EP1557534A1 - Aube de turbine à gaz et turbine à gaz avec une telle aube - Google Patents

Aube de turbine à gaz et turbine à gaz avec une telle aube Download PDF

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Publication number
EP1557534A1
EP1557534A1 EP04001107A EP04001107A EP1557534A1 EP 1557534 A1 EP1557534 A1 EP 1557534A1 EP 04001107 A EP04001107 A EP 04001107A EP 04001107 A EP04001107 A EP 04001107A EP 1557534 A1 EP1557534 A1 EP 1557534A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine
metal part
sheet metal
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.)
Withdrawn
Application number
EP04001107A
Other languages
German (de)
English (en)
Inventor
Stefan Dr. Baldauf
Hans-Thomas Dr. 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
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 EP04001107A priority Critical patent/EP1557534A1/fr
Priority to PCT/EP2005/000223 priority patent/WO2005068785A1/fr
Priority to JP2006548254A priority patent/JP4499747B2/ja
Priority to CNB2005800019558A priority patent/CN100400795C/zh
Priority to AT05706868T priority patent/ATE520862T1/de
Priority to EP05706868A priority patent/EP1706593B1/fr
Priority to ES05706868T priority patent/ES2370644T3/es
Priority to RU2006129944/06A priority patent/RU2332575C2/ru
Priority to US10/586,462 priority patent/US7607889B2/en
Priority to PL05706868T priority patent/PL1706593T3/pl
Publication of EP1557534A1 publication Critical patent/EP1557534A1/fr
Priority to US12/563,369 priority patent/US7963746B2/en
Withdrawn legal-status Critical Current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
    • F01D5/22—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 a along a blade axis arranged airfoil and with a platform area located at the foot of the airfoil has a platform that is transverse to the blade axis extends.
  • the invention further leads to a Gas turbine with one along an axis of the gas turbine itself extending flow channel with annular cross section for a working medium, a second behind a first along the axis arranged blade stage, wherein a blade stage a number of annularly arranged radially in Having the channel extending turbine blades.
  • DE 2 628 807 A1 discloses an impingement cooling system for a Turbine blade of the type mentioned forth.
  • the DE 2 628 807 A1 is for cooling the platform in front of the Hot gas side facing away from the platform, so behind the Platform, d. H. between a blade root and the platform, arranged a perforated wall element. Through the holes the wall element meets cooling air under relatively high pressure on the side facing away from the hot gas side of the platform, thereby An efficient impingement cooling is achieved.
  • EP 1 073 827 B1 introduces a new way of construction of the platform portion of molded turbine blades.
  • the platform area is a double platform of two each other formed opposite platform walls. Thereby is achieved that the flow channel and thus the Hot gas directly exposed, the flow channel limiting Platform wall can be made thin.
  • the limiting the flow channel Platform wall is essentially for the sewer responsible for the hot gas.
  • the opposite, from the Hot gas unimpaired platform wall takes over the recording the loads resulting from the blade. This separation of functions allows it, which limits the flow channel Platform wall run so thin that the hot gas ducting is guaranteed without incurring significant burdens to catch.
  • Desirable would be as simple as possible and at the same time easy to cool and sealed flow channel limitation a gas turbine.
  • the invention begins, whose task it is to specify a turbine bucket with a platform that at the same time simply designed and also the geometrical-structural and cooling requirements in the Frame of a flow channel limitation of a gas turbine advantageous enough.
  • the task is accomplished by the Invention solved with the turbine blade mentioned, in the present invention, the platform by a on the blade fitting spring-elastic sheet metal part is formed.
  • the invention is based on the consideration that the use a non-supporting platform for the representation of the boundary a pressurized with hot gas flow channel a Gas turbine is basically suitable for the platform, and thus limiting the flow channel, as effective as possible to cool. Beyond that, the essential insight lies the invention in that it is possible, the platform to equip itself with an increased sealing effect, and while the platform is so thin-walled, that they by a fitting to the airfoil elastic Sheet metal part is formed.
  • the platform fulfills as a hot gas acted upon Flow channel limiting part all requirements in terms of cooling and also a sealing element.
  • the voltage applied to the blade leaf resilient sheet metal part is the platform as such sufficiently flexible to simultaneous relative movements of adjacent blades and other parts and still get the sealing effect. This eliminates the need for a special sealing element. This simplifies the design and cooling the flow channel boundary.
  • this is resilient Sheet metal part provided as a non-supporting platform wall, which limits the hot gas loaded flow channel.
