EP2146054A1 - Turbine axiale pour une turbine à gaz - Google Patents

Turbine axiale pour une turbine à gaz Download PDF

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Publication number
EP2146054A1
EP2146054A1 EP08012960A EP08012960A EP2146054A1 EP 2146054 A1 EP2146054 A1 EP 2146054A1 EP 08012960 A EP08012960 A EP 08012960A EP 08012960 A EP08012960 A EP 08012960A EP 2146054 A1 EP2146054 A1 EP 2146054A1
Authority
EP
European Patent Office
Prior art keywords
axial turbine
radial
annular space
curvature
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Withdrawn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
EP08012960A
Other languages
German (de)
English (en)
Inventor
Stefan Braun
Christian Dr. Cornelius
Andreas Dr. Heilos
Olaf Dr. Hein
Thomas Dr. Hofbauer
Annika Juchems
Christian Lerner
Silvio-Ulrich Dr. Martin
Thorsten Mattheis
Ralf Müsgen
Eckart Dr. Schumann
Rostislav Dr. Teteruk
Adam Zimmermann
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 EP08012960A priority Critical patent/EP2146054A1/fr
Priority to CN200980128055.8A priority patent/CN102099548B/zh
Priority to EP09797468.7A priority patent/EP2297430B1/fr
Priority to US13/054,162 priority patent/US20110188999A1/en
Priority to JP2011517874A priority patent/JP5260740B2/ja
Priority to PCT/EP2009/058682 priority patent/WO2010006976A1/fr
Publication of EP2146054A1 publication Critical patent/EP2146054A1/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour

