EP1774179B1 - Compressor blade - Google Patents

Compressor blade Download PDF

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Publication number
EP1774179B1
EP1774179B1 EP05767976A EP05767976A EP1774179B1 EP 1774179 B1 EP1774179 B1 EP 1774179B1 EP 05767976 A EP05767976 A EP 05767976A EP 05767976 A EP05767976 A EP 05767976A EP 1774179 B1 EP1774179 B1 EP 1774179B1
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EP
European Patent Office
Prior art keywords
blade
sealing lip
profile
compressor
side wall
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.)
Active
Application number
EP05767976A
Other languages
German (de)
French (fr)
Other versions
EP1774179A1 (en
Inventor
Christian Cornelius
Bernhard Küsters
Stephan Mais
Andreas Peters
Achim Schirrmacher
Lutz Stephan
Bernd Van Den Toorn
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Siemens AG
Original Assignee
Siemens AG
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Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP05767976A priority Critical patent/EP1774179B1/en
Priority to PL05767976T priority patent/PL1774179T3/en
Publication of EP1774179A1 publication Critical patent/EP1774179A1/en
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Publication of EP1774179B1 publication Critical patent/EP1774179B1/en
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Classifications

    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—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
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
    • 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 invention relates to a compressor blade as in the preamble of Anspuchs. 1
  • Such a compressor blade is for example from the DE-A-1428165 or the JP-A-2000130102 known.
  • a turbine blade with a molded on the blade sealing lip is out of US 6,039,531 known.
  • the sealing lip runs centrally between the suction side and the pressure side at the profile tip.
  • a compressor blade which has at its free end of the blade profile on an end face on which a lip-like rib extends in the region of the suction side of the blade profile from a leading edge to a trailing edge.
  • the rib of the compressor blade serves as a sealing element in the operation of the compressor to reduce the peak gap losses in the compressor that occur between the blade tip and the confinement of the compressor duct.
  • the object of the invention is therefore to provide an aerodynamically improved compressor blade, without reducing the sealing effect of the sealing lip.
  • the invention is based on the recognition that a sealing lip of a compressor blade according to the invention is produced inexpensively by a three-axis milling device, although due to the geometrically demanding, aerodynamic shape of the blade profile of the compressor blade this is produced by means of a five-axis milling device or by precision forging ,
  • the accuracy of the geometry of the sealing lip according to the invention can be checked and controlled more easily than that of a sealing lip, which is executed parallel to the suction side. This leads to a further reduction in manufacturing costs.
  • the height of the sealing lip is at most two percent of the height of the blade profile. Previously, a sealing lip integrally connected to the blade profile had a greater height for manufacturing reasons.
  • the sealing lip has a suction-side side surface and a pressure-side side surface, which run parallel to the main axis. This can be made particularly simple and therefore inexpensive. Above that are the two To manufacture side surfaces so that they also run parallel to the profile center line. Consequently, the side surfaces of the sealing lip are not aerodynamically shaped, that is not inclined to the main axis, such as the contour of the side walls of the blade profile. Furthermore, the sealing lip reduces the tip gap losses across the profile tip.
  • the side surfaces of the sealing lip are connected to each other by means of a rubbing surface, which rubbing surface is perpendicular to the radius of the rotor of the compressor.
  • a cylindrical gap can be formed between the housing or hub components and the compressor blade, which reduces the gap losses.
  • the compressor blade according to the invention can be used in the same way advantageous as a blade as well as a vane.
  • At least one side surface of the sealing lip is connected to the end face over a transition radius, whose size is at most 25 percent of the height of the sealing lip. Due to the particularly small transition radius, an extremely low sealing lip height can be achieved.
  • the production of such a transition radius is cost-effective together with the sealing lip by means of an end mill on a three-axis milling device.
  • previously highly curved blade profiles with a milled with a large transition radius sealing lip especially in the central region between the leading edge and trailing edge on a larger sealing lip height than in the region of the inflow and outflow, which previously led to flow disturbances. This convex course of the sealing lip or its height can be avoided with much smaller transition radii.
  • FIG. 1 a gas turbine 1 with a rotatably mounted about a rotational axis 3 rotor fifth
  • the gas turbine 1 has an intake chamber 7, a compressor 9, a toroidal annular combustion chamber 11 and a turbine unit 13.
  • guide vanes 15 and blades 17 are each arranged in rings.
  • a blade ring 19 follows a stator blade ring 21.
  • the blades 17 are mounted on the rotor 5 by means of rotor discs 23, whereas the guide blades 15 are fixedly mounted on the housing 25.
  • Wreaths 21 of guide vanes 15 are likewise arranged in the turbine unit 13, which, viewed in the direction of the flow medium, is followed by a ring of rotor blades 17.
  • the respective blade profiles of the guide vanes 15 and of the rotor blades 17 extend radially in an annular flow channel 27.
  • air 29 is sucked through the intake manifold 7 and compressed by the compressor.
  • the compressed air is guided to the burners 33, which lie on a ring at the annular combustion chamber 11 are provided.
  • the compressed air 29 is mixed with a fuel 35, which mixture in the annular combustion chamber 11 is burned to a hot gas 37.
  • the hot gas 37 flows through the flow channel 27 of the turbine unit 13 past guide vanes 15 and blades 17.
  • the hot gas 37 relaxes on the blades 17 of the turbine unit 13 to perform work.
  • the rotor 5 of the gas turbine 1 is set in a rotational movement, which serves to drive the compressor 9 and to drive a work machine, not shown.
  • FIG. 2 shows a compressor blade 50 in a perspective view.
  • the compressor blade 50 has along a main axis 53 a blade root 55, a platform region 57 with a platform 59 and a blade profile 61.
  • the blade profile 61 is flowed around during operation of the compressor 9 of air 29, which the blade profile 61 on a leading edge 63 on and flows from a trailing edge 65.
  • the blade profile 61 is formed by a pressure side wall 67 and by a suction side wall 69 and has a blade height H extending in the direction of the main axis 53.
  • a profile center line 71 which has at each point of its course a vertical, which perpendicular 74 both the suction side wall 69 and the pressure side wall 67 intersects.
  • a first distance A between the intersections of the vertical 74 with the profile center line 71 and the pressure side wall 67 with the vertical 74 is identical to a second distance B, which between the intersections of the profile center line 71 with the vertical 74 and the suction side wall 69 with the vertical 74, is present.
  • the blade profile 61 on its side facing away from the platform 59 profile tip 72 on an end face 73 on which a sealing lip 75 is arranged.
  • the sealing lip 75 is narrower than the blade profile 61, extending from the leading edge 63 to the trailing edge 65 and extends along the profile center line 71, ie at a distance between the contour of the suction side wall 69 and the pressure side wall 67th
  • the sealing lip 75 also called squealer edge, has a first side surface 77 facing the pressure side wall 67 and a second side surface 79 facing the suction side wall 69.
  • the curved side surfaces 77, 79 of the sealing lip 75 are parallel to the main axis 53 and also parallel to the profile center line 71, whereas the suction side wall 69 of the blade profile 61 and the pressure side wall 67 of the blade profile 61 inclined for aerodynamic reasons, i. obliquely, to the main axis 53 run. Compared with a blade of the prior art, a simplified production of the sealing lip 75 can thereby be achieved.
  • the sealing lip 75 has a parallel to the main axis 53 directed height HL, which between the end face. 73 of the blade profile and the abraded surface 81 is measured and is part of the blade profile height H.
  • FIG. 3 shows a detailed view of a squealer according to the invention. It is clearly evident here that the sealing lip 75 extends centrally between the suction side wall 69 and the pressure side wall 67 from the leading edge 63 to the trailing edge 65, with side surfaces 77, 79 aligned parallel to the main axis 53 and the profile center line 71.
  • the side surfaces 77, 79 pass over a transition radius R in the end face 73, which is advantageously at most 25 percent of the sealing lip height H1. As a result, a particularly low sealing lip can be produced, whose height HL is at most 2 percent of the blade height H.
  • the new geometry and position of the sealing lip 75 eliminates error-prone and costly manufacturing steps. As a result, both the manufacturing costs and the reject rate of the manufactured compressor blades 50 can be reduced. A deterioration of the top gap losses across the radial gap between compressor blade 50 and inner housing does not occur, as well as flow losses due to the insignificantly reduced, maximum possible aerodynamically effective profile surface.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A sealing lip (75) extends along the profile center line of a profile, spaced apart from a suction side wall (69) and pressure side wall (67). The sealing lip has a suction-side side surface (79) and a pressure-side side-surface, which extend parallel to the main axis (53). An independent claim is included for a compressor for a gas turbine.

