CA1252075A - Diffuser construction for a centrifugal compressor - Google Patents
Diffuser construction for a centrifugal compressorInfo
- Publication number
- CA1252075A CA1252075A CA000455551A CA455551A CA1252075A CA 1252075 A CA1252075 A CA 1252075A CA 000455551 A CA000455551 A CA 000455551A CA 455551 A CA455551 A CA 455551A CA 1252075 A CA1252075 A CA 1252075A
- Authority
- CA
- Canada
- Prior art keywords
- diffuser
- plate
- flow path
- centrifugal compressor
- width
- 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.)
- Expired
Links
- 238000010276 construction Methods 0.000 title abstract description 10
- 239000012530 fluid Substances 0.000 claims description 6
- 230000000717 retained effect Effects 0.000 claims description 2
- 125000006850 spacer group Chemical group 0.000 claims description 2
- 238000004891 communication Methods 0.000 abstract description 4
- 230000006854 communication Effects 0.000 abstract description 4
- 230000007423 decrease Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 210000003027 ear inner Anatomy 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000002093 peripheral 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
- F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
- F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/12—Multi-stage pumps
- F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
DIFFUSER CONSTRUCTION FOR A CENTRIFUGAL COMPRESSOR
Abstract of the Disclosure Constant flow width through the last stage diffuser of a centrifugal compressor is maintained against widening by the forces of differential pressure via a diffuser defined between oppositely positioned radial faces of a diaphragm and an annular diffuser plate secured spaced from the diaphragm at the desired with. Enabling the diffuser plate to withstand width deflection and/or enlargement is a pressure balance imposed against the rear surface of the plate as compared to the pressure level incurred from the gas flow at the front surface facing the diaphragm. This is achieved by a sealed radial cavity exposed to the rear surface of the plate and in continuous pressure communica-tion with the front surface through a plurality of vent holes extending therebetween.
Abstract of the Disclosure Constant flow width through the last stage diffuser of a centrifugal compressor is maintained against widening by the forces of differential pressure via a diffuser defined between oppositely positioned radial faces of a diaphragm and an annular diffuser plate secured spaced from the diaphragm at the desired with. Enabling the diffuser plate to withstand width deflection and/or enlargement is a pressure balance imposed against the rear surface of the plate as compared to the pressure level incurred from the gas flow at the front surface facing the diaphragm. This is achieved by a sealed radial cavity exposed to the rear surface of the plate and in continuous pressure communica-tion with the front surface through a plurality of vent holes extending therebetween.
Description
12S~ 5 The field of art to which the invention pertains comprises the art of turbomachinery and component constructions therefor.
Multistage centrifugal compressors are used for a variety of applications requiring high pressure, high volume throughput of a particular gas. To a large extent, such com-pressors are custom sized and manufactured to meet customer's specifications with tolerances and configurations being closely held on the various components in order to assure the design performance intended for the equipment. Such compressors are constructed from a plurality of parts forming the diffusers.
The parts are positioned in end to end relationship forming the compressor.
Despite the accuracy of manufacture, a problem has been identified as associated with relatively small diffuser widths of such compressors in, for example, the last stage of a barrel-type straight through compressor or a back-to-back type compressor. Specifically, it has been found that in such com-pressors, the overall lengthof the multiplicity of parts sometimes results in at least one wall of the last diffuser stage tending to move slightly because of resultant stresses imposed by high operating pressures, causing width enlargment beyond the design dimensions. The resultant increase in diffuser flow width can typically amount to on the order of about 0.03 inches (0.076 cm) at differential pressures of 30 psig (207 KPa) in a compressor with a casing diameter of 60 inches (150 cm) or on the order of about 0.04 inches (0.102 cm) at differential pressures of 300 psig (2070 KPa) in a 24 inch (60 cm) casing diameter.
Such width changes in the diffuser are, of course, undesirable in that it tends to alter the design performance of the compressor at the affected stage. Notwithstanding recogni-tion of the problem, however, a solution therefor has not here-tofore been known.
Summary of the Invention This invention relates to improvements in centrifugal L ~
mab/
~ .
