JPS60175707A - Variable nozzle of radial turbine - Google Patents

Variable nozzle of radial turbine

Info

Publication number
JPS60175707A
JPS60175707A JP3030484A JP3030484A JPS60175707A JP S60175707 A JPS60175707 A JP S60175707A JP 3030484 A JP3030484 A JP 3030484A JP 3030484 A JP3030484 A JP 3030484A JP S60175707 A JPS60175707 A JP S60175707A
Authority
JP
Japan
Prior art keywords
nozzle
wall member
turbine
vane
housing
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
Application number
JP3030484A
Other languages
Japanese (ja)
Other versions
JPH0610403B2 (en
Inventor
Seiji Achinami
阿知波　清次
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.)
Nissan Motor Co Ltd
Original Assignee
Nissan Motor Co Ltd
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 Nissan Motor Co Ltd filed Critical Nissan Motor Co Ltd
Priority to JP59030304A priority Critical patent/JPH0610403B2/en
Publication of JPS60175707A publication Critical patent/JPS60175707A/en
Publication of JPH0610403B2 publication Critical patent/JPH0610403B2/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line

Abstract

PURPOSE:To eleminate a gap between a nozzle van and a housing to improve the efficiency of a turbine by providing a movable wall member pressed against a wall surface position of a housing opposed to an end face of the nozzle vane. CONSTITUTION:A plurality of nozzle vanes 1 rotatable about a pivot shaft 2 are arranged circumferentially at equal intervals along a rotor inlet portion 4 of a turbine housing 3 for receiving a turbine rotor 5. An annular groove 10 is formed to interconnect the opposed positions of the end faces 1A of nozzle vanes in the turbine housing 3. And an annular movable wall member 11 is slidably received in the annular groove 10 and pressed against the vane 1 by the force of a spring 16 through a holding pin 14. Also, the movable wall member 11 is provided with a plurality of communicating holes 12 to afford communication between a nozzle portion 13 and a space in the groove 10 so that differential pressure is not produced between both portions.

Description

【発明の詳細な説明】 〔技術分骨〕 本発明はラジアルタービンの可変ノズルに関し、特にタ
ービンロータ入口部に沿って複数のノズル翼を配置し、
これらの軸をリングを介して一斉回動させるようにした
ラジアルタービンの可変ノズルに関する。[Detailed description of the invention] [Technical details] The present invention relates to a variable nozzle for a radial turbine, and in particular, a variable nozzle in which a plurality of nozzle blades are arranged along the inlet of a turbine rotor,
This invention relates to a variable nozzle for a radial turbine in which these shafts are rotated simultaneously through a ring.

〔従来技術〕[Prior art]

最近では自動車エンジン等のターボチャージャにこの種
の可変ノズル翼を設けたものが開発されてきており、以
て、低速から高速までの広い範囲にわたり排気エネルギ
の有効利用が図られている。Recently, turbochargers for automobile engines and the like have been developed that are equipped with variable nozzle blades of this type, and exhaust energy is effectively utilized over a wide range from low speeds to high speeds.

第１図はこのようなラジアルタービンの可変ノズルを示
すもので、本例は三菱１工技報ＶＯＬ、　２０−隘５　
（１９８３−９１の［トラック・バス用バリアプル・ジ
ェオメトリ・ターボ過給機付きエンジンの開発］に開示
されたものである。Figure 1 shows a variable nozzle for such a radial turbine, and this example is published in Mitsubishi 1 Engineering Report VOL, 20-5.
(This was disclosed in 1983-91 [Development of Varia-Pull Geometry Turbocharged Engine for Trucks and Buses]).

ここで、１はノズルベーン、２はそのノズルベーン１の
端面に取付けられたベーン回動軸であり、回動軸２によ
り回動自在としたこのような複数のノズルベーン１がタ
ービンハウジング３で形成されたロータ人口部４に沿っ
て周方向等間隔に配置されている。５はタービンロータ
である。Here, 1 is a nozzle vane, 2 is a vane rotating shaft attached to the end face of the nozzle vane 1, and a plurality of such nozzle vanes 1, which are rotatable by the rotating shaft 2, are formed in a turbine housing 3. They are arranged at equal intervals in the circumferential direction along the rotor artificial part 4. 5 is a turbine rotor.

しかして回動軸２は片側のハウジング３に枢支されてお
り、との回動軸２の他端には図示しないレバが取付けら
れていて、とのレバ端を摺動自在に保持するスライダ、
スライダとビンで連結されスライダと共に回動するリン
グ、リングを回動させる駆動装置（以上図示せず）を介
して回動軸２を同方向に一斉回動させ、以て、ノズルベ
ーン１の翼角を変化させて、ベーン１間のスロートの面
積を変化させるようにしている。The rotating shaft 2 is pivotally supported by a housing 3 on one side, and a lever (not shown) is attached to the other end of the rotating shaft 2, and a slider slidably holds the lever end of the rotating shaft 2. ,
The rotation shaft 2 is rotated all at once in the same direction through a ring that is connected to the slider through a bottle and rotates together with the slider, and a drive device that rotates the ring (not shown above). The area of the throat between the vanes 1 is changed by changing the area of the throat between the vanes 1.

