EP2462320A2 - Blade - Google Patents

Blade

Info

Publication number
EP2462320A2
EP2462320A2 EP10754675A EP10754675A EP2462320A2 EP 2462320 A2 EP2462320 A2 EP 2462320A2 EP 10754675 A EP10754675 A EP 10754675A EP 10754675 A EP10754675 A EP 10754675A EP 2462320 A2 EP2462320 A2 EP 2462320A2
Authority
EP
European Patent Office
Prior art keywords
airfoil
thickening
blade
housing
profile
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.)
Granted
Application number
EP10754675A
Other languages
German (de)
French (fr)
Other versions
EP2462320B1 (en
Inventor
Sergio Elorza Gomez
Rudolf Selmeier
Wilfried SCHÜTTE
Peter EIBELSHÄUSER
Harald Passrucker
Manfred Dupslaff
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2462320A2 publication Critical patent/EP2462320A2/en
Application granted granted Critical
Publication of EP2462320B1 publication Critical patent/EP2462320B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/713—Shape curved inflexed

Definitions

  • the present invention relates to an airfoil of a turbomachine, in particular an adjustable guide vane of a gas turbine, with at least one thickening on a pressure side of the airfoil profile, wherein the thickening is arranged in a radially outer, housing-side region of the airfoil.
  • the disclosed thickenings of the airfoils serve in particular to minimize the so-called secondary flow losses.
  • the thickening of the airfoil is in each case formed in the housing and / or the scar-side suction and pressure region of the airfoil.
  • Thickenings of the blade profile in the housing-side area are also necessary in order to counteract the high static stresses frequently occurring on the housing side of adjustable guide vanes of compressors.
  • the suction and pressure side formed thickenings have aerodynamic o disadvantages.
  • An inventive blade of a turbomachine in particular an adjustable guide vane of a gas turbine, comprising at least one thickening on a pressure side of the airfoil profile, wherein the thickening is disposed in a radially outer, housing-side portion of the airfoil and the thickening of a leading edge and a trailing edge of the airfoil each spaced is trained.
  • a complete thickening of the radially outer, housing-side regions of the airfoils is dispensed with.
  • thin, aerodynamic favorable airfoil profiles can be designed, which still have the required strength due to the locally pronounced thickening.
  • the thickening is designed as a convex contour within the overall concave contour of the pressure side of the airfoil profile.
  • the convex contour or the at least partially convex configuration of the thickening has proved to be advantageous in terms of flow mechanics.
  • the thickening in the housing-side end region of the airfoil can have their greatest profile thickness. In this case, the profile thickness of the thickening, starting from the largest profile thickness continuously decrease to a normal profile thickness of the airfoil profile without thickening.
  • the thickening extends maximally to a height of the housing and pressure side region of the blade, which corresponds to 25% of the blade blade height. It has been found that such a dimensioning of the thickening the necessary strength ensures the blade in the housing-side area. In addition, you can
  • the distance between the leading edge of the blade and the thickening in the housing-side end region of the blade is at least 15% of a chord length of the blade in this end region.
  • the convex contour of the thickening at the ends of the thickening can each extend tangentially to the concave contour of the pressure side of the blade leaf profile.
  • the thickening may be formed at least partially bead or hump.
  • this housing side is connected to a rotatably mounted in a housing of the turbomachine turntable.
  • the leading edge and the trailing edge of the blade can be arranged completely within the diameter of the turntable.
  • the leading edge and / or the trailing edge of the blade can protrude beyond the turntable.
  • the thickening ends outside the diameter of the turntable it has proven to be advantageous that the thickening ends outside the diameter of the turntable. As a result, it is possible to specifically reduce stresses on the edge of the turntable.
  • a turbomachine according to the invention in particular gas turbine, with a stator and / or rotor blading comprises a plurality of blades according to the exemplary embodiments of the invention described above.
  • a compressor according to the invention of a turbomachine in particular a high-pressure compressor of a gas turbine, comprises a stator blading with a multiplicity of airfoils according to one of the exemplary embodiments described above.
  • Figure 1 is a schematic representation of a blade without thickening according to the
  • Figure 2 is a schematic representation of an airfoil according to the invention
  • Figure 3 is a schematic representation of a arranged on a turntable blade without thickening according to the prior art
  • Figure 4 is a schematic representation of a arranged on a turntable according to the invention blade according to a second embodiment.
  • FIG. 1 shows a schematic representation of a blade 10 without thickening according to the prior art.
  • the airfoil 10 has a conventional airfoil contour 16, wherein the airfoil contour 16 on the pressure side D of the airfoil 10 as a whole is concave and on the suction side S of the airfoil 10 is formed as a whole convex o.
  • the chord length Se of the airfoil 10 is usually defined as a linear distance between the leading edge 12 and the trailing edge 14 of the respective profile section.
  • FIG. 2 shows a schematic representation of a blade 10 according to an embodiment of the invention.
  • the airfoil 10 is an airfoil 5 of a turbomachine, in particular an adjustable guide vane of a gas turbine. It can be seen that the airfoil 10 has a thickening 18 on a pressure side D of the airfoil profile P, wherein the thickening 18 is arranged in a radially outer, housing-side region of the airfoil 10. In this illustration, the housing is not shown.
  • the airfoil profile P is formed and defined by an airfoil contour 16 o. It is clear that the thickening 18 as a convex contour
  • the extent E of the thickening 18 is selected such that the thickening 18 is formed in a spaced manner in total from the front edge 12 and the trailing edge 14 of the airfoil 10.
  • the distance between the front edge 12 and the thickening 18 in the housing-side end region of the blade 10 shown is approximately 15% of the chord length Se of the blade 10 in this end region. This distance is marked with Se 15 .
  • the thickening 18 in the housing-side end region of the airfoil 10 has its largest profile thickness d raax .
  • the profile thickness d decreases continuously in the direction of the end region opposite the housing-side end region of the airfoil 10-usually a hub region of a turbomachine-up to a normal profile thickness d norm of the airfoil profile P without thickening 18.
  • the convex contour 20 of the thickening 18 at the ends of the thickening 18 runs tangentially to the concave contour of the pressure side D of the airfoil profile P. It can be seen that the thickening 18 is formed at least partially höckerformig.
  • FIG. 3 shows a schematic representation of a blade plate 10 without thickening arranged on a turntable 22 according to the prior art.
  • the blade 10 is arranged on the turntable 22, that its front edge 12 protrudes on the turntable 22 and the rear edge 14 over the diameter of the turntable 22.
  • FIG. 4 shows a schematic representation of an airfoil 10 arranged on a turntable 22 in accordance with a second embodiment of the invention.
  • the turntable 22 serves to adjust the airfoil 10 and is rotatably mounted within a housing of the turbomachine.
  • the blade 10 is arranged in the illustrated exemplary embodiment on the turntable 22 that its front edge 12 of the blade 10 on the turntable 22 and the rear edge 14 projects beyond the diameter of the turntable 22.
  • the thickening 18 is spaced from the leading edge 12 and the trailing edge 14 of the airfoil 10.
  • the thickening 18 In the illustrated housing-side end region of the airfoil 10, the thickening 18 their biggest profile thickness d ma ⁇ on.
  • the exemplary embodiment shown is part of a stator blading of a compressor of a turbomachine, in particular of a high-pressure compressor of a gas turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)