Description

Die Erfindung betrifft eine Verdichterschaufel wie im Oberbegriff der Anspuchs 1.The invention relates to a compressor blade as in the preamble of Anspuchs. 1

Eine solche verdichter Schaufel ist Z.B aus der DE-A-1428165 oder der JP-A-2000130102 bekannt.Such a compressor blade is for example from the DE-A-1428165 or the JP-A-2000130102 known.

Eine Turbinenschaufel mit einer an dem Schaufelblatt angegossenen Dichtlippe ist aus der US 6,039,531 bekannt. Die Dichtlippe verläuft mittig zwischen Saugseite und Druckseite an der Profilspitze.A turbine blade with a molded on the blade sealing lip is out of US 6,039,531 known. The sealing lip runs centrally between the suction side and the pressure side at the profile tip.

Außerdem ist aus der JP-A-2000130102 eine Verdichterlaufschaufel, die an ihrem freien Ende des Schaufelprofils eine Stirnfläche auf weist, an der eine lippenartige Rippe im Bereich der Saugseite des Schaufelprofils von einer Anströmkante zu einer Abströmkante verläuft. Die Rippe der Verdichterlaufschaufel dient beim Betrieb des Verdichters als Dichtelement, um die Spitzenspaltverluste im Verdichter, welche zwischen der Schaufelspitze und der Begrenzung des Verdichterkanals auftreten, zu verringern.Moreover, from the JP-A-2000130102 a compressor blade, which has at its free end of the blade profile on an end face on which a lip-like rib extends in the region of the suction side of the blade profile from a leading edge to a trailing edge. The rib of the compressor blade serves as a sealing element in the operation of the compressor to reduce the peak gap losses in the compressor that occur between the blade tip and the confinement of the compressor duct.