~ZS2~'75 compressors and more specifically to a construction in a centri-fugal compressor able to substantially maintain a constant diffuser width under operating conditions at which uncontrolled increased widths have previously been encountered.
The present invention resides in a multistage centri--fugal compressor f~r compressing fluid flow including a housing defining a flow path from an inlet to an outlet with a multi-stage impeller being provided in the flow path. Cooperating walls define a stationary diffuser radially extending downstream from the impeller at each of the stages. At least one cooperating wall of the diffuser for at least one of the stages includes an annular plate having a front surface facing toward the fluid path through the diffuser and a rear opposite surface facing from the fluid flow path through the diffuser. Means is effective to impose a pressure against the rear surface approaching equali-zation with the fluid pressure imposed against the front surface.
More specifically, the constant diffuser width is achieved in accordance with the invention by constructing one wall of the affected diffuser with an annular diffuser plate secured fastened in place thereat spaced from the diaphragm surface at the intended width. To avoid the adverse deflection effects of high pressure differentials imposed by the gas flow, the back face of the diffuser plate includes a radial ex-tending recess which cooperates with the support wall thereat to define an annular cavity. A pressure balance between the front and back faces of the diffuser plate is achieved by a plurality of circumferentially spaced axial bores extending between the faces. Since the pressure balance effectively equalizes the pressure values exposed to both faces of the diffuser plate, the diaphragm surface can move as a result of the high pressures without changing the width of the diffuser flow passageway.
It is therefore an object of the invention to afford an improvement in centrifugal compressor construction able to maintain substantially constant diffuser width under operating ~- 2 -.J~ '~ mab/ ~
~sz~s conditions at which undesirable in~eases in diffuser widths have previously occurred.
In summary, therefore, the above abject is met by the present invention which provides an imprcved multistage centrifugal ccmpressor, the c~mpressor including a diffuser having first and second portions defining a fluid flow path therein located radially ou~wardly of each i~peller, the improvement comprising: an annul æ recess located in the first portion of the diffuser adjacent to the flow path defined thereby; an annular plate moveably located in the recess, the plate having a front surface defining a porti~n of the diffusex flow path, a rear surface located in the recess, and a plurality of spaced ve~t holes extendina through the front and rear surfaces whereby the pressure in the recess is approximately e~ual to the pressure in th~
flow path; a plurality of spacing membeLs located in the flow path in engagement with the front surface of the plate and with the second portion of the diffuser; and, fastener means connecting the annul æ
plate and spacer members to the second portion of the diffuser acr~s.s the flow path whereby the annLlar plate is retained in fixed relaticnship to the second portion to define the width of the flow path, the plate, spacing nembers and fastener means being moveable relative to the first portion.
Brief Description of the Drawinqs Fig. 1 is a lcngitudinal section through a straight through type centrifugal compressor embodying the invention hereof;
Fig. 2 is a longitudinal section through a back-tc-back . 2a .
S
,: ~
~2S2~5 type centrifugal compressor embodying the invention hereof;
Fig. 3 is an enlarged sectional view of the encircled portions 3 of Figs. 1 and 2; and Fig. 4 is a fragmentary view as seen substantially along the lines 4-4 of Fig. 3.
Referring now to the drawings, there is illustrated in Fig. 1 a multistage centrifugal compressor of a straight through type comprising a housing 10 defining a flow path extending from an inlet 12 in communication with a plurality of stages 14 leading to a discharge outlet 16.
Comprising stages 14 are a plurality of axially spaced impellers 18 secured to a rotatable shaft 20. The stages are arranged in series flow communication with each other, and each impeller discharges a high velocity gas at its periphery. Energy transmitted to the gas creates a pressure rise as flow velocity decreases in the diffuser section 22 immediately aownstream of the impeller. From the diffuser, a stationary guide vane 24 directs the flow for proper entry into the next stage of succeeding impeller 18.
Between each impeller stage is a stationary diaphragm here designated 26, 28, 30 and 32 providing support for the stationary elements utilized between impellers such as the diffuser faces, guide vanes, return bend, labyrinths, etc.