Abstract

The present invention relates to a blade of a turbomachine, in particular an adjustable guide blade of a gas turbine, comprising at least one thickened area (18) on a pressure side (D) of the blade profile (P), wherein the thickened area (18) is arranged in a radially outer, housing-side area of the blade (10), wherein the thickened area (18) is designed at a distance from a front edge (12) and a rear edge (14) of the blade (10).

Description

Schaufelblatt  airfoil
Beschreibung description
5  5
Die vorliegende Erfindung betrifft ein Schaufelblatt einer Strömungsmaschine, insbesondere eine verstellbare Leitschaufel einer Gasturbine, mit mindestens einer Aufdickung auf einer Druckseite des Schaufelblattprofils, wobei die Aufdickung in einem radial außenliegenden, gehäuseseitigen Bereich des Schaufelblatts angeordnet ist. The present invention relates to an airfoil of a turbomachine, in particular an adjustable guide vane of a gas turbine, with at least one thickening on a pressure side of the airfoil profile, wherein the thickening is arranged in a radially outer, housing-side region of the airfoil.
0 0
Derartige Schaufelblätter für Strömungsmaschinen sind aus der DE 28 41 616, der  Such blades for turbomachines are known from DE 28 41 616, the
DE 10 2004 026 386 und der EP 0 789 447 Bl bekannt. Die offenbarten Aufdickungen der Schaufelblätter dienen insbesondere zur Minimierung der so genannten Sekundärströ- mungsverluste. Die Aufdickung des Schaufelblatts ist dabei jeweils im gehäuse- und/oder5 narbenseitigen Saug- und Druckbereich des Schaufelblatts ausgebildet. Die bekannten  DE 10 2004 026 386 and EP 0 789 447 B1. The disclosed thickenings of the airfoils serve in particular to minimize the so-called secondary flow losses. The thickening of the airfoil is in each case formed in the housing and / or the scar-side suction and pressure region of the airfoil. The well-known
Aufdickungen des Schaufelprofils im gehäuseseitigen Bereich sind zudem notwendig, um die an der Gehäuseseite von verstellbaren Leitschaufeln von Verdichtern häufig auftretenden hohen statischen Spannungen entgegenzuwirken. Die bekannten umlaufenden, d. h. auf der Saug- und Druckseite ausgebildeten Aufdickungen weisen jedoch aerodynamische o Nachteile auf.  Thickenings of the blade profile in the housing-side area are also necessary in order to counteract the high static stresses frequently occurring on the housing side of adjustable guide vanes of compressors. The well-known circulating, d. H. However, on the suction and pressure side formed thickenings have aerodynamic o disadvantages.
Es ist daher Aufgabe der vorliegenden Erfindung ein Schaufelblatt der eingangs genannten Art bereitzustellen, welches eine relativ dünnes, aerodynamisch günstiges Schaufelprofil bei gleichzeitig verbesserter Festigkeit aufweist.It is therefore an object of the present invention to provide an airfoil of the type mentioned, which has a relatively thin, aerodynamically favorable blade profile with improved strength.
5 5
Gelöst wird diese Aufgabe durch ein Schaufelblatt gemäß den Merkmalen des Anspruchs 1.  This object is achieved by an airfoil according to the features of claim 1.
Vorteilhafte Ausgestaltungen der Erfindung sind in den jeweiligen Unteransprüchen be- o schrieben. Ein erfindungsgemäßes Schaufelblatt einer Strömungsmaschine, insbesondere eine verstellbare Leitschaufel einer Gasturbine, umfasst mindestens eine Aufdickung auf einer Druckseite des Schaufelblattprofils, wobei die Aufdickung in einem radial außenliegenden, gehäuseseitigen Bereich des Schaufelblatts angeordnet ist und die Aufdickung von einer Vorderkante und einer Hinterkante des Schaufelblatts jeweils beabstandet ausgebildet ist. Erfindungsgemäß wird auf eine vollumfängliche Aufdickung der radial außenliegenden, gehäuseseitigen Bereiche der Schaufelblätter verzichtet. Vorteilhafterweise können somit dünne, aerodynamische günstige Schaufelblattprofile ausgelegt werden, die aufgrund der lokal ausgeprägten Aufdickung dennoch die geforderte Festigkeit aufweisen. Dadurch kön- nen zudem Spannungen im Bereich der Gehäuseseite, insbesondere hohe statische Spannungen, die im Bereich eines gehäuseseitigen Drehtellers bei verstellbaren Schaufelblättern auftreten, minimiert werden. Durch eine optimierte Ausformung der Aufdickung ist es zudem möglich, dass lokal der statische Druck im druckseitigen Bereich einer erfindungsgemäß ausgebildeten Leitschaufel reduziert werden kann. Dadurch verringert sich vorteilhaft- erweise die Intensität der Spaltströmung in diesen Bereich. Advantageous embodiments of the invention are described in the respective subclaims. An inventive blade of a turbomachine, in particular an adjustable guide vane of a gas turbine, comprising at least one thickening on a pressure side of the airfoil profile, wherein the thickening is disposed in a radially outer, housing-side portion of the airfoil and the thickening of a leading edge and a trailing edge of the airfoil each spaced is trained. According to the invention, a complete thickening of the radially outer, housing-side regions of the airfoils is dispensed with. Advantageously, therefore, thin, aerodynamic favorable airfoil profiles can be designed, which still have the required strength due to the locally pronounced thickening. As a result, stresses in the region of the housing side, in particular high static stresses, which occur in the region of a housing-side turntable with adjustable blade leaves, can also be minimized. By an optimized formation of the thickening, it is also possible that locally the static pressure in the pressure-side region of a guide vane designed according to the invention can be reduced. This advantageously reduces the intensity of the gap flow in this area.