Die Herstellung einer solchen Dichtrippe an der Saugseite der Schaufel mit einer Anstreifkante kann insbesondere bei stark randzonenkorrigierten, d.h. im Spitzenbereich besonders stark gekrümmten, Schaufeln kostenintensiv sein, da die Herstellung bzw. die Konturfräsung mittels eines Fünf-Achs-Fräsers durchgeführt wird. Nach dem Fräsen der Saugseitenwand und der Dichtlippengeometrie wird die Schaufel saugseitig manuell geschliffen, um die geforderte Oberflächengüte zu erzielen. Diese manuelle Bearbeitung führt zu häufigen Fertigungsfehlern mit entsprechenden Nachteilen, wie z.B. Ausschuss bzw. nicht optimalen Konturen.The production of such a sealing rib on the suction side of the blade with a squealer edge may be particularly in the case of highly edge-zone corrected, i. Particularly curved blades in the tip area must be cost-intensive, since the production or contour milling is carried out by means of a five-axis milling cutter. After milling the suction side wall and the sealing lip geometry, the blade is ground manually on the suction side in order to achieve the required surface quality. This manual processing leads to frequent manufacturing errors with corresponding disadvantages, such as Committee or non-optimal contours.

Aufgabe der Erfindung ist es daher, eine aerodynamisch verbesserte Verdichterschaufel anzugeben, ohne die Dichtwirkung der Dichtlippe zu vermindern.The object of the invention is therefore to provide an aerodynamically improved compressor blade, without reducing the sealing effect of the sealing lip.

Die auf die Verdichterschaufel bezogene Aufgabe wird durch die Merkmale des Anspruchs 1 gelöst.The task related to the compressor blade is solved by the features of claim 1.

Die Erfindung geht von der Erkenntnis aus, dass eine erfindungsgemäße Dichtlippe einer Verdichterschaufel kostengünstig durch eine Drei-Achs-Fräseinrichtung hergestellt wird, obwohl aufgrund der geometrisch anspruchsvollen, aerodynamischen Form des Schaufelprofils der Verdichterschaufel dieses mittels einer Fünf-Achs-Fräseinrichtung oder durch Präzisionsschmieden hergestellt wird.The invention is based on the recognition that a sealing lip of a compressor blade according to the invention is produced inexpensively by a three-axis milling device, although due to the geometrically demanding, aerodynamic shape of the blade profile of the compressor blade this is produced by means of a five-axis milling device or by precision forging ,

Zur Herstellung kann somit ein einfacheres Herstellungsverfahren und/oder dafür eine in der Benutzung kostengünstigere Maschine eingesetzt werden. Insbesondere bei im Spitzenbereich vergleichsweise stark gekrümmten Verdichterschaufeln ist dies von Vorteil.Thus, a simpler manufacturing process and / or a more cost-effective machine can be used for the production. This is advantageous particularly in the case of comparatively heavily curved compressor blades in the tip region.

Zudem entfallen fehleranfällige und kostenintensive Fertigungsschritte, wie beispielsweise eine manuelle Nachbearbeitung, ersatzlos. Der Herstellungsprozess verkürzt sich. Ferner führt der Wegfall der manuellen Nachbearbeitung zu einer wesentlich höheren Prozesssicherheit.In addition, error-prone and cost-intensive production steps, such as manual post-processing, are eliminated without substitution. The manufacturing process is shortened. Furthermore, the omission of manual post-processing leads to a significantly higher process reliability.

Auch kann die Genauigkeit der erfindungsgemäßen Geometrie der Dichtlippe einfacher überprüft und kontrolliert werden, als diejenige einer Dichtlippe, die parallel zur Saugseite ausgeführt ist. Dies führt zu einer weiteren Herstellungskostenreduzierung.Also, the accuracy of the geometry of the sealing lip according to the invention can be checked and controlled more easily than that of a sealing lip, which is executed parallel to the suction side. This leads to a further reduction in manufacturing costs.

Erfindungsgemäß beträgt die Höhe der Dichtlippe maximal zwei Prozent der Höhe des Schaufelprofils. Bisher wies eine mit dem Schaufelprofil einstückig verbundene Dichtlippe eine größere Höhe aus fertigungstechnischen Gründen auf.According to the invention, the height of the sealing lip is at most two percent of the height of the blade profile. Previously, a sealing lip integrally connected to the blade profile had a greater height for manufacturing reasons.

Berechnungen zeigen, dass die neu gewählte Größe der Dichtlippe an der Stirnseitenfläche keinen negativen Einfluss auf die aerodynamische Leistungsfähigkeit des Schaufelprofils hat, vielmehr vergrößert sich aufgrund der niedrigeren Dichtlippe die aerodynamisch optimierte, wirksame Fläche des Schaufelprofils, was bei einem mit der erfindungsgemäßen Verdichterschaufel bestücktem Verdichter zu einer verbesserten Aerodynamik, zu geringeren Strömungsstörungen im Spitzenbereich des Schaufelprofils und insgesamt zu einem gesteigerten Wirkungsgrad führt.Calculations show that the newly selected size of the sealing lip on the front side surface has no negative influence on the aerodynamic performance of the blade profile, but increases due to the lower sealing lip aerodynamically optimized, effective area of the blade profile, which in a populated with the compressor blade according to the invention compressor Improved aerodynamics, lower flow disturbances in the tip region of the blade profile and overall leads to increased efficiency.

