EP0056233A1 - Diffusor mit Grenzschichtabsaugung - Google Patents

Diffusor mit Grenzschichtabsaugung Download PDF

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Publication number
EP0056233A1
EP0056233A1 EP82100019A EP82100019A EP0056233A1 EP 0056233 A1 EP0056233 A1 EP 0056233A1 EP 82100019 A EP82100019 A EP 82100019A EP 82100019 A EP82100019 A EP 82100019A EP 0056233 A1 EP0056233 A1 EP 0056233A1
Authority
EP
European Patent Office
Prior art keywords
slot
wall
diffuser
upstream
inlet
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.)
Granted
Application number
EP82100019A
Other languages
English (en)
French (fr)
Other versions
EP0056233B1 (de
Inventor
Michel Vincent De Paul
Gilbert Riollet
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.)
Alsthom Atlantique SA
Original Assignee
Alsthom Atlantique SA
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 Alsthom Atlantique SA filed Critical Alsthom Atlantique SA
Priority to AT82100019T priority Critical patent/ATE9832T1/de
Publication of EP0056233A1 publication Critical patent/EP0056233A1/de
Application granted granted Critical
Publication of EP0056233B1 publication Critical patent/EP0056233B1/de
Expired legal-status Critical Current

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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 symmetrical parietal suction diffuser of revolution about an axis AA 'and with a substantially axial inlet, used for example in a turbine or in a wind tunnel, comprising an outer wall surrounding the fluid flowing at the interior of the diffuser from the inlet to the outlet, said wall being provided with a circular slot evacuating a fraction of the incoming flow and having a pattern such that the pressure gradient measured at its surface in the direction of flow is negative upstream of said slot.
  • the object of the invention is to avoid any detachment.
  • This object is achieved by a diffuser as defined above which is characterized in that said wall, downstream of said slot, has a layout such that the direction of flow all along said wall downstream of said slot either in the direction of inlet to outlet and the pressure gradient measured at its surface in the direction of flow is positive.
  • Diffusers are also known in which the pressure gradient upstream and downstream of the slot is zero. '
  • the diffuser according to the invention making it possible to use a lower suction rate on an outer wall having a pattern such that the pressure gradient measured on its surface in the direction of flow is negative upstream of said slot and positive downstream, which prevents any separation of the boundary layer upstream of the slit as downstream.
  • the angle of entry of the fluid into the slot is between 100 ° and 120 °.
  • the optimal width of the slit is close to this value.
  • the slit has a small width, on the one hand, this reduces the possibilities of picking up any detached zones occurring upstream of the slit and, on the other hand, it increases the losses in the slit, the speed of penetration into the slit then being too high (at constant suction rate).
  • the width of the slit is too large, the speed of penetration into the slit is too low (at constant suction rate) and the detachments upstream of the slit are facilitated, and moreover there will be a overspeed on the leading edge downstream of the slit causing a thickening of the boundary layer which can go as far as detachment.
  • FIGS 1 and 2 there is shown an axial inlet diffuser having an outer wall and a slot 1 separating said wall into an upstream part 2 and a downstream part 3.
  • the diffuser also has an internal wall 4.
  • the diffuser is symmetrical with revolution around an axis and the outer wall 2, 3 has a pattern such that the pressure gradient upstream and downstream of the slot is zero.
  • Figure 1 there is shown a normal flow which is sought.
  • the boundary layer located upstream of the slot 1 along the outer wall 2 is sucked in through the slot 1.
  • a represents the variation in the suction rate X as a function of the width b of the slot 1.
  • a first curve (I) in dashed line represents the minimum values of X as a function of b for which the flow regime of FIG. 1 is established
  • a second curve (II) in solid line represents the maximum values of X as a function of b where it is established, for sure, the flow regime of figure 2.
  • b bo we obtain a value of X, X 1 on the curve I and X 2 on curve II. For the values of X less than or equal to X 2 , only the flow regime of FIG. 2 is established.
  • suction rate X a value equal to or greater than that defined by curve I.
  • FIG 3 there is shown the diffuser according to the invention also symmetrical with respect to an axis of revolution AA '.
  • the outer wall is interrupted by a slot 1 which separates it from the upstream wall 2 and the downstream wall 3.
  • the outer wall has a pattern such that the pressure gradient measured at its surface in the direction of flow is negative upstream of the said wall. slit and positive downstream.
  • the inlet section of the diffuser is So and the average speed in this section is Vo.
  • the circular slot 1 is also symmetrical in revolution about the axis AA 'and has a width b at its inlet BC and the speed of the fluid on the wall 2 at the inlet of the slot 1 at point C is V i . Slot 1 widens slightly after entering.
  • R the radius of curvature of the upstream wall 2 at the entrance to the slot 1 and by r the radius measured with respect to the axis AA 'of the entrance to the slot.
  • FIG. 6 shows curves I and II for a diffuser according to the invention, in which the outer wall has a line such that the pressure gradient measured at its surface in the direction of flow is negative upstream of the slot and positive downstream.
  • Curves I and II are lowered and it is therefore possible to obtain, with the same slot width (if we compare with FIG. 5), correct operation by using a suction rate X which is significantly lower.
  • the pressure on the wall 2 will gradually decrease from the inlet of the diffuser to the inlet of the slot 1, so that the fluid will be accelerated and the state of the boundary layer will be further from the separation.
  • We will generally take a speed of 15% to 40% higher than the speed of entry into the diffuser, depending on the layout possibilities available.
  • the layout of the wall 3 will reduce the risks of formation of the flow of FIG. 2.
  • the slit width is an important parameter. In fact, if it is too low, the possibilities of capturing any detached areas occurring on the wall 2 are reduced. In addition, this increases losses in the slit (at constant suction rate). If the width is too large, the detachment on the wall 2 is facilitated and in addition the stopping point S (where the speed is zero) may be slightly inside the slot, hence a significant overspeed of the flow around the leading edge following S on the wall 3, which will cause a thickening of the boundary layer on the wall 3 which can go as far as detachment, therefore greater losses for this diffuser.
  • the report can easily be measured by placing a static pressure tap at the inlet of the slot (p1) and another in the inlet plane of the diffuser (in), then by measuring the stop pressure (p ) in said entry plane using a pitot probe
  • the report is equal to
  • V being the speed at point M taken on the wall 2 or 3 as a function of the curvilinear abscissa OM, 0 being the point of the wall 2 at the inlet of the diffuser.
  • the wall 3 downstream of the slot is offset in the flow (see Figure 4); this offset ⁇ is measured by the distance of two planes perpendicular to the axis AA ', one tangent to the upstream convex wall 2, the other passing through the center of the osculating circle at the leading edge of the downstream wall 3
  • This offset A is preferably equal to or slightly greater than the value b opt indicated previously.
EP82100019A 1981-01-08 1982-01-05 Diffusor mit Grenzschichtabsaugung Expired EP0056233B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT82100019T ATE9832T1 (de) 1981-01-08 1982-01-05 Diffusor mit grenzschichtabsaugung.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8100210 1981-01-08
FR8100210A FR2497544A1 (fr) 1981-01-08 1981-01-08 Diffuseur a aspiration parietale

