US20020062945A1 - Wall part acted upon by an impingement flow - Google Patents

Wall part acted upon by an impingement flow Download PDF

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Publication number
US20020062945A1
US20020062945A1 US10/002,633 US263301A US2002062945A1 US 20020062945 A1 US20020062945 A1 US 20020062945A1 US 263301 A US263301 A US 263301A US 2002062945 A1 US2002062945 A1 US 2002062945A1
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United States
Prior art keywords
impingement
wall part
troughs
flow
trough
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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.)
Abandoned
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US10/002,633
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English (en)
Inventor
Rainer Hocker
Josef Hausladen
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Individual
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Individual
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Priority to US10/002,633 priority Critical patent/US20020062945A1/en
Publication of US20020062945A1 publication Critical patent/US20020062945A1/en
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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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to an impingement flow for wall parts according to the preamble of patent claim 1.
  • the highest heat transmission coefficients can be achieved with impingement cooling and impingement heating respectively.
  • the impingement flow is realized by virtue of the fact that a cooling or heating fluid (e.g. air, water, steam, hydrogen, liquid sodium, etc) flows through one or more orifices in a wall and strikes an opposite surface more or less perpendicularly.
  • a cooling or heating fluid e.g. air, water, steam, hydrogen, liquid sodium, etc
  • DE-A1 44 30 302 discloses impingement cooling of the type mentioned at the beginning.
  • the method shown in said document is distinguished by a plurality of impingement tubes which are arranged areally with their inlet on a plane or curved carrier and are directed with their mouth toward the wall part to be cooled, the carrier being arranged at a distance from the wall part.
  • the impingement area of the wall part to be cooled is designed as a relief, in which case the jets directly strike projecting humps.
  • the inhomogeneous heat transmission in the impingement jets is to be compensated for and a homogeneous temperature distribution on the hot side of the wall part is to be achieved.
  • the humps are designed essentially as cylinders having rounded-off edges, which are brought about during manufacture.
  • the relief is present in the form of ribs.
  • Both geometrical forms have no advantageous thermal boundary conditions in relation to the heat transmission.
  • the heat which can be dissipated via the surface of an element projecting from the wall to be cooled, must first of all be directed through the base area and the material to the surface. As a result, a thermal stratification occurs in the material of the element. Depending on material and geometrical form, this thermal stratification may result in the temperature difference between fluid and element becoming so small at the points furthest away from the base of the element that virtually no more heat transmission takes place.
  • one object of the invention is to provide a novel impingement arrangement in which the roughness elements are optimized with regard to the manufacturing process and the thermal efficiency.
  • both the geometrical form and its size and arragement relative to the free jets are to be taken into account for this purpose.
  • the webs between the troughs may be provided with spacers to the jet-producing plate or, depending on the design of this plate, may even be used directly as spacers if the plate rests on the webs.
  • FIG. 1 shows a longitudinal section through an impingement-flow arrangement
  • FIGS. 2 a - c show various geometrical forms of troughs
  • FIG. 3 shows a quadruple arrangement of troughs
  • FIG. 4 shows a nested sextuple arrangement of troughs
  • FIG. 5 shows a variant of the quadruple arrangement according to FIG. 3;
  • FIG. 6 shows a variant of the sextuple arrangement according to FIG. 4;
  • FIG. 7 shows an impingement-cooled gas-turbine blade
  • FIG. 8 shows an exemplary embodiment with impingement tubes instead of impingement orifices
  • FIG. 9 shows an exemplary embodiment with structured carrier.
  • impingement cooling As can be used, for example, for cooling hot turbomachine components around which a flow occurs, such as gas-turbine blades or combustion-chamber walls.
  • the wall part to be cooled, for example, by means of cooling air 5 is designated by 3 in FIG. 1.
  • This wall 3 is a plane wall around which a hot medium, designated by the arrows 6 , flows on the outside.
