JP4346708B2 - Turbine turbocharger - Google Patents

Turbine turbocharger Download PDF

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Publication number
JP4346708B2
JP4346708B2 JP29360298A JP29360298A JP4346708B2 JP 4346708 B2 JP4346708 B2 JP 4346708B2 JP 29360298 A JP29360298 A JP 29360298A JP 29360298 A JP29360298 A JP 29360298A JP 4346708 B2 JP4346708 B2 JP 4346708B2
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Japan
Prior art keywords
guide bearing
fixed guide
turbine
turbocharger
turbine rotor
Prior art date
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JP29360298A
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Japanese (ja)
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JPH11193703A (en
Inventor
リップル アレクサンダー
リンク ヘルマン
ワーグナー ギュンター
シャフリツル フランツ
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MAN B&W Diesel GmbH
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MAN B&W Diesel GmbH
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    • 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
    • F01D25/18—Lubricating arrangements
    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/166—Sliding contact bearing
    • F01D25/168—Sliding contact bearing for axial load mainly
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Description

【０００１】
【発明の属する技術分野】
本発明は特許請求の範囲の請求項１の前文に記載のタービン式過給機に関する。
【０００２】
まず従来におけるタービン式過給機を図４を参照して説明する。このタービン式過給機はガスタービン１および圧縮機２を有している。ガスタービン１のタービンランナ３および圧縮機２の圧縮機ランナ４はタービンロータ（軸）５上に配置されている。タービンロータ５は軸受６、７によって径方向に支持され、案内軸受（スラスト軸受）８が軸方向力を受けている。この案内軸受８の部分Ｖが図５に拡大して詳細に示されている。この案内軸受８はタービン式過給機のハウジングに固定された固定案内軸受９およびこの固定案内軸受９の両側においてタービンロータ５上に配置された回転リング１０、１１を有している。各回転リング１０、１１とタービンロータ５との結合は調整ばね１２によって行われている。両回転リング１０、１１は間隔ブッシュ１３によって固定案内軸受９の幅より軸方向遊隙ｓだけ大きな間隔を保たれている。この軸方向遊隙ｓは通常１０分の数ｍｍである。間隔ブッシュ１３と固定案内軸受９の内周面１４との間に油室１５が形成されている。この油室１５は固定案内軸受９と回転リング１０、１１との間の面１６、１７にそれぞれ通じている。これらの面１６、１７はタービンロータ５の軸方向力を受ける軸受面である。油室１５に孔１８、１９を通って潤滑油が導入されている。
【０００３】
タービン式過給機が高速回転する際に軸方向スラストの方向が逆転するので、運転状態に応じていずれか一方の面１６あるいは面１７が軸受面として機能する。従って固定案内軸受９のこれらの面１６、１７を含む両側に潤滑油を供給しなければならない。しかしタービンロータ５の軸方向力の方向に応じて固定案内軸受９の無負荷側に、図５に示されている運転状態においては面１７に軸方向遊隙ｓに起因する隙間２０が生ずるので、この隙間２０を通って潤滑油が自由に流れ出てしまう。これにより油が大きな流量で流れ、また負荷側面（ここでは面１６）への油の導入が制限され、その結果、摩擦損失が増大してしまう。
【０００４】
【発明が解決しようとする課題】
本発明の課題は、タービン式過給機においてタービンロータの案内軸受を少ない潤滑油消費量で効果的に潤滑することができるようにすることにある。