  • a supporting platform wall as provided in EP 1 073 827 B1, which are arranged behind the elastic sheet metal part could be, according to the first variant of the invention largely omitted, since in this case a blade foot in Platform area as a special load bearing structure is provided.
  • the platform so only from the on the blade adjacent resilient sheet metal part.
  • the spring-elastic Sheet metal part in the idle state of the turbine blade loose a stop at the foot of the blade.
  • the elastic Sheet metal part also be attached to the foot of the blade.
  • a stop in the form of a groove or Be formed edge This allows a particularly reliable Installation of the resilient sheet metal part at the foot of the Airfoil.
  • the platform by a first on a first stop on one side of the airfoil fitting elastic sheet metal part is formed and through a second at a second stop on the other side the resilient airfoil part of the blade is formed.
  • At least one of elastic sheet metal parts, especially the first one, on one another stop is held.
  • this can be formed further stop in the form of a support.
  • a support by a between Shovel foot and foot of the blade formed integrally formed step be.
  • the at least one resilient sheet metal part The support can advantageously engage behind or, in addition or alternatively, be attached to the stage.
  • the invention also leads to the solution of the problem an initially mentioned gas turbine, wherein a blade stage a number of annularly arranged radially in the Flow channel extending turbine blades, wherein According to the invention, a turbine blade according to one of the above Art is executed.
  • the turbine blade a blade.
  • Such a blade is at one attached axially extending turbine rotor and turns during operation of the gas turbine with the turbine rotor.
  • For rotary Operation of a turbine blade in the form of a blade on the turbine rotor is one through the rotation of the Foot of the blade in the direction of the blade acting centrifugal force generated. This sees the first training ago that the resilient sheet metal part by the centrifugal force pressed against a stop and thereby centrifugally mounted is.
  • the elastic sheet metal part at rest of the blade loose on a Stop at the foot of the airfoil rests through the Centrifugal force ensures that the resilient sheet metal part is attached to the blade in the operating state.
  • the elastic sheet metal part has the function of a Sealing element.
  • the contact surface of the elastic sheet metal part on a stop at the foot of the Airfoil or on the other stop in the form of a Support as a sealing abutment for the sheet metal part.
  • the turbine blade As a guide vane on a peripheral turbine housing intended.
  • Cooling medium a pressure gradient from the foot of the airfoil ago generated in the direction of the airfoil. It sees the second development before that the resilient sheet metal part pressed by the pressure gradient against the stop and thereby is pressure-fastened.
  • the pressure gradient is thus characterized creates that spring-elastic sheet metal part from behind with Coolant is applied and thereby against a stop pressed the above-explained type.
  • the pressure drop is sufficiently large, so this not only passed for a pressure attachment of the resilient sheet metal part, but also in operation of the vane In the gas turbine, the resilient sheet metal part the function a sealing element has.
  • the contact surfaces of the elastic Sheet metal part act on a stop explained above as sufficient sealing surfaces and abutments for the elastic Sheet metal part.
  • FIG. 1 shows a gas turbine 1 with one extending along one Axis 3 extending flow channel 5 with annular cross-section for a working medium M.
  • the flow channel 5 is a number of blade stages arranged.
  • a second blade stage 13 behind a first Blade stage 11 is arranged.
  • the vane stages 7, 9 have a number of annular at a peripheral Turbine housings 15 are arranged radially in the flow channel 5 extending vanes 21.
  • a blade stage 11, 13 in this case has a number of annular on a axial turbine rotor 19 arranged radially in the Flow channel 5 extending blades 23.
  • the flow a working medium M is in the form of a hot gas generated by a burner 17.
  • a burner 17 According to the annular Cross section of the flow channel 5 is a number of such Burner 17 in a in the cross-sectional drawing of FIG 1 Not shown annulus disposed about the axis 3 around.
  • a vane 21 and a blade 23 are in the 1 shows schematically.
  • a vane 21 has a along a blade axis 25 arranged blade tip 27, an airfoil 29 and a platform section 31.
  • Of the Platform region 31 has a transverse to the blade axis 25th extending platform 33 and a blade root 35.
  • a blade 23 has one along a blade axis arranged blade tip 37, a blade 39 and a Platform area 41 on.
  • the platform area 41 has a transverse to the blade axis 45 extending platform 43 and a blade foot 47 on.
  • the peripheral boundary 49 is part of the peripheral turbine housing 15.
