EP1247937B1 - Gas turbine blade and gas turbine - Google Patents

Gas turbine blade and gas turbine 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
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German (de)
French (fr)
Other versions
EP1247937A1 (en
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
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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 EP01108477A priority Critical patent/EP1247937B1/en
Priority to ES01108477T priority patent/ES2243358T3/en
Priority to DE50106970T priority patent/DE50106970D1/en
Priority to JP2002098226A priority patent/JP2002357102A/en
Priority to CNB021085943A priority patent/CN100366865C/en
Priority to US10/117,590 priority patent/US20020157250A1/en
Publication of EP1247937A1 publication Critical patent/EP1247937A1/en
Application granted granted Critical
Publication of EP1247937B1 publication Critical patent/EP1247937B1/en
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)
  • Ceramic Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die vorliegende Erfindung betrifft eine Turbinenschaufel, insbesondere für eine Gasturbine, mit einem Tragflügelprofil und zwei an entgegengesetzten Enden des Tragflügelprofils angeordneten Plattformen zur Befestigung an einem übergeordneten Bauteil. Sie betrifft weiter eine Turbine unter Verwendung einer derartigen Turbinenschaufel.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.

Derartige Turbinenschaufeln und Gußverfahren zu ihrer Herstellung sind beispielsweise aus der US 5,599,166 und der US 5,820,774 bekannt. Die bei den bekannten Turbinenschaufeln vorgesehene Plattform ragt in Umfangsrichtung der Turbine nach beiden Seiten des Tragflügelprofils ab. Sie steht senkrecht zu einer Längsachse des Tragflügelprofils. Zudem sind aus der GB 712,523 Turbinenschaufeln bekannt, deren Plattformen sich jeweils schräg zur Längsachse des Tragflügelprofils erstrecken.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. In addition are From the GB 712,523 turbine blades known, their platforms each obliquely to the longitudinal axis of the airfoil profile extend.

Die bekannten Turbinenschaufeln sind im Zuge der Steigerung von Leistungen und Wirkungsgrad sowie Verringerung der Emission den thermischen und mechanischen Randbedingungen nicht mehr gewachsen. Es wird daher ein Wechsel der Materialstruktur dahingehend angestrebt, daß die Turbinenschaufel aus einem einzigen, durchgehenden Kristall besteht. Um das Wachstum eines derartigen Einkristalls zu erreichen, müssen bestimmte Anforderungen erfüllt sein, wie beispielsweise eine definierte Erstarrungstemperatur. Eine plötzliche Änderung des Erstarrungsquerschnitts und/oder der Erstarrungsrichtung müssen möglichst vermieden werden.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.

Bei den bekannten Turbinenschaufeln gestaltet sich daher auf Grund der Änderung im Erstarrungsquerschnitt und der Erstarrungsrichtung insbesondere im Übergang von der Plattform zum Tragflügelprofil die Erzeugung eines Einkristalls sehr schwierig. Die Gußform muß stellenweise beheizt beziehungsweise gekühlt werden. Alternativ oder zusätzlich müssen Kornbeihalter vorgesehen werden. Die Auswirkungen beider Möglichkeiten lassen sich nur schwer vorhersehen und unterliegen zudem Schwankungen im Guß- und Erstarrungsvorgang. Die Ausschußrate steigt daher stark an.In the known turbine blades is therefore on Reason for the change in the solidification cross section and the solidification direction especially in the transition from the platform to Wing profile the generation of a single crystal very difficult. The mold must be heated in places or be cooled. Alternatively or additionally Kornbeihalter must be provided. The effects of both possibilities are difficult to predict and subject to Fluctuations in the casting and solidification process. The reject rate therefore rises strongly.

Aufgabe der vorliegenden Erfindung ist es daher, eine Turbinenschaufel bereitzustellen, die auf Grund ihrer besonderen Konstruktion einfacher und mit wesentlich geringerem Ausschuß als bisher als Einkristall ausgebildet sein kann.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.

Erfindungsgemäß wird diese Aufgabe bei einer Turbinenschaufel der eingangs genannten Art dadurch gelöst, daß beide Plattformen ausschließlich einen stumpfen Winkel mit einer Längsachse des Tragflügelprofils einschließen.According to the invention, 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.

