US2361726A - Multistage compressor - Google Patents
Multistage compressor Download PDFInfo
- Publication number
- US2361726A US2361726A US377704A US37770441A US2361726A US 2361726 A US2361726 A US 2361726A US 377704 A US377704 A US 377704A US 37770441 A US37770441 A US 37770441A US 2361726 A US2361726 A US 2361726A
- Authority
- US
- United States
- Prior art keywords
- compressor
- chamber
- cooler
- stage
- coolers
- 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 - Lifetime
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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
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
- F04D29/5826—Cooling at least part of the working fluid in a heat exchanger
-
- 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
- F04D17/127—Multi-stage pumps with radially spaced stages, e.g. for contrarotating type
Definitions
- This invention relates to a turbine-like multistage compressor with radial admission of the working fluid, provided with intermediate cooling.
- the object of the invention is therefore to suitably arrange the cooler within the compressor, particularly within a turbine-like multi-stage compressor with radial admission of the working medium and whose blades are subdivided into a plurality of rows of bladeswhich are traversed one after the other by the working fluid.
- the cooler or coolers of substantially the circular type are arranged in the by-pass space provided between two blade rings.
- Fig. 1 shows a longitudinal view
- Fig. 2 a lateral view, partly in section.
- the blading is subdivided into a plurality of blade groups I, arranged on the shaft 3 at both sides of the discs 2 and traversed one after the other by the air to be compressed in the direction as indicated by the arrows A. Between these two rows of blades is provided an intermediate cool-- ing, i. e., the intermediate coolers are arranged in the by-pass spaces 4 and 5 between two rows of blades.
- the great advantage of such an arrangement lies in the fact that the compressed air on its way from one group of blades to the other may flow directly through thecooler without encountering appreciable resistances.
- a reversal of the compressed air is necessary between two groups of blades so that as the only additional loss there results in the cooler itself the loss due to the resistance to flow.
- the intermediate coolers i. e., the intermediate coolers are arranged in the by-pass spaces 4 and 5 between two rows of blades.
- a compressor is, 5
- tubes l 4 dimensioning the blades and by a suitable choice of the velocity of flow.
- the by-pass spaces 4 and 5 have end walls 8 and I having apertures '8 and 9 respectively.
- the fluid coolers HI and H, in the spaces 4 and 5 respectively, comprise heads I! and i3 and series of and i5 to serve as heat exchange elements.
- the coolers l0 and II are insertable through the apertures 8 and 9 and the heads I! and I3 are attached to walls 8 and 1 by bolts IS.
- the cooling water circulates through the coolers l0 and H by pipes II, as indicated by the arrows B. It will be noted (Fig. 1) that the cooler ll disposed in space 5, the secondary stage chamber, is provided with a larger number of tubes I5, thus having a greater capacity than the cooler Ill disposed in the space 4, the primary stage chamber. a
- a fluid cooler comprising a head which constitutes the means of attachment of said cooler to the rim of said aperture, and heat exchange elements attached to said head to form a unit, and insertable axially through said aperture so as to be entirely contained within said chamber.
- a turbo-compressor wherein the working fluid flows generally outwardly to a peripheral chamber, and then flows generally radially inwardly therefrom, a circular end wall for said chamber provided with a plurality of segmental apertures, and a plurality of fluid coolers insertable axially of the compressor through said apertures, respectively, so as to be entirely contained within said chambers, each cooler comprising a head constituting the means 01' attachment of the cooler to the rim of the aperture, and heat exchange elements attached to the head to form a unit.
- each cooler comprising a head constituting the means of attachment of the cooler to the rim of the aperture, and heat exchange elements attached to thehead to ⁇ cm a unit, the elements a of the unit in the second stage chamber having a capacity greater than the elements of the unit in the primary stage chamber.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Oct. 31, 1944. w. WElMAR 2,361,726
MUL'II STAGE COMPRES SOR Filed Feb. 6, 1941 .Evenior Wilhelm Wimar.
r y flax fltlornay.
Patented Oct. 31, 1944 UNITED. STATES,
MULTISTAGE comrnnsson Wilhelm 'Weimar, Berlin-Siemensstadt,
Ger-
many; vested in the Alien Property Custodian Application February a, 1941, Serial No.- 371,704 In Germany December 20, 1939 4 Claims. (Cl. 230 209) This invention relates to a turbine-like multistage compressor with radial admission of the working fluid, provided with intermediate cooling.
