EP2787168A2 - Turbomachine et rotor pour une turbomachine - Google Patents

Turbomachine et rotor pour une turbomachine Download PDF

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Publication number
EP2787168A2
EP2787168A2 EP20140002196 EP14002196A EP2787168A2 EP 2787168 A2 EP2787168 A2 EP 2787168A2 EP 20140002196 EP20140002196 EP 20140002196 EP 14002196 A EP14002196 A EP 14002196A EP 2787168 A2 EP2787168 A2 EP 2787168A2
Authority
EP
European Patent Office
Prior art keywords
rotor
rings
compressor
turbomachine
cavity
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
EP20140002196
Other languages
German (de)
English (en)
Other versions
EP2787168A3 (fr
EP2787168B1 (fr
Inventor
Harald Hoell
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP14002196.5A priority Critical patent/EP2787168B1/fr
Publication of EP2787168A2 publication Critical patent/EP2787168A2/fr
Publication of EP2787168A3 publication Critical patent/EP2787168A3/fr
Application granted granted Critical
Publication of EP2787168B1 publication Critical patent/EP2787168B1/fr
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
    • F01D5/026—Shaft to shaft connections
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • 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
    • F01D5/088—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in a closed cavity
    • 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
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing

Definitions

  • the invention relates to a rotor for a turbomachine, with a hollow shaft arranged coaxially with respect to its axis of rotation, which is supported on both sides on two axially opposite sections of the rotor, encloses an inner central cavity and is formed in the axial direction of the rotor of a plurality of contiguous rings that the adjacent and adjacent to the sections rings limit the cavity to the outside. Furthermore, the invention relates to a turbomachine with such a rotor.
  • FIG. 4 shows the FIG. 4 a gas turbine 1, which, arranged along a rotatably mounted about an axis 2 rotor 3, a compressor 5, a combustion chamber 6 and a turbine unit 11.
  • the compressor 5 as well as in the turbine unit 11 guide vanes 12, 35 on the housing and blades 15, 37 on the rotor 3 in each case with the formation of blade rings 17, 19, 36, 38 attached.
  • a vane ring 19, 36 forms with the blade ring 17, 38 a compressor stage 21 and a turbine stage 34, wherein a plurality of stages are connected in series.
  • the blades 15 of a ring 17, 38 are fixed to the rotor 3 by means of an annular, centrally perforated disc 26, 39.
  • a central tie rod 7 which braces the turbine disks 39 and compressor disks 26 with each other. Further, for bridging the distance caused by the combustion chamber 6, between the compressor 5 and the turbine unit 11 between the compressor disk 26 of the last compressor stage 21 and the turbine disk 39 of the first turbine stage 34, a hollow shaft 13 is arranged.
  • the compressor 5 sucks in ambient air and compresses it.
  • the compressed air is mixed with a fuel and fed to the combustion chamber 6, in which the mixture is burned to a hot working medium M.
  • the latter flows from the combustion chamber 6 in the turbine unit 11 and drives by means of the blades 15 to the rotor 3 of the gas turbine 1, which drives the compressor 5 and a working machine, for example a generator.
  • the torque acting on the blades of the turbine unit and generated by the working fluid is transmitted to the generator as useful energy and to the compressor as driving energy for compressing the ambient air. Therefore, the hollow shaft must transmit the required for the compression of the ambient air in the compressor drive energy from the turbine disk of the first turbine stage to the compressor disk of the last compressor stage.
  • the combustion chamber of the gas turbine which can heat inadmissible this axial region of the rotor during operation.
  • thermal stresses can occur, which can weaken the strength as well as rigidity of the hollow shaft, so that the mechanical stress occurring can cause premature fatigue of the material of the hollow shaft.
  • a rotor for a compressor which is formed from a plurality of axially adjacent, tensioned compressor disks.
  • the compressor discs have a central opening which forms a hollow shaft.
  • the shows GB 661,078 a hollow shaft for a gas turbine rotor, which is formed from two adjacent pipe sections radially within the combustion chamber.
  • the object of the invention is to provide a rotor for a turbomachine, which has a longer service life and a lower susceptibility to mechanical defects. It is another object of the invention to provide a turbomachine for this purpose.
  • the invention provides in the case of the rotor mentioned at the outset that one of the two sections of the rotor is formed by a compressor disk and the other section is formed by a turbine disk and the rotor has at least one tie rod extending parallel to the axis of rotation, which clamps the disks and the ring extends therethrough, each ring being I-shaped in cross-section, the land of the I-shape extending in the radial direction of the rotor.