しかしながら、このような従来のラジアルタービンの可
変ノズルにあっては、通常の場合、ノズルベー７１およ
びタービンハウジング３が共に金属で形成されているた
め、エンジンの作動中はこれらがしばしば高温雰囲気中
にさらされることにより、熱膨張によってノズルベーン
１のｆｉ面ＩＡとタービンハウジング３の壁面３Ａとが
接触して動作不能となる虞がある。However, in the variable nozzle of such a conventional radial turbine, the nozzle bay 71 and the turbine housing 3 are usually both formed of metal, so they are often exposed to a high temperature atmosphere during engine operation. As a result, there is a possibility that the fi surface IA of the nozzle vane 1 and the wall surface 3A of the turbine housing 3 come into contact with each other due to thermal expansion, making it impossible to operate.

そこで、予めノズルベーン１とタービンハウジング３と
の間には、このような熱膨張を見越してしかも接触が発
生しないだけのすき間が得られるように構成されていた
。しかして、本来、ベーンとベーンとの間を通るガス流
体がすき間が生ずることによりこ−から洩れ、タービン
入口に必要とする十分な流れが形成されず、タービン効
率を大幅に低下させる。Therefore, a gap between the nozzle vane 1 and the turbine housing 3 was designed in advance to allow for such thermal expansion and to prevent contact between the nozzle vane 1 and the turbine housing 3. Therefore, the gas fluid that originally passes between the vanes leaks through the gaps, and a sufficient flow required at the turbine inlet is not formed, resulting in a significant reduction in turbine efficiency.

〔目　的〕〔the purpose〕

本発明の目的は、このような問題点に着目し、ノズルベ
ーンとタービンハウジングとの間のスキ間をエンジンの
運転中宮に零化させることによシ、タービン効率の向上
を図ることができ、ターボチャージャに適用した場合は
そのエンジンの加速性能および出力性能の向上にも貢献
することのできるラジアルタービンの可変ノズルを提供
することにある。An object of the present invention is to address these problems and to reduce the gap between the nozzle vane and the turbine housing during engine operation, thereby improving turbine efficiency. The object of the present invention is to provide a variable nozzle for a radial turbine that, when applied to a charger, can contribute to improving the acceleration performance and output performance of the engine.

〔構　成〕〔composition〕

かかる目的を達成するために、本発明では、ノズルベー
ンの端面と対向するハウジングの壁面位（５） 置に、この端面に向けて押接可能な可動壁部材を設け、
この可動壁部材をばねおよびガス圧の少なくとも何れか
によりノズルベーン端面に向けて押接させ、以て、相互
間に面接触状態が保たれるようにする。In order to achieve such an object, the present invention provides a movable wall member that can be pressed toward the end surface of the nozzle vane at a position (5) on the wall surface of the housing opposite to the end surface of the nozzle vane.
This movable wall member is pressed toward the end face of the nozzle vane by at least one of a spring and gas pressure, thereby maintaining surface contact therebetween.

〔実施例〕〔Example〕

以下に、図面に基づき本発明の詳細な説明する０ 第２図は本発明の第１の実施例を示す。ここで、１０は
タービンハウジング３におけるノズルベーン端面ＩＡの
対向位置を連ねるようにして形成した環状溝であり、１
１はこの環状溝１０に受容され、端面ＩＡとは直角方向
に摺動自在と々した環状の可動壁部材（以下で単に壁部
材という）である。The present invention will be described in detail below with reference to the drawings. FIG. 2 shows a first embodiment of the present invention. Here, 10 is an annular groove formed so as to connect the opposite positions of the nozzle vane end surfaces IA in the turbine housing 3;
Reference numeral 1 denotes an annular movable wall member (hereinafter simply referred to as a wall member) which is received in this annular groove 10 and is slidable in a direction perpendicular to the end face IA.

なお、壁部材１１は熱膨張の影響を考慮してセラミック
スで形成するのが好適である。また、本例では壁部材１
１に連通孔１２を設けるようになし、溝１０の空間とノ
ズルベーン１が設けられているノズル部１３とを連通さ
せることにより、双（ｆｉ） 方間に圧力差が生じないようにする。Note that the wall member 11 is preferably formed of ceramics in consideration of the influence of thermal expansion. In addition, in this example, wall member 1
1 is provided with a communication hole 12, and the space of the groove 10 is communicated with the nozzle part 13 in which the nozzle vane 1 is provided, thereby preventing a pressure difference from occurring between the two directions.

１４は壁部材１１の溝空間側に当接させた壁部材保持ビ
ンであり、保持ビン１４を孔１５に摺動自在に嵌合わせ
、そのビン１４をばね１６のばね力により壁部材１１に
向けて圧接させ、以て壁部材１１をノズルベーンの端面
ＩＡに当接させるようにする。１７はばね１６の端部を
係止しているボルトであり、ボルト１７を孔１５に螺締
することによりばね１６のばね力を調整することができ
る。14 is a wall member holding bottle that is brought into contact with the groove space side of the wall member 11. The holding bottle 14 is slidably fitted into the hole 15, and the bottle 14 is directed toward the wall member 11 by the spring force of the spring 16. so that the wall member 11 is brought into contact with the end surface IA of the nozzle vane. Numeral 17 is a bolt that locks the end of the spring 16, and by screwing the bolt 17 into the hole 15, the spring force of the spring 16 can be adjusted.

