EP2642079A1 - Turbinenleitapparat - Google Patents

Turbinenleitapparat Download PDF

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Publication number
EP2642079A1
EP2642079A1 EP12160555.4A EP12160555A EP2642079A1 EP 2642079 A1 EP2642079 A1 EP 2642079A1 EP 12160555 A EP12160555 A EP 12160555A EP 2642079 A1 EP2642079 A1 EP 2642079A1
Authority
EP
European Patent Office
Prior art keywords
ring
diaphragm
side walls
radially
turbine
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Withdrawn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
EP12160555.4A
Other languages
English (en)
French (fr)
Inventor
Angus Brummitt-Brown
Adrian Lord
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 EP12160555.4A priority Critical patent/EP2642079A1/de
Priority to JP2013058651A priority patent/JP2013194742A/ja
Priority to CN2013100913316A priority patent/CN103321694A/zh
Priority to US13/848,199 priority patent/US20140322007A1/en
Publication of EP2642079A1 publication Critical patent/EP2642079A1/de
Withdrawn legal-status Critical Current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
    • 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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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
    • F01D9/047—Nozzle boxes
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/54—Building or constructing in particular ways by sheet metal manufacturing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • This disclosure relates to the construction of diaphragms for turbines, and in particular, to a novel structure and manufacturing process for diaphragms in the high or intermediate pressure (HP or IP) stages of axial flow steam turbine power plants.
  • HP or IP high or intermediate pressure
  • a known way of constructing a turbine diaphragm is to mount an annulus of static guide blade units between an inner ring and an outer ring.
  • Each such blade unit comprises an aerofoil portion that extends between an inner platform and an outer platform, the blade unit normally being manufactured as a single integral component.
  • This is known as the "platform" type of construction.
  • Each platform is in the form of a segment of a cylinder so that when the annulus of blade units is assembled the inner platforms combine to create an inner cylinder and the outer platforms combine to create an outer cylinder.
  • the inner platforms are welded to an inner ring that retains the blade units and provides a mount for a sealing arrangement, such as a labyrinth seal, that acts between the inner ring and a rotor shaft of the turbine.
  • the outer platforms are welded to an outer ring that provides support and rigidity to the diaphragm.
  • Each of the inner and outer rings comprises two semi-circular halves which are joined along a plane that contains the major axis of the diaphragm and passes between blade units so that the entire diaphragm can be separated into two parts for assembly around the rotor of the turbo-machine.
  • Existing platform constructions for large HP or IP steam turbine diaphragms generally comprise solid inner and outer rings cut from thick metal plate, or forged, or formed from bar stock. Since such rings have substantial dimensions in the axial direction of the turbine, e.g., 100mm to 200mm, the cost of such rings is a significant factor in the ex-works price of a large steam turbine. If the rings are cut from thick plate, there is a high proportion of waste (e.g., the centre cut-out portion of an inner ring), whereas forging or other forming operations add more expense and become more difficult to control as greater thicknesses and weights of stock are manipulated.
  • the present disclosure provides a high or intermediate pressure, axial flow, turbine diaphragm comprising a radially inner ring and a radially outer ring, at least one such ring being hollow and having axially opposed walls comprising plate material.
  • the turbine diaphragm comprises:
  • both the inner and outer rings are not always necessary for both the inner and outer rings to comprise hollow structures.
  • one of the rings could be hollow, but the other ring could be a known type of solid construction.
  • the box structure of the inner hollow diaphragm ring comprises:
  • box structure of the outer hollow diaphragm ring may comprise:
  • At least one, and preferably both, of the radially inner and outer platform portions of the static blade units are integrally formed with the aerofoil portion, e.g. by machining from a single piece of material.
  • the radially outer wall of the outer diaphragm ring may be divided into a plurality of separate circumferentially extending sections by radially outward projections of at least one of the reinforcing ribs.
