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
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades
  • F01D5/14—Form or construction
  • F01D5/141—Shape, i.e. outer, aerodynamic form
  • F01D5/145—Means for influencing boundary layers or secondary circulations
• • 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
  • F01D1/20—Non-positive-displacement machines or engines, e.g. steam turbines without stationary working-fluid guiding means traversed by the working-fluid substantially axially
• • 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
  • F01D5/12—Blades
  • F01D5/14—Form or construction
  • F01D5/141—Shape, i.e. outer, aerodynamic form
  • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
  • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2200/00—Mathematical features
  • F05D2200/20—Special functions
  • F05D2200/26—Special functions trigonometric
  • F05D2200/261—Sine
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2200/00—Mathematical features
  • F05D2200/20—Special functions
  • F05D2200/26—Special functions trigonometric
  • F05D2200/262—Cosine
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2200/00—Mathematical features
  • F05D2200/20—Special functions
  • F05D2200/26—Special functions trigonometric
  • F05D2200/264—Cotangent
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10S415/00—Rotary kinetic fluid motors or pumps
  • Y10S415/914—Device to control boundary layer

Definitions

• the present invention relates to a turbine stage comprising a circular fixed grid followed by a circular mobile grid, each grid comprising vanes mounted between a floor and a ceiling.
• This series of blades thus defines a series of channels traversed by a fluid, each channel being limited by two consecutive blades and by the floor and the ceiling.
• the direction of radial variation of the static pressure which decreases from the top to the base, amplifies the secondary vortex of the ceiling and opposes the secondary vortex of the plancner, as it is visible in Figure 2.
• the direction of radial variation of the intergrid static pressure is therefore harmful to the ceiling and favorable to the base.
• the absolute value of the radial static pressure gradient at the base has no reason to be just that necessary to minimize secondary losses.
• the invention relates to a turbine stage comprising a circular fixed grid followed by a circular mobile grid, each grid comprising blades mounted between a plancner and a ceiling of revolution around the axis of the turbine, the pitch of the blades of the fixed grid being L S at the ceiling and L B at the plank and the exit angle of the jet of fluid from the fixed grid with the plane of this grid being ⁇ 1S in line with the ceiling and ⁇ 1B in line with the floor, in this case the distance to the axis of the ceiling decreases from the entry of the fixed grid towards the exit of the fixed grid or it has the value r S , then goes increasing from the entry of the movable grid where it has the value r S until leaving the movable grid.
• Such a turbine stage is known from British Patent No. 596,784.
• the curvature of the floor and the ceiling is calculated so that the pressure is constant in the intergrid space (at the outlet of the fixed grid) from the bottom to the top of this space, it that is, the radial static pressure gradient is zero.
• the meridian curvature of the ceiling in line with the intergrid plane is substantially equal
• the invention also relates to a turbine stage comprising a circular fixed grid followed by a circular mobile grid comprising vanes mounted between a floor and a ceiling of revolution around the axis of the turbine, the pitch of the vanes of the fixed grid being L S at the ceiling and L B at the floor and the exit angle of the jet of fluid from the fixed grid with the plane of this grid being ⁇ 1S to the right of the ceiling and ⁇ 1B to the right of the floor in which the distance to l plancner axis varies continuously from the entry of the fixed grid towards the exit of said fixed grid where it reaches an extremum r composer, then varies in the opposite direction in a continuous way from the entry of the grid mobile where it has the value r B until the mobile grid exits.
• This turbine stage is also known from British Patent No. 596,784.
• the meridian curvature of the floor of the fixed grid in line with the intergrid plane is substantially equal to the difference
• the extremum r B being a minimum when the difference is negative and a maximum when the difference is positive.
• the radial gradient of intergrid static pressure is not zero, as in the British patent, but is equal to the tangential gradient of intergrid static pressure, which has the effect of confining the disturbed zone to the floor in a relatively small flow passage section.
• the two measurements can be combined on the ceiling and on the floor so as to confine the disturbed area on the ceiling and that on the floor in a relatively small flow passage section.
• ⁇ with ⁇ > 1
• the tangential gradient of static pressure in the vicinity of the ceiling at the outlet of the fixed grid the meridian curvature of the ceiling the fixed grid to the right of the intergrid plane is substantially equal to
• the turbine stage comprises the 2 combined variants, which makes it possible, on the one hand, to reduce the intensity of the vortices on the ceiling and on the floor and, on the other hand, to confine in a narrow area.
• the distance to the axis of the ceiling varies according to a curve having a maximum at the entry of the fixed grid and at the exit of the movable grid and a minimum in the intargrilated plane.
• FIG. 1 and 2 show part of a fixed grid of a conventional turbine stage.
• FIG. 3 represents the variation curves of the intergrille pressure as a function of the distance r from the axis.
• FIG. 4 schematically represents a fixed grid belonging to a turbine stage according to the invention.
• FIG. 5 shows a section of a fixed grid according to Figure 4 at the ceiling.
• Figure ⁇ shows a section of a fixed grid according to Figure 4 at floor level.
• FIG. 7 represents a first embodiment of the stage of this turbine according to the invention.
• FIG. 8 represents a second embodiment of the turbine stage according to the invention.
• FIG. 9 shows a third embodiment of the turbine stage according to the invention.
• FIG. 10 represents a fourth embodiment of the turbine stage according to the invention.
• FIG. 11 represents a fifth embodiment of the turbine stage according to the invention.
