EP2233719A1 - Gehäusebefestigungsverfahren - Google Patents

Gehäusebefestigungsverfahren Download PDF

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Publication number
EP2233719A1
EP2233719A1 EP08791296A EP08791296A EP2233719A1 EP 2233719 A1 EP2233719 A1 EP 2233719A1 EP 08791296 A EP08791296 A EP 08791296A EP 08791296 A EP08791296 A EP 08791296A EP 2233719 A1 EP2233719 A1 EP 2233719A1
Authority
EP
European Patent Office
Prior art keywords
housing
fastener
face
flange
turbine
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.)
Withdrawn
Application number
EP08791296A
Other languages
English (en)
French (fr)
Other versions
EP2233719A4 (de
Inventor
Yasutaka Sakai
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.)
IHI Corp
Original Assignee
IHI Corp
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 IHI Corp filed Critical IHI Corp
Publication of EP2233719A1 publication Critical patent/EP2233719A1/de
Publication of EP2233719A4 publication Critical patent/EP2233719A4/de
Withdrawn legal-status Critical Current

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B39/00—Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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
    • F05D2260/39—Retaining components in desired mutual position by a V-shaped ring to join the flanges of two cylindrical sections, e.g. casing sections of a turbocharger

Definitions

  • This invention relates to a housing fastening method for fastening housings together by a fastener such as a G-coupling and a turbocharger having housings fastened together by a fastener such as a G-coupling, and particularly a housing fastening method and turbocharger capable of keeping down a reduction in fastening force applied by a fastener.
  • a rotary machine which obtains power by converting kinetic energy of a fluid supplied to its bladed rotor to rotation of the bladed rotor is generally called a turbine.
  • a type in which a fluid is supplied to the bladed rotor radially and discharged axially is called a radial turbine, in particular.
  • An automotive turbocharger is a device using such radial turbine.
  • the automotive turbocharger comprises a gas turbine including a bladed turbine rotor rotated by exhaust gas supplied thereto and a compressor including an impeller for drawing in air, connected with the bladed turbine rotor coaxially. The air drawn in and compressed by the compressor is delivered to an engine, where it is mixed with fuel and burnt.
  • Exhaust gas produced from combustion is sent to the gas turbine to do work, and finally emitted into the atmosphere.
  • the passage through which the exhaust gas is supplied to the bladed turbine rotor includes a scroll portion extending spirally around the axis of rotation of the bladed turbine rotor so that the exhaust gas is accelerated and supplied to the bladed turbine rotor radially.
  • the automotive turbocharger as described above has a rotating shaft which connects the bladed turbine rotor of the gas turbine and the impeller of the compressor.
  • the rotating shaft is supported by a bearing housing, rotatably.
  • a turbine housing and the bearing housing are connected together by fastening a fastener such as a G-coupling to flange portions of the turbine housing and bearing housing (see Patent Document 1, FIG. 12, for example).
  • An object of the present invention is to provide, by contriving a housing structure, a housing fastening method and turbocharger capable of keeping down the reduction in fastening force applied by a fastener such as a G-coupling even when housings are exposed to high temperature.
  • the present invention provides a housing fastening method comprising the steps of inserting a projecting portion of a housing in a recessed portion of another housing so that an end face of the projecting portion butts against a step portion of the recessed portion serving as a stopper face and that a flange portion around the recessed portion and a flange portion around the projecting portion face each other, and thereafter, fastening the housings together by an annular fastener with a grooved portion on its inside adapted to receive the flange portions facing each other, wherein the axial position of the stopper face of the step portion and the shapes of the recessed portion and the projecting portion are determined to ensure that a gap produced between the grooved portion of the fastener and the flange portions does not exceed a specified size even when the housings and the fastener experience thermal expansion during use.
  • the above-described housing fastening method according to the present invention was contrived through the inventor's keen research on reduction in fastening force applied by a fastener such as a G-coupling for fastening housings together, due to thermal expansion, which research led to the finding that there exists a connection between the axial position of the stopper face of the step portion and the fastening force applied by the fastener.
  • the gap produced between the fastener and the flange portions can be easily controlled by appropriately determining the axial position of the stopper face of the step portion and the shapes of the recessed portion and the projecting portion. For example, by setting the axial position of the stopper face of the step portion nearer to the end (reducing the depth of the recessed portion) compared with the prior art, reduction in fastening force applied by the fastener due to thermal expansion can be kept down even when the inside of the housing is exposed to high temperature (ca 1000°C, for example).