In vorteilhaften Ausgestaltungen des erfindungsgemäßen Schaufelblatts ist die Aufdickung als konvexe Kontur innerhalb der insgesamt konkaven Kontur der Druckseite des Schaufelblattprofils ausgebildet. Die konvexe Kontur bzw. die zumindest teilweise konvexe Ausgestaltung der Aufdickung hat sich als strömungsmechanisch vorteilhaft erwiesen. Zudem kann die Aufdickung im gehäuseseitigen Endbereich des Schaufelblatts ihre größte Profildicke aufweisen. Dabei kann die Profildicke der Aufdickung ausgehend von der größten Profildicke kontinuierlich bis zu einer normalen Profildicke des Schaufelblattprofils ohne Aufdickung abnehmen. Auch diese Ausgestaltungen der Aufdickung haben sich als besonders vorteilhaft hinsichtlich der strömungsmechanischen Anforderungen in diesem Bereich erwiesen. In advantageous embodiments of the blade according to the invention, the thickening is designed as a convex contour within the overall concave contour of the pressure side of the airfoil profile. The convex contour or the at least partially convex configuration of the thickening has proved to be advantageous in terms of flow mechanics. In addition, the thickening in the housing-side end region of the airfoil can have their greatest profile thickness. In this case, the profile thickness of the thickening, starting from the largest profile thickness continuously decrease to a normal profile thickness of the airfoil profile without thickening. These embodiments of the thickening have proven to be particularly advantageous in terms of fluid mechanical requirements in this area.
In einer weiteren vorteilhaften Ausgestaltung des erfindungsgemäßen Schaufelblatts erstreckt sich die Aufdickung maximal bis zu einer Höhe von dem gehäuse- und druckseiti- gen Bereich des Schaufelblatts, die 25 % der Schaufelblatthöhe entspricht. Es hat sich herausgestellt, dass eine derartige Dimensionierung der Aufdickung die notwendige Festigkeit des Schaufelblatts im gehäuseseitigen Bereich gewährleistet. Zudem können In a further advantageous embodiment of the blade according to the invention, the thickening extends maximally to a height of the housing and pressure side region of the blade, which corresponds to 25% of the blade blade height. It has been found that such a dimensioning of the thickening the necessary strength ensures the blade in the housing-side area. In addition, you can
überwiegende Bereiche des Schaufelblatts ein relativ dünnes, aerodynamisch optimiertes Schaufelblattprofil aufweisen.  vast areas of the airfoil have a relatively thin, aerodynamically optimized airfoil profile.
5 In weiteren vorteilhaften Ausgestaltungen des erfindungsgemäßen Schaufelblatts beträgt der Abstand zwischen der Vorderkante des Schaufelblatts und der Aufdickung im gehäuseseitigen Endbereich des Schaufelblatts mindestens 15 % einer Sehnenlänge des Schaufelblatts in diesem Endbereich. Zudem kann die konvexe Kontur der Aufdickung an den Enden der Aufdickung jeweils tangential zur konkaven Kontur der Druckseite des Schaufel-0 blattprofils verlaufen. Die Aufdickung kann zumindest teilweise wulst- oder höckerförmig ausgebildet sein. Auch diese Ausgestaltungsmöglichkeiten der Aufdickung beinhalten die Möglichkeit der Ausbildung eines aerodynamisch günstigen Schaufelprofils bei einer gleichzeitig verbesserten Festigkeit des Schaufelblatts zum Ausgleich von gehäuseseitig auftretenden Spannungen.In further advantageous embodiments of the blade according to the invention, the distance between the leading edge of the blade and the thickening in the housing-side end region of the blade is at least 15% of a chord length of the blade in this end region. In addition, the convex contour of the thickening at the ends of the thickening can each extend tangentially to the concave contour of the pressure side of the blade leaf profile. The thickening may be formed at least partially bead or hump. These embodiments of the thickening include the possibility of forming an aerodynamically favorable blade profile with a simultaneously improved strength of the blade to compensate for voltages occurring on the housing side.
5 5
In weiteren vorteilhaften Ausgestaltungen des erfindungsgemäßen Schaufelblatts ist dieses gehäuseseitig mit einem in einem Gehäuse der Strömungsmaschine drehbar gelagerten Drehteller verbunden. Dabei kann die Vorderkante und die Hinterkante des Schaufelblatts vollständig innerhalb des Durchmessers des Drehtellers angeordnet sein. Es ist aber auch o möglich, dass die Vorderkante und/oder die Hinterkante des Schaufelblatts über den Drehteller hinausragt. Für den Fall, dass die Hinterkante des Schaufelblatts über den Drehteller hinausragt, hat es sich als vorteilhaft erwiesen, dass die Aufdickung außerhalb des Durchmessers des Drehtellers endet. Dadurch können insbesondere Spannungen am Rand des Drehtellers gezielt reduziert werden. In further advantageous embodiments of the blade according to the invention this housing side is connected to a rotatably mounted in a housing of the turbomachine turntable. In this case, the leading edge and the trailing edge of the blade can be arranged completely within the diameter of the turntable. However, it is also possible for the leading edge and / or the trailing edge of the blade to protrude beyond the turntable. In the event that the trailing edge of the blade extends beyond the turntable, it has proven to be advantageous that the thickening ends outside the diameter of the turntable. As a result, it is possible to specifically reduce stresses on the edge of the turntable.
5 5
