EP1247937B1 - Aube de turbine à gaz et turbine à gaz - Google Patents

Aube de turbine à gaz et turbine à gaz Download PDF

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Publication number
EP1247937B1
EP1247937B1 EP01108477A EP01108477A EP1247937B1 EP 1247937 B1 EP1247937 B1 EP 1247937B1 EP 01108477 A EP01108477 A EP 01108477A EP 01108477 A EP01108477 A EP 01108477A EP 1247937 B1 EP1247937 B1 EP 1247937B1
Authority
EP
European Patent Office
Prior art keywords
turbine
turbine blade
airfoil profile
platforms
longitudinal axis
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.)
Expired - Lifetime
Application number
EP01108477A
Other languages
German (de)
English (en)
Other versions
EP1247937A1 (fr
Inventor
Michael Haendler
Peter Tiemann
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 DE50106970T priority Critical patent/DE50106970D1/de
Priority to ES01108477T priority patent/ES2243358T3/es
Priority to EP01108477A priority patent/EP1247937B1/fr
Priority to JP2002098226A priority patent/JP2002357102A/ja
Priority to CNB021085943A priority patent/CN100366865C/zh
Priority to US10/117,590 priority patent/US20020157250A1/en
Publication of EP1247937A1 publication Critical patent/EP1247937A1/fr
Application granted granted Critical
Publication of EP1247937B1 publication Critical patent/EP1247937B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • 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
    • Y10T29/49336—Blade making