【０００５】
【課題を解決するための手段】
本発明によればこの課題は、特許請求の範囲の請求項１に記載の特徴事項を有するタービン式過給機によって解決される。
【０００６】
潤滑油の入口室が固定案内軸受の非負荷側面に対して絞りによって閉じられているために、軸方向遊隙に基づく隙間、即ち固定案内軸受の非負荷側面における潤滑油の流出が防止される。これによって案内軸受に導入される潤滑油は十分に負荷側面に導かれる。従って、案内軸受の負荷側面は少ない油流量で良好に潤滑される。軸方向スラストの方向が逆転した際にタービンロータと固定案内軸受との接触個所が変化することに伴って、軸方向スラストの方向に応じて負荷される面への潤滑油の導入および発生する隙間に対する絞りが自動的に現れる。案内軸受の負荷側面の良好な潤滑はタービン式過給機の効率を向上させ、同時に排気ガス温度を低下させる。
【０００７】
本発明の他の特徴および利点は従属請求項に関連して理解できる。
【０００８】
【発明の実施の形態】
以下図に示した実施例を参照して本発明を詳細に説明する。
【０００９】
図１に示されている案内軸受８．１は幾つかの構造部品については図５に示されている案内軸受８と一致している。従ってこの実施例の場合およびこれ以後の実施例の場合において説明を単純化するために同一の構造部品に対して同一符号を利用する。変更された構造部品には添字例えば「．１」が付されている。図示された案内軸受８．１は固定軸受９．１を有し、この固定軸受９．１の両側にタービンロータ（軸）５上に配置された回転リング１０、１１が付設されている。なお回転リング１１はラビリンスリングとして作用し、これは圧縮室を密封するためのラビリンスパッキンの一部としてラビリンスを含んでいる。図５における案内軸受８に類似して回転リング１０、１１は調整ばね１２によってタービンロータ５にかみ合いトルク結合されている。更にタービンロータ５の軸方向力の方向に応じて軸受面として使われる面１６、１７が回転リング１０、１１と固定案内軸受９．１との間に存在している。
【００１０】
図５の場合と異なって、固定案内軸受９．１の内周面１４と間隔ブッシュ１３．１との間に存在する油室１５は入口室（流入室）２１．１も含んでいる。この入口室２１．１は有利には固定案内軸受９．１の内周面１４にある周溝２２．１によって形成され、間隔ブッシュ１３．１のつば（鍔）２３．１で境界づけられている。
【００１１】
タービンロータ５が図示された位置にある場合、軸方向力は矢印Ｒ１の方向に作用している。この位置において固定案内軸受９．１と回転リング１０との間の面１６が軸受面として使用され、回転リング１１と固定案内軸受９．１との間に軸方向遊隙ｓの幅の隙間２０が生じている。間隔ブッシュ１３．１のつば２３．１の一方の縁は固定案内軸受９．１の内周面１４と共に絞り２４．１を形成し、つば２３．１の他方の縁に固定案内軸受９．１の内周面１４に対して幅ｂの出口（貫流）隙間２５．１が生じている。このためにつば２３．１はその長さが周溝２２．１の幅より寸法ｂだけ短くされている。好適にはこの寸法ｂは隙間２０の幅ｓと同じである。
【００１２】
孔１８、１９を通して導入される潤滑油は入口室２１．１に到達し、絞り２４．１において継続して流れて隙間２０を通して流出することは阻止される。しかしつば２３．１の直径がその組立上の理由から固定案内軸受９．１の内周面１４より小さくされているので、その経路を通って油が漏洩するが、これはほんの僅かであり問題とならない。従って、導入された潤滑油は出口隙間２５．１を通って軸方向力で負荷される面１６に導かれ、この面１６が良好に潤滑される。
【００１３】
タービンロータ５の軸方向スラストの方向が矢印Ｒ２の方向に逆転された際、タービンロータ５は軸方向遊隙ｓだけ右に移動され、これによって面１７が接触し、軸方向力で負荷され、面１６において隙間が形成される。同時に今までの出口隙間２５．１の部分にタービンロータが変位することによりつば２３．１が右に移動することによって絞りが生じ、今までの絞り２４．１の部分に出口隙間が生ずる。そしていまや潤滑油は負荷側面１７に導かれ、離間した面１６への経路はしゃ断される。この位置は当該技術者にとって容易に理解できるので図示されていない。
【００１４】
図２における案内軸受８．２はタービンロータ５、固定案内軸受９．２、回転リング１０、１１、調整ばね１２、固定案内軸受９．２の内周面１４、油室１５および面１６、１７の位置については図１に示されている案内軸受８．１に非常に類似している。相違点は潤滑油の入口室２１．２が主に間隔ブッシュ１３．２の外周面にある周溝２６．２に存在し、詳しくはそのつば２３．２の部位に存在していることにある。つば２３．２の両側端は絞り２４．２および幅ｂの出口隙間２５．２を形成するためにそのまま存在していなければならない。孔１８、１９を介して導入された潤滑油が出口隙間２５．２に到達できるようにするために固定案内軸受９．２の内周面に浅い周溝２２．２も設けられている。矢印Ｒ１の方向に軸方向スラストがかかる場合に油はそこから側面１６に流入する。軸方向スラストが矢印Ｒ２の方向に逆転した場合、図１において上述した状態が生ずる。その説明は重複を避けるために省略する。
【００１５】