  • the invention is based on the consideration that the hollow shaft, which is subject to high mechanical and thermal loads, is replaced in the region of the combustion chamber by a plurality of contiguous and comparatively short rings in the axial direction.
  • the mechanical stresses can be significantly reduced.
  • the stresses and the resulting resulting creep deformations are reduced. This increases the life of each ring.
  • the hollow shaft by transmission of the energy required by the compressor over its axial length especially stressed on torsion.
  • the axial length of a ring over the previous overall lengths of the hollow shaft is greatly shortened, so that each ring is much less stressed to torsion. Therefore, the mechanical loads are further reduced with the invention.
  • one of the two sections is designed as a compressor disk and the other as a turbine disk, the power required to compress the intake ambient air at the compressor is transmitted without loss from the turbine unit to the compressor by means of the rings arranged therebetween.
  • the rings with their webs extending in the radial direction, effect a better thermal insulation of the central hollow space by means of an intermediate further hollow space with respect to a radially outer area, so that colder air is present in the hollow space on the surfaces of the component. Consequently, the areas with particularly high mechanical loads during operation of the turbomachine below a transition temperature required for the creep (activation energy) are operated, so that especially at this point creep can be avoided. Thus, the thermal load of the rings is further reduced, which allows a higher mechanical load.
  • the I-shaped cross section of the rings allows a particularly stiff, lightweight and mechanically resilient design of the ring.
  • the rotor has at least one tie rod extending parallel to the axis of rotation.
  • the sections of the rotor are each formed by a disc, wherein the at least one tie rod for bracing the discs and the rings extends through them.
  • the tie rod extends centrally through the discs and through the rings.
  • the tie rod which is centrally arranged relative to the axis of rotation, can clamp the stacked rings and disks of the compressor and of the turbine unit and at the same time be used for the axial and radial bearing of the rotor.
  • the rotor has a plurality of tie rods spaced apart from the axis of rotation, which extend through the disks and the rings.
  • the application of the multi-piece hollow shaft is thus also applicable to rotors, which provides the tension with multiple tie rods.
  • each ring and each section has positive-locking means for transmitting the torque of the rotor from one of the two sections to the opposite section.
  • a known loss as loss relative movement in the circumferential direction between the immediately adjacent rings or between a ring and a portion can thus be effectively avoided.
  • the means for transmitting the torque at the end faces of the ring and at which the portions are designed as spur toothing in the manner of a Hirth toothing This positive engagement allows a slip-free operation of the rotor.
  • an axially extending flange is arranged at each end of the web, so that between two adjacent rings and between the radially inner flanges and the radially outer flanges, a further cavity is formed.
  • This allows a spatial separation of a region of the combustion chamber radially outer and relatively hot outer region of a closed by the rings central cavity.
  • the heat input from the outer region into the rings, in particular into the radially inner flanges of the rings can be reduced, since the further cavity isolates the central cavity from the outer region, so that colder air is present in the cavity on the surfaces of the component.
  • the further cavities may be in fluid communication with each other via passages located in the webs. Either the connections between two adjacent further cavities leads to a faster and more uniform insulating effect, or they serve as connection channels for the cooling medium, if this compressor side in the form of compressor air in the other cavity can be supplied and removed turbine side. In this case, in the compressor, the compressor air can take place both by removal openings arranged in the rotor or behind the compressor by a suitable device.
  • the cavity can be flowed through in the axial direction by a cooling medium.
  • the rings and the portions for sealing the cavity have labyrinth-like sealing means.
  • the sealing means may be provided on the flanges of the rings, on which no means for transmitting the torque are provided.
  • a flange of the ring may be designed comparatively broad in its radial material thickness, which then transmits the torque, and the other flange be designed comparatively narrow, which then serves only for sealing the cavity to the outside and to form the further cavity.
  • the cooling air cools the rings so that the average component temperature decreases.
  • the invention leads to the solution of the task directed to an initially mentioned turbomachine, that the rotor is designed according to one of claims 1 to 11.