  • Such an arrangement could facilitate the fitting of load lifting features to the upper and lower halves of the outer ring, and/or engagement of the outer ring with corresponding location features in a turbine casing surrounding the diaphragm. Engagement of the outer ring with such location features could enable cross-key location of the diaphragm within the turbine casing and/or prevent rotation of the diaphragm within the casing as the static blades deflect the steam flow during operation of the steam turbine.
  • the radially inner side of the radially inner wall of the radially inner ring may comprise a circumferentially extending recess configured to retain a seal against leakage between relatively high and low pressure sides of the diaphragm.
  • the diaphragm is fabricated as two halves which upon assembly are united with each other on a diametric joint line.
  • the joint may comprise a bolted joint provided at each end of the diametric joint line of the outer diaphragm ring.
  • the diametrically opposed ends of the upper and lower halves of the diaphragm may be held in registration with each other by means of location features that support the outer diaphragm ring within the surrounding turbine casing.
  • only one of the inner and outer diaphragm rings will be a hollow structure, the other ring being solid.
  • the present disclosure also provides methods of manufacture of the hollow diaphragm rings and the diaphragm, as described herein and claimed in the appended claims.
  • Figure 1 illustrates a known "platform" type of construction for a large, heavy duty, axial flow, steam turbine diaphragm 1, and shows a view on a radial section of the upper half of a diaphragm during manufacture, the centreline of the diaphragm 1 being shown as dash-dotted line C.
  • the view includes a static blade unit 2, comprising radially inner and outer platforms 3, 4, and an aerofoil portion 5 whose radially inner and outer ends are integral with the aerofoils and platforms, the entire blade unit being machined from solid.
  • the inner and outer platforms 3, 4 form the inner and outer port walls for the flow of steam through the diaphragm.
  • a complete diaphragm 1 is built up by assembling successive blade units 2 into an annular array between inner and outer diaphragm rings 6, 7 and attaching the platforms to the diaphragm rings by means of deep filler welds 8 to 11.
  • the inner and outer diaphragm rings and platforms are further machined as appropriate to accommodate turbine sealing features and to fit adjacent turbine features.
  • a sealing feature has been machined on the inside circumference of the inner ring 6, comprising a channel 12 with re-entrant hook features 13, this being provided to hold a labyrinth seal or the like (not shown) to seal between the inner ring 6 and a turbine shaft 14, which is indicated by dashed lines.
  • FIG. 2 is a diagram of a radial section through the upper half of an HP or IP steam diaphragm 20 constructed in accordance with the concept disclosed herein, in which the radially inner and outer diaphragm rings 22, 24, are hollow, being fabricated from plate material as box structures.
  • the box structure of the inner hollow diaphragm ring 22 comprises a pair of axially opposed side walls 221, 222, a radially inner circumferentially extending wall 223, and a radially outer circumferentially extending wall 261 formed by radially inner platform portions of static blade units 26.
  • the box structure of the outer hollow diaphragm ring 24 comprises a pair of axially opposed side walls 241, 242, a radially inner circumferentially extending wall 262 formed by radially outer platform portions of the static blade units 26, and a radially outer circumferentially extending wall 243.
  • each side wall 221, 222, 241, 242 and the outer wall 243 could be less than 35%, (say, 20% to 30%) of the axial thickness of the ring of which it is a part.
  • the radially inner most wall 223 is shown as having a greater thickness than the other walls because a recess 228 is machined into it, as explained later.
  • a suitable plate material for fabrication of the hollow diaphragm rings is chrome molybdenum steel plate, such as specification ASTM A 387 Gr.22 C12. Such steels are commonly used to fabricate pressure vessels and there are many suppliers of chrome molybdenum steel plate worldwide. Other high alloy steels may also be suitable.
  • the radially inner and outer platform portions 261, 262, respectively, of the static blade units 26 are integrally formed with their aerofoil portions 263.
  • the static blade units 26 may comprise, for example, the well-known and readily available 12Cr alloy steel, although other materials, such as nickel-base superalloys, could also be used
