JPH01305134A - Nozzle setting mechanism of gas turbine - Google Patents
Nozzle setting mechanism of gas turbineInfo
- Publication number
- JPH01305134A JPH01305134A JP1097678A JP9767889A JPH01305134A JP H01305134 A JPH01305134 A JP H01305134A JP 1097678 A JP1097678 A JP 1097678A JP 9767889 A JP9767889 A JP 9767889A JP H01305134 A JPH01305134 A JP H01305134A
- Authority
- JP
- Japan
- Prior art keywords
- lever
- ball joint
- nozzle
- connecting rod
- control ring
- 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
- 230000007812 deficiency Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
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
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Support Of The Bearing (AREA)
Abstract
Description
【発明の詳細な説明】
ノズルの対応シャンクに剛に取付けたレバーの全部を単
一の制御リングに接続する連結棒の有効長を適宜な長さ
に容易に変えて隣接ノズルのベーンによって画成される
チャンネルの流れ面積を厳密に一定とするように前記ノ
ズルを正しい位置に設定することを可能とする、新規な
小型の丈夫な機構に関する。DETAILED DESCRIPTION OF THE INVENTION The effective length of a connecting rod connecting all of the levers rigidly attached to the corresponding shanks of the nozzles to a single control ring can be easily varied to the appropriate length defined by the vanes of adjacent nozzles. The present invention relates to a novel compact and robust mechanism that allows the nozzle to be set in the correct position so as to have a strictly constant flow area of the channel.
指向方向調節可能のノズルをそなえたガスタービンにお
いては、これらノズルのシャンクに剛に取付けたレバー
に連結ロッドで組立時に接続した単一の制御リングによ
って同時に作動せしめられるのが一般である。このよう
な組立体が完成した時、隣接ノズルのベーン間の間隙に
よって画成される流れ面積は全体にわたって一定でなけ
ればならない。従ってまた、不可避的に生ずる製造公差
によるアンバランスを補償するようなやり方で各個のノ
ズルを正規位置に設定することができなければならない
。Gas turbines with directional nozzles are typically operated simultaneously by a single control ring connected during assembly by a connecting rod to a lever rigidly mounted on the shank of the nozzle. When such an assembly is completed, the flow area defined by the gaps between the vanes of adjacent nozzles should be constant throughout. It must therefore also be possible to set each individual nozzle in its normal position in such a way as to compensate for unbalances due to unavoidable manufacturing tolerances.
当業界の現在の技術レベルでは、このような位置設定は
、各連結ロッドの長さを変えることにより、すなわち連
結ロッドを制御リングに枢着する点とこれを各ノズルの
レバーに枢着する点との問の距離を変えることにより行
っている。これは、それぞれ右ねじおよび左ねじを有す
るねじ端部をそなえ、ここに連結ロッドのふたつの鳩目
部分をねじ込むようにした中間スリーブを用いて行なっ
ている。この連結ロッドの長さは、この中間スリーブを
ねじ込む程度を変えて一方向または他方向の角移動を、
対応するレバーに従ってこのレバーと一体のノズルに伝
達せしめて、これを、タービンケーシング内に収容され
ている軸受によって支持されているそのシャフトを中心
として回動せしめることによって変更せしめられる。At the current state of the art in the industry, such positioning is accomplished by varying the length of each connecting rod, i.e. by pivoting the connecting rod to the control ring and pivoting it to the lever of each nozzle. This is done by changing the distance between the questions. This is accomplished by using an intermediate sleeve with threaded ends, each with a right-hand thread and a left-hand thread, into which the two eyelets of the connecting rod are screwed. The length of this connecting rod allows for angular movement in one direction or the other by varying the degree to which this intermediate sleeve is threaded.
The nozzle integrated with this lever is transmitted in accordance with the corresponding lever and is changed by rotating it about its shaft, which is supported by a bearing housed in the turbine casing.