図３における案内軸受８．３は分割構造の固定案内軸受９．３を有している。ここでもタービンロータ５、回転リング１０、１１、調整ばね１２、固定案内軸受９．３の内周面１４、油室１５および面１６、１７の位置は上述の案内軸受に非常に類似している。固定案内軸受９．３が分割構造に形成されているために、間隔ブッシュ１３．３はそのつば２３．３が入口室２１．３の場所を提供する深い周溝２２．３の中に深く入り込んでいる。つば２３．３の両側端は溝２２．３の側壁と共に絞り２４．３および幅ｂの出口隙間２５．３を形成している。矢印Ｒ１の方向の軸方向力の場合に潤滑油は孔１８、１９を通って入口室２１．３に導かれ、出口隙間２５．３および油室１５の右側部位を通って負荷面１６に導かれる。軸方向スラストが矢印Ｒ２の方向に逆転した場合、図１において上述した状態が生ずる。その説明は重複を避けるために省略する。入口室２１．３は間隔ブッシュ１３．３のつば２３．３の部位において周溝２２．３の深さを非常に減少した状態で形成することもできる。
【図面の簡単な説明】
【図１】本発明に基づく案内軸受の一つの実施例の部分断面図。
【図２】本発明に基づく案内軸受の異なった実施例の部分断面図。
【図３】本発明に基づく案内軸受の更に異なった実施例の部分断面図。
【図４】従来におけるタービン式過給機の断面図。
【図５】図４の部分Ｖの拡大詳細断面図。
【符号の説明】
１ ガスタービン
２ 圧縮機
３ タービンランナ
５ タービンロータ
８．１ 案内軸受
９．１ 固定案内軸受
１３．１ 間隔ブッシュ
１５ 油室
１６、１７ 面
２１．１ 入口室（流入室）
２３．１ つば
２４．１ 絞り
２５．１ 出口隙間（貫流隙間）[0001]
BACKGROUND OF THE INVENTION
The invention relates to a turbine supercharger according to the preamble of claim 1 of the claims.
[0002]
First, a conventional turbocharger will be described with reference to FIG. This turbine supercharger has a gas turbine 1 and a compressor 2. A turbine runner 3 of the gas turbine 1 and a compressor runner 4 of the compressor 2 are disposed on a turbine rotor (shaft) 5. The turbine rotor 5 is supported in the radial direction by bearings 6 and 7, and a guide bearing (thrust bearing) 8 receives an axial force. Part V of this guide bearing 8 is shown in detail in an enlarged manner in FIG. The guide bearing 8 has a fixed guide bearing 9 fixed to the housing of the turbine supercharger and rotating rings 10 and 11 arranged on the turbine rotor 5 on both sides of the fixed guide bearing 9. The rotating rings 10 and 11 and the turbine rotor 5 are coupled to each other by an adjustment spring 12. Both rotary rings 10 and 11 are spaced apart by an axial clearance s from the width of the fixed guide bearing 9 by a spacing bush 13. This axial play s is usually a few tenths of a millimeter. An oil chamber 15 is formed between the spacing bush 13 and the inner peripheral surface 14 of the fixed guide bearing 9. The oil chamber 15 communicates with surfaces 16 and 17 between the fixed guide bearing 9 and the rotating rings 10 and 11, respectively. These surfaces 16 and 17 are bearing surfaces that receive the axial force of the turbine rotor 5. Lubricating oil is introduced into the oil chamber 15 through the holes 18 and 19.
