EP3061909A1 - Rotorwelle mit Kühlbohrungseinlässen - Google Patents

Rotorwelle mit Kühlbohrungseinlässen Download PDF

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Publication number
EP3061909A1
EP3061909A1 EP15156738.5A EP15156738A EP3061909A1 EP 3061909 A1 EP3061909 A1 EP 3061909A1 EP 15156738 A EP15156738 A EP 15156738A EP 3061909 A1 EP3061909 A1 EP 3061909A1
Authority
EP
European Patent Office
Prior art keywords
bore
rotor
rotor shaft
cooling
fillet
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP15156738.5A
Other languages
English (en)
French (fr)
Other versions
EP3061909B1 (de
Inventor
Steffen Holzhaeuser
Carlos Simon-Delgado
Carl Berger
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.)
Ansaldo Energia Switzerland AG
Original Assignee
General Electric Technology 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 General Electric Technology GmbH filed Critical General Electric Technology GmbH
Priority to EP15156738.5A priority Critical patent/EP3061909B1/de
Publication of EP3061909A1 publication Critical patent/EP3061909A1/de
Application granted granted Critical
Publication of EP3061909B1 publication Critical patent/EP3061909B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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 field of rotating machines, and, more particularly, to a rotor shaft for a turbo-machinery, especially for a gas or steam turbine.
  • the rotor shaft comprising a rotor cavity configured concentrically or quasi-concentrically to the rotor axis inside the rotor shaft, and a plurality of cooling bores extending radially or quasi-radially outward from the inside to an outside of the rotor shaft.
  • Each cooling bore having a bore inlet location and a distal bore outlet portion. The respective bore inlet location being adapted to abut on the rotor cavity.
  • compressors, gas turbines, steam turbines and other thermal machines are subjected to high thermal and mechanical stresses. Accordingly, it is indispensable to reduce such thermal and mechanical stresses.
  • a rotor shaft In a gas turbine, a rotor shaft, among the various other parts, such as rotor blades and stator vanes, are exposed to high thermal and mechanical stresses.
  • Critical locations may be, among others, cooling bore inlets in rotor cavities of the rotor shaft.
  • the rotor cavities are configured inside of the rotor shaft, and the cooling bore inlets are arranged on outer circumference of such rotor cavities.
  • the cooling bores extend from the inside of the rotor shaft mainly in a radial direction. Where such cooling bores and rotor cavities are concerned, the stresses arising in the rotor cavities depend critically on a cross-sectional contour of the rotor cavities.
  • the cooling bores usually constitute a mechanical weakening of the rotor shaft in the area where they extend from the rotor cavities, which may have an adverse effect in the case of high thermal and mechanical stresses.
  • the internal radial compressor of the rotor is provided in the form of ribs on the rotor cavity wall.
  • the internal ribs accelerate the air flow in circumferential direction and thus increase its swirl. Referring to the drawbacks this comports that the ribs have a very high surface to volume ratio and thus have a very fast thermal behaviour while the rotor disc with a very low surface to volume ratio has a very slow thermal behaviour. This can introduce very high thermal stresses into the rotor disc so that the design of such ribs results difficult.
  • the present invention describes an improved rotor shaft of a gas turbine, steam turbine or, generally, turbo-machinery, that will be presented in the following simplified summary to provide a basic understanding of one or more aspects of the disclosure that are intended to overcome the discussed drawbacks, but to include all advantages thereof, along with providing some additional advantages.
  • An object of the present invention is to describe an improved rotor shaft, which may be adaptable in terms of reducing effect of thermal and mechanical stresses arise thereon while a machine or turbine in which relation it is being used is in running condition.
  • the rotor shaft of the present invention independently of the fact whether the rotor shaft of the present invention being made of single piece or of multiple piece, the rotor shaft of the present invention has an objective of withstanding or reducing effects of thermal and mechanical stresses.
  • Another object of the present invention is to describe an improved rotor shaft, which is convenient to use in an effective and economical way.
  • the main aspects of the inventive step include a first embodiment that at least one side or part-side of the cooling bore inlet location is provided with an asymmetric edge fillet in order to maximize the wall thickness between two adjacent cooling bores.
  • an improved rotor shaft for a gas turbine engine of a power plant.
  • the rotor shaft adapted to rotate about a rotor axis thereof.
  • the rotor shaft includes a rotor cavity configured concentrically or quasi-concentrically to the rotor axis inside the rotor shaft. It is to be understood that the invention is not to be strictly limited to a concentrically cavity configuration.
  • the rotor shaft further includes a plurality of cooling bores extending radially or quasi-radially outward from the inside to an outside of the rotor shaft. It is to be understood that the invention is not to be strictly limited to a radially configuration.
  • Each cooling bore includes a bore inlet portion and a distal bore outlet portion. The respective bore inlet portions being adapted to abut on the rotor cavity.
  • the bore itself (between the inlet portion and the outlet portion) is a "normal" straight bore with a constant bore diameter.
  • the rotor shaft in one embodiment may be a single piece configuration or in another embodiment may be a two or more pieces configuration welded to be assembled along at least one weld seam.