なお、ここで、保持ビン１４．孔１５、ばね１６オヨヒ
ボルト１７を構成する位置は、ノズルベーン１が設けら
れている位置の必ずしも全てに設ける必要はなく、環状
をなす壁部材１１の開方向等分の位置に配設するように
してもよい。また、保持ビン１４は耐熱性に優れ、しか
も熱膨張率の低いセラミックスで形成するのが好適であ
る。Note that here, the holding bottle 14. The holes 15, the springs 16 and the bolts 17 do not necessarily have to be provided at all the positions where the nozzle vanes 1 are provided, but may be arranged at equal positions in the opening direction of the annular wall member 11. Good too. Further, it is preferable that the holding bottle 14 is made of ceramic which has excellent heat resistance and has a low coefficient of thermal expansion.

このように構成したラジアルタービンの可変ノズルにあ
っては、ノズルベーン１やハウジング３が高温雰囲気で
熱膨張しても、壁部材１１がばね１６のばね力によりノ
ズルベーン１の端面ＩＡＫ向けて保持ビン１４を介し圧
接した状態に保たれるので、端面ＩＡと壁部材１１の圧
接面との間にすき間の生じることがない。すなわち、す
き間の零化を達成することができる。In the variable nozzle of the radial turbine configured in this way, even if the nozzle vane 1 and the housing 3 thermally expand in a high-temperature atmosphere, the wall member 11 is moved toward the end face IAK of the nozzle vane 1 by the spring force of the spring 16 into the holding bin 14. Since the end face IA and the pressure contact surface of the wall member 11 are maintained in a pressed state, no gap is generated between the end face IA and the pressure contact surface of the wall member 11. In other words, the gap can be reduced to zero.

しかも、環状溝１０の空間とノズル部１３とは連通孔１
２により連通されているので、ノズル部１３に発生する
圧力によって、壁部材１１のノズルベーン１への押圧力
が影響されるようなことがなく、あくまで予め調整した
ばね１６の好適々ばね力のみによって壁部材】１をベー
ン１の端面ＩＡに押圧させた状態に保つことができて、
ノズルベーン１を回動させる駆動力が過大となるような
ことがない。Moreover, the space of the annular groove 10 and the nozzle part 13 are connected to the communication hole 1.
2, the pressure generated in the nozzle part 13 will not affect the pressing force of the wall member 11 against the nozzle vane 1, and the pressure generated in the nozzle part 13 will not be affected, and the pressure generated in the nozzle part 13 will not be affected, and the pressure generated in the nozzle part 13 will not be affected, and the pressure generated in the nozzle part 13 will not be affected. [Wall member] 1 can be kept pressed against the end surface IA of the vane 1,
The driving force for rotating the nozzle vane 1 does not become excessive.

第３図は本発明の第２の実施例を示す。本例は壁部材１
１の内周面および外周面と摺接するハウジング３側の環
状溝１０の壁面側に全周にわたりそれぞれ突出部１０Ａ
を形設し、これらの突出部１０Ａと壁部材１１の内周面
および外周面が線接触を保つようにしだものである。な
お、その他の構成については第２図に示した例と同様と
する。FIG. 3 shows a second embodiment of the invention. In this example, wall member 1
A protruding portion 10A is provided on the wall side of the annular groove 10 on the housing 3 side, which is in sliding contact with the inner circumferential surface and the outer circumferential surface of the housing 1, over the entire circumference.
are formed so that these protrusions 10A and the inner and outer peripheral surfaces of the wall member 11 maintain line contact. Note that the other configurations are the same as the example shown in FIG. 2.

しかして、このように構成することにより、壁部材１１
摺接摩擦抵抗を軽減することができ、壁部材１１のノズ
ルベーン１との接触動作を円滑にすることができる。Therefore, by configuring in this way, the wall member 11
The sliding friction resistance can be reduced, and the contact movement of the wall member 11 with the nozzle vane 1 can be made smooth.

第４図はこれらのようにして、壁部材１１をベーン１に
押接させ、以て、ベー７１とハウジング形態のタービン
において、すき間を設計点で０，４關に設定した場合の
タービン温度効率特性曲線が破線で示されており、実線
は本発明によりすき間を零化した場合のその特性曲線を
示す。すなわち、本発明を適用することにより、すき間
を設定した場合は７５％程度であったタービンの温度効
率を８５％程度にまで向上させることができることを確
認した。FIG. 4 shows the turbine temperature efficiency when the wall member 11 is pressed against the vane 1 in this manner, and the clearance between the vane 71 and the housing type turbine is set to 0.4 at the design point. The characteristic curve is shown by a broken line, and the solid line shows the characteristic curve when the gap is reduced to zero according to the invention. That is, it has been confirmed that by applying the present invention, the temperature efficiency of the turbine can be improved from about 75% when a gap is set to about 85%.

第５図は本発明の第３の実施例を示す。本例は壁部材１
１をノズルベーン１の端面ＩＡに押圧させるのにばねを
用いず気体圧のみを用いるように（９） したものである。FIG. 5 shows a third embodiment of the invention. In this example, wall member 1
1 is pressed against the end surface IA of the nozzle vane 1 by using only gas pressure without using a spring (9).