Die Dichtlippe weist eine saugseitige Seitenfläche und eine druckseitige Seitenfläche auf, welche parallel zur Hauptachse verlaufen. Diese kann besonders einfach und somit kostengünstig hergestellt werden. Darüber sind die beiden Seitenflächen so zu fertigen, dass sie auch parallel zur Profilmittenlinie verlaufen. Folglich sind die Seitenflächen der Dichtlippe nicht aerodynamisch geformt, d.h. nicht zur Hauptachse geneigt, wie die Kontur der Seitenwände des Schaufelprofils. Weiterhin vermindert die Dichtlippe die Spitzenspaltverluste über die Profilspitze hinweg.The sealing lip has a suction-side side surface and a pressure-side side surface, which run parallel to the main axis. This can be made particularly simple and therefore inexpensive. Above that are the two To manufacture side surfaces so that they also run parallel to the profile center line. Consequently, the side surfaces of the sealing lip are not aerodynamically shaped, that is not inclined to the main axis, such as the contour of the side walls of the blade profile. Furthermore, the sealing lip reduces the tip gap losses across the profile tip.

Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben.Advantageous embodiments are specified in the subclaims.

In einer vorteilhaften Ausgestaltung sind die Seitenflächen der Dichtlippe mittels einer Anstreiffläche miteinander verbunden, welche Anstreiffläche senkrecht zu dem Radius des Rotors des Verdichters steht. Somit kann zwischen Gehäuse- bzw. Nabenbauteilen und der Verdichterschaufel ein zylindrischer Spalt gebildet werden, welcher die Spaltverluste reduziert.In an advantageous embodiment, the side surfaces of the sealing lip are connected to each other by means of a rubbing surface, which rubbing surface is perpendicular to the radius of the rotor of the compressor. Thus, a cylindrical gap can be formed between the housing or hub components and the compressor blade, which reduces the gap losses.

Die erfindungsgemäße Verdichterschaufel lässt sich in gleicher Weise vorteilhaft als Laufschaufel wie auch als Leitschaufel verwenden.The compressor blade according to the invention can be used in the same way advantageous as a blade as well as a vane.

Besonders bevorzugt ist die Ausgestaltung, bei der mindestens eine Seitenfläche der Dichtlippe mit der Stirnseitenfläche über einen Übergangsradius miteinander verbunden ist, dessen Größe maximal 25 Prozent der Höhe der Dichtlippe beträgt. Aufgrund des besonders kleinen Übergangsradius kann eine äußerst niedrige Dichtlippenhöhe erzielt werden. Die Herstellung eines solchen Übergangsradius erfolgt kostengünstig zusammen mit der Dichtlippe mittels eines Schaftfräsers auf einer Drei-Achs-Fräseinrichtung. Dagegen wiesen bisher stark gekrümmte Schaufelprofile mit einer mit einem großen Übergangsradius gefrästen Dichtlippe besonders im mittleren Bereich zwischen Anströmkante und Abströmkante eine größere Dichtlippenhöhe auf als im Bereich der Anström- und Abströmkante, was bisher zu Strömungsstörungen führte. Dieser konvexe Verlauf der Dichtlippe bzw. deren Höhe kann mit wesentlich kleineren Übergangsradien vermieden werden.Particularly preferred is the embodiment in which at least one side surface of the sealing lip is connected to the end face over a transition radius, whose size is at most 25 percent of the height of the sealing lip. Due to the particularly small transition radius, an extremely low sealing lip height can be achieved. The production of such a transition radius is cost-effective together with the sealing lip by means of an end mill on a three-axis milling device. In contrast, previously highly curved blade profiles with a milled with a large transition radius sealing lip especially in the central region between the leading edge and trailing edge on a larger sealing lip height than in the region of the inflow and outflow, which previously led to flow disturbances. This convex course of the sealing lip or its height can be avoided with much smaller transition radii.

Die Erfindung wird anhand einer Zeichnung näher erläutert. Es zeigen:

FIG 1
einen Längsteilschnitt durch eine Gasturbine mit einem Verdichter,
FIG 2
eine erfindungsgemäße Verdichterschaufel in einer perspektivischen Ansicht und
FIG 3
eine Detailansicht einer Anstreiffläche einer ver- dichterschaufel.
The invention will be explained in more detail with reference to a drawing. Show it:
FIG. 1
a partial longitudinal section through a gas turbine with a compressor,
FIG. 2
a compressor blade according to the invention in a perspective view and
FIG. 3
a detailed view of a rubbing surface of a compressor blade.

