JPS63183204A - Stall prevention structure of axial flow rotary device - Google Patents
Stall prevention structure of axial flow rotary deviceInfo
- Publication number
- JPS63183204A JPS63183204A JP1414187A JP1414187A JPS63183204A JP S63183204 A JPS63183204 A JP S63183204A JP 1414187 A JP1414187 A JP 1414187A JP 1414187 A JP1414187 A JP 1414187A JP S63183204 A JPS63183204 A JP S63183204A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- impeller
- passages
- stall prevention
- wall
- 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
- 230000002265 prevention Effects 0.000 title claims abstract description 16
- 239000012530 fluid Substances 0.000 abstract description 9
- 230000000694 effects Effects 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 7
- 230000007423 decrease Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 238000011835 investigation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
- F04D29/526—Details of the casing section radially opposing blade tips
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
（産業上の利用分野）
本発明は、軸流回転装置の失速防止構造に関し、詳しく
は、ボイラ用または換気用軸流送風機、産業用軸流圧縮
機、ガスタービン、航空機用ジェットエンジンのターボ
ファン、軸流型水ポンプ等の軸流回転装置の失速防止構
造に関する。DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a stall prevention structure for an axial flow rotating device, and specifically relates to an axial flow blower for boilers or ventilation, an industrial axial flow compressor, a gas turbine, The present invention relates to a stall prevention structure for axial flow rotating devices such as turbo fans of aircraft jet engines and axial flow water pumps.
（従来の技術）
軸流送風機等において、吐出圧力が許容値を越えたとき
、羽根車の失速により吐出側供給ラインに激しい脈動が
発生し、操業不能に至ることがあり、失速限界の改善が
望まれている。(Prior art) When the discharge pressure of an axial blower exceeds a permissible value, the stall of the impeller causes severe pulsations in the discharge side supply line, which can lead to inoperability, and it is difficult to improve the stall limit. desired.
第７図は従来の軸流送風機の失速防止構造の縦断面図、
第８図は第７図のＦ矢視断面図、第９図は第８図の要部
の平面展開図である。Figure 7 is a vertical cross-sectional view of the stall prevention structure of a conventional axial blower.
FIG. 8 is a sectional view taken along arrow F in FIG. 7, and FIG. 9 is a developed plan view of the main part of FIG.
静止壁ａは、軸流送風機のケーシングｅの羽根車すの翼
先端に対向する部分に装着されていて、羽根車すの回転
方向を矢印Ｒとしたとき、スロットＣが回転方向にスキ
ュード角θ（図では６０°）を持って前傾させるように
静止壁ａの内壁面の円周上に多数穿設され、内部に設け
られたリング状の空洞ｄに連通するよう構成されている
。The stationary wall a is attached to a portion of the casing e of the axial blower that faces the blade tip of the impeller, and when the rotation direction of the impeller is indicated by arrow R, the slot C has a skewed angle θ in the rotation direction. A large number of holes are formed on the circumference of the inner wall surface of the stationary wall a so as to tilt it forward at an angle of 60° (60° in the figure), and it is configured to communicate with a ring-shaped cavity d provided inside.
羽根車すの回転により、空気の主流は第７図に示す矢印
Ｘ方向に圧送される。そして翼先端においては主流の一
部が１つの穴、つまりスロットＣより流入と流出を行う
ようにして失速限界改善を計っている。As the impeller rotates, the main flow of air is forced in the direction of arrow X shown in FIG. At the tip of the blade, a portion of the main flow flows in and out through one hole, that is, slot C, in order to improve the stall limit.
ところで、上記従来例にあっては、失速限界改善という
目的からして、失速防止効果はある程度期待できるもの
の、流体の流れから見た究明が十分なされていないため
、この点改善の余地がある。また、一方では失速防止効
果の向上を計れば計る程送風機としての効率低下をもた
らしており未だ実用化に問題を残しているのが現状であ
る。By the way, in the above conventional example, from the purpose of improving the stall limit, a stall prevention effect can be expected to some extent, but since sufficient investigation from the perspective of fluid flow has not been done, there is room for improvement in this point. On the other hand, the more efforts are made to improve the stall prevention effect, the more the efficiency of the blower decreases, and there are still problems in practical application.
