WO2021073786A1 - Rotor comprenant un composant de rotor disposé entre deux disques de rotor - Google Patents

Rotor comprenant un composant de rotor disposé entre deux disques de rotor Download PDF

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Publication number
WO2021073786A1
WO2021073786A1 PCT/EP2020/066858 EP2020066858W WO2021073786A1 WO 2021073786 A1 WO2021073786 A1 WO 2021073786A1 EP 2020066858 W EP2020066858 W EP 2020066858W WO 2021073786 A1 WO2021073786 A1 WO 2021073786A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
flank
groove
projection
annular groove
Prior art date
Application number
PCT/EP2020/066858
Other languages
German (de)
English (en)
Inventor
Peter Kury
Mirko Milazar
Christopher W ROSS
Yulia Bagaeva
Karsten Kolk
Ivan Lbov
Alexander Romanov
Harald Hoell
Kevin KAMPKA
Rene Mahnke
Andreas Föhrigen
Daniel Hofsommer
Ekkehard Maldfeld
Jörg Richter
Original Assignee
Siemens Energy Global GmbH & Co. KG
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 Energy Global GmbH & Co. KG filed Critical Siemens Energy Global GmbH & Co. KG
Priority to KR1020227016184A priority Critical patent/KR20220078706A/ko
Priority to US17/767,883 priority patent/US20240084708A1/en
Priority to CN202080073026.2A priority patent/CN114599859B/zh
Priority to JP2022520774A priority patent/JP7394979B2/ja
Priority to EP20735094.3A priority patent/EP4013950B1/fr
Publication of WO2021073786A1 publication Critical patent/WO2021073786A1/fr

Links

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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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
    • 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
    • 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
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/37—Retaining components in desired mutual position by a press fit connection