[0003]
Since the direction of the axial thrust is reversed when the turbine supercharger rotates at high speed, either one of the surfaces 16 or 17 functions as a bearing surface depending on the operating state. Accordingly, lubricating oil must be supplied to both sides of the fixed guide bearing 9 including these surfaces 16 and 17. However, in accordance with the direction of the axial force of the turbine rotor 5, a clearance 20 due to the axial clearance s is formed on the surface 17 in the operating state shown in FIG. 5 on the unloaded side of the fixed guide bearing 9. The lubricating oil flows out freely through the gap 20. As a result, the oil flows at a large flow rate, and the introduction of the oil to the load side surface (here, the surface 16) is limited. As a result, the friction loss increases.
[0004]
[Problems to be solved by the invention]
An object of the present invention is to enable the guide bearing of the turbine rotor to be effectively lubricated with a small amount of lubricating oil consumption in the turbocharger.
[0005]
[Means for Solving the Problems]
According to the invention, this problem is solved by a turbine supercharger having the features of claim 1.
[0006]
Since the lubricant inlet chamber is closed by the restriction with respect to the non-load side surface of the fixed guide bearing, the clearance based on the axial play, that is, the lubricant oil is prevented from flowing out on the non-load side surface of the fixed guide bearing. . As a result, the lubricating oil introduced into the guide bearing is sufficiently guided to the load side surface. Therefore, the load side surface of the guide bearing is well lubricated with a small oil flow rate. When the axial thrust direction is reversed, the clearance between the turbine rotor and the fixed guide bearing changes and the lubricant is introduced into the surface to be loaded in accordance with the axial thrust direction and the generated clearance. The aperture for automatically appears. Good lubrication of the load side of the guide bearing improves the efficiency of the turbocharger and at the same time lowers the exhaust gas temperature.
[0007]
Other features and advantages of the invention can be understood in connection with the dependent claims.
[0008]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, the present invention will be described in detail with reference to the embodiments shown in the drawings.
[0009]
The guide bearing 8.1 shown in FIG. 1 corresponds to the guide bearing 8 shown in FIG. 5 for some structural parts. Therefore, the same reference numerals are used for the same structural parts in order to simplify the description in the case of this embodiment and the following embodiments. Subscripts such as “.1” are attached to the changed structural parts. The illustrated guide bearing 8.1 has a fixed bearing 9.1, and rotating rings 10 and 11 arranged on the turbine rotor (shaft) 5 are attached to both sides of the fixed bearing 9.1. The rotating ring 11 acts as a labyrinth ring, which includes the labyrinth as part of the labyrinth packing for sealing the compression chamber. Similar to the guide bearing 8 in FIG. 5, the rotating rings 10 and 11 are meshed with the turbine rotor 5 by an adjusting spring 12 and are torque coupled. Furthermore, surfaces 16 and 17 used as bearing surfaces according to the direction of the axial force of the turbine rotor 5 exist between the rotating rings 10 and 11 and the fixed guide bearing 9.1.
[0010]
Unlike the case of FIG. 5, the oil chamber 15 existing between the inner peripheral surface 14 of the fixed guide bearing 9.1 and the spacing bush 13.1 also includes an inlet chamber (inflow chamber) 21.1. This inlet chamber 21.1 is preferably formed by a circumferential groove 22.1 in the inner peripheral surface 14 of the fixed guide bearing 9.1 and bounded by a flange 23.1 of the spacing bush 13.1. Yes.