しかしながらガスタービンの指向方向調節可能のノズル
を正規位置に設定するこの型式の既知機構は重大な欠陥
を有するものである。すなわち連結ロッドが必然的に小
型で特別の形状のものとなるので、破損ことにノズルが
故障で動かなくなった時に破損するなど非常に弱いもの
であった。これに加えて、中間スリーブが必要であるた
めに連結ロッドの全体が大きなものとなり、指向方向調
節可能のノズルを多数有するこの種タービンにおいては
特に致命的な欠点となっていた。However, this type of known mechanism for setting the orientable nozzle of a gas turbine in the correct position has serious deficiencies. In other words, since the connecting rod is necessarily small and has a special shape, it is extremely vulnerable to damage, such as damage when the nozzle stops working due to a failure. In addition, the need for an intermediate sleeve increases the overall size of the connecting rod, which is a particularly fatal drawback in this type of turbine having a large number of nozzles whose pointing direction can be adjusted.
本発明の目的は、全体の嵩を増さずに、しかも連結ロッ
ドを弱体化することなくこれらを丈夫で小型のものとし
、その上効率よく信頼性ありしかも作動がじん速である
、ガスタービンの指向方向調節可能ノズルを正規位置に
設定する機構を提供することにより、前述の従来の欠点
を克服することにある。The object of the present invention is to provide a gas turbine which is strong and compact without increasing the overall bulk and without weakening the connecting rods, and which is efficient, reliable and operates at high speed. The object of the present invention is to overcome the above-mentioned disadvantages of the prior art by providing a mechanism for setting an adjustable pointing nozzle in the correct position.
このことは、各ノズルを正規位置に設定するための前述
の回動を、各連結ロッドが制御リングおよびノズルのレ
バーにそれぞれ枢着する点の間の距離を偏心ピンによっ
て変えることによって行なうことにより実質的に達成す
ることができる。This is achieved by effecting the aforementioned rotation for setting each nozzle in its normal position by varying the distance between the points at which each connecting rod pivots on the control ring and the lever of the nozzle, respectively, by means of an eccentric pin. substantially achievable.
すなわち本発明は、ガスタービンの指向方向調節可能の
ノズルを正規位置に設定する機構であって、前記ノズル
のそれぞれが、タービンケーシング内に収容された軸受
によって回動可能に支持されると共に、シャンクに直交
して配設され連結ロンドにより単一の制御リングに接続
されて全部を同時に作動せしめられるレバーに剛に取付
けられている機構において、前記連結ロッドのそれぞれ
が、玉継手により前記制御リングに接続されると共に、
別の玉継手によって前記ノズルのレバーに接続されてお
り、後者の玉継手の偏心率がキーによって調整できるよ
うにしたことを特徴とする機構にある。That is, the present invention provides a mechanism for setting the nozzles of a gas turbine whose directivity can be adjusted to a normal position, in which each of the nozzles is rotatably supported by a bearing housed in a turbine casing, and the shank is rotatably supported. in a mechanism rigidly attached to levers disposed orthogonally to the control ring and connected by connecting rods to a single control ring, all actuated simultaneously, each of said connecting rods being connected to said control ring by a ball joint. Along with being connected,
The mechanism is characterized in that it is connected to the lever of the nozzle by another ball joint, and the eccentricity of the latter ball joint can be adjusted by means of a key.
以下、添付図面に例示した本発明の好適な実施例につい
て本発明を詳述する。The present invention will now be described in detail with reference to preferred embodiments thereof, as illustrated in the accompanying drawings.
図面において、符号１はガスタービンの指向方向調節可
能のノズルのひとつを示すものである。In the drawings, reference numeral 1 designates one of the nozzles of the gas turbine whose pointing direction can be adjusted.
このノズル！のシャンク２は、タービンケーシング４内
に収容された軸受３により回動可能に支持されている。This nozzle! The shank 2 is rotatably supported by a bearing 3 housed within a turbine casing 4.
このシャンク２はこれと直交して配設されたレバー５の
一端部に剛に取付けである。This shank 2 is rigidly attached to one end of a lever 5 disposed perpendicularly thereto.
レバー５の他端部にはフォーク６が形成されており、こ
こに連結ロッド８の鳩目部分７が挿置しである。この、
鳩目部分７は玉継手９によりレバー５に接続しである。A fork 6 is formed at the other end of the lever 5, into which an eyelet portion 7 of a connecting rod 8 is inserted. this,
The eyelet part 7 is connected to the lever 5 by a ball joint 9.
玉継手９は偏心率ｅのカム１１を包含するピンｌＯによ
り正規位置に保持されている。The ball joint 9 is held in position by a pin lO containing a cam 11 with eccentricity e.
