JPS5987203A - Stationary blade structure of axial flow-type fluid machine - Google Patents
Stationary blade structure of axial flow-type fluid machineInfo
- Publication number
- JPS5987203A JPS5987203A JP57197486A JP19748682A JPS5987203A JP S5987203 A JPS5987203 A JP S5987203A JP 57197486 A JP57197486 A JP 57197486A JP 19748682 A JP19748682 A JP 19748682A JP S5987203 A JPS5987203 A JP S5987203A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- divided
- split
- fixed
- section
- 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.)
- Pending
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
- F01D17/162—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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Hydraulic Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【発明の詳細な説明】
〔発明の利用分野〕
本発明は軸流形流体機械の静翼構造に係９、特に次段動
翼への流入角の調整が可能な静翼構造に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Application of the Invention] The present invention relates to a stator vane structure for an axial flow type fluid machine, and particularly to a stator vane structure capable of adjusting an inflow angle to a next-stage rotor blade.
軸流形流体機械において、静翼を、その取付軸を中心に
回転させ、次段動翼への流れの流入角を広い作動流量範
囲において調整することは従来から行われている。とこ
ろで、軸流形流体機械においては、動翼の半径方向の周
速の違いから、一般には半径方向に速度五角形が異なる
。従って、前記流体機械の運転点によって、静翼を回転
させ次段動翼への流入角のマツチングを図る場合も、半
径方向の速度三角形の分布を考慮するのがよシ好ましい
。BACKGROUND ART In axial flow type fluid machines, it has been conventionally practiced to rotate a stator vane around its mounting axis to adjust the inflow angle of a flow to a next-stage rotor blade over a wide operating flow rate range. By the way, in an axial fluid machine, the speed pentagons generally differ in the radial direction due to the difference in the circumferential speed of the rotor blades in the radial direction. Therefore, when rotating the stationary blades and matching the inflow angle to the next-stage rotor blade depending on the operating point of the fluid machine, it is preferable to consider the distribution of velocity triangles in the radial direction.
しかし、前記の従来技術は、単に静莢を回転させるもの
でろるから、次段動翼における半径方向の速度三角形の
分布を考慮した流入角度調整を行うことは困難である。However, since the above-mentioned conventional technology simply rotates the static pod, it is difficult to adjust the inflow angle in consideration of the distribution of velocity triangles in the radial direction in the next-stage rotor blade.
また、特公昭３４−１２４１号公報において、静翼を半
径方向に三分割し、各分割翼を軸周りに別個に回転させ
うるようにした静翼構造が開示されているが、これは各
分割風がそれぞれ独立して回転するものであるから、各
分割翼の制御が難しい問題がある。Furthermore, Japanese Patent Publication No. 34-1241 discloses a stator blade structure in which a stator blade is divided into three parts in the radial direction, and each divided blade can be rotated separately around an axis. Since each wind rotates independently, it is difficult to control each divided wing.
本発明の目的Ｖよ、従来技術の問題点を解消し、次段ｍ
Ｊ典における生仏方向の速度三角形の分布を考１帳した
流入角度調整が可能で、しかも静翼の制御が容易な軸流
形流体機械の静翼構造を提供することにある。Objective V of the present invention is to solve the problems of the prior art and to
It is an object of the present invention to provide a stator vane structure for an axial flow type fluid machine, which allows the inflow angle to be adjusted taking into consideration the distribution of velocity triangles in the direction of the flow in the J standard, and which allows easy control of the stator vanes.