本発明は、以上の如き問題点に鑑みてなされたもので、
その目的は流体の流れについて究明し、より失速防止効
果を向上させ、しかも装置自体のもつ効率の低下を最小
に留めた軸流回転装置の失速防止構造を提供することに
ある。The present invention has been made in view of the above problems.
The objective is to provide a stall prevention structure for an axial flow rotating device that further improves the stall prevention effect by studying fluid flow and minimizes the decrease in efficiency of the device itself.
Ｃ問題点を解決するための手段〕
本発明はケーシングの壁面の羽根車の翼先端に対向する
部分に失速防止のための静止壁を装着した軸流回転装置
において、該静止壁の翼先端に対向する内壁面の円周上
に、流入路を内壁面の翼後縁側に該羽根車の回転方向に
前傾するように多数設けると共に、流出路を内壁面の翼
前縁側に該流入路とは逆方向に傾斜させて多数設け、該
静止壁の内部にリング状の空洞を設け、該空洞に該流入
路および該流出路をそれぞれ連通したことを要旨とする
。Means for Solving Problem C] The present invention provides an axial flow rotating device in which a stationary wall for stall prevention is attached to a portion of the wall surface of the casing that faces the blade tip of the impeller. On the circumference of the opposing inner wall surfaces, a large number of inflow passages are provided on the blade trailing edge side of the inner wall surface so as to be inclined forward in the rotation direction of the impeller, and an outflow passage is provided on the blade leading edge side of the inner wall surface. The gist is that a plurality of the stationary walls are provided tilted in opposite directions, a ring-shaped cavity is provided inside the stationary wall, and the inflow passage and the outflow passage are communicated with the cavity, respectively.
第１−５図を参照しつつ、以下作用について説明する。 The operation will be explained below with reference to FIGS. 1-5.
静止壁９の内壁面の円周上に流入路１０と流出路１１を
設けると共に、内部にリング状の空洞１２を設けて、流
体の局所的な循環流１７を生じさせ、この循環流１７の
作用によって羽根車２の失速、すなわち軸流回転装置の
失速を防止する。An inflow path 10 and an outflow path 11 are provided on the circumference of the inner wall surface of the stationary wall 9, and a ring-shaped cavity 12 is provided inside to generate a local circulation flow 17 of the fluid. This action prevents the impeller 2 from stalling, that is, the axial flow rotating device from stalling.
流入路１０を静止壁９の内壁面のＩＩ縁１４側に配し、
かつ羽根車の回転方向Ｒに前傾させたことにより、主流
と分岐された流れは、翼後縁１４側の圧力面１６から静
止壁９内へ円滑に吸い込まれる。The inflow channel 10 is arranged on the II edge 14 side of the inner wall surface of the stationary wall 9,
In addition, by tilting the impeller forward in the rotational direction R, the flow branched from the main flow is smoothly sucked into the stationary wall 9 from the pressure surface 16 on the blade trailing edge 14 side.
流入路１０を通って吸込まれた流れは、空洞１２内を循
環する。The flow sucked in through the inlet channel 10 circulates within the cavity 12 .
流出路１１を静止壁９内壁面の流入路１０とは逆方向に
傾斜させたことにより、空洞１２内を循環する流れは翼
前縁１３側の負圧面１５に流出し、主流と円滑な合流が
行われるため、流体損失がなく、回転装置自体のもつ効
率低下を最小限に留めることができると共に失速防止の
効果も増大する。By slanting the outflow path 11 in the opposite direction to the inflow path 10 on the inner wall surface of the stationary wall 9, the flow circulating within the cavity 12 flows out to the negative pressure surface 15 on the blade leading edge 13 side, and smoothly merges with the main flow. Since this is performed, there is no fluid loss, and the reduction in efficiency of the rotating device itself can be minimized, and the effect of stall prevention is also increased.
