JPS60132099A - centrifugal compressor - Google Patents
centrifugal compressorInfo
- Publication number
- JPS60132099A JPS60132099A JP58237919A JP23791983A JPS60132099A JP S60132099 A JPS60132099 A JP S60132099A JP 58237919 A JP58237919 A JP 58237919A JP 23791983 A JP23791983 A JP 23791983A JP S60132099 A JPS60132099 A JP S60132099A
- Authority
- JP
- Japan
- Prior art keywords
- guide vanes
- closing member
- impeller
- centrifugal compressor
- flow
- 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
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 239000012530 fluid Substances 0.000 description 8
- 238000010586 diagram Methods 0.000 description 3
- 238000013459 approach Methods 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002265 prevention Effects 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
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- 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
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
- F04D29/464—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps adjusting flow cross-section, otherwise than by using adjustable stator blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
〔発明の利用分野〕
(1)
本発明はターボ冷凍機などに用いられる羽根付きディフ
ューザを備える遠心圧縮機、特にその羽根付きディフュ
ーザの構造に関するものである。DETAILED DESCRIPTION OF THE INVENTION [Field of Application of the Invention] (1) The present invention relates to a centrifugal compressor equipped with a vaned diffuser used in a turbo refrigerator, etc., and particularly to the structure of the vaned diffuser.
従来の典型的な遠心圧縮機は第1図および第2図に示す
ように、羽根車1から吐出される流体の流れ2の運動エ
ネルギを効率的に圧力エネルギに変換させるため、相対
向して設けた側壁間に案内羽根3を円形状に配列してな
る羽根付きディフューザ3を羽根車1の吐出側(下流側
)に、がっ羽根車1の外周側に設けた構造からなり、相
隣る案内羽根4,4間には、ディフューザ流路5が形成
され、これらの各流路5内を流体が矢印6方向に流れて
いる。このような周知の圧縮機では、低流量の稼動条件
のもとでサージング現象を生ずるため、性能が大幅に低
下し、極端な場合には正常な運転が不能となる恐れがあ
る。As shown in FIGS. 1 and 2, a typical conventional centrifugal compressor has two compressors facing each other in order to efficiently convert the kinetic energy of a fluid flow 2 discharged from an impeller 1 into pressure energy. It has a structure in which a vaned diffuser 3 in which guide vanes 3 are arranged in a circular shape between the provided side walls is provided on the discharge side (downstream side) of the impeller 1, and on the outer peripheral side of the impeller 1. A diffuser flow path 5 is formed between the guide vanes 4, 4, and fluid flows in each of these flow paths 5 in the direction of the arrow 6. In such known compressors, surging occurs under low flow operating conditions, resulting in a significant reduction in performance, and in extreme cases, normal operation may become impossible.
次に上記サージング現象を説明の便宜上、第3図に示す
ようにディフューザの案内羽根4のうち相隣る二枚の案
内羽根4a、4bについて説明す(2)
る。Next, for convenience of explanation of the surging phenomenon, two adjacent guide vanes 4a and 4b of the guide vanes 4 of the diffuser as shown in FIG. 3 will be described (2).
案内羽根4a、4bに吹き付ける羽根車(図示せず)の
吐出流により、案内羽根4aの流路5aに面した側8は
圧力面となり、案内羽根4bの流路5aに面した側9は
負圧面となる。案内羽根4a、4b付近に生ずる流体的
現象は第4図および第5図に示すとおりであり、第4図
は設計値に近い流量で正常に作動している状態を、第5
図は比較的に小流量でディフューザの失速が生じている
状態をそれぞれ示す。Due to the discharge flow from an impeller (not shown) blowing onto the guide vanes 4a and 4b, the side 8 of the guide vane 4a facing the flow path 5a becomes a pressure surface, and the side 9 of the guide vane 4b facing the flow path 5a becomes a negative pressure surface. It becomes a pressure surface. The fluid phenomena that occur near the guide vanes 4a and 4b are as shown in FIGS. 4 and 5, and FIG.
The figures each show a state in which the diffuser stalls at a relatively small flow rate.
