EP2604799A1 - Rotor of a turbomachine - Google Patents

Rotor of a turbomachine Download PDF

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Publication number
EP2604799A1
EP2604799A1 EP11193229.9A EP11193229A EP2604799A1 EP 2604799 A1 EP2604799 A1 EP 2604799A1 EP 11193229 A EP11193229 A EP 11193229A EP 2604799 A1 EP2604799 A1 EP 2604799A1
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EP
European Patent Office
Prior art keywords
blade
disc
recesses
profiled
rotor according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP11193229.9A
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German (de)
French (fr)
Inventor
Günter Dr. Ramm
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
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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
Priority to EP11193229.9A priority Critical patent/EP2604799A1/en
Publication of EP2604799A1 publication Critical patent/EP2604799A1/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the invention relates to a rotor of a turbomachine with at least one disc and with a plurality of detachably connected to the disc blades, wherein the blade-disc connection has a form-fitting profiling and by an axial or predominantly axial relative movement of blade and disc produced and solvable, according to the preamble of claim 1.
  • Rotors with such a blade-disc connection correspond to the state of the art and are regularly used in gas turbine engines. This technique has the advantage that individual blades can be easily and quickly replaced in the event of damage, in contrast to the so-called Bliskbauweise.
  • the load-transmitting surfaces of the positive connection are preferably profiled in dovetail or fir tree, the first form being used mainly in the compressor area, the second shape mainly in the turbine area.
  • Fig. 1 shows such a rotor 1 according to the prior art, which comprises a disc 3 and blades 5.
  • the blade-disc connection 7 extends over the full axial length of the blade root and the disc edge.
  • the fir-tree-shaped profiling of the blade root and the edge of the disc - rotated by 90 ° about the vertical - is additionally drawn in, which would be de facto visible in the axial direction of the disc.
  • Complementary shows Fig. 1 beyond the rotor 1 also has a guide blade 15 and an existing between the latter and the rotor 1 labyrinth seal.
  • the components shown are intended to belong to a stage of a low-pressure turbine of a gas turbine engine and correspond to a so-called cut-off design.
  • This design aims at noise reduction at the turbine exit and is based on the principle that the number of upstream vanes 15 in the blade ring is significantly higher than the number of downstream blades 5 in the blade ring.
  • An optimal blade number ratio is about 1.5.
  • the number of guide vanes 15 by about 50% larger than the number of blades 5 on the periphery.
  • the blades 5 have relatively large dimensions in the axial and circumferential directions.
  • the blade-disc connection 7 this means that it becomes relatively long and generally bulky and heavy in the axial direction with respect to torsional vibrations of the blade.
  • Depending on the blade material and blade load can resulting in a strength significantly oversized blade-disk connection 7.
  • the profiled blade roots and / or the profiled disc edge have recesses in the axially central region.
  • material and thus weight are saved to a considerable extent in the mechanically less loaded area of the blade-disk connection, without negatively influencing the deformation behavior, vibration behavior and the service life of the rotor.
  • Due to the reduced mass moment of inertia the rotor is easier to accelerate and decelerate. Possibly.
  • the disc as such, adjacent waves, etc. can be filled more filigree and easier.
  • the profiled blade feet and the profiled disk edge preferably have corresponding recesses in the axially central region, which form a torus-like cavity running around the edge of the disk in the circumferential direction.
  • FIG. 2 shows the foot of a blade 6 and the edge region of a disc 4 in radial-axial sections and in disassembled state.
  • the foot of a blade 6 is shown with a so-called cut-off design.
  • the blade leaves down into an inner platform 14, with the underside of the profiled blade root 10 is connected.
  • the blade root 10 has a weight-reducing recess 12 in the axially central region.
  • the axial extent of the blade root 10 may be shown upstream and downstream the recess 12 be about the same.
  • the edge region of a corresponding disc 4 with a profiled and facilitated disc edge 9 is shown.
  • the recess 11 divides the profiled disk edge 9 into an upstream and a downstream region. With respect to the axial extent of these two areas, the above statements on the blade root 10 apply accordingly.
  • an annular flange with its cross-section extends predominantly vertically downwards, with a balancing weight being fastened to it.
  • the blade 6 To mount the blade 6 on the disc 4 of the blade root 10 is inserted in the axial or predominantly axial direction from upstream or downstream in the complementarily profiled disc edge 9. If the axial extent of the recesses 11 and 12 is sufficiently large, the blade 6 can be initially inserted radially into the recess 11, for example, with the right portion of the blade root 10, wherein the left portion of the disc edge 9 moves into the recess 12. Thereafter, a relatively small, axial relative movement between the blade 6 and disc 4 is sufficient to achieve the desired mounting position. A then required, axial fixation, z. B. by means of sheets, rivets, screws, etc. is familiar to the expert and not shown for simplicity. In the mounted state, the recesses 11 and 12, which are at least approximately aligned in the circumferential direction, form a toroidal cavity, which allows considerable weight savings.
  • z. B. For the preparation of the recesses 11, 12 it should be said that these are machined, z. B. by drilling, turning, milling, broaching and / or grinding, and / or electrical, z. B. by spark erosion, and / or electrochemical, z. B. by ECM and / or PECM can be made.
  • a surface hardening of the recesses 11, 12 is for example by Deep rolling and / or shot peening possible.
  • oxidation and / or sulfidation corresponding coatings of the recesses 11, 12 are applicable.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The rotor has rotor blades (6) detachably connected with a disk (4). A blade-disk-connection includes a form-fit profiling i.e. dovetail or fir tree-like profiling, at blade roots (10) and at disk edges (9). The blade-disk-connection is produced and released by an axial relative movement of the rotor blades and the disk. The profiled blade roots and/or the profiled disk edges include openings (11, 12) in an axial middle region. The openings form a toroid-like cavity in a mounted condition of the rotor blades. The cavity extends around the disk edges in a circumferential direction. The openings are coated with corrosion-, oxidation- and/or sulfidation protection layers.