  • both the inner and the outer diaphragm rings will comprise a hollow box construction, but it would nevertheless be possible for only one of the rings to be hollow, the other ring being of a solid construction.
  • the box structures may be fabricated by attaching the side walls 221, 222 and 241, 242 to the reinforcing ribs 28 and 30, then attaching the inner platforms 261 of the blade units 26 to the side walls 221, 222 of the inner ring 22. After this, the side walls 241, 242 of the outer ring 24 may be attached to the outer platforms 262 of the blade units 26.
  • the box structures of the inner and outer rings may be completed by attaching the inner circumferentially extending wall 223 to the side walls of the inner ring 22 and attaching the outer circumferentially extending wall 243 to the side walls of the outer ring 24.
  • welds 226 and 227 attach the side walls 221, 222 to the platform portions 261 and welds 224 and 225 attach the side walls 221, 222 to the radially inner wall 223, whereas for outer ring 24, welds 244 and 245 attach the side walls 241, 242 to the platform portions 262 and welds 246 and 247 attach the side walls 241, 242 to the radially outer wall 243.
  • the radially inner side of the radially inner wall 223 of the radially inner ring 22 may comprise a recess or hook arrangement 228 configured to retain and hold a shaft seal, such as a labyrinth or brush seal (not shown), in sealing engagement with a shaft 14 to minimise leakage between relatively high and low pressure sides of the diaphragm.
  • a shaft seal such as a labyrinth or brush seal (not shown)
  • the diaphragms are fabricated in two halves, an upper half and a lower half, which are united with each other on a horizontal diametric joint line J.
  • a bolted joint can be provided at each end of the joint line J.
  • the top and bottom halves of the diaphragm can each be independently supported by means of cross-key location features, as known in the industry.
  • Figure 3 is a three-dimensional pictorial view of a partially de-constructed embodiment of the upper half of an HP or IP steam turbine diaphragm
  • Figure 4 is a similar view of the lower half of the diaphragm.
  • only one static blade unit 26 is shown in position between upper and lower, inner and outer half-rings 22U, 24U and 22L, 24L, the other blade units having been omitted to show the box construction of the half-rings more clearly.
  • Figures 3 and 4 use the same reference numbering scheme as Figure 2 .
  • stiffening ribs 28 are attached to one of the side walls of each of the inner half-rings 22U, 22L, and the stiffening ribs 30, together with the joint blocks 32U, 34U, are attached to one of the side walls of the outer half-ring 24U, the joint blocks 32U, 34U being positioned at diametrically opposite ends of the outer half-ring 24U.
  • stiffening ribs 30, together with the joint blocks 32L, 34L are attached to one of the side walls of the outer half-ring 24L.
  • the other side walls of the inner and outer half-rings are attached to the ribs 28 and 30 and - in the case of the outer half-rings - to the joint blocks.
  • threaded bolt holes 36U, 36L can be machined into their respective joint blocks.
  • upper and lower inner half rings 22, 22L comprise only their side walls and their stiffening ribs
  • upper and lower outer half rings 24, 25L comprise only their side walls, their stiffening ribs and their joint blocks.
  • the inner half rings for the upper and lower halves of the diaphragm can now be placed together on a jig to produce an inner ring.
  • the outer half rings for the lower and upper halves of the diaphragm can be joined together to produce an outer ring.
  • the inner half-rings may be joined together on the jig by temporary tack welding
  • the outer half-rings may be joined together by temporary bolts which extend through the joint blocks provided at the diametrically opposed ends of the upper and lower, outer half-rings.
  • the inner platforms 261 of the static blade units 26 can be tack welded to the side walls 221, 222 of the inner ring to produce the assembly shown in Figure 5 .
  • a machining operation is performed to produce even, circular outer surfaces on the outer platforms 262 of the static blade units 26.
  • the outer ring is heated up and then shrunk on to the blade units 26 to bring the side walls 241, 242 into engagement with the outer platforms 262, thereby producing the assembly shown in Figure 6 .
  • the circumferential welds 226, 227 and 244, 245, which were noted in connection with Figure 2 are performed on the assembly of Figure 6 to securely bond the inner and outer rings 22, 24 to the static blade units 26.
  • the circumferential welds can be interrupted at the joint line J between the upper and lower halves of the diaphragm.