• Figures 12 and 13 represent a simplified version of the embodiments of Figures 10 and 11.
• Figures 14 and 15 show a modified turbine still according to the invention comprising means reducing the tangential static pressure gradient of the fixed grid.
• FIG. 1 there are shown two blades A and B which are part of a fixed grid and whose foot is fixed on a floor 1 and the head on a ceiling 2.
• the floor and the ceiling are usually cylindrical or frustoconical surfaces .
• the lower surface of dawn 3, the upper surface of dawn A, the floor 1 and the ceiling 2 define a channel 3.
• the flow is done by following healthy nets such as (vs).
• the fluid threads are orthogonal to the isobars and follow the directions shown (1), (m) then begin to swirl as soon as they hit the upper surface of dawn (A ).
• FIG. 2 it is indicated at the outlet of a fixed grid in the vicinity of the upper surface of dawn At the static pressure p s in the vicinity of the ceiling and the static pressure p B in the vicinity of the floor of the grid fixed blades.
• the pressure ptician is greater than the pressure p, so that in the vicinity of the ceiling, the secondary vortex is amplified while it is damped in the vicinity of the floor.
• the static pressure constantly decreases from the ceiling to the floor.
• the evolution of the intergriile static radial pressure in a conventional turbine is represented in FIG. 3 by the curve in solid schematic line which starts from r B radius of the planoner in the interplan grid up to r S radius of the ceiling in the same plane and the dotted curve diagrams the desired evolution.
• the meridian of the ceiling and / or the vein plank of the fixed grid must have a curved shape.
• FIG. 5 there is shown a cylindrical section of the top of the blades A and 3 of a fixed grid.
• the angle ⁇ 1S designates the injection angle of the jet (in the following mobile grid) with the grid front in line with the ceiling, V 1 the absolute speed intergrille, V u the tangent component of the absolute intergriile speed and V m the projection of the absolute speed intergrille in the meridian plane.
• L S represents the pitch of the blades on the ceiling
• the year ⁇ 1S is calculated very easily: from this the relation on ( ⁇ S being the width of the neck between the blades A and B in the vicinity of the ceiling).
• FIG. 6 there is shown a cylindrical section of the foot of the blades A and B of a fixed grid.
• the angle ⁇ 1S designates the angle of injection of the jet (in the following mobile grid) with the front of grills.
• the pitch of vanes A and B on the floor is L B
• the width of the neck is o ⁇ B
• the angle ⁇ 1 B can be calculated very easily from the relation
• the radial gradient of intergriile static pressure is determined by the following formula:
• ⁇ 1 being the angle of injection of the jet with this grid front at level r and L is the spacing between 2 consecutive blades at the same level. is an experimental coefficient and ⁇ P is the pressure drop in the fixed grid.
• V 1 2 V u 2 + V m 2
• FIG 7 there is shown in section a turbine stage according to the invention in which minimized the effect of secondary losses in the vicinity of the ceiling.
• the fluid for example, goes along the arrow from right to left.
• the stage comprises a fixed grid 4 followed by a movable grid 5.
• the fixed grid comprises vane cases 6 mounted between a plancner 1 and a ceiling 2.
• the movable grid 5 comprises vanes 7 mounted between a floor 11 and a ceiling 12.
• the ceiling 2 of the grid 4 is a surface of revolution around the axis of the turbine, the meridian of which is a half-arc of a sinusoid which approaches the axis, from the inlet to the outlet.
• the ceiling 12 of the grid 5 is substantially symmetrical with the ceiling 2 with respect to the intergrid plane which is perpendicular to the axis of the turbine.
• the floor is that of a conventional turbine.
• FIGS. 8 and 9 there is shown in section a turbine stage according to the invention in which the effect of the secondary losses in the vicinity of the plancner has been minimized.
• the numbers of references are those of the references of figure 7 in which one added 100.
• the floor 101 of the fixed grid 104 is a surface of revolution around the axis of the tooth turbine.
• the meridian is a half-arc of a sinusoid which moves closer to the axis, from the entry to exit.
• the floor 111 of the movable grid 105 is substantially symmetrical with the floor 101 with respect to the intergrid plane.
• the meridian of the floor 111 'of the movable grid 105 is the symmetrical of the meridian of the floor 101' with respect to the intergrid plane.
• FIG. 10 shows a turbine stage according to the invention with a ceiling similar to that of the stage in FIG. 7 and a plancner similar to that in FIG. 8.
• the reference numbers have been increased by 200 by compared to those in figure 7.
• FIG. 11 a turbine stage according to the invention is shown with a ceiling like that of the turbine screen of FIG. 7 and a plank like that of FIG. 9.
• the numbers of these references have been increased by 100 compared to those of FIG. 9.
• FIGS. 12 and 13 are variants of FIGS. 10 to 11 in which the meridians of the plancner 311 respectively: 311 ′ and of the ceiling 312 of the movable grid 305 feel straight lines.
• FIG. 14 shows a neck of a grills fixed by a surface that revolution around the axis comprising means for reduce secondary losses in each channel limited by the upper surface 401 of a blade A and the lower surface 402 of a blade B. These means are described, for example, in Belgian patent n ° 677969.
• the floor and / or the ceiling were dug in 403 in the vicinity of the upper surface of dawn A, which causes a local reduction in the overpressure at the level of the floor and / or ceiling.
• material 401 has been brought onto the plank and / or the ceiling in the vicinity of the lower surface of the blade 3, which causes a local decrease in the depression in line with the floor and / or the ceiling.
• the internal shape of the fixed grid also has a radians periodicity, being the number of blades of the directrix. However, in the exit plane of the grid perpendicular to the axis, the set of channels is tangent to a surface of revolution around the axis.
• the tangential static pressure gradient in the vicinity of the ceiling is reduced by a factor ⁇ and / or the tangential static pressure gradient in the vicinity of the plancner at the outlet of the fixed grid by a factor of one.