Die Erstarrungsrichtung muß daher nicht mehr wie bei den bekannten Schaufeln schlagartig um 90 Grad geändert werden. Erfindungsgemäß ist nur eine Umlenkung um einen Winkel erforderlich, der kleiner als 90 Grad ist. Hierdurch wird die Ausbildung der Turbinenschaufel als Einkristall nochmals unterstützt. Es bietet sich selbstverständlich an, die Turbinenschaufel dann auch als Einkristall auszubilden.The solidification direction must therefore no longer as in the known Shovels are suddenly changed by 90 degrees. According to the invention is only a deflection by an angle required which is less than 90 degrees. This will be the training the turbine blade as a single crystal again supported. It goes without saying, the turbine blade then also form as a single crystal.

Die Plattformen ragen bevorzugt im Umfangsrichtung ab.The platforms preferably protrude in the circumferential direction.

Es sind zwei Plattformen vorgesehen, die an entgegengesetzten Enden des Tragflügelprofils angeordnet sind. Eine der Plattformen wird hierbei als Fußplatte und die andere als Kopfplatte bezeichnet. Die erste Plattform dient dann zur Befestigung an einem Gehäuse oder Rotor der Turbine und zur Abdeckung des Zwischenraums zwischen zwei Turbinenschaufeln. Mittels der zweiten Plattform werden die Enden der Tragflügelprofile miteinander verbunden. There are two platforms on opposite sides Ends of the airfoil are arranged. 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.

Vorteilhaft ist die mindestens eine Plattform gerade oder teilweise oder vollständig gebogen ausgebildet. Zwischen den Plattformen benachbarter Turbinenschaufeln kann ein sanfter oder winkliger Übergang vorgesehen werden. Somit wird eine optimale Anpassung an die jeweiligen Randbedingungen erreicht. Die Plattformen können nur in einem Übergangsbereich zu dem Tragflügelprofil gebogen sein und im übrigen im wesentlichen gerade verlaufen. Durch diese Ausgestaltung wird ein möglichst gleichmäßiger Querschnitt mit nur geringen Verlusten ermöglicht.Advantageously, 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.

Gemäß einer ersten vorteilhaften Ausgestaltung ragen die Plattformen nach beiden Seiten des Tragflügelprofils ab. Sie können symmetrisch zu der Längsachse des Tragflügelprofils angeordnet werden. Die Längsachse kann dann wie bei bekannten Konstruktionen durch eine Drehachse eines Rotors der Turbine verlaufen.According to a first advantageous embodiment, the projecting Platforms 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.

Gemäß einer zweiten vorteilhaften Ausgestaltung ragt die mindestens eine Plattform nur nach einer Seite des Tragflügelprofils ab. Durch das nur einseitige Abragen der Plattform wird eine mehrfache Änderung der Erstarrungsrichtung vermieden. Die Erstarrung kann entweder an einem freien Ende des Tragflügelprofils beginnen und sich anschließend bis zum Ende der Plattform fortsetzen. Alternativ kann die Erstarrung an einem freien Ende der Plattform beginnen und anschließend über das Tragflügelprofil bis hin zum freien Ende einer gegebenenfalls vorgesehenen zweiten Plattform ablaufen. Bei Verwendung nur einer Plattform tritt somit nur eine Änderung der Erstarrungsrichtung auf. Auch diese Ausgestaltung ermöglicht somit eine einfachere Ausbildung der Turbinenschaufel als Einkristall.According to a second advantageous embodiment, the at least a platform only to one side of the wing profile from. Due to the only one-sided projection of the platform a multiple change of the solidification direction is avoided. 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.

Bei dieser Ausgestaltung können bei Verwendung von zwei Plattformen an entgegengesetzten Enden des Tragflügelprofils diese nach unterschiedlichen, insbesondere einander entgegengesetzten Seiten des Tragflügelprofils abragen. In Umfangsrichtung ragt dann beispielsweise die Fußplatte nach links und die Kopfplatte nach rechts ab. Diese Konstruktion verringert Hinterschneidungen und vereinfacht somit die Herstellung. Die angestrebte Ausbildung der Turbinenschaufel als Einkristall wird durch das Abragen nach unterschiedlichen Seiten vorteilhaft unterstützt, da eine Umkehrung der Erstarrungsrichtung nicht erforderlich ist.In this embodiment, when using two Platforms at opposite ends of the airfoil profile these according to different, in particular opposite Protruding sides of the airfoil profile. In the circumferential direction then, for example, the foot plate protrudes to the left and the top plate to the right. This construction reduces Undercuts and thus simplifies the production. The desired training of the turbine blade as Single crystal becomes different by the protrusion Pages favorably supported, as a reversal of the solidification direction is not required.