  • the axial position of the stopper face of the step portion is set within the axial projected width of the fastener.
  • the axial distance between the contact positions on the respective flange portions against the fastener is equal to the axial distance between the stopper face and the contact position on the flange portion of the housing having the recessed portion against the fastener subtracted from the axial distance between the stopper face and the contact position on the flange portion of the housing having the projecting portion against the fastener.
  • the housing having the recessed portion experiences a greater degree of thermal expansion compared with the housing having the projecting portion, the axial distance between the contact positions on the respective flange portions against the fastener relatively reduces, so that a gap is produced between the housings and the fastener.
  • the axial distance between the contact position on the flange portion of the housing having the recessed portion against the fastener and the stopper face of the step portion is small, the increase in the axial distance between the contact position and the stopper face due to thermal expansion of the housing having the recessed portion is very small. Consequently, even when the housing having the recessed portion is exposed to higher temperature compared with the housing having the projecting portion and the fastener, increase in size of the gap between the housings and the fastener due to thermal expansion can be kept down, so that reduction in fastening force applied by the fastener can be kept down.
  • the shape of the projecting portion is determined taking account of the thickness of a thin sheet held between the stopper face of the step portion and the end face of the projecting portion.
  • the flange portion of the housing which is likely to experience a smaller degree of thermal expansion is formed to be greater in outside diameter than the flange portion of the housing which is likely to experience a greater degree of thermal expansion.
  • This aspect enables the edges of both flange portions to take approximately the same radial position at high temperature, although the housings fastened together experience different degrees of thermal expansion, thereby greatly reducing a force tending to tilt the fastener.
  • the allowable limit k may be set on the basis of the allowable size for a gap produced between the fastener and the contact position on the flange portion at a specified temperature. Specifically, it is desirable to set the allowable limit k to meet the condition 0 ⁇ k ⁇ 0.0388/cos( ⁇ /2), where ⁇ is an angle of divergence of a pair of support portions of the fastener.
  • determining the axial distance Az in the recessed portion and the axial distance Bz in the projecting portion to meet the above-mentioned condition leads to limiting the size of the gap produced between the fastener and the flange portion at high temperature within a desired range. Consequently, reduction in fastening force applied by the fastener can be kept down.
  • the present invention also provides a turbocharger comprising a turbine including a bladed rotor rotated by a fluid supplied thereto, a compressor including an impeller for drawing in air, connected with the bladed rotor by a rotating shaft, a turbine housing constituting an outer shape of the turbine, and a bearing housing rotatably supporting the rotating shaft, a projecting portion of the bearing housing being inserted in a recessed portion of the turbine housing such that an end face of the projecting portion butts against a step portion of the recessed portion serving as a stopper face and that a flange portion around the recessed portion and a flange portion around the projecting portion face each other, the flange portions being fastened together by an annular fastener with a grooved portion on its inside adapted to receive the flange portions facing each other, wherein the bearing housing and the turbine housing are fastened together by the fastener according to any of the above aspects of the housing fastening method.
  • the turbocharger having a configuration described above can keep down the reduction in fastening force applied by the fastener due to thermal expansion.
  • FIG. 1A is a longitudinal cross-sectional view of a turbocharger according to the present invention
  • FIG. 1B a front view of a G-coupling shown in FIG. 1A
  • FIG. 2A shows portion II of FIG. 1A on an enlarged scale
  • FIG. 2B shows a portion corresponding to the portion shown in FIG. 2A in prior art.
  • the turbocharger according to the present invention shown in FIG. 1A comprises a turbine 1 including a bladed rotor 1a rotated by a fluid supplied thereto, a compressor 2 including an impeller 2a for drawing in air, connected with the bladed rotor 1a by a rotating shaft 3a, a turbine housing 1b constituting an outer shape of the turbine 1, and a bearing housing 3 rotatably supporting the rotating shaft 3a.
