US3306574A - Rotary fluid flow machine - Google Patents

Rotary fluid flow machine Download PDF

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Publication number
US3306574A
US3306574A US448389A US44838965A US3306574A US 3306574 A US3306574 A US 3306574A US 448389 A US448389 A US 448389A US 44838965 A US44838965 A US 44838965A US 3306574 A US3306574 A US 3306574A
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United States
Prior art keywords
working medium
flow path
flow
path system
rotor
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Expired - Lifetime
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US448389A
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English (en)
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Bachl Herbert
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Individual
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Individual
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    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D30/00—Producing pneumatic or solid tyres or parts thereof
    • B29D30/06—Pneumatic tyres or parts thereof (e.g. produced by casting, moulding, compression moulding, injection moulding, centrifugal casting)
    • B29D30/38—Textile inserts, e.g. cord or canvas layers, for tyres; Treatment of inserts prior to building the tyre
    • B29D30/46—Cutting textile inserts to required shape
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
    • F02C5/02—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion characterised by the arrangement of the combustion chamber in the chamber in the plant

Definitions

  • My invention relates to fluid flow machines. More particularly, it relates to such improved machine for expanding or compressing gaseous materials, mixtures of gaseous and liquid materials and mixtures of gases .and liquid materials having finely dispersed solid particles therein.
  • the rotor blades may be made hollow so that a second working medium such as a cooling fluid may be caused to flow radially therethrough.
  • a fluid flow machine for handling at least one working medium fluid and comprising rotor wheel stages mounted on an axially centrally disposed shaft therein and wherein working medium fluid is caused to flow in a substantially axial direction in the center Zone and substantially tangentially at the outer peripheries of the rotor stages; the improvement which comprises a centripetal axial flow path system and a centrifugal radial flow path system in at least one of the rotor wheel stages.
  • FIG. 1 is a front elevational view of a rotor wheel stage in a fluid flow machine in which axial flow of working medium fluid occurs in the center zone and tangential fluid flow takes place in the rotor wheel stage peripheral zone
  • FIG. 2 is a schematic section which includes the rotor wheel stage shown in FIG. 1, the section being generally parallel to the rotor axis but along some of the curved flow channels and hence not planar
  • FIGS. 3 and 5 show in end elevation rotor wheel stages for providing flow path systems in accordance with the principles of the invention
  • FIG. 4 is a schematic depiction of the flow path principles of the invention
  • FIG. 6 is a schematic diagram of a gas turbine system application of the invention
  • FIG. 7 shows more in detail a partial section of a machine according to the invention
  • FIG. 8 is a cross section. along the line VIII-VIII in FIG. 7, and
  • FIG. 9 shows part of a section along the line IXIX in FIG. 8.
  • FIGS. 1 and 2 there is shown a rotor 23 and a guide wheel stage.
  • the rotor is mounted on an axially disposed shaft 21 in a fluid flow machine as disclosed in the aforesaid application 227,477, in end and side elevations respectively.
  • Thestator 22, which comprises the guide stage, has a cap-shaped portion 22' extending over the rotor 23.
  • FIG. 1 shows an arrangement and an effect which is present in known axial-flow type turbines and which comprises hook-shaped blades in axial section.
  • the arrangement shown in FIGS. 1 and 2 is modified such that the radial portion of the flow path is obliquely disposed in axial section.
  • the radial portion of the flow path is developed at least in a zone of intersection with an axial flow path component.
  • AA is the designation of the expansion channels and BB is the designation of the compression channels.
  • the designation a denotes the entry into the expansion channels and the designation b denotes the entry into the compression channels.
  • the working medium flows through channels AA centripetally and through channels BB centrifu-gally.
  • the radial channels suitably terminate in tangential disposition at the peripheral zone of the rotor wheel although such terminations may also be cylindrical or conical surfaces. Both working media move axially in the same direction but radially in opposite directions whereby there is enabled the obtaining of optimum design conditions for the two changes of state, i.e., expansion and compression, at the same speed.
  • the working medium accumulation which is divided in the radial channels of the rotor wheel in one system of fiow paths can be utilized for the overlapping of the channels of the second system of flow paths and thus each flow path can be developed to provide optimum performance with the two systems affecting each other relative to space requirements only very slightly.
  • the machine constructed in accordance with the principles of the invention enables the providing of axial and radial flow paths which are mutually substantially independent, i.e., there is little, if any, mutual influencing of each other With respect to shape and required space, whereby substantially optimal performance with regard to expansion and compression may be effected.
  • the inventive machine also makes possible such coordination of the two changes of state, i.e., compression and expansion, relative to flow and pressure coeflicients whereby substantially the same quantities of the same working medium can be used in the same thermodynamic process. To effect further equalization, it is merely necessary to arrange successively occurring pure compression or pure expansion stages.
