WO2022091798A1 - Joint d'étanchéité en nid d'abeilles et machine rotative - Google Patents

Joint d'étanchéité en nid d'abeilles et machine rotative Download PDF

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Publication number
WO2022091798A1
WO2022091798A1 PCT/JP2021/038035 JP2021038035W WO2022091798A1 WO 2022091798 A1 WO2022091798 A1 WO 2022091798A1 JP 2021038035 W JP2021038035 W JP 2021038035W WO 2022091798 A1 WO2022091798 A1 WO 2022091798A1
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WO
WIPO (PCT)
Prior art keywords
partition wall
honeycomb seal
strength
honeycomb
rotor
Prior art date
Application number
PCT/JP2021/038035
Other languages
English (en)
Japanese (ja)
Inventor
亜積 吉田
信広 國武
正樹 種池
敦司 清水
Original Assignee
三菱重工業株式会社
三菱パワー株式会社
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 三菱重工業株式会社, 三菱パワー株式会社 filed Critical 三菱重工業株式会社
Publication of WO2022091798A1 publication Critical patent/WO2022091798A1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16J—PISTONS; CYLINDERS; SEALINGS
    • F16J15/00—Sealings
    • F16J15/44—Free-space packings

Definitions

  • the present disclosure relates to honeycomb seals and rotary machines.
  • the present application claims priority with respect to Japanese Patent Application No. 2020-182710 filed in Japan on October 30, 2020, the contents of which are incorporated herein by reference.
  • Patent Document 1 discloses a honeycomb seal used for a gas turbine or the like.
  • the honeycomb seal is a kind of so-called abradable seal, and is a free-cutting body (seal member) that is interposed between the stator and the rotor and is cut by the fins on the rotor side.
  • the honeycomb seal itself is cut into the fins in the turbine casing to secure a suitable clearance between the honeycomb seals and the fins.
  • the inside of the turbine casing becomes hot during the operation of the gas turbine, so that the partition wall of the honeycomb seal is subjected to high-temperature oxidative thinning, and the sealing performance may be deteriorated. Further, if the thickness of the partition wall is increased, the machinability of the honeycomb seal by the fins of the moving blades deteriorates.
  • the present disclosure has been made to solve the above problems, and an object of the present invention is to provide a honeycomb seal and a rotary machine capable of improving machinability while suppressing deterioration of sealing performance. ..
  • the honeycomb seal according to the present disclosure includes a honeycomb structure in which a plurality of holes arranged so as to be recessed from the sealing surface are partitioned by a partition wall, and the partition wall is the hole portion. It has a high-strength portion and a low-strength portion having a lower strength than the high-strength portion at different positions in the depth direction.
  • the rotary machine according to the present disclosure includes a rotor that rotates around an axis, a stator that surrounds the rotor, and a sealing device that seals a space between the rotor and the stator. It has the honeycomb seal provided on one of the rotor and the stator, and fins provided on the other of the rotor and the stator so as to face the honeycomb seal.
  • the gas turbine 1 includes a compressor 2 that generates compressed air, a combustor 9 that produces combustion gas by mixing fuel with compressed air and burning it, and combustion. It comprises a gas-driven turbine 10.
  • the compressor 2 has a compressor rotor 3 that rotates around the axis ⁇ , and a compressor casing 4 that covers the compressor rotor 3 from the outer peripheral side.
  • the compressor rotor 3 has a columnar shape extending along the axis ⁇ .
  • Each compressor blade stage 5 has a plurality of compressor blades arranged at intervals in the circumferential direction of the axis ⁇ on the outer peripheral surface of the compressor rotor 3.
  • the compressor casing 4 has a cylindrical shape centered on the axis ⁇ .
  • a plurality of compressor stationary blade stages 7 arranged at intervals in the axis ⁇ direction are provided on the inner peripheral surface of the compressor casing 4. These compressor static blade stages 7 are alternately arranged with respect to the above-mentioned compressor moving blade stage 5 when viewed from the axis ⁇ direction.
  • Each compressor stationary blade stage 7 has a plurality of compressor stationary blades arranged at intervals in the circumferential direction of the axis ⁇ on the inner peripheral surface of the compressor casing 4.
  • the combustor 9 is provided between the compressor 2 and the turbine 10 continuing to the downstream side (right side in FIG. 1).
  • the compressed air generated by the compressor 2 is mixed with the fuel inside the combustor 9 to become a premixed gas. Combustion of this premixed gas in the combustor 9 produces high-temperature and high-pressure combustion gas, and the combustion gas is guided into the turbine 10.
  • the turbine 10 has a rotor 11 that rotates about an axis ⁇ and a stator 12 that surrounds the rotor 11.
  • FIG. 2 is an enlarged view of part II of FIG. Hereinafter, it will be described with reference to FIG.
  • the rotor 11 has a rotary shaft 11a and a plurality of turbine blade stages 20.
  • the rotating shaft 11a has a columnar shape extending along the axis ⁇ .