すなわち、ここで、２０は環状溝１０とタービンスクロ
ール部２１とを連通させるようにした圧力導通管である
。一般に、スクロール部２１のこのような壁面に沿った
位置での静圧は、これより流速の高められるノズル部１
３の壁面に沿った位置での静圧に比して高く保たれてい
る。そこで、このスクロール部２１の高く保たれている
静圧を圧力導通管２０により環状溝１０の空間に導いて
、その圧力差により壁部材１１をノズルベーン１の端面
ＩＡに押圧させるようにする。That is, here, 20 is a pressure communication pipe that connects the annular groove 10 and the turbine scroll portion 21. Generally, the static pressure at such a position along the wall surface of the scroll portion 21 is higher than that of the nozzle portion 1 where the flow velocity is increased.
The static pressure is maintained higher than the static pressure at the position along the wall surface of No. 3. Therefore, the static pressure maintained at a high level in the scroll portion 21 is introduced into the space of the annular groove 10 through the pressure conduction pipe 20, and the wall member 11 is pressed against the end surface IA of the nozzle vane 1 due to the pressure difference.

第６図（４）は第５図に示した第３の実施例に対し、そ
の壁部材１１の内周面ならびに外周面と、これらの面に
対応する環状溝１０側のそれぞれの面との間にシールリ
ング３０を設けるようにしたものであし、３１はそのリ
ング溝である。また、第６図（Ｂ）は第６図（４）のシ
ールリング３０やリング溝３１に代えて、ラビリンスシ
ール３２を設けた例である。FIG. 6(4) shows the inner circumferential surface and outer circumferential surface of the wall member 11 and the respective surfaces on the annular groove 10 side corresponding to these surfaces in the third embodiment shown in FIG. A seal ring 30 is provided in between, and 31 is the ring groove. Moreover, FIG. 6(B) is an example in which a labyrinth seal 32 is provided in place of the seal ring 30 and ring groove 31 in FIG. 6(4).

すなわち、このようなシール装置を設けること（１０） により、壁部材１１に摺動性を保持させながら、環状溝
１０の空間とノズル部１３との間にある程度の気密性を
保持させることができる。That is, by providing such a sealing device (10), it is possible to maintain a certain degree of airtightness between the space of the annular groove 10 and the nozzle portion 13 while maintaining the slidability of the wall member 11. .

第７図は本発明の第４の実施例を示す。FIG. 7 shows a fourth embodiment of the invention.

本例では壁部材１１の環状溝１０空間側に突起部１１Ａ
を形成すると共に、この突起部１１Ａに保持ピン１４が
当接するようになし、保持ピン１４の径を十分大きくす
ることにより、突起部１１Ａに当接する保持ピン１４の
端面１４Ａが突起部１１Ａの当接端面に比して十分大き
い面積に保たれるようにする。In this example, a protrusion 11A is provided on the annular groove 10 space side of the wall member 11.
At the same time, by making the diameter of the holding pin 14 sufficiently large so that the end surface 14A of the holding pin 14 that contacts the protrusion 11A comes into contact with the protrusion 11A. The area should be kept sufficiently large compared to the contact surface.

更にまた、本例では圧力導通管２０の外に、保持ピン１
４を摺動自在に嵌合保持している孔１５の空間と、ノズ
ル部１３より下流の例えばシュラウド部３Ｂとの間に圧
力導通管３３を設ける。なお、これらの圧力導通管２０
および３３や保持ピン１４．孔１５．ばね１６およびボ
ルト１７を設ける位置は、第２図の場合と同様タービン
ロータ５の置方向に適当の間隔を置いて配設すればよく
、ノズルベー７１の必ずしも全ての設置位置に設ける必
要はない。Furthermore, in this example, a holding pin 1 is provided outside the pressure conduit 20.
A pressure conduction pipe 33 is provided between the space of the hole 15 in which the nozzle 4 is slidably fitted and held, and the shroud part 3B downstream of the nozzle part 13, for example. In addition, these pressure conduction pipes 20
and 33 and retaining pin 14. Hole 15. The springs 16 and bolts 17 may be provided at appropriate intervals in the direction of placement of the turbine rotor 5, as in the case of FIG. 2, and do not necessarily need to be provided at all locations on the nozzle bay 71.

このように構成したラジアルタービンの可変ノズルにお
いては、エンジンの運転状態に応じてガスの差圧とばね
のばね力との双方を組合せた力で壁部材１１をノズルベ
ーン１の端面ＩＡに押圧させることができる。すなわち
、ノズル部１３において、可変ノズルが絞られておらず
、あるいはタービンロータ５への流入ガス流量が少ない
ような運転状態では、スクロール部２１とノズル部１３
とで圧力差が大方零に近くなり、もし、ばね１６や導通
管３３が設けてないとすると、上記の圧力差のみで壁部
材１１をベーン端面ＩＡに押圧させることが困難となり
、不安定ガ状態から壁部材１１に振動が発生する虞があ
る。In the variable nozzle of the radial turbine configured in this way, the wall member 11 is pressed against the end surface IA of the nozzle vane 1 by a force that combines both the gas pressure difference and the spring force of the spring depending on the operating state of the engine. I can do it. That is, in an operating state in which the variable nozzle is not throttled in the nozzle portion 13 or the flow rate of gas flowing into the turbine rotor 5 is small, the scroll portion 21 and the nozzle portion 13
If the spring 16 and the conduit pipe 33 were not provided, it would be difficult to press the wall member 11 against the vane end face IA with only the above pressure difference, resulting in unstable gas. There is a possibility that vibration will occur in the wall member 11 due to this condition.

