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
  • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
  • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
• • 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
  • F05D2260/30—Retaining components in desired mutual position
  • F05D2260/31—Retaining bolts or nuts
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49316—Impeller making
  • Y10T29/49318—Repairing or disassembling
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49316—Impeller making
  • Y10T29/4932—Turbomachine making
  • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

• the invention relates to a rotor for an axially flow-through turbomachine, comprising a number of a plurality of disc-shaped or drum-shaped rotor components and at least one extending through the rotor components through tie rods, on whose protruding ends in each case an abutment for axially clamping the rotor components arranged therebetween is screwed.
• a rotor for an axially flow-through turbomachine comprising a number of a plurality of disc-shaped or drum-shaped rotor components and at least one extending through the rotor components through tie rods, on whose protruding ends in each case an abutment for axially clamping the rotor components arranged therebetween is screwed.
• Such rotors are from the extensive existing
• a similar construction is also possible with decentralized tie rods, wherein, for example, twelve tie rods are arranged in the same radius distributed over the same radius.
• the object of the invention is to provide an alternative design of rotors for an axially permeable turbomachine. Another object of the invention is to provide the necessary components.
• the rotor-related object is achieved with a rotor according to the features of claim 1.
• the object directed to the components is achieved with a double nut according to the features of claim 11.
• Tie rod is axially divided in at least two tie rod elements and are, wherein the immediately adjacent tie rod elements are each releasably connected to each other via a connecting means.
• the rotor comprises along its longitudinal extent a first rotor end section, at least one further rotor section and a second rotor end section, wherein the connecting means is arranged axially in one of the further rotor sections.
• the connecting means and one of the rotor components are configured such that after releasing the arranged on the second rotor end portion abutment adjacent to the second rotor end portionffensstoff- with the disposed on the first rotor end portion abutment clamps the rotor components arranged therebetween.
• a particular advantage of this embodiment is that, in a first assembly step, that on the first Ankerelement adoptedfädelten rotor components of one of the two abutment and the connecting means can already be clamped, although the rotor is not yet fully equipped with rotor components. Only after fastening the second or further tie rod element, the further disc-shaped or drum-shaped rotor components are threaded onto this, after which the second counter bearing can then be screwed at the end of the second or further Buchankerelements, whereby all disk-shaped or drum-shaped Ro- torbaumaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschinemaschine
• the tension which in the meantime acts on one part of the disk-shaped or drum-shaped rotor components from one of the two counter bearings and the connecting element, is thereby released again.
• the elastic expansions of the two tie rod elements are matched to one another in such a way that the bracing of the rotor components between the two counter bearings at least partially, but preferably completely, completely releases the initial tensioning of counter bearing and connecting element.
• the connecting means is designed as a nut in which the opposite ends of axially adjacent tie rod elements are screwed.
• the connecting element is monolithically connected to one of the tie rod elements.
• a tie rod element can also have an internal thread as connection means for screwing on another tie rod element at one end.
• the connecting means has a plurality of openings for the passage of a fluid from one of the rotor (end) sections to another of the rotor (end) sections.
• the respective connecting means has a circumferentially arranged circumferential collar, in that the openings are arranged as passage openings for cooling fluid.
• the connecting means can also be used to realize a support of the tie rod to reduce vibrations during operation of the turbomachine. For this purpose, only a radial support of at least one of the rotor components on the respective connection means is required.
• the embodiment in which the rotor is designed as a gas turbine rotor, the first rotor end portion as a compressor rotor, the further rotor portion as a central rotor portion and the second rotor end portion as a turbine rotor.
• the central rotor section may be formed solely by a hollow shaft or by a plurality of blade-less rotor disks and the rotor end sections by rotor disks.
• the double nut for connecting two tie rod elements centrally between the two screw holes has an inwardly directed rim or a separating web, which prevents the tie rod elements are screwed too deep in the double nut.
• FIG. 1 shows a partial longitudinal section through a rotor according to the invention for a stationary axial flow turbine engine
• Figure 2 shows a detail of the longitudinal section of FIG
• FIG. 3 shows the same section of Figure 2, according to an alternative embodiment
• FIG. 4 shows a connection element for connecting two tension anchor elements with one arranged on the circumference
• FIG. 5 is a perspective view of the connecting element according to FIG. 4 and FIG.
• FIG. 6 shows a connecting element radially supported on the rotor component in a longitudinal section according to FIG. 2.
• the rotor 10 is designed as a gas turbine rotor, the remaining components of the gas turbine not being shown here.
