JPH0633706A - Fluid machine with rotor - Google Patents
Fluid machine with rotorInfo
- Publication number
- JPH0633706A JPH0633706A JP15158193A JP15158193A JPH0633706A JP H0633706 A JPH0633706 A JP H0633706A JP 15158193 A JP15158193 A JP 15158193A JP 15158193 A JP15158193 A JP 15158193A JP H0633706 A JPH0633706 A JP H0633706A
- Authority
- JP
- Japan
- Prior art keywords
- fluid machine
- adjusting element
- blade
- cavity
- guide device
- 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.)
- Granted
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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
- F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】この発明は、半径方向へ貫流され
るロータ、翼を有する案内装置、及び同心に配置されロ
ータ軸に対し平行に移動可能であって貫流断面を変更す
る調節要素を備える流体機械、特にタービン過給機に関
する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention comprises a rotor which is flowed through in a radial direction, a guide device having vanes, and an adjusting element which is arranged concentrically and is movable parallel to the rotor axis and which changes the flow-through cross section. The present invention relates to a fluid machine, particularly a turbine supercharger.
【０００２】[0002]
【従来の技術】調節要素が案内装置の側壁の一部として
タービンの流出側に形成され、案内装置の向かい合う側
壁が軸受ハウジングと強固に結合され、貫流断面中へ突
入する翼の高さが調節要素の直線状の軸方向移動及び翼
の輪郭に相応し翼を収容する空所により変更可能である
ような前記の種類の流体機械は既に知られている。An adjusting element is formed on the outlet side of the turbine as part of the side wall of the guide device, the opposite side wall of the guide device being firmly connected to the bearing housing and adjusting the height of the blades projecting into the through-flow section. Fluid machines of the above-mentioned type are already known, in which the linear axial movement of the elements and the corresponding contour of the blade can be changed by means of a cavity containing the blade.
【０００３】貫流断面の変更は例えばタービンロータの
前方の案内装置を種々の流量に適合させるために、又は
圧縮機ロータの後方の後置案内装置を種々の流量に適合
させるために望ましい。A modification of the through-flow cross section is desirable, for example, to adapt the guide device in front of the turbine rotor to different flow rates, or to adapt the rear guide device behind the compressor rotor to different flow rates.
【０００４】アメリカ合衆国特許第4403914 号明細書か
ら、タービンの案内装置及び圧縮機の後置案内装置の可
変な形状寸法を備えるこの種の流体機械が知られてい
る。その用途は燃焼室の中で特に液体又は気体の燃料が
燃焼されるタービン原動機（ガスタービン）である。燃
焼が少ない残滓で行われる高品質の燃料の使用を前提と
して、タービン案内装置の翼への侵食的に作用する堆積
物、従って調節要素の作動の際の翼及び空所の激しい摩
耗をほぼ完全に防止することができる。From US Pat. No. 4,403,914, a fluid machine of this kind is known with variable geometry of the turbine guide and the compressor rear guide. Its application is in turbine engines, in which liquid or gaseous fuels are burned, especially in combustion chambers. Given the use of high-quality fuels with low-burning residues, erosive deposits on the blades of turbine guides and thus severe wear on the blades and cavities during actuation of the adjusting elements are almost completely eliminated. Can be prevented.
【０００５】これに対していわゆる残留燃料（重油）の
燃焼の際に発生する燃焼残滓は不燃性成分と共に侵食特
性を有する固着性堆積物を形成し、この堆積物は効率を
低下させるばかりでなく激しい摩耗を引き起こす。同様
な状態は重油により運転されるディーゼルエンジンの過
給のために用いられる半径流タービン過給機の場合にも
生じる。On the other hand, the combustion residue generated during the combustion of so-called residual fuel (heavy oil) forms, together with the non-combustible components, a sticky deposit having erosion characteristics, which not only lowers the efficiency. Causes severe wear. A similar situation occurs with radial-flow turbine superchargers used for supercharging diesel engines operated with heavy oil.