第4図および第5図において、案内羽根4aと4bの前
縁7aと7bとを結ぶ線BCを考えると、この線BCは
図示付近における羽根車(図示せず)の接線と近似的に
平行になると見なしうる。図中の矢印11a、llbは
案内羽根4−a、4bに吹きつけられる羽根車の吐出流
をそれぞれ示し、一点鎖線12a、12bはそれぞれ案
内羽根4a。4 and 5, considering the line BC connecting the leading edges 7a and 7b of the guide vanes 4a and 4b, this line BC is approximately parallel to the tangent to the impeller (not shown) in the vicinity of the illustration. It can be considered that Arrows 11a and llb in the figure indicate the impeller discharge flows blown onto the guide vanes 4-a and 4b, respectively, and dash-dotted lines 12a and 12b indicate the guide vanes 4a, respectively.
4bの反り線である。4b is the warp line.
設計点では第4図に示すように、吐出流11bと近似接
線BCとのなす角δ、は、反り線12b(3)
と近似接線BCとのなす角δ2に近づく。これらの角δ
1とδ2の差δ、が小さな値となるように案内羽根4
bを配設すれば、前記差δ、は小さな値であるため、吐
出流体は流路5aを充満して流れるので、ディフューザ
は所定の性能を発揮するから、圧縮機は正常な運転を行
うことが可能である。At the design point, as shown in FIG. 4, the angle δ between the discharge flow 11b and the approximate tangent line BC approaches the angle δ2 between the warp line 12b(3) and the approximate tangent line BC. These angles δ
Guide vane 4 is set so that the difference δ between 1 and δ2 is a small value.
If b is provided, the difference δ is a small value, so the discharged fluid flows filling the flow path 5a, the diffuser exhibits the specified performance, and the compressor can operate normally. is possible.
この正常状態における羽根車の回転数を保った状態で流
量を減少させると、羽根車の吐出流々速の接線方向成分
はほとんど変らず、半径方向成分は減少するので、流れ
11.’ a、11’ bは第5図に示すように近似接
線BCの方向に近接した方向になる。したがって、流れ
11’ a、11’ bと近似接線BCとのなす角は、
反り線12a。If the flow rate is reduced while maintaining the rotational speed of the impeller in this normal state, the tangential component of the impeller's discharge flow velocity will hardly change, and the radial component will decrease, so the flow 11. 'a, 11' b is in a direction close to the direction of the approximate tangent line BC, as shown in FIG. Therefore, the angle between the flows 11'a, 11'b and the approximate tangent line BC is:
Curved line 12a.
12bと近似接線BCとのなす角よりもδ8だけ小さく
なる。この62の値が案内羽根4a、4bの形状と配置
により決定される限界値より大きいと、流れ11′ b
は案内羽根4bの負圧面9に沿って流れないため、大規
模な剥離流れ領域13が発生する。12b and the approximate tangent BC by δ8. If this value of 62 is larger than the limit value determined by the shape and arrangement of the guide vanes 4a, 4b, the flow 11' b
does not flow along the negative pressure surface 9 of the guide vane 4b, so a large-scale separated flow region 13 occurs.
(4)
この剥離流れ領域13は案内羽根4bの負圧面だけでな
く、ディフューザを構成している案内羽根の大部分ない
し全部について発生し、十分な圧力上昇かえられなくな
ってサージング現象を発生する。このようなサージング
現象を防止するため、一般に第6図に示すように案内羽
根4を羽根車1の回転軸14に平行な支持軸15を中心
として、矢印D−E方向に回動させる手段が実施されて
いる。(4) This separated flow region 13 occurs not only on the negative pressure surface of the guide vane 4b, but also on most or all of the guide vanes constituting the diffuser, and a sufficient pressure increase is not achieved and a surging phenomenon occurs. In order to prevent such a surging phenomenon, there is generally a means for rotating the guide vanes 4 in the direction of arrow D-E about a support shaft 15 parallel to the rotation axis 14 of the impeller 1, as shown in FIG. It has been implemented.