しかるに、本例ではばね１６を併用していることにより
、このような状況下ではばね１６のばね力で保持ピン１
４を介して壁部材１１をベーン端面ＩＡに押圧させるこ
とができる。However, in this example, since the spring 16 is also used, under such a situation, the spring force of the spring 16 will hold the holding pin 1.
4, the wall member 11 can be pressed against the vane end surface IA.

また、上記の圧力差により壁部材１１がベーン１に向け
て偏倚される場合は、低圧側からの圧力を導入する導通
管３３により孔１５の空間にスクロール部２１における
より低い静圧が導かれていることによって、保持ビ／１
４の両端部に働く差圧によりばね１６のばね力が減殺さ
れる方向に働く。Further, when the wall member 11 is biased toward the vane 1 due to the above pressure difference, the lower static pressure in the scroll portion 21 is introduced into the space of the hole 15 by the conduit pipe 33 that introduces pressure from the low pressure side. By keeping the
The differential pressure acting on both ends of the spring 16 acts in a direction that reduces the spring force of the spring 16.

かくして、壁部材１１に作用する力として差圧に更にば
ね力が加重されて過大になり過ぎるのを防止することが
できる。In this way, it is possible to prevent the force acting on the wall member 11 from becoming too excessive due to the addition of the spring force to the differential pressure.

第８図は本発明の更に第５の実施例を示す。本例は第７
図の例に対して、更に連通孔３４を設けるようにしたも
のであり、この連通孔３４は壁部材１１に直接設けて、
環状溝１０の空間部とノズル部１３との間を連通させる
ようにしてもよいし、図示はしないが、スクロール部２
１より低い静圧の得られるところから環状溝１０の空間
部へとハウジング３に直接連通孔を設けるようにしても
よい０ なお、本例はこのような連通孔３４を設けることにより
、第４の実施例より更に一層差圧を抑制するようにした
ものであシ、シたがって、連通孔（１３） ３４の孔の大きさの設定にあたっては、差圧が強大とな
り過ぎるような状態を想定して、これに対して差圧を低
減させるに好適な寸法となるようにする。FIG. 8 shows a further fifth embodiment of the invention. In this example, the seventh
In contrast to the example shown in the figure, a communication hole 34 is further provided, and this communication hole 34 is directly provided in the wall member 11,
The space of the annular groove 10 and the nozzle part 13 may be communicated with each other, and although not shown, the scroll part 2
A communicating hole may be provided directly in the housing 3 from a place where a static pressure lower than 1 is obtained to the space of the annular groove 10. In this example, by providing such a communicating hole 34, This is designed to suppress the differential pressure even more than the embodiment described above. Therefore, when setting the size of the communicating hole (13) 34, we assumed a situation where the differential pressure would become too strong. In contrast, the dimensions are set to be suitable for reducing the differential pressure.

〔効　果〕〔effect〕

以上説明したように、本発明によれば、一方のハウジン
グ壁に回動自在に保持されている複数のノズルベーンの
他方の端面と対向するハウジング壁の位置に、ノズルベ
ーンの端面に向けて移動可能な連続した環状の可動壁部
材を設け、この可動壁部材をばねおよび作動ガス圧の少
なくとも何れかによりノズルベーンの端面に向けて圧接
させるようにしたので、エンジンの運転中、ノズルベー
ンとタービンハウジングの壁との間のすき間を常時零化
することができて、タービン効率を向上させることがで
き、特にターボチャージャに適用した場合は、そのエン
ジンの加速性能および出力性能の向上にも貢献する。As explained above, according to the present invention, the plurality of nozzle vanes rotatably held on one housing wall are movable toward the end surfaces of the nozzle vanes at a position on the housing wall opposite to the other end surface of the plurality of nozzle vanes. A continuous annular movable wall member is provided and this movable wall member is brought into pressure contact with the end face of the nozzle vane by at least one of a spring and working gas pressure, so that the nozzle vane and the wall of the turbine housing are kept in contact with each other during engine operation. The gap between the two can be constantly reduced to zero, improving turbine efficiency, and especially when applied to a turbocharger, it also contributes to improving the acceleration performance and output performance of the engine.

更にまた、ばねのばね力とガスの作用圧とがエンジンの
運転状態に応じて適切に相互作用するよ（１４） う構成することにより、過大な圧接力がノズルベーンに
作用するのを抑制することができる。Furthermore, by configuring the structure so that the spring force of the spring and the working pressure of the gas interact appropriately depending on the operating state of the engine (14), it is possible to suppress excessive contact force from acting on the nozzle vane. I can do it.

なお、以上の実施例のうち保持ビンを介して可動壁部祠
をノズルベーンの端面に押接させるようにしたものにあ
っては、保持ビンと可動壁部材とを一体化して形成する
ことも可能であり、更にこれらをセラミックスで形成す
るようにしてもよいことは勿論である。In addition, among the above embodiments, in those in which the movable wall shrine is pressed against the end face of the nozzle vane via the holding bottle, it is also possible to form the holding bottle and the movable wall member integrally. Of course, they may also be made of ceramics.