Die erfindungsgemäße Turbinenschaufel kann insbesondere als Leitschaufel ausgebildet werden. Die Verwendung von Leitschaufeln in Form eines Einkristalls ermöglicht eine Verringerung der Wandstärke der Leitschaufeln. Durch diese Verringerung kann der Verbrauch eines zur Kühlung verwendeten Kühlmediums gesenkt werden.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.

Die Erfindung betrifft weiter eine Turbine, insbesondere eine Gasturbine mit einem Gehäuse und einem in dem Gehäuse aufgenommenen Rotor sowie mehreren oben beschriebenen Turbinenschaufeln gemäß der zweiten Ausgestaltung. Erfindungsgemäß verläuft eine Längsachse des Tragflügelprofils jeder Turbinenschaufel beabstandet zu einer Drehachse des Rotors. Die Turbinenschaufeln werden somit nicht mehr parallel zum Radius der Turbine angeordnet. Vielmehr schließt die Längsachse des Tragflügelprofils jeder Turbinenschaufel mit einem Radius der Turbine einen Winkel ein, dessen Größe vorteilhaft zwischen 8 und 18 Grad liegt. Die Größe des Winkels hängt vom Ausmaß der Schrägstellung der mindestens einen Plattform gegenüber der Längsachse des Tragflügelprofils ab.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. According to 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.

Nachstehend wird die Erfindung an Hand von Ausführungsbeispielen näher erläutert, die in schematischer Weise in der Zeichnung dargestellt sind. Dabei zeigt:

  • Figur 1 einen schematischen Längsschnitt durch eine Turbine;
  • Figur 2 einen Schnitt längs der Linie II-II in Figur 1 bei einer Turbine gemäß dem Stand der Technik;
  • Figur 3 eine Darstellung einer einzelnen Turbinenschaufel gemäß dem Stand der Technik;
  • Figur 4 eine schematische Darstellung der Erstarrungsrichtung bei einer Turbinenschaufel gemäß dem Stand der Technik; die Figuren 5 bis 7 Ansichten entsprechend den Figuren 2 bis 4 bei einer erfindungsgemäßen Turbinenschaufel; die Figuren 8 und 10 weitere Ausführungsbeispiele der Erfindung in einer Ansicht ähnlich Figur 5; und
  • Figur 11 eine Ansicht einer Turbinenschaufel gemäß Pfeilrichtung XI in Figur 10.
    • The invention will be explained in more detail below with reference to exemplary embodiments, which are shown schematically in the drawing. Showing:
  • Figure 1 is a schematic longitudinal section through a turbine;
  • Figure 2 is a section along the line II-II in Figure 1 in a turbine according to the prior art;
  • Figure 3 is an illustration of a single turbine blade according to the prior art;
  • Figure 4 is a schematic representation of the solidification direction in a turbine blade according to the prior art; Figures 5 to 7 are views corresponding to Figures 2 to 4 in a turbine blade according to the invention; Figures 8 and 10 show further embodiments of the invention in a view similar to Figure 5; and
  • FIG. 11 shows a view of a turbine blade according to arrow direction XI in FIG. 10.

    • Figur 1 zeigt einen schematischen Längsschnitt durch eine Gasturbine 10 mit einem Gehäuse 11 und einen Rotor 12. Das Gehäuse 11 ist mit Leitschaufeln 13 und der Rotor 12 mit Laufschaufeln 14 versehen. Die Gasturbine 10 wird in Pfeilrichtung 15 von heißem Gas durchströmt, das zu einer Drehung des Rotors 12 um seine Drehachse 16 in Pfeilrichtung 17 führt.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.

    Die Figuren 2 bis 4 zeigen eine Ausgestaltung gemäß dem Stand der Technik. Wie sich insbesondere aus den Figuren 2 und 3 ergibt, sind mehrere Leitschaufeln A vorgesehen, die gleichmäßig über den Umfang der Gasturbine 10 verteilt sind. Jede Leitschaufel A weist eine Fußplatte B zur Befestigung am Gehäuse 11 und zum Überdecken des Abstands zwischen zwei Leitschaufeln A, eine Kopfplatte C sowie ein dazwischenliegendes Tragflügelprofil D auf. Eine Längsachse E des Tragflügelprofils verläuft durch die Drehachse 16 des Rotors 12. Die Fuß- und Kopfplatten B, C ragen von dem Tragflügelprofil D jeweils unter Einschluß eines rechten Winkels F ab. Zur Erläuterung sind schematisch mit Strichpunktlinien G, H die von den Fußplatten B und Kopfplatten C gebildeten Kreise angedeutet.Figures 2 to 4 show an embodiment according to the state of the technique. As can be seen in particular from FIGS. 2 and 3 results, several vanes A are provided, the uniform are distributed over the circumference of the gas turbine 10. 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. For explanation are schematically with dashed lines G, H of the foot plates B and head plates C formed circles indicated.