【０００６】[0006]
【発明が解決しようとする課題】この発明の課題は、製
作費が少なく、貫流断面の変更のために必要な部品の摩
耗が堆積層が厚い場合にも極めて小さく、かつ翼上に形
成された堆積層の除去のためにタービンの停止時間中に
これらの部品を利用できるように、前記の種類の流体機
械特にタービン過給機のための半径流タービンを改良す
ることにある。The object of the present invention is that the manufacturing cost is low, the wear of the parts necessary for changing the cross section of the flow-through is extremely small even when the deposited layer is thick, and it is formed on the blade. The object is to improve the radial flow turbines for fluid machines of the type mentioned above, in particular for turbine superchargers, so that these parts can be utilized during turbine downtime for the removal of deposits.
【０００７】[0007]
【課題を解決するための手段】この課題はこの発明に基
づき、上記の摩耗性の改善のため、案内装置又は翼及び
貫流断面を変更する調節要素の所定の部品に対して適当
な材料を用いることにより解決される。このために案内
装置の翼を収容する空所を備える部品がセラミックから
作られ、翼がこれを支持する部品と共に金属材料から作
られる。用いられるセラミックは例えば一体構造の酸化
ジルコニウムとすることができる。翼及び翼を支持する
部品のための金属材料に関しては、今日では粉末冶金で
一般に用いられる方法（熱間静水圧成形法）により作ら
れた特にコバルトベース（例えばステライト）又はニッ
ケルベースの材料を用いることができる。耐熱性を有す
る金属材料をこれらの部品のために用い、これらの部品
に熱的方法（火炎又はプラズマ溶射）によりセラミック
又は炭化物又は酸化物の材料の溶射層を設けることも考
えられる。セラミックに関しては例えばＡｌ2 Ｏ3 、Ａ
ｌ2 Ｏ3 ＋ＴｉＯ2、Ｃｒ2 Ｏ3 ／ＮｉＡｌ又はＣｒ2
Ｏ3 を用いることができ、炭化物に関しては例えばＷＣ
／Ｃｏ、ＷＣ／Ｎｉ／Ａｌ又はＣｏ／Ｃｒ／Ｍｏ／Ｗ／
Ｎｉ／Ｓｉを用いることができ、また酸化物に関しては
例えばＴｉＯ2 又はＺｒＯ2 を用いることができる。そ
のほか金属部品の被覆のために化学的又は物理的蒸着法
を使用することもでき、そのために例えばＶＣ、Ｎｂ
Ｃ、ＴｉＣ、ＴｉＮ、Ｗ2 Ｃ、Ｃｒ7 Ｃ3 又はＡｌ2 Ｏ
3 を用いることができる。This object is based on the invention on the basis of the invention by using suitable materials for certain parts of the guide device or of the wing and of the adjusting element for changing the flow-through section. Will be solved. For this purpose, the component with the cavities for accommodating the vanes of the guide device is made of ceramic, and the vanes together with the components supporting them are made of metallic material. The ceramic used can be, for example, monolithic zirconium oxide. With regard to metallic materials for blades and parts supporting blades, especially cobalt-based (eg stellite) or nickel-based materials made today by methods commonly used in powder metallurgy (hot isostatic pressing) are used. be able to. It is also conceivable that a heat-resistant metallic material is used for these parts and that these parts are provided with a thermal spray layer of a ceramic or carbide or oxide material by a thermal method (flame or plasma spraying). For ceramics, for example, Al 2 O 3 , A
l 2 O 3 + TiO 2 , Cr 2 O 3 / NiAl or Cr 2
O 3 can be used, for carbides such as WC
/ Co, WC / Ni / Al or Co / Cr / Mo / W /
Ni / Si can be used, and for the oxide, for example, TiO 2 or ZrO 2 can be used. In addition, it is also possible to use chemical or physical vapor deposition methods for the coating of metal parts, for example VC, Nb
C, TiC, TiN, W 2 C, Cr 7 C 3 or Al 2 O
3 can be used.