【図面の簡単な説明】[Brief explanation of drawings]

第１図は従来のラジアルタービンの可変ノズルの構成の
一例を示す断面図、 第２図は本発明ラジアルタービンの可変ノズルの第１実
施例の構成を示す断面図、 第３図は本発明の第２実施例の構成を示す断面図・ 第４図は本発明ラジアルタービン可変ノズルと従来例と
のタービン温度効率を比較して示す特性曲線図、 第５図は本発明の第３実施例の構成を示す断面図１ 第６図（４）および（Ｂ）は第３実施例の一部を変形し
たそれぞれ形態を示す断面図、 第７図は本発明の第４実施例の構成を示す断面図＼ 第８図は本発明の第５実施例の構成を示す断面図である
。 １・・・ノズルベーン、 ＩＡ・・・端面、 ２・・・回動軸、 ３・・・タービンハウジング、 ３Ａ・・・壁面、 ３Ｂ・・・シュラウド部、 ４・・・ロータ入口部・ ５・・・タービンロータ、 １０・・・環状溝、 １０Ａ・・・突出部、 １１・・・可動壁部材、 １１Ａ・・・突起部、 １２・・・連通孔、 １３・・・ノズル部、 １４・・・保持ビン、 １４Ａ・・・端面、 １５・・・孔、 １６・・・ばね、 １７・・・ボルト、 ２０・・・圧力導通管、 ２１・・・スクロール部、 ３０・・・シールリング、 ３１・・・リング溝、 ３２・・・ラビリンスシール、 ３３・・・圧力導通管、 ３４・・・連通孔。 特許出願人　日産自動車株式金社 （１７） で計　− ♂　詔　ρ ｒ＞−’ｗ、′Ｘ四柩Ｓ羅ト く 区　− ！−一 綜 ト　９ 区　０ ４ 綜 区　０ ト 昧 Ｑつ 綜 区　区 Ｄ　Ｃ 派　憾FIG. 1 is a sectional view showing an example of the configuration of a variable nozzle of a conventional radial turbine, FIG. 2 is a sectional view showing the configuration of a first embodiment of a variable nozzle of a radial turbine of the present invention, and FIG. 3 is a sectional view of a variable nozzle of the present invention. A sectional view showing the configuration of the second embodiment. Fig. 4 is a characteristic curve diagram showing a comparison of the turbine temperature efficiency of the variable radial turbine nozzle of the present invention and a conventional example. Fig. 5 is a characteristic curve diagram showing the turbine temperature efficiency of the variable radial turbine nozzle of the present invention and a conventional example. Cross-sectional view showing the structure 1 FIGS. 6(4) and (B) are cross-sectional views showing partially modified forms of the third embodiment, and FIG. 7 is a cross-sectional view showing the structure of the fourth embodiment of the present invention. FIG. 8 is a sectional view showing the configuration of a fifth embodiment of the present invention. DESCRIPTION OF SYMBOLS 1... Nozzle vane, IA... End face, 2... Rotation shaft, 3... Turbine housing, 3A... Wall surface, 3B... Shroud part, 4... Rotor inlet part, 5. ... Turbine rotor, 10... Annular groove, 10A... Projection, 11... Movable wall member, 11A... Projection, 12... Communication hole, 13... Nozzle part, 14. ...Holding bottle, 14A... End face, 15... Hole, 16... Spring, 17... Bolt, 20... Pressure conduction pipe, 21... Scroll part, 30... Seal ring , 31...Ring groove, 32...Labyrinth seal, 33...Pressure communication pipe, 34...Communication hole. Patent applicant Nissan Motor Co., Ltd. Kinsha (17) Total - ♂ Edict ρ r＞-'w,' - 1 9 wards 0 4 wards 0 4 wards 0 4 wards 0 4 wards 0

Claims (1)