  • turbomachine is designed as a gas turbine and in which the gas turbine along the rotor successively a compressor, at least one combustion chamber and a turbine unit, wherein one of the two sections by a compressor disc arranged in the compressor and the other section is formed by a turbine disk arranged in the turbine unit.
  • FIG. 1 shows a rotor 3 of a gas turbine 1 with a central tie rod 7 in a longitudinal section in the region between compressor 5 and turbine unit 11. From the compressor 5, a flow channel 23 is shown with only the last compressor stage 21. Along the rotatable about the rotation axis 2 rotor 3 follows a compressor outlet 25, a diffuser 27 and a combustion chamber 29. The latter has a combustion chamber 31, which opens into a hot gas duct 33 of a turbine unit 11.
  • rotatable guide vanes 12 are mounted in rings 19. These are upstream of blades 15, which are mounted on the rotor 3 by means of a compressor disk 26.
  • the hot gas passage 33 has vanes 35 and further downstream blades 37.
  • the stationary vanes 35 are connected to the housing of the gas turbine 1, whereas the blades 37 are fixed to a turbine disk 39.
  • the rotor 3 has, between the compressor disk 26 and the turbine disk 39, three axially successive rings 43 instead of the one-piece hollow shaft known from the prior art.
  • each ring 43 is I-shaped in cross section, so that two flanges 45, 46 extending in the axial direction of the tie rod 7 are connected to one another via a web 47 extending in the radial direction.
  • an axially extending central cavity 51 which is suitable for guiding a cooling fluid, for example compressor air.
  • a cooling fluid for example compressor air.
  • the serration is arranged, with which the torque of the rotor 3 is passed from the turbine disk 39 via the rings 43 to the compressor disk 26.
  • the end faces 57 of the turbine disk 39 and the compressor disk 26 likewise have the serration.
  • the radially inner flanges 46 of the rings 43 have on their end faces 59 labyrinth-like seals 62, which seal the cavity 51 against the outer region 61.
  • the outer flanges 45 pass through the torque from one end face 55 to its opposite end face 55, the outer flanges 45 have a greater width in the radial direction than the inner flanges 46, which carry only the seals 62.
  • air is compressed by the compressor 5 in the flow channel 23 of the compressor 5, wherein a proportion of the compressed air as cooling air through disc bores 24 is removed and guided according to the arrows 63 along the tie rod 7 from the compressor-side end of the cavity 51 to the turbine end.
  • Disc bores 24 located in the turbine disk 39 from inner diameter to outer diameter guide the cooling air to the blades 37 of the first turbine stage 34. The cooling air cools the blades 37 and then escapes into the hot gas passage 33.
  • the labyrinth seals 65 and the seals 62 provided between tie rods 7 and disks 26, 39 prevent escape of the cooling air from the cavity 51.
  • FIG. 2 shows a rotor 3 of a gas turbine 1 with a plurality of tie rods 8 in a longitudinal section in the region between the compressor 5 and the turbine unit 11.
  • FIG. 1 shows FIG. 2 the compressor 5, the combustion chamber 6, the turbine unit 11 and the rotor 3 assembled from compressor disks 26, turbine disks 39 and rings 43
  • FIG. 1 shown central tie rod 7 is in FIG. 2 one of a plurality of spaced apart from the axis of rotation 2 decentralized tie rods 8 is shown.
  • the decentralized tie rod 8 is so spaced from the axis of rotation 2 that the webs 47 of the rings 43 are penetrated by him.
  • the distance could be chosen so that the tie rod 8 pierces the flanges 45 of the rings.
  • FIG. 3 a tensioned with a central tie rod rotor, in which, for example in a radially outer flange 45 of the compressor side arranged ring 43 holes 71 may be provided through which still comparatively cool Verreterend Kunststoff in a formed between the radially inner and radially outer flanges 45, 46 cavity 66th
  • holes 71 may be provided through which still comparatively cool Verreterend Kunststoff in a formed between the radially inner and radially outer flanges 45, 46 cavity 66th
  • the cooling air flowing into the further cavity 66 "is guided through passages 72 located in the webs 47 in the direction of the turbine unit and further via disk bores 24 to the turbine blades 27 of the first turbine stage, where it can be used as cooling air.
  • the central cavity 51 serves in this case as a supply channel for cooling air for the turbine blades 37 of the second turbine stage 34th
  • a gap 69 can be made possible between the compressor disk 26 and the radially inner flange 46 of the ring 43 resting against it, in order to bring about a targeted supply of cooling air into a further cavity 66 'radially delimited by the flanges 45, 46.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14002196.5A 2004-03-17 2005-03-10 Rotor pour une turbomachine avec un arbre creux Active EP2787168B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14002196.5A EP2787168B1 (fr) 2004-03-17 2005-03-10 Rotor pour une turbomachine avec un arbre creux