Verdichter und Gasturbinen sowie deren Arbeitsweisen sind allgemein bekannt. Hierzu zeigt FIG 1 eine Gasturbine 1 mit einem um eine Rotationsachse 3 drehbar gelagerten Rotor 5.Compressors and gas turbines and their operations are well known. This shows FIG. 1 a gas turbine 1 with a rotatably mounted about a rotational axis 3 rotor fifth

Entlang der Rotationsachse 3 weist die Gasturbine 1 ein Ansaughaus 7, einen Verdichter 9, eine torusartige Ringbrennkammer 11 und eine Turbineneinheit 13 auf.Along the rotation axis 3, the gas turbine 1 has an intake chamber 7, a compressor 9, a toroidal annular combustion chamber 11 and a turbine unit 13.

Sowohl im Verdichter 9 als auch in der Turbineneinheit 13 sind Leitschaufeln 15 und Laufschaufeln 17 jeweils in Kränzen angeordnet. Im Verdichter 9 folgt dabei einem Laufschaufelkranz 19 ein Leitschaufelkranz 21. Die Lauf schaufeln 17 sind dabei am Rotor 5 mittels Rotorscheiben 23 befestigt, wohingegen die Leitschaufeln 15 feststehend am Gehäuse 25 montiert sind.Both in the compressor 9 and in the turbine unit 13 guide vanes 15 and blades 17 are each arranged in rings. In the compressor 9 while a blade ring 19 follows a stator blade ring 21. The blades 17 are mounted on the rotor 5 by means of rotor discs 23, whereas the guide blades 15 are fixedly mounted on the housing 25.

Ebenso sind in der Turbineneinheit 13 Kränze 21 aus Leitschaufeln 15 angeordnet, denen jeweils in Richtung des Strömungsmediums gesehen ein Kranz aus Laufschaufeln 17 folgt.Wreaths 21 of guide vanes 15 are likewise arranged in the turbine unit 13, which, viewed in the direction of the flow medium, is followed by a ring of rotor blades 17.

Die jeweiligen Schaufelprofile der Leitschaufeln 15 und der Laufschaufeln 17 erstrecken sich dabei strahlenförmig in einem ringförmigen Strömungskanal 27.The respective blade profiles of the guide vanes 15 and of the rotor blades 17 extend radially in an annular flow channel 27.

Beim Betrieb der Gasturbine 1 wird vom Verdichter 9 Luft 29 durch das Ansaughaus 7 angesaugt und verdichtet. Am Austritt 31 des Verdichters 9 wird die verdichtete Luft zu den Brennern 33 geführt, welche auf einem Ring liegend an der Ringbrennkammer 11 vorgesehen sind. In den Brennern wird die verdichtete Luft 29 mit einem Brennmittel 35 vermischt, welches Gemisch in der Ringbrennkammer 11 zu einem Heißgas 37 verbrannt wird. Anschließend strömt das Heißgas 37 durch den Strömungskanal 27 der Turbineneinheit 13 an Leitschaufeln 15 und Laufschaufeln 17 vorbei. Dabei entspannt sich das Heißgas 37 an den Laufschaufeln 17 der Turbineneinheit 13 arbeitsleistend. Hierdurch wird der Rotor 5 der Gasturbine 1 in eine Drehbewegung versetzt, welche zum Antrieb des Verdichters 9 und zum Antrieb einer nicht dargestellten Arbeitsmaschine dient.During operation of the gas turbine 1 9 air 29 is sucked through the intake manifold 7 and compressed by the compressor. At the outlet 31 of the compressor 9, the compressed air is guided to the burners 33, which lie on a ring at the annular combustion chamber 11 are provided. In the burners, the compressed air 29 is mixed with a fuel 35, which mixture in the annular combustion chamber 11 is burned to a hot gas 37. Subsequently, the hot gas 37 flows through the flow channel 27 of the turbine unit 13 past guide vanes 15 and blades 17. In this case, the hot gas 37 relaxes on the blades 17 of the turbine unit 13 to perform work. As a result, the rotor 5 of the gas turbine 1 is set in a rotational movement, which serves to drive the compressor 9 and to drive a work machine, not shown.

FIG 2 zeigt eine Verdichterschaufel 50 in einer perspektivischen Ansicht. Die Verdichterschaufel 50 weist entlang einer Hauptachse 53 einen Schaufelfuß 55, einen Plattformbereich 57 mit einer Plattform 59 und ein Schaufelprofil 61 auf. Das Schaufelprofil 61 wird beim Betrieb des Verdichters 9 von Luft 29 umströmt, die das Schaufelprofil 61 an einer Anströmkante 63 an- und von einer Abströmkante 65 abströmt. Das Schaufelprofil 61 wird von einer Druckseitenwand 67 und von einer Saugseitenwand 69 gebildet und weist eine in Richtung der Hauptachse 53 verlaufende Schaufelhöhe H auf. FIG. 2 shows a compressor blade 50 in a perspective view. The compressor blade 50 has along a main axis 53 a blade root 55, a platform region 57 with a platform 59 and a blade profile 61. The blade profile 61 is flowed around during operation of the compressor 9 of air 29, which the blade profile 61 on a leading edge 63 on and flows from a trailing edge 65. The blade profile 61 is formed by a pressure side wall 67 and by a suction side wall 69 and has a blade height H extending in the direction of the main axis 53.