この目的を達成するだめに、本発明の軸流形流体機械の
静翼構造は、静ｇが前翼部と後翼部とに分割され、その
前翼部はケーシングに固定されると共に、ｒｉｌＪ、％
都と後興部との間には、ケーシングに固定した固定軸が
設けられ、前記後呉部は半径方向に複数に分割され、そ
の各分割翼はそれぞれ前記固定！１１１１に、固定軸周
りに回転可能に連結され、かつ最外側の分割翼は駆動部
に連結され、各分割翼の互に対向する面は、その一方に
設けた突起と、他方の而に設けた前記突起を嵌合する溝
とによりそれぞれ係合され、前記溝は、前記突起を設け
た側の分割翼が固定軸周りに回転する際、突起の運動方
向にあそびを有して成る、ことを特徴とする。In order to achieve this objective, the stator blade structure of the axial flow fluid machine of the present invention is such that the static g is divided into a front wing section and a rear wing section, the front wing section is fixed to the casing, and ,%
A fixed shaft fixed to the casing is provided between the capital and the rear part, and the rear part is divided into a plurality of parts in the radial direction, each of which has a fixed shaft fixed to the casing. 1111 is rotatably connected around a fixed axis, and the outermost divided blade is connected to a drive part, and the mutually opposing surfaces of each divided blade have a protrusion provided on one side and a protrusion provided on the other side. and grooves into which the protrusions are fitted, and the grooves have a play in the direction of movement of the protrusions when the split wing on the side where the protrusions are provided rotates around a fixed axis. It is characterized by
以下、本発明の一実施例を図面に従って説明する。第１
図は本発明による静翼構造を軸流圧縮機に適用した縦断
面図で、１は内側ケーシング、２は外側ケーシング、３
は静翼、４は動翼、ｆは主流の流れ方向を示し７ている
。前記静翼３は、前翼部３１と後諷部３２とに分割され
ていると共に、両翼部の間には、上下端を内外ケーシン
グに固定した固定軸５が配設されている。前記前翼部３
１はケーシングに固定され、前記後諷部３２は半径方向
に６分割されていて、各分割ｇ３２ａ、３２ｂ。An embodiment of the present invention will be described below with reference to the drawings. 1st
The figure is a longitudinal sectional view of the stator vane structure according to the present invention applied to an axial flow compressor, in which 1 is the inner casing, 2 is the outer casing, and 3 is the outer casing.
7 indicates the stationary blade, 4 indicates the rotor blade, and f indicates the flow direction of the main flow. The stationary blade 3 is divided into a front wing part 31 and a rear wing part 32, and a fixed shaft 5 whose upper and lower ends are fixed to the inner and outer casings is disposed between the two wing parts. The front wing section 3
1 is fixed to the casing, and the rear part 32 is divided into six in the radial direction, each divided into six parts g32a and 32b.
３２ｃ、３２ｄ、３２ｅ、３２ｆは、後述する構造によ
って前記固定軸５に、固定軸５周わりに回転できるよう
に連結されている。まだ最外側の分割翼３２ａは、その
上面に外側ケーシング２を貫通して駆動部（図示せず）
に連結する軸６を具えている。また各分割翼の互に対向
する面は、後述する構造によシ係合されている。32c, 32d, 32e, and 32f are connected to the fixed shaft 5 by a structure described later so as to be rotatable around the fixed shaft 5. The outermost split wing 32a has a drive section (not shown) that penetrates the outer casing 2 on its upper surface.
The shaft 6 is connected to the shaft 6. Further, the mutually opposing surfaces of each divided wing are engaged with a structure to be described later.
第２図ないし第４図は各分割翼を固定軸５に連結する構
造を示し、各分割翼には固定軸５を挿通させたアーム７
がそれぞれ設けられている。このアーム７は、固定軸５
の挿通部において大径部７ａと小径部７ｂとを有してい
る。そして互に隣り合うアーム７の大径部７ａと小径部
７ｂとの間には、焼バメによシ固定軸５に嵌着したスペ
ーサ８がそれぞれ介在されて、各アーム７の間隔が保た
れている、つ−１，ｂ各分割諷の固定軸方向の位置決め
がなされている。前記スペーサ８の外径は、アーム７の
小径部７ｂの外径と同径に形成されていると共に、中間
部外周に鍔８ａを有している。Figures 2 to 4 show a structure in which each split wing is connected to a fixed shaft 5, and each split wing has an arm 7 through which the fixed shaft 5 is inserted.
are provided for each. This arm 7 has a fixed shaft 5
The insertion portion has a large diameter portion 7a and a small diameter portion 7b. Spacers 8 fitted onto the fixed shafts 5 by shrink fitting are interposed between the large diameter portions 7a and small diameter portions 7b of the arms 7 adjacent to each other, so that the distance between the arms 7 is maintained. The positioning of each of the divisions 1 and 2b in the direction of the fixed axis is performed. The outer diameter of the spacer 8 is formed to be the same as the outer diameter of the small diameter portion 7b of the arm 7, and has a flange 8a on the outer periphery of the intermediate portion.
そしてスペーサ８の鍔８ａとアーム７の大径部７ａとの
間には、スペーサ８とアーム７の小径部７ｂに亘って外
嵌する可変リング９がそれぞれ介在されている。この可
変リング９は、温度によって形状が変化する形状記憶合
金によって作られている。この実施例におけるｉ’Ｔ変
リング９は、通常状態ではスペーサ８とアーム７の小径
部７ｂとにきつく嵌着するような形状となっているが、
導線ｉを通じて通電され該可変リング９自体の電気抵抗
により温度が高くなると、形状変化して可変リング９と
スペーサ８及びアーム７の小径部７ｂとの間に隙間を形
成するようになっている。つまり、各分割翼の固定１１
１Ｉ５周わりの回転を許容する。A variable ring 9 is interposed between the collar 8a of the spacer 8 and the large diameter portion 7a of the arm 7, and is fitted over the spacer 8 and the small diameter portion 7b of the arm 7. This variable ring 9 is made of a shape memory alloy whose shape changes depending on temperature. The i'T deformation ring 9 in this embodiment has a shape that fits tightly into the spacer 8 and the small diameter portion 7b of the arm 7 in the normal state.