  • the rotor-side boundary 51 is part of the operating state the gas turbine 1 rotating turbine rotor 19th
  • FIG 2 shows a representative of a platform area 31, 41 a platform portion 61.
  • the second shown in FIG Turbine blade 63 and first turbine blade 65 is here representative of a first vane 21 of a first Guide vane stage 7 and an axially arranged directly behind it second vane 21 of a second vane stage 9 shown.
  • the second turbine blade 63 and the first Turbine blade 65 are also representative of one in the 1 shows first blade 23 of the first blade stage 11 and an axially directly behind arranged second Blade 23 of the second blade stage 13 shown.
  • the turbine blades 63, 65 are but around vanes.
  • the first turbine blade 65 has a subscribed in demolition Blade 67 on.
  • the second turbine blade 63 has a drawn in demolition blade 69.
  • a platform 71 formed, which is transverse to the Blade axis 73, 75 extends.
  • the platform is 71 on the one hand by a shown in the first blade 65, the first resilient sheet metal part 77 formed and the other by a second spring-elastic shown in the second blade 63 Sheet metal part 79 formed.
  • the first elastic Sheet metal part 77 is located on a first stop 81 on the one side of the airfoil 67, which side at the first turbine blade 65 is shown.
  • the second elastic Sheet metal part 79 is located on a second stop 83 the other side of the airfoil 69, which side at the second turbine blade 63 is shown.
  • the first stop 81 and the second stop 83 is in each case in Formed a groove in which in each case the first resilient Sheet metal part 77 and the second spring-elastic Sheet metal part 79 each with its on the blade 67 and am Airfoil 69 ends edge pierces.
  • the first elastic Sheet metal part 77 is also at another Stop 85 of the first turbine blade 65 held. In the present embodiment, the first elastic Sheet metal part 77 attached to stop 85. Alternatively or in addition could the first spring-elastic sheet metal part also the other Engage stop 85 behind.
  • the latter is the case for the second resilient sheet metal part 79 of the second turbine blade 63, which together with the first spring elastic Sheet metal part 77 on the further stop 85 of the first turbine blade 67 is held.
  • the second spring elastic engages behind Sheet metal part 79 the further stop 85.
  • the other Stop 85 is for holding the first resilient sheet metal part 77 and for holding the second resilient sheet metal part 79 formed in the form of a support and thus forms on its second resilient sheet metal part 79 facing Side a sealing surface, which serves as an abutment for the second elastic sheet metal part 79 is used.
  • the platform 71 comes on its back 89 largely without a support structure or a bearing decking wall. Rather, it is up the rear side 89 a first cooling space 91 and a second cooling space 93 formed, which allow the platform 71 in the Area between the first turbine blade 65 and the second Turbine blade 63 to cool optimally. In this way can be an otherwise usually complicated to be designed Platform edge construction in connection with the other Stops 85 easier and without thermally hazardous area be designed.
  • 93 is that from the foot of the airfoil 67, 69th outgoing support structure 95, 97 of the turbine blades 65, 63 optimized in shape to the blade root 35, 47 in FIG 1 continued.
  • first turbine blade 65 and the second turbine blade 63 preferably in the form of a in 1 shown guide vane 21 or possibly also in the form of a rotor blade 23 shown in FIG 1, results the particular on the further stop 85 and the attacks 81, 83 provided sealing effect of the first elastic Sheet metal part 77 and the second spring-elastic Sheet metal part 79.
  • 63 in the form of a blade 23 on a turbine rotor 19 becomes one by the rotation from the foot of the Airfoil 67, 69 in the direction 99 of the airfoil 67, 69 acting centrifugal force generated.
  • the resilient sheet metal part 79 by means of a Sheet metal part 79 self-generated bias on further stop 85 sealingly applied. This allows the pressure gradient generated contact pressure to be increased.
  • the platform 71 in the form of elastic sheet metal parts 77, 79 by the centrifugal force or by the pressure gradient against the further stop 85 and the first stop 81 as also pressed against the second stop 83.
  • the resilient sheet metal parts 77, 79 of the platform 71st centrifugal force fastened or pressure-mounted and unfold simultaneously their sealing effect and separation effect between the H thoroughlygasbeetzmannten flow channel 5 and thedemediumbeaufschlagten Rear 89 of the platform 71.
  • a gas turbine 1 as simple as possible, at a turbine blade 63, 65 with one along a Blade axis 73, 75 arranged blade 67, 69 and with a platform area 61 at the foot of the airfoil 67, 69 arranged a platform 71, which transversely extends to the blade axis 73, 75, suggested that the Platform 71 by a voltage applied to the blade 67, 69 resilient sheet metal part 77, 79 is formed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
EP04001107A 2004-01-20 2004-01-20 Aube de turbine à gaz et turbine à gaz avec une telle aube Withdrawn EP1557534A1 (fr)