このカム１１の姿勢は、この目的のため空所１２内に挿
入されるアレンキー（Ａｌｉｅｎ ｋｅｙ）により調節
することができる。The position of this cam 11 can be adjusted by means of an Alien key inserted into the cavity 12 for this purpose.
鳩目部分７と直交して配設された連結ロッド８の他端の
鳩目部分１３は、玉継手１４によって単一の制御リング
１５に接続されている。この制御リング１５は玉継手１
４を固定する貫通孔１６を有するものである。The eyelet section 13 at the other end of the connecting rod 8, which is arranged orthogonally to the eyelet section 7, is connected by a ball joint 14 to a single control ring 15. This control ring 15 is connected to the ball joint 1
It has a through hole 16 for fixing 4.
以上本発明を、添付図面に例示したその好適な実施例に
ついて詳述したが、本発明はこの特定の実施例に限定さ
れるものではなく、本発明の精神を逸脱しないで幾多の
変化変形が行なえることはもちろんである。Although the present invention has been described in detail with respect to the preferred embodiment thereof illustrated in the accompanying drawings, the present invention is not limited to this specific embodiment, and many changes and modifications may be made without departing from the spirit of the invention. Of course it can be done.
図面はガスタービンの指向方向調節可能のノズルを正規
位置に設定するための本発明機構の好適な一実施例を一
部切り欠いて示す斜視図セある。The drawing is a perspective view, partially cut away, of a preferred embodiment of the mechanism of the present invention for setting an adjustable nozzle of a gas turbine in its normal position.
Claims (1)
設定する機構であって、前記ノズルのそれぞれが、ター
ビンケーシング内に収容された軸受によって回動可能に
支持されると共に、シャンクに直交して配設され連結ロ
ッドにより単一の制御リングに接続されて全部を同時に
作動せしめられるレバーに剛に取付けられている機構に
おいて、前記連結ロッドのそれぞれが、玉継手により前
記制御リングに接続されると共に、別の玉継手によって
前記ノズルのレバーに接続されており、後者の玉継手の
偏心率がキーによって調整できるようにしたことを特徴
とする機構。A mechanism for setting directionally adjustable nozzles of a gas turbine in a normal position, each of the nozzles being rotatably supported by a bearing housed in a turbine casing and disposed orthogonally to a shank. a mechanism rigidly attached to the levers provided and connected by connecting rods to a single control ring, all actuated simultaneously, each of said connecting rods being connected to said control ring by a ball joint; A mechanism characterized in that it is connected to the lever of the nozzle by a further ball joint, the eccentricity of the latter ball joint being adjustable by means of a key.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IT20272/88A IT1217437B (en) | 1988-04-21 | 1988-04-21 | IMPROVED SYSTEM OF ADJUSTMENT OF THE ADJUSTABLE NOZZLES OF A GAS TURBINE IN POSITION |
| IT20272A/88 | 1988-04-21 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH01305134A true JPH01305134A (en) | 1989-12-08 |
| JP2864127B2 JP2864127B2 (en) | 1999-03-03 |
Family
ID=11165325
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1097678A Expired - Lifetime JP2864127B2 (en) | 1988-04-21 | 1989-04-19 | Gas turbine nozzle setting mechanism |
Country Status (7)
| Country | Link |
|---|---|
| JP (1) | JP2864127B2 (en) |
| CA (1) | CA1333695C (en) |
| CH (1) | CH675748A5 (en) |
| DE (1) | DE3913195A1 (en) |
| FR (1) | FR2630498B1 (en) |
| GB (1) | GB2217790B (en) |
| IT (1) | IT1217437B (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3771765B2 (en) * | 2000-01-24 | 2006-04-26 | 三菱重工業株式会社 | Variable turbocharger |
| DE10035762A1 (en) * | 2000-07-22 | 2002-01-31 | Daimler Chrysler Ag | Turbocharger for motor vehicle internal combustion engine has vanes to adjust flow through turbine and vary flow cross section |
| DE10238413A1 (en) * | 2002-08-22 | 2004-03-04 | Volkswagen Ag | Turbocharger with variable turbine geometry |
| FR2879695B1 (en) * | 2004-12-16 | 2007-04-06 | Snecma Moteurs Sa | DEVICE FOR CONNECTING ADJUSTABLE LENGTH BETWEEN TWO PIECES |
| US7594794B2 (en) * | 2006-08-24 | 2009-09-29 | United Technologies Corporation | Leaned high pressure compressor inlet guide vane |