    Die Erstarrungsrichtung beim Guß der bekannten Leitschaufel A ist schematisch in Figur 4 dargestellt. Ausgehend von dem dem Rotor 12 zugewandten Ende der Leitschaufel A muß zunächst die Kopfplatte C erstarren. Es tritt hierbei ein Wechsel der Erstarrungsrichtung um 180 Grad auf. Anschließend wechselt die Erstarrungsrichtung erneut um 90 Grad bei der Ausbildung des Tragflügelprofils D. Beim Übergang in die Kopfplatte B muß sich die Erstarrung in Umfangsrichtung nach links und rechts unter Einschluß eines rechten Winkels aufspalten. Eine Ausbildung der bekannten Leitschaufel A als Einkristall ist daher nur durch aufwendige Maßnahmen zu erreichen. Selbst dann liegt eine sehr hohe Ausschußquote vor.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.

    In den Figuren 5 bis 7 sind eine erfindungsgemäße Leitschaufel 13 und eine erfindungsgemäße Turbinenkonstruktion näher dargestellt. Wie beim Stand der Technik sind mehrere, gleichmäßig über den Umfang der Gasturbine 10 verteilte Leitschaufeln 13 vorgesehen. Jede Leitschaufel 13 weist eine Fußplatte 18, eine Kopfplatte 19 und ein dazwischen liegendes Tragflügelprofil 20 mit einer Längsachse 21 auf. Die Längsachse 21 verläuft beabstandet zu der Drehachse 16 des Rotors 12. Sie schließt mit einem Radius 27 einen Winkel 26 ein, der im dargestellten Ausführungsbeispiel bei etwa 8 Grad liegt.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.

    Sowohl die Fußplatte 18 als auch die Kopfplatte 19 ragen in Umfangsrichtung nur nach einer Seite des Tragflügelprofils 20 ab. Die Fußplatte 18 ragt hierbei in der Darstellung gemäß Figur 6 nach links und die Kopfplatte 19 zur entgegengesetzten Seite ab, also nach rechts. Beide Platten 18, 19 schließen mit der Längsachse 21 des Tragflügelprofils 20 jeweils stumpfe Winkel 22, 23 ein. Die von den Fußplatten 18 und den Kopfplatten 19 gebildeten Kreise sind wiederum schematisch mit Strichpunktlinien 24, 25 dargestellt.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.

    Sowohl die Fußplatte 18 als auch die Kopfplatte 19 reichen direkt bis zum Tragflügelprofil 20 der jeweils benachbarten Leitschaufel 13. Ihre freien Enden sind von der Form her entsprechend angepaßt. Sie können an dem benachbarten Tragflügelprofil 20 direkt verankert werden. Alternativ können die Platten 18, 19 in gewissem Umfang verformbar ausgebildet werden. Die maximal zulässige Verformung wird durch einen geeigneten, nicht näher dargestellten Anschlag begrenzt. 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. Alternatively, the Plates 18, 19 are formed to some extent deformable. The maximum allowable deformation is determined by a suitable, limited stop not shown.

    Die Fußplatte 18 ist im dargestellten Ausführungsbeispiel an der Saugseite des Tragflügelprofils 20 und die Kopfplatte 19 an der Druckseite angeordnet.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.

    Die Erstarrungsrichtung der erfindungsgemäßen Leitschaufel 13 ist schematisch in Figur 7 dargestellt. Abrupte, rechtwinklige Änderungen der Erstarrungsrichtung treten auf Grund der erfindungsgemäßen Schaufelkonstruktion nicht mehr auf. Es ist ebenfalls keine Aufspaltung der Erstarrungsrichtung wie bei den bekannten Schaufeln erforderlich. Die erfindungsgemäße Leitschaufel 13 kann somit einfach und kostengünstig mit wesentlich verringerten Ausschußquoten als Einkristall ausgebildet werden. Sie ist dann sowohl thermisch als auch mechanisch deutlich belastbarer als die bekannten Schaufeln.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.