When electricity is applied through the conductor i and the temperature rises due to the electric resistance of the variable ring 9 itself, the shape changes and a gap is formed between the variable ring 9, the spacer 8, and the small diameter portion 7b of the arm 7. In other words, the fixed 11 of each split wing
Allows rotation of about 1I5 rotations.
尚、前記の構造において、可変リング９に通１厩する際
、スペー′す８、アーム７等に電流が流れるのを防ぐた
め、可変リング９と接する部分に不導体コーティング１
０が施される。In the above structure, in order to prevent current from flowing through the space 8, arm 7, etc. when passing through the variable ring 9, a non-conductor coating 1 is applied to the portion in contact with the variable ring 9.
0 is applied.
第５図ないし第８図は各分割ν茎の対向面を係合させる
構造を示し、第５図は第１図のＸ−Ｘ矢視図、第６図は
その正面図、第７図は第１図のＹ −Ｘ矢視図、第８図
はその正面図を示している。分割翼３２ｂのＦ面には突
起１１が突設され、分割翼３２ｃの上面には前記突起１
１を嵌合する溝１２が設けられている。この溝１２は、
分割翼３２ｂが固定軸５周わりに回転する際、突起１１
の運転方向に適宜のあそびを有している。また、分割翼
３２ａと分割翼３２ｂ１分割ＩＫ３２Ｃと分割翼３２ｄ
１分割翼３２ｄと分割翼３２ｅ１分割Ｒ３ｚ ｅと分割
翼３２ｆの各対向する而も前記と同様にそれぞれ突起と
溝とにより係合されている。5 to 8 show the structure for engaging the opposing surfaces of each divided ν stalk, FIG. 5 is a view taken along the line X-X in FIG. 1, FIG. 6 is a front view thereof, and FIG. 7 is a FIG. 1 shows a Y-X arrow view, and FIG. 8 shows a front view thereof. A protrusion 11 is provided on the F side of the split wing 32b, and the protrusion 11 is provided on the upper surface of the split wing 32c.
1 is provided with a groove 12 into which it fits. This groove 12 is
When the split wing 32b rotates around the fixed shaft 5, the protrusion 11
It has an appropriate play in the driving direction. In addition, the divided blade 32a, the divided blade 32b1, the divided IK32C, and the divided blade 32d.
The opposing portions of the one-segment wing 32d, the one-segment wing 32e, the one-segment R3z e, and the split wing 32f are also engaged by projections and grooves, respectively, in the same manner as described above.
また分割翼３２ｆにおいては、第３図に示した如く分割
翼３２ｆＦ而に設けた突起１１が固定軸５の取１；１台
１３に設けた溝１２に嵌合することにより、該取付台１
３に係合している。In addition, in the split wing 32f, as shown in FIG.
3 is engaged.
従って、分割Ｊ’（３２ａが軸６を介して駆動部により
回転させられると、その分割ｇ３２ａの回転運動が前記
突起１１及び溝１２を介して分割す８３２ｂ、３２ｃ・
・・の順に他の分割具に順次伝達される。また分割翼３
２ａの回転運動が他の分割翼に伝達される際、突起１１
を嵌合する溝１２は、突起１１の運動方向にあそびを有
しているため、回転運動の回転角度がずれて伝達される
。即ち、後翼部３２が固定軸５周わりに回転する際、分
割翼３２ａの回転角度が１番犬きく分割具３２ｆの回転
角度が１番小さくなる。Therefore, when the division J' (32a) is rotated by the drive unit via the shaft 6, the rotational movement of the division G32a is caused by the divisions 832b, 32c, and
... is sequentially transmitted to other dividing tools. Also split wing 3
When the rotational movement of 2a is transmitted to other divided wings, the projection 11
Since the groove 12 into which the projection 11 is fitted has a play in the movement direction of the protrusion 11, the rotation angle of the rotation movement is transmitted with a deviation. That is, when the rear wing portion 32 rotates around the fixed shaft 5, the rotation angle of the split wing 32a is the smallest, and the rotation angle of the split tool 32f is the smallest.