Description

Die Erfindung betrifft einen Rotor einer Strömungsmaschine mit mindestens einer Scheibe und mit mehreren lösbar mit der Scheibe verbundenen Laufschaufeln, wobei die Schaufel-Scheiben-Verbindung eine formschlüssige Profilierung aufweist und durch eine axiale oder vorwiegend axiale Relativbewegung von Laufschaufel und Scheibe herstellbar und lösbar ist, gemäß dem Oberbegriff des Patentanspruchs 1.The invention relates to a rotor of a turbomachine with at least one disc and with a plurality of detachably connected to the disc blades, wherein the blade-disc connection has a form-fitting profiling and by an axial or predominantly axial relative movement of blade and disc produced and solvable, according to the preamble of claim 1.

Rotoren mit einer derartigen Schaufel-Scheiben-Verbindung entsprechen dem Stand der Technik und werden bei Gasturbinentriebwerken regelmäßig eingesetzt. Diese Technik hat den Vorteil, dass einzelne Schaufeln im Beschädigungsfall leicht und schnell ausgetauscht werden können, im Gegensatz zur sogenannten Bliskbauweise. Die lastübertragenden Flächen der formschlüssigen Verbindung sind bevorzugt in Schwalbenschwanzform (dovetail) oder in Tannenbaumform (fir tree) profiliert, wobei die erste Form hauptsächlich im Verdichterbereich, die zweite Form hauptsächlich im Turbinenbereich zur Anwendung kommt.Rotors with such a blade-disc connection correspond to the state of the art and are regularly used in gas turbine engines. This technique has the advantage that individual blades can be easily and quickly replaced in the event of damage, in contrast to the so-called Bliskbauweise. The load-transmitting surfaces of the positive connection are preferably profiled in dovetail or fir tree, the first form being used mainly in the compressor area, the second shape mainly in the turbine area.