Eine erfindungsgemäße Strömungsmaschine, insbesondere Gasturbine, mit einer Stator- und/oder Rotorbeschaufelung umfasst eine Vielzahl von Schaufelblättern gemäß den im vorhergehenden beschriebenen erfindungsgemäßen Ausfuhrungsbeispielen. Ein erfindungsgemäßer Verdichter einer Strömungsmaschine, insbesondere ein Hochdruckverdich- o ter einer Gasturbine, umfasst eine Statorbeschaufelung mit einer Vielzahl von Schaufelblättern gemäß einem der im Vorhergehenden beschriebenen Ausführungsbeispiele. Weitere Vorteile, Merkmale und Einzelheiten der Erfindung ergeben sich aus der nachfolgenden Beschreibung zweier zeichnerisch dargestellter Ausführungsbeispiele. Dabei zeigen A turbomachine according to the invention, in particular gas turbine, with a stator and / or rotor blading comprises a plurality of blades according to the exemplary embodiments of the invention described above. A compressor according to the invention of a turbomachine, in particular a high-pressure compressor of a gas turbine, comprises a stator blading with a multiplicity of airfoils according to one of the exemplary embodiments described above. Further advantages, features and details of the invention will become apparent from the following description of two drawings illustrated embodiments. Show
5 Figur 1 eine schematische Darstellung eines Schaufelblatts ohne Aufdickung gemäß dem Figure 1 is a schematic representation of a blade without thickening according to the
Stand der Technik;  State of the art;
Figur 2 eine schematische Darstellung eines erfindungsgemäßen Schaufelblatts; o Figur 3 eine schematische Darstellung eines auf einem Drehteller angeordneten Schaufelblatts ohne Aufdickung gemäß dem Stand der Technik; und Figure 2 is a schematic representation of an airfoil according to the invention; Figure 3 is a schematic representation of a arranged on a turntable blade without thickening according to the prior art; and
Figur 4 eine schematische Darstellung eines auf einem Drehteller angeordneten erfindungsgemäßen Schaufelblatts gemäß einer zweiten Ausführungsform.Figure 4 is a schematic representation of a arranged on a turntable according to the invention blade according to a second embodiment.
5 5
Figur 1 zeigt eine schematische Darstellung eines Schaufelblatts 10 ohne Aufdickung gemäß dem Stand der Technik. Das Schaufelblatt 10 weist eine übliche Schaufelblattkontur 16 auf, wobei die Schaufelblattkontur 16 auf der Druckseite D des Schaufelblatts 10 insgesamt konkav und auf der Saugseite S des Schaufelblatts 10 insgesamt konvex ausgebildet o ist. Die Sehnenlänge Se des Schaufelblatts 10 wird üblicherweise als linearer Abstand zwischen der Vorderkante 12 und der Hinterkante 14 des jeweiligen Profilschnitts definiert.  Figure 1 shows a schematic representation of a blade 10 without thickening according to the prior art. The airfoil 10 has a conventional airfoil contour 16, wherein the airfoil contour 16 on the pressure side D of the airfoil 10 as a whole is concave and on the suction side S of the airfoil 10 is formed as a whole convex o. The chord length Se of the airfoil 10 is usually defined as a linear distance between the leading edge 12 and the trailing edge 14 of the respective profile section.
Figur 2 zeigt eine schematische Darstellung eines Schaufelblatts 10 gemäß einem Ausführungsbeispiel der Erfindung. Bei dem Schaufelblatt 10 handelt es sich um ein Schaufelblatt 5 einer Strömungsmaschine, insbesondere um eine verstellbare Leitschaufel einer Gasturbine. Man erkennt, dass das Schaufelblatt 10 eine Aufdickung 18 auf einer Druckseite D des Schaufelblattprofils P aufweist, wobei die Aufdickung 18 in einem radial außenliegenden, gehäuseseitigen Bereich des Schaufelblatts 10 angeordnet ist. In dieser Darstellung ist das Gehäuse nicht dargestellt. Das Schaufelblattprofil P wird durch eine Schaufelblattkontur 16 o ausgebildet und definiert. Dabei wird deutlich, dass die Aufdickung 18 als konvexe KonturFigure 2 shows a schematic representation of a blade 10 according to an embodiment of the invention. The airfoil 10 is an airfoil 5 of a turbomachine, in particular an adjustable guide vane of a gas turbine. It can be seen that the airfoil 10 has a thickening 18 on a pressure side D of the airfoil profile P, wherein the thickening 18 is arranged in a radially outer, housing-side region of the airfoil 10. In this illustration, the housing is not shown. The airfoil profile P is formed and defined by an airfoil contour 16 o. It is clear that the thickening 18 as a convex contour
20 innerhalb der insgesamt konkaven Kontur der Druckseite D des Schaufelblattprofils P ausgebildet ist. Die Erstreckung E der Aufdickung 18 ist dabei derart gewählt, dass die Aufdickung 18 insgesamt von der Vorderkante 12 und der Hinterkante 14 des Schaufelblatts 10 jeweils beabstandet ausgebildet ist. Dabei beträgt der Abstand zwischen der Vorderkante 12 und der Aufdickung 18 in dem gezeigten gehäuseseitigen Endbereich des Schaufelblatts 10 ca. 15 % der Sehnenlänge Se des Schaufelblatts 10 in diesem Endbereich. Dieser Abstand ist mit Se15 gekennzeichnet. 20 within the total concave contour of the pressure side D of the airfoil profile P. is trained. The extent E of the thickening 18 is selected such that the thickening 18 is formed in a spaced manner in total from the front edge 12 and the trailing edge 14 of the airfoil 10. In this case, the distance between the front edge 12 and the thickening 18 in the housing-side end region of the blade 10 shown is approximately 15% of the chord length Se of the blade 10 in this end region. This distance is marked with Se 15 .