[0011]
When the turbine rotor 5 is in the illustrated position, the axial force is acting in the direction of the arrow R1. In this position, the surface 16 between the fixed guide bearing 9.1 and the rotary ring 10 is used as a bearing surface, and a gap 20 having a width of the axial clearance s is provided between the rotary ring 11 and the fixed guide bearing 9.1. Has occurred. One edge of the flange 23.1 of the spacing bush 13.1 forms a throttle 24.1 with the inner peripheral surface 14 of the fixed guide bearing 9.1, and the fixed guide bearing 9.1 on the other edge of the collar 23.1. An outlet (through-flow) gap 25.1 having a width b is formed with respect to the inner peripheral surface 14. For this purpose, the length of the collar 23.1 is made shorter by the dimension b than the width of the circumferential groove 22.1. This dimension b is preferably the same as the width s of the gap 20.
[0012]
Lubricating oil introduced through the holes 18, 19 reaches the inlet chamber 21.1 and is prevented from continuously flowing in the throttle 24.1 and flowing out through the gap 20. However, since the diameter of the collar 23.1 is smaller than the inner peripheral surface 14 of the fixed guide bearing 9.1 for the reasons of its assembly, oil leaks through the path, but this is only a slight problem. Not. Accordingly, the introduced lubricating oil is guided to the surface 16 loaded by the axial force through the outlet gap 25.1, and this surface 16 is well lubricated.
[0013]
When the axial thrust direction of the turbine rotor 5 is reversed in the direction of the arrow R2, the turbine rotor 5 is moved to the right by the axial clearance s, whereby the surface 17 comes into contact and is loaded with an axial force, A gap is formed on the surface 16. At the same time, the displacement of the turbine rotor in the portion of the exit gap 25.1 so far causes the collar 23.1 to move to the right, thereby producing a throttle, and an exit gap in the portion of the throttle 24.1 so far. And now the lubricating oil is guided to the load side 17 and the path to the spaced side 16 is cut off. This position is not shown because it can be easily understood by those skilled in the art.
[0014]
The guide bearing 8.2 in FIG. 2 includes the turbine rotor 5, the fixed guide bearing 9.2, the rotating rings 10 and 11, the adjustment spring 12, the inner peripheral surface 14 of the fixed guide bearing 9.2, the oil chamber 15 and the surfaces 16 and 17. Is very similar to the guide bearing 8.1 shown in FIG. The difference is that the lubricating oil inlet chamber 21.2 is present mainly in the circumferential groove 26.2 on the outer peripheral surface of the spacing bush 13.2, and more specifically in the area of the collar 23.2. . Both ends of the collar 23.2 must be present as they are in order to form the aperture 24.2 and the exit gap 25.2 of width b. A shallow circumferential groove 22.2 is also provided on the inner circumferential surface of the fixed guide bearing 9.2 in order to allow the lubricating oil introduced through the holes 18, 19 to reach the outlet gap 25.2. When axial thrust is applied in the direction of the arrow R1, the oil flows into the side 16 from there. When the axial thrust is reversed in the direction of arrow R2, the state described above in FIG. 1 occurs. The description is omitted to avoid duplication.
[0015]
The guide bearing 8.3 in FIG. 3 has a fixed guide bearing 9.3 having a divided structure. Here too, the positions of the turbine rotor 5, the rotating rings 10, 11, the adjustment spring 12, the inner peripheral surface 14, the oil chamber 15 and the surfaces 16, 17 of the fixed guide bearing 9.3 are very similar to those of the above-mentioned guide bearing. . Since the fixed guide bearing 9.3 is formed in a split structure, the spacing bush 13.3 penetrates deeply into the deep circumferential groove 22.3 whose collar 23.3 provides the location of the inlet chamber 21.3. It is out. Both ends of the collar 23.3 form a throttle 24.3 and an outlet gap 25.3 of width b together with the side walls of the groove 22.3. In the case of an axial force in the direction of the arrow R1, the lubricating oil is guided to the inlet chamber 21.3 through the holes 18, 19 and to the load surface 16 through the outlet gap 25.3 and the right part of the oil chamber 15. It is burned. When the axial thrust is reversed in the direction of arrow R2, the state described above in FIG. 1 occurs. The description is omitted to avoid duplication. The inlet chamber 21.3 can also be formed with the depth of the circumferential groove 22.3 being greatly reduced at the location of the flange 23.3 of the spacing bush 13.3.