    Die Figuren 8 und 9 zeigen zwei weitere Ausführungsbeispiele der Erfindung in einer Ansicht ähnlich Figur 5. In Figur 8 sind Leitschaufeln 33 dargestellt, die jeweils eine Fußplattform 38a, 38b und eine Kopfplattform 39a, 39b aufweisen. Beide Plattformen 38a, 38b, 39a, 39b ragen nach beiden Seiten des Tragflügelprofils 20 ab und sind symmetrisch zur Längsachse 21 angeordnet. Die Plattformen 38a, 38b, 39a, 39b sind gebogen ausgebildet. Die aneinander stoßenden Abschnitte 38a, 38b gehen hierbei sanft ineinander über. Sie schließen jeweils einen stumpfen Winkel 22, 23 mit der Längsachse 21 ein.Figures 8 and 9 show two further embodiments of the invention in a view similar to Figure 5. In Figure 8 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.

    Auf Grund der bogenförmigen Ausgestaltung der Plattformen 38a, 38b, 39a, 39b läßt sich ein Abragen unter dem stumpfen Winkel 22, 23 erreichen, obwohl sämtliche Längsachsen 21 die Drehachse 16 des Rotors 12 schneiden.Due to the arched design of the platforms 38a, 38b, 39a, 39b can be a projecting under the blunt Angle 22, 23 reach, although all longitudinal axes 21 the Rotate axis 16 of the rotor 12.

    Figur 9 zeigt eine weitere Ausgestaltung. Bei diesen Leitschaufeln 43 sind ebenfalls gebogene Plattformen 48a, 48b, 49a, 49b vorgesehen. Zwischen den Abschnitten 48a, 48b, 49a, 49b einer Leitschaufel 43 sind jeweils gerade Übergangsbereiche 50, 51 angeordnet. Die einzelnen Abschnitte 48a, 49a schließen wiederum jeweils einen stumpfen Winkel 22, 23 mit der Längsachse 21 ein. Auf Grund der wie in Figur 8 symmetrischen Anordnung ergibt sich für Abschnitte 48b, 49b derselbe Winkel 22, 23. Wie bei Figur 8 schneiden die Längsachsen 21 die Drehachse 16.FIG. 9 shows a further embodiment. 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.

    In den Figuren 10 und 11 ist eine dritte Ausgestaltung einer Leitschaufel 43 dargestellt. Die Plattformen 48a, 48b, 49a, 49b weisen einen ersten, gebogenen Bereich 52a, 52b und einen weiteren, im wesentlichen gerade verlaufenden Bereich 53a, 53b auf. Der Übergang zwischen den Bereichen 52a, 53a beziehungsweise 52b, 53b ist schematisch mit der Strichlinie 54 in Figur 11 dargestellt.In Figures 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.

    Die Krümmung des Bereichs 53a, 53b ist kleiner als die des Bereichs 52a, 52b. Sie wird vorteilhaft so gewählt, daß der Bereich 53a, 53b einen Zylinderabschnitt um die Drehachse 16 definiert. Im Betrieb der Turbine 10 bilden sich daher nur minimale Spalte zwischen den freien Enden der Laufschaufeln 14 und dem Bereich 53a, 53b. Strömungsverluste an den Laufschaufeln 14 vorbei können daher auf ein Minimum reduziert werden.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.

    Die Länge des Bereichs 52a, 52b wird hierbei so gewählt, daß die Erstarrungsfront aus dem Tragflügelprofil 20 austreten und in Richtung des Bereichs 52a, 52b umgelenkt werden kann. Im Anschluß erfolgt eine nochmalige Richtungsänderung in Richtung des Bereichs 53a, 53b. Der Winkel 55 der Umlenkung ist wie die Winkel 22, 23 größer als 90 Grad. Dieser Wechsel der Erstarrungsrichtung ist daher gut beherrschbar. Der Querschnitt der Bereiche 52a, 52b, 53a, 53b ist etwa gleich, so daß lediglich eine Änderung der Erstarrungsrichtung erforderlich ist.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.

    Die vorliegende Erfindung vermeidet einen plötzlichen Richtungs- und Querschnittswechsel der Erstarrungsrichtung bei der Herstellung der Leitschaufeln 13, 33, 43. Die Leitschaufeln 13, 33, 43 können daher wesentlich einfacher als bisher als Einkristall ausgebildet werden.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.