Fig. 1 zeigt einen solchen Rotor 1 gemäß dem Stand der Technik, welcher eine Scheibe 3 und Laufschaufeln 5 umfasst. Die Schaufel-Scheiben-Verbindung 7 erstreckt sich über die volle axiale Länge des Schaufelfußes und des Scheibenrandes. Zum besseren Verständnis ist die tannenbaumförmige Profilierung von Schaufelfuß und Scheibenrand - um 90° um die Vertikale gedreht - zusätzlich eingezeichnet, welche de facto bei axialer Blickrichtung auf die Scheibe sichtbar wäre. Ergänzend zeigt Fig. 1 über den Rotor 1 hinaus noch eine Leitschaufel 15 sowie eine zwischen Letzterer und dem Rotor 1 vorhandene Labyrinthdichtung. Die gezeigten Bauteile sollen zu einer Stufe einer Niederdruckturbine eines Gasturbinentriebwerks gehören und einer sogenannten Cutoff-Auslegung entsprechen. Diese Auslegung zielt auf eine Lärmreduktion am Turbinenaustritt ab und basiert auf dem Prinzip, dass die Anzahl der stromaufwärtigen Leitschaufeln 15 im Schaufelkranz deutlich höher ist, als die Anzahl der stromabwärtigen Laufschaufeln 5 im Schaufelkranz. Ein optimales Schaufelzahlverhältnis liegt etwa bei 1,5. Somit ist die Zahl der Leitschaufeln 15 um ca. 50 % größer, als die Zahl der Laufschaufeln 5 am Umfang. Dies hat zur Folge, dass die Laufschaufeln 5 in Axial- und in Umfangsrichtung relativ große Abmessungen aufweisen. Für die Schaufel-Scheiben-Verbindung 7 bedeutet dies, dass sie u. a. im Hinblick auf Torsionsschwingungen der Schaufel in Axialrichtung relativ lang und insgesamt voluminös und schwer wird. Je nach Schaufelwerkstoff und Schaufelbelastung kann sich eine festigkeitsmäßig deutlich überdimensionierte Schaufel-Scheiben-Verbindung 7 ergeben. Fig. 1 shows such a rotor 1 according to the prior art, which comprises a disc 3 and blades 5. The blade-disc connection 7 extends over the full axial length of the blade root and the disc edge. For a better understanding, the fir-tree-shaped profiling of the blade root and the edge of the disc - rotated by 90 ° about the vertical - is additionally drawn in, which would be de facto visible in the axial direction of the disc. Complementary shows Fig. 1 beyond the rotor 1 also has a guide blade 15 and an existing between the latter and the rotor 1 labyrinth seal. The components shown are intended to belong to a stage of a low-pressure turbine of a gas turbine engine and correspond to a so-called cut-off design. This design aims at noise reduction at the turbine exit and is based on the principle that the number of upstream vanes 15 in the blade ring is significantly higher than the number of downstream blades 5 in the blade ring. An optimal blade number ratio is about 1.5. Thus, the number of guide vanes 15 by about 50% larger than the number of blades 5 on the periphery. As a result, the blades 5 have relatively large dimensions in the axial and circumferential directions. For the blade-disc connection 7 this means that it becomes relatively long and generally bulky and heavy in the axial direction with respect to torsional vibrations of the blade. Depending on the blade material and blade load can resulting in a strength significantly oversized blade-disk connection 7.

Demgegenüber besteht die Aufgabe der Erfindung darin, einen Rotor mit einer lösbaren Schaufel-Scheiben-Verbindung vorzuschlagen, wobei Letztere festigkeits- und gewichtsmäßig optimiert ist.In contrast, the object of the invention is to propose a rotor with a detachable blade-disc connection, the latter being optimized in terms of strength and weight.

Diese Aufgabe wird durch die in Anspruch 1 gekennzeichneten Merkmale gelöst, in Verbindung mit den gattungsbildenden Merkmalen in dessen Oberbegriff. Erfindungsgemäß weisen die profilierten Schaufelfüße und/oder der profilierte Scheibenrand im axial mittleren Bereich Aussparungen auf. Dadurch wird im mechanisch weniger belasteten Bereich der Schaufel-Scheiben-Verbindung in erheblichem Maße Material und somit Gewicht eingespart, ohne das Verformungsverhalten, Schwingungsverhalten und die Lebensdauer des Rotors negativ zu beeinflussen. Durch das verringerte Massenträgheitsmoment ist der Rotor leichter zu beschleunigen und zu verzögern. Ggf. können die Scheibe als solche, angrenzende Wellen etc. filigraner und leichter ausgefüllt werden.This object is achieved by the features characterized in claim 1, in conjunction with the generic features in the preamble. According to the invention, the profiled blade roots and / or the profiled disc edge have recesses in the axially central region. As a result, material and thus weight are saved to a considerable extent in the mechanically less loaded area of the blade-disk connection, without negatively influencing the deformation behavior, vibration behavior and the service life of the rotor. Due to the reduced mass moment of inertia, the rotor is easier to accelerate and decelerate. Possibly. The disc as such, adjacent waves, etc. can be filled more filigree and easier.