  • the cooling-air-side carrier 1 is also of corresponding plane design. In the case shown, it is fastened to the wall 3 at a uniform distance 20 by suitable means (not shown).
  • the carrier has a plurality of impingement orifices 2 and may be conceived as a simple perforated plate.
  • the wall 3 to be cooled is provided with a number of troughs 4 arranged next to one another.
  • these troughs are in the form of spherical cups.
  • the distance between the troughs is selected in such a way that a narrow web 7 is obtained between the adjacent trough walls.
  • the wall part to be cooled is preferably cast in one piece together with the troughs. Irrespective of the manufacturing process, a structure of high strength is obtained.
  • An impingement jet is provided for each trough, this impingement jet, which discharges from the impingement orifice 2 , normally striking the trough base at least approximately perpendicularly. When it strikes, the impingement jet is deflected onto the remaining impingement area, i.e. the walls of the trough.
  • the cooling medium which is heated when flowing around the spherical cup, then flows off into the free space between carrier and wall part, the cross flow which occurs also helping to cool the webs 7 .
  • FIG. 2 Various further possible geometrical forms of troughs are explained in FIG. 2. Since the elements are of symmetrical construction, only one trough half is shown in each case.
  • FIG. 2 a shows an ellipse shape. As in the case of the spherical cup, this shape is also generated by rotation of the corresponding segment about the axis U.
  • FIG. 2 b shows a shape which is approximated to a shortened cycloid and has been generated by rotation of the corresponding segment about an axis U offset in parallel from the impingement-jet axis. It goes without saying that, in the case of this shape, the impingement jet must strike the inflection point exactly for full effectiveness.
  • FIG. 2 c shows a trapezoidal trough which has a plane base and whose walls may be made straight or curved (as shown).
  • a honeycombed structure is obtained in combination, to the individual elements of which a free jet is assigned in each case.
  • the latter is positioned in such a way that its core, under the given boundary conditions—inter alia the cross flow of the outflowing cooling medium of adjacent elements—produces a stagnation point in the lower base region of the troughs.
  • the axial position of the free jet can deviate from the rotation axis of the solid of rotation.
  • the geometry to be selected in each case is to influence the heat flow in such a way that the surface temperature decreases only marginally with increasing distance from the base and thus a virtually constant heat flow can flow through the entire surface.
  • the impingement orifices 2 and the troughs 4 may either be arranged in a row according to FIG. 3 or they may staggered relative to one another, for example by half a spacing according to FIG. 4. This results in arrangements which are either square or hexagonal, as the broken lines in FIGS. 3 and 4 respectively show.
  • the troughs 4 are preferably arranged at the intersections of these broken lines. As FIG. 3 shows, in the arrangement in a row, troughs which are directly adjacent are arranged without intermediate spaces, i.e. without webs. Nonetheless, relatively large webs 7 are formed in this embodiment in the center of in each case four troughs. Spacers to the carrier may be provided on these webs, in which case these spacers may also be cast integrally with the wall 3 .
  • FIG. 5 corresponds in its geometry to that of FIG. 3.
  • the size of and the mutual distance between the impingement orifices 2 are selected to be the same.
  • the diameter D of the troughs has been increased, which leads to the intersecting of adjacent troughs and to smaller webs 7 .
  • This solution can have production-related advantages and, depending on the choice of diameter, can lead to shallower troughs.
  • FIG. 6 corresponds in its geometry to that of FIG. 4.
  • the size of and the mutual distance between the impingement orifices 2 are again selected to be the same.
  • the diameter D of the troughs has been increased, which leads to the intersecting of adjacent troughs and to extremely small webs. It will be seen here that, from a certain trough diameter, no more webs at all are formed.
  • a gas-turbine blade 16 is shown as an example of a component to be cooled.
  • the carriers with the impingement orifices 2 are conceived as more or less tubular inserts 17 A, 17 B and 17 C and are arranged in the hollow interior of the blade.