Associated with each diaphragm in the flow path entering the succeeding vane 24 is a flow clearance of predetermined width defined between the surface of the diaphragm and the bulb section 34 thereat. As can be noti-ced, the diffuser widths immediately downstream of the impeller at a common peripheral distance progressively decrease from the first relatively low pressure stage at diaphragm 26 to the final relatively high pressure stage at diaphragm 32. For purposes of explanation, the intended design width at diaphragm 32 is assumed to have a dimension X and for maintaining the dimension substantially constant, utilizes a construction 35 in accordance with the invention as will be described below.
Fig. 2 is a comparable section to that o Fig. 1 for a back-to-back type compressor having a housing 36 that provides for a first section intake 38, a first section - ~252~
discharge 40, a second section intake 42 and a second section discharge 44 with the sections being separated by a division wall 46, Like in the construction of Fig. 1, each section includes a plurality of successive stages 14 5 comprised of spacea impellers 18 secured to a rotatable shaft 20. Series flow communication is provided between stages, and the impeller at each stage discharges a high velocity gas at its periphery. Between each impeller stage in each of the sections is a stationary diaphragm which for 10 the first section are designated 26', 28', 30', 32' and 48', while for the secona section are designated 26", 28", 30", 32" and 50" for maintaining the width of their respective diffuser 22. Forming the diffuser between division wall 46 and diaphragm 50" is the construction designated 35 in 15 accordance with the invention as will be described.
Referring now to Figs. 3 and 4, constant width X of diffuser 22 for the last stage in the embodiments of Figs.
1 and 2 is maintained in accordance herewith by means of an annular diffuser plate 54 received in a closely sized 20 annular recess 56 defined in diaphragm wall 32 or division wall 46. Opposite thereto for defining the diffuser is cooperating vane wall 33 and diaphragm wall 50, respectively.
The diffuser plate 54 is secured accurately positioned via a plurality of circumferentially spaced bolts 58 to the 25 opposite wall thereat through a sleeve bushing 60 of width dimension corresponding to' diffuser dimension X sought to be maintained for the diffuser. An O-ring seal 52 maintains a pressure seal.
To render the diffuser plate 54 effective for the 30 purposes hereof, its rear face includes an annular radially extending recess 64 which in cooperation with recess wall 56 defines an annular cavity 65. By means of a plurality of axially through vent holes 66, radially located to prodllce a mean pressure balance, pressure Pl in diffuser 22 is 35 continuously communicated with cavity 65 such that pressure value P2 in the latter is the same as or closely approaching the pressure value Pl on the former. By this arrangement, therefore, a pressure balance between the front and rear faces of the diffuser plate is substantially maintained :~252~'~5 thereby precluding undesirable effects of movement of the com-pressor parts as a result of high pressure as has occurred to increase diffuser width in the manner of the prior art.
The dash line shown in Fig. 3 illustrates the exag-gerated position of the division wall 46 when high pressure is in the diffuser passageway. It should be noted that although the wall 46 has moved, the plate 54 remains in its initial position maintaining the flow passageway width "X" constant.
1~
By the above description there is di.closed a novel improvement for a centrifugal compressor affording a substantially constant diffuser width under conditions similar to which con-ventional diffusers of the prior art have encountered undesirable increases in the width dimension. By maintaining the diffuser width constant in the manner hereof, performance of the affected stage is able to conform with design specifications without loss attributed to uncontrolled width increases as has previously occurred. At the same time, the construction of the invention
Multistage centrifugal compressors are used for a variety of applications requiring high pressure, high volume throughput of a particular gas. To a large extent, such com-pressors are custom sized and manufactured to meet customer's specifications with tolerances and configurations being closely held on the various components in order to assure the design performance intended for the equipment. Such compressors are constructed from a plurality of parts forming the diffusers.
The parts are positioned in end to end relationship forming the compressor.
