EP2320030B1 - Rotor et aube de rotor pour une turbomachine axiale - Google Patents

Rotor et aube de rotor pour une turbomachine axiale Download PDF

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Publication number
EP2320030B1
EP2320030B1 EP10189854A EP10189854A EP2320030B1 EP 2320030 B1 EP2320030 B1 EP 2320030B1 EP 10189854 A EP10189854 A EP 10189854A EP 10189854 A EP10189854 A EP 10189854A EP 2320030 B1 EP2320030 B1 EP 2320030B1
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EP
European Patent Office
Prior art keywords
rotor
axial
hammerhead
moving blade
blade
Prior art date
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Active
Application number
EP10189854A
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German (de)
English (en)
Other versions
EP2320030A1 (fr
Inventor
Erich Kreiselmaier
Kurt Rubischon
Christoph Nagler
Herbert Brandl
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Publication date
Priority claimed from CH01724/09A external-priority patent/CH702204A1/de
Priority claimed from CH01723/09A external-priority patent/CH702203A1/de
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2320030A1 publication Critical patent/EP2320030A1/fr
Application granted granted Critical
Publication of EP2320030B1 publication Critical patent/EP2320030B1/fr
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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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • 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
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the present invention relates to the art of axial flow turbomachinery. It relates to a rotor for an axial flow turbine engine according to the preamble of claim 1 and a blade for such a rotor.
  • FIG. 1 shows a perspective, partially sectioned view of an example of such a gas turbine, which is offered by the Applicant and is known under the type designation GT26 ® .
  • the gas turbine 10 of Fig. 1 is equipped with a so-called sequential combustion. It comprises a multi-stage compressor 12, which draws and compresses air via an air inlet 15. The compressed air is used in a subsequent first annular combustion chamber 14a partially for the combustion of a injected fuel. The resulting hot gas flows through a first turbine 13a and then enters a second combustion chamber 14b, where the remaining air is used to burn a re-injected fuel. The hot gas stream coming from the second combustion chamber 14b is expanded under operating power in a second turbine 13b and exits the gas turbine 10 through an exhaust gas outlet 16 to be discharged to the outside or used to generate steam in a combined cycle power plant.
  • the compressor 12 and the two turbines 13a, 13b have sets of blades rotating about the axis 30 which, together with stator vanes secured to the surrounding stator, form the blading of the machine. All blades are arranged on a common, rotatable about the axis of the rotor 11 and releasably secured to the rotor shaft by means provided therefor rotor grooves. Particular attention is paid to the last stages 12a of the compressor 12, in which the compressed air reaches temperatures of several hundred degrees Celsius.
  • the corresponding surfaces of the rotor groove and blade root are provided with at least one projection which engages in a complementary recess of the adjacent surface and thus fix the blade in addition.
  • Hardly calculable stress states and increased susceptibility of the rotor to stress corrosion cracking limit the possible applications of this solution.
  • the blade arrangement according to GB 674543 has at the bottom of the rotor groove radially directed recesses that perform a similar function.
  • the rotor groove EP-A2-707135 Such adverse effects of difficult to calculate stress states are determined by an embodiment of the rotor groove EP-A2-707135 avoided.
  • the rotor groove is described by a number of successive radii R 1 , ..., R n , which divide their contour into circular arcs defined by these radii and give it a continuous course without tapering edges that unfold a notch effect.
  • An increase in power of the gas turbine is associated with an increase in mass flow through the compressor resulting in a higher gas temperature in the last compressor stages 12a.
  • the contemporary, advanced aerodynamic design of the blades of the compressor requires greater axial chord lengths, resulting in a greater distance between the rotor slots 19.
  • a rotor groove designed in this way has at its bottom a reduced ground area 23 with a continuously curved cross-sectional contour, which is characterized by a large radius of curvature in the area of the median plane 33 and is mirror-symmetrical to the median plane 33 in order to reduce thermal stresses.
  • the object is solved by the entirety of the features of claims 1 and 2.
  • the basic idea of the invention is that the rotor groove at its bottom for reducing thermal stresses in a conventional manner has an extended in the axial and radial directions bottom area with a continuously curved cross-sectional contour, and the blade root of the blades is adapted in the radial direction to the extended bottom area ,
  • the extended bottom region of the rotor groove is mirror-symmetrical to a rotor groove going through, perpendicular to the axis formed while the extended bottom portion in the axial direction has a predetermined maximum width, that the radial abutment surfaces in the axial direction have a predetermined minimum distance, and that the ratio of minimum distance to maximum width is between 0.1 and 0.6, ie 0.1 ⁇ d 5 / d 1 ⁇ 0.6, and the extended bottom area relative to the radial abutment surfaces has a predetermined first maximum depth which is extended Bottom area relative to the inner edges of the axial abutment surfaces has a predetermined second maximum depth, and the ratio of the second maximum depth to the first maximum depth is between 0.4 and 0.9, ie 0.4 ⁇ d 3 / d 4 ⁇ 0, 9 and when provided in the axial direction a plurality of similar rotor grooves offset by a predetermined distance, and the behavior of maximum width to spacing is between 0.5 and 0.8, ie