ここで、分割ｇ３２ｂ及び分割に３２Ｃを例にとって第
９図によシ説明すると、分割翼３２ｂが回転運動全始め
る前の状態では第９図（ａ）のように分割具３２ｂと分
割翼３２Ｃとは重なっており、分割５１２ｂが回転運動
を始めた直後では第９図（ｂ）のように突起１１が溝１
２のあそびの中を動くだめ分割具３２Ｃは回転し２ない
。そしてム１９図（Ｃ）のように分割％３２ｂの突起１
１が分割翼３２Ｃの溝１２の端部に当接すると分割Ｒ３
２Ｃが回転運動を始める。その結果、分割１”ｔ ３２
ｂの回転角度は分割具３２ｃの回転角度よりも犬きく
なる。Here, an explanation will be given with reference to FIG. 9, taking the division g32b and the division 32C as an example. In the state before the division blade 32b starts its full rotational movement, the division tool 32b and the division blade 32C are separated as shown in FIG. 9(a). are overlapping, and immediately after the division 512b starts rotating, the protrusion 11 overlaps the groove 1 as shown in FIG. 9(b).
The divider 32C, which moves in the play of 2, does not rotate. Then, as shown in Figure 19 (C), protrusion 1 of division % 32b
1 comes into contact with the end of the groove 12 of the split blade 32C, the split R3
2C starts rotating. As a result, the division 1”t 32
The rotation angle b is greater than the rotation angle of the dividing tool 32c.
しかるに本発明による静Ｓへ構造においては、軸流圧縮
機の運転点によって、静翼３における後翼部３１が回転
［１Ｉ１１１５周わりに回転する除、その各分割翼の回
転角度は分割翼３２ａで最も太きく、分割ｇ３２ｆで最
も小さくなる。即ち、次段動翼４の半径方向の速度巳角
形の分布を考慮した適切な流入角度が実現することにな
る。その結果、軸流圧縮機の適正作動流量範囲の拡大、
サージマージンの拡大を図れる。また、前記の流入角度
は、後翼部３１の分割翼３２ａを回転させるだけで得ら
れるから、その制御もきわめて容易である。However, in the static S structure according to the present invention, depending on the operating point of the axial flow compressor, the rear blade portion 31 of the stator blade 3 rotates [1I1115], but the rotation angle of each divided blade is equal to the rotation angle of the divided blade 32a. It is the thickest and the smallest at division g32f. In other words, an appropriate inflow angle is realized that takes into account the distribution of the velocity angle in the radial direction of the next-stage rotor blade 4. As a result, the proper operating flow range of axial flow compressors has been expanded,
Surge margin can be expanded. Further, since the above-mentioned inflow angle can be obtained by simply rotating the divided blades 32a of the rear wing section 31, its control is also extremely easy.
尚、本実施例においては、後翼部３２を６分割した例全
示したが、次段動翼４における半径方向のＡＢ Ｉｉ三
角形の分布にマツチングした流入角ＩＩが得られれば列
分割してもよい。In this embodiment, all examples are shown in which the rear blade section 32 is divided into six, but if an inflow angle II that matches the distribution of AB Ii triangle in the radial direction in the next stage rotor blade 4 is obtained, it can be divided into rows. Good too.
以」二説明し７たように、本発明（よれば、次段動翼に
おける半径方向の速度二角形の分布を考慮した流入角度
調整が可能とな９、しかも静翼の制御を容易に行える。As explained above, according to the present invention, it is possible to adjust the inflow angle in consideration of the radial velocity diagonal distribution in the next stage moving blade, and the stator blade can be easily controlled. .
図面は本発明の一実施例を示し、第１図は本発明による
静置構造を軸流圧縮機に適用した縦断面図、第２図は分
割翼を固定軸に連結する構造を７ｊ＜す外観斜視図、第
３図は第２図の縦断面図、第４図は第３図のＡ部拡大図
、第５図は第１図のＸ −Ｘ矢視図、第６図はその正面
図、第７図は第１図のＹ−Ｘ矢視図、第８図はその正面
図、第９図は分割翼における回転運動の伝達の様子を模
式的に示す図である。
１・・・内側ケーシング、２・・・外側ケーシング、３
・・・静翼、４・・・動翼、５・・・固定軸、６・・・
軸、３１・・・静翼の前興部、３２・・・静翼の後翼部
、３２ａ〜３２ｆ・・・後翼部の分割具。
箭 １ ｎ
ｌ
冨 ？ 図
ｆＪＪ 図
冨 ４ 図The drawings show an embodiment of the present invention, and FIG. 1 is a longitudinal cross-sectional view of a stationary structure according to the present invention applied to an axial flow compressor, and FIG. Exterior perspective view, Figure 3 is a vertical cross-sectional view of Figure 2, Figure 4 is an enlarged view of section A in Figure 3, Figure 5 is a view taken along arrow X-X in Figure 1, and Figure 6 is its front view. 7 is a view along the Y-X arrow in FIG. 1, FIG. 8 is a front view thereof, and FIG. 9 is a diagram schematically showing how rotational motion is transmitted in the split blade. 1...Inner casing, 2...Outer casing, 3
... Stationary blade, 4... Moving blade, 5... Fixed shaft, 6...