Priority Applications (11)

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
EP05706868A EP1706593B1 (fr) 2004-01-20 2005-01-12 Aube de turbine a gaz et turbine a gaz avec une telle aube
JP2006548254A JP4499747B2 (ja) 2004-01-20 2005-01-12 タービン翼およびそのタービン翼を備えたガスタービン
CNB2005800019558A CN100400795C (zh) 2004-01-20 2005-01-12 涡轮叶片和具有这种涡轮叶片的燃气轮机
AT05706868T ATE520862T1 (de) 2004-01-20 2005-01-12 Turbinenschaufel und gasturbine mit einer solchen turbinenschaufel
PCT/EP2005/000223 WO2005068785A1 (fr) 2004-01-20 2005-01-12 Aube de turbine et turbine a gaz pourvue de cette aube de turbine
ES05706868T ES2370644T3 (es) 2004-01-20 2005-01-12 Pala de turbina y turbina de gas con una pala de turbina de este tipo.
RU2006129944/06A RU2332575C2 (ru) 2004-01-20 2005-01-12 Турбинная лопатка и газовая турбина с такой турбинной лопаткой
US10/586,462 US7607889B2 (en) 2004-01-20 2005-01-12 Turbine blade and gas turbine equipped with a turbine blade
PL05706868T PL1706593T3 (pl) 2004-01-20 2005-01-12 Łopatka turbiny i turbina gazowa z taką łopatką
US12/563,369 US7963746B2 (en) 2004-01-20 2009-09-21 Turbine blade and gas turbine equipped with a turbine blade

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP1557534A1 true EP1557534A1 (fr) 2005-07-27

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 Not-in-force EP1706593B1 (fr) 2004-01-20 2005-01-12 Aube de turbine a gaz et turbine a gaz avec une telle aube