  • the circumferential welds can be continuous over the joint lines, the weld bead being subsequently machined away at the joint line to enable separation of the upper and lower halves of the diaphragm from each other.
  • the final steps of the diaphragm fabrication process are to attach the radially outer wall 243 of the outer ring 24 to the side walls 241, 242, and to attach the radially inner wall 223 of the inner ring 22 to the side walls 221, 222, using circumferential welds 224, 225 and 246, 247 as indicated in Figure 2 . It will be evident that these welds may be interrupted if necessary to take account of the joints between the upper and lower half-rings and any sections of the outer wall 243 divided from each other by the ribs 30, for the reasons explained below.
  • the radially inner wall 223 may be attached to the hollow inner ring 22 before the inner platforms 261 of blade units 26 are attached to the side walls 221, 222 of the inner ring.
  • the radially outer wall 243 may be attached to the hollow outer ring 24 either before or after the side walls 241, 242 of the outer ring 24 are attached to the outer platforms 262 of blade units 26.
  • the radially inner wall 223 of the inner ring is continuous over the entire circumferential extent of each of the upper and lower half-rings 22U, 22L, whereas the radially outer wall 243 is discontinuous, being divided into a plurality of separate circumferentially extending sections by radial outward projections of the reinforcing ribs 30.
  • the ribs 30 project radially beyond the radial extent of the side walls 241, 242, the ribs do not extend all the way through the radial thickness of the sections of the radially outer wall 243, thereby creating rectangular recesses in the radially outer wall 243.
  • recesses may aid the addition of features to facilitate handling of the assembled diaphragm, in that threaded holes (not shown) may be drilled in the exposed ends of ribs 30 to accommodate crane lifting eyes.
  • the recesses may be used to enable engagement of the outer ring 24 with correspondingly projecting anti-rotation keys and/or cross-key location features in the turbine casing (not shown) that surrounds it in the fully assembled turbine.
  • the outer wall 243 may be divided by a plurality of the ribs 30, it should be understood that the number of ribs 30 selected to project beyond the radial extent of the walls 241, 242 is at the option of the designer. For example, a single rib projecting at top dead centre, in conjunction with a complementary feature in the turbine casing, would be sufficient to create an anti-rotation feature for the diaphragm.
  • a rib 301 has a radially outer edge surface that is flush with the radially outer edge surfaces of the side walls, so that an unbroken section of the outer wall 243 can be welded into place over the rib 301, see Figure 3 .
  • all the ribs 30 in the outer ring 24 could be like rib 301, so that the radially outer wall 243 would not be divided into sections, except by the joint blocks 32L, 34L and 32U, 34U. Any required lifting or location features could then be machined into or welded onto the outer wall 243.
  • a diaphragm in which only one of the rings would be a hollow box structure, the other ring being of a solid construction.
  • the inner diaphragm ring is a hollow box structure, it could be fabricated and assembled on the jig as described above, complete with the static blade units, and the two halves of the solid outer ring could be joined together and shrunk onto the outer platforms of the blade units, followed by welding as appropriate.
  • the two halves of the solid inner diaphragm ring could be assembled onto the jig and the inner platforms of the blade units could be tack welded onto the inner solid ring.
  • the outer ring could be manufactured as described previously and could then be shrunk onto the outer platforms of the blade units and welded as appropriate.
  • the diaphragm Following fabrication of the diaphragm as described above, it is necessary for it to undergo a stress-relieving heat-treatment and final machining procedures, e.g., machining of the recess 228 in the inner wall 223 of the inner ring 22, see Figure 2 .
  • the diaphragm can then be split into its upper and lower halves, ready for assembly into a turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12160555.4A 2012-03-21 2012-03-21 Turbinenleitapparat Withdrawn EP2642079A1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP12160555.4A EP2642079A1 (de) 2012-03-21 2012-03-21 Turbinenleitapparat
JP2013058651A JP2013194742A (ja) 2012-03-21 2013-03-21 タービンダイアフラム構成
CN2013100913316A CN103321694A (zh) 2012-03-21 2013-03-21 涡轮隔板结构
US13/848,199 US20140322007A1 (en) 2012-03-21 2013-03-21 Turbine diaphragm construction