Definitions

  • the invention relates to an axial turbine for a gas turbine, wherein the axial turbine has low gap losses.
  • a gas turbine has a turbine, for example, in axial construction.
  • the turbine has a housing and a rotor which is surrounded by the housing.
  • the rotor has a shaft on which shaft power is removable.
  • a hub Surrounding the shaft, a hub is provided, whose hub contour together with the inner contour of the housing forms a flow channel through the turbine.
  • the flow channel has a cross section which widens in the flow direction.
  • the rotor has a plurality of rotor stages, each formed by a blade grid.
  • the blade lattices have a plurality of rotor blades, which are fastened with their one end in each case on the hub side to the rotor and with its other end pointing radially outward.
  • a blade tip is formed, which faces the inside of the housing and is disposed immediately adjacent.
  • the distance between the blade tips and the inside of the housing is formed as a radial gap, which is dimensioned such that on the one hand the blade tips do not rub against the housing during operation of the gas turbine and on the other hand the leakage flow through the radial gap that occurs during operation of the gas turbine is as low as possible ,
  • the leakage flow through the radial gap is desirable for the leakage flow through the radial gap to be as low as possible, so that the power gain in the turbine is as high as possible.
  • the housing of the turbine is massively designed to withstand the pressure and temperature stresses associated with gas turbine operation to be able to withstand. Furthermore, the housing is rigid, so that the load application to the housing during operation of the gas turbine has only a small deformation of the housing result. In contrast, the blades are thinner and less massive compared to the housing.
  • the inside of the housing and the blades are in contact with hot gas, with the blades completely bypassing the hot gas.
  • the blades heat up faster than the housing.
  • the blades and the housing have different thermal expansion rates, so that when starting and stopping the gas turbine, the height of the radial gap changes, the radial gap is smaller when starting and larger when starting. So that when starting the blade tips of the blades do not abut the housing and damage it, the radial gap is provided with a minimum height dimensioned such that when the gas turbine starts, the blade tips almost never touch the housing. This has the consequence that a correspondingly dimensioned radial gap is kept at the blade tips, which leads to a reduction of the power density and the efficiency of the gas turbine.
  • Modern blades have a very high aerodynamic efficiency, which is achieved by a high pressure load of the blades. Caused by the high pressure load, the leakage flow through the radial gap is high, so that the overall efficiency of the blade is greatly affected by the character and intensity of the leakage flow through the radial gap. A reduction in the losses caused by the leakage flow causes a great improvement in the overall efficiency of the blade.
  • attempts are made to reduce the aerodynamic losses in the gap area of the blade by means of reduction measures to reduce the leakage flow.
  • measures to reduce the radial gap or a special shape of the blade tips are provided, such as crowns or targetedde Kunststoffausblasonne.
  • the object of the invention is to provide an axial turbine for a gas turbine, which has a high aerodynamic efficiency.
  • the axial turbine according to the invention for a gas turbine has a blade lattice, which is formed by blades, each having a leading edge and a radially outer, free-standing blade tip, an annular wall enclosing the blade lattice with an annular space inside, with the annular space immediately adjacent to the blade tips to form the Radial gap between the envelope of the blade tips and the annular space inside is arranged, the blades are designed aerodynamically at their blade tips that is located in the operation of the axial turbine, the region with the highest pressure load of the blade tips in the leading edges, and wherein the blades in the area Leading edges each have a radial elevation and the annular space wall on the annular space inside a circumferential radial recess which cooperates with the radial elevations such that a Spaltw eitenminimum located in the main flow direction of the axial turbine is located in the region of the leading edge.
  • the profile section on the blade tip is designed contrary to the conventional design as a "front-loaded design". That is, the largest pressure load is moved from the rear part of the blade in the region of the profile leading edge.
  • the annular space in the region of the blade tip is designed as a contour deviating from the conventional annular space. In determining the shape of the annular space contour is also taken into account that the minimum gap width is arranged in the operation of the axial turbine in the range of maximum pressure difference between the pressure side and the suction side of the blade.
  • the amount of leakage flow is directly targeted reduced and reduced their adverse effects on the overall efficiency of the blade lattice.
  • the blade is designed in the region of the blade tip in the "front-loaded design". Seen over the height of the blade, this range can be about 20%. The remainder of the blade can then be conventionally designed in a "rear-loaded design”.
  • the radial recess is arranged in the front third.
  • the radial recess is located in the region of the highest pressure load of the blade tip, so that the gap flow is reduced.
  • the radial depression and the radial elevations are shaped in such a way that the course of the radial gap seen in the main flow direction of the axial turbine runs essentially the same distance, wavy, edge-free and step-free.
  • the course of the radial recess on the annular space inside seen in the main flow direction of the axial turbine has a first curvature section, an adjoining second curvature section and an adjoining third curvature section, wherein the first curvature section is delimited by the second curvature section with a first inflection point and the second curvature portion is bordered by the third curvature portion at a second inflection point, so that the curvatures of the first curvature portion and the third curvature portion have the same sign different from the sign of the curvature of the second curvature portion.
  • the annular gap in the main flow direction has a uniform, not abruptly changing course, so that the flow in the region of the blade tip has low losses.
  • the profile of the radial elevations seen in the main flow direction of the axial turbine is modeled on the course of the radial recess at its sides facing the radial gap.
  • the curvature of the first curvature portion is preferably larger than that of the third curvature portion.
  • the first inflection point is preferably located in the region of the front edge.
  • the course of the annular channel seen in the main flow direction of the axial turbine is divergent.
  • FIGS. 1 to 3 has an axial turbine 1 on a blade 2, which has a front edge 3 and a trailing edge 4.
  • the rotor blade 2 has a pressure side 5 and a suction side 6, which each extend from the front edge 3 to the trailing edge 4.
  • the pressure side 5 is lined with the suction side 6 more concave curved.
  • the blade 2 has at its radially outer end a blade tip 13, which is exposed. In the area of the blade tip 13, the blade 2 is designed in the "front-loaded design" 7.
  • the "rear-loaded design” 8 is shown, in which the pressure side 5 is less curved in the region of the front edge 3 than in the "front-loaded design" 7.
  • the region 9 with the highest pressure loading of the blade 2 is located in the region of the blade tip 13 in the vicinity of the leading edge 3.
  • the axial turbine 1 on the hub side, a hub contour 10 on which the blade 2 is fixed. Radially outward, the axial turbine 1 has an annular space wall 11 which has an annular space inner side 12 facing the blade tip 13. With the annular space wall 11, the blade 2 is sheathed and forms with the annular space inside 13 together with the hub contour 10 a divergent annular space of the axial turbine first
  • FIG. 3 the blade 2 is also shown with a conventional blade tip 23 and the annular space wall 11 with a conventional annular space inside 24, wherein the conventional blade tip 23 and the conventional annular space inside 24 have a straight course.
  • annular space wall 11 on the annular space inside a radial recess 12 which is arranged in the region of the front edge 3 of the blade 2.
  • a radial elevation 16 is provided on the blade tip 13. The radial elevation 16 runs essentially parallel to the radial recess 15, so that the radial gap 14 has a uniform course seen in the main flow direction of the axial turbine 1.
  • the radial recess has a first curved section 17, an adjoining second curved section 19 and an adjoining third curved section 21.
  • the first curvature portion 17 is delimited from the second curvature portion 19 with a first inflection point 18, and the second curvature portion 19 is from the third curvature portion 21 from a second inflection point 20 demarcated.
  • the center of curvature of the first curvature section 17 and of the third curvature section 21 lies radially outside the axial turbine 1 and the center of curvature of the second curvature section 19 within the axial turbine 1.
  • the curvature of the first curvature portion 17 is greater than the curvature of the third curvature portion 21, so that the radial gap 14 in the region of the front edge 3 has a radially outward, steeper course than in the region of the third curvature portion 21st
  • the radial recess 15 and the radial elevation 16 are arranged in the front third of the blade tip 13. Because the blade 2 is designed in the "front-loaded design" in the area of the blade tip 13, the area 9 with the highest pressure load is located precisely in this area.
  • the radial recess 15 and the radial elevation 16 are arranged to one another such that a gap minimum 22 is formed in the region 9 of the highest pressure load.
  • a leakage flow which forms during operation of the axial turbine 1 through the radial gap 14 is exactly low in the region 9 with the highest pressure load.
  • the moving blade 2 has a high aerodynamic efficiency, in particular in the area of the blade tip 13.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08012960A 2008-07-17 2008-07-17 Turbine axiale pour une turbine à gaz Withdrawn EP2146054A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP08012960A EP2146054A1 (fr) 2008-07-17 2008-07-17 Turbine axiale pour une turbine à gaz
CN200980128055.8A CN102099548B (zh) 2008-07-17 2009-07-08 燃气涡轮机的在叶片和外壳间具有小间隙的轴流式涡轮机
EP09797468.7A EP2297430B1 (fr) 2008-07-17 2009-07-08 Turbine axiale pour une turbine à gaz
US13/054,162 US20110188999A1 (en) 2008-07-17 2009-07-08 Axial turbine for a gas turbine with limited play between blades and housing
JP2011517874A JP5260740B2 (ja) 2008-07-17 2009-07-08 ブレードとハウジングとの間に規定された遊びを備えるガスタービンのための軸流タービン
PCT/EP2009/058682 WO2010006976A1 (fr) 2008-07-17 2009-07-08 Turbine axiale pour turbine à gaz, à faible jeu entre les aubes et la carcasse