  • the rotor shaft could also be bolted together.
  • the present invention introduces an asymmetric edge filet at the inlet of a cooling bore in the cavity of the rotor.
  • the cooling air flows through a centre, or quasi-center, or other disposed bore into a rotor cavity and enters the cooling air bores which guide it towards rotor blades.
  • the rotational velocity of the cooling air is only small in the rotor cavity. In the transition from the cavity to the cooling bores, the rotational velocity of the cooling air increases significantly which leads to pressure losses and recirculation areas at the bore inlet.
  • the introduction of the asymmetric edge fillet allows for a smoother transition from the rotor cavity to the cooling bores and thus improves the flow conditions at the bore inlet.
  • the disclosed inlet design of the cooling holes is used to guide the air through the rotor disc and not for pressurizing the air.
  • the recirculation areas are reduced and, thus, the effective flow cross section in the cooling bore inlet is increased. This limits the peak-velocities to smaller values and reduces the pressure losses significantly.
  • the cooling bore diameter can be reduced while the cooling air velocity and pressure losses stay the same or increase only slightly.
  • the edge fillet is only applied on one side of the bores and is thus asymmetric while the other side remains basically without fillet, but basically does not mean fundamentally, i.e. within a narrow range, the side which is available without fillet can be provided with a reduced edge fillet without sacrificing the predominant underlying asymmetry.
  • the side comprising the edge fillet is applied at the front of the bore in direction of rotation of the rotor.
  • the rotor shaft can be configured as a single piece configuration, or the rotor shaft is configured in two or more pieces, welded to be assembled along one welded seam.
  • the edge fillet referring to the asymmetric side of the bore is ideally manufactured as a round fillet with a radius between factor 0.3 to 0.7 0f the cooling bore diameter. Due to manufacturing limitations, the round fillet can be approximated by 3 or more chamfers with uniform angular steps in between. In case the fillet is approximated by chamfers, the overall width w and the overall depth d of the edge fillet are also between factor 0.3 and 0.7 of the cooling bore diameter.
  • the final aim of the present invention consists in introduction of an asymmetric edge fillet at the inlet of a rotating cooling bore in a rotor disc in order to improve the flow conditions at the inlet and, thus, to reduce the inlet pressure losses, allowing for a smaller bore diameter for a given mass flow. Accordingly, the remaining wall thickness between neighboring bores is improved which is beneficial for the rotor lifetime.
  • FIG 1 reproduces a perspective side view of the rotor shaft 100, without blading, of a gas turbine and will be described in conjunction to Figure 2 .
  • the rotor shaft 100 rotationally symmetric with respect to a rotor axis 110, is subdivided into a compressor part 101 and a turbine part 102. Between the two parts 101 and 102, inside the gas turbine dome, a combustion chamber may be arranged, into which air compressed in the compressor part 101 is introduced and out of which the hot gas flows through the turbine part 102.
  • the turbine part 102 arranged one behind the other in the axial direction, has a plurality of rotor disks 103, in which axially oriented reception slots for the reception of corresponding moving blades are formed so as to be distributed over the circumference. Blade roots of the blades are held in the reception slots in the customary way by positive connection by means of a fir tree-like cross-sectional contour.
  • the rotor cavity (see Figure 2 ) may be connected to a central cooling air supply 104 running in an axial direction within the rotor shaft 100 to supply cool air therefrom to the rotor cavity, and there to the plurality of cooling bores (see Figure 2 ).
  • the rotor shaft comprising a rotor cavity configured concentrically to the rotor axis inside the rotor shaft and a plurality of cooling bores extending radially outward from the inside to an outside of the rotor shaft.
  • Each cooling bore having a bore inlet portion and a distal bore outlet portion, and the respective bore inlet portion is adapted to abut on the rotor cavity.
  • the rotor cavity comprises a cross-sectional profile adapted to be circumferentially straight at a location whereas the each respective bore inlet portion abuts on the rotor cavity, enabling reduction in at least thermal and mechanical stresses across the major cross-sectional profile of the rotor cavity.
  • each cooling bore 130 includes a bore inlet portion 132 and distal bore outlet portion 134.
  • the respective bore inlet portion 132 being adapted to abut on the rotor cavity 120.
  • the term 'abut' is defined to mean that the bore inlet portion 132 and the rotor cavity 120 whereat the bore inlet portion 132 meets share a same plane.
  • the rotor cavity 120 may be connected to a central cooling air supply 104 running in an axial direction within the rotor shaft 100 to supply cool air therefrom to the rotor cavity 120, and there to the plurality of cooling bores 130.
  • the air could be delivered to the cavity differently.
  • the cool air from the plurality of cooling bores 130 reaches the outside of the rotor shaft 100 between the blades and blade roots 103 for cooling thereto.
  • FIG 3 shows a most preferred embodiment of the present invention in accordance with section view III-III of Figure 2 .
  • the present embodiment introduces an asymmetric edge filet 150 at an inlet location of a cooling bore 130 in the rotor cavity 120.
  • the cooling air flows through a different placed bore into a rotor cavity and enters the cooling air bores which guide it towards rotor blades (see Figure 2 ).