Bevorzugt weisen die profilierten Schaufelfüße und der profilierte Scheibenrand im axial mittleren Bereich korrespondierende Aussparungen auf, welche einen in Umfangsrichtung um den Scheibenrand herum verlaufenden, torusartigen Hohlraum bilden.The profiled blade feet and the profiled disk edge preferably have corresponding recesses in the axially central region, which form a torus-like cavity running around the edge of the disk in the circumferential direction.

Diese und weitere bevorzugte Ausgestaltungen des Rotors sind in den Unteransprüchen gekennzeichnet.These and other preferred embodiments of the rotor are characterized in the subclaims.

Die Erfindung wird anschließend anhand der Figur 2 noch näher erläutert. Diese zeigt den Fußbereich einer Laufschaufel 6 und den Randbereich einer Scheibe 4 in radial-axialen Teilschnitten sowie in demontiertem Zustand.The invention will be described below with reference to FIG. 2 explained in more detail. This shows the foot of a blade 6 and the edge region of a disc 4 in radial-axial sections and in disassembled state.

Im oberen Bereich der Figur ist der Fußbereich einer Laufschaufel 6 mit sogenannter Cutoff-Auslegung dargestellt. Das Schaufelblatt geht nach unten in eine innere Plattform 14 über, mit deren Unterseite der profilierte Schaufelfuß 10 verbunden ist. Erfindungsgemäß weist der Schaufelfuß 10 im axial mittleren Bereich eine gewichtsreduzierende Aussparung 12 auf. Die axiale Erstreckung des Schaufelfußes 10 kann, wie dargestellt, stromaufwärts und stromabwärts der Aussparung 12 etwa gleich sein. Ebenso ist es möglich, den in Betrieb stärker belasteten Bereich des Schaufelfußes axial länger, d. h. mit mehr tragender Fläche, auszuführen. In letzterem Fall wird die Aussparung 12 entsprechend aus der axialen Mitte näher zu einem axialen Ende des Schaufelfußes 10 verschoben.In the upper part of the figure, the foot of a blade 6 is shown with a so-called cut-off design. The blade leaves down into an inner platform 14, with the underside of the profiled blade root 10 is connected. According to the invention, the blade root 10 has a weight-reducing recess 12 in the axially central region. The axial extent of the blade root 10 may be shown upstream and downstream the recess 12 be about the same. Likewise, it is possible to make the region of the blade root that is more heavily loaded in operation axially longer, ie with more load-bearing surface. In the latter case, the recess 12 is moved accordingly from the axial center closer to an axial end of the blade root 10.

Im unteren Bereich der Figur ist der Randbereich einer korrespondierenden Scheibe 4 mit einem profilierten und erleichterten Scheibenrand 9 dargestellt. Die Aussparung 11 teilt den profilierten Scheibenrand 9 in einen stromaufwärtigen und einen stromabwärtigen Bereich. Bezüglich der axialen Erstreckung dieser beiden Bereiche gelten die obigen Aussagen zum Schaufelfuß 10 entsprechend. Ausgehend vom rechten Bereich des Scheibenrandes 9 erstreckt sich ein ringförmiger Flansch mit seinem Querschnitt vorwiegend vertikal nach unten, wobei ein Wuchtgewicht an diesem befestigt ist.In the lower part of the figure, the edge region of a corresponding disc 4 with a profiled and facilitated disc edge 9 is shown. The recess 11 divides the profiled disk edge 9 into an upstream and a downstream region. With respect to the axial extent of these two areas, the above statements on the blade root 10 apply accordingly. Starting from the right-hand region of the disk rim 9, an annular flange with its cross-section extends predominantly vertically downwards, with a balancing weight being fastened to it.