従って、エネルギレベルの高い翼後縁１４側の圧力面１
６の流体の流れが、失速を起し易い男前縁１３側の負圧
面１５に円滑に導かれることにより、回転機械の効率低
下をもたらすことなく、回転機械の失速を効果的に防止
する。Therefore, the pressure surface 1 on the blade trailing edge 14 side where the energy level is high
6 is smoothly guided to the negative pressure surface 15 on the side of the male leading edge 13 where stalling is likely to occur, thereby effectively preventing stalling of the rotating machine without reducing the efficiency of the rotating machine.
以下に、本発明の好適な一実施例を添付図面に基づいて
詳述する。Hereinafter, a preferred embodiment of the present invention will be described in detail with reference to the accompanying drawings.
第１図は本発明に係るボイラ用軸流送風機の概要説明図
、第２−４図は本発明に係る要部の第１実施例の説明図
、第５図は本発明に係る要部の第２実施例の説明図であ
る。Fig. 1 is a schematic explanatory diagram of an axial flow blower for a boiler according to the present invention, Figs. 2-4 are explanatory diagrams of a first embodiment of the main parts according to the present invention, and Fig. 5 is an explanatory diagram of the main parts according to the present invention. It is an explanatory view of a second example.
第１図において、円筒上のケーシング１内に回転可能に
納められた羽根車２は回転軸３により駆動される。羽根
車２の回転により、空気は矢印Ｘで示す如く、上流側に
設けたダクト４から吸入され、出口側ディフューザ５か
ら吐出される。図中、６は案内羽根、１は後置案内羽根
、８は内筒である。なお、以上の構成については公知で
ある。In FIG. 1, an impeller 2 rotatably housed in a cylindrical casing 1 is driven by a rotating shaft 3. As shown in FIG. As the impeller 2 rotates, air is sucked in from the duct 4 provided on the upstream side, as shown by arrow X, and is discharged from the outlet diffuser 5. In the figure, 6 is a guide vane, 1 is a rear guide vane, and 8 is an inner cylinder. Note that the above configuration is publicly known.
本発明は、ケーシング１に装着した静止壁９の構造にあ
る。すなわち、静止壁９は円周２分割し、一体向な筒状
体に構成したものであり、羽根車２の先端の軸方内申よ
りやや広巾の胴長を有し、その内壁面が羽根車２の先端
に対向するようにケーシング１に嵌合するようにして装
着されている。The invention resides in the structure of the stationary wall 9 attached to the casing 1. In other words, the stationary wall 9 is divided into two parts around the circumference and formed into an integral cylindrical body, and has a body length that is slightly wider than the axial inner diameter of the tip of the impeller 2, and its inner wall surface is similar to that of the impeller. It is fitted into the casing 1 so as to face the tip of the casing 2 .
次に静止壁９の詳細について説明する。Next, details of the stationary wall 9 will be explained.
第２図は、本発明の第１実施例に係る要部の縦断面模式
図、第３図は第２図のＧおよびＨ矢視断面図で図の中央
左はＧ矢視、中央布はＨ矢視断面図、第４図は第３図の
平面展開図である。FIG. 2 is a schematic vertical cross-sectional view of the main parts according to the first embodiment of the present invention, and FIG. 3 is a cross-sectional view taken along arrows G and H in FIG. A sectional view taken along arrow H, and FIG. 4 is a developed plan view of FIG. 3.
第２〜４図において、ケーシング１に装置された静止壁
９の内壁面円周上に流入路１０および流出路１１を第２
図に示す如く羽根車２の翼先端に対向する位置に設ける
。流入路１０は流体の流れ方向を矢印Ｘとしたとき、内
壁面の翼後縁１４側に配設し、第３図に示す如く、羽根
車２の回転方向を矢印Ｒとしたとき、回転方向に前傾さ
せてスキュード角約６０°を有するように、またスロッ
ト状に多数穿設されている。また、流出路１１は翼前縁
１３側に配設し、第３図に示す如く上記流入路１０と逆
方向に約６０°傾斜させスロット状に多数穿設されてい
る。リング状の空洞１２が静止壁９の内部に設けられて
おり、流入路１０および流出路１１がそれぞれ空洞１２
に連通されている。In FIGS. 2 to 4, an inflow passage 10 and an outflow passage 11 are formed on the circumference of the inner wall surface of the stationary wall 9 installed in the casing 1.