Despite the accuracy of manufacture, a problem has been identified as associated with relatively small diffuser widths of such compressors in, for example, the last stage of a barrel-type straight through compressor or a back-to-back type compressor. Specifically, it has been found that in such com-pressors, the overall lengthof the multiplicity of parts sometimes results in at least one wall of the last diffuser stage tending to move slightly because of resultant stresses imposed by high operating pressures, causing width enlargment beyond the design dimensions. The resultant increase in diffuser flow width can typically amount to on the order of about 0.03 inches (0.076 cm) at differential pressures of 30 psig (207 KPa) in a compressor with a casing diameter of 60 inches (150 cm) or on the order of about 0.04 inches (0.102 cm) at differential pressures of 300 psig (2070 KPa) in a 24 inch (60 cm) casing diameter.
Such width changes in the diffuser are, of course, undesirable in that it tends to alter the design performance of the compressor at the affected stage. Notwithstanding recogni-tion of the problem, however, a solution therefor has not here-tofore been known.
Summary of the Invention This invention relates to improvements in centrifugal L ~
mab/
~ .
~ZS2~'75 compressors and more specifically to a construction in a centri-fugal compressor able to substantially maintain a constant diffuser width under operating conditions at which uncontrolled increased widths have previously been encountered.
The present invention resides in a multistage centri--fugal compressor f~r compressing fluid flow including a housing defining a flow path from an inlet to an outlet with a multi-stage impeller being provided in the flow path. Cooperating walls define a stationary diffuser radially extending downstream from the impeller at each of the stages. At least one cooperating wall of the diffuser for at least one of the stages includes an annular plate having a front surface facing toward the fluid path through the diffuser and a rear opposite surface facing from the fluid flow path through the diffuser. Means is effective to impose a pressure against the rear surface approaching equali-zation with the fluid pressure imposed against the front surface.
More specifically, the constant diffuser width is achieved in accordance with the invention by constructing one wall of the affected diffuser with an annular diffuser plate secured fastened in place thereat spaced from the diaphragm surface at the intended width. To avoid the adverse deflection effects of high pressure differentials imposed by the gas flow, the back face of the diffuser plate includes a radial ex-tending recess which cooperates with the support wall thereat to define an annular cavity. A pressure balance between the front and back faces of the diffuser plate is achieved by a plurality of circumferentially spaced axial bores extending between the faces. Since the pressure balance effectively equalizes the pressure values exposed to both faces of the diffuser plate, the diaphragm surface can move as a result of the high pressures without changing the width of the diffuser flow passageway.
It is therefore an object of the invention to afford an improvement in centrifugal compressor construction able to maintain substantially constant diffuser width under operating ~- 2 -.J~ '~ mab/ ~
~sz~s conditions at which undesirable in~eases in diffuser widths have previously occurred.
In summary, therefore, the above abject is met by the present invention which provides an imprcved multistage centrifugal ccmpressor, the c~mpressor including a diffuser having first and second portions defining a fluid flow path therein located radially ou~wardly of each i~peller, the improvement comprising: an annul æ recess located in the first portion of the diffuser adjacent to the flow path defined thereby; an annular plate moveably located in the recess, the plate having a front surface defining a porti~n of the diffusex flow path, a rear surface located in the recess, and a plurality of spaced ve~t holes extendina through the front and rear surfaces whereby the pressure in the recess is approximately e~ual to the pressure in th~
flow path; a plurality of spacing membeLs located in the flow path in engagement with the front surface of the plate and with the second portion of the diffuser; and, fastener means connecting the annul æ
plate and spacer members to the second portion of the diffuser acr~s.s the flow path whereby the annLlar plate is retained in fixed relaticnship to the second portion to define the width of the flow path, the plate, spacing nembers and fastener means being moveable relative to the first portion.
Brief Description of the Drawinqs Fig. 1 is a lcngitudinal section through a straight through type centrifugal compressor embodying the invention hereof;
Fig. 2 is a longitudinal section through a back-tc-back . 2a .
S
,: ~
~2S2~5 type centrifugal compressor embodying the invention hereof;
Fig. 3 is an enlarged sectional view of the encircled portions 3 of Figs. 1 and 2; and Fig. 4 is a fragmentary view as seen substantially along the lines 4-4 of Fig. 3.