Zur Montage der Laufschaufel 6 an der Scheibe 4 wird der Schaufelfuß 10 in axialer bzw. vorwiegend axialer Richtung von stromaufwärts oder stromabwärts in den komplementär profilierten Scheibenrand 9 eingeschoben. Falls die axiale Erstreckung der Aussparungen 11 und 12 ausreichend groß ist, kann die Laufschaufel 6 zur Montage beispielsweise mit dem rechten Bereich ihres Schaufelfußes 10 zunächst radial in die Aussparung 11 gesteckt werden, wobei sich der linke Bereich des Scheibenrandes 9 in die Aussparung 12 bewegt. Danach genügt eine relativ kleine, axiale Relativbewegung zwischen Laufschaufel 6 und Scheibe 4, um die Montage-Sollposition zu erreichen. Eine dann erforderliche, axiale Fixierung, z. B. mittels Blechen, Nieten, Schrauben etc. ist dem Fachmann geläufig und der Einfachheit halber nicht dargestellt. Im montierten Zustand bilden die in Umfangsrichtung zumindest annähernd fluchtenden Aussparungen 11 und 12 einen torusartigen Hohlraum, welcher erhebliche Gewichtseinsparungen ermöglicht.To mount the blade 6 on the disc 4 of the blade root 10 is inserted in the axial or predominantly axial direction from upstream or downstream in the complementarily profiled disc edge 9. If the axial extent of the recesses 11 and 12 is sufficiently large, the blade 6 can be initially inserted radially into the recess 11, for example, with the right portion of the blade root 10, wherein the left portion of the disc edge 9 moves into the recess 12. Thereafter, a relatively small, axial relative movement between the blade 6 and disc 4 is sufficient to achieve the desired mounting position. A then required, axial fixation, z. B. by means of sheets, rivets, screws, etc. is familiar to the expert and not shown for simplicity. In the mounted state, the recesses 11 and 12, which are at least approximately aligned in the circumferential direction, form a toroidal cavity, which allows considerable weight savings.

Es sei erwähnt, dass es auch möglich ist, Aussparungen nur am Scheibenfuß oder nur am Scheibenrand vorzusehen, wobei die Gewichtseinsparung dann aber deutlich geringer ausfällt.It should be noted that it is also possible to provide recesses only at the disk base or only at the edge of the disk, but the weight saving then but significantly lower.

Zur Herstellung der Aussparungen 11, 12 sei gesagt, dass diese spanabhebend, z. B. durch Bohren, Drehen, Fräsen, Räumen und/oder Schleifen, und/oder elektrisch, z. B. durch Funkenerosion, und/oder elektrochemisch, z. B. durch ECM und/oder PECM, gefertigt werden können. Eine Oberflächenverfestigung der Aussparungen 11, 12 ist beispielsweise durch Festwalzen und/oder Kugelstrahlen möglich. Zum Schutz gegen Korrosion, Oxidation und/oder Sulfidation sind entsprechende Beschichtungen der Aussparungen 11, 12 anwendbar.For the preparation of the recesses 11, 12 it should be said that these are machined, z. B. by drilling, turning, milling, broaching and / or grinding, and / or electrical, z. B. by spark erosion, and / or electrochemical, z. B. by ECM and / or PECM can be made. A surface hardening of the recesses 11, 12 is for example by Deep rolling and / or shot peening possible. For protection against corrosion, oxidation and / or sulfidation corresponding coatings of the recesses 11, 12 are applicable.

Claims (8)

