WO2003050392A1 - Turbine a courant pilote - Google Patents

Turbine a courant pilote Download PDF

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Publication number
WO2003050392A1
WO2003050392A1 PCT/GB2002/005227 GB0205227W WO03050392A1 WO 2003050392 A1 WO2003050392 A1 WO 2003050392A1 GB 0205227 W GB0205227 W GB 0205227W WO 03050392 A1 WO03050392 A1 WO 03050392A1
Authority
WO
WIPO (PCT)
Prior art keywords
blades
nozzles
turbine
turbines
rotor
Prior art date
Application number
PCT/GB2002/005227
Other languages
English (en)
Inventor
Ibrahim Omran Liguery
Omar Omran Ghoweri
Original Assignee
Science-Logic Company Limited
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 Science-Logic Company Limited filed Critical Science-Logic Company Limited
Priority to AU2002339197A priority Critical patent/AU2002339197A1/en
Priority to GB0408635A priority patent/GB2396388A/en
Publication of WO2003050392A1 publication Critical patent/WO2003050392A1/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
    • F01D1/18—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means
    • 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
    • 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
    • F01D1/34—Non-positive-displacement machines or engines, e.g. steam turbines characterised by non-bladed rotor, e.g. with drilled holes

Definitions

  • the main principle of this work is to build turbines with 'horizontal Nozzles and blades with certain 2 angles to each other where the blades during their rotation will guide themselves to be under sustain and continuos jet pressure from the Nozzles and in the direction of motion (rotation) of the blades to achieve the highest efficiency possible.
  • a- The blades for single stage and for what I call continuous stages turbines (as a replacement for the existing several stages turbines) can be built horizontally (assembled on or machined in) directly on certain area 360° around the cylindrical surface of the rotor itself.
  • the Nozzles (single stage, continuous stages) can be built horizontally (assembled in or machined in) directly 360° around the body of the cylindrical surface of the housing (casing) of the turbine.
  • the alignment of the Nozzles will be in opposite alignment to the blades and with reference to the axis of the cylindrical housing which will be the same as the axis of the shaft of the concerned turbine [e.g.
  • Figure 1 shows a schematic diagram of flat section from the rotor, line A is a mark where blades start, 1-8 left doted lines marking the alignment of the blades with x angle 10 (45°) in relation to the direction of the rotor axis 11, Line B marking where the blades ends to 360° around grove between line B and line C;
  • Figure 2 shows a schematic diagram of flat section from rotor, 1-8 the blades
  • Figure 3 a schematic diagram of flat section from rotor and 360 around grove 9;
  • Figure 4 is a schematic diagram of flat section from Pilot Stream Rotor, 1-8 the blades have been machined in or assembled on with angle 13 (45°) between the tangent of the rotor 16 and the blades (blade 7);
  • Figure 6 shows a schematic diagram of cross section from Pilot Stream Rotor
  • Figure 7 shows a schematic diagram of flat section from the cylindrical casing, line A is a mark where Nozzles start, 1-8 right doted lines marking the alignment of the Nozzles with x angle 10 (45°) in relation to the direction of the casing axis 11, line B marking where the Nozzles ends, line C marking of positions of the outlet connectors 9;
  • Figure 8 shows a schematic diagram of flat section from casing, 1-8 the Nozzles
  • Figure 9 is a simple schematic diagram outlining a flat section from Pilot
  • Stream Cylindrical Casing Turbine 1-8 the Nozzles have been machined in or assembled in with V shape 17, 18 represent the inside section of the Nozzles with length equal to each one of the blades wide and the Nozzles width ranging from minimum and up to any one of the blades wide;
  • Figure 10 shows a schematic diagram outlining section from Pilot Stream
  • Cylindrical Casing, 1-8 the Nozzles have been machined in or assembled in with V shape 17, 18 represent the inside section of the Nozzles with length equal to each one of the blades wide and the Nozzles wide is ranging from minimum and up to any one of the blades wide, 19 is the inside surface of the casing, 20 is the thickness of the cylindrical casing for housing the blades
  • Figure 11 shows a schematic diagram of cross section from Pilot Stream
  • Cylindrical Casing Turbine 1-8 the Nozzles top side have been machined in or assembled in with N shape 17, 18 represent the inside section of the Nozzles with length equal to each one of the blades wide and the Nozzles width is ranging from minimum and up to any one of the blades wide, 19 is the inside surface of the casing;
  • Figure 12 shows a schematic diagram of cross section from Pilot Stream
  • Nozzles top side have been machined in or assembled in with V shape 17, 21 represent the jet fluid via Nozzles to strike on the blades all time and with right angle;
  • Figure 13 is a schematic diagram of overall single stage of Pilot Stream Rotor
  • Figure 14 shows a schematic diagram of overall single stage Pilot Stream
  • Figure 15 shows a schematic diagram of Single Stage Rotor and its Casing of
  • Figure 16 is showing a schematic diagram of Single Stage of Pilot Stream
  • Turbine A for direct injection
  • B for indirect injection inlet 1, outlet 2, jacket for indirect injection 3;
  • Figure 17 is a schematic diagram of: [17-A; 1 is the axis of the turbine, 2 are the blades aligned to the turbine axis, 3 is the angle of the blades alignment, 4 are the Nozzles aligned to the turbine axis, 5 is the angle of the Nozzles alignment,
  • 6 is the direction of the pressurized fluid along the Nozzles alignment
  • 8-9 represent the effective area between Nozzles and blades], [17-A, B, C and D; marking the striking positions of the Nozzles on the bales and the direction of the rotation of the rotor 7];
  • Figure 18 shows a schematic diagram of Continuous Stages Pilot Stream
  • Figure 19 shows a schematic diagram of Several Stage Pilot Stream Turbines
  • Figure 20 shows a schematic diagram of Single Stage Wheel of Pilot Stream
  • a single stage turbine is that turbine which has each one of its inside area Nozzles 3 length is equal exactly to the wide of any one of the single used blades and as we will see in this section.
  • Each one of the eight blades around the rotor must have exact 5 wide and identical to each one of the rest of the blades and as its clear each one of the blades has wide is equal to y divided by 8 (the number of the blades).
  • FIG. 17 shows only one blade 2 and one Nozzle 4 (for simplicity only) of
  • Continuous Stages Turbine can be identified by that turbine which has its Nozzles length (effective area 9-8 fig. 17 A) acceded the wide of any one of its blades. Apart from this point which is related to the force needed to be generated, there is a complete similarity between single stage and continuous stages turbines (figure 18).
  • the force can be increased by the percentage increase of the Nozzles length related to the Nozzles length of the concerned single stage turbine; if the Nozzles and blades length (keeping the extra length we chosen and as mentioned before for the blades to be added later) were increased by e.g. three times of the length of its original single stage Nozzles length, this will lead to, that each of the Nozzles will striking on a number of blades three times more than the number of blades been before, this will lead to, that the force will be generated by this new continuous stages turbine will increase by three times. So the increase in the effective area (figure 17 A 8-9) of single stage turbines will transfer this category of turbines to the continuous stages turbines and this increase will respond directly to the force or power which can be generated.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Hydraulic Turbines (AREA)