As shown in the figure, it is provided at a position opposite to the blade tip of the impeller 2. The inflow passage 10 is arranged on the blade trailing edge 14 side of the inner wall surface when the fluid flow direction is indicated by arrow X, and as shown in FIG. It is tilted forward and has a skewed angle of approximately 60 degrees, and is bored in a number of slot shapes. Further, the outflow passage 11 is disposed on the blade leading edge 13 side, and is inclined at an angle of about 60 degrees in the opposite direction to the inflow passage 10, as shown in FIG. A ring-shaped cavity 12 is provided inside the stationary wall 9, and an inflow passage 10 and an outflow passage 11 are respectively connected to the cavity 12.
is communicated with.
なお、１５は負圧面、１６は圧力面、１７は循環流であ
る。Note that 15 is a negative pressure surface, 16 is a pressure surface, and 17 is a circulating flow.
第５図により第２実施例について説明する。A second embodiment will be explained with reference to FIG.
第５図は、前述の第１実施例を示す第２図に代る要部の
縦断面模式図であって、静止壁９の内壁面の円周上に設
ける流入路１０および流出路１１の開口部は出来るだけ
接近させ、反面、空洞１２との連通部では出来るだけ離
反するように構成する。その他流入路１０と流出路１１
にスキュード角を設けること等は前述の第１実施例と同
じであるので説明を省略するが、第２実施例のものは、
第１実施例に比して循環流と主流との分岐および合流に
おける流体力学的特性に優れている。FIG. 5 is a schematic longitudinal cross-sectional view of a main part of the first embodiment described above, in place of FIG. The openings are arranged as close together as possible, while the communication section with the cavity 12 is arranged as far apart as possible. Other inflow path 10 and outflow path 11
Since the provision of a skewed angle is the same as in the first embodiment described above, the explanation will be omitted, but in the second embodiment,
Compared to the first embodiment, this embodiment has excellent hydrodynamic characteristics in branching and merging the circulating flow and the main stream.
第６図は動翼角度可変軸流送風機の特性曲線図で、横軸
に風量 １１ｆ３／ｍｉｎ 、縦軸に全圧上昇ｍｍＡＱ
としたとき、動翼角度を２０°から５５°まで変えた場
合の失速限界を示し、■は従来の静止壁を設けない場合
、■は第７−９図に示した従来例の場合、■は第２〜４
図に示す本発明の第１実施例であって、スキュード角６
０°とした流入路と流出路をもつ静止壁を用いた場合の
失速限界である。Figure 6 is a characteristic curve diagram of a variable rotor blade angle axial flow blower, where the horizontal axis shows the air volume of 11 f3/min, and the vertical axis shows the total pressure increase mmAQ.
, the stall limit is shown when the rotor blade angle is changed from 20° to 55°. are 2nd to 4th
A first embodiment of the invention shown in the figure, with a skewed angle of 6
This is the stall limit when using a stationary wall with an inflow path and an outflow path set to 0°.
一般に失速限界の改善は、送風機の特性曲線によって示
されるが、第６図から明らかなように本発明の失速限界
曲線■は従来の１１１１に比して低風量側に寄り、失速
限界の改善がなされていることがわかる。Generally, the improvement in the stall limit is shown by the characteristic curve of the blower, but as is clear from Fig. 6, the stall limit curve (■) of the present invention is closer to the lower air volume side than the conventional 1111, and the improvement in the stall limit is shown by the characteristic curve of the blower. I can see what is being done.
なお、上記実施例においては、流入路１０のスキュード
角を６０°とした場合について示したがこれに限定され
るものではなく、また流出路１１についても同様に、流
体の流入、流出を円滑にするように、ある傾斜角を有し
ておればよい。In the above embodiment, the skewed angle of the inflow passage 10 is set to 60°, but the skewed angle is not limited to this, and the outflow passage 11 is similarly designed to smoothly inflow and outflow the fluid. It suffices to have a certain angle of inclination so that it does.
その他車発明の要旨を逸脱しない範囲内で変更し得るこ
とは勿論である。Of course, other changes may be made without departing from the gist of the invention.
以上の構成から本発明は次のような優れた効果を発揮す
る。With the above configuration, the present invention exhibits the following excellent effects.