Des Weiteren erkennt man, dass die Aufdickung 18 im gehäuseseitigen Endbereich des Schaufelblatts 10 ihre größte Profildicke draax aufweist. Ausgehend von dieser größten Pro- fildicke dmax nimmt die Profildicke d in Richtung des dem gehäuseseitigen Endbereich des Schaufelblatts 10 gegenüberliegenden Endbereichs - üblicherweise ein Nabenbereich einer Strömungsmaschine - kontinuierlich bis zu einer normalen Profildicke dnorm des Schaufelblattprofils P ohne Aufdickung 18 hin ab. Weiterhin wird deutlich, dass die konvexe Kontur 20 der Aufdickung 18 an den Enden der Aufdickung 18 tangential zur konkaven Kontur der Druckseite D des Schaufelblattprofüs P verläuft. Man erkennt, dass die Aufdickung 18 zumindest teilweise höckerformig ausgebildet ist. Furthermore, it can be seen that the thickening 18 in the housing-side end region of the airfoil 10 has its largest profile thickness d raax . Starting from this largest profile thickness d max , the profile thickness d decreases continuously in the direction of the end region opposite the housing-side end region of the airfoil 10-usually a hub region of a turbomachine-up to a normal profile thickness d norm of the airfoil profile P without thickening 18. Furthermore, it becomes clear that the convex contour 20 of the thickening 18 at the ends of the thickening 18 runs tangentially to the concave contour of the pressure side D of the airfoil profile P. It can be seen that the thickening 18 is formed at least partially höckerformig.
Figur 3 zeigt eine schematische Darstellung eines auf einem Drehteller 22 angeordneten Schaufelblatts 10 ohne Aufdickung gemäß dem Stand der Technik. Das Schaufelblatt 10 ist dabei derart auf dem Drehteller 22 angeordnet, dass dessen Vorderkante 12 auf dem Drehteller 22 und dessen Hinterkante 14 über den Durchmesser des Drehtellers 22 hinausragt. FIG. 3 shows a schematic representation of a blade plate 10 without thickening arranged on a turntable 22 according to the prior art. The blade 10 is arranged on the turntable 22, that its front edge 12 protrudes on the turntable 22 and the rear edge 14 over the diameter of the turntable 22.
Figur 4 zeigt eine schematische Darstellung eines auf einem Drehteller 22 angeordneten Schaufelblatts 10 gemäß einer zweiten Ausführungsform der Erfindung. Der Drehteller 22 dient dabei zur Verstellung des Schaufelblatts 10 und ist innerhalb eines Gehäuses der Strömungsmaschine drehbar gelagert. Das Schaufelblatt 10 ist in dem dargestellten Ausfuhrungsbeispiel derart auf dem Drehteller 22 angeordnet, dass dessen Vorderkante 12 des Schaufelblatts 10 auf dem Drehteller 22 und dessen Hinterkante 14 über den Durchmesser des Drehtellers 22 hinausragt. Es wird wiederum deutlich, dass die Aufdickung 18 von der Vorderkante 12 und der Hinterkante 14 des Schaufelblatts 10 beabstandet ausgebildet ist. Im dargestellten gehäuseseitigen Endbereich des Schaufelblatts 10 weist die Aufdickung 18 ihre größte Profildicke dmaχ auf. Die Profildicke d der Aufdickung 18 nimmt wiederum ausgehend von der größten Profildicke dmax kontinuierlich bis zu einer normalen Profildicke dnorm des Schaufelblattprofϊls P hin ab. Des Weiteren wird deutlich, dass sich die Aufdickung 18 maximal bis zu einer Höhe von dem gehäuse- und druckseitigen Bereich des Schaufelblatts 10 erstreckt, die 25 % der Schaufelblatthöhe Sh entspricht. Aus dieser Darstellung des Schaufelblattprofils P wie auch der in Figur 2 gezeigten Darstellung wird deutlich, dass die größte Profildicke dmax der Aufdickung 18 über die gedachte Linie der Sehnenlänge Se hinausragt. Dabei weist die in Figur 4 gezeigte Aufdickung 18 relativ zu der in Figur 2 dargestellten Aufdickung 18 eine größere Erstreckung E über die Druckseite D des Schaufelblatts 10 auf. Des Weiteren wird deutlich, dass die Aufdickung 18 außerhalb des Durchmessers des Drehtellers 22 endet. FIG. 4 shows a schematic representation of an airfoil 10 arranged on a turntable 22 in accordance with a second embodiment of the invention. The turntable 22 serves to adjust the airfoil 10 and is rotatably mounted within a housing of the turbomachine. The blade 10 is arranged in the illustrated exemplary embodiment on the turntable 22 that its front edge 12 of the blade 10 on the turntable 22 and the rear edge 14 projects beyond the diameter of the turntable 22. Again, it will be appreciated that the thickening 18 is spaced from the leading edge 12 and the trailing edge 14 of the airfoil 10. In the illustrated housing-side end region of the airfoil 10, the thickening 18 their biggest profile thickness d ma χ on. The profile thickness d of the thickening 18, in turn, continuously decreases starting from the largest profile thickness d max up to a normal profile thickness d norm of the airfoil profile P. Furthermore, it is clear that the thickening 18 extends maximally to a height from the housing and pressure-side region of the blade 10, which corresponds to 25% of the blade blade height Sh. From this representation of the airfoil profile P as well as the illustration shown in Figure 2 it is clear that the largest profile thickness d max of the thickening 18 extends beyond the imaginary line of the chord length Se. In this case, the thickening 18 shown in FIG. 4 has a greater extent E over the pressure side D of the blade 10 relative to the thickening 18 shown in FIG. Furthermore, it is clear that the thickening 18 ends outside the diameter of the turntable 22.
Das gezeigte Ausführungsbeispiel ist Teil einer Statorbeschaufelung eines Verdichters einer Strömungsmaschine, insbesondere eines Hochdruckverdichters einer Gasturbine. The exemplary embodiment shown is part of a stator blading of a compressor of a turbomachine, in particular of a high-pressure compressor of a gas turbine.