  • These inserts as well as the blade wall provided with the troughs 4 may be designed as a casting. They may likewise be designed as a pressure-bearing structure for internal pressures, which may be up to twice the pressure prevailing in the actual impingement zone.
  • the inflow of the cooling medium into the inserts takes place as a rule from the blade root toward the blade tip.
  • the impingement orifices 2 and the troughs 4 are staggered over the blade height and the blade circumference at the requisite distance apart. Flow may occur through the inserts 17 A-C individually or in series.
  • the gaseous or vaporous cooling medium may be circulated in closed circuit in the plurality of inserts, i.e. it is drawn off again via the blade root after cooling has been carried out.
  • the cooling medium flowing off from the cooled wall parts may discharge from the blade into the flow duct. This preferably takes place at that point of the blade at which the lowest external pressure prevails. As a rule, therefore, the cooling medium will be made to discharge at the trailing edge 18 of the blade.
  • FIG. 8 shows an exemplary embodiment in which the carrier is likewise sheetlike and is provided with a multiplicity of impingement tubes 21 , which are equidistant here and are arranged in rows.
  • Their inlet 22 corresponds to an impingement orifice and is flush with the carrier surface.
  • the impingement tubes have a conical internal passage narrowing constantly in the direction of flow. The narrowest cross section of the impingement tubes thus lies at the mouth 23 .
  • the impingement tubes are directed with their mouth 23 perpendicularly toward the wall part to be cooled. The mouth is located at the impingement distance 25 from the wall. In the example, the ratio of this impingement distance to the narrowest diameter of the impingement tubes is about 1.
  • the troughs have hitherto always been considered to be rotationally symmetrical bodies which have been generated by rotation of the corresponding section through 360°.
  • the corresponding section is not rotated about an axis U but is displaced along a preferably straight axis U. In this way, longitudinal channels having a circular, elliptical or trapezoidal shape are obtained at the area to be cooled. In this configuration, the stabilizing effect of the surface-enlarging structure occurs in a defined direction.
  • the impingement jets are likewise to strike the base of the channel.
  • a certain number of impingement jets in the longitudinal extent of the channel will be provided here, in which case, according to the requisite cooling capacity, attention is to be paid to the impingement-jet spacing to be selected.
  • a defective arrangement, for example related to production, of the impingement jets has only a marginal effect on the effectiveness of the entire system.
  • the carrier 1 is a plane perforated plate. According to FIG. 9, however, a perforated plate having spherical-cup-like depressions 26 may also be used.
  • the depressions in each case contain the impingement orifices 2 , and it can be seen that this solution provides a simple means of influencing the impingement distance 25 .
  • the troughs being designed in a channel shape, it is advisable to also configure the depressions 26 as channels.
  • the latter need not necessarily run in the same direction as the troughs. They may run at any angle between 0° and 90° to the trough direction or to the direction of the cooling flow 5 .
  • the intermediate spaces 27 present between the depressions may thereby be utilized for the specific discharge of the cooling medium.
  • the different direction offers the possibility of supporting the channel-shaped depression 26 directly on the webs 7 of the trough (not shown).
  • the invention is of course not restricted to the examples shown and described. It goes without saying that, depending on requirements, the number and spacing of the impingement orifices 2 or impingement tubes 21 as well as the length and shape of the latter can be optimized from case to case.
  • the invention also sets no limits to the selection of the cooling medium, to its pressure and to its further use after the cooling activity.
  • the person skilled in the art will recognize that the invention can be used not only for the purpose of cooling wall parts of machines, apparatus or plants in general but can just as easily be used for heating them. Examples for such a use of the heating of surface areas are the drying of paper, the melting and bonding of plastics, the deicing of aircraft wings, etc.
US10/002,633 1997-09-30 2001-12-05 Wall part acted upon by an impingement flow Abandoned US20020062945A1 (en)

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Application Number Priority Date Filing Date Title
US