ところが、上記手段によれば、全部の案内羽根4を駆動
させるために、支持軸15を駆動させる機構が大形とな
り、ディフューザ装置全体も大型化するばかりでなく、
重量化するからコスト高となる。また、全部の案内羽根
4を回動させるので、その案内羽根4の側面と、これに
対向するケーシング面との間の隙間より比較的に多量の
流体が漏洩するから、遠心圧縮機の正常作動時の性能が
低下する欠点がある。However, according to the above means, in order to drive all the guide vanes 4, the mechanism for driving the support shaft 15 becomes large, and the entire diffuser device also becomes large.
The weight increases, which increases the cost. In addition, since all the guide vanes 4 are rotated, a relatively large amount of fluid leaks from the gap between the side surface of the guide vane 4 and the casing surface facing it, so that the centrifugal compressor can operate normally. The disadvantage is that the performance at times deteriorates.
本発明は上記にかんがみ簡単な構造により小流(5)
量運転時にサージング現象の発生するのを防止し、圧縮
機の効率を向上させることを目的とするものである。In view of the above, it is an object of the present invention to prevent the occurrence of surging phenomenon during small flow (5) operation using a simple structure, and to improve the efficiency of the compressor.
本発明は上記目的を達成するために、公知の羽根付きデ
ィフューザを備える遠心圧縮機において、前記ディフュ
ーザの一方側々壁に閉鎖部材を軸方向に移動可能に埋設
し、小流量運転時に前記閉鎖部材を案内羽根間の流路内
または案内羽根の入口側周方向または出口側周方向に進
出させることにより、前記流路を部分的に閉塞するよう
にしたことを特徴とするものである。In order to achieve the above object, the present invention provides a centrifugal compressor equipped with a known bladed diffuser, in which a closing member is embedded in one side wall of the diffuser so as to be movable in the axial direction, and the closing member is provided during low flow rate operation. This is characterized in that the flow path is partially blocked by advancing into the flow path between the guide vanes or in the circumferential direction on the inlet side or the circumferential direction on the outlet side of the guide vanes.
以下、本発明の実施例について説明する。 Examples of the present invention will be described below.
第7図および第8図において、1は回転軸14に取付け
られた羽根車、16は一方側(図では左側)のディフュ
ーザ側壁18に設けた溝19内に、支持棒17を介して
軸方向に移動可能に収納された閉鎖部材、20a〜2O
nは羽根車1の外周側に、かつ相対向するディフューザ
側壁18.18(6)
間に円形状に配列された任意数の案内羽根である。In FIGS. 7 and 8, 1 is an impeller attached to a rotating shaft 14, and 16 is inserted into a groove 19 provided in a diffuser side wall 18 on one side (the left side in the figure) through a support rod 17 in the axial direction. Closing members movably housed in, 20a to 20
n is an arbitrary number of guide vanes arranged in a circular shape on the outer peripheral side of the impeller 1 and between the opposing diffuser side walls 18, 18 (6).
次に上記のような構成からなる本実施例の作用について
説明する。Next, the operation of this embodiment configured as described above will be explained.
圧縮機を大流量で運転する場合には、閉鎖部材16は第
7図の実線で示すように、ディフューザ側壁18に設け
た溝19内に収納されているので、羽根車1から吐出さ
れた流体の流れ2は、案内羽根20a〜2Onの相隣る
案内羽根間の流路21を充満して流れる。逆に圧縮機を
小流量で運転する場合には、閉鎖部材16は支持棒17
により軸方向(図では右方向)に移動し、第7図の一点
鎖風で示すように案内羽根20aと20b (図示せず
)との間の流路21の入口部21aを部分的に閉塞する
。すなわち、第8図に示すように閉鎖部材16と案内羽
根20a、20bとの間に、狭小流路22a、22bが
それぞれ形成されるので、羽根車1から吐出された流体
の流れは、前記狭小流路22a、22bを矢印で示すよ
うに流通する。When the compressor is operated at a large flow rate, the closing member 16 is housed in a groove 19 provided in the diffuser side wall 18, as shown by the solid line in FIG. The flow 2 flows filling the flow path 21 between adjacent guide vanes of the guide vanes 20a to 2On. Conversely, when the compressor is operated at a small flow rate, the closing member 16 is connected to the support rod 17.
moves in the axial direction (to the right in the figure), and partially blocks the inlet part 21a of the flow path 21 between the guide vanes 20a and 20b (not shown), as shown by the one-point chain in Figure 7. do. That is, as shown in FIG. 8, narrow channels 22a and 22b are formed between the closing member 16 and the guide vanes 20a and 20b, so that the flow of fluid discharged from the impeller 1 is limited to the narrow channels 22a and 22b, respectively. The fluid flows through the flow paths 22a and 22b as shown by arrows.