Claims

Patentansprüche claims
1. Schaufelblatt einer Strömungsmaschine, insbesondere verstellbare Leitschaufel einer1. airfoil of a turbomachine, in particular adjustable vane one
5 Gasturbine, mit mindestens einer Aufdickung (18) auf einer Druckseite (D) des Schaufelblattprofils (P), wobei die Aufdickung (18) in einem radial außenliegenden, gehäuseseiti- gen Bereich des Schaufelblatts (10) angeordnet ist, dadurch gekennzeichnet, dass die Aufdickung (18) von einer Vorderkante (12) und einer Hinterkante (14) des Schaufelblatts (10) beabstandet ausgebildet ist.5 gas turbine, with at least one thickening (18) on a pressure side (D) of the airfoil profile (P), wherein the thickening (18) in a radially outer, housing-side region of the airfoil (10) is arranged, characterized in that the Thickening (18) from a front edge (12) and a trailing edge (14) of the airfoil (10) spaced apart.
0 0
2. Schaufelblatt nach Anspruch 1, dadurch gekennzeichnet, dass die Aufdickung (18) als konvexe Kontur (20) innerhalb der insgesamt konkaven Kontur der Druckseite (D) des Schaufelblattprofils (P) ausgebildet ist. 5 2. airfoil according to claim 1, characterized in that the thickening (18) as a convex contour (20) within the overall concave contour of the pressure side (D) of the airfoil profile (P) is formed. 5
3. Schaufelblatt nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Aufdickung (18) im gehäuseseitigen Endbereich des Schaufelblatts (10) ihre größte Profildicke (dmax) aufweist. 3. airfoil according to claim 1 or 2, characterized in that the thickening (18) in the housing-side end portion of the airfoil (10) has its largest profile thickness (d max ).
4. Schaufelblatt nach Anspruch 3, dadurch gekennzeichnet, dass eine Profildicke (d) der o Aufdickung (18) ausgehend von der größten Profildicke (dmax) kontinuierlich bis zu einer normalen Profildicke (dnorm) des Schaufelblattprofils (P) ohne Aufdickung (18) abnimmt. 4. An airfoil according to claim 3, characterized in that a profile thickness (d) of the o thickening (18), starting from the largest profile thickness (d max ) continuously up to a normal profile thickness (d norm ) of the airfoil profile (P) without thickening (18 ) decreases.
5. Schaufelblatt nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass sich die Aufdickung (18) maximal bis zu einer Höhe von dem gehäuse- und druckseitigen5 Bereich des Schaufelblatts (10) erstreckt, die 25% der Schaufelblatthöhe(Sh) entspricht. 5. Blade according to one of the preceding claims, characterized in that the thickening (18) extends to a maximum extent to a height of the housing and pressure side5 region of the airfoil (10), which corresponds to 25% of the blade height (Sh).
6. Schaufelblatt nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass der Abstand zwischen der Vorderkante (12) des Schaufelblatts (10) und der Aufdickung (18) im gehäuseseitigen Endbereich des Schaufelblatts (10) mindestens 15% einer Sehnen- o länge (Se) des Schaufelblatts (10) in diesem Endbereich entspricht. An airfoil according to one of the preceding claims, characterized in that the distance between the leading edge (12) of the airfoil (10) and the thickening (18) in the housing-side end region of the airfoil (10) is at least 15% of a chordal length (Se ) of the airfoil (10) in this end region corresponds.
7. Schaufelblatt nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die konvexe Kontur (20) der Aufdickung (18) an den Enden der Aufdickung (18) jeweils tangential zur konkaven Kontur der Druckseite (D) des Schaufelblattprofϊls (P) verläuft. 7. airfoil according to one of the preceding claims, characterized in that the convex contour (20) of the thickening (18) at the ends of the thickening (18) each tangent to the concave contour of the pressure side (D) of the Schaufelblattprofϊls (P).
5 8. Schaufelblatt nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Aufdickung (18) zumindest teilweise wulst- oder höckerförmig ausgebildet ist. 5 8. An airfoil according to one of the preceding claims, characterized in that the thickening (18) is at least partially bead or hump-shaped.
9. Schaufelblatt nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Schaufelblatt (10) gehäuseseitig mit einem in einem Gehäuse drehbar gelagerten Dreh-0 teller (22) verbunden ist. 9. airfoil according to one of the preceding claims, characterized in that the blade (10) on the housing side with a rotatably mounted in a housing rotary plate (22) is connected.
10. Schaufelblatt nach Anspruch 9, dadurch gekennzeichnet, dass die Vorderkante (12) und die Hinterkante (14) des Schaufelblatts (10) vollständig innerhalb des Durchmessers des Drehtellers (22) angeordnet sind.An airfoil according to claim 9, characterized in that the leading edge (12) and trailing edge (14) of the airfoil (10) are disposed entirely within the diameter of the turntable (22).
5 5
11. Schaufelblatt nach Anspruch 9, dadurch gekennzeichnet, dass die Vorderkante (22) und/oder die Hinterkante (14) des Schaufelblatts (10) über den Drehteller (22) hinausragt.  11. An airfoil according to claim 9, characterized in that the front edge (22) and / or the trailing edge (14) of the airfoil (10) projects beyond the turntable (22).
12. Schaufelblatt nach Anspruch 11, dadurch gekennzeichnet, dass die Hinterkante (14) o über den Drehteller (22) hinausragt und die Aufdickung (18) außerhalb des Durchmessers des Drehtellers (22) endet. 12. An airfoil according to claim 11, characterized in that the trailing edge (14) o projects beyond the turntable (22) and the thickening (18) outside the diameter of the turntable (22) ends.
13. Strömungsmaschine, insbesondere Gasturbine, mit einer Stator- und/oder Rotorbeschaufelung umfassend eine Vielzahl von Schaufelblättern (10) gemäß einem der Ansprü-5 che 1 bis 12. 13. Turbomachine, in particular gas turbine, with a stator and / or rotor blading comprising a plurality of airfoils (10) according to one of Ansprü-5 che 1 to 12.
14. Verdichter einer Strömungsmaschine, insbesondere Niederdruckverdichter einer Gasturbine, mit einer Statorbeschaufelung umfassend eine Vielzahl von Schaufelblättern (10) gemäß einem der Ansprüche 1 bis 12. 14. A compressor of a turbomachine, in particular a low-pressure compressor of a gas turbine, with a stator blading comprising a plurality of airfoils (10) according to one of claims 1 to 12.
EP10754675.6A 2009-08-06 2010-08-05 Blade Active EP2462320B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009036406A DE102009036406A1 (en) 2009-08-06 2009-08-06 airfoil
PCT/DE2010/000920 WO2011015193A2 (en) 2009-08-06 2010-08-05 Blade