The work of compression in as is well known, the smaller, the more the curve f compression approaches the isothermal curve. The coincidence of the compression curve with the isothermal curve is the more difllcult to bring about, the greater the number of stages of the compressor, which is particularly the case in turbine-like compressors with radial admission of the working fluid. Here the number pf stages is so great and the dimensions of the blade are so small that the intermediatecooling cannot be practically carried out when employing hollow blades or similar means. There is no other remedy than to provide an intermediate cooling, for instance, between two stages. The object of the invention is therefore to suitably arrange the cooler within the compressor, particularly within a turbine-like multi-stage compressor with radial admission of the working medium and whose blades are subdivided into a plurality of rows of bladeswhich are traversed one after the other by the working fluid. In this case the cooler or coolers of substantially the circular type are arranged in the by-pass space provided between two blade rings.
In the accompanying drawing is shown an embodiment of the invention in diagrammatic form, in which Fig. 1 shows a longitudinal view and Fig. 2 a lateral view, partly in section.
In this turbine-like compressor with radial admission of the working fluid, the blading is subdivided into a plurality of blade groups I, arranged on the shaft 3 at both sides of the discs 2 and traversed one after the other by the air to be compressed in the direction as indicated by the arrows A. Between these two rows of blades is provided an intermediate cool-- ing, i. e., the intermediate coolers are arranged in the by-pass spaces 4 and 5 between two rows of blades. The great advantage of such an arrangement lies in the fact that the compressed air on its way from one group of blades to the other may flow directly through thecooler without encountering appreciable resistances. A reversal of the compressed air is necessary between two groups of blades so that as the only additional loss there results in the cooler itself the loss due to the resistance to flow. However, the
loss may be reduced to a minimum by suitably a compressor is, 5
tubes l 4 dimensioning the blades and by a suitable choice of the velocity of flow.
Since in the case of coolers certain damages and pollutions must always be reckoned with, it is preferable to subdivide the cooler into a plurality of individual segments which may be arranged in the parallel or in series and which may be separately removed without great diillculties in order to cleanand to replace the same. The by-pass spaces 4 and 5 have end walls 8 and I having apertures '8 and 9 respectively. The fluid coolers HI and H, in the spaces 4 and 5 respectively, comprise heads I! and i3 and series of and i5 to serve as heat exchange elements. The coolers l0 and II are insertable through the apertures 8 and 9 and the heads I! and I3 are attached to walls 8 and 1 by bolts IS. The cooling water circulates through the coolers l0 and H by pipes II, as indicated by the arrows B. It will be noted (Fig. 1) that the cooler ll disposed in space 5, the secondary stage chamber, is provided with a larger number of tubes I5, thus having a greater capacity than the cooler Ill disposed in the space 4, the primary stage chamber. a
What is claimed is:
1. In a turbo-compressor wherein the working fluid flows generally outwardly to a peripheral chamber, and then flows'generally radially inwardly therefrom, said chamber having an end wall with an aperture therein, a fluid cooler comprising a head which constitutes the means of attachment of said cooler to the rim of said aperture, and heat exchange elements attached to said head to form a unit, and insertable axially through said aperture so as to be entirely contained within said chamber.
2. In a turbo-compressor wherein the working fluid flows generally outwardly to a peripheral chamber, and then flows generally radially inwardly therefrom, a circular end wall for said chamber provided with a plurality of segmental apertures, and a plurality of fluid coolers insertable axially of the compressor through said apertures, respectively, so as to be entirely contained within said chambers, each cooler comprising a head constituting the means 01' attachment of the cooler to the rim of the aperture, and heat exchange elements attached to the head to form a unit.
3. In a multi-stage turbo-compressor wherein, in each stage, the working fluid flows generally outwardly to a peripheral chamber and then flows generally radially inwardly therefrom, there being a separate chamber for each stage,
an end wall for each chamber, having an aperture therein, and a plurality of iiuid coolers insortable axially or the compressor through said secondary stages, wherein in each stage the working fluid flows generally outwardly to a peripheral chamber and then flows generally radially inwardly therefrom, there being a separate chamber for each stage, an end wall for each chamber, having an aperture therein, and a pair of fluid coolers insertable axially of the compressor through said apertures, respectively,
so as to be entirely contained within said chambers, each cooler comprising a head constituting the means of attachment of the cooler to the rim of the aperture, and heat exchange elements attached to thehead to {cm a unit, the elements a of the unit in the second stage chamber having a capacity greater than the elements of the unit in the primary stage chamber.
