WO2003078798A1 - Roue a aubes de turbine - Google Patents

Roue a aubes de turbine Download PDF

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Publication number
WO2003078798A1
WO2003078798A1 PCT/DE2003/000823 DE0300823W WO03078798A1 WO 2003078798 A1 WO2003078798 A1 WO 2003078798A1 DE 0300823 W DE0300823 W DE 0300823W WO 03078798 A1 WO03078798 A1 WO 03078798A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine impeller
channels
impeller according
drive medium
grooves
Prior art date
Application number
PCT/DE2003/000823
Other languages
German (de)
English (en)
Inventor
Christian Dinger
Original Assignee
Christian Dinger
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 Christian Dinger filed Critical Christian Dinger
Priority to AU2003223864A priority Critical patent/AU2003223864A1/en
Priority to DE10391016T priority patent/DE10391016D2/de
Publication of WO2003078798A1 publication Critical patent/WO2003078798A1/fr

Links

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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/32—Non-positive-displacement machines or engines, e.g. steam turbines with pressure velocity transformation exclusively in rotor, e.g. the rotor rotating under the influence of jets issuing from the rotor, e.g. Heron turbines
    • 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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • 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
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction

Definitions

  • the invention relates to a turbine impeller according to the preamble of claim 1.
  • Turbine impellers are known in the most varied of embodiments. Usually they have inclined blades with respect to the direction of flow through the drive medium, which are acted upon by the drive medium and thereby set the blades into a rotary movement. The disadvantage of some known turbine impellers is that their efficiency is not optimal. The areas of application are also limited.
  • DE 33 43 752 A1 shows an open impeller for turbomachines, in particular for centrifugal pumps, of the type specified at the outset.
  • the turbine impeller is formed by a body which is composed of individual impeller segments. These impeller segments are attached to a common hub.
  • the impeller segments each consist of an impeller wall segment and an integrally formed blade.
  • the channels formed in this way run with respect to the axis of rotation, viewed in the direction of the inflow, essentially in a circular, spiral or helical shape.
  • the disadvantage of this known open impeller for turbomachines is that due to the central hub, the drive medium must be injected very far away from the axis of rotation, so that the efficiency of the turbine impeller is not optimal.
  • the invention is based on the objective of improving the efficiency of a turbine impeller of the type specified in the introduction.
  • the basic idea of the turbine impeller according to the invention is to design the blades as guide channels for the drive medium.
  • the number of blades, the height and width ratio and the diameter are freely selectable.
  • This creates a long movement path of the drive medium, so that a high degree of efficiency is achieved.
  • the drive medium can be injected centrally or almost centrally by means of the construction of the turbine impeller according to the invention. This impacts all the blades of the turbine impeller. In this way, a simple control of the speed and thus the power is created via one or possibly several nozzles.
  • the flow of the turbine impeller is - with a single nozzle - via the tip or - with several nozzles - slightly offset with respect to the tip and at the same time deflected in all blades. This ensures an optimal flow and all the blades are pressurized with the drive medium.
  • the development according to claim 2 has the advantage that an optimal torque is exerted on the turbine impeller and thus a high speed is brought about.
  • the development according to claim 3 creates an optimal channel shape, by means of which the drive medium is optimally guided.
  • the channels With regard to the radial extent of the channels with respect to the axis of rotation, their width increases in the radial direction according to the development in claim 4. Alternatively, the width of the channels can preferably also decrease towards the outside.
  • the development according to claim 5 creates a compact design of the turbine impeller in that a large part of the turbine impeller cross section is covered with channels.
  • the development according to claim 6 creates an optimal flow of the drive medium in the channels.
  • a preferred development of the turbine impeller according to the invention proposes claim 7. This creates a type of rotating impeller with flower-like troughs, wherein the molded body can be made of plastic or metal.
  • the kinetic energy of the drive beam is transferred to the rotating impeller and taken from the shaft attached to the underside. This results in a variety of properties and advantages.
  • This turbine impeller is characterized by low manufacturing costs and a compact and small design.
  • the turbine impeller is also very robust. After all, there is no cavitation and there is no risk of clogging with flotsam.
  • the molded body is formed from one piece. Accordingly, the turbine impeller can be cast in a mold. A development of this suggests that the channels are formed as channels in the top of the molded body.
  • the molded body is preferably made of one piece.
  • the channel-shaped grooves can be formed relatively deep in the molded body.
  • the central tip is then preferably sunk. This design of the channel-shaped channels has the advantage (particularly with regard to the recessed configuration of the tip) that the injected drive medium almost completely gets into the channel-shaped channels and is not lost.
  • Fig. 1 is a perspective view of a first embodiment of the
  • FIG. 2 shows a plan view of the turbine impeller in FIG. 1;
  • FIG. 3 shows a side view of the turbine impeller in FIG. 1;
  • FIG. 4 shows a perspective view of a second embodiment of the turbine impeller
  • FIG. 5 is a top view of the turbine impeller in FIG. 4;
  • FIG. 6 shows a side view of the turbine impeller in FIG. 4.
  • the turbine impeller of the first embodiment in FIGS. 1 to 3 consists of a one-piece molded body 1, in particular made of metal or plastic.
  • this molded body 1 blades in the form of grooves 2 with vertical side walls 3 are formed on the inflow side.
  • the course of these channels 2 is the combination of a spiral with a helix.
  • the side walls 3 converge to a point in the region of the axis of rotation.
  • the channels 2 widen in the direction of flow.
  • this On the other side of the molded body 1 with respect to the tip, this has a shaft 4.
  • the drive medium is injected in the flow direction A1 through a nozzle, not shown.
  • the drive medium is distributed over a total of six channels 2 (and thus acts on all blades) and flows in the direction of the outlet end of the channels 2.
  • the outflow direction A2 is indicated.
  • the shaped body 1 On the underside, the shaped body 1 has the shaft 4, which decreases the kinetic energy of the beam.
  • the turbine impeller of the second embodiment in FIGS. 4 to 6 has a solid molded body 1 made of metal.
  • the four channels 2 are formed relatively deep, the course of these channels 2 also being the combination of a spiral or a partial circle with a spiral.
  • the grooves 2 converge to a tip, which is sunk on the upstream side with respect to the highest point of the molded body 1.
  • the width of the channels 2 is reduced in this second embodiment.
  • this body On the other side of the molded body 1 with respect to the tip, this body also has a shaft 4 in this embodiment.
  • the principle of operation is the same as in the first embodiment.
  • the centrally injected drive medium acts on all blades or troughs 2 and flows in the direction of the outlet end of the troughs.
  • the width of this second embodiment decreases towards the outside.
  • a cover (not shown) for the channels 2 can also be provided.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Hydraulic Turbines (AREA)