  • the rotating shaft 11a is integrally connected to the compressor rotor 3 in the axis ⁇ direction to form a gas turbine rotor that rotates around the axis ⁇ .
  • the plurality of turbine blade stages 20 are provided on the outer peripheral surface of the rotating shaft 11a, and are arranged at intervals in the axis ⁇ direction.
  • Each turbine blade stage 20 has a plurality of turbine blades 30 and an annular shroud 42.
  • the plurality of turbine blades 30 are arranged on the outer peripheral surface of the rotor 11 at intervals in the circumferential direction of the axis ⁇ .
  • the shroud 42 is provided at the blade tips of a plurality of turbine blades 30, and is integrated with the turbine blades 30 arranged in the circumferential direction of the axis ⁇ to increase the rigidity of the turbine blade stage 20.
  • the stator 12 has a turbine casing 15, a plurality of turbine stationary blade stages 13, and an annular holding ring 40.
  • the turbine casing 15 has a cylindrical shape centered on the axis ⁇ .
  • the plurality of turbine stationary blade stages 13 are provided on the inner peripheral side of the turbine casing 15, and are arranged at intervals in the axis ⁇ direction. These turbine blade stages 13 are alternately arranged with respect to the turbine blade stage 20 when viewed from the axis ⁇ direction.
  • Each turbine vane stage 13 has a plurality of turbine vanes 14 arranged at intervals in the circumferential direction of the axis ⁇ near the inner peripheral surface of the turbine casing 15.
  • the holding ring 40 is provided in an annular shape over the inner peripheral surface of the turbine casing 15.
  • the holding ring 40 is provided to prevent the high-temperature and high-pressure combustion gas from coming into direct contact with the turbine casing 15.
  • the number of holding rings 40 is the same as the number of stages of the turbine blade stage 20 on the inner peripheral surface of the turbine casing 15 so as to correspond to the turbine blade stage 20.
  • the turbine vane 14 is supported across the holding rings 40 adjacent to each other in the axis ⁇ direction.
  • a sealing device between the turbine blade 30 and the holding ring 40 to prevent combustion gas from leaking from between the turbine blade 30 and the holding ring 40 to the space near the turbine stationary blade 14 existing in the subsequent stage. 50 is provided. That is, the sealing device 50 seals the space between the rotor 11 and the stator 12.
  • the sealing device 50 has a honeycomb seal 44 and fins 43.
  • the honeycomb seal 44 is provided on the inner peripheral surface of the holding ring 40.
  • the fin 43 is provided on the outer peripheral surface of the shroud 42, and the radial outer end portion of the fin 43 faces the honeycomb seal 44 through a minute gap.
  • honeycomb seal 44 of the first embodiment will be described with reference to FIGS. 3 and 4.
  • FIG. 3 is a schematic view showing a part of the honeycomb seal 44.
  • the honeycomb seal 44 includes a honeycomb structure 45.
  • the surface of the honeycomb structure 45 facing outward in the radial direction is an outer peripheral surface fixed to the holding ring 40.
  • the surface of the honeycomb structure 45 facing inward in the radial direction is a sealing surface 46 facing the fin 43.
  • the inside of the honeycomb structure 45 has a structure in which a plurality of holes arranged so as to be recessed from the sealing surface 46 are partitioned by a partition wall 47.
  • the honeycomb structure 45 is a structure as a free-cutting body having a continuous honeycomb shape composed of a substantially regular hexagonal void and a partition wall 47.
  • the sealing surface 46 is a virtual surface formed by an end surface of the partition wall 47 of the honeycomb structure 45 facing the turbine blade 30 side, and is close to the radial outer end portion of the fin 43.
  • the partition wall 47 is made of a material that is softer than the material of the fin 43.
  • a free-cutting material containing a metal such as nickel is adopted as the material of the partition wall 47.
  • the partition wall 47 has a high-strength portion 48 and a low-strength portion 49 having a lower strength than the high-strength portion 48 at different positions in the depth direction H of the hole portion.
  • FIG. 4 is a cross-sectional view of one partition wall 47 of the honeycomb structure 45 shown in FIG. 3 in the IV-IV direction.
  • the high-strength portion 48 is a thick portion 48a having a predetermined plate thickness.
  • the low-strength portion 49 is a thin-walled portion 49a having a plate thickness thinner than that of the thick-walled portion 48a.
  • a plurality of thick portions 48a and thin wall portions 49a are formed alternately in the depth direction H of the holes of the partition wall 47.
  • the depth direction H shown in the text of the present specification is a direction substantially orthogonal to the sealing surface 46 of the honeycomb structure 45 and toward the holding ring 40 from the sealing surface 46 in the hole portion.
  • the surface of the partition wall 47 facing the inside of the hole has a substantially sinusoidal shape wavy in the depth direction H.
  • the waveforms of the pair of surfaces facing the inside of the hole of the partition wall 47 are formed substantially symmetrically with respect to the center line C of the cross section of the partition wall 47.