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• Engineering & Computer Science (AREA)
• Physics & Mathematics (AREA)
• Fluid Mechanics (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Engine Equipment That Uses Special Cycles (AREA)
• Crystals, And After-Treatments Of Crystals (AREA)
• Separation By Low-Temperature Treatments (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Priority Applications (1)

Applications Claiming Priority (2)

Publications (2)

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ID=9253860

Family Applications (1)

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• 1981
  • 1981-01-05 ZA ZA8234A patent/ZA8234B/xx unknown
  • 1981-12-30 JP JP57500218A patent/JPH023003B2/ja not_active Expired - Lifetime
  • 1981-12-30 US US06/414,253 patent/US4778338A/en not_active Expired - Fee Related
  • 1981-12-30 EP EP82900113A patent/EP0068002B1/de not_active Expired
  • 1981-12-30 DE DE8282900113T patent/DE3169495D1/de not_active Expired
  • 1981-12-30 AT AT82900113T patent/ATE12291T1/de active
  • 1981-12-30 WO PCT/FR1981/000172 patent/WO1982002418A1/en active IP Right Grant
• 1982
  • 1982-01-04 IT IT67002/82A patent/IT1154402B/it active
• 1988
  • 1988-07-01 US US07/214,992 patent/US4832567A/en not_active Expired - Fee Related

Non-Patent Citations (1)

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