【０００８】すべての翼が流体機械の停止時間中に軸方
向全長にわたり直線的な軸方向移動により空所中へ導入
でき、かつすべての空所が貫流路に向かう稜部を有する
ように空所が形成されることにより、空所中への翼の導
入の際に翼から堆積層を削り取ることができる。All the vanes can be introduced into the void by a linear axial movement over the entire axial length during the downtime of the fluid machine, and all voids have ridges towards the through-passage. Due to the formation of the layer, the deposition layer can be scraped off from the blade when the blade is introduced into the void.
【０００９】[0009]
【実施例】次にこの発明に基づく流体機械の複数の実施
例を示す図面により、この発明を詳細に説明する。DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will now be described in detail with reference to the drawings showing a plurality of embodiments of a fluid machine according to the present invention.
【００１０】第１図に示す流体機械は一つ又は複数の流
入路２が内部に設けられたハウジング１を有する。ハウ
ジング１と強固に結合された軸受ハウジング２２には、
半径方向へ貫流されるロータ４が軸３上に回転自在に軸
受支持されている。ロータ４はこの実施例ではタービン
ロータである。流入路２は貫流路５を介してロータ４と
結合されている。貫流方向に関してロータ４の前方に翼
６を備える案内装置７が配置されている。案内装置７は
ロータ４の周囲に同心に配置され側壁として形成された
リング形の調節要素８を有する。調節要素８には貫流路
５の中へ達する翼６が強固に取り付けられている。この
調節要素８は貫流路５に対し直稜部にすなわち軸３に対
し軸平行に移動可能に流体機械のハウジング１の中に配
置されている。調節要素８の軸方向寸法は、調節要素８
とハウジング１との間の流れを防止するために、タービ
ンの運転の際の最大の所定調節行程より大きいように選
択されている。流体機械の運転中には調節行程の大きさ
は、最小貫流断面積が最大貫流断面積の少なくとも半分
の大きさであるように設計されている。さもなければ案
内装置の後ろでの強い流れ剥離による効率の低下を覚悟
しなければならない。しかしタービンの停止中には調節
要素８を翼６の清掃のために貫流路５の幅全体にわたり
動かすことができる。案内装置７の調節要素８と向かい
合う側壁９は強固に軸受ハウジング２２中に組み込ま
れ、翼６の輪郭に相応する空所１０を有する。空所１０
は僅かに錐形に構成されているので、貫流路に向かう稜
部２３は翼６から堆積物を除去するために逃げ研磨面付
ききさげのように働くことができる。錐形の凹所の最も
狭い個所は貫流路５に隣接する。翼６の軸方向寸法は、
最大貫流断面に調節されている場合にも翼が側壁９の空
所１０中で案内されるように選択されている。The fluid machine shown in FIG. 1 has a housing 1 in which one or a plurality of inflow passages 2 are provided. The bearing housing 22 firmly connected to the housing 1 includes:
A rotor 4 which flows through in the radial direction is rotatably supported on the shaft 3 by bearings. The rotor 4 is a turbine rotor in this embodiment. The inflow passage 2 is connected to the rotor 4 via the through passage 5. A guide device 7 with blades 6 is arranged in front of the rotor 4 in the flow-through direction. The guide device 7 has a ring-shaped adjusting element 8 arranged concentrically around the rotor 4 and formed as a side wall. The adjusting element 8 is rigidly mounted with wings 6 which extend into the through passage 5. This adjusting element 8 is arranged in the housing 1 of the fluid machine in such a way that it can be moved along the straight channel with respect to the through-passage 5, that is to say parallel to the axis 3. The axial dimension of the adjusting element 8 is
In order to prevent a flow between the housing 1 and the housing 1, it is selected to be larger than the maximum predetermined adjusting stroke during the operation of the turbine. During operation of the fluid machine, the size of the adjustment stroke is designed such that the minimum cross-sectional flow area is at least half the maximum cross-sectional flow area. Otherwise, one must be prepared to lose efficiency due to strong flow separation behind the guide. However, during shutdown of the turbine, the adjusting element 8 can be moved over the width of the passage 5 for cleaning the blades 6. The side wall 9 of the guide device 7 facing the adjusting element 8 is rigidly integrated in the bearing housing 22 and has a cavity 10 corresponding to the contour of the blade 6. Vacant space 10
Is slightly pyramidal, the ridges 23 towards the through channels can act like flanks with flanks for removing deposits from the blades 6. The narrowest part of the conical recess is adjacent to the through channel 5. The axial dimension of the blade 6 is
The blades are also selected so that they are guided in the cavity 10 of the side wall 9 even when adjusted to the maximum flow-through section.
