US2161517A - Axial flow turbo compressor - Google Patents

Axial flow turbo compressor Download PDF

Info

Publication number
US2161517A
US2161517A US164954A US16495437A US2161517A US 2161517 A US2161517 A US 2161517A US 164954 A US164954 A US 164954A US 16495437 A US16495437 A US 16495437A US 2161517 A US2161517 A US 2161517A
Authority
US
United States
Prior art keywords
flow
axial
axial flow
stages
wheel
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
Application number
US164954A
Other languages
English (en)
Inventor
Keller Curt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
ESCHER WYSS MACHINENFABRIKEN A
ESCHER WYSS MACHINENFABRIKEN AG
Original Assignee
ESCHER WYSS MACHINENFABRIKEN A
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by ESCHER WYSS MACHINENFABRIKEN A filed Critical ESCHER WYSS MACHINENFABRIKEN A
Application granted granted Critical
Publication of US2161517A publication Critical patent/US2161517A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/02—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal
    • F04D17/025—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal comprising axial flow and radial flow stages
    • 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

Definitions

  • the problem is particularly diflicult in a multistage axial flow turbo-compressor, because in passing from a stage or group of stages to the intercooler, the direction of flow must change from axial to substantially radial. Such deflection can be effected by the use of curved ducts or casings, but this solution of the problem is attended by the disadvantage that much valuable space is consumed. Furthermore, there are serious energy losses because in an axialflow compressor the velocities of flow are high as compared with the peripheral velocity of the wheel.
  • the present invention overcomes the above difficulty by causing the stage or group of stages of the axial flow turbo-compressor todeliver to an auxiliary centrifugal wheel deflecting the axial through-flow into the supply conduit leading to the intermediate cooler.
  • the change in direction of flow takes place with the performance of work by the auxiliary centrifugal Wheel, but only to the extent as is necessary for a deflection in the small possible space.
  • the auxiliary wheel imparts a rotary motion tb the medium undergoing compression, such rotary motion occurring in a plane which is normal or approximately normal to the axis of the compressbr shaft.
  • This rotary motion is partially .converted into pressure in the conduit leading to the intermediate cooler, such conduit being suitably designed for the purpose, as a special casing acting as a diffuser. Since the auxiliary centrifugal wheel receives the medium from' the .pre-
  • the auxiliary wheel operates with good efficiency so that the transition from the axial flowcompressor to the intermediate cooler occurs with little or no energy loss. Consequently, the invention not only economizes space as compared to. the/prior'art, but reduces the energy losses to a very small amount.
  • Fig. l is a view, part in elevation and part in longitudinal section, of an axial flow turbocompressor, having a single casing and having two intermediate coolers with associated radial flow wheels.
  • Fig. 2 is a section on the line 2-2 of Fig. 1.
  • Fig. 3 is an end view of the compressor of Fig. 1 as viewed from the left in that figure.
  • Fig. '4- is a view similar to Fig. 1 and showing a modification in-which separate casings are used for different groups of stages.
  • Fig. 5 is a view similar to the right hand portion of Fig. 4 and showing a possible further motor 9 through shaft H and carries blades I2,
  • cooler 28 (identical with cooler 22).
  • the blades just mentioned are divided into three groups A, B and C by the interposition of radial flow, i. e., centrifugal runners l6 and I! with associated diffuser housings I8 and I9. These are identical except that they differ in dimensions to correspond to the different stages of compression.
  • the auxiliary centrifugal wheel l6 receives from group A and deflects the axial through-flow into the spiral diffuser housing [8 which delivers through duct 2
  • the auxiliary centrifugal wheel ll receives compressed gas from group B and deflects the axial through-flow into the spiral diffuser housing l9 which delivers through duct 21 to inter- From cooler 28 flow 'is by pipe 29 'to the inlet ring 3
  • the auxiliary radial flow wheels l6, 11 provide for the necessary deflection of the axial through-flow in a very small space and with the smallest possible loss. Since the centrifugal wheels l6 and i1 impart rotary movement to the gas undergoing compression, the housings l8 and is are designed for atleast a part of their extent as spiral casings serving as diffusers.
  • FIG. 5 shows a unit identical with the right hand unit in Fig. 4 except that the heel I60, un-
  • a turbo-compressor comprising two groups ot'axial flow stages;- an intercooler for cooling comprwed working medium; a radial flow wheel coaxial with said turbo-compressor betweeen said groups and arranged to receive working medium Water connections are i compressed in the first group and deliver it with change of direction to said intercooler with performance of work approximately to the extent necessary for deflection; and a connection for conducting working medium from the intercooler to said second group.
  • a turbo-compressor comprising two group of axial flow stages; an intercooler for cooling compressed Working medium; a radial flow unit arranged coaxially with said axial flow stages and so as to receive medium compressed by the first group of stages, said radial unit including a radial flow wheel and coacting spiral casing arranged to act as a diffuser and deliver medium leaving theradial wheel to the intercooler, the wheel and easing being so designed that the change in wheel turning with said runner within said hous-- ing, the radial flow wheel being so designed as to receive medium from the first of said successive stages, deflect it from its axial path, and deliver it to said intercooler with performance of work approximately. to the extent necessary for deflection.
  • a multi-stage axial flow turbo-compressor including a housing and a run: ner, and having at least one intercooler interposed between two successive stages; and a flow diverting unit comprising a radial flow wheel turning with said runner within a portion of said housing formed as a diffuser, the parts being so designed that the radial flow wheel receives working medium from the first of said successive stages, and deflects it through said difiuser to said intercooler with performance of work approximately to the extent necessary for deflection.
  • a multi-stage axial flow turbo-compressor including a housing and a runner and having at least one intercooler interposed between two successive stages; and means for guiding working medium flowing from the first of said successive stages from its axial path to said intercooler without substantial loss of energy, said means comprising a radial flow wheel turning coaxially with said runner, and so designed .as to perform substantially the minimum work consistent with efficient deflection of the working medium from its axial path.
  • a multi-stage axial flow turbo-compressor including a housing and a run- 'ner and having at least one intercooler interposed between two successive stages; and means for guiding working medium flowing from the first of said successive stages from its axial path to said, intercooler without substantial loss of energy, said means comprising a radial flow wheel turningcoaxially with said runner, and a housing for said radial flow wheel, said housing serving as a difiuser toconvert velocity head of medium leaving the radial wheel into pressure as the medium approaches the intercooler, and the radialflow wheel being so designed as to perform substantially the minimum .work consistent with effective deflection of the working medium from