Von der Anströmkante 63 zur Abströmkante 65 verläuft eine Profilmittenlinie 71, die an jeder Stelle ihres Verlaufes eine Senkrechte aufweist, welche Senkrechte 74 sowohl die Saugseitenwand 69 als auch die Druckseitenwand 67 schneidet. Dabei ist jeweils ein erster Abstand A zwischen den Schnittpunkten der Senkrechten 74 mit der Profilmittenlinie 71 und der Druckseitenwand 67 mit der Senkrechten 74 identisch zu einem zweiten Abstand B, welcher zwischen den Schnittpunkten der Profilmittenlinie 71 mit der Senkrechten 74 und der Saugseitenwand 69 mit der Senkrechten 74, vorliegt.From the leading edge 63 to the trailing edge 65 runs a profile center line 71 which has at each point of its course a vertical, which perpendicular 74 both the suction side wall 69 and the pressure side wall 67 intersects. In each case, a first distance A between the intersections of the vertical 74 with the profile center line 71 and the pressure side wall 67 with the vertical 74 is identical to a second distance B, which between the intersections of the profile center line 71 with the vertical 74 and the suction side wall 69 with the vertical 74, is present.

Ferner weist das Schaufelprofil 61 an seiner der Plattform 59 abgewandten Profilspitze 72 eine Stirnseitenfläche 73 auf, an der eine Dichtlippe 75 angeordnet ist. Die Dichtlippe 75 ist schmaler als das Schaufelprofil 61, erstreckt sich von Anströmkante 63 zur Abströmkante 65 und verläuft entlang der Profilmittenlinie 71, also im Abstand zwischen der Kontur der Saugseitenwand 69 und der Druckseitenwand 67.Furthermore, the blade profile 61 on its side facing away from the platform 59 profile tip 72 on an end face 73 on which a sealing lip 75 is arranged. The sealing lip 75 is narrower than the blade profile 61, extending from the leading edge 63 to the trailing edge 65 and extends along the profile center line 71, ie at a distance between the contour of the suction side wall 69 and the pressure side wall 67th

Die Dichtlippe 75, auch Anstreifkante genannt, weist eine der Druckseitenwand 67 zugewandte erste Seitenfläche 77 und eine der Saugseitenwand 69 zugewandte zweite Seitenfläche 79 auf.The sealing lip 75, also called squealer edge, has a first side surface 77 facing the pressure side wall 67 and a second side surface 79 facing the suction side wall 69.

Die gekrümmten Seitenflächen 77, 79 der Dichtlippe 75 verlaufen parallel zur Hauptachse 53 und auch parallel zur Profilmittenlinie 71, wohingegen die Saugseitenwand 69 des Schaufelprofils 61 als auch die Druckseitenwand 67 des Schaufelprofils 61 aus aerodynamischen Gründen geneigt, d.h. schräg, zur Hauptachse 53 verlaufen. Verglichen mit einer Schaufel aus dem Stand der Technik kann hierdurch eine vereinfachte Herstellung der Dichtlippe 75 erzielt werden.The curved side surfaces 77, 79 of the sealing lip 75 are parallel to the main axis 53 and also parallel to the profile center line 71, whereas the suction side wall 69 of the blade profile 61 and the pressure side wall 67 of the blade profile 61 inclined for aerodynamic reasons, i. obliquely, to the main axis 53 run. Compared with a blade of the prior art, a simplified production of the sealing lip 75 can thereby be achieved.

Außerdem sind die Seitenflächen 77, 79 der Dichtlippe 75 mittels einer Anstreiffläche 81, miteinander verbunden, welche Anstreiffläche 81 senkrecht zu dem Radius des Rotors 5 des Verdichters 9 steht.In addition, the side surfaces 77, 79 of the sealing lip 75 by means of a abradable surface 81, connected to each other, which abrading surface 81 is perpendicular to the radius of the rotor 5 of the compressor 9.

Die Dichtlippe 75 weist eine parallel zur Hauptachse 53 gerichtete Höhe HL auf, welche zwischen der Stirnseitenfläche . 73 des Schaufelprofils und der Anstreiffläche 81 gemessen wird und Teil der Schaufelprofilhöhe H ist.The sealing lip 75 has a parallel to the main axis 53 directed height HL, which between the end face. 73 of the blade profile and the abraded surface 81 is measured and is part of the blade profile height H.

FIG 3 zeigt eine Detailansicht einer erfindungsgemäßen Anstreifkante. Hierbei ist klar ersichtlich, dass die Dichtlippe 75 mittig zwischen der Saugseitenwand 69 und der Druckseitenwand 67 von der Anströmkante 63 zur Abströmkante 65 verläuft, mit parallel zur Hauptachse 53 und zur Profilmittenlinie 71 ausgerichteten Seitenflächen 77, 79. FIG. 3 shows a detailed view of a squealer according to the invention. It is clearly evident here that the sealing lip 75 extends centrally between the suction side wall 69 and the pressure side wall 67 from the leading edge 63 to the trailing edge 65, with side surfaces 77, 79 aligned parallel to the main axis 53 and the profile center line 71.