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05706868A Not-in-force EP1706593B1 (fr) 2004-01-20 2005-01-12 Aube de turbine a gaz et turbine a 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 (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7766609B1 (en) * 2007-05-24 2010-08-03 Florida Turbine Technologies, Inc. Turbine vane endwall with float wall heat shield
WO2010149528A1 (fr) 2009-06-23 2010-12-29 Siemens Aktiengesellschaft Segment de canal d'écoulement de forme annulaire pour une turbomachine

Families Citing this family (13)

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Publication number Priority date Publication date Assignee Title
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
US20110194936A1 (en) * 2008-09-29 2011-08-11 Bender Andrew L High efficiency turbine
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
RU2457336C1 (ru) * 2011-01-11 2012-07-27 Светлана Владимировна Иванникова Венец турбины повышенной эффективности (втпэ)-а (варианты)
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
US10344606B2 (en) * 2013-04-01 2019-07-09 United Technologies Corporation Stator vane arrangement for a turbine engine
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
US11852018B1 (en) * 2022-08-10 2023-12-26 General Electric Company Turbine nozzle with planar surface adjacent side slash face

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DE579989C (de) * 1933-07-04 Karl Roeder Dr Ing Kopfringlose Beschaufelung fuer axialbeaufschlagte Dampf- oder Gasturbinen
US5244345A (en) * 1991-01-15 1993-09-14 Rolls-Royce Plc Rotor
FR2831207A1 (fr) * 2001-10-24 2003-04-25 Snecma Moteurs Plates-formes pour aubes d'un ensemble rotatif

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CH291898A (de) * 1951-06-09 1953-07-15 Escher Wyss Ag Beschaufelung an Rotoren von axial durchströmten Kreiselmaschinen, insbesondere von Dampf-, Gasturbinen und Verdichtern.
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EP1073827B1 (fr) 1998-04-21 2003-10-08 Siemens Aktiengesellschaft Aube de turbine
US6431835B1 (en) * 2000-10-17 2002-08-13 Honeywell International, Inc. Fan blade compliant shim
US6860722B2 (en) * 2003-01-31 2005-03-01 General Electric Company Snap on blade shim
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Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE579989C (de) * 1933-07-04 Karl Roeder Dr Ing Kopfringlose Beschaufelung fuer axialbeaufschlagte Dampf- oder Gasturbinen
US5244345A (en) * 1991-01-15 1993-09-14 Rolls-Royce Plc Rotor
FR2831207A1 (fr) * 2001-10-24 2003-04-25 Snecma Moteurs Plates-formes pour aubes d'un ensemble rotatif

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7766609B1 (en) * 2007-05-24 2010-08-03 Florida Turbine Technologies, Inc. Turbine vane endwall with float wall heat shield
WO2010149528A1 (fr) 2009-06-23 2010-12-29 Siemens Aktiengesellschaft Segment de canal d'écoulement de forme annulaire pour une turbomachine
EP2282014A1 (fr) * 2009-06-23 2011-02-09 Siemens Aktiengesellschaft Section de canal d'écoulement annulaire pour une turbomachine

Also Published As

Publication number Publication date
US7963746B2 (en) 2011-06-21
ES2370644T3 (es) 2011-12-21
EP1706593A1 (fr) 2006-10-04
WO2005068785A1 (fr) 2005-07-28
JP4499747B2 (ja) 2010-07-07
CN100400795C (zh) 2008-07-09
EP1706593B1 (fr) 2011-08-17
JP2007518917A (ja) 2007-07-12
US7607889B2 (en) 2009-10-27
RU2006129944A (ru) 2008-02-27
CN1906380A (zh) 2007-01-31
ATE520862T1 (de) 2011-09-15
US20100008773A1 (en) 2010-01-14
US20080232956A1 (en) 2008-09-25
RU2332575C2 (ru) 2008-08-27
PL1706593T3 (pl) 2012-01-31

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