[Brief description of the drawings]
FIG. 1 is a partial sectional view of one embodiment of a guide bearing according to the present invention.
FIG. 2 is a partial sectional view of a different embodiment of a guide bearing according to the invention.
FIG. 3 is a partial sectional view of a further different embodiment of the guide bearing according to the invention.
FIG. 4 is a sectional view of a conventional turbocharger.
FIG. 5 is an enlarged detailed cross-sectional view of a portion V in FIG.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Gas turbine 2 Compressor 3 Turbine runner 5 Turbine rotor 8.1 Guide bearing 9.1 Fixed guide bearing 13.1 Space bush 15 Oil chamber 16, 17 surface 21.1 Inlet chamber (inflow chamber)
23.1 Collar 24.1 Restriction 25.1 Exit gap (through gap)

Claims (5)

ガスタービン（１）と圧縮機（２）とを備え、そのタービンランナ（３）および圧縮機ランナ（４）がタービンロータ（５）上に配置され、このタービンロータ（５）が案内軸受（８）によって、軸方向遊隙（ｓ）を有して軸方向に支持され、この案内軸受（８）が固定案内軸受（９）、この固定案内軸受の両側にタービンロータ上に配置された回転リング（１１）およびこれらの回転リング間に存在する間隔ブッシュ（１３）を有し、更に固定案内軸受と間隔ブッシュとの間に固定案内軸受と回転リングとの間の面に通じる油室（１５）が形成されているようなタービン式過給機において、前記油室（１５）が間隔ブッシュ（１３．１、１３．２、１３．３）のつば（２３．１、２３．２、２３．３）と固定案内軸受（９．１、９．２、９．３）との間に設けられた入口室（２１．１、２１．２、２１．３）を含み、この入口室が一方ではつば（２３．１、２３．２、２３．３）の絞り（２４．１、２４．２、２４．３）によって固定案内軸受（９．１、９．２、９．３）の非負荷面（１７）に通じる油室（１５）の部分に対して境界づけられ、他方ではつば（２３．１、２３．２、２３．３）の出口隙間（２５．１、２５．２、２５．３）によって固定案内軸受（９．１、９．２、９．３）の負荷面（１６）に通じる油室（１５）の部分に対して境界づけられ、その出口隙間（２５．１、２５．２、２５．３）がタービンロータ（５）が軸方向に変位した際に、前記軸方向遊隙（ｓ）の範囲内で閉じられ、絞り（２４．１、２４．２、２４．３）が開けられるタービン式過給機であって、前記出口隙間（２５．１、２５．２、２５．３）の幅（ｂ）が、前記軸方向遊隙（ｓ）の大きさに決められていることを特徴とするタービン式過給機。A gas turbine (1) and a compressor (2) are provided, and the turbine runner (3) and the compressor runner (4) are disposed on a turbine rotor (5), and the turbine rotor (5) is provided with a guide bearing (8 ) With an axial clearance (s) and is supported in the axial direction, the guide bearing (8) being a fixed guide bearing (9) and a rotating ring arranged on both sides of the fixed guide bearing on the turbine rotor (11) and a space bush (13) existing between the rotating rings, and an oil chamber (15) communicating between the fixed guide bearing and the space bush and leading to a surface between the fixed guide bearing and the rotating ring. In the turbine-type supercharger in which the oil chamber (15) is formed, the oil chamber (15) has a flange (23.1, 23.2, 23.3) of a spacing bush (13.1, 13.2, 13.3). ) And fixed guide bearings (9.1, 9.2, 9) 3) including an inlet chamber (21.1, 21.2, 21.3) provided between the throttle chamber (23.1, 23.2, 23.3) on the one hand. 24.1, 24.2, 24.3) bounding the part of the oil chamber (15) leading to the unloaded surface (17) of the fixed guide bearing (9.1, 9.2, 9.3) On the other hand, fixed guide bearings (9.1, 9.2, 9.3) are provided by outlet gaps (25.1, 25.2, 25.3) of the collars (23.1, 23.2, 23.3). ) With respect to the portion of the oil chamber (15) leading to the load surface (16), and the exit gaps (25.1, 25.2, 25.3) are displaced in the axial direction of the turbine rotor (5). The turbocharger is closed within the range of the axial clearance (s) and the throttles (24.1, 24.2, 24.3) are opened. There are, turbine type wherein the outlet width of the gap (25.1,25.2,25.3) (b), characterized in that it is determined the magnitude of the previous SL-axis direction clearance (s) Turbocharger. 