  • the rotational velocity of the cooling air is only very small in the rotor cavity. In the transition from the cavity to the cooling bores, the rotational velocity of the cooling air increases significantly which leads to pressure losses and recirculation areas at the bore inlet location 160.
  • asymmetric edge fillet 150 allows for a smoother transition from the rotor cavity 120 to the cooling bores 130 and thus improves the flow conditions at the bore inlet location.
  • the recirculation areas are reduced and, thus, the effective flow cross section in the cooling bore inlet location 160 is increased. This limits the Mach-number to smaller values and reduces the pressure losses significantly.
  • the cooling bore diameter D (see also Figure 4 ) can be reduced while the cooling air velocity and pressure losses stay the same or increase only slightly.
  • the edge fillet 150 is only applied on one side of the bores and is thus asymmetric while the other side remains basically without edge fillet, in order to keep the minimum wall thickness as big as possible, i.e.at least one side or part-side of the circumferential area of the cooling bore inlet 160 are provided with an asymmetric edge fillet 150 in order to maximize the wall thickness downstream of the edge fillet between two adjacent cooling bores.
  • the side comprising the edge fillet 150 is applied at the front of the cooling bore 130 in direction of rotation of the rotor.
  • the edge fillet 150 referring to the asymmetric side of the bore 130 is ideally milled, wherein each other manufacturing is also possible, as a round fillet with a radius R (item 170) between factors 0.3 to 0.7 of the cooling bore diameter D.
  • the cooling bore 130 comprising a constant cooling bore diameter D in the region between the first end of said bore inlet location 160 which is located in the direction to the bore outlet portion 134 and said bore outlet portion 134. As described above the opposite second end of the bore inlet location 160 abuts on the rotor cavity 120.
  • the round fillet can be approximated by 3 or more milled chamfers with uniform angular steps in between.
  • the overall width w (see Figure 4 ) and the overall depth d of the edge fillet are also between factor 0.3 and 0.7 of the cooling bore diameter D.
  • the final aim of the present invention consists in introduction of an asymmetric edge fillet at the inlet of a rotating cooling bore in a rotor disc in order to improve the flow conditions at the inlet and, thus, to reduce the inlet pressure losses, allowing for a smaller bore diameter for a given mass flow. Accordingly, the remaining wall thickness between neighboring bores is improved which is beneficial for the rotor lifetime.
  • Figure 4 shows the embodiment of the present invention in accordance with section view IV-IV of Figure 2 , in order to keep the minimum wall thickness as big as possible with respect to the high number of cooling bores 130, the edge fillet 150 is only applied on one side or part-side of the bores and is thus asymmetric while the other side remains basically without edge fillet, in order to keep the minimum wall thickness as big as possible.
  • the edge fillet (see also description under Figure 3 ) referring to the asymmetric side of the bore 130 is ideally milled as a round fillet with a radius between factors 0.3 to 0.7 of the cooling bore diameters D. Due to manufacturing limitations, the round fillet can be approximated by 3 or more milled chamfers with uniform angular steps in between. In case the fillet is approximated by chamfers, the overall width w and the overall depth d (see Figure 4 ) of the edge fillet are also between factor 0.3 and 0.7 of the cooling bore diameter D.
  • the improved rotor shaft of the present invention is advantageous in various scopes.
  • the rotor shaft may be adaptable in terms of reducing effect of thermal and mechanical stresses arise thereon while a machine or turbines in which relation it is being used is in running condition.
  • the rotor shaft of the present disclosure is advantageous in withstanding or reducing effects of temperature and centrifugal or axial forces.
  • the improved rotor shaft with such a cross-sectional profile is capable of exhibiting the total life cycle to be increased by 2 to 5 times of the conventional rotor in the discussed location.
  • the rotor shaft of present disclosure is also advantageous in reducing the acting stresses in the area of the bore inlet by 10 to 40%.
  • the acting stresses are a mixture of mechanical and thermal stresses.
  • the rotor shaft is convenient to use in an effective and economical way.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15156738.5A 2015-02-26 2015-02-26 Rotorwelle mit Kühlbohrungseinlässen Active EP3061909B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15156738.5A EP3061909B1 (de) 2015-02-26 2015-02-26 Rotorwelle mit Kühlbohrungseinlässen

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15156738.5A EP3061909B1 (de) 2015-02-26 2015-02-26 Rotorwelle mit Kühlbohrungseinlässen

Publications (2)

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EP3061909A1 true EP3061909A1 (de) 2016-08-31
EP3061909B1 EP3061909B1 (de) 2018-10-03

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Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4203705A (en) * 1975-12-22 1980-05-20 United Technologies Corporation Bonded turbine disk for improved low cycle fatigue life
EP0926311A1 (de) * 1997-12-24 1999-06-30 Asea Brown Boveri AG Rotor einer Strömungsmaschine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4203705A (en) * 1975-12-22 1980-05-20 United Technologies Corporation Bonded turbine disk for improved low cycle fatigue life
EP0926311A1 (de) * 1997-12-24 1999-06-30 Asea Brown Boveri AG Rotor einer Strömungsmaschine

Also Published As

Publication number Publication date
EP3061909B1 (de) 2018-10-03

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