    Claims (10)

    1. Turbine blade, in particular for a gas turbine (10), having an airfoil profile (20) and two platforms (18; 19; 38; 39; 48; 49) arranged at opposite ends of the airfoil profile (20) for fastening to a primary component (11; 12), characterized in that both platforms (18; 19; 38; 39; 48; 49) exclusively enclose an obtuse angle (22; 23) with a longitudinal axis (21) of the airfoil profile (20).
    2. Turbine blade according to Claim 1, characterized in that the at least one platform (38; 39; 48; 49) is designed to be straight or partly or completely curved.
    3. Turbine blade according to one of Claims 1 to 2, characterized in that the platforms (38; 39; 48; 49) project on both sides of the airfoil profile (20).
    4. Turbine blade according to Claim 3, characterized in that the platforms (38; 39; 48; 49) are arranged symmetrically to the longitudinal axis (21) of the airfoil profile (20).
    5. Turbine blade according to one of Claims 1 to 2, characterized in that the at least one platform (18; 19) projects only on one side of the airfoil profile (20).
    6. Turbine blade according to Claims 1 and 5, characterized in that the platforms (18, 19) project on different sides, in particular opposite one another, of the airfoil profile (20).
    7. Turbine blade according to one of Claims 1 to 6, characterized in that the turbine blade (13; 33; 43) is designed as a single crystal.
    8. Turbine blade according to one of Claims 1 to 7, characterized in that the turbine blade (13) is designed as a guide blade.
    9. Turbine, in particular a gas turbine (10), having a casing (11) and a rotor (12) accommodated in the casing (11) and also a plurality of turbine blades (13) according to Claim 5 or 6, characterized in that a longitudinal axis (21) of the airfoil profile (20) of each turbine blade (13) runs at a distance from a rotation axis (16) of the rotor (12).
    10. Turbine according to Claim 9, characterized in that the longitudinal axis (21) of the airfoil profile (20) of each turbine blade (13) encloses an angle (26) of 8 to 18° with a radius (27) of the turbine (10).
    EP01108477A 2001-04-04 2001-04-04 Gas turbine blade and gas turbine Expired - Lifetime EP1247937B1 (en)

    Priority Applications (6)

    Application Number Priority Date Filing Date Title
    EP01108477A EP1247937B1 (en) 2001-04-04 2001-04-04 Gas turbine blade and gas turbine
    ES01108477T ES2243358T3 (en) 2001-04-04 2001-04-04 TURBINE AND TABBINE ALABE.
    DE50106970T DE50106970D1 (en) 2001-04-04 2001-04-04 Turbine blade and turbine
    JP2002098226A JP2002357102A (en) 2001-04-04 2002-04-01 Turbine blade and turbine
    CNB021085943A CN100366865C (en) 2001-04-04 2002-04-04 Turbine propeller and turbine engine
    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 (en) 2001-04-04 2001-04-04 Gas turbine blade and gas turbine

    Publications (2)

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    EP1247937A1 EP1247937A1 (en) 2002-10-09
    EP1247937B1 true EP1247937B1 (en) 2005-08-03

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    EP01108477A Expired - Lifetime EP1247937B1 (en) 2001-04-04 2001-04-04 Gas turbine blade and gas turbine

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    EP (1) EP1247937B1 (en)
    JP (1) JP2002357102A (en)
    CN (1) CN100366865C (en)
    DE (1) DE50106970D1 (en)
    ES (1) ES2243358T3 (en)

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    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 (en) * 2013-12-17 2015-06-18 Nuovo Pignone Srl IMPELLER WITH PROTECTION ELEMENTS AND CENTRIFUGAL COMPRESSOR
    FR3014942B1 (en) * 2013-12-18 2016-01-08 Snecma DAWN, WHEEL IN AUBES AND TURBOMACHINE; PROCESS FOR MANUFACTURING DAWN
    CN104454027B (en) * 2014-10-31 2016-01-06 中国南方航空工业(集团)有限公司 The processing method of power turbine guider
    CN113513368B (en) * 2021-07-08 2022-09-02 哈尔滨工程大学 Turbine capable of directly backing with primary and secondary moving blade structures

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    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
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    DE50106970D1 (en) 2005-09-08
    JP2002357102A (en) 2002-12-13
    EP1247937A1 (en) 2002-10-09
    CN100366865C (en) 2008-02-06
    US20020157250A1 (en) 2002-10-31
    CN1379165A (en) 2002-11-13
    ES2243358T3 (en) 2005-12-01

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