上記狭小流路22a、22bは、所要の小流量が流通す
るのに必要なだけの幅を有するように形(7)
成されているので、逆流を生ずることはないから圧縮機
がサージング現象を起す恐れはない。耐記狭小流路22
a、22bを入口側(羽根車1側)から出口側(反羽根
車側)に至るにしたがって拡大する。換言すれば羽根車
1から遠ざかるとしたがって拡大するように形成すれば
、羽根車1から吐出された流体の流れが有する運動エネ
ルギの一部を圧力に変換することができるから、圧縮機
の効率をより一層に向上させることが可能である利点が
ある。The narrow flow passages 22a and 22b are shaped (7) to have the width necessary for the required small flow rate to flow, so that no backflow occurs and the compressor does not suffer from the surging phenomenon. There is no fear of it happening. Narrow passage 22
a and 22b are enlarged from the inlet side (impeller 1 side) to the outlet side (counter-impeller side). In other words, if the impeller is formed so that it expands as it moves away from the impeller 1, part of the kinetic energy of the fluid flow discharged from the impeller 1 can be converted into pressure, thereby increasing the efficiency of the compressor. There is an advantage that it can be further improved.
第9図に示す第2実施例は、前記閉鎖部材16を案内羽
根20により形成される多数の流路21の一部、すなわ
ち偶数番目または奇数番目の流路に設けたものである。In the second embodiment shown in FIG. 9, the closing member 16 is provided in a part of a large number of channels 21 formed by guide vanes 20, that is, in an even-numbered channel or an odd-numbered channel.
このように構成すれば、流量制御性能は第1実施例(第
8図)に比べて劣るが、構造を簡易化することができる
長所がある。With this configuration, although the flow rate control performance is inferior to that of the first embodiment (FIG. 8), it has the advantage of simplifying the structure.
第10図に示す第3実施例は、長い案内羽根2OLと短
かい案内羽根20Mとを組合せて配列し、短かい案内羽
根20Mの入口側に周方向に長い閉鎖部材16Aを配列
したものである。このよ(8)
うに構成すれば、閉鎖部材の数を減少して構造をさらに
簡易化することができる利点がある。In the third embodiment shown in FIG. 10, a long guide vane 2OL and a short guide vane 20M are arranged in combination, and a circumferentially long closing member 16A is arranged on the inlet side of the short guide vane 20M. . This configuration (8) has the advantage that the number of closing members can be reduced and the structure can be further simplified.
第11図に示す第4実施例は、閉鎖部材16を案内羽根
20の入口側周方向、すなわち案内羽根20の内周側に
配列し、相隣る閉業部材16゜16間の間隙23を小流
量運転時の流路としたちまである。このように構成すれ
ば、案内羽根20と閉鎖部材16の相対寸法の精度は厳
格でなくてもよい利点がある。In the fourth embodiment shown in FIG. 11, the closing members 16 are arranged in the circumferential direction on the inlet side of the guide vanes 20, that is, on the inner circumferential side of the guide vanes 20, and the gap 23 between the adjacent closing members 16° 16 is reduced. There is a flow path and a chittle during flow rate operation. With this configuration, there is an advantage that the accuracy of the relative dimensions of the guide vane 20 and the closing member 16 does not have to be strict.
第12図に示す第5実施例は、閉鎖部材16を案内羽根
20の出口側周方向、すなわち案内羽根2Oの外周側に
配列したものである。このように構成すれば、第4実施
例と同様に案内羽根20と閉鎖部材16の相対寸法の精
度は厳格でなくてもよい利点がある。In the fifth embodiment shown in FIG. 12, the closing members 16 are arranged in the circumferential direction on the outlet side of the guide vanes 20, that is, on the outer circumferential side of the guide vanes 2O. With this configuration, there is an advantage that the accuracy of the relative dimensions of the guide vane 20 and the closing member 16 does not have to be strict, as in the fourth embodiment.