  • FIG. 6 wherein there is schematically depicted an application of a machine constructed in accordance with the principles of the invention for a gas turbine system
  • the designating numeral 1 denotes fuel injection, fuel being injected into a combustion chamber 2.
  • the hot combustion gases produced therein are fed to the expansion channels of the machine 5, such feeding being designated by the numeral 3.
  • Air is fed into machine 5, such feeding being designated by the numeral 4.
  • the air fed to machine 5 is heated therein, partially by the compression process and partially by inner regenerative preheating.
  • machine 5 can comprise a plurality of pure compression stages and the heated air may be brought to a necessary pressure therein.
  • the heated air at the proper pressure enters and then leaves an external regenerative preheater 7, such entering being designated by the numeral 6 and such leaving being designated by the numeral 8, to enter combustion chamber 2.
  • the wall thicknesses between the flow paths are chosen such that they have both sufiicient mechanical strength for the transmission of the differential energy (expansion energy minus compression energy) to the shaft and for an intensive heat transfer from channels wherein a working medium fluid is expanded at a high temperature 'level to channels wherein compression takes place at a low temperature level.
  • FIGS. 7, 8 and 9 show an embodiment of a fluid flow machine according to the invention more in detail, FIG. 7 being an axial section, FIG. 8 a top view onto a rotor Wheel with a sectional illustration of the stationary guiding structure, and FIG. 9 a cross section of the rotor wheel.
  • the flow paths are schematically entered.
  • the flow cross sections are shown to be substantially equal, whereas in reality they are narrower in the regions of higher pressures than in the regions of lower pressures.
  • FIG. 7 shows at 21 a portion of the rotor shaft.
  • the housing 22 of the machine comprises the stationary guideblade structures. Only one stage 23 of the rotor is shown in full axial width, the next following stage 24 of the rotor being partly broken away.
  • the various seals between rotor and housing are denoted by 25.
  • the working medium to be expanded enters at 26 as indicated by an arrow.
  • the working medium to be compressed enters in the same direction at 27 in the vicinity of the rotor shaft 21.
  • the heating stage may also be designed as a firing chamber in which a suitable fuei is burned, the air or other oxygen-supplying gas required for the combustion being previously compressed.
  • the pressure conduit 26 (FIG. 7) serves to supply the gases to be expanded and consequently has a relatively small cross section in comparison with the suction duct 27 whose cross section is considerably larger.
  • the medium to be reduced in pressure for performing work passes first through a nozzle group 31 in the machine housing 22.
  • This nozzle group forms part of the guiding structure.
  • the medium enters into the flow channel 33 of the first rotor wheel 23.
  • Guide blades 43 are provided at the inlet of the rotor flow channel 33.
  • channel 33 there occurs a reversal in flow direction so that the flow passes tangentially from the rotor channel 34 into a stationary channel 35 of the housing structure 22.
  • the working medium now passes through the direction reversing channel 36 and leaves the stationary structure through a nozzle group 37 which forms part of the second rotor-wheel stage.
  • the working medium now passes between a set of guiding blades 44 and thence through the flow channels of the second rotor wheel, and so forth.
  • the transitions between the stationary guiding structure and the rotating wheels likewise extend in substantially tangential directions.
  • the flow of the working medium to be compressed extends along analogous paths. After the medium enters into the housing at 27, it passes at 42 into the direction reversing channel 43 of the first rotor wheel 23. The medium then leaves the blades of the rotor wheel 23 at 54 and enters at 55 into the first stationary guide wheel structure of the housing 22. The direction reversing channel 46 of the first guiding stage terminates at 47 where the working medium passes into the flow channel 48 of the second rotor wheel 24.
  • the inner channel ports are located in the vicinity of the axis of rotation. If desired, however, the reversal-s in flow direction may all be located in the outer region of the rotor wheels'so that the inner peripheral speed considerably contributes to the energy conversion. In this case it is sometimes preferable to have the inner channel ports also terminate laterally in axial blades as is the case in the illustrated embodiments for the outer channel ports.
  • a fluid fiow machine for handling at least one working medium fluid and comprising rotor wheel and guide stages mounted on a rotatable axially centrally disposed shaft therein and wherein working medium fluid is caused to flow in a substantially axial direction in the center zone and substantially tangentially at the outer peripheries of said rotor stages; the improvement which comprises a centripetal axial flow path system and a centrifugal radial flow path system in at least one of said rotor wheel stages, said flow path systems being uninterconnected and intersecting in the center zone of said one rotor wheel stage, said working medium fluids flowing through said centripetal flow path system axially in the same direction and through said centrifugal flow path system radially in opposite directions whereby in said centripetal flow path system there is effected a working medium fluid expansion and whereby in said centrifugal flow path system there is effected a working medium fluid compression.
  • said rotor wheel and guide stages comprising channels which terminate in surfaces which are cylindrical to the axis of rotation.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Textile Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
US448389A 1964-04-15 1965-04-15 Rotary fluid flow machine Expired - Lifetime US3306574A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEB0076342 1964-04-15