  • a rotor blade for a rotor designed in this way has a blade root designed as a hammer head, which is extended below the hammer head to bridge the radial extension of the widened base region in the radial direction by means of a radially extending extension bolt, wherein the hammer head has a predetermined height d 2 and a predetermined radial length d is 1, and that the ratio of height to length of between 0.2 and 0.8, ie 0.2 ⁇ d 2 / d 1 ⁇ 0.8, and the hammer head has a first predetermined axial width d 3 and a predetermined second axial width d 4 , and the ratio of the second to the first axial width is between 0.2 and 0.6, ie 0.2 ⁇ d 4 / d 3 ⁇ 0.6.
  • the comparatively slim extension pin bridges the gap without adding bulk to the blade.
  • extension bolt is formed on the hammer head.
  • a curved transition surface is provided at the transition between the extension bolt and the hammer head to ensure a steady transition.
  • extension bolt as a separate part and to connect this with the hammer head.
  • the mass of the blade can be reduced further if mass-reducing recesses are provided in the blade root.
  • the recesses extend over the hammer head and the extension bolt.
  • these recesses may extend in other, for example, radial direction.
  • An embodiment of the rotor according to the invention is characterized in that between the lower end of the extension bolt and the bottom of the extended bottom portion, a gap remains free, and that in the free space, a spring is arranged, which the blade with the blade root in the radial direction against presses the radial abutment surfaces.
  • Fig. 4 shows that too Fig. 2 comparable longitudinal section through the rotor 11 of a gas turbine in the region of the last stages of the compressor according to the invention.
  • a comparison of Fig. 2 and 4 shows that the upper portion of the rotor groove 21 compared to the known Rotornutgeometrie Fig. 2 remains unchanged. Accordingly, the radial and axial abutment surfaces 25 and 20 remain virtually unchanged. Thus, the proven design can be used in this area.
  • the widened floor area 23 of the rotor groove 21 is characterized in that the cross-sectional contour of the floor area 23 is continuously curved and that the radius of curvature of the cross-sectional contour of the floor area 23 in the area of the median plane is very large and starts from the median plane decreases sharply towards the edge.
  • the cross-sectional contour is mirror-symmetrical to the median plane.
  • the extended bottom portion 23 extends immediately below the axial abutment surfaces 20 on both sides in the axial direction in the manner of an undercut. He shows how Fig. 3 shows, in the axial direction, a predetermined maximum width d 1 , while the radial abutment surfaces 25 have a predetermined minimum distance d 5 in the axial direction. It is particularly favorable if the ratio of minimum distance d 5 to maximum width d 1 is between 0.1 and 0.6, ie if the inequality 0.1 ⁇ d 5 / d 1 ⁇ 0.6 applies.
  • the extended bottom portion 23 has a predetermined first maximum depth d 4 .
  • the extended bottom portion 23 has a predetermined second maximum depth d 3 . It is particularly favorable if the ratio of the second maximum depth d 3 to the first maximum depth d 4 is between 0.4 and 0.9, ie if the inequality 0.4 ⁇ d 3 / d 4 ⁇ 0.9 applies.
  • Another inequality relates to the offset of the rotor grooves to each other. If a plurality of similar rotor slots 21 are provided offset from each other by a predetermined distance d 2 in the axial direction, it is advantageous if the ratio of maximum width d 1 to distance d 2 is between 0.5 and 0.8, ie the inequality 0 , 5 ⁇ d 1 / d 2 ⁇ 0.8.
  • the blade 26 of the Fig. 5 and 6 has a blade root 27, which is formed in the upper portion, which extends to the axial abutment surfaces, substantially the same as the blade root 18 from Fig. 2 ,
  • the hammer head 32 attached radial extension downwards by means of an integrally formed on the hammer head 32 extension bolt 29, which is narrower (width d 4 ) than the hammer head 32 (width d 3 ).
  • the radial length (d 1 ) of the extension pin 29 is significantly greater than the height (d 2 ) of the hammer head 32nd
  • a curved transition surface 28 is preferably provided at the transition between the extension bolt 29 and the hammer head 32 to ensure a steady transition.
  • the extension pin 29 As a cost-effective alternative for the axial extension of the blade root 18, it is advisable to form the extension pin 29 as a separate part and to connect that with the hammer head 32. As the requirements of practical operation sufficient connection method have thereby screwing or welding proven.
  • the hammer head 32 may be provided at the bottom 34 in the region of the median plane 33 with a threaded bore 35. With the help of an integrally formed threaded bolt 36 of the extension bolt 29 is screwed into the blade root 18, as in Fig. 7 outlined as an example.
  • one or more mass-reducing recesses 31 are provided in the blade root 18, 27, which can be designed as a circular, elliptical or otherwise shaped hole or slot in a single or multiple design.
  • the recess (s) 31 extend or extend in the radial direction, preferably via the hammer head 32 and the extension bolt 29. In this case, this recess (s) 31 extends or runs preferably, but not necessarily, in the circumferential direction, as in FIG Fig. 5 . 6 and 7 shown.
  • other suitable directional curves and embodiments of mass-reducing recesses 31 are likewise conceivable, for example in the form of bores introduced radially into the blade root 27.
  • the ratio of height (d 2 ) of the hammer head 32 to length (d 1 ) of the extension bolt 29 is preferably between 0.2 and 0.8, ie the inequality 0.2 ⁇ d 2 / d 1 ⁇ 0.8 applies.
  • the ratio of the axial width (d 4 ) of the extension bolt 29 to the axial width (d 3 ) of the hammer head 32 is preferably between 0.2 and 0.6, ie, the inequality 0.2 ⁇ d 4 / d 3 ⁇ 0, 6th