以上説明したように、本発明によれば、簡単な構造によ
り小流量運転時にサージング現象の発生するのを防止し
、圧縮機の効率を向上させることができる。As described above, according to the present invention, the simple structure can prevent the surging phenomenon from occurring during low flow rate operation and improve the efficiency of the compressor.
(9)(9)
第1図は瑛型的な遠心圧縮機の断面図、第2図は第1図
のA−A矢視図、第3図は第2図の案内羽根部分の一部
拡大図、第4図および第5図は作動説明図、第6図は従
来のサージング防止手段の概略図、第7図は本発明の遠
心圧縮機の一実施例を示す要部断面図、第8図は第7図
のB−B矢視図、第9図ないし第12図は本発明に係わ
る他の実施例の要部を示す図である。
1・・・羽根車、16.16A・・・閉鎖部材、18・
・・ディフューザ側壁、19・・・溝、20.20a〜
20n。
20L、20M−・・案内羽根、21−・・流路、21
a(10)
第1図
AA
−i
■ 2 図
b
第 6 図
・〆〈\4
特開昭GO−132099(5)
fJ7 図
、′&−−− ’<i〜/へ、
・ノ
第9図
2ρ
築 tθ 図
′I!1間昭GO−132099(6)第 11 図
篤 /Z 図
*≦幌Σい6\
6
/
74禿−崖りFigure 1 is a cross-sectional view of a centrifugal compressor, Figure 2 is a view taken along the line A-A in Figure 1, Figure 3 is a partially enlarged view of the guide vane in Figure 2, and Figure 4. 5 is an explanatory diagram of the operation, FIG. 6 is a schematic diagram of a conventional surging prevention means, FIG. 7 is a sectional view of a main part showing an embodiment of the centrifugal compressor of the present invention, and FIG. The BB arrow view and FIGS. 9 to 12 are diagrams showing essential parts of other embodiments of the present invention. 1... Impeller, 16.16A... Closing member, 18.
...Diffuser side wall, 19...Groove, 20.20a~
20n. 20L, 20M--Guide vane, 21--Flow path, 21
a(10) Fig. 1 AA -i ■ 2 Fig. b Fig. 6・〆〈\4 JP-A-132099 (5) fJ7 Fig., '&---'<i~/to, ・ノ9th Figure 2ρ construction tθ Figure'I! 1. Sho GO-132099 (6) No. 11 Figure Atsushi /Z Figure *≦Top Σ 6\ 6 / 74 Bald - Cliff
Claims (1)
る羽根付きディフューザを羽根車の外周側に設けた遠心
圧縮機において、前記側壁の一方側に閉鎖部材を軸方向
に移動可能に埋設し、小流量運°転時に前記閉鎖部材を
案内羽根間の流路内または案内羽根の入口側周方向また
は出[1側局方向に進出させることにより、前記流路を
部分的に閉塞するようにしたことを特徴とする遠心圧縮
機。 2、上記閉鎖部材の進出状態における閉鎖部材と案内羽
根との間または閉鎖部材の相互間にそれぞれ形成される
流路を、羽根車から遠ざかるにしたがって拡大するよう
に形成したことを特徴とする特許請求の範囲第1項記載
の遠心圧縮機。[Scope of Claims] 1. A centrifugal compressor in which a vaned diffuser having guide vanes arranged in a circular shape between opposing side walls is provided on the outer peripheral side of the impeller, and a closing member is provided on one side of the side wall. The closing member is buried so as to be movable in the axial direction, and when operating at a small flow rate, the closing member is advanced into the flow path between the guide vanes or in the circumferential direction on the inlet side of the guide vanes or in the direction toward the first side. A centrifugal compressor characterized by being partially blocked. 2. A patent characterized in that the flow paths formed between the closing member and the guide vane or between the closing members in the extended state of the closing member are formed so as to expand as they move away from the impeller. A centrifugal compressor according to claim 1.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP58237919A JPS60132099A (en) | 1983-12-19 | 1983-12-19 | centrifugal compressor |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP58237919A JPS60132099A (en) | 1983-12-19 | 1983-12-19 | centrifugal compressor |
Publications (1)
Publication Number | Publication Date |
---|---|
JPS60132099A true JPS60132099A (en) | 1985-07-13 |
Family
ID=17022387
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP58237919A Pending JPS60132099A (en) | 1983-12-19 | 1983-12-19 | centrifugal compressor |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPS60132099A (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7326027B1 (en) * | 2004-05-25 | 2008-02-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Devices and methods of operation thereof for providing stable flow for centrifugal compressors |