WILHEIMWEMAR.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE2361726X | 1939-12-20 |
Publications (1)
Publication Number | Publication Date |
---|---|
US2361726A true US2361726A (en) | 1944-10-31 |
Family
ID=7995488
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US377704A Expired - Lifetime US2361726A (en) | 1939-12-20 | 1941-02-06 | Multistage compressor |
Country Status (1)
Country | Link |
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US (1) | US2361726A (en) |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2474410A (en) * | 1945-01-13 | 1949-06-28 | Sulzer Ag | Multistage compressor |
US2623580A (en) * | 1947-03-05 | 1952-12-30 | Du Pin Cellulose | Centrifugal evaporator |
US2672953A (en) * | 1946-08-02 | 1954-03-23 | Clayton Manufacturing Co | Dynamometer with built-in heat exchanger |
US2672954A (en) * | 1947-09-23 | 1954-03-23 | Clayton Manufacturing Co | Dynamometer |
US2712895A (en) * | 1950-08-12 | 1955-07-12 | Vladimir H Pavlecka | Centripetal subsonic compressor |
US2819882A (en) * | 1953-10-01 | 1958-01-14 | Westinghouse Electric Corp | Heat exchange apparatus |
US3001692A (en) * | 1949-07-26 | 1961-09-26 | Schierl Otto | Multistage compressors |
US3037352A (en) * | 1958-09-08 | 1962-06-05 | Vladimir H Pavlecka | Bypass jet engines using centripetal flow compressors and centrifugal flow turbines |
US3039567A (en) * | 1959-11-23 | 1962-06-19 | Gen Motors Corp | Fluid cooled brake |
US4923364A (en) * | 1987-03-20 | 1990-05-08 | Prc Corporation | Gas laser apparatus, method and turbine compressor therefor |
WO1991004417A1 (en) * | 1989-09-18 | 1991-04-04 | Framo Developments (Uk) Limited | Pump or compressor unit |
US20040055740A1 (en) * | 2002-09-20 | 2004-03-25 | Meshenky Steven P. | Internally mounted radial flow intercooler for a combustion air charger |
US20080295515A1 (en) * | 2007-05-29 | 2008-12-04 | Behr Gmbh & Co. Kg | Arrangement of supercharging units for supercharging an internal combustion engine |
US20240035480A1 (en) * | 2021-02-05 | 2024-02-01 | Siemens Energy Global GmbH & Co. KG | Multi-stage compressor assembly having rows of blades arranged to rotate in counter-opposite rotational directions |
-
1941
- 1941-02-06 US US377704A patent/US2361726A/en not_active Expired - Lifetime
Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2474410A (en) * | 1945-01-13 | 1949-06-28 | Sulzer Ag | Multistage compressor |
US2672953A (en) * | 1946-08-02 | 1954-03-23 | Clayton Manufacturing Co | Dynamometer with built-in heat exchanger |
US2623580A (en) * | 1947-03-05 | 1952-12-30 | Du Pin Cellulose | Centrifugal evaporator |
US2672954A (en) * | 1947-09-23 | 1954-03-23 | Clayton Manufacturing Co | Dynamometer |
US3001692A (en) * | 1949-07-26 | 1961-09-26 | Schierl Otto | Multistage compressors |
US2712895A (en) * | 1950-08-12 | 1955-07-12 | Vladimir H Pavlecka | Centripetal subsonic compressor |
US2819882A (en) * | 1953-10-01 | 1958-01-14 | Westinghouse Electric Corp | Heat exchange apparatus |
US3037352A (en) * | 1958-09-08 | 1962-06-05 | Vladimir H Pavlecka | Bypass jet engines using centripetal flow compressors and centrifugal flow turbines |
US3039567A (en) * | 1959-11-23 | 1962-06-19 | Gen Motors Corp | Fluid cooled brake |
US4923364A (en) * | 1987-03-20 | 1990-05-08 | Prc Corporation | Gas laser apparatus, method and turbine compressor therefor |
WO1991004417A1 (en) * | 1989-09-18 | 1991-04-04 | Framo Developments (Uk) Limited | Pump or compressor unit |
AU656883B2 (en) * | 1989-09-18 | 1995-02-23 | Framo Developments (Uk) Limited | Pump or compressor unit |
US5417544A (en) * | 1989-09-18 | 1995-05-23 | Framo Developments (Uk) Limited | Pump or compressor unit |
US20040055740A1 (en) * | 2002-09-20 | 2004-03-25 | Meshenky Steven P. | Internally mounted radial flow intercooler for a combustion air charger |
US7278472B2 (en) * | 2002-09-20 | 2007-10-09 | Modine Manufacturing Company | Internally mounted radial flow intercooler for a combustion air changer |
US20080295515A1 (en) * | 2007-05-29 | 2008-12-04 | Behr Gmbh & Co. Kg | Arrangement of supercharging units for supercharging an internal combustion engine |
US8099956B2 (en) * | 2007-05-29 | 2012-01-24 | Behr Gmbh & Co. Kg | Arrangement of supercharging units for supercharging an internal combustion engine |
US20240035480A1 (en) * | 2021-02-05 | 2024-02-01 | Siemens Energy Global GmbH & Co. KG | Multi-stage compressor assembly having rows of blades arranged to rotate in counter-opposite rotational directions |
US12092118B2 (en) * | 2021-02-05 | 2024-09-17 | Siemens Energy Global GmbH & Co. KG | Multi-stage compressor assembly having rows of blades arranged to rotate in counter-opposite rotational directions |
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