Shaft, 31... Forward part of stator blade, 32... Rear wing part of stator blade, 32a to 32f... Divider of rear wing part. Bamboo 1 nl Tomi ? Figure fJJ Figure 4
Claims (1)
翼部とに分割され、その前翼部はケーシングに固定され
ると共に、前翼部と後翼部との間には、ケーシングに固
定した固定軸が設けられ、前記後翼部は半径方向に複数
に分割され、その各分割翼はそれぞれ前記固定軸に、固
定軸周シに回転可能に連結−，５ｇ、かつ最外側の分割
翼は駆動部に連結され、各分割翼の互に対向する面は、
その一方に設けた突起と、他方の面に設けた前記突起を
嵌合する溝とによりそれぞれ係合され、前記溝は、前記
突起を設けた側の分割翼が固定軸周りに回転する際、突
起の運動方向にあそびを有して成る、ことを特徴とする
軸流形流体機械の静翼構造。In a stator vane for an axial flow fluid machine, the stator vane is divided into a front wing section and a rear wing section, the front wing section is fixed to a casing, and there is a space between the front wing section and the rear wing section. , a fixed shaft fixed to the casing is provided, the rear wing section is divided into a plurality of parts in the radial direction, and each of the divided wings is rotatably connected to the fixed shaft and the fixed shaft periphery. The outer divided blades are connected to the drive part, and the mutually opposing surfaces of each divided blade are
The protrusions provided on one side are engaged with the grooves provided on the other surface into which the protrusions fit, and when the split wing on the side provided with the protrusions rotates around a fixed axis, the grooves are engaged with each other. A stationary vane structure for an axial flow fluid machine, characterized in that the protrusion has a play in the direction of movement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57197486A JPS5987203A (en) | 1982-11-12 | 1982-11-12 | Stationary blade structure of axial flow-type fluid machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57197486A JPS5987203A (en) | 1982-11-12 | 1982-11-12 | Stationary blade structure of axial flow-type fluid machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS5987203A true JPS5987203A (en) | 1984-05-19 |
Family
ID=16375268
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP57197486A Pending JPS5987203A (en) | 1982-11-12 | 1982-11-12 | Stationary blade structure of axial flow-type fluid machine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5987203A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1172006A (en) * | 1997-08-28 | 1999-03-16 | General Electric Co <Ge> | Variable area turbine nozzle segment |
| US20120039706A1 (en) * | 2009-02-19 | 2012-02-16 | Mtu Aero Engines Gmbh | Compressor having a guide vane assembly with a radially variable outflow |
| JP2016191382A (en) * | 2016-05-31 | 2016-11-10 | ボルボ ラストバグナー アーベー | Device for controlling gas flow, exhaust post-processing system and system for forwarding vehicle |
| US11970948B2 (en) | 2022-08-09 | 2024-04-30 | Pratt & Whitney Canada Corp. | Variable vane airfoil with airfoil twist to accommodate protuberance |
-
1982
- 1982-11-12 JP JP57197486A patent/JPS5987203A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1172006A (en) * | 1997-08-28 | 1999-03-16 | General Electric Co <Ge> | Variable area turbine nozzle segment |
| US20120039706A1 (en) * | 2009-02-19 | 2012-02-16 | Mtu Aero Engines Gmbh | Compressor having a guide vane assembly with a radially variable outflow |
| JP2016191382A (en) * | 2016-05-31 | 2016-11-10 | ボルボ ラストバグナー アーベー | Device for controlling gas flow, exhaust post-processing system and system for forwarding vehicle |
| US11970948B2 (en) | 2022-08-09 | 2024-04-30 | Pratt & Whitney Canada Corp. | Variable vane airfoil with airfoil twist to accommodate protuberance |
| EP4332347A3 (en) * | 2022-08-09 | 2024-05-01 | Pratt & Whitney Canada Corp. | Variable vane airfoil with airfoil twist to accommodate protuberance |
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