Definitions

  • the present invention relates to a turbine blade, in particular for a gas turbine, with a wing profile and two disposed at opposite ends of the airfoil profile Platforms for attachment to a parent Component. It further relates to a turbine using such a turbine blade.
  • Such turbine blades and casting process for their preparation are for example from US 5,599,166 and US 5,820,774 known.
  • the in the known turbine blades provided platform protrudes in the circumferential direction of the turbine from both sides of the airfoil profile. It is vertical to a longitudinal axis of the airfoil profile.
  • their platforms each obliquely to the longitudinal axis of the airfoil profile extend.
  • the well-known turbine blades are in the course of the increase of performance and efficiency as well as emission reduction the thermal and mechanical boundary conditions not more grown. It will therefore be a change in the material structure to the effect that the turbine blade from a single, continuous crystal exists. To the growth To achieve such a single crystal must be certain Be met requirements, such as a defined Solidification temperature. A sudden change in the solidification cross section and / or the solidification direction must avoided as far as possible.
  • Object of the present invention is therefore to provide a turbine blade to provide that due to their particular Construction simpler and with much less waste may be formed as a single crystal so far.
  • this object is achieved with a turbine blade of the type mentioned solved in that both platforms only an obtuse angle with a longitudinal axis of the airfoil profile.
  • the platforms preferably protrude in the circumferential direction.
  • One of the platforms is here as a foot plate and the other as a top plate designated.
  • the first platform then serves for attachment to a housing or rotor of the turbine and to the cover the gap between two turbine blades. through the second platform becomes the ends of the wing profiles connected with each other.
  • the at least one platform is straight or partially or fully bent formed. Between Platforms of adjacent turbine blades can be a gentler or angled transition. Thus, a optimal adaptation to the respective boundary conditions achieved.
  • the platforms can only work in a transition area be bent to the wing profile and the rest substantially just lost. By this configuration is as uniform a cross section as possible with only minimal losses allows.
  • the projecting Platform s off to both sides of the airfoil profile.
  • she can be symmetrical to the longitudinal axis of the airfoil profile to be ordered.
  • the longitudinal axis can then as in known Constructions by a rotation axis of a rotor of the turbine run.
  • the solidification can either be at a free end of the Starting wing profiles and then to the end continue the platform. Alternatively, the solidification can Start a free end of the platform and then over the wing profile up to the free end of an optionally expire provided second platform. Using only one platform thus only changes the Solidification direction. This design allows thus a simpler design of the turbine blade than Single crystal.
  • the turbine blade according to the invention can in particular as Guide vane are formed.
  • the use of vanes in the form of a single crystal allows a reduction the wall thickness of the vanes. By this reduction may be the consumption of a cooling medium used for cooling be lowered.
  • the invention further relates to a turbine, in particular a Gas turbine with a housing and a housed in the housing Rotor and several turbine blades described above according to the second embodiment.
  • a turbine in particular a Gas turbine with a housing and a housed in the housing Rotor and several turbine blades described above according to the second embodiment.
  • the invention extends a longitudinal axis of the airfoil profile of each turbine blade spaced from a rotation axis of the rotor.
  • the Turbine blades are thus no longer parallel to the radius arranged the turbine. Rather, the longitudinal axis of the Airfoil profile of each turbine blade with a radius of Turbine an angle whose size is advantageous between 8 and 18 degrees. The size of the angle depends on the extent of the Inclination of the at least one platform relative to the Longitudinal axis of the airfoil profile.
  • FIG. 1 shows a schematic longitudinal section through a gas turbine 10 with a housing 11 and a rotor 12.
  • the housing 11 is with vanes 13 and the rotor 12 with blades 14 provided.
  • the gas turbine 10 is in the arrow direction 15 flows through hot gas, which leads to a rotation of the Rotor 12 leads around its axis of rotation 16 in the direction of arrow 17.
  • FIGS. 2 and 3 show an embodiment according to the state of the technique.
  • each Guide vane A has a foot plate B for attachment to the housing 11 and for covering the distance between two vanes A, a top plate C and an intermediate one Wing profile D on.
  • a longitudinal axis E of the airfoil profile passes through the axis of rotation 16 of the rotor 12.
  • the foot and head plates B, C protrude from the airfoil profile D, respectively Inclusion of a right angle F.
  • dashed lines G, H of the foot plates B and head plates C formed circles indicated.
  • the solidification direction during casting of the known vane A. is shown schematically in FIG. Starting from the Rotor 12 facing the end of the vane A must first Solidify top plate C. There is a change in the direction of solidification up 180 degrees. Then the changes Solidification direction again by 90 degrees in the formation of the Wing profile D. During the transition to the top plate B must the solidification in the circumferential direction to the left and right split with the inclusion of a right angle.
  • An education the known vane A as a single crystal is therefore can only be achieved through costly measures. Even if There is a very high rate of rejects.
  • FIGS. 5 to 7 show a guide vane according to the invention 13 and a turbine construction according to the invention in more detail shown. As in the prior art, several are even Distributed over the circumference of the gas turbine 10 vanes 13 provided. Each vane 13 has a foot plate 18, a top plate 19 and an intermediate airfoil profile 20 with a longitudinal axis 21. The longitudinal axis 21 is spaced from the axis of rotation 16 of the rotor 12. Sie closes with a radius 27 an angle 26, which in the illustrated Embodiment is about 8 degrees.
  • Both the foot plate 18 and the top plate 19 protrude into Circumferential direction only to one side of the airfoil profile 20th from.
  • the foot plate 18 protrudes in the representation according to Figure 6 to the left and the top plate 19 to the opposite Page off, so to the right.