Abstract

L'invention concerne une roue à aubes pointue d'une turbine, recevant un flux de façon centrale, présentant en tant qu'aubes des canaux (2) délimités par des parois latérales, lesdits canaux s'étendant de manière essentiellement combinée de façon circulaire, spiralée ou hélicoïdale. Par ailleurs, les canaux (2) sont formés dans un corps moulé massif (1) et les aubes s'étendent directement à partir de la pointe de la roue recevant le flux.
PCT/DE2003/000823 2002-03-15 2003-03-14 Roue a aubes de turbine WO2003078798A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
AU2003223864A AU2003223864A1 (en) 2002-03-15 2003-03-14 Turbine blade wheel
DE10391016T DE10391016D2 (de) 2002-03-15 2003-03-14 Turbinenlaufrad

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10211423.4 2002-03-15
DE2002111423 DE10211423B4 (de) 2002-03-15 2002-03-15 Turbinenlaufrad

Publications (1)

Publication Number Publication Date
WO2003078798A1 true WO2003078798A1 (fr) 2003-09-25

Family

ID=27815654

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2003/000823 WO2003078798A1 (fr) 2002-03-15 2003-03-14 Roue a aubes de turbine

Country Status (3)

Country Link
AU (1) AU2003223864A1 (fr)
DE (2) DE10211423B4 (fr)
WO (1) WO2003078798A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006005843B3 (de) * 2005-11-17 2007-05-10 Frank Eckert Reaktionsrad zur Verwendung in Turbinen- bzw. Verdichteranordnungen
DE102012106810B4 (de) * 2012-07-26 2020-08-27 Ihi Charging Systems International Gmbh Laufrad für eine Fluidenergiemaschine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2460849A (en) * 1945-07-16 1949-02-08 Jurg A Senn Constant speed rotor for turbines
FR80110E (fr) * 1961-07-17 1963-03-15 Commissariat Energie Atomique Turbo-pompe
DE1628210A1 (de) * 1965-09-22 1971-02-25 Budd Co Turbogeblaeserad-Zusammenbau und Verfahren zur Herstellung desselben
CH529292A (de) * 1970-11-27 1972-10-15 Hollymatic Corp Druckmediummotor
US4302147A (en) * 1980-03-06 1981-11-24 General Motors Corporation Lightweight radial flow fluid machine with fluid bearing sealed flexible blades
DE3343752A1 (de) * 1983-12-02 1985-06-20 Philipp Hilge Gmbh, 6501 Bodenheim Offenes laufrad fuer stroemungsmaschinen
AU571324B2 (en) * 1984-12-17 1988-04-14 Culhane, Terence William Radial flow gas turbine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2460849A (en) * 1945-07-16 1949-02-08 Jurg A Senn Constant speed rotor for turbines
FR80110E (fr) * 1961-07-17 1963-03-15 Commissariat Energie Atomique Turbo-pompe
DE1628210A1 (de) * 1965-09-22 1971-02-25 Budd Co Turbogeblaeserad-Zusammenbau und Verfahren zur Herstellung desselben
CH529292A (de) * 1970-11-27 1972-10-15 Hollymatic Corp Druckmediummotor
US4302147A (en) * 1980-03-06 1981-11-24 General Motors Corporation Lightweight radial flow fluid machine with fluid bearing sealed flexible blades
DE3343752A1 (de) * 1983-12-02 1985-06-20 Philipp Hilge Gmbh, 6501 Bodenheim Offenes laufrad fuer stroemungsmaschinen
AU571324B2 (en) * 1984-12-17 1988-04-14 Culhane, Terence William Radial flow gas turbine

Also Published As

Publication number Publication date
DE10391016D2 (de) 2005-02-10
DE10211423A1 (de) 2003-10-09
DE10211423B4 (de) 2004-02-19
AU2003223864A1 (en) 2003-09-29

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