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12160555.4A EP2642079A1 (de) 2012-03-21 2012-03-21 Turbinenleitapparat

Publications (1)

Publication Number Publication Date
EP2642079A1 true EP2642079A1 (de) 2013-09-25

Family

ID=45939140

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12160555.4A Withdrawn EP2642079A1 (de) 2012-03-21 2012-03-21 Turbinenleitapparat

Country Status (4)

Country Link
US (1) US20140322007A1 (de)
EP (1) EP2642079A1 (de)
JP (1) JP2013194742A (de)
CN (1) CN103321694A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105612312A (zh) * 2013-10-10 2016-05-25 西门子股份公司 涡轮叶片和燃气涡轮

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104481606B (zh) * 2014-11-25 2016-02-17 东方电气集团东方汽轮机有限公司 一种试验用汽轮机隔板
CN106321169B (zh) * 2015-06-29 2018-01-12 上海汽轮机厂有限公司 中低压合缸用的隔板
KR101958110B1 (ko) * 2017-09-20 2019-03-13 두산중공업 주식회사 터빈 스테이터, 터빈 및 이를 포함하는 가스터빈
CN108999652B (zh) * 2018-07-11 2019-09-24 中国航发沈阳发动机研究所 一种对开机匣与静子叶片周向止动结构
BE1027992B1 (fr) * 2020-01-15 2021-08-17 Safran Aero Boosters Méthode et ensemble pour la sélection d’un jeu d’aubes

Citations (6)

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Publication number Priority date Publication date Assignee Title
FR975095A (fr) * 1942-01-29 1951-03-01 & Chantiers De Bretagne Atel Mode de construction d'ailetage fixe pour turbines à vapeur ou à gaz et compresseurs rotatifs
JPS5958103A (ja) * 1982-09-28 1984-04-03 Toshiba Corp 蒸気タ−ビンノズル
JPH06101411A (ja) * 1992-09-22 1994-04-12 Toshiba Corp 蒸気タービンノズルダイヤフラムの製造方法
JPH11303604A (ja) * 1998-04-24 1999-11-02 Toshiba Corp タービンノズル
JP2004124751A (ja) * 2002-09-30 2004-04-22 Toshiba Corp 蒸気タービンの湿分分離装置
EP2339120A1 (de) * 2009-12-22 2011-06-29 Techspace Aero S.A. Leitschaufelstufe einer Strömungsmaschine und zugehöriger Verdichter

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US2247387A (en) * 1940-01-25 1941-07-01 Gen Electric Elastic fluid turbine diaphragm supporting and centering arrangement
US2377611A (en) * 1941-03-01 1945-06-05 William E Caldwell Turbine
US2417486A (en) * 1943-02-19 1947-03-18 Allis Chalmers Mfg Co Nozzle construction
GB0505978D0 (en) * 2005-03-24 2005-04-27 Alstom Technology Ltd Interlocking turbine blades
GB0700633D0 (en) * 2007-01-12 2007-02-21 Alstom Technology Ltd Turbomachine
JP4884410B2 (ja) * 2008-03-04 2012-02-29 株式会社日立製作所 二軸ガスタービン

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR975095A (fr) * 1942-01-29 1951-03-01 & Chantiers De Bretagne Atel Mode de construction d'ailetage fixe pour turbines à vapeur ou à gaz et compresseurs rotatifs
JPS5958103A (ja) * 1982-09-28 1984-04-03 Toshiba Corp 蒸気タ−ビンノズル
JPH06101411A (ja) * 1992-09-22 1994-04-12 Toshiba Corp 蒸気タービンノズルダイヤフラムの製造方法
JPH11303604A (ja) * 1998-04-24 1999-11-02 Toshiba Corp タービンノズル
JP2004124751A (ja) * 2002-09-30 2004-04-22 Toshiba Corp 蒸気タービンの湿分分離装置
EP2339120A1 (de) * 2009-12-22 2011-06-29 Techspace Aero S.A. Leitschaufelstufe einer Strömungsmaschine und zugehöriger Verdichter

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105612312A (zh) * 2013-10-10 2016-05-25 西门子股份公司 涡轮叶片和燃气涡轮
CN105612312B (zh) * 2013-10-10 2017-12-15 西门子股份公司 涡轮叶片和燃气涡轮

Also Published As

Publication number Publication date
CN103321694A (zh) 2013-09-25
US20140322007A1 (en) 2014-10-30
JP2013194742A (ja) 2013-09-30

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Effective date: 20131024