【特許請求の範囲】 １）タービンロータ入口部のハウジング壁面間にノズル
部を形成し、該ノズル部に複数の回動自在としたノズル
ベーンを配置したラジアルタービンの可変ノズルにおい
て、前記ノズル部の一方のハウジング壁面に環状溝を形
成し、該環状溝に可動壁部材を前記タービンロータの軸
方向に摺動自在に嵌合して、該可動壁部材をばねおよび
タービンロータの作動圧の少なくとも一方によって前記
ノズルベーンの端面に押圧させるようにしたことを特徴
とするラジアルタービンの可変ノズル。 ２、特許請求の範囲第１項に記載のラジアルタービンの
可変ノズルにおいて、前記可動壁部材を前記ノズル部よ
り上流の前記作動圧により前記ノズルベーンの端面に押
圧するようにしたことを特徴とするラジアルタービンの
可変ノズル。 ５）特許請求の範囲第１項または第２項に記載のラジア
ルタービンの可変ノズルにおいて、前記環状溝はその底
部の周方向等分の位置にビンを摺動自在に保持する孔を
有し、該孔に設けたばねＫより前記ピンを介して前記可
動壁部材を前記ノズルベーンの端面に押圧させるように
したことを特徴とするラジアルタービンの可変ノズル。 リ　特許請求の範囲第３項に記載のラジアルタービンの
可変ノズルにおいて、前記可動壁部材を、前記ノズル部
の少なくとも上流から供給される作動圧と前記ノズル部
の下流から供給される作動圧との差圧および前記ばねの
ばね力の合力により前記ノズルベーンの端面に押圧させ
るようにしたことを特徴とするラジアルタービンの可変
ノズル。 （以下余白）[Scope of Claims] 1) A variable nozzle for a radial turbine in which a nozzle part is formed between the housing walls at the inlet of the turbine rotor, and a plurality of rotatable nozzle vanes are arranged in the nozzle part, wherein one of the nozzle parts an annular groove is formed in the housing wall surface of the housing, a movable wall member is slidably fitted in the annular groove in the axial direction of the turbine rotor, and the movable wall member is moved by at least one of a spring and an operating pressure of the turbine rotor. A variable nozzle for a radial turbine, characterized in that the variable nozzle is pressed against an end face of the nozzle vane. 2. The variable nozzle for a radial turbine according to claim 1, wherein the movable wall member is pressed against the end surface of the nozzle vane by the operating pressure upstream of the nozzle part. Variable nozzle of the turbine. 5) In the variable nozzle for a radial turbine according to claim 1 or 2, the annular groove has holes for slidably holding bottles at positions equidistant in the circumferential direction of the annular groove, A variable nozzle for a radial turbine, characterized in that a spring K provided in the hole presses the movable wall member against the end face of the nozzle vane via the pin. (2) In the variable nozzle for a radial turbine according to claim 3, the movable wall member is configured to operate between a working pressure supplied from at least upstream of the nozzle part and a working pressure supplied from downstream of the nozzle part. A variable nozzle for a radial turbine, characterized in that the end face of the nozzle vane is pressed by the resultant force of the differential pressure and the spring force of the spring. (Margin below)
JP59030304A 1984-02-22 1984-02-22 Variable nozzle of Radiator bottle Expired - Lifetime JPH0610403B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP59030304A JPH0610403B2 (en) 1984-02-22 1984-02-22 Variable nozzle of Radiator bottle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP59030304A JPH0610403B2 (en) 1984-02-22 1984-02-22 Variable nozzle of Radiator bottle

Publications (2)

Publication Number Publication Date
JPS60175707A true JPS60175707A (en) 1985-09-09
JPH0610403B2 JPH0610403B2 (en) 1994-02-09

Family

ID=12300011

Family Applications (1)

Application Number Title Priority Date Filing Date
JP59030304A Expired - Lifetime JPH0610403B2 (en) 1984-02-22 1984-02-22 Variable nozzle of Radiator bottle

Country Status (1)

Country Link
JP (1) JPH0610403B2 (en)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5564895A (en) * 1995-04-26 1996-10-15 Rotoflow Corporation Active automatic clamping control
GB2347973A (en) * 1999-03-11 2000-09-20 Ishikawajima Harima Heavy Ind Gas sealing apparatus for variable capacity supercharger.
EP1111196A3 (en) * 1999-12-21 2002-07-24 DaimlerChrysler AG Variable guide vane system for the turbine of a turbocharger
WO2004027218A1 (en) * 2002-09-18 2004-04-01 Honeywell International Inc. Turbocharger having variable nozzle device
EP1420152A2 (en) * 2002-11-18 2004-05-19 BorgWarner Turbo Systems GmbH Turbocharger
DE10237413B4 (en) * 2002-08-16 2004-07-15 Daimlerchrysler Ag Exhaust gas turbocharger for an internal combustion engine
WO2004083606A1 (en) * 2003-03-21 2004-09-30 Honeywell International Inc. Swinging vane concept for vnt turbochargers
WO2004099573A1 (en) * 2003-05-08 2004-11-18 Honeywell International Inc. Turbocharger with a variable nozzle device
WO2006015613A1 (en) * 2004-08-12 2006-02-16 Honeywell International Inc. Turbocharger
WO2006131724A1 (en) * 2005-06-07 2006-12-14 Cummins Turbo Technologies Limited Variable geometry turbine
EP1900908A2 (en) * 2006-09-12 2008-03-19 Iveco Motorenforschung AG Variable geometry turbine
JP2008546939A (en) * 2005-06-07 2008-12-25 カミンズ・ターボ・テクノロジーズ・リミテッド Variable vane turbine
EP2171219A2 (en) * 2007-06-26 2010-04-07 BorgWarner Inc. Variable geometry turbocharger
EP2233718A1 (en) * 2007-12-12 2010-09-29 IHI Corporation Turbocharger
CN109983204A (en) * 2016-11-18 2019-07-05 液化空气(中国)投资有限公司 The low friction inlet nozzle of turbo-expander
EP3530881A1 (en) * 2018-02-27 2019-08-28 Cummins Ltd Variable geometry turbine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FI127077B (en) * 2016-04-19 2017-10-31 Evac Oy A method for controlling a vacuum system and a vacuum system

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS55161001U (en) * 1979-05-09 1980-11-19
JPS59192603U (en) * 1983-06-07 1984-12-21 三菱重工業株式会社 Radial flow fluid machine with variable guide vanes

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS55161001U (en) * 1979-05-09 1980-11-19
JPS59192603U (en) * 1983-06-07 1984-12-21 三菱重工業株式会社 Radial flow fluid machine with variable guide vanes