（１）流入路を翼模縁側に、また流出路を翼前縁側に位
置するようにそれぞれ配設したので、流体は翼の圧力面
から流入して、翼の負圧面に流出し、循環流が自然に生
じ失速限界改善の大巾な向上が計れる。(1) Since the inflow channel is located on the blade edge side and the outflow channel is located on the blade leading edge side, fluid flows in from the pressure surface of the blade and flows out to the suction surface of the blade, creating a circulating flow. occurs naturally and can significantly improve the stall limit.
（２）流入路および流出路に相互逆方向のスキュード角
をもたせたので、循環流の主流との分岐および合流を流
体力学的に円滑に行え、流体損失がなく、装置自体のも
つ効率の低下を最小限に留め、かつ失速防止の効果も向
上する。(2) Since the inlet and outlet channels have mutually opposite skewed angles, branching and merging of the circulating flow with the main stream can be done hydrodynamically smoothly, without fluid loss, and reducing the efficiency of the device itself. This also minimizes the impact and improves the effectiveness of stall prevention.
（３）空気、水など全ゆる流体を扱う軸流回転装置に適
用できる。(3) Applicable to axial flow rotating devices that handle all types of fluids such as air and water.
第１図は本発明に係るボイラ用軸流送Ｊ！Ｉｎのａｔ要
説明図、第２図は本発明の第１実施例に係る要部の縦断
面模式図、第３図は第２図のＧおよびＨ矢視断面図、第
４図は第３図の、平面展開図、第５図は本発明の第２実
施例に係る要部の縦断面模式図、第６図は動翼角度可変
軸流送風機の特性曲線図、第７図は従来の失速防止構造
の縦新面図、第８図は第７図のＦ矢視断面図、第９図は
第８図の平面展開図である。
図中、１はケーシング、２は羽根車、３は回転軸、４は
ダクト、５は出口側ディフューザ、６は案内羽根、１は
後置案内羽根、８は内筒、９は静止壁、１０は流入路、
１１は流出路、１２は空洞、１３は翼前縁、１４は翼後
縁、１５は負圧面、１６は圧力面、１７は循環流、矢印
Ｒは羽根車の回転方向、矢印Ｘは流体の流れ方向を示す
。
特許出願人 石川−島１磨重工業株式会社第１図
第２図 第３図
第４図
第５図
第６図
Ｉｌｌ １１FIG. 1 shows the axial flow J! for boilers according to the present invention. 2 is a vertical cross-sectional schematic diagram of the main part according to the first embodiment of the present invention, FIG. 3 is a sectional view taken along arrows G and H in FIG. 2, and FIG. FIG. 5 is a schematic vertical cross-sectional view of the main parts according to the second embodiment of the present invention, FIG. 6 is a characteristic curve diagram of a variable rotor blade angle axial flow blower, and FIG. 7 is a diagram of a conventional axial blower. FIG. 8 is a sectional view taken along the arrow F in FIG. 7, and FIG. 9 is a developed plan view of FIG. 8. In the figure, 1 is a casing, 2 is an impeller, 3 is a rotating shaft, 4 is a duct, 5 is an outlet side diffuser, 6 is a guide vane, 1 is a rear guide vane, 8 is an inner cylinder, 9 is a stationary wall, 10 is the inflow path,
11 is the outflow path, 12 is the cavity, 13 is the leading edge of the blade, 14 is the trailing edge of the blade, 15 is the negative pressure surface, 16 is the pressure surface, 17 is the circulating flow, arrow R is the rotation direction of the impeller, and arrow X is the fluid flow direction. Indicates flow direction. Patent Applicant: Ishikawa Shima Ichima Heavy Industries Co., Ltd. Figure 1 Figure 2 Figure 3 Figure 4 Figure 5 Figure 6 Ill 11
Claims (1)
失速防止のための静止壁を装着した軸流回転装置におい
て、該静止壁の翼先端に対向する内壁面の円周上に、流
入路を内壁面の翼後縁側に該羽根車の回転方向に前傾す
るように多数設けると共に、流出路を内壁面の翼前縁側
に該流入路とは逆方向に傾斜させて多数設け、該静止壁
の内部にリング状の空洞を設け、該空洞に該流入路およ
び該流出路をそれぞれ連通したことを特徴とする軸流回