【００１１】図２は案内装置７の翼６が係合する空所１
０を備える側壁９を示し、その際各翼６の輪郭を囲むで
きるだけ狭い間隙１１が形成されている。側壁９は一体
のリングとしてばかりでなく図示のように複数の個別部
分から集成することもできる。FIG. 2 shows a space 1 in which the wings 6 of the guiding device 7 engage.
A side wall 9 with 0 is shown, in which the narrowest possible gap 11 is formed which encloses the contour of each wing 6. The side wall 9 may not only be an integral ring, but may also be assembled from a plurality of individual parts as shown.
【００１２】更に流体機械はロータ４の軸３に対し同心
にハウジング１に回動可能に支持された調節リング１２
を有し、この調節リング中には回動方向に対し斜めに延
びる溝１３が掘り込まれ、また調節リングは調節レバー
１４と強固に結合されている。各溝１３にはピン１５が
係合する。各ピン１５はつめ１６を介して、ハウジング
１内で直線的に案内装置７のリング形の調節要素８の軸
線に対し平行に導かれたピン１７の自由端上に強固に取
り付けられている。ピン１７は同じく案内装置７の調節
要素８と強固に結合されている。清掃のために必要であ
るような貫流路５の全幅にわたる調節要素８の軸方向移
動を可能にするために、調節リング１２の幅は貫流路５
の最大幅より大きく選択されている。Further, the fluid machine has an adjusting ring 12 rotatably supported on the housing 1 concentrically with the shaft 3 of the rotor 4.
A groove 13 extending obliquely with respect to the rotating direction is formed in the adjusting ring, and the adjusting ring is firmly connected to the adjusting lever 14. A pin 15 is engaged with each groove 13. Each pin 15 is rigidly mounted via a pawl 16 on the free end of a pin 17 which is guided linearly in the housing 1 parallel to the axis of the ring-shaped adjusting element 8 of the guide device 7. The pin 17 is likewise rigidly connected to the adjusting element 8 of the guiding device 7. The width of the adjusting ring 12 is such that the axial movement of the adjusting element 8 over the entire width of the through channel 5 as required for cleaning is possible.
Is selected to be larger than the maximum width of.
【００１３】機械的に又は油圧で又は空気圧で行うこと
ができる調節レバー１４の操作の際に、調節リング１２
が回動する。回動方向に対し斜めに延びる溝１３のため
に、ピン１７が調節リング１２により溝１３の延び方向
の傾斜に応じて多少とも軸方向に移動する。ピン１７の
軸方向移動により調節要素８及び貫流路５中へ達する翼
６が軸方向へ動く。その際翼６は多少とも案内装置７の
向かい合う側壁９の空所１０中へ入る。それにより翼６
の高さ従って貫流路５の貫流断面積が無段階に変更され
る。それにより貫流断面をそのつどの流量に適合させる
ことができる。その際調節運動のための制御量として例
えば流入路中の圧力のような流体機械自体の運転パラメ
ータを用いることができる。流体機械が排気タービン過
給機であるならば、エンジンの運転パラメータを制御量
として用いることもできる。During actuation of the adjusting lever 14, which can be done mechanically or hydraulically or pneumatically, the adjusting ring 12
Rotates. Due to the groove 13 extending obliquely with respect to the direction of rotation, the pin 17 is moved by the adjusting ring 12 more or less axially according to the inclination of the groove 13 in the extending direction. Axial movement of the pin 17 causes axial movement of the adjusting element 8 and the wings 6 which reach into the through passage 5. The wings 6 then more or less enter the cavities 10 of the opposite side walls 9 of the guiding device 7. Thereby wings 6
And therefore the cross-sectional flow-through area of the through-flow channel 5 is continuously changed. The flow-through section can thereby be adapted to the respective flow rate. The operating parameters of the fluid machine itself, such as the pressure in the inlet channel, can be used as control variables for the adjusting movement. If the fluid machine is an exhaust turbine supercharger, engine operating parameters can also be used as control variables.