Definitions

  • Rotor component with a rotor arranged between two rotor disks
  • the invention relates to a rotor of a gas turbine which has at least two rotor disks connected to one another, between which an annular rotor component is arranged.
  • annular rotor component for shielding the inner region of the rotor from the hot gas flowing through the gas turbine being arranged between the rotor disks.
  • the two rotor disks each have a plurality of rotor blades distributed around the outer circumference. Between the two rows of rotor blades there is a row with guide vanes distributed around the circumference, each of which is attached to the stationary housing. Because of the rotation of the rotor, there is inevitably a gap between the guide vanes and the rotor blades. This basically allowed hot gas to enter the area radially inside the guide vanes.
  • an annular rotor component is arranged between the two adjacent rotor disks in some gas turbines. For this purpose, this rotor component is mounted on both sides of the rotor disk.
  • the rotor component basically only has the task of preventing the penetration of hot gas. There is usually no other function.
  • the mounting of the rotor component is kept simple in the usual way, with only one annular, axially extending shoulder engaging in a corresponding annular groove.
  • the rotor component is supported on both sides of the respective rotor disk with a press fit.
  • the rotor component is usually arranged at the location of the press fit on the side facing the rotor axis relative to the rotor disk. This is due in particular to the fact that, when centrifugal forces occur, the rotor component is subject to greater deformation than the rotor disks, which are solidly designed on the other hand.
  • the object of the present invention is therefore to ensure the position of the rotor component even during the heating and cooling of the gas turbine without exceeding the permissible stresses on the Ro gate component or on the rotor disks.
  • the generic rotor is initially used for use in a gas turbine. Regardless of this, however, it is also possible to use the embodiment of the rotor in another To bring flow machine, for example in a steam turbine, to use.
  • At least the rotor has a first rotor disk and a second rotor disk that is directly and firmly connected to the first rotor disk.
  • the rotor disks each have a plurality of blade holding grooves which axially penetrate the respective rotor disk, distributed on the outer circumference.
  • the blade retaining grooves serve to hold blades.
  • first rotor disk has a circumferential first fastening projection extending axially towards the second rotor disk radially below the blade retaining grooves.
  • second rotor disk has a circumferential second fastening projection extending axially towards the first rotor disk radially below the blade retaining grooves.
  • An annular rotor component is arranged between the two rotor disks in the area of the blade holding grooves and / or radially below the blade holding grooves. This encloses the rotor, which is located in sections within the rotor component, or sections of the two rotor disks.
  • the rotor component has a circumferential, axially opening first annular groove at one axial end and a circumferential, axially opening second annular groove axially opposite.
  • the first fastening projection of the first rotor disk engages in the first annular groove and the second fastening projection of the second rotor disk engages in the second annular groove.
  • a defined position of the rotor component is now ensured without inadmissibly high stresses occurring by, when the rotor is at a standstill, when the rotor is essentially at room temperature, a Pressing is provided on the outer circumference of the first fastening projection.
  • a first groove outer flank of the first annular groove rests against a first protruding outer flank of the first fastening protrusion under pressure.
  • connection of the rotor component to the second rotor disk is essentially stress-free when the rotor is at a standstill at room temperature. For this, it is necessary that there is play between a second outer flank of the second annular groove and a second outer flank of the second fastening projection and that there is play between a second inner flank of the second annular groove and a second inner flank of the second fastening projection is.
  • An advantageous coordination with regard to the fastening of the rotor component between the rotor disks and the compressive stresses that occur, taking into account a rotation of the rotor when the gas turbine is started up with the associated expansions of the rotor component and the rotor disks, is particularly advantageous if in a first transition state at a first speed of the rotor , there is a change in the fastening state from the first rotor disk to the second rotor disk.
  • the first speed is lower than the nominal speed at which the rotor is operated as intended.
  • the transition state gives the first outer flank of the groove the same contact with the first outer flank of the protrusion, and the second inner flank of the groove also bears against the second inner flank of the protrusion. In contrast to this, there remains undiminished play between the first inside flank of the groove and the first inside protrusion flank, as well as play between the second outside flank of the groove (35) and the second outside flank of the protrusion.
  • the first speed is advantageously greater than 0.2 times the nominal speed.
  • the design should provide that the first speed is less than 0.6 times the nominal speed.
  • the position of the rotor component relative to the rotor disks can advantageously be guaranteed when the gas turbine is started up.
  • the pressure between the first outer flank of the protrusion and the outer flank of the groove decreases, with contact between the second inner flank of the groove and the second inner flank of the protrusion.
  • the rotor component is fixed by the second rotor disk.
  • the second speed is higher than the first speed, but lower than the nominal speed of the Turbo machine.
  • a second speed can advantageously be assumed which corresponds to at least 0.8 times the nominal speed.
  • the components In the second transition state, the components have a second transition temperature.
  • the rotor component When the gas turbine is started up and all components are heated up, the rotor component usually heats up significantly faster than the more massive rotor disks due to its lower mass.