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08012960A EP2146054A1 (fr) 2008-07-17 2008-07-17 Turbine axiale pour une turbine à gaz

Publications (1)

Publication Number Publication Date
EP2146054A1 true EP2146054A1 (fr) 2010-01-20

Family

ID=40010789

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08012960A Withdrawn EP2146054A1 (fr) 2008-07-17 2008-07-17 Turbine axiale pour une turbine à gaz
EP09797468.7A Not-in-force EP2297430B1 (fr) 2008-07-17 2009-07-08 Turbine axiale pour une turbine à gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP09797468.7A Not-in-force EP2297430B1 (fr) 2008-07-17 2009-07-08 Turbine axiale pour une turbine à gaz

Country Status (5)

Country Link
US (1) US20110188999A1 (fr)
EP (2) EP2146054A1 (fr)
JP (1) JP5260740B2 (fr)
CN (1) CN102099548B (fr)
WO (1) WO2010006976A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020115410A1 (fr) * 2018-12-05 2020-06-11 Safran Turbine ou de compresseur pour moteur a turbine a gaz a pertes de jeu limitees

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201006449D0 (en) * 2010-04-19 2010-06-02 Rolls Royce Plc Blades
JP6012519B2 (ja) * 2013-03-21 2016-10-25 三菱重工業株式会社 タービン、及びこれを備えた回転機械
FR3010463B1 (fr) * 2013-09-11 2015-08-21 IFP Energies Nouvelles Impulseur de pompe polyphasique avec des moyens d'amplification et de repartition d'ecoulements de jeu.
GB201508763D0 (en) * 2015-05-22 2015-07-01 Rolls Royce Plc Rotary blade manufacturing method
CN108487942A (zh) * 2018-03-15 2018-09-04 哈尔滨工业大学 控制涡轮叶尖间隙流动的机匣及叶片联合造型方法
BE1026579B1 (fr) * 2018-08-31 2020-03-30 Safran Aero Boosters Sa Aube a protuberance pour compresseur de turbomachine
RU2694560C1 (ru) * 2018-09-12 2019-07-16 Государственный научный центр Российской Федерации - федеральное государственное унитарное предприятие "Исследовательский Центр имени М.В. Келдыша" Центростремительная турбина
CN114517794B (zh) * 2022-03-01 2024-07-09 大连海事大学 一种跨音速轴流压气机联合机匣处理结构
CN114962329B (zh) * 2022-05-27 2024-04-26 哈尔滨工程大学 一种压气机转子间隙结构及应用