Referring now to the drawings, there is illustrated in Fig. 1 a multistage centrifugal compressor of a straight through type comprising a housing 10 defining a flow path extending from an inlet 12 in communication with a plurality of stages 14 leading to a discharge outlet 16.
Comprising stages 14 are a plurality of axially spaced impellers 18 secured to a rotatable shaft 20. The stages are arranged in series flow communication with each other, and each impeller discharges a high velocity gas at its periphery. Energy transmitted to the gas creates a pressure rise as flow velocity decreases in the diffuser section 22 immediately aownstream of the impeller. From the diffuser, a stationary guide vane 24 directs the flow for proper entry into the next stage of succeeding impeller 18.
Between each impeller stage is a stationary diaphragm here designated 26, 28, 30 and 32 providing support for the stationary elements utilized between impellers such as the diffuser faces, guide vanes, return bend, labyrinths, etc.
Associated with each diaphragm in the flow path entering the succeeding vane 24 is a flow clearance of predetermined width defined between the surface of the diaphragm and the bulb section 34 thereat. As can be noti-ced, the diffuser widths immediately downstream of the impeller at a common peripheral distance progressively decrease from the first relatively low pressure stage at diaphragm 26 to the final relatively high pressure stage at diaphragm 32. For purposes of explanation, the intended design width at diaphragm 32 is assumed to have a dimension X and for maintaining the dimension substantially constant, utilizes a construction 35 in accordance with the invention as will be described below.
Fig. 2 is a comparable section to that o Fig. 1 for a back-to-back type compressor having a housing 36 that provides for a first section intake 38, a first section - ~252~
discharge 40, a second section intake 42 and a second section discharge 44 with the sections being separated by a division wall 46, Like in the construction of Fig. 1, each section includes a plurality of successive stages 14 5 comprised of spacea impellers 18 secured to a rotatable shaft 20. Series flow communication is provided between stages, and the impeller at each stage discharges a high velocity gas at its periphery. Between each impeller stage in each of the sections is a stationary diaphragm which for 10 the first section are designated 26', 28', 30', 32' and 48', while for the secona section are designated 26", 28", 30", 32" and 50" for maintaining the width of their respective diffuser 22. Forming the diffuser between division wall 46 and diaphragm 50" is the construction designated 35 in 15 accordance with the invention as will be described.
Referring now to Figs. 3 and 4, constant width X of diffuser 22 for the last stage in the embodiments of Figs.
1 and 2 is maintained in accordance herewith by means of an annular diffuser plate 54 received in a closely sized 20 annular recess 56 defined in diaphragm wall 32 or division wall 46. Opposite thereto for defining the diffuser is cooperating vane wall 33 and diaphragm wall 50, respectively.
The diffuser plate 54 is secured accurately positioned via a plurality of circumferentially spaced bolts 58 to the 25 opposite wall thereat through a sleeve bushing 60 of width dimension corresponding to' diffuser dimension X sought to be maintained for the diffuser. An O-ring seal 52 maintains a pressure seal.
To render the diffuser plate 54 effective for the 30 purposes hereof, its rear face includes an annular radially extending recess 64 which in cooperation with recess wall 56 defines an annular cavity 65. By means of a plurality of axially through vent holes 66, radially located to prodllce a mean pressure balance, pressure Pl in diffuser 22 is 35 continuously communicated with cavity 65 such that pressure value P2 in the latter is the same as or closely approaching the pressure value Pl on the former. By this arrangement, therefore, a pressure balance between the front and rear faces of the diffuser plate is substantially maintained :~252~'~5 thereby precluding undesirable effects of movement of the com-pressor parts as a result of high pressure as has occurred to increase diffuser width in the manner of the prior art.
The dash line shown in Fig. 3 illustrates the exag-gerated position of the division wall 46 when high pressure is in the diffuser passageway. It should be noted that although the wall 46 has moved, the plate 54 remains in its initial position maintaining the flow passageway width "X" constant.