  • the second transition temperature is characterized in that the rotor component has almost reached the operating temperature, while the rotor disks, on the other hand, have a temperature that is significantly lower than the operating temperature, for example by approximately 30%.
  • An advantageous assembly of the rotor component in the rotor is made possible if the diameter of the first annular groove is set in a suitable ratio to the diameter of the first fastening projection. It is particularly advantageous here if the rotor component is heated to an assembly temperature of at least 100 ° C. and a maximum of 200 ° C. for assembly, while the rotor disks, on the other hand, are at room temperature. Taking into account the corresponding expansion of the rotor component due to the temperature increase, the required dimension of the first annular groove in relation to the first fastening projection can be determined. It is advantageous here if at the assembly temperature the pressure between the first groove outer flank and the first projection outer flank corresponds to a maximum of 10% of the pressure between the two components at room temperature. It is particularly advantageous here if the overlap existing at room temperature is essentially eliminated by means of the assembly temperature with a corresponding design of the diameter of the fastening projection and the annular groove.
  • the pressure between the first groove inner flank and the first protrusion inner flank may in this case be a maximum of 10% of the pressure that is present at room temperature between the first groove outer flank and the first protrusion outer flank. It is advantageous in any case if a play remains between the first groove inner flank and the first projection inner flank even at the assembly temperature.
  • the rotor component it has a cover section by means of which the blade holding grooves or the blade roots fastened in the blade holding grooves can be covered at least in sections by the rotor blade.
  • the cover section extends in the circumferential direction and radially.
  • the cover section is arranged radially outside of the first ring segment groove. It is further provided that the cover section rests axially with a support surface on an end face of the first rotor disk in the area between the blade holding grooves.
  • the rotor component has a cover section axially opposite on both sides.
  • the support surface rests against the end surface under pressure when the cover section is elastically deformed. It can thus be ensured that when the turbo machine is in operation from standstill up to the nominal speed at operating temperature, the support surface is always in contact with the end face.
  • the rotor component is heated to an assembly temperature between 100 ° C and 200 ° C, which is accompanied by a deformation of the rotor component and in particular of the cover section, so that in the intended position of the rotor component in the area of the annular groove relative to the fastening projection, the pressure between the support surface and the end face corresponds to a maximum of 10% of the pressure at room temperature.
  • This state with the deformation in particular of the cover section in the axial direction in the area of the support surface is favored on the one hand by the design of the rotor component with the cover section arranged at the axial end.
  • a design with a lower material thickness is effective in the central area between the two annular groove advantageous in terms of the desired deformation.
  • the desired effect can be promoted by the targeted increase in temperature, preferably in the area of the first annular groove.
  • the corresponding design of the rotor component in particular the definition of the diameter of the first annular groove and the second annular groove as well as the overlap between the support surface and the end face, taking into account the possible installation temperature of the rotor component, on the one hand, enables installation without too much effort and a secure location of the Rotor component guaranteed between the rotor disks in operation.
  • a free first expansion distance is maintained between a first projection end face of the first fastening projection and the first groove base of the first annular groove.
  • the first expansion distance here is at least 0.5 mm.
  • the first expansion distance is more than 5 mm.
  • a first expansion distance of at least 1 mm and a maximum of 2.5 mm is particularly advantageous.
  • a second expansion distance is present between a second projection end face of the second fastening projection and the second groove base of the second annular groove.
  • the second expansion distance should be a maximum of 0.2 times the first expansion distance.
  • the first rotor disk has to be made available once.
  • first rotor disk is stored horizontally with the rotor axis aligned vertically.
  • the rotor component must be heated to an assembly temperature of at least 100 ° C.
  • a temperature of 200 ° C should not be exceeded here.
  • the rotor component is to be placed on the first rotor disk in such a way that the first annular groove is located above the first fastening projection.
  • the rotor component can thus be pressed onto the first rotor disk until a support surface comes into contact with an end face of the rotor disk.
  • the target position of the rotor component relative to the rotor disk is achieved, the target position being achieved by a previously defined first expansion distance between a first projection face of the first fastening projection and the first groove base of the first annular groove is defined.
  • the rotor component can now cool down, during which the rotor component must be held in position relative to the first rotor disk.
  • the second rotor disk can be placed or pressed onto the first rotor disk and the rotor component at the same time.
  • the second fastening projection engages in the second annular groove.
  • an exemplary embodiment is outlined for a rotor according to the invention. Show it: 1 shows schematically in section the rotor component between two rotor disks;
  • Fig. 2 shows in detail the interference fit between the first loading fastening projection and the first annular groove
  • Fig. 3 in detail the game between the second fastening supply projection and the second annular groove
  • FIGS. 4-7 show the displacement of the rotor component relative to the rotor disks when the gas turbine is started up