間隔ブッシュ（１３．１、１３．２）がそのつば（２３．１、２３．２）ともども固定案内軸受（９．１、９．２）の内周面（１４）によって案内されていることを特徴とする請求項１記載のタービン式過給機。  The spacing bush (13.1, 13.2) is guided by the inner peripheral surface (14) of the fixed guide bearing (9.1, 9.2) together with its collar (23.1, 23.2). The turbocharger according to claim 1, wherein the turbocharger is a turbocharger. 固定案内軸受（９．３）が分割構造に形成され、間隔ブッシュ（１３．３）のつば（２３．２）が案内軸受（９．３）の内周面にある周溝（２２．３）の中に突入していることを特徴とする請求項１記載のタービン式過給機。  The fixed guide bearing (9.3) is formed in a split structure, and the flange (23.2) of the spacing bush (13.3) is on the inner peripheral surface of the guide bearing (9.3). The turbine-type supercharger according to claim 1, wherein the turbocharger is inserted into the engine. 入口室（２１．１、２１．３）が固定案内軸受（９．１、９．３）の内周面にある周溝（２２．１、２２．３）として形成されていることを特徴とする請求項１ないし３のいずれか１つに記載のタービン式過給機。  The inlet chamber (21.1, 21.3) is formed as a circumferential groove (22.1, 22.3) in the inner peripheral surface of the fixed guide bearing (9.1, 9.3). The turbine supercharger according to any one of claims 1 to 3. 入口室（２１．２）が間隔ブッシュ（１３．２）のつば（２３．２）の外周面にある周溝（２６．２）として形成されていることを特徴とする請求項１ないし３のいずれか１つに記載のタービン式過給機。  The inlet chamber (21.2) is formed as a circumferential groove (26.2) in the outer peripheral surface of the collar (23.2) of the spacing bush (13.2). The turbine-type supercharger as described in any one.
JP29360298A 1997-10-17 1998-10-15 Turbine turbocharger Expired - Fee Related JP4346708B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19745659.6 1997-10-17
DE1997145659 DE19745659C1 (en) 1997-10-17 1997-10-17 Turbo-supercharger for internal combustion engine

Publications (2)

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JPH11193703A JPH11193703A (en) 1999-07-21
JP4346708B2 true JP4346708B2 (en) 2009-10-21

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CH (1) CH693238A5 (en)
DE (1) DE19745659C1 (en)
FR (1) FR2769951B1 (en)

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DE102004055429B3 (en) * 2004-11-17 2006-08-10 Man B & W Diesel Ag Sealing device for a particularly lubricated at standstill bearing a rotor shaft
JP6097188B2 (en) * 2013-09-25 2017-03-15 三菱重工業株式会社 Turbocharger

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GB639293A (en) * 1948-02-16 1950-06-28 Henry George Yates Combined journal and thrust bearings
GB1129853A (en) * 1966-06-02 1968-10-09 Mach Tool Industry Res Ass Improvements in or relating to hydrostatic bearing assemblies
GB1373507A (en) * 1971-11-16 1974-11-13 Federal Mogul Westwind Air gas or fluid bearings
FR2250401A5 (en) * 1973-07-20 1975-05-30 Renault
JPS5613513U (en) * 1979-07-10 1981-02-05
JPS5887935U (en) * 1981-12-10 1983-06-15 石川島播磨重工業株式会社 Turbocharger thrust bearing

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CH693238A5 (en) 2003-04-30
FR2769951B1 (en) 2000-10-13
FR2769951A1 (en) 1999-04-23
JPH11193703A (en) 1999-07-21

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