• the design of the rotor 10 is fundamentally modular and can be used as a disk construction. to draw.
• the rotor 10 comprises a number of rotor disks 12, which are also referred to here as disc-shaped rotor components 14.
• the rotor 10 also comprises a drum-shaped rotor component 16, which in the exemplary embodiment is designated as the middle hollow shaft 18.
• the middle hollow shaft 18 In addition to the central hollow shaft 18, there is also a front hollow shaft 22 screwed onto a tie rod 20 and a rear hollow shaft 24 screwed on the opposite end.
• the front hollow shaft 22 is also referred to here as first counter bearing 26 and the rear hollow shaft 24 as second counter bearing 28.
• the two abutments 26, 28 clamp with the help of the tie rod 20, the rotor components 14, 16 with each other and press them firmly together. To achieve this, the entire tie rod 20 is elastically stretched by the two abutments 26, 28.
• the tie rod 20 comprises two separately produced tie rod elements 30, 32.
• the tie rod 20 also includes a connecting means 34 which connects the two monolithic tie rod elements 30, 32 releasably to each other.
• the connecting means 34 is designed as a nut or as a double nut, which has an inwardly directed collar 36 between its two screw-in openings 37 (FIG. 5).
• the rotor 10 can theoretically be axially divided into a first rotor end section 38, into a further rotor section 40 and into a second rotor end section 42, wherein the connecting means 34 is arranged axially in the further rotor section 40.
• the first rotor end section 38 is designed as a compressor rotor 44
• the second rotor end section 42 as a turbine rotor 48.
• a combustion chamber of the gas turbine is arranged radially outside the rotor 10.
• FIGS. 2 to 4 show a section from the transition region between the further rotor section 40 and the second rotor end section 42 in a longitudinal section. Shown are the two tie rod elements 30 and 32 as well as a double nut 35 which connects them to each other as connecting means 34.
• the central hollow shaft 18 is arranged radially adjacent to the double nut 35.
• the double nut 35 has a conical surface 50, whose pitch corresponds to an inwardly facing surface 52 of the central hollow shaft 18.
• a smaller shaft collar 54 is provided centrally between the two screw-in openings 37 of the double nut 35, the side surface 56 of which bears against a side surface 58 of the central hollow shaft 18 parallel thereto.
• the first abutment 26 is first screwed onto the tie rod element 30 at the end. Subsequently, this assembly is placed vertically, so that the individual disk-shaped or drum-shaped rotor components 14, 16 can be placed from above onto the first abutment 26. Subsequently, the double nut 35 is screwed onto the still free end of the tie rod element 30, during which the rotor components 14, 16 lying between the double nut 35 and the first abutment 26 are clamped together. Subsequently, the second tie rod element 32 is screwed into the double nut 35, after which provided for the turbine rotor 48 rotor disks 12 can be threaded onto the second tie rod element 32 from above and stored.
• the second abutment 28 is screwed onto the still free end of the tie rod element 32.
• the entire tie rod 20 is stretched so elastically that the bracing tion of the double nut 35 and the connecting means 34 and the first abutment 26 dissolves again.
• axially extending holes 60 may be provided both in the central hollow shaft 18 and in the double nut 35, with which a coolant from a rotor (end) section to another rotor (end) section can be passed.
• FIG. 3 shows the same section as FIG. 2, but with the construction for axial clamping in the region of the double nut 35 and the middle hollow shaft 18 being slightly modified compared with the construction according to FIG.
• the radial overlap of double nut and middle hollow shaft 18 required for establishing the axial clamping is effected here using a sleeve 62 provided with a collar therebetween.
• FIG 4 shows another embodiment for clamping the rotor components 14, 16 between a first counter bearing (not shown in FIG 4) and the connecting means 34.
• the connecting means 34 is again designed as a double nut 35 with two opposing Einschraubö réelleen 37.
• a larger shaft collar 54 is provided on the outer circumference, in which openings 64 distributed uniformly over the circumference are provided for the passage of a cooling fluid.
• the two parallel side surfaces 56 of the shaft collar 54 go over a radius in curved sloping flanks 57, which terminate at the screw-37 openings.
• This double nut 35 with the screw-in opening 37 and four uniformly distributed passage openings 64 is shown in FIG 5 in perspective view.
• a circumferential groove 66 with a support wire 68 lying therein can be provided on the shell-side surface of the shaft collar 54, with the aid of which the tie rod 20 extends radially on one of the rotor components, according to FIG 6 on the central hollow shaft 18, is supported.
• FIGS. 2 to 6 mean that they show gas turbine rotors 10 in which the second counter bearing 28 has not yet been screwed onto the second tie rod element 32, so that only those in FIGS. 2 to 6 to the left of the double nut 35 Rotor components shown 14, 16 are braced with the first abutment 26 and the rotor components 14, 16 shown to the right thereof not.
• the invention thus relates to a rotor 10 for an axially flow-through turbomachine, comprising a number of several disc-shaped or drum-shaped Rotorbau- parts 14, 16 and at least one extending through the rotor components 14, 16 extending pin-shaped tie rods 20, at its protruding ends in each case one Counter bearing 26, 28 is screwed for axial clamping of the rotor components 14, 16 arranged therebetween.
• the tie rod 20 comprises at least two axially adjacent tie rod elements 30, 32, which are each detachably connected to one another via a connecting means 34.