Rotor (2) einer Strömungsmaschine, insbesondere einer Niederdruckturbine eines Gasturbinentriebwerks, mit mindestens einer Scheibe (4) und mit mehreren lösbar mit der Scheibe (4) verbundenen Laufschaufeln (6), wobei die Schaufel-Scheiben-Verbindung (8) eine formschlüssige Profilierung, vorzugsweise eine schwalbenschwanz- oder tannenbaumförmige Profilierung, am Schaufelfuß (10) und am Scheibenrand (9) aufweist und durch eine axiale oder vorwiegend axiale Relativbewegung von Laufschaufel (6) und Scheibe (6) herstellbar und lösbar ist,
dadurch gekennzeichnet,
dass die profilierten Schaufelfüße (10) und/oder der profilierte Scheibenrand (9) im axial mittleren Bereich Aussparungen (11, 12) aufweisen/aufweist.Rotor (2) of a turbomachine, in particular a low-pressure turbine of a gas turbine engine, with at least one disc (4) and with several detachably connected to the disc (4) blades (6), wherein the blade-disc connection (8) has a form-fitting profiling, preferably a dovetail or fir-tree-shaped profiling, on the blade root (10) and on the disc edge (9) and can be produced and released by an axial or predominantly axial relative movement of the moving blade (6) and disc (6),
characterized,
in that the profiled blade roots (10) and / or the profiled disk edge (9) in the axially central region of recesses (11, 12) have / has. Rotor nach Anspruch 1, dadurch gekennzeichnet, dass die profilierten Schaufelfüße (10) und der profilierte Scheibenrand (9) im axial mittleren Bereich korrespondierende Aussparungen (11, 12) aufweisen, welche - im montierten Zustand der Laufschaufeln (6) - einen in Umfangsrichtung um den Scheibenrand (9) herum verlaufenden, torusartigen Hohlraum bilden.Rotor according to claim 1, characterized in that the profiled blade roots (10) and the profiled disc edge (9) in the axially central region corresponding recesses (11, 12) which - in the assembled state of the blades (6) - in the circumferential direction to form the torus-like cavity running around the disk rim (9). Rotor nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Last aufnehmenden Flächen der formschlüssig profilierten Schaufel-Scheiben-Verbindung (8) stromaufwärts und stromabwärts der Aussparungen (11, 12) mittels ihrer axialen Länge an die im Betrieb vorherrschende Lastverteilung angepasst sind.Rotor according to claim 1 or 2, characterized in that the load-receiving surfaces of the form-fitting profiled blade-disc connection (8) upstream and downstream of the recesses (11, 12) are adapted by its axial length to the prevailing load distribution in operation. Rotor nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Aussparungen (11, 12) spanabhebend bearbeitet sind, z. B. durch Bohren, Drehen, Fräsen, Räumen und/oder Schleifen.Rotor according to one of claims 1 to 3, characterized in that the recesses (11, 12) are machined, z. B. by drilling, turning, milling, broaching and / or grinding. Rotor nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Aussparungen (11, 12) elektrisch und/oder elektrochemisch bearbeitet sind, z. B. durch Funkenerosion, ECM und/oder PECM.Rotor according to one of claims 1 to 4, characterized in that the recesses (11, 12) are processed electrically and / or electrochemically, for. B. by spark erosion, ECM and / or PECM. Rotor nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Aussparungen (11, 12) oberflächenverfestigt sind, z. B. durch Festwalzen und/oder Kugelstrahlen.Rotor according to one of claims 1 to 5, characterized in that the recesses (11, 12) are surface hardened, z. B. by deep rolling and / or shot peening. Rotor nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die Aussparungen (11, 12) beschichtet sind, z. B. mit einer Korrosions-, Oxidations- und/oder Sulfidationsschutzschicht.Rotor according to one of claims 1 to 6, characterized in that the recesses (11, 12) are coated, for. B. with a corrosion, oxidation and / or sulfidation protective layer. Rotor nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass er Teil einer lärmreduzierten Niederdruckturbinenstufe mit sogenannter Cutoff-Auslegung eines Gasturbinentriebwerks ist.Rotor according to one of claims 1 to 7, characterized in that it is part of a noise-reduced low-pressure turbine stage with so-called cut-off design of a gas turbine engine.
EP11193229.9A 2011-12-13 2011-12-13 Rotor of a turbomachine Withdrawn EP2604799A1 (en)

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EP2604799A1 true EP2604799A1 (en) 2013-06-19

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3904638A1 (en) * 2020-04-27 2021-11-03 Raytheon Technologies Corporation Rotor assembly

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2751189A (en) * 1950-09-08 1956-06-19 United Aircraft Corp Blade fastening means
DE1428230A1 (en) * 1963-12-04 1969-01-09 Rolls Royce Flow machine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2751189A (en) * 1950-09-08 1956-06-19 United Aircraft Corp Blade fastening means
DE1428230A1 (en) * 1963-12-04 1969-01-09 Rolls Royce Flow machine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3904638A1 (en) * 2020-04-27 2021-11-03 Raytheon Technologies Corporation Rotor assembly
US11441440B2 (en) 2020-04-27 2022-09-13 Raytheon Technologies Corporation Rotor assembly

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