  • the wavelength ⁇ and the amplitude A of the waveform of the surface facing the inside of the hole of the partition wall 47 are selected to be suitable values at the time of manufacturing the honeycomb structure 45.
  • the wavelength ⁇ of the waveform (sine wave) of the surface facing the inside of the hole of the partition wall 47 is 10 to 100 ⁇ m. More preferably, it is 25 to 50 ⁇ m.
  • the amplitude A of the waveform (sine wave) of the surface facing the inside of the hole of the partition wall 47 is 10 to 100 ⁇ m. More preferably, it is 12 to 25 ⁇ m.
  • the thick portion 48a is a part of the partition wall 47, and the thick portion 48a is sandwiched between a portion of the surface of the partition wall 47 facing the inside of the pair of holes, which is a convex portion (corresponding to a mountain portion of a wave) and a portion in the vicinity thereof. It is a part.
  • the thin-walled portion 49a is a part of the partition wall 47, and the thin-walled portion 49a is a portion of the surface of the partition wall 47 facing the inside of the pair of holes, which is sandwiched between a portion (corresponding to a valley of a wave) and a portion in the vicinity thereof. ..
  • the thin-walled portion 49a is thinner than the thick-walled portion 48a, it is less susceptible to stress applied to the partition wall 47 than the thick-walled portion 48a. Therefore, when stress is applied, it is likely to break starting from the thin portion 49a.
  • the operation of the fin 43 according to the present embodiment will be described.
  • the turbine blades 30 in the turbine casing 15 may thermally expand, and the rotor 11 may be shaken.
  • the radially outer end of the fin 43 which was located radially inside the seal surface 46, advances radially outward from the seal surface 46, and the fin 43 joins the honeycomb structure 45.
  • the end of the fin 43 comes into contact with the honeycomb structure 45, stress is applied to the partition wall 47 of the honeycomb structure 45 in contact with the end of the fin 43 in the rotational direction of the fin 43.
  • the honeycomb seal 44 has a configuration in which a plurality of thick portions 48a and thin portions 49a are alternately formed in the depth direction H of the holes of the partition wall 47.
  • the thin wall portion 49a existing at the position closest to the sealing surface 46 becomes the starting point of the partition wall 47. Part of it breaks. That is, the partition wall 47 from the sealing surface 46 to the thin-walled portion 49a located at the nearest position is easily cut by the tip portion of the fin 43. Therefore, the machinability of the honeycomb seal 44 can be improved.
  • each thin-walled portion 49a is cut by the fins 43 in order from the sealing surface 46.
  • the partition wall 47 is not cut excessively. Therefore, the partition wall 47 can be efficiently cut, and the honeycomb seal 44 can be used for a long period of time.
  • the plate thickness of the thin portion 49a is set to a thickness that can secure high temperature oxidation resistance, machinability can be ensured. Further, the presence of the thick portion 48a can ensure the high temperature oxidation resistance of the entire partition wall 47 and suppress the deterioration of the sealing performance.
  • honeycomb seal 44 of the second embodiment of the present disclosure has the same configuration as that of the first embodiment except for the configuration of the partition wall 47.
  • the same components as those in the first embodiment are designated by the same reference numerals, and detailed description thereof will be omitted.
  • FIG. 5 is a cross-sectional view taken along the line VV of one partition wall 47 of the honeycomb structure 45 shown in FIG.
  • the partition wall 47 has a high-strength portion 48 and a low-strength portion 49 having a lower strength than the high-strength portion 48, as in the first embodiment, at different positions in the depth direction H of the hole portion.
  • the partition wall 47 has a plurality of defects 49c which are voids in the plate thickness (the surface and the inside of the partition wall 47).
  • the defects 49c are scattered in the plate thickness of the partition wall 47, and the defects 49c are intentionally created in the molding process of the partition wall 47.
  • the defect 49c is a crack extending from the surface to the inside or a gap as a closed space existing inside.
  • the low-strength portion 49 is a part of the partition wall 47, and is a portion in the vicinity of the defect 49c including the defect 49c. That is, the low-strength portion 49 is a defective portion 49b having a defect 49c in the plate thickness of the partition wall 47.
  • the high-strength portion 48 is a part of the partition wall 47 and is a portion having no defect 49c. That is, the high-strength portion 48 is a defect-free portion 48b having no defect 49c in the plate thickness of the partition wall 47.
  • the defective portion 49b has a defect 49c in the plate thickness, so that the defective portion 49b has a lower strength than the non-defect portion 48b, and the fins. It is vulnerable to stress applied in the rotation direction of 43. Therefore, when stress is applied, it is easy to break from the defective portion 49b as a starting point.