  • FIGS. 8-11 show the assembly of the rotor component on the first rotor disk.
  • FIG. 1 the installation of the rotor component 21 between the rotor disks 01 and 11 is sketched schematically in a sectional illustration.
  • the rotor disks 01, 11 each have blade holding grooves 02, 12 that penetrate axially through the respective rotor disk 01, 11 on the outer circumference.
  • the blade retaining grooves 02, 12 are intended to accommodate blades.
  • the respective rotor disks 01, 11 in turn each have a fastening projection 04, 14 running around the rotor axis 10. As can be seen, the fastening projections 04, 14 each extend axially to the opposite rotor disk. That located between the two rotor disks 01, 11
  • Rotor component 21 covers the space between the rotor disks 01, 11.
  • the rotor component 21 has an annular groove 24, 34 on each of the axially opposite sides, into which the respective fastening projection 04, 24 engages.
  • the cover section 22, which 22 extends in the circumferential direction and radially, can also be seen at an axial end of the rotor component 21. This 22 covers the blade retaining grooves 02 in the first rotor disk.
  • the press fit between tween the first fastening projection 04 and the first annular groove 24 is now outlined in detail. For this purpose, the rotor component 21 is shown axially offset for better visibility.
  • the first rotor disk has a first outer projection flank 05 on the first fastening projection 04 on the radially outer side.
  • the first projection inner flank 06 is located on the radially opposite side.
  • the first projection end face 07 is located at the free end of the first fastening projection 04.
  • the rotor component 21 has a first groove on the first annular groove 24 on the radially outer side.
  • Outer flank 25 and on the radially inner side a first groove inner flank 26.
  • Opposite the first protrusion end face 07 is the first groove base 27 on the annular groove 24 available. This results from a geometric overlap 08 between the two corresponding components 01, 21.
  • On the radially opposite inner side there is a play 28 between the first projection inner flank and the first groove inner flank.
  • FIG. 3 the assembly between the second rotor disk 11 and the rotor component 21 is sketched in detail, the rotor component 21 being offset analogously to FIG. 2.
  • the second rotor disk 11 with rudimentary blade retaining groove 12 and the second fastening projection 14 can again be seen; this 14 has the second projection outer flank 15 on the radially outer side and the second projection inner flank 16 on the radially opposite side and the second projection end face 17 on the front side on.
  • the second groove outer flank 35 and opposite the second groove inner flank 36 and opposite the second projection end face 17 the second groove base 27 are located on the second annular groove 34 on the radially outer side.
  • FIG. 4 the state after assembly or in the idle state is sketched as described above.
  • FIG. 5 now shows the first transitional state when starting up the gas turbine. If the rotor is now set in motion, a first speed w ⁇ is reached, which w ⁇ is still well below the nominal speed wN, whereby the component temperatures T01, 11, 21 of the rotor disks 01, 14 and the rotor component can be slightly increased, but still far are removed from the operating temperature TN. It is essential that, in the first transitional state, the second groove inner flank 36 now rests against the second projection inner flank 16. Depending on the temperature T01, 11, 21 of the components 01, 11, 21 and the existing play 29 in the idle state, the installation takes place at different speeds, the play 29 preferably being set to a value that corresponds to an installation at approximately 0.3- times the nominal speed wN.
  • the second fastening projection 14 and the rotor component 21 on the radially inner side increases, whereas the pressure between the first fastening projection 04 and the rotor component 21 on the radially outer side decreases.
  • the second transition state which is sketched in FIG. 6, there is now a play on the radially outer side between the first fastening projection 04 and the rotor component 21 Free space is available.
  • the second speed w2 lies between the first speed w ⁇ in the first transition state and the nominal speed wN, the second speed w2 being approximately 0.6 times the nominal speed wN.
  • the component temperature T01, 11 of the rotor disks 01, 11 is significantly lower than that
  • Component temperature T21 of the rotor component which T21 gradually approaches the operating temperature TN.
  • FIGS. 8 to 11 the assembly of the rotor component 21 on the first rotor disk 01 is shown schematically. It should be noted at this point that, for advantageous assembly, the rotor disk 01 is aligned vertically and not horizontally as shown here, and the rotor component 21 is accordingly located above the rotor disk 0 1. As described above, it is provided that an overlap 08 between the first projection outer flank 0 5 of the first fastening projection 04 and the first groove outer flank 25 of the first annular groove 24 is present, so that a press fit is created. Furthermore, it is provided that the cover section 22 rests with a support surface 23 under pressure on an end surface 03 of the rotor disk 01. This requires the rotor component 21 to be heated for advantageous assembly.
  • FIG. 9 sketches the position of the rotor component 21 on the rotor disk 01 after the rotor component 21 has taken place until the support surface 23 rests on the end face 03.
  • an enlarged expansion distance 33 ′ remains between the first projection end face 07 and the first groove base 27.
  • the rotor component 21 is then pressed onto the first fastening projection 04 of the first rotor disk 01 until the previously defined expansion distance 33 is reached - see FIG. 10.
  • the deformation continues the cover section 22, an initial pressure being produced between the support surface 23 and the end surface 03.
  • FIG. 11 now shows the state when, starting from the desired position, as shown in FIG. 10, the rotor component 21 cools down again. Care must be taken that the expansion distance 33 is kept constant.
  • the temperature-related deformation of the cover section 22 now remains as a geometrically-related deformation with a pressure between the support surface 23 and the end face 03, here in FIG. 11 the theoretical state with an overlap 13 between the rotor component 21 and the rotor disk 01 is sketched.