Landscapes

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

Priority Applications (10)

Applications Claiming Priority (2)

Publications (1)

Family

ID=49182221

Family Applications (2)

Family Applications After (1)

Country Status (12)

Cited By (5)

Families Citing this family (3)

Citations (5)

Family Cites Families (13)

• 2013
  • 2013-09-06 WO PCT/EP2013/068505 patent/WO2014037521A1/de active Application Filing
  • 2013-09-06 US US14/425,013 patent/US20150260044A1/en not_active Abandoned
  • 2013-09-06 CN CN201380046776.0A patent/CN104619954B/zh not_active Expired - Fee Related
  • 2013-09-06 KR KR1020157005723A patent/KR20150047509A/ko not_active Withdrawn
  • 2013-09-06 RU RU2015112596A patent/RU2015112596A/ru not_active Application Discontinuation
  • 2013-09-06 KR KR1020157005701A patent/KR20150047508A/ko not_active Withdrawn
  • 2013-09-06 US US14/425,016 patent/US20150247406A1/en not_active Abandoned
  • 2013-09-06 MX MX2015002944A patent/MX2015002944A/es unknown
  • 2013-09-06 JP JP2015530418A patent/JP2015527534A/ja not_active Ceased
  • 2013-09-06 CA CA2884133A patent/CA2884133A1/en not_active Abandoned
  • 2013-09-06 CA CA2884126A patent/CA2884126A1/en not_active Abandoned
  • 2013-09-06 EP EP13763011.7A patent/EP2888448A1/de not_active Withdrawn
  • 2013-09-06 RU RU2015109757A patent/RU2015109757A/ru not_active Application Discontinuation
  • 2013-09-06 JP JP2015530419A patent/JP2015528539A/ja active Pending
  • 2013-09-06 BR BR112015004983A patent/BR112015004983A2/pt not_active IP Right Cessation
  • 2013-09-06 EP EP13762773.3A patent/EP2880264A1/de not_active Withdrawn
  • 2013-09-06 BR BR112015004993A patent/BR112015004993A2/pt not_active IP Right Cessation
  • 2013-09-06 IN IN890DEN2015 patent/IN2015DN00890A/en unknown
  • 2013-09-06 CN CN201380046855.1A patent/CN104603396B/zh not_active Expired - Fee Related
  • 2013-09-06 WO PCT/EP2013/068507 patent/WO2014037523A1/de active Application Filing
• 2015
  • 2015-02-16 IN IN1253DEN2015 patent/IN2015DN01253A/en unknown
  • 2015-03-04 SA SA515360111A patent/SA515360111B1/ar unknown
  • 2015-03-04 SA SA515360112A patent/SA515360112B1/ar unknown

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