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

Claims (11)

  1. Rotor (11) pour une turbomachine axiale, lequel rotor (11) porte une pluralité d'aubes mobiles (26) qui sont respectivement insérées, par l'intermédiaire d'un pied d'aube (27), dans une rainure de rotor (21) s'étendant autour de l'axe (30) et y sont maintenues, le pied d'aube (27) comportant un pied-marteau doté d'une tête de marteau (32) et s'appuyant contre des surfaces de butée radiales (25) de la rainure de rotor (21) qui sont situées plus à l'extérieur dans la direction radiale, à l'encontre de forces centrifuges agissant sur l'aube mobile (26), et s'appuyant contre des surfaces de butée axiales (20) qui sont situées plus à l'intérieur dans la direction radiale, à l'encontre de forces axiales agissant sur l'aube mobile (26), la rainure de rotor (21) comprenant, au niveau de son fond, une région de fond (23) élargie dans la direction radiale et dans la direction axiale et dotée d'un contour en section transversale présentant une courbure continue, en vue de la réduction des contraintes thermiques, la région de fond (23) élargie étant réalisée de manière à présenter une symétrie miroir par rapport à un plan médian perpendiculaire à l'axe (30) et passant par la rainure de rotor (21), et le rayon de courbure du contour en section transversale de la région de fond (23) diminuant à partir du plan médian jusqu'au bord, caractérisé en ce que la région de fond (23) élargie présente une largeur maximale prédéfinie (d1) dans la direction axiale, en ce que les surfaces de butée radiales (25) présentent un écart minimal prédéfini (d5) dans la direction axiale, et en ce que le rapport de l'écart minimal (d5) à la largeur maximale (d1) vaut entre 0,1 et 0,6, c'est-à-dire que 0,1 < d5/d1 < 0,6, en ce que la région de fond (23) élargie présente une première profondeur maximale prédéfinie (d4) par rapport aux surfaces de butée radiales (25), en ce que la région de fond (23) élargie présente une deuxième profondeur maximale prédéfinie (d3) par rapport aux bords intérieurs des surfaces de butée axiales (20), et en ce que le rapport de la deuxième profondeur maximale (d3) à la première profondeur maximale (d4) vaut entre 0,4 et 0,9, c'est-à-dire que 0,4 < d3/d4 < 0,9, en ce que, dans la direction axiale, plusieurs rainures de rotor (21) similaires sont prévues de manière décalée d'une distance prédéfinie (d2), et en ce que le rapport de la largeur maximale (d1) à la distance (d2) vaut entre 0,5 et 0,8, c'est-à-dire que 0,5 < d1/d2 < 0, 8 .
  2. Aube mobile (26) pour un rotor (11) pour une turbomachine axiale, lequel rotor (11) porte une pluralité d'aubes mobiles (26) qui sont respectivement insérées, par l'intermédiaire d'un pied d'aube (27), dans une rainure de rotor (21) s'étendant autour de l'axe (30) et y sont maintenues, le pied d'aube (27) comportant un pied-marteau doté d'une tête de marteau (32) et s'appuyant contre des surfaces de butée radiales (25) de la rainure de rotor (21) qui sont situées plus à l'extérieur dans la direction radiale, à l'encontre de forces centrifuges agissant sur l'aube mobile (26), et s'appuyant contre des surfaces de butée axiales (20) qui sont situées plus à l'intérieur dans la direction radiale, à l'encontre de forces axiales agissant sur l'aube mobile (26), la rainure de rotor (21) comprenant, au niveau de son fond, une région de fond (23) élargie dans la direction radiale et dans la direction axiale et dotée d'un contour en section transversale présentant une courbure continue, en vue de la réduction des contraintes