Publications (1)

Publication Number Publication Date
US3306574A true US3306574A (en) 1967-02-28

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Application Number Title Priority Date Filing Date
US448389A Expired - Lifetime US3306574A (en) 1964-04-15 1965-04-15 Rotary fluid flow machine

Country Status (8)

Country Link
US (1) US3306574A (de)
AT (1) AT255840B (de)
BE (1) BE662374A (de)
CH (1) CH455399A (de)
DE (1) DE1426793A1 (de)
GB (1) GB1066531A (de)
NL (1) NL6502044A (de)
SE (1) SE311099B (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3726605A (en) * 1969-06-30 1973-04-10 H Bachl Fluid-flow machine
US3748057A (en) * 1972-01-11 1973-07-24 M Eskeli Rotary compressor with cooling
US3828573A (en) * 1972-01-11 1974-08-13 M Eskeli Heating and cooling wheel
US3874190A (en) * 1973-10-30 1975-04-01 Michael Eskeli Sealed single rotor turbine
US3948588A (en) * 1973-08-29 1976-04-06 Bakerdrill, Inc. Swivel for core drilling
US4029431A (en) * 1974-08-23 1977-06-14 Herbert Bachl Fluid-flow machine
US20090035121A1 (en) * 2007-07-31 2009-02-05 Dresser, Inc. Fluid Flow Modulation and Measurement
DE102015222241A1 (de) * 2015-11-11 2017-05-24 Mahle International Gmbh Hydraulikantrieb

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2821233C2 (de) * 1978-05-16 1983-07-28 GETEWENT Gesellschaft für technische und wissenschaftliche Energieumsatzentwicklungen mbH, 8950 Kaufbeuren Scheibenförmiges Laufrad einer Strömungsmaschine
CZ302324B6 (cs) * 2008-07-16 2011-03-09 Majchráková@Viktória Expanzní dvoustupnová turbína

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2382564A (en) * 1943-09-16 1945-08-14 Laval Steam Turbine Co Turbine system
US2410259A (en) * 1941-12-13 1946-10-29 Fed Reserve Bank Elastic fluid mechanism
US2841362A (en) * 1952-04-14 1958-07-01 Yeomans Clifton Multistage turbine
US2911189A (en) * 1953-07-20 1959-11-03 Ohain Hans J Pabst Von Fluid machine
US2988266A (en) * 1959-01-19 1961-06-13 Hughes John Wesley Self-cooled radial rotor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2410259A (en) * 1941-12-13 1946-10-29 Fed Reserve Bank Elastic fluid mechanism
US2382564A (en) * 1943-09-16 1945-08-14 Laval Steam Turbine Co Turbine system
US2841362A (en) * 1952-04-14 1958-07-01 Yeomans Clifton Multistage turbine
US2911189A (en) * 1953-07-20 1959-11-03 Ohain Hans J Pabst Von Fluid machine
US2988266A (en) * 1959-01-19 1961-06-13 Hughes John Wesley Self-cooled radial rotor

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3726605A (en) * 1969-06-30 1973-04-10 H Bachl Fluid-flow machine
US3748057A (en) * 1972-01-11 1973-07-24 M Eskeli Rotary compressor with cooling
US3828573A (en) * 1972-01-11 1974-08-13 M Eskeli Heating and cooling wheel
US3948588A (en) * 1973-08-29 1976-04-06 Bakerdrill, Inc. Swivel for core drilling
US3874190A (en) * 1973-10-30 1975-04-01 Michael Eskeli Sealed single rotor turbine
US4029431A (en) * 1974-08-23 1977-06-14 Herbert Bachl Fluid-flow machine
US20090035121A1 (en) * 2007-07-31 2009-02-05 Dresser, Inc. Fluid Flow Modulation and Measurement
DE102015222241A1 (de) * 2015-11-11 2017-05-24 Mahle International Gmbh Hydraulikantrieb

Also Published As

Publication number Publication date
BE662374A (de) 1965-10-12
SE311099B (de) 1969-05-27
DE1426793A1 (de) 1969-03-20
CH455399A (de) 1968-07-15
NL6502044A (de) 1965-10-18
AT255840B (de) 1967-07-25
GB1066531A (en) 1967-04-26

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