Die Seitenflächen 77, 79 gehen über einen Übergangsradius R in die Stirnseitenfläche 73 über, welcher vorteilhafterweise maximal 25 Prozent der Dichtlippenhöhe H1, beträgt. Hierdurch kann eine besonders niedrige Dichtlippe hergestellt werden, deren Höhe HL maximal 2 Prozent der Schaufelblatthöhe H beträgt.The side surfaces 77, 79 pass over a transition radius R in the end face 73, which is advantageously at most 25 percent of the sealing lip height H1. As a result, a particularly low sealing lip can be produced, whose height HL is at most 2 percent of the blade height H.

Durch die neue Geometrie und Position der Dichtlippe 75 entfallen fehleranfällige und kostenintensive Fertigungsschritte. Hierdurch können sowohl die Fertigungskosten als auch die Ausschussrate der hergestellten Verdichterschaufeln 50 reduziert werden. Eine Verschlechterung der Spitzenspaltverluste über den Radialspalt zwischen Verdichterschaufel 50 und Innengehäuse tritt dabei nicht auf, ebenso wenig wie Strömungsverluste aufgrund der unwesentlich verringerten, maximal möglichen aerodynamisch wirksamen Profilfläche.The new geometry and position of the sealing lip 75 eliminates error-prone and costly manufacturing steps. As a result, both the manufacturing costs and the reject rate of the manufactured compressor blades 50 can be reduced. A deterioration of the top gap losses across the radial gap between compressor blade 50 and inner housing does not occur, as well as flow losses due to the insignificantly reduced, maximum possible aerodynamically effective profile surface.

Claims (3)

  1. Compressor blade (50) for a compressor (9),
    which blade, along a main axis (53), has a blade root (55), a platform section (59) and a blade profile (61), with a profile tip (72), adjoining the platform section,
    which blade profile (61) is formed by a convex suction side wall (69) and a concave pressure side wall (67) opposite the suction side wall (69),
    which walls (67, 69) extend diagonally to the main axis (53), with regard to a flow medium, extend from a leading edge (65) to a trailing edge (65), and between which a profile center line (71) extends in the middle, wherein an end face (73), which is disposed transversely to the main axis (53), is located on the profile tip (72),
    upon which end face a sealing lip (75) extends at least partially from the leading edge (65) to the trailing edge (65), and the blade profile (61), including the sealing lip (74), has a blade profile height (H) which extends in the direction of the main axis (53),
    characterized in that the sealing lip (75) is formed in one piece with the blade profile (61) and extends along the profile center line (71) at a distance from suction side wall (69) and from pressure side wall (67),
    in that the height (HL) of the sealing lip (74) is less than two per cent of the height (H) of the blade profile (61), and in that the sealing lip (75) has a side face (79) on the suction side and a side face (77) on the pressure side, which side faces each extend parallel to the main axis (53) and parallel to the profile center line (71).
  2. Compressor blade (50) according to Claim 1,
    in which the side faces (77, 79) of the sealing lip (75) are interconnected by means of a feathered surface (81), which feathered surface (81) is disposed perpendicularly to the radius of the rotor (5) of the compressor (9).
  3. Compressor blade (50) according to one of Claims 1 or 2, in which at least one side face (77, 79) of the sealing lip (75) is interconnected to the end face (73) by a radius (R), the size of which is at most 25 percent of the height (HL) of the sealing lip (75).
EP05767976A 2004-08-06 2005-06-20 Compressor blade Active EP1774179B1 (en)

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EP05767976A EP1774179B1 (en) 2004-08-06 2005-06-20 Compressor blade
PL05767976T PL1774179T3 (en) 2004-08-06 2005-06-20 Compressor blade

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04018728A EP1624192A1 (en) 2004-08-06 2004-08-06 Impeller blade for axial compressor
PCT/EP2005/052848 WO2006015899A1 (en) 2004-08-06 2005-06-20 Compressor blade and production and use of a compressor blade
EP05767976A EP1774179B1 (en) 2004-08-06 2005-06-20 Compressor blade

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EP1774179A1 EP1774179A1 (en) 2007-04-18
EP1774179B1 true EP1774179B1 (en) 2011-08-03

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EP04018728A Withdrawn EP1624192A1 (en) 2004-08-06 2004-08-06 Impeller blade for axial compressor
EP05767976A Active EP1774179B1 (en) 2004-08-06 2005-06-20 Compressor blade