  • the honeycomb seal 44 according to the second embodiment of the present disclosure has a configuration in which a plurality of defective portions 48b and defective portions 49b are alternately formed in the depth direction H of the hole portion of the partition wall 47.
  • the defective partition wall 49b existing at the position closest to the sealing surface 46 becomes the starting point of the partition wall 47. Part of is broken. That is, the partition wall 47 from the sealing surface 46 to the defective portion 49b existing at the nearest position is easily cut by the tip portion of the fin 43. Therefore, the machinability of the honeycomb seal 44 can be improved.
  • each defective portion 49b is cut by the fin 43 in order from the sealing surface 46.
  • the partition wall 47 is not cut excessively. Therefore, the partition wall 47 can be efficiently cut, and the honeycomb seal 44 can be used for a long period of time.
  • the machinability can be improved by the presence of the defective portion 49b, and the plate thickness does not need to be suppressed, so that the high temperature oxidation resistance can be ensured.
  • the partition wall 47 of the honeycomb structure 45 of the above embodiment may be manufactured by a laminating molding (AM) process using a 3D printer using a powder material.
  • AM laminating molding
  • the honeycomb structure 45 of the above embodiment is a structure in which a honeycomb structure composed of a substantially regular hexagonal void and a partition wall 47 is continuous, but is not limited to a substantially hexagonal shape. ..
  • the defect 49c is formed in the manufacturing process of the honeycomb structure 45, but the partition wall 47 is manufactured by a method in which the defect 49c is not formed, and the surface is cut out to intentionally scratch or crack. , And using them as defects 49c, a defective portion 49b may be created later.
  • the partition wall 47 of the honeycomb structure 45 has a thick portion 48a and a defect-free portion 48b, a thin portion 49a, and a thin portion 49a.
  • the defective portion 49b may coexist.
  • honeycomb seal 44 of the above embodiment is provided on the stator 12 side and faces the fin 43 on the rotor 11 side, but the honeycomb seal 44 is provided on the rotor 11 side and is provided on the stator 12 side. It may be configured to face the fin 43.
  • honeycomb seal 44 of the above embodiment is the honeycomb seal 44 used for the gas turbine 1, but may be used for other rotating machines such as a steam turbine.
  • honeycomb seal 44 and the rotating machine according to the embodiment are grasped as follows, for example.
  • the honeycomb seal 44 includes a honeycomb structure 45 in which a plurality of holes arranged so as to be recessed from the sealing surface 46 are partitioned by a partition wall 47, and the partition wall 47 is the hole.
  • a high-strength portion 48 and a low-strength portion 49 having a lower strength than the high-strength portion 48 are provided at different positions in the depth direction H of the portions.
  • the honeycomb seal 44 according to the second aspect is the honeycomb seal 44 of (1), and the high-strength portion 48 and the low-strength portion 49 alternately have a plurality of each in the depth direction H. It may be formed.
  • the low-strength portion 49 of the partition wall 47 existing at the position closest to the sealing surface 46 becomes the starting point and causes breakage. Therefore, the portion from the end portion of the partition wall 47 to the low-strength portion 49 is cut by the fin 43 in order from the sealing surface 46, and the partition wall 47 is not cut excessively.
  • the honeycomb seal 44 according to the third aspect is the honeycomb seal 44 of (1) or (2), and the high-strength portion 48 is a thick portion 48a having a predetermined plate thickness.
  • the low-strength portion 49 may be a thin-walled portion 49a having a plate thickness thinner than that of the thick-walled portion 48a.
  • the thin portion 49a closest to the fin 43 breaks. Further, the thick portion 48a ensures the high temperature oxidation resistance of the entire partition wall 47.
  • the honeycomb seal 44 according to the fourth aspect is the honeycomb seal 44 of (1) or (2), and the high-strength portion 48 does not have a defect 49c in the plate thickness of the partition wall 47.
  • the defect-free portion 48b, and the low-strength portion 49 may be a defective portion 49b having a defect 49c in the plate thickness of the partition wall 47.
  • the defective portion 49b closest to the fin 43 breaks. Further, the presence of the defective portion 49b can improve the machinability, and it is not necessary to suppress the plate thickness, so that the high temperature oxidation resistance can be ensured.
  • the rotating machine is a sealing device 50 that seals the rotor 11 that rotates around the axis ⁇ , the stator 12 that surrounds the rotor 11, and the space between the rotor 11 and the stator 12.
  • the sealing device 50 comprises the honeycomb seal 44 according to any one of (1) to (4) provided on one of the rotor 11 and the stator 12, and the rotor 11 and the stator 12. On the other hand, it has fins 43 provided so as to face the honeycomb seal 44.
  • Low-strength part 49a Thin-walled part 49b . Defected part 49c . Defect 50 ... Sealing device ⁇ ... Axis H ... Depth direction ⁇ ... Turbine A ... Fluctuation C ... Center line