  • the turbine housing 1a and the bearing housing 3 and the bearing housing 3 [sic] are assembled as follows: A projecting portion 3b of the bearing housing 3 is inserted in a recessed portion 1c of the turbine housing 1a so that an end face 3c of the projecting portion 3b butts against a step portion 1d of the recessed portion 1c serving as a stopper face and that a flange portion 1e around the recessed portion 1c and a flange portion 3d around the projecting portion 3b face each other.
  • the flange portions 1e and 3e are fastened together by an annular G-coupling 4 with a grooved portion on its inside adapted to receive the flange portions 1e and 3d facing each other, where the axial position of the stopper face of the step portion 1d and the shapes of the recessed portion 1c and the projecting portion 3b are determined as described later.
  • the turbine 1 of the turbocharger shown in FIG. 1A has a multiple-chamber scroll portion 1f
  • the turbocharger may have a single-chamber scroll portion, and may include a variable nozzle for regulating flow rate, between the scroll portion 1f and the bladed rotor 1a.
  • a compressor housing 2b and the bearing housing 3 are fastened together by bolts 2c distributed circumferentially, they may be fastened together in another manner.
  • the axial position of the stopper face of the step portion 1d is set, for example within the axial projected width Zg of the G-coupling 4, as indicated in FIG. 2A .
  • Za is the axial distance between the end face of the flange portion 1e and the stopper face of the step portion 1d of the turbine housing 1b.
  • the axial position of the stopper face of the step portion 1d is set outside the axial projected width Zg of the G-coupling 4, so that there exists a relationship Za > 0.5Zg.
  • the axial position of the stopper face of the step portion 1d is set nearer to the end face of the flange portion 1e compared with the prior art so as to solve the above-mentioned problems.
  • the G-coupling 4 is a type of fastener, and as shown in FIG. 1B , includes a pair of semicircular arc portions 4a, 4a, flange portions 4b, 4b at an end of the respective semicircular arc portions 4a, turned-back portions 4c, 4c at the opposite end of the respective semicircular arc portions 4a, a fastener 4d such as a bolt and nut for fastening the flange portions 4b together, and a ring 4e for binding the turned-back portions 4c, 4c.
  • a fastener 4d such as a bolt and nut for fastening the flange portions 4b together
  • a ring 4e for binding the turned-back portions 4c, 4c.
  • each semicircular arc portion 4a has the grooved portion adapted to receive the flange portion 1e of the turbine housing 1b and the flange portion 3d of the bearing housing 3, inside.
  • the grooved portion has sloping sides gradually diverging from each other from the bottom to the top of the grooved portion.
  • the flange portion 1a of the turbine housing 1b and the flange portion 3d of the bearing housing 3 each taper such that the flange portion can contact the corresponding sloping surface of the G-coupling 4.
  • the tapering surfaces of the flange portions 1e, 3d each contact the corresponding sloping surface of the G-coupling 4 at one point.
  • each tapering surface and the corresponding sloping surface make a line contact along the length of each semicircular arc portion 4a shown in FIG. 1B .
  • the fastener 4d By fastening the fastener 4d with the flange portion 1e of the turbine housing 1b and the flange portion 3d of the bearing housing 3 held between the inner sloping surfaces of the G-coupling 4, the turbine housing 1b and the bearing housing 3 are fastened together.
  • the G-coupling 4 is sometimes called a V-band coupling.
  • a heat shield plate 5 which is a thin sheet formed into a tubular shape, is arranged with its edge portion held between the stopper face of the step portion 1d of the turbine housing 1b and the end face 3c of the projecting portion 3b of the bearing housing 3.
  • the heat shield plate 5 is a member for protecting the bearing housing 3 from high-temperature exhaust gas flowing backward from the turbine housing 1b.
  • the heat shield plate 5 in the present invention has a greater axial length compared with the prior art, which results from setting the axial position of the stopper face of the step potion 1d nearer to the end face of the flange portion 1e.
  • the shape of the projecting portion 3b needs to be designed, taking account of the sheet thickness thereof. It is to be noted that the heat shield plate 5 is not an indispensable element.
  • a spacer in the form of a thin annular sheet serving as a sealing member may be held between the stopper face and the end face, or the stopper face of the step portion 1d of the turbine housing 1b may be in direct contact with the end face 3c of the projecting portion 3b of the bearing housing 3.
  • FIG. 3 is an explanatory diagram indicating sizes referred to in describing a housing fastening method according to an embodiment of the present invention.
  • FIG. 4A shows a relation between the G-coupling 4 and the flange portions 1e and 3d at normal temperature
  • FIG. 4B shows a relation between the G-coupling 4 and the flange portions 1e and 3d at high temperature.
  • FIG. 4C shows a relation between gaps ⁇ g and ⁇ c shown in FIG. 4B .
  • symbol Pg denote a position on the G-coupling 4 which contacted the contact position Pb at normal temperature.