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FR996967A (fr) * 1949-09-06 1951-12-31 Rateau Soc Perfectionnement aux aubages de turbomachines
EP0292250A1 (fr) * 1987-05-19 1988-11-23 Union Carbide Corporation Joint d'étanchéité de gaz tournant et aubes pour turbine et compresseur
EP1057969A2 (fr) * 1999-06-03 2000-12-06 Ebara Corporation Aubage de turbine
EP1253295A2 (fr) * 2001-04-27 2002-10-30 Mitsubishi Heavy Industries, Ltd. Turbine axiale ayant un gradin dans un passage d'échappement
EP1267042A2 (fr) * 2001-06-14 2002-12-18 Mitsubishi Heavy Industries, Ltd. Aube de turbine à gaz avec bande de recouvrement
EP1531233A2 (fr) * 2003-11-12 2005-05-18 MTU Aero Engines GmbH Turbine à gaz conprenant des aubes statoriques ayant différentes courbures radiales

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US4738586A (en) * 1985-03-11 1988-04-19 United Technologies Corporation Compressor blade tip seal
US5639095A (en) * 1988-01-04 1997-06-17 Twentieth Technology Low-leakage and low-instability labyrinth seal
JPH0726904A (ja) * 1993-07-12 1995-01-27 Ishikawajima Harima Heavy Ind Co Ltd 回転機械装置の翼端部構造
JP3118136B2 (ja) * 1994-03-28 2000-12-18 株式会社先進材料利用ガスジェネレータ研究所 軸流圧縮機のケーシング
EP0903468B1 (fr) * 1997-09-19 2003-08-20 ALSTOM (Switzerland) Ltd Dispositif d'étanchéité pour un interstice
US6338609B1 (en) * 2000-02-18 2002-01-15 General Electric Company Convex compressor casing
JP3927886B2 (ja) * 2002-08-09 2007-06-13 本田技研工業株式会社 軸流圧縮機
DE102004059904A1 (de) * 2004-12-13 2006-06-14 Alstom Technology Ltd Laufschaufel für eine Turbomaschine sowie Verfahren zu deren Herstellung
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Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR996967A (fr) * 1949-09-06 1951-12-31 Rateau Soc Perfectionnement aux aubages de turbomachines
EP0292250A1 (fr) * 1987-05-19 1988-11-23 Union Carbide Corporation Joint d'étanchéité de gaz tournant et aubes pour turbine et compresseur
EP1057969A2 (fr) * 1999-06-03 2000-12-06 Ebara Corporation Aubage de turbine
EP1253295A2 (fr) * 2001-04-27 2002-10-30 Mitsubishi Heavy Industries, Ltd. Turbine axiale ayant un gradin dans un passage d'échappement
EP1267042A2 (fr) * 2001-06-14 2002-12-18 Mitsubishi Heavy Industries, Ltd. Aube de turbine à gaz avec bande de recouvrement
EP1531233A2 (fr) * 2003-11-12 2005-05-18 MTU Aero Engines GmbH Turbine à gaz conprenant des aubes statoriques ayant différentes courbures radiales

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020115410A1 (fr) * 2018-12-05 2020-06-11 Safran Turbine ou de compresseur pour moteur a turbine a gaz a pertes de jeu limitees
FR3089543A1 (fr) * 2018-12-05 2020-06-12 Safran Rotor de turbine ou de compresseur pour moteur à turbine à gaz à pertes de jeu limitées

Also Published As

Publication number Publication date
US20110188999A1 (en) 2011-08-04
CN102099548A (zh) 2011-06-15
JP2011528082A (ja) 2011-11-10
CN102099548B (zh) 2014-03-19
JP5260740B2 (ja) 2013-08-14
WO2010006976A1 (fr) 2010-01-21
EP2297430B1 (fr) 2013-08-28
EP2297430A1 (fr) 2011-03-23

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