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Un joint d'étanchéité en nid d'abeilles est pourvu d'une structure en nid d'abeilles dans laquelle une pluralité de parties trous agencées de manière à être en retrait par rapport à une surface d'étanchéité sont définies par des parois de séparation. La paroi de séparation a une partie à haute résistance et une partie à faible résistance ayant une résistance inférieure à celle de la partie à haute résistance à différentes positions dans la direction de la profondeur de la partie trou. En conséquence, la partie à faible résistance de la paroi de séparation provoque une rupture lorsqu'une ailette entre en contact avec la structure en nid d'abeilles.
PCT/JP2021/038035 2020-10-30 2021-10-14 Joint d'étanchéité en nid d'abeilles et machine rotative WO2022091798A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2020182710 2020-10-30
JP2020-182710 2020-10-30

Publications (1)

Publication Number Publication Date
WO2022091798A1 true WO2022091798A1 (fr) 2022-05-05

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2014231797A (ja) * 2013-05-29 2014-12-11 三菱日立パワーシステムズ株式会社 ガスタービン
JP2016027287A (ja) * 2015-11-19 2016-02-18 三菱重工業株式会社 シール装置
JP2016153654A (ja) * 2012-11-13 2016-08-25 三菱重工コンプレッサ株式会社 回転機械

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2016153654A (ja) * 2012-11-13 2016-08-25 三菱重工コンプレッサ株式会社 回転機械
JP2014231797A (ja) * 2013-05-29 2014-12-11 三菱日立パワーシステムズ株式会社 ガスタービン
JP2016027287A (ja) * 2015-11-19 2016-02-18 三菱重工業株式会社 シール装置

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