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04006393A EP1577493A1 (fr) 2004-03-17 2004-03-17 Turbomachine et rotor pour une turbomachine
EP05715935.2A EP1725741B1 (fr) 2004-03-17 2005-03-10 Rotor de turbomachine
EP14002196.5A EP2787168B1 (fr) 2004-03-17 2005-03-10 Rotor pour une turbomachine avec un arbre creux

Related Parent Applications (2)

Application Number Title Priority Date Filing Date
EP05715935.2A Division-Into EP1725741B1 (fr) 2004-03-17 2005-03-10 Rotor de turbomachine
EP05715935.2A Division EP1725741B1 (fr) 2004-03-17 2005-03-10 Rotor de turbomachine

Publications (3)

Publication Number Publication Date
EP2787168A2 true EP2787168A2 (fr) 2014-10-08
EP2787168A3 EP2787168A3 (fr) 2015-04-15
EP2787168B1 EP2787168B1 (fr) 2016-01-06

Family

ID=34833623

Family Applications (3)

Application Number Title Priority Date Filing Date
EP04006393A Withdrawn EP1577493A1 (fr) 2004-03-17 2004-03-17 Turbomachine et rotor pour une turbomachine
EP05715935.2A Active EP1725741B1 (fr) 2004-03-17 2005-03-10 Rotor de turbomachine
EP14002196.5A Active EP2787168B1 (fr) 2004-03-17 2005-03-10 Rotor pour une turbomachine avec un arbre creux

Family Applications Before (2)

Application Number Title Priority Date Filing Date
EP04006393A Withdrawn EP1577493A1 (fr) 2004-03-17 2004-03-17 Turbomachine et rotor pour une turbomachine
EP05715935.2A Active EP1725741B1 (fr) 2004-03-17 2005-03-10 Rotor de turbomachine

Country Status (6)

Country Link
US (1) US7585148B2 (fr)
EP (3) EP1577493A1 (fr)
JP (1) JP4722120B2 (fr)
CN (1) CN101010486B (fr)
RU (1) RU2347912C2 (fr)
WO (1) WO2005093219A1 (fr)

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Also Published As

Publication number Publication date
EP1725741B1 (fr) 2014-09-24
RU2347912C2 (ru) 2009-02-27
JP2007529668A (ja) 2007-10-25
EP1725741A1 (fr) 2006-11-29
WO2005093219A1 (fr) 2005-10-06
JP4722120B2 (ja) 2011-07-13
EP1577493A1 (fr) 2005-09-21
US7585148B2 (en) 2009-09-08
EP2787168A3 (fr) 2015-04-15
US20080159864A1 (en) 2008-07-03
RU2006136413A (ru) 2008-04-27
CN101010486A (zh) 2007-08-01
CN101010486B (zh) 2011-06-01
EP2787168B1 (fr) 2016-01-06

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