【００１４】流体機械は図３に示すように調節可能な案
内装置１８を有することもできる。この案内装置１８は
その翼１９が側面部２１を介して流体機械の軸受ハウジ
ング２２と結合されるように構成されている。側壁とし
て形成された調節要素２０は翼１９の輪郭に適合し翼１
９により貫かれる空所１０を有し、空所中には図３の初
期位置に示された翼１９が若干突入している。各翼１９
の輪郭を囲んでここでもできるかぎり狭い間隙１１が残
っている。この実施例の場合も空所１０は第１の実施例
と同様に同じ目的のために僅かに錐形に形成することが
できる。この調節要素２０はピン１７により上記の限界
内で移動可能である。可能な位置が図３に破線で示され
ている。この実施例の場合にも調節要素２０を貫流路５
の幅全体にわたって軸方向に移動できるようにするため
に、空所１０は少なくとも翼６の軸方向寸法と同じ深さ
に構成しなければならない。この調節要素２０は側壁９
と同様に一体にするか又は複数の部分から集成すること
ができる。The fluid machine may also have an adjustable guide device 18 as shown in FIG. The guide device 18 is constructed such that its wings 19 are connected via a side part 21 to a bearing housing 22 of the fluid machine. The adjusting element 20 formed as a side wall conforms to the contour of the wing 19 and
There is a cavity 10 pierced by 9 in which a wing 19 shown in the initial position of FIG. 3 projects slightly. Each wing 19
There is still a narrow gap 11 surrounding the contour of FIG. In this embodiment too, the cavity 10 can be formed in a slightly conical shape for the same purpose as in the first embodiment. This adjusting element 20 is movable by means of a pin 17 within the limits mentioned above. The possible positions are indicated by dashed lines in FIG. In the case of this embodiment as well, the adjusting element 20 extends through the flow path 5
The cavity 10 must be constructed at least as deep as the axial dimension of the airfoil 6 in order to be able to move axially over its entire width. This adjusting element 20 has a side wall 9
As well as can be integrated or assembled from multiple parts.
【００１５】この変形例は、流動力により生じる接線力
がピン１７上に働かず、ピン案内部中の大きい摩擦が避
けられるという長所を有する。This modification has the advantage that the tangential force generated by the flow force does not act on the pin 17 and large friction in the pin guide is avoided.
【００１６】軸方向移動の際の翼６、１９の固渋を心配
する必要なしに、案内装置７、１８の翼６、１９と案内
装置７、１８の側壁９又は案内装置２０中の空所１０と
の間の間隙１１を最小にするために、翼６、１９はほん
の僅かだけ錐形に特に筒形に構成することができる。A void in the wings 6, 19 of the guide device 7, 18 and the side wall 9 of the guide device 7, 18 or the guide device 20 without having to worry about the tightness of the wings 6, 19 during axial movement. In order to minimize the gap 11 between the vanes 6, the wings 6, 19 can be designed to be only slightly pyramidal, in particular cylindrical.
【図１】この発明に基づく流体機械の一実施例の軸方向
断面図である。FIG. 1 is an axial sectional view of an embodiment of a fluid machine according to the present invention.
【図２】図１に示す案内装置の切断線Ａ−Ａによる断面
図である。2 is a cross-sectional view taken along the line AA of the guide device shown in FIG.
【図３】貫流断面を変更する調節要素の異なる実施例の
軸方向断面図である。FIG. 3 is an axial sectional view of a different embodiment of the adjusting element for changing the flow-through section.