thermiques, caractérisée en ce qu'en dessous de la tête de marteau (32), pour enjamber l'élargissement radial de la région de fond (23) élargie de la rainure de rotor (21), le pied d'aube (27) est prolongé dans la direction radiale au moyen d'une cheville de prolongement (29) s'étendant dans la direction radiale, la tête de marteau (32) possédant une hauteur prédéfinie (d2), la cheville de prolongement (29) possédant une longueur radiale prédéfinie (d1), et le rapport de la hauteur à la longueur (d2/d1) se situant entre 0,2 et 0,8, c'est-à-dire que 0,2 < d2/d1 < 0,8, et la tête de marteau (32) possédant une première largeur axiale prédéfinie (d3), la cheville de prolongement (29) possédant une deuxième largeur axiale prédéfinie (d4), et le rapport de la deuxième à la première largeur axiale (d4/d3) se situant entre 0,2 et 0,6, c'est-à-dire que 0,2 < d4/d3 < 0,6.
  3. Aube mobile selon la revendication 2, caractérisée en ce que la cheville de prolongement (29) est formée sur la tête de marteau (32).
  4. Aube mobile selon la revendication 2 ou 3, caractérisée en ce qu'une surface de transition courbe (28) est prévue au niveau de la transition entre la cheville de prolongement (29) et la tête de marteau (32) pour assurer une transition continue.
  5. Aube mobile selon la revendication 2, caractérisée en ce que la cheville de prolongement (29) est réalisée sous forme de pièce séparée et est reliée à la tête de marteau (32).
  6. Aube mobile selon la revendication 5, caractérisée en ce que la cheville de prolongement (29) est vissée sur la tête de marteau (32).
  7. Aube mobile selon la revendication 5, caractérisée en ce que la cheville de prolongement (29) est soudée sur la tête de marteau (32).
  8. Aube mobile selon l'une quelconque des revendications 2 à 7, caractérisée en ce que des évidements réduisant la masse (31) sont prévus dans le pied d'aube (27).
  9. Aube mobile selon la revendication 8, caractérisée en ce que les évidements (31) s'étendent au-dessus de la tête de marteau (32) et de la cheville de prolongement (29).
  10. Aube mobile selon la revendication 8 ou 9, caractérisée en ce que les évidements (31) s'étendent dans la direction périphérique.
  11. Aube mobile selon la revendication 8 ou 9, caractérisée en ce que les évidements (31) s'étendent dans la direction radiale.
EP10189854A 2009-11-10 2010-11-03 Rotor et aube de rotor pour une turbomachine axiale Active EP2320030B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH01724/09A CH702204A1 (de) 2009-11-10 2009-11-10 Rotor für eine axial durchströmte turbomaschine sowie gasturbine für solchen rotor.
CH01723/09A CH702203A1 (de) 2009-11-10 2009-11-10 Rotor für eine axial durchströmte turbomaschine sowie laufschaufel für einen solchen rotor.

Publications (2)

Publication Number Publication Date
EP2320030A1 EP2320030A1 (fr) 2011-05-11
EP2320030B1 true EP2320030B1 (fr) 2012-12-19

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EP10189854A Active EP2320030B1 (fr) 2009-11-10 2010-11-03 Rotor et aube de rotor pour une turbomachine axiale

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US (1) US8770938B2 (fr)
EP (1) EP2320030B1 (fr)
JP (1) JP5765918B2 (fr)
CN (1) CN102121400B (fr)

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Also Published As

Publication number Publication date
US20110110785A1 (en) 2011-05-12
CN102121400B (zh) 2015-12-16
JP2011102586A (ja) 2011-05-26
JP5765918B2 (ja) 2015-08-19
EP2320030A1 (fr) 2011-05-11
US8770938B2 (en) 2014-07-08
CN102121400A (zh) 2011-07-13

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