Publications (2)

Publication Number Publication Date
EP2462320A2 true EP2462320A2 (en) 2012-06-13
EP2462320B1 EP2462320B1 (en) 2016-10-12

Family

ID=43430143

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10754675.6A Active EP2462320B1 (en) 2009-08-06 2010-08-05 Blade

Country Status (5)

Country Link
US (1) US9011081B2 (en)
EP (1) EP2462320B1 (en)
CN (1) CN102472111B (en)
DE (1) DE102009036406A1 (en)
WO (1) WO2011015193A2 (en)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2696031B1 (en) * 2012-08-09 2015-10-14 MTU Aero Engines AG Blade for a flow machine engine and corresponding flow machine engine.
DE102012222953A1 (en) * 2012-12-12 2014-06-26 Honda Motor Co., Ltd. Wing profile for an axial flow compressor
JP6025961B2 (en) * 2013-02-21 2016-11-16 三菱重工業株式会社 Turbine blade
US9896950B2 (en) 2013-09-09 2018-02-20 Rolls-Royce Deutschland Ltd & Co Kg Turbine guide wheel
US20150275675A1 (en) * 2014-03-27 2015-10-01 General Electric Company Bucket airfoil for a turbomachine
FR3022295B1 (en) * 2014-06-17 2019-07-05 Safran Aircraft Engines TURBOMACHINE DAWN COMPRISING AN ANTIWINDER FIN
US20160024930A1 (en) * 2014-07-24 2016-01-28 General Electric Company Turbomachine airfoil
US9995166B2 (en) 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
JP6639275B2 (en) * 2016-03-10 2020-02-05 株式会社東芝 Guide vane & hydraulic machine of hydraulic machine
US11168566B2 (en) 2016-12-05 2021-11-09 MTU Aero Engines AG Turbine blade comprising a cavity with wall surface discontinuities and process for the production thereof
GB201702382D0 (en) * 2017-02-14 2017-03-29 Rolls Royce Plc Gas turbine engine fan blade
DE102017216620A1 (en) 2017-09-20 2019-03-21 MTU Aero Engines AG Shovel for a turbomachine
EP3561226A1 (en) * 2018-04-24 2019-10-30 Siemens Aktiengesellschaft Compressor aerofoil
BE1026579B1 (en) * 2018-08-31 2020-03-30 Safran Aero Boosters Sa PROTUBERANCE VANE FOR TURBOMACHINE COMPRESSOR
US11421702B2 (en) 2019-08-21 2022-08-23 Pratt & Whitney Canada Corp. Impeller with chordwise vane thickness variation
FR3101914B1 (en) * 2019-10-10 2021-11-12 Safran Aircraft Engines Variable-pitch stator vane with aerodynamic fins