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US (1) US8951008B2 (en)
EP (2) EP1624192A1 (en)
JP (1) JP4660547B2 (en)
CN (1) CN100523519C (en)
AT (1) ATE519036T1 (en)
CA (1) CA2575948C (en)
ES (1) ES2370402T3 (en)
MX (1) MX2007001443A (en)
PL (1) PL1774179T3 (en)
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WO (1) WO2006015899A1 (en)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4830812B2 (en) * 2006-11-24 2011-12-07 株式会社Ｉｈｉ Compressor blade
GB0807358D0 (en) * 2008-04-23 2008-05-28 Rolls Royce Plc Fan blade
DE102010034604A1 (en) * 2010-08-13 2012-02-16 Ziehl-Abegg Ag Impeller for a fan
CN102536897B (en) * 2010-12-29 2015-04-22 台达电子工业股份有限公司 Fan and impeller thereof
FR2972380A1 (en) 2011-03-11 2012-09-14 Alstom Technology Ltd METHOD FOR MANUFACTURING STEAM TURBINE DIAPHRAGM
US8790088B2 (en) * 2011-04-20 2014-07-29 General Electric Company Compressor having blade tip features
RU2476729C1 (en) * 2011-07-29 2013-02-27 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Gas turbine axial compressor wheel
EP2798175A4 (en) * 2011-12-29 2017-08-02 Rolls-Royce North American Technologies, Inc. Gas turbine engine and turbine blade
JP5555727B2 (en) 2012-01-23 2014-07-23 川崎重工業株式会社 Axial flow compressor blade manufacturing method
EP2696031B1 (en) 2012-08-09 2015-10-14 MTU Aero Engines AG Blade for a flow machine engine and corresponding flow machine engine.
CN103883361B (en) * 2012-12-20 2016-05-04 中航商用航空发动机有限责任公司 Turbo blade
CN103925244B (en) * 2014-04-02 2017-03-15 清华大学 A kind of big flow high load axial compressor and fan for 300MW F level heavy duty gas turbines
US20160238021A1 (en) * 2015-02-16 2016-08-18 United Technologies Corporation Compressor Airfoil
US10934847B2 (en) * 2016-04-14 2021-03-02 Mitsubishi Power, Ltd. Steam turbine rotor blade, steam turbine, and method for manufacturing steam turbine rotor blade
CN106271469B (en) * 2016-08-29 2018-03-30 中航动力股份有限公司 A kind of processing method of the more cavity thin-wall compressor blades of elongated hollow
CN111219362A (en) * 2018-11-27 2020-06-02 中国航发商用航空发动机有限责任公司 Axial compressor blade, axial compressor and gas turbine
CN110076524B (en) * 2019-04-30 2020-07-31 沈阳透平机械股份有限公司 Method for processing static blade runner plate of axial flow compressor
DE102021130682A1 (en) 2021-11-23 2023-05-25 MTU Aero Engines AG Airfoil for a turbomachine

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1428165A1 (en) 1962-12-18 1969-02-20 Licentia Gmbh A method of making an end of a flow machine blade
DE1937395A1 (en) 1969-07-23 1971-02-11 Dettmering Prof Dr Ing Wilhelm Grid to avoid secondary flow
US3854842A (en) * 1973-04-30 1974-12-17 Gen Electric Rotor blade having improved tip cap
US4390320A (en) * 1980-05-01 1983-06-28 General Electric Company Tip cap for a rotor blade and method of replacement
JPS62142805A (en) * 1985-12-18 1987-06-26 Toshiba Corp Moving blade for axial-flow fluid machine
GB9112043D0 (en) * 1991-06-05 1991-07-24 Sec Dep For The Defence A titanium compressor blade having a wear resistant portion
US5476363A (en) * 1993-10-15 1995-12-19 Charles E. Sohl Method and apparatus for reducing stress on the tips of turbine or compressor blades
GB2310897B (en) * 1993-10-15 1998-05-13 United Technologies Corp Method and apparatus for reducing stress on the tips of turbine or compressor blades
JP3137527B2 (en) * 1994-04-21 2001-02-26 三菱重工業株式会社 Gas turbine blade tip cooling system
JP3453268B2 (en) * 1997-03-04 2003-10-06 三菱重工業株式会社 Gas turbine blades
US6219916B1 (en) * 1997-12-19 2001-04-24 United Technologies Corporation Method for linear friction welding and product made by such method
JP2000130102A (en) 1998-10-29 2000-05-09 Ishikawajima Harima Heavy Ind Co Ltd Rotary machine blade tip structure
US6206642B1 (en) * 1998-12-17 2001-03-27 United Technologies Corporation Compressor blade for a gas turbine engine
US6086328A (en) * 1998-12-21 2000-07-11 General Electric Company Tapered tip turbine blade
US6190129B1 (en) * 1998-12-21 2001-02-20 General Electric Company Tapered tip-rib turbine blade
US6059530A (en) * 1998-12-21 2000-05-09 General Electric Company Twin rib turbine blade
JP2001303904A (en) * 2000-04-24 2001-10-31 Mitsubishi Heavy Ind Ltd Gas turbine moving blade
US6672829B1 (en) * 2002-07-16 2004-01-06 General Electric Company Turbine blade having angled squealer tip

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Publication number Publication date
CA2575948C (en) 2010-10-19
JP4660547B2 (en) 2011-03-30
EP1774179A1 (en) 2007-04-18
CA2575948A1 (en) 2006-02-16
WO2006015899A1 (en) 2006-02-16
EP1624192A1 (en) 2006-02-08
MX2007001443A (en) 2007-04-19
CN101035988A (en) 2007-09-12
US8951008B2 (en) 2015-02-10
RU2343322C2 (en) 2009-01-10
CN100523519C (en) 2009-08-05
ATE519036T1 (en) 2011-08-15
US20110044800A1 (en) 2011-02-24
PL1774179T3 (en) 2011-12-30
JP2008509316A (en) 2008-03-27
RU2007108295A (en) 2008-09-20
ES2370402T3 (en) 2011-12-15

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