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5769602A (en) * 1995-04-26 1998-06-23 Rotoflow Corporation Active automatic clamping control
US5564895A (en) * 1995-04-26 1996-10-15 Rotoflow Corporation Active automatic clamping control
GB2347973A (en) * 1999-03-11 2000-09-20 Ishikawajima Harima Heavy Ind Gas sealing apparatus for variable capacity supercharger.
GB2347973B (en) * 1999-03-11 2003-01-08 Ishikawajima Harima Heavy Ind Variable capacity supercharger having a gas sealing apparatus
EP1111196A3 (en) * 1999-12-21 2002-07-24 DaimlerChrysler AG Variable guide vane system for the turbine of a turbocharger
DE10237413B4 (en) * 2002-08-16 2004-07-15 Daimlerchrysler Ag Exhaust gas turbocharger for an internal combustion engine
WO2004027218A1 (en) * 2002-09-18 2004-04-01 Honeywell International Inc. Turbocharger having variable nozzle device
EP1420152A2 (en) * 2002-11-18 2004-05-19 BorgWarner Turbo Systems GmbH Turbocharger
EP1420152A3 (en) * 2002-11-18 2006-07-19 BorgWarner Turbo Systems GmbH Turbocharger
WO2004083606A1 (en) * 2003-03-21 2004-09-30 Honeywell International Inc. Swinging vane concept for vnt turbochargers
WO2004099573A1 (en) * 2003-05-08 2004-11-18 Honeywell International Inc. Turbocharger with a variable nozzle device
US7794200B2 (en) * 2003-05-08 2010-09-14 Honeywell International, Inc. Turbocharger with a variable nozzle device
WO2006015613A1 (en) * 2004-08-12 2006-02-16 Honeywell International Inc. Turbocharger
JP2008546939A (en) * 2005-06-07 2008-12-25 カミンズ・ターボ・テクノロジーズ・リミテッド Variable vane turbine
US8172516B2 (en) 2005-06-07 2012-05-08 Cummins Turbo Technologies Limited Variable geometry turbine
WO2006131724A1 (en) * 2005-06-07 2006-12-14 Cummins Turbo Technologies Limited Variable geometry turbine
JP4885949B2 (en) * 2005-06-07 2012-02-29 カミンズ・ターボ・テクノロジーズ・リミテッド Variable vane turbine
EP1900908A2 (en) * 2006-09-12 2008-03-19 Iveco Motorenforschung AG Variable geometry turbine
EP1900908A3 (en) * 2006-09-12 2011-09-28 Iveco Motorenforschung AG Variable geometry turbine
EP2171219A2 (en) * 2007-06-26 2010-04-07 BorgWarner Inc. Variable geometry turbocharger
EP2171219A4 (en) * 2007-06-26 2013-08-14 Borgwarner Inc Variable geometry turbocharger
EP2233718A1 (en) * 2007-12-12 2010-09-29 IHI Corporation Turbocharger
EP2233718A4 (en) * 2007-12-12 2011-08-03 Ihi Corp Turbocharger
CN109983204A (en) * 2016-11-18 2019-07-05 液化空气(中国)投资有限公司 The low friction inlet nozzle of turbo-expander
JP2019533117A (en) * 2016-11-18 2019-11-14 レール・リキード−ソシエテ・アノニム・プール・レテュード・エ・レクスプロワタシオン・デ・プロセデ・ジョルジュ・クロード Low friction inlet nozzle for turbo expander
US11143053B2 (en) * 2016-11-18 2021-10-12 L'Air Liquide, Société Anonyme pour l'Etude et l'Exploitation des Procédés Georges Claude Low friction inlet nozzle for a turbo expander
EP3530881A1 (en) * 2018-02-27 2019-08-28 Cummins Ltd Variable geometry turbine
US11162380B2 (en) 2018-02-27 2021-11-02 Cummins Ltd. Variable geometry turbine

Also Published As

Publication number Publication date
JPH0610403B2 (en) 1994-02-09

Similar Documents

Publication Publication Date Title
JPS60175707A (en) Variable nozzle of radial turbine
KR101240109B1 (en) Exhaust-gas-turbine casing
JP6331736B2 (en) Variable nozzle unit and variable capacity turbocharger
JP6542246B2 (en) Variable displacement turbocharger
WO2012036122A1 (en) Fixed vane-type turbo charger
US20140321990A1 (en) Turbocharger
EP1233147A2 (en) Gas turbine with cooling arrangement
US11578645B2 (en) Valve system
JPH0696988B2 (en) Method and apparatus for improving engine cooling
JPS59138728A (en) External shaft support type exhaust turbo over-feeder equipped with non-cooling gas passage
JP2001355737A (en) Surface trailing brush seal
JP2016507695A (en) Active clearance control system by suction
CN109154231B (en) Variable capacity turbocharger
WO2019220112A1 (en) Vanes and shrouds for a turbo-machine
JP4371610B2 (en) Steam turbine sealing equipment
JP6684698B2 (en) Turbocharger
EP3179069B1 (en) Exhaust bypass valve of multi-stage turbocharger
CA1149181A (en) Ceramic duct system for turbine engine
JP2006200413A (en) Variable displacement turbocharger
US11697997B2 (en) Vanes and shrouds for a turbo-machine
CN105736126B (en) Exhaust turbine assembly
JP6089791B2 (en) Variable nozzle unit and variable capacity turbocharger
JP3310906B2 (en) Seal structure between gas turbine disks
JPS6229632Y2 (en)
JPS6244096Y2 (en)