転装置の失速防止構造。In an axial flow rotating device in which a stationary wall for stall prevention is attached to a portion of the wall surface of the casing facing the blade tip of the impeller, an inflow passage is provided on the circumference of the inner wall surface facing the blade tip of the stationary wall. A large number of outflow passages are provided on the inner wall surface on the blade trailing edge side so as to be inclined forward in the rotation direction of the impeller, and a large number of outflow passages are provided on the inner wall surface on the blade leading edge side so as to be inclined in the opposite direction to the inflow passages, and the stationary wall 1. A stall prevention structure for an axial flow rotating device, characterized in that a ring-shaped cavity is provided inside the cavity, and the inflow passage and the outflow passage are communicated with the cavity, respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1414187A JPS63183204A (en) | 1987-01-26 | 1987-01-26 | Stall prevention structure of axial flow rotary device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1414187A JPS63183204A (en) | 1987-01-26 | 1987-01-26 | Stall prevention structure of axial flow rotary device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS63183204A true JPS63183204A (en) | 1988-07-28 |
Family
ID=11852870
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1414187A Pending JPS63183204A (en) | 1987-01-26 | 1987-01-26 | Stall prevention structure of axial flow rotary device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS63183204A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5474417A (en) * | 1994-12-29 | 1995-12-12 | United Technologies Corporation | Cast casing treatment for compressor blades |
| US5586859A (en) * | 1995-05-31 | 1996-12-24 | United Technologies Corporation | Flow aligned plenum endwall treatment for compressor blades |
| JP2007536459A (en) * | 2004-05-07 | 2007-12-13 | プラット アンド ホイットニー カナダ コーポレイション | Extraction of shock wave induced boundary layer of transonic gas turbine |
| JP2009539015A (en) * | 2006-06-02 | 2009-11-12 | シーメンス アクチエンゲゼルシヤフト | Ring-shaped fluid conduit for fluid machinery in which main flow can flow axially |
| WO2011045975A1 (en) * | 2009-10-16 | 2011-04-21 | 三菱重工業株式会社 | Compressor for exhaust turbo-charger |
| EP2818724A1 (en) * | 2013-06-27 | 2014-12-31 | MTU Aero Engines GmbH | Fluid flow engine, casing treatment and method |
-
1987
- 1987-01-26 JP JP1414187A patent/JPS63183204A/en active Pending
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5474417A (en) * | 1994-12-29 | 1995-12-12 | United Technologies Corporation | Cast casing treatment for compressor blades |
| US5586859A (en) * | 1995-05-31 | 1996-12-24 | United Technologies Corporation | Flow aligned plenum endwall treatment for compressor blades |
| EP0751280A1 (en) * | 1995-05-31 | 1997-01-02 | United Technologies Corporation | Flow aligned plenum endwall treatment for compressor blades |
| JP2007536459A (en) * | 2004-05-07 | 2007-12-13 | プラット アンド ホイットニー カナダ コーポレイション | Extraction of shock wave induced boundary layer of transonic gas turbine |
| JP2009539015A (en) * | 2006-06-02 | 2009-11-12 | シーメンス アクチエンゲゼルシヤフト | Ring-shaped fluid conduit for fluid machinery in which main flow can flow axially |
| WO2011045975A1 (en) * | 2009-10-16 | 2011-04-21 | 三菱重工業株式会社 | Compressor for exhaust turbo-charger |
| US8888440B2 (en) | 2009-10-16 | 2014-11-18 | Mitsubishi Heavy Industries, Ltd. | Compressor of exhaust gas turbocharger |
| EP2818724A1 (en) * | 2013-06-27 | 2014-12-31 | MTU Aero Engines GmbH | Fluid flow engine, casing treatment and method |
| US20150003976A1 (en) * | 2013-06-27 | 2015-01-01 | MTU Aero Engines AG | Turbomachine, circulation structure and method |
| US10151206B2 (en) | 2013-06-27 | 2018-12-11 | MTU Aero Engines AG | Turbomachine, circulation structure and method |
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