  • Both plates 18, 19 close with the longitudinal axis 21 of the airfoil 20 each obtuse angles 22, 23.
  • the of the foot plates 18 and the Head plates 19 formed circles are again schematic shown with dashed lines 24, 25.
  • Both the foot plate 18 and the top plate 19 are sufficient directly to the airfoil 20 of each adjacent Guide vane 13. Their free ends are similar in shape customized. You can at the adjacent airfoil profile 20 anchored directly.
  • the Plates 18, 19 are formed to some extent deformable. The maximum allowable deformation is determined by a suitable, limited stop not shown.
  • the base plate 18 is in the illustrated embodiment the suction side of the airfoil 20 and the top plate 19th arranged on the pressure side.
  • the solidification direction of the guide vane 13 according to the invention is shown schematically in FIG. Abrupt, right-angled Changes in the solidification direction occur due to the inventive blade construction no longer on. It is likewise no splitting of the solidification direction as with required the known blades.
  • the inventive Guide blade 13 can thus easily and inexpensively with essential reduced reject rates formed as a single crystal become. It is then both thermally and mechanically significantly more resilient than the known blades.
  • Figures 8 and 9 show two further embodiments of the invention in a view similar to Figure 5.
  • Guide vanes 33 are shown, each having a foot platform 38a, 38b and a head platform 39a, 39b. Both platforms 38a, 38b, 39a, 39b project to both sides of the airfoil 20 and are symmetrical to the longitudinal axis 21 arranged.
  • the platforms 38a, 38b, 39a, 39b are bent formed.
  • the abutting portions 38a, 38b are gently merging. They close each one an obtuse angle 22, 23 with the longitudinal axis 21 a.
  • FIG. 9 shows a further embodiment.
  • vanes 43 With these vanes 43 are also curved platforms 48a, 48b, 49a, 49b provided. Between sections 48a, 48b, 49a, 49b of a vane 43 are each straight transition areas 50, 51 arranged.
  • the individual sections 48a, 49a in turn each include an obtuse angle 22, 23 with the longitudinal axis 21 a. Due to the symmetrical as in Figure 8 Arrangement results for sections 48b, 49b the same Angles 22, 23. As in FIG. 8, the longitudinal axes 21 intersect the axis of rotation 16.
  • FIG. 10 and 11 a third embodiment of a Guide vane 43 shown.
  • the platforms 48a, 48b, 49a, 49b have a first, bent portion 52a, 52b and a another, substantially straight region 53a, 53b on.
  • the transition between the areas 52a, 53a, respectively 52b, 53b is shown schematically by the dashed line 54 in FIG Figure 11 shown.
  • the curvature of the region 53a, 53b is smaller than that of the Area 52a, 52b. It is advantageously chosen so that the Area 53 a, 53 b defines a cylinder portion about the axis of rotation 16. During operation of the turbine 10, therefore, only minimal Gap between the free ends of the blades 14th and the area 53a, 53b. Flow losses on the blades 14 can therefore be reduced to a minimum.
  • the length of the region 52a, 52b is chosen so that the solidification front emerge from the wing profile 20 and can be deflected in the direction of the region 52a, 52b. Following is a renewed change in direction Direction of the area 53a, 53b.
  • the angle 55 of the deflection is like the angles 22, 23 greater than 90 degrees. This change The solidification direction is therefore easy to control.
  • the cross section the areas 52a, 52b, 53a, 53b is about the same, so that only a change in the direction of solidification required is.
  • the present invention avoids a sudden directional and cross section change the solidification direction at the manufacture of the guide vanes 13, 33, 43.
  • the vanes 13, 33, 43 can therefore be much easier than before be formed as a single crystal.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Aube de turbine, notamment pour une turbine (10) à gaz, ayant un profil (20) d'aile portante et deux plateformes (18 ; 19 ; 38 ; 39 ; 48 ; 49) disposées à des extrémités opposées du profil (20) d'aile portante pour la fixation sur un élément (11 ; 12) disposé au-dessus, caractérisée en ce que les deux plateformes (18 ; 19 ; 38 ; 39 ; 48 ; 49) font exclusivement un angle (22 ; 23) obtus avec un axe (21) longitudinal du profil (20) d'aile portante.
  2. Aube de turbine suivant la revendication 1, caractérisée en ce que la au moins une plateforme (38 ; 39 ; 48 ; 49) est rectiligne ou courbée en tout ou partie.
  3. Aube de turbine suivant l'une des revendications 1 à 2, caractérisée en ce que les plateformes (38 ; 39 ; 48 ; 49) font saillie des deux côtés du profil (20) d'aile portante.
  4. Aube de turbine suivant la revendication 3, caractérisée en ce que les plateformes (38 ; 39 ; 48 ; 49) sont disposées symétriquement par rapport à l'axe (21) longitudinal du profil (20) d'aile portante.
  5. Aube de turbine suivant l'une des revendications 1 à 2, caractérisée en ce que la au moins une plateforme (18 ; 19) ne fait saillie que d'un côté du profil (20) d'aile portante.
  6. Aube de turbine suivant la revendication 1 et 5, caractérisée en ce que les plateformes (18 ; 19) font saillie vers des côtés différents, notamment mutuellement opposés, du profil (20) d'aile portante.
  7. Aube de turbine suivant l'une des revendications 1 à 6, caractérisée en ce que l'aube (13 ; 33 ; 43) de turbine est constituée d'un monocristal.
  8. Aube de turbine suivant l'une des revendications 1 à 7, caractérisée en ce que l'aube (13) de turbine est constituée en aube directrice.
  9. Turbine, notamment turbine (10) à gaz, ayant une carcasse (11) et un rotor (12) reçu dans la carcasse (11) ainsi que plusieurs aubes (13) de turbine suivant la revendication 5 ou 6, caractérisée en ce qu'un axe (21) longitudinal du profil (20) d'aile portante de chaque aube (13) de turbine s'étend à distance d'un axe (16) de rotation du rotor (12).
  10. Turbine suivant la revendication 9, caractérisée en ce que l'axe (21) longitudinal du profil (20) d'aile portante de chaque aube (13) de turbine fait un angle (26) de 8 à 18° degrés avec un rayon (27) de la turbine (10).
EP01108477A 2001-04-04 2001-04-04 Aube de turbine à gaz et turbine à gaz Expired - Lifetime EP1247937B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
DE50106970T DE50106970D1 (de) 2001-04-04 2001-04-04 Turbinenschaufel und Turbine
ES01108477T ES2243358T3 (es) 2001-04-04 2001-04-04 Turbina y alabe de turbina.
EP01108477A EP1247937B1 (fr) 2001-04-04 2001-04-04 Aube de turbine à gaz et turbine à gaz
JP2002098226A JP2002357102A (ja) 2001-04-04 2002-04-01 タービン翼およびタービン
CNB021085943A CN100366865C (zh) 2001-04-04 2002-04-04 涡轮叶片和涡轮机
US10/117,590 US20020157250A1 (en) 2001-04-04 2002-04-04 Turbine blade and turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01108477A EP1247937B1 (fr) 2001-04-04 2001-04-04 Aube de turbine à gaz et turbine à gaz