１ 流体機械ハウジング ４ ロータ ５ 貫流路 ６、１９ 翼 ７、１８ 案内装置 ８、２０ 調節要素 ９、２１ 部品 １０ 空所 １２ 調節リング １３ 溝 １５、１７ ピン １６ つめ ２２ 軸受ハウジング ２３ 稜部 DESCRIPTION OF SYMBOLS 1 Fluid machinery housing 4 Rotor 5 Through flow path 6,19 Wing 7,18 Guide device 8,20 Adjusting element 9,21 Parts 10 Vacancy 12 Adjusting ring 13 Groove 15,17 pin 16 Pawl 22 Bearing housing 23 Ridge
Claims (9)
る案内装置、及び同心に配置されロータ軸に対し平行に
移動可能であって貫流断面を変更する調節要素を備え、
その際調節要素が案内装置の側壁の一部としてタービン
の流出側に形成され、案内装置の向かい合う側壁が軸受
ハウジングと強固に結合され、貫流断面中へ突入する翼
の高さが調節要素の直線状の軸方向移動及び翼の輪郭に
相応し翼を収容する空所により変更可能であるような流
体機械において、空所（１０）はすべての翼（６、１
９）がその軸方向全長にわたり調節要素（８、２０）の
直線的な軸方向移動により空所（１０）の中へ導入可能
であるように構成され、また空所（１０）が翼（６、１
９）の表面付着物除去のために貫流路（５）に向かう稜
部（２３）を有し、空所（１０）を備える部品（９、２
０）がセラミックから成り、翼（６、１９）がこれを支
持する部品（８、２１）と共に金属材料から成ることを
特徴とする流体機械。1. A rotor having a radial flow-through, a guide device with vanes, and a concentrically arranged movable element parallel to the rotor axis and for changing the flow-through cross section,
In this case, the adjusting element is formed on the outlet side of the turbine as part of the side wall of the guide device, the opposite side wall of the guide device is firmly connected to the bearing housing, and the height of the blades projecting into the through-flow cross section is the straight line of the adjusting element. In a fluid machine in which the axial movement of the blade and the cavity corresponding to the contour of the blade can be changed, the cavity (10) comprises all the blades (6, 1).
9) is constructed such that it can be introduced into the cavity (10) by linear axial movement of the adjusting element (8, 20) over its entire axial length, and the cavity (10) is also a blade (6). 1
A component (9, 2) having a ridge (23) toward the through channel (5) for removing surface deposits of (9) and having a void (10).
A fluid machine characterized in that 0) is made of ceramic and the blades (6, 19) are made of metallic material together with the parts (8, 21) supporting them.
（６）が強固に結合された調節要素であり、空所（１
０）を有する部品（９）は向かい合って置かれ軸受ハウ
ジング（２２）を介して流体機械のハウジング（１）と
強固に結合された案内要素（７）の側壁（９）であるこ
とを特徴とする請求項１記載の流体機械。2. The component (8) supporting the wing (6) is an adjusting element to which the wing (6) is firmly connected, the cavity (1)
The component (9) with 0) is a side wall (9) of the guide element (7) which is placed face to face and is rigidly connected to the housing (1) of the fluid machine via the bearing housing (22). The fluid machine according to claim 1.
体機械の軸受ハウジング（２２）と強固に結合された案
内装置（１８）の側面部分であり、この側面部分に翼
（１９）が強固に結合され、空所（１０）を有する部品
（２０）が調節要素を形成する案内装置（１８）の側壁
であることを特徴とする請求項１記載の流体機械。3. A part (21) for supporting the wing (19) is a side part of a guide device (18) rigidly connected to a bearing housing (22) of the fluid machine, and the wing (19) is attached to this side part. A fluid machine according to claim 1, characterized in that the component (20) is rigidly connected and the part (20) with the cavity (10) is the side wall of the guiding device (18) forming the adjusting element.
それにより貫流路（５）に向かう稜部（２３）が翼
（６、１９）の表面付着物除去のために逃げ研磨面付き
きさげのように働くことを特徴とする請求項１ないし３
の一つに記載の流体機械。4. The void (10) is formed in a slightly conical shape,
4. The ridges (23) towards the through passages (5) thereby act like a flank with a relief grinding surface for removing surface deposits on the blades (6, 19).