Publications (2)

Publication Number Publication Date
EP0056233A1 true EP0056233A1 (de) 1982-07-21
EP0056233B1 EP0056233B1 (de) 1984-10-10

Family

ID=9253948

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82100019A Expired EP0056233B1 (de) 1981-01-08 1982-01-05 Diffusor mit Grenzschichtabsaugung

Country Status (13)

Country Link
US (1) US4471910A (de)
EP (1) EP0056233B1 (de)
JP (1) JPS57146003A (de)
KR (1) KR890000914B1 (de)
AT (1) ATE9832T1 (de)
AU (1) AU547535B2 (de)
BR (1) BR8200051A (de)
CA (1) CA1193513A (de)
DE (1) DE3260910D1 (de)
ES (1) ES508555A0 (de)
FR (1) FR2497544A1 (de)
RO (1) RO82608A (de)
ZA (1) ZA82121B (de)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5059093A (en) * 1990-06-07 1991-10-22 United Technologies Corporation Compressor bleed port
FR2835019B1 (fr) * 2002-01-22 2004-12-31 Snecma Moteurs Diffuseur pour moteur a turbine a gaz terrestre ou aeronautique
GB0229307D0 (en) * 2002-12-17 2003-01-22 Rolls Royce Plc A diffuser arrangement
US8474266B2 (en) 2009-07-24 2013-07-02 General Electric Company System and method for a gas turbine combustor having a bleed duct from a diffuser to a fuel nozzle
US8381532B2 (en) * 2010-01-27 2013-02-26 General Electric Company Bled diffuser fed secondary combustion system for gas turbines
US20130051974A1 (en) * 2011-08-25 2013-02-28 Honeywell International Inc. Gas turbine engines and methods for cooling components thereof with mid-impeller bleed cooling air
CN103244459B (zh) * 2013-04-25 2015-08-05 哈尔滨工业大学 一种亚音速吸附式轴流压气机气动设计方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1000767A (en) * 1963-05-08 1965-08-11 Int Research & Dev Co Ltd Diffusers for fluids
GB1024328A (en) * 1961-12-05 1966-03-30 Gen Electric Improvements in high performance fluid-dynamic component

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR992353A (fr) * 1944-06-22 1951-10-17 Cem Comp Electro Mec Amélioration de la récupération des diffuseurs
FR2401311A1 (fr) * 1977-08-25 1979-03-23 Europ Turb Vapeur Dispositif d'echappement pour turbine axiale a fluide condensable

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1024328A (en) * 1961-12-05 1966-03-30 Gen Electric Improvements in high performance fluid-dynamic component
GB1000767A (en) * 1963-05-08 1965-08-11 Int Research & Dev Co Ltd Diffusers for fluids

Also Published As

Publication number Publication date
ES8302862A1 (es) 1982-12-01
RO82608A (ro) 1983-09-26
JPH0259285B2 (de) 1990-12-12
DE3260910D1 (en) 1984-11-15
ATE9832T1 (de) 1984-10-15
CA1193513A (fr) 1985-09-17
FR2497544B1 (de) 1985-05-03
ZA82121B (en) 1982-11-24
US4471910A (en) 1984-09-18
BR8200051A (pt) 1982-10-26
KR890000914B1 (ko) 1989-04-13
EP0056233B1 (de) 1984-10-10
AU7926482A (en) 1982-07-15
ES508555A0 (es) 1982-12-01
KR830009415A (ko) 1983-12-21
AU547535B2 (en) 1985-10-24
JPS57146003A (en) 1982-09-09
FR2497544A1 (fr) 1982-07-09

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