JP2009068431A (en) * | 2007-09-13 | 2009-04-02 | Ihi Corp | Pipe diffuser type centrifugal compressor |
WO2012140509A3 (en) * | 2011-04-12 | 2013-01-03 | Toyota Jidosha Kabushiki Kaisha | Compressor |
JP2014114727A (en) * | 2012-12-07 | 2014-06-26 | Mitsubishi Heavy Ind Ltd | Centrifugal compressor |
CN113586504A (en) * | 2020-04-30 | 2021-11-02 | 特灵国际有限公司 | Interstage flow control valve for bypass flow distribution and regulation of multistage centrifugal compressor |
US11536277B2 (en) | 2020-04-30 | 2022-12-27 | Trane International Inc. | Interstage capacity control valve with side stream flow distribution and flow regulation for multi-stage centrifugal compressors |
US11841026B2 (en) | 2021-11-03 | 2023-12-12 | Trane International Inc. | Compressor interstage throttle, and method of operating therof |
EP4336050A1 (en) * | 2022-09-12 | 2024-03-13 | Hamilton Sundstrand Corporation | Variable pipe diffuser |
-
1983
- 1983-12-19 JP JP58237919A patent/JPS60132099A/en active Pending
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7326027B1 (en) * | 2004-05-25 | 2008-02-05 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Devices and methods of operation thereof for providing stable flow for centrifugal compressors |
JP2009068431A (en) * | 2007-09-13 | 2009-04-02 | Ihi Corp | Pipe diffuser type centrifugal compressor |
WO2012140509A3 (en) * | 2011-04-12 | 2013-01-03 | Toyota Jidosha Kabushiki Kaisha | Compressor |
JP2014114727A (en) * | 2012-12-07 | 2014-06-26 | Mitsubishi Heavy Ind Ltd | Centrifugal compressor |
CN104838149A (en) * | 2012-12-07 | 2015-08-12 | 三菱重工业株式会社 | Centrifugal compressor |
EP3904691A1 (en) * | 2020-04-30 | 2021-11-03 | Trane International Inc. | Interstage capacity control valve with side stream flow distribution and flow regulation for multi stage centrifugal compressors |
CN113586504A (en) * | 2020-04-30 | 2021-11-02 | 特灵国际有限公司 | Interstage flow control valve for bypass flow distribution and regulation of multistage centrifugal compressor |
US11391289B2 (en) | 2020-04-30 | 2022-07-19 | Trane International Inc. | Interstage capacity control valve with side stream flow distribution and flow regulation for multi-stage centrifugal compressors |
US11536277B2 (en) | 2020-04-30 | 2022-12-27 | Trane International Inc. | Interstage capacity control valve with side stream flow distribution and flow regulation for multi-stage centrifugal compressors |
US11661949B2 (en) | 2020-04-30 | 2023-05-30 | Trane International Inc. | Interstage capacity control valve with side stream flow distribution and flow regulation for multi-stage centrifugal compressors |
US11859621B2 (en) | 2020-04-30 | 2024-01-02 | Trane International Inc. | Interstage capacity control valve with side stream flow distribution and flow regulation for multi-stage centrifugal compressors |
US11841026B2 (en) | 2021-11-03 | 2023-12-12 | Trane International Inc. | Compressor interstage throttle, and method of operating therof |
EP4336050A1 (en) * | 2022-09-12 | 2024-03-13 | Hamilton Sundstrand Corporation | Variable pipe diffuser |
US12135039B2 (en) | 2022-09-12 | 2024-11-05 | Hamilton Sundstrand Corporation | Variable pipe diffuser |
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