A fluid machine according to one of the items.
２）がロータ（４）の軸に対し同心に回動可能に支持さ
れ、この調節リングはその回動方向に対し斜めに延びる
溝（１３）を有し、溝には調節要素（８、２０）と強固
に結合された各一つのピン（１５）が係合することを特
徴とする請求項１ないし４の一つに記載の流体機械。5. An adjusting ring (1) in the housing (1).
2) is rotatably supported concentrically with respect to the axis of the rotor (4), this adjusting ring having a groove (13) extending obliquely to its direction of rotation, in which groove the adjusting element (8, 20) is provided. 5. A fluid machine as claimed in claim 1, characterized in that each pin (15) which is rigidly connected to the said (1) engages.
節リング（１２）の溝（１３）に係合し、各つめ（１
６）がハウジング（１）内で直線的に導かれるピン（１
７）の自由端に固く係合し、ピン（１７）が案内装置
（７、１８）の調節要素（８、２０）に強固に結合され
ていることを特徴とする請求項１ないし５の一つに記載
の流体機械。6. A pin (15) comprising a pawl (16) engages in a groove (13) of the adjusting ring (12), each pawl (1)
6) a pin (1) which is guided linearly in the housing (1)
One of the claims 1 to 5, characterized in that the pin (17) is rigidly connected to the free end of the guide element (7) and is rigidly connected to the adjusting element (8, 20) of the guide device (7, 18). Fluid machine according to item 1.
積の少なくとも半分の大きさであることを特徴とする請
求項１ないし６の一つに記載の流体機械。7. The fluid machine according to claim 1, wherein the minimum cross-sectional flow area is at least half the maximum cross-sectional cross-sectional area during operation.
加工されていることを特徴とする請求項１記載の流体機
械。8. A fluid machine according to claim 1, characterized in that the parts (9, 20) with voids are machined in one piece.
部分から集成されていることを特徴とする請求項１記載
の流体機械。9. Fluid machine according to claim 1, characterized in that the component (9, 20) with a cavity is assembled from a plurality of parts.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19924218229 DE4218229C1 (en) | 1992-06-03 | 1992-06-03 | Turbocharger with radial flow through impeller - has blade retaining recesses, into which blades are insertable after axial shift of adjuster |
| DE4218229.8 | 1992-06-03 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0633706A true JPH0633706A (en) | 1994-02-08 |
| JP3258136B2 JP3258136B2 (en) | 2002-02-18 |
Family
ID=6460263
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP15158193A Expired - Fee Related JP3258136B2 (en) | 1992-06-03 | 1993-05-28 | Fluid machine with rotor |
Country Status (2)
| Country | Link |
|---|---|
| JP (1) | JP3258136B2 (en) |
| DE (1) | DE4218229C1 (en) |
Cited By (3)
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|---|---|---|---|---|
| JP2007056791A (en) * | 2005-08-25 | 2007-03-08 | Mitsubishi Heavy Ind Ltd | Variable displacement exhaust turbosupercharger and manufacturing method for variable nozzle mechanism constituent member |
| JP2007211716A (en) * | 2006-02-10 | 2007-08-23 | Ishikawajima Harima Heavy Ind Co Ltd | Turbo compressor and freezer equipped with turbo compressor |
| JP2010169101A (en) * | 2010-05-14 | 2010-08-05 | Mitsubishi Heavy Ind Ltd | Variable displacement exhaust turbo supercharger and method of manufacturing variable nozzle mechanism structuring member |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19513044C2 (en) * | 1995-03-29 | 1997-09-18 | Heinz Noack | Flow turbine |
| GB9707453D0 (en) * | 1997-04-12 | 1997-05-28 | Holset Engineering Co | Linkage mechanism |
| DE10009099A1 (en) * | 2000-02-25 | 2001-08-30 | Man Nutzfahrzeuge Ag | Flow machine with radial construction for exhaust gas turbocharger; has adjustable conductor with rotatable guide blade formed with twist and fixed in sliding ring, to slide axially when it rotates |