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

Abstract

L'invention concerne un rotor d'une turbine à gaz comprenant deux disques de rotor adjacents (01, 11), sur chacun desquels sont fixées des pales mobiles, un composant de rotor annulaire (21) étant disposé entre les disques de rotor (01, 11) et présentant au niveau de ses extrémités opposées des rainures annulaires circonférentielles (24, 34), dans chacune desquelles s'engage une saillie de fixation circonférentielle (04, 14) sur le disque de rotor respectif (01, 11). Selon l'invention, lorsque le rotor est immobile, un premier flanc extérieur (25) de la première rainure annulaire (24) repose sous pression contre un premier flanc extérieur (05) de la première saillie de fixation (04) et il y a un jeu entre un premier flanc interne (26) de la première rainure annulaire (24) et un premier flanc interne (06) de la première saillie de fixation (04).
PCT/EP2020/066858 2016-02-05 2020-06-18 Rotor comprenant un composant de rotor disposé entre deux disques de rotor WO2021073786A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
KR1020227016184A KR20220078706A (ko) 2019-10-18 2020-06-18 2개의 로터 디스크들 사이에 배열된 로터 구성 요소를 구비한 로터
US17/767,883 US20240084708A1 (en) 2016-02-05 2020-06-18 Rotor comprising a rotor component arranged between two rotor discs
CN202080073026.2A CN114599859B (zh) 2019-10-18 2020-06-18 具有设置在两个转子盘之间的转子构件的转子
JP2022520774A JP7394979B2 (ja) 2019-10-18 2020-06-18 ２つのロータディスクの間に配置されたロータコンポーネントを有するロータ
EP20735094.3A EP4013950B1 (fr) 2019-10-18 2020-06-18 Rotor comprenant un composant de rotor disposé entre deux disques de rotor

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201962916811P 2019-10-18 2019-10-18
US62/916,811 2019-10-18

Publications (1)

Publication Number Publication Date
WO2021073786A1 true WO2021073786A1 (fr) 2021-04-22

Family

ID=71266618

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2020/066858 WO2021073786A1 (fr) 2016-02-05 2020-06-18 Rotor comprenant un composant de rotor disposé entre deux disques de rotor

Country Status (5)

Country Link
EP (1) EP4013950B1 (fr)
JP (1) JP7394979B2 (fr)
KR (1) KR20220078706A (fr)
CN (1) CN114599859B (fr)
WO (1) WO2021073786A1 (fr)

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EP2639409A2 (fr) * 2012-03-12 2013-09-18 General Electric Company Système d'étanchéité inter-étages de turbine
DE102014115197A1 (de) * 2013-10-28 2015-04-30 General Electric Company Dichtungsbauteil zur Reduktion von sekundärer Luftströmung in einem Turbinensystem

Also Published As

Publication number Publication date
CN114599859B (zh) 2023-11-17
KR20220078706A (ko) 2022-06-10
EP4013950A1 (fr) 2022-06-22
CN114599859A (zh) 2022-06-07
EP4013950B1 (fr) 2023-11-08
JP2022552170A (ja) 2022-12-15
JP7394979B2 (ja) 2023-12-08

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