1~
By the above description there is di.closed a novel improvement for a centrifugal compressor affording a substantially constant diffuser width under conditions similar to which con-ventional diffusers of the prior art have encountered undesirable increases in the width dimension. By maintaining the diffuser width constant in the manner hereof, performance of the affected stage is able to conform with design specifications without loss attributed to uncontrolled width increases as has previously occurred. At the same time, the construction of the invention
2~ is relatively simple and economical to implement for achieving the sought after result of enhanced compressor performance.
Since many changes could be made in the above con-struction, and many apparently widely different embodiments of this invention could be made without departing from the scope thereof, it is intended that all matter contained in the drawings and specification shall be interpreted as illustrative and not in a limiting sense.
mab/
``~.
Since many changes could be made in the above con-struction, and many apparently widely different embodiments of this invention could be made without departing from the scope thereof, it is intended that all matter contained in the drawings and specification shall be interpreted as illustrative and not in a limiting sense.
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Claims (4)
PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. An improved multistage centrifugal compressor, said compressor including a diffuser having first and second portions defining a fluid flow path therein located radially outwardly of each impeller, the improvement comprising:
an annular recess located in the first portion of said diffuser adjacent to the flow path defined thereby;
an annular plate moveably located in said recess, said plate having a front surface defining a portion of the diffuser flow path, a rear surface located in said recess, and a plurality of spaced vent holes extending through said front and rear surfaces whereby the pressure in said recess is approximately equal to the pressure in said flow path;
a plurality of spacing members located in said flaw path in engagement with the front surface of said plate and with said second portion of said diffuser; and, fastener means connecting said annular plate and spacer members to the second portion of said diffuser across said flaw path whereby said annular plate is retained in fixed relationship to said second portion to define the width of said flow path, said plate, spacing members and fastener means being moveable relative to the first portion.
an annular recess located in the first portion of said diffuser adjacent to the flow path defined thereby;
an annular plate moveably located in said recess, said plate having a front surface defining a portion of the diffuser flow path, a rear surface located in said recess, and a plurality of spaced vent holes extending through said front and rear surfaces whereby the pressure in said recess is approximately equal to the pressure in said flow path;
a plurality of spacing members located in said flaw path in engagement with the front surface of said plate and with said second portion of said diffuser; and, fastener means connecting said annular plate and spacer members to the second portion of said diffuser across said flaw path whereby said annular plate is retained in fixed relationship to said second portion to define the width of said flow path, said plate, spacing members and fastener means being moveable relative to the first portion.
2. The multistage centrifugal compressor according to claim 1 wherein said spacing members comprise a plurality of circumferentially spaced members located in said diffuser flow path in engagement with said front surface to establish the design width thereof.
3. The multistage centrifugal compressor according to claim 2 wherein said fastener means comprises a plurality of bolts and each of said spacing members comprises a tubular æ sleeve through which one of said bolts extends.
4. The multistage centrifugal compressor of claim 3 wherein said annular plate has an annular groove in the rear surfaces thereof adjacent to said first portion of said diffuser, said vent holes extending into said annular groove.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US53488183A | 1983-09-22 | 1983-09-22 | |