| DE10016745B4 (en) | 2000-04-04 | 2005-05-19 | Man B & W Diesel Ag | Axial flow machine with a nozzle comprising a number of adjustable guide vanes |
| WO2002006636A1 (en) * | 2000-07-19 | 2002-01-24 | Honeywell Garrett Sa | Sliding vane turbocharger with graduated vanes |
| GB0121864D0 (en) | 2001-09-10 | 2001-10-31 | Leavesley Malcolm G | Turbocharger apparatus |
| DE10243103A1 (en) * | 2002-09-17 | 2004-03-25 | Rolls-Royce Deutschland Ltd & Co Kg | Device for adjusting the compressor blades of a gas turbine, comprises angled levers mounted on an adjusting ring and coupled to a blade spindle |
| DE102004047103A1 (en) * | 2004-09-29 | 2006-04-13 | Bayerische Motoren Werke Ag | turbocharger |
| US8608434B2 (en) | 2008-04-01 | 2013-12-17 | Cummins Turbo Technologies Limited | Variable geometry turbine |
| GB2462115A (en) * | 2008-07-25 | 2010-01-27 | Cummins Turbo Tech Ltd | Variable geometry turbine |
| GB0822474D0 (en) * | 2008-12-10 | 2009-01-14 | Cummins Turbo Tech Ltd | Variable geometry turbine nozzle ring |
| DE102009004890A1 (en) | 2009-01-16 | 2010-07-22 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Charging device, particularly exhaust gas turbocharger for motor vehicle, has adjusting element, which is adjusted parallel to turbine wheel axis that is operatively connected with rotatably supported guide vane |
| DE102009032306B4 (en) | 2009-07-09 | 2016-08-11 | Man Diesel & Turbo Se | Bearing housing a turbomachine and method for machining a bearing housing |
| GB0921350D0 (en) | 2009-12-05 | 2010-01-20 | Cummins Turbo Tech Ltd | Vaariable geometry turbomachine |
| CN102269018A (en) * | 2011-08-23 | 2011-12-07 | 常州环能涡轮动力有限公司 | Nozzle component of variable-section supercharger |
| GB201408087D0 (en) | 2014-05-07 | 2014-06-18 | Cummins Ltd | Variable geometry turbine assembly |
| DE102015212808A1 (en) * | 2015-07-08 | 2017-01-12 | Continental Automotive Gmbh | Exhaust gas turbocharger with adjustable turbine geometry |
| EP3633151A1 (en) * | 2018-10-05 | 2020-04-08 | Rolls-Royce plc | A variable geometry diffuser |
| GB2585634A (en) * | 2019-05-14 | 2021-01-20 | Cummins Ltd | Turbine |
| GB2592446A (en) * | 2020-02-28 | 2021-09-01 | Cummins Ltd | Variable geometry turbine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4403914A (en) * | 1981-07-13 | 1983-09-13 | Teledyne Industries, Inc. | Variable geometry device for turbomachinery |
-
1992
- 1992-06-03 DE DE19924218229 patent/DE4218229C1/en not_active Expired - Fee Related
-
1993
- 1993-05-28 JP JP15158193A patent/JP3258136B2/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007056791A (en) * | 2005-08-25 | 2007-03-08 | Mitsubishi Heavy Ind Ltd | Variable displacement exhaust turbosupercharger and manufacturing method for variable nozzle mechanism constituent member |
| JP4545068B2 (en) * | 2005-08-25 | 2010-09-15 | 三菱重工業株式会社 | Variable displacement exhaust turbocharger and variable nozzle mechanism component manufacturing method |
| JP2007211716A (en) * | 2006-02-10 | 2007-08-23 | Ishikawajima Harima Heavy Ind Co Ltd | Turbo compressor and freezer equipped with turbo compressor |
| JP2010169101A (en) * | 2010-05-14 | 2010-08-05 | Mitsubishi Heavy Ind Ltd | Variable displacement exhaust turbo supercharger and method of manufacturing variable nozzle mechanism structuring member |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3258136B2 (en) | 2002-02-18 |
| DE4218229C1 (en) | 1993-03-04 |
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