Publications (2)

Publication Number Publication Date
EP1247937A1 EP1247937A1 (fr) 2002-10-09
EP1247937B1 true EP1247937B1 (fr) 2005-08-03

Family

ID=8177045

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01108477A Expired - Lifetime EP1247937B1 (fr) 2001-04-04 2001-04-04 Aube de turbine à gaz et turbine à gaz

Country Status (6)

Country Link
US (1) US20020157250A1 (fr)
EP (1) EP1247937B1 (fr)
JP (1) JP2002357102A (fr)
CN (1) CN100366865C (fr)
DE (1) DE50106970D1 (fr)
ES (1) ES2243358T3 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6854960B2 (en) * 2002-06-24 2005-02-15 Electric Boat Corporation Segmented composite impeller/propeller arrangement and manufacturing method
US8434543B2 (en) 2009-07-09 2013-05-07 Honeywell International Inc. Method of making turbine stator airfoils with individual orientations
US8894365B2 (en) * 2011-06-29 2014-11-25 United Technologies Corporation Flowpath insert and assembly
ITCO20130067A1 (it) * 2013-12-17 2015-06-18 Nuovo Pignone Srl Girante con elementi di protezione e compressore centrifugo
FR3014942B1 (fr) 2013-12-18 2016-01-08 Snecma Aube, roue a aubes et turbomachine ; procede de fabrication de l'aube
CN104454027B (zh) * 2014-10-31 2016-01-06 中国南方航空工业(集团)有限公司 动力涡轮导向器的加工方法
CN113513368B (zh) * 2021-07-08 2022-09-02 哈尔滨工程大学 一种带有子母动叶片结构的可直接倒车涡轮

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US984812A (en) * 1910-01-15 1911-02-21 John W Hearst Propeller-wheel for airships.
GB712589A (en) * 1950-03-03 1954-07-28 Rolls Royce Improvements in or relating to guide vane assemblies in annular fluid ducts
US2962260A (en) * 1954-12-13 1960-11-29 United Aircraft Corp Sweep back in blading
US3749518A (en) * 1972-03-15 1973-07-31 United Aircraft Corp Composite blade root configuration
US3745629A (en) * 1972-04-12 1973-07-17 Secr Defence Method of determining optimal shapes for stator blades
US4826400A (en) * 1986-12-29 1989-05-02 General Electric Company Curvilinear turbine airfoil
US5061154A (en) * 1989-12-11 1991-10-29 Allied-Signal Inc. Radial turbine rotor with improved saddle life
US5292385A (en) * 1991-12-18 1994-03-08 Alliedsignal Inc. Turbine rotor having improved rim durability
US5599166A (en) 1994-11-01 1997-02-04 United Technologies Corporation Core for fabrication of gas turbine engine airfoils
US5716192A (en) * 1996-09-13 1998-02-10 United Technologies Corporation Cooling duct turn geometry for bowed airfoil
US5820774A (en) 1996-10-28 1998-10-13 United Technologies Corporation Ceramic core for casting a turbine blade

Also Published As

Publication number Publication date
JP2002357102A (ja) 2002-12-13
US20020157250A1 (en) 2002-10-31
CN1379165A (zh) 2002-11-13
DE50106970D1 (de) 2005-09-08
CN100366865C (zh) 2008-02-06
EP1247937A1 (fr) 2002-10-09
ES2243358T3 (es) 2005-12-01

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