| GB2470586A (en) * | 2009-05-29 | 2010-12-01 | Rolls Royce Plc | Eccentric joint for actuator connection rod. |
| US8714916B2 (en) * | 2010-09-28 | 2014-05-06 | General Electric Company | Variable vane assembly for a turbine compressor |
| US8668444B2 (en) * | 2010-09-28 | 2014-03-11 | General Electric Company | Attachment stud for a variable vane assembly of a turbine compressor |
| EP2594743A1 (en) * | 2011-11-21 | 2013-05-22 | Siemens Aktiengesellschaft | Eccentric diaphragm adjusting pins for a gas turbine engine |
| DE102012206755B4 (en) * | 2012-04-25 | 2022-11-24 | Zf Friedrichshafen Ag | control rod arrangement |
| DE102015213321A1 (en) * | 2015-07-16 | 2017-01-19 | Bosch Mahle Turbo Systems Gmbh & Co. Kg | Variable turbine or compressor geometry for an exhaust gas turbocharger |
| US11486304B2 (en) * | 2017-11-03 | 2022-11-01 | Borgwarner Inc. | Lever with pre-attached self locking nut for a variable turbine geometry turbocharger |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS55134704A (en) * | 1979-04-07 | 1980-10-20 | Mitsui Eng & Shipbuild Co Ltd | Structure for fine adjustment of setting angle of stator blade for furnace-top pressure turbine |
| JPS6052840A (en) * | 1983-09-01 | 1985-03-26 | Fuji Xerox Co Ltd | Device for illuminating original for copying machine |
| JPS6137441A (en) * | 1984-07-31 | 1986-02-22 | Toshiba Corp | High-speed printing processing system of dot printer |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1060663A (en) * | 1952-07-29 | 1954-04-05 | High pressure axial fan | |
| US2933235A (en) * | 1955-01-11 | 1960-04-19 | Gen Electric | Variable stator compressor |
| GB1276720A (en) * | 1969-12-19 | 1972-06-07 | English Electric Co Ltd | Drives to adjustable stator blades for turbomachinery |
| US3949550A (en) * | 1975-03-05 | 1976-04-13 | United Technologies Corporation | Engine exhaust flow diverter |
| US4139329A (en) * | 1977-05-16 | 1979-02-13 | Westinghouse Canada Limited | Vane tip motion transfer device |
-
1988
- 1988-04-21 IT IT20272/88A patent/IT1217437B/en active
-
1989
- 1989-04-12 CH CH1385/89A patent/CH675748A5/it not_active IP Right Cessation
- 1989-04-13 CA CA000596599A patent/CA1333695C/en not_active Expired - Lifetime
- 1989-04-19 GB GB8908878A patent/GB2217790B/en not_active Expired - Lifetime
- 1989-04-19 JP JP1097678A patent/JP2864127B2/en not_active Expired - Lifetime
- 1989-04-21 FR FR8905308A patent/FR2630498B1/en not_active Expired - Lifetime
- 1989-04-21 DE DE3913195A patent/DE3913195A1/en active Granted
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS55134704A (en) * | 1979-04-07 | 1980-10-20 | Mitsui Eng & Shipbuild Co Ltd | Structure for fine adjustment of setting angle of stator blade for furnace-top pressure turbine |
| JPS6052840A (en) * | 1983-09-01 | 1985-03-26 | Fuji Xerox Co Ltd | Device for illuminating original for copying machine |
| JPS6137441A (en) * | 1984-07-31 | 1986-02-22 | Toshiba Corp | High-speed printing processing system of dot printer |
Also Published As
| Publication number | Publication date |
|---|---|
| IT1217437B (en) | 1990-03-22 |
| IT8820272A0 (en) | 1988-04-21 |
| GB2217790B (en) | 1992-07-01 |
| DE3913195C2 (en) | 1991-05-23 |
| GB8908878D0 (en) | 1989-06-07 |
| CA1333695C (en) | 1994-12-27 |
| GB2217790A (en) | 1989-11-01 |
| FR2630498A1 (en) | 1989-10-27 |
| JP2864127B2 (en) | 1999-03-03 |
| CH675748A5 (en) | 1990-10-31 |
| DE3913195A1 (en) | 1989-11-02 |
| FR2630498B1 (en) | 1993-12-24 |
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