| US534,881 | 1983-09-22 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1252075A true CA1252075A (en) | 1989-04-04 |
Family
ID=24131906
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000455551A Expired CA1252075A (en) | 1983-09-22 | 1984-05-31 | Diffuser construction for a centrifugal compressor |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JPS6067797A (en) |
| CA (1) | CA1252075A (en) |
| DE (1) | DE3430307A1 (en) |
| FR (1) | FR2552501B1 (en) |
| IT (1) | IT1179392B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10995761B2 (en) | 2017-02-21 | 2021-05-04 | Siemens Energy Global GmbH & Co. KG | Return stage |
| US11073162B2 (en) | 2017-02-10 | 2021-07-27 | Siemens Energy Global GmbH & Co. KG | Return stage of a multi-staged compressor or expander with twisted guide vanes |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1997033092A1 (en) * | 1996-03-06 | 1997-09-12 | Hitachi, Ltd. | Centrifugal compressor and diffuser for the centrifugal compressor |
| JP3492097B2 (en) * | 1996-07-25 | 2004-02-03 | 三菱重工業株式会社 | Diffuser with wings for centrifugal compressor |
| DE19654840C2 (en) * | 1996-12-23 | 2001-12-13 | Mannesmann Ag | Multi-stage turbo compressor |
| DE102009019061A1 (en) | 2009-04-27 | 2010-10-28 | Man Diesel & Turbo Se | Multistage centrifugal compressor |
| DE102009029647A1 (en) * | 2009-09-21 | 2011-03-24 | Man Diesel & Turbo Se | Axial-radial flow machine |
| JP6037906B2 (en) | 2013-03-21 | 2016-12-07 | 三菱重工業株式会社 | Centrifugal fluid machine |
| JP6124659B2 (en) * | 2013-04-15 | 2017-05-10 | 株式会社日立製作所 | Multistage centrifugal fluid machine |
| DE102014203251A1 (en) | 2014-02-24 | 2015-08-27 | Siemens Aktiengesellschaft | Return stage for a radial turbomachine |
| DE102014219821A1 (en) * | 2014-09-30 | 2016-03-31 | Siemens Aktiengesellschaft | Return step |
| JP7105563B2 (en) * | 2014-12-23 | 2022-07-25 | エービービー スウィッツァーランド リミテッド | diffuser for centrifugal compressor |
| JP6934781B2 (en) | 2017-09-06 | 2021-09-15 | 株式会社日立インダストリアルプロダクツ | Multi-stage centrifugal fluid machine |
| EP4015832A1 (en) | 2020-12-18 | 2022-06-22 | Siemens Energy Global GmbH & Co. KG | Static flow guide, radial turbomachine |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR645393A (en) * | 1927-01-20 | 1928-10-24 | Escher Wyss & Cie Const Mec | Centrifugal pump |
| FR667306A (en) * | 1928-02-02 | 1929-10-15 | Rateau Soc | Device for adjusting the operating conditions of centrifugal machines |
| CH350408A (en) * | 1957-04-04 | 1960-11-30 | Sulzer Ag | Multi-stage centrifugal compressor |
| US3105632A (en) * | 1960-03-14 | 1963-10-01 | Dresser Ind | High pressure centrifugal compressor |
| FR1357580A (en) * | 1963-05-31 | 1964-04-03 | Licentia Gmbh | Radial compressor |
| US3426964A (en) * | 1966-10-11 | 1969-02-11 | Dresser Ind | Compressor apparatus |
| US3667860A (en) * | 1970-03-13 | 1972-06-06 | Carrier Corp | Diffuser valve mechanism for centrifugal gas compressor |
| CH532202A (en) * | 1970-12-15 | 1972-12-31 | Bbc Sulzer Turbomaschinen | Installation block for installation in a multistage centrifugal compressor |
| DE2458014C3 (en) * | 1974-12-07 | 1981-12-03 | Nevskij mašinostroitel'nyj zavod imeni V.I. Lenina, Leningrad | Stator of a multistage centrifugal compressor |
-
1984
- 1984-05-31 CA CA000455551A patent/CA1252075A/en not_active Expired
- 1984-07-09 IT IT48532/84A patent/IT1179392B/en active
- 1984-07-24 JP JP59153906A patent/JPS6067797A/en active Granted
- 1984-08-15 DE DE19843430307 patent/DE3430307A1/en not_active Ceased
- 1984-09-20 FR FR8414457A patent/FR2552501B1/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11073162B2 (en) | 2017-02-10 | 2021-07-27 | Siemens Energy Global GmbH & Co. KG | Return stage of a multi-staged compressor or expander with twisted guide vanes |
| US10995761B2 (en) | 2017-02-21 | 2021-05-04 | Siemens Energy Global GmbH & Co. KG | Return stage |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2552501A1 (en) | 1985-03-29 |
| JPS6067797A (en) | 1985-04-18 |
| IT1179392B (en) | 1987-09-16 |
| JPH0520597B2 (en) | 1993-03-19 |
| DE3430307A1 (en) | 1985-04-04 |
| FR2552501B1 (en) | 1989-11-24 |
| IT8448532A0 (en) | 1984-07-09 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEX | Expiry |