Abstract

Selon l'invention, des ailettes horizontales (2) sont disposées sur 360 ° autour du rotor, et des buses horizontales (4) sont disposées sur 360 ° autour des ailettes, en étant alignées avec le même angle (3) et (5) et opposées les unes aux autres, par rapport à l'axe de leur tige (1) menant au bâtiment des turbines (outils de production mécanique) avec un couple maximal et un angle idéal dans la direction de rotation (7), ce qui permet d'obtenir une nouvelle génération de turbines à très haut rendement.
PCT/GB2002/005227 2001-12-11 2002-11-20 Turbine a courant pilote WO2003050392A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
AU2002339197A AU2002339197A1 (en) 2001-12-11 2002-11-20 Pilot stream turbine
GB0408635A GB2396388A (en) 2001-12-11 2002-11-20 Pilot stream turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0129533.6 2001-12-11
GB0129533A GB0129533D0 (en) 2001-12-11 2001-12-11 Pilot stream turbine

Publications (1)

Publication Number Publication Date
WO2003050392A1 true WO2003050392A1 (fr) 2003-06-19

Family

ID=9927344

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2002/005227 WO2003050392A1 (fr) 2001-12-11 2002-11-20 Turbine a courant pilote

Country Status (3)

Country Link
AU (1) AU2002339197A1 (fr)
GB (2) GB0129533D0 (fr)
WO (1) WO2003050392A1 (fr)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR673932A (fr) * 1929-04-24 1930-01-21 Moteur rotatif
GB381699A (en) * 1930-09-22 1932-10-13 Gabriel Bertin Improvements in or relating to rotary engines operating with or upon an elastic fluid
US1902439A (en) * 1930-12-30 1933-03-21 Edward T Skeffington Flying worm steam motor
FR1522468A (fr) * 1967-03-15 1968-04-26 Turbine à gaz à jet tangentiel
US3490851A (en) * 1967-09-29 1970-01-20 Edward Krzyszczuk Circular flow air compressor or diffusion motor
US3592558A (en) * 1969-12-10 1971-07-13 Robert G Bandy Pressure fluid operated motor
DE2213841A1 (de) * 1972-03-22 1973-09-27 Friedrich Rabe Drehscheiben-motor
US4141671A (en) * 1977-04-20 1979-02-27 Tarsoly Balazs K Tool gas turbine motor
GB2072757A (en) * 1979-12-08 1981-10-07 Hall R Fluid turbine having spiral chambers

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR673932A (fr) * 1929-04-24 1930-01-21 Moteur rotatif
GB381699A (en) * 1930-09-22 1932-10-13 Gabriel Bertin Improvements in or relating to rotary engines operating with or upon an elastic fluid
US1902439A (en) * 1930-12-30 1933-03-21 Edward T Skeffington Flying worm steam motor
FR1522468A (fr) * 1967-03-15 1968-04-26 Turbine à gaz à jet tangentiel
US3490851A (en) * 1967-09-29 1970-01-20 Edward Krzyszczuk Circular flow air compressor or diffusion motor
US3592558A (en) * 1969-12-10 1971-07-13 Robert G Bandy Pressure fluid operated motor
DE2213841A1 (de) * 1972-03-22 1973-09-27 Friedrich Rabe Drehscheiben-motor
US4141671A (en) * 1977-04-20 1979-02-27 Tarsoly Balazs K Tool gas turbine motor
GB2072757A (en) * 1979-12-08 1981-10-07 Hall R Fluid turbine having spiral chambers

Also Published As

Publication number Publication date
AU2002339197A1 (en) 2003-06-23
GB0408635D0 (en) 2004-05-19
GB2396388A (en) 2004-06-23
GB0129533D0 (en) 2002-01-30

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