  • the axial distance Cg between the contact positions Pa and Pg on the G-coupling 4 is longer than the axial distance C between the contact positions Pa and Pb on the flange portions 1e and 3d.
  • ⁇ C denotes this difference (Cg-C).
  • ⁇ g needs to meet at least the condition ⁇ g ⁇ 0.0388mm. Consequently, ⁇ C needs to meet the condition ⁇ C ⁇ 0.0388/cos( ⁇ /2).
  • an allowable limit k is set. Specifically, in order to achieve at least a slight increase in fastening force applied by the G-coupling 4 compared with the prior art when the exhaust gas supplied to the turbine 1 is at 1050°C, the allowable limit k needs to be set within the range of 0 ⁇ k ⁇ 0.0388/cos( ⁇ /2) (in mm). Further, in the present invention, in order to effectively keep down the reduction in fastening force applied by the G-coupling 4, the gap ⁇ g should desirably be around 0.002mm. In this case, the allowable limit k should be set within the range of 0 ⁇ k ⁇ 0.002/cos( ⁇ /2) (in mm). When a standard G-coupling 4 is used, the range within which the allowable limit k should be set can be expressed by 0 ⁇ k ⁇ 0.0016 (in mm).
  • the values of the parameters (axial distance Bz, radial distance Br, angle of divergence ⁇ , etc.) relating to the shape of the projecting portion 3b can be determined taking account of the sheet thickness t (thickness of the thin sheet), and therefore the shape of the projecting portion 3b can be designed taking account of the sheet thickness t.
  • FIG. 5A is a longitudinal cross-sectional view showing a fastening structure made by a housing fastening method according to another embodiment of the present invention
  • FIG. 5B is a longitudinal cross-sectional view showing a fastening structure according to a further embodiment.
  • the components similar to those shown in FIG. 2A are assigned the same reference characters, and the explanation of such components is omitted to avoid repetition.
  • the flange portion 3d of the bearing housing 3 is ⁇ h greater in outside diameter (radius) than the flange portion 1e of the turbine housing 1b. This is out of consideration for the fact that the turbine housing 1b is likely to experience a greater temperature rise and therefore a greater degree of thermal expansion than the bearing housing 3. In other words, considering that the difference in thermal expansion results in difference in radial displacement between contact positions Pa and Pb, the configuration is determined such that, at high temperature, the contact positions Pa and Pb are displaced onto a line approximately parallel to the axial direction.
  • the above-mentioned expressions for calculating the axial distance C between contact positions Pa and Pb and the axial distance Cg between contact positions Pa and Pg can be applied without modification. It is to be noted, however, that even when the housing fastening method shown in FIG. 5A is not adopted, the axial distance C between contact positions Pa and Pb can be easily calculated taking account of an angle between a line connecting the contact positions Pa and Pb and the axial direction.
  • the stopper face of the step portion 1d of the recessed portion 1c of the turbine housing 1b is in direct contact with the end face 3c of the projecting portion 3b of the bearing housing 3.
  • this is the case not requiring a heat shield plate 5 as shown in FIG. 2A .
  • the axial distances C and Cg can be easily calculated only by eliminating the variables relating to the heat shield plate 5 (t, ⁇ , ⁇ Ts) from the above-mentioned expressions for calculating the axial distance C between contact positions Pa and Pb and the axial distance Cg between contact positions Pa and Pg, respectively.
  • the axial distances C, Cg can be calculated by introducing the sheet thickness and liner coefficient of expansion for such member.
  • the present invention is not limited to the above-described embodiments. Needless to say, it allows a variety of modifications not departing from the spirit and scope of the present invention.
  • the present invention is applicable to fasteners other than the G-coupling.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
EP08791296.0A 2008-01-18 2008-07-17 Gehäusebefestigungsverfahren Withdrawn EP2233719A4 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2008009156A JP2009167971A (ja) 2008-01-18 2008-01-18 ハウジング締結方法及び過給機
PCT/JP2008/062942 WO2009090768A1 (ja) 2008-01-18 2008-07-17 ハウジング締結方法

Publications (2)

Publication Number Publication Date
EP2233719A1 true EP2233719A1 (de) 2010-09-29
EP2233719A4 EP2233719A4 (de) 2017-07-26

Family

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Application Number Title Priority Date Filing Date
EP08791296.0A Withdrawn EP2233719A4 (de) 2008-01-18 2008-07-17 Gehäusebefestigungsverfahren

Country Status (6)

Country Link
US (1) US20100296925A1 (de)
EP (1) EP2233719A4 (de)
JP (1) JP2009167971A (de)
KR (1) KR20100091259A (de)
CN (1) CN101918692B (de)
WO (1) WO2009090768A1 (de)

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EP3660283A1 (de) * 2018-11-29 2020-06-03 Toyota Jidosha Kabushiki Kaisha Turbolader
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WO2009090768A1 (ja) 2009-07-23
EP2233719A4 (de) 2017-07-26
CN101918692B (zh) 2013-01-16
CN101918692A (zh) 2010-12-15
KR20100091259A (ko) 2010-08-18
US20100296925A1 (en) 2010-11-25
JP2009167971A (ja) 2009-07-30

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