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2918254A (en) * 1954-05-10 1959-12-22 Hausammann Werner Turborunner
SU411214A1 (en) * 1968-05-12 1974-01-15
JPS5447907A (en) 1977-09-26 1979-04-16 Hitachi Ltd Blading structure for axial-flow fluid machine
DE2835349C2 (en) * 1978-08-11 1979-12-20 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Adjustable grille for highly loaded compressors, especially of gas turbine engines
ATE196042T1 (en) 1996-02-07 2000-09-15 Schroecker Rainer BATTERY-POWERED SMALL ELECTRICAL APPLIANCE
DE59704501D1 (en) 1996-03-28 2001-10-11 Mtu Aero Engines Gmbh Airfoil blade
GB2339244B (en) * 1998-06-19 2002-12-18 Rolls Royce Plc A variable camber vane
US6283705B1 (en) * 1999-02-26 2001-09-04 Allison Advanced Development Company Variable vane with winglet
DE19913269A1 (en) * 1999-03-24 2000-09-28 Asea Brown Boveri Turbine blade
JP2001271602A (en) * 2000-03-27 2001-10-05 Honda Motor Co Ltd Gas turbine engine
GB0323909D0 (en) * 2003-10-11 2003-11-12 Rolls Royce Plc Turbine blades
EP1591624A1 (en) * 2004-04-27 2005-11-02 Siemens Aktiengesellschaft Compressor blade and compressor.
DE102004026386A1 (en) 2004-05-29 2005-12-22 Mtu Aero Engines Gmbh Airfoil of a turbomachine and turbomachine
WO2006053579A1 (en) * 2004-11-16 2006-05-26 Honeywell International Inc. Variable nozzle turbocharger
US7134842B2 (en) * 2004-12-24 2006-11-14 General Electric Company Scalloped surface turbine stage
US7407369B2 (en) * 2004-12-29 2008-08-05 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method
US7220100B2 (en) * 2005-04-14 2007-05-22 General Electric Company Crescentic ramp turbine stage
ITMI20060341A1 (en) * 2006-02-27 2007-08-28 Nuovo Pignone Spa SHOVEL OF A ROTOR OF A NON-STAGE OF A COMPRESSOR
US8366399B2 (en) * 2006-05-02 2013-02-05 United Technologies Corporation Blade or vane with a laterally enlarged base
US7527477B2 (en) * 2006-07-31 2009-05-05 General Electric Company Rotor blade and method of fabricating same

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2011015193A2 *

Also Published As

Publication number Publication date
CN102472111A (en) 2012-05-23
WO2011015193A3 (en) 2011-09-15
US9011081B2 (en) 2015-04-21
US20120128480A1 (en) 2012-05-24
CN102472111B (en) 2017-03-01
EP2462320B1 (en) 2016-10-12
WO2011015193A2 (en) 2011-02-10
DE102009036406A1 (en) 2011-02-10

Similar Documents

Publication Publication Date Title
EP2462320B1 (en) Blade
EP2304186B1 (en) Axial turbomachine with low tip leakage losses
DE102006057063B3 (en) Stator stage of an axial compressor of a turbomachine with cross blades to increase efficiency
DE112006001614B4 (en) A blade
EP2356321B1 (en) Turbo engine
EP2696029B1 (en) Blade row with side wall contours and fluid flow engine
WO2007042522A1 (en) Turbo-machine blade
EP2478186B1 (en) Rotor of a turbomachine
EP2725194A1 (en) Turbine rotor blade of a gas turbine
DE102009013399A1 (en) Tandem blade design
EP1923567A2 (en) Rotor blade and wind turbine
DE102007020025A1 (en) Shape of a gas channel in an axial flow gas turbine engine
EP2746534B1 (en) Stator and/or rotor stage of a turbomachine and corresponding gas turbine
EP2846000B1 (en) Vane ring of a gas turbine
EP2558685A2 (en) Guide blade of a turbomachine
EP3431708B1 (en) Flow assembly, corresponding turbomachine and use
WO2013020643A1 (en) Component
EP2827003B1 (en) Gas turbine compressor guide vane assembly
WO2011147401A1 (en) Blade of a turbomachine, having passive boundary layer control
EP2526263A2 (en) Housing system for an axial turbomachine
AT525734B1 (en) vane
DE102009006209A1 (en) Charger i.e. exhaust gas turbocharger, for motor vehicle, has guide vanes with profile in sectional plane arranged perpendicular to rotary axle, where profile has profile center line with turning points
EP1698759B1 (en) Rotor end piece
EP3460187B1 (en) Blade for a turbomachine
WO2010000229A2 (en) Blade cascade for a flow engine and flow engine comprising said blade cascade

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20120116

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MTU AERO ENGINES AG

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160422

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 836714

Country of ref document: AT

Kind code of ref document: T

Effective date: 20161015

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502010012566

Country of ref document: DE

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20161012

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170113

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170112

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170212

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170213

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502010012566

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 8

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170112

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

26N No opposition filed

Effective date: 20170713

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170831

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170831

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170831

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170805

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170805

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170831

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 836714

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170805

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170805

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20100805

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20161012

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161012

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230824

Year of fee payment: 14

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230821

Year of fee payment: 14

Ref country code: DE

Payment date: 20230822

Year of fee payment: 14