Landscapes

  • 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)
US164954A 1936-10-26 1937-09-21 Axial flow turbo compressor Expired - Lifetime US2161517A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH189934T 1936-10-26

Publications (1)

Publication Number Publication Date
US2161517A true US2161517A (en) 1939-06-06

Family

ID=4436622

Family Applications (1)

Application Number Title Priority Date Filing Date
US164954A Expired - Lifetime US2161517A (en) 1936-10-26 1937-09-21 Axial flow turbo compressor

Country Status (6)

Country Link
US (1) US2161517A (de)
CH (1) CH189934A (de)
DE (1) DE671913C (de)
FR (1) FR826453A (de)
GB (1) GB478498A (de)
NL (1) NL43877C (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2540991A (en) * 1942-03-06 1951-02-06 Lockheed Aircraft Corp Gas reaction aircraft power plant
US2739756A (en) * 1952-03-07 1956-03-27 Worthington Corp Turbo-compressor
US2828066A (en) * 1954-07-05 1958-03-25 Sulzer Ag Turbocompressor plant
US3303989A (en) * 1963-03-02 1967-02-14 Gutehoffnungshuette Sterkrade Axial-and radial-flow, multistage centrifugal compressor
CN114207286A (zh) * 2019-08-07 2022-03-18 开利公司 轴流式和下游压缩机组件

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE974845C (de) * 1949-07-27 1961-05-10 Demag Ag Kreiselverdichter mit mindestens vier hintereinandergeschalteten Stufen
DE977315C (de) * 1951-09-20 1965-12-02 Bruno Dr-Ing Eck Radialgeblaese-Laufrad mit vorgeschaltetem Axialrad
DE1112246B (de) * 1957-02-15 1961-08-03 Ingbuero Dipl Ing Friedrich He Wasserkuehler fuer Druckluft
US3476485A (en) * 1967-09-18 1969-11-04 Dresser Ind Multistage centrifugal compressor

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2540991A (en) * 1942-03-06 1951-02-06 Lockheed Aircraft Corp Gas reaction aircraft power plant
US2739756A (en) * 1952-03-07 1956-03-27 Worthington Corp Turbo-compressor
US2828066A (en) * 1954-07-05 1958-03-25 Sulzer Ag Turbocompressor plant
US3303989A (en) * 1963-03-02 1967-02-14 Gutehoffnungshuette Sterkrade Axial-and radial-flow, multistage centrifugal compressor
CN114207286A (zh) * 2019-08-07 2022-03-18 开利公司 轴流式和下游压缩机组件

Also Published As

Publication number Publication date
NL43877C (de) 1938-07-16
CH189934A (de) 1937-03-31
FR826453A (fr) 1938-03-31
GB478498A (en) 1938-01-19
DE671913C (de) 1939-02-16

Similar Documents

Publication Publication Date Title
US3243102A (en) Centrifugal fluid pump
US4219306A (en) Multistage turbocompressor with multiple shafts
US2656096A (en) Centrifugal pump and compressor
US2087834A (en) Fluid impeller and turbine
US3171353A (en) Centrifugal fluid pump
US2161517A (en) Axial flow turbo compressor
CN109268295A (zh) 一种具有径轴向扩压器的两级空气压缩系统
US4224010A (en) Multistage turbocompressor with diagonal-flow impellers
US11306734B2 (en) Centrifugal compressor
US2341871A (en) Centrifugal blower with spiral casing
CN106151063B (zh) 一种co循环气压缩机
US1213889A (en) Turbine pump or compressor.
EP3489595A1 (de) Auf wellenrotor basierende mehrstufige kühlanlage
CN209212609U (zh) 一种具有径轴向扩压器的两级空气压缩系统
CN107989804A (zh) 双转子对转冲压压气机
US2474410A (en) Multistage compressor
US2612310A (en) Intermediate cooler for multistage rotary compressors
US2367223A (en) Combined centrifugal compressor and cooler
US2923246A (en) Vortex pump
US2311024A (en) Guide apparatus for centrifugal blowers and pumps
US1158978A (en) Turbine-pump, turbine-blower, and propeller.
US2759662A (en) Centrifugal compressors
US2380772A (en) Centrifugal compressor
US1263056A (en) Operation of centrifugal-compressor plants.
CN213953896U (zh) 一种螺杆式压缩机