13) étage d'aube (7, 9, 11, 13) situé en aval d'un premier (7, 11) étage d'aube le long d'un axe (3). Selon l'invention, un étage d'aube comporte une pluralité d'aubes de turbine (63, 65) disposées de manière annulaire et s'étendant radialement dans le canal d'écoulement (5).
EP05706868A 2004-01-20 2005-01-12 Aube de turbine a gaz et turbine a gaz avec une telle aube Expired - Lifetime EP1706593B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PL05706868T PL1706593T3 (pl) 2004-01-20 2005-01-12 Łopatka turbiny i turbina gazowa z taką łopatką
EP05706868A EP1706593B1 (fr) 2004-01-20 2005-01-12 Aube de turbine a gaz et turbine a gaz avec une telle aube

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04001107A EP1557534A1 (fr) 2004-01-20 2004-01-20 Aube de turbine à gaz et turbine à gaz avec une telle aube
PCT/EP2005/000223 WO2005068785A1 (fr) 2004-01-20 2005-01-12 Aube de turbine et turbine a gaz pourvue de cette aube de turbine
EP05706868A EP1706593B1 (fr) 2004-01-20 2005-01-12 Aube de turbine a gaz et turbine a gaz avec une telle aube

Publications (2)

Publication Number Publication Date
EP1706593A1 true EP1706593A1 (fr) 2006-10-04
EP1706593B1 EP1706593B1 (fr) 2011-08-17

Family

ID=34626466

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04001107A Withdrawn EP1557534A1 (fr) 2004-01-20 2004-01-20 Aube de turbine à gaz et turbine à gaz avec une telle aube
EP05706868A Expired - Lifetime EP1706593B1 (fr) 2004-01-20 2005-01-12 Aube de turbine a gaz et turbine a gaz avec une telle aube

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP04001107A Withdrawn EP1557534A1 (fr) 2004-01-20 2004-01-20 Aube de turbine à gaz et turbine à gaz avec une telle aube

Country Status (9)

Country Link
US (2) US7607889B2 (fr)
EP (2) EP1557534A1 (fr)
JP (1) JP4499747B2 (fr)
CN (1) CN100400795C (fr)
AT (1) ATE520862T1 (fr)
ES (1) ES2370644T3 (fr)
PL (1) PL1706593T3 (fr)
RU (1) RU2332575C2 (fr)
WO (1) WO2005068785A1 (fr)

Cited By (1)

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RU2457336C1 (ru) * 2011-01-11 2012-07-27 Светлана Владимировна Иванникова Венец турбины повышенной эффективности (втпэ)-а (варианты)

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US20100003139A1 (en) * 2008-07-03 2010-01-07 Rotating Composite Technologies, Llc Propulsor devices having variable pitch fan blades with spherical support and damping surfaces
WO2010037087A1 (fr) * 2008-09-29 2010-04-01 Bender Andrew L Turbine à haut rendement
EP2282014A1 (fr) 2009-06-23 2011-02-09 Siemens Aktiengesellschaft Section de canal d'écoulement annulaire pour une turbomachine
US8356975B2 (en) * 2010-03-23 2013-01-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured vane platform
US9976433B2 (en) 2010-04-02 2018-05-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
US8550785B2 (en) 2010-06-11 2013-10-08 Siemens Energy, Inc. Wire seal for metering of turbine blade cooling fluids
US20170049331A1 (en) * 2011-05-02 2017-02-23 Canon Kabushiki Kaisha Object information acquiring apparatus and method of controlling the same
US8961134B2 (en) * 2011-06-29 2015-02-24 Siemens Energy, Inc. Turbine blade or vane with separate endwall
US11035238B2 (en) * 2012-06-19 2021-06-15 Raytheon Technologies Corporation Airfoil including adhesively bonded shroud
WO2014165518A1 (fr) * 2013-04-01 2014-10-09 United Technologies Corporation Dispositif d'aube de stator pour un moteur à turbine
JP6547274B2 (ja) 2014-10-20 2019-07-24 株式会社デンソー 粒子状物質検出センサ
US10371162B2 (en) 2016-10-05 2019-08-06 Pratt & Whitney Canada Corp. Integrally bladed fan rotor
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Publication number Priority date Publication date Assignee Title
RU2457336C1 (ru) * 2011-01-11 2012-07-27 Светлана Владимировна Иванникова Венец турбины повышенной эффективности (втпэ)-а (варианты)

Also Published As

Publication number Publication date
ATE520862T1 (de) 2011-09-15
CN100400795C (zh) 2008-07-09
US20100008773A1 (en) 2010-01-14
RU2006129944A (ru) 2008-02-27
US7607889B2 (en) 2009-10-27
WO2005068785A1 (fr) 2005-07-28
EP1557534A1 (fr) 2005-07-27
JP4499747B2 (ja) 2010-07-07
CN1906380A (zh) 2007-01-31
US7963746B2 (en) 2011-06-21
RU2332575C2 (ru) 2008-08-27
EP1706593B1 (fr) 2011-08-17
ES2370644T3 (es) 2011-12-21
US20080232956A1 (en) 2008-09-25
PL1706593T3 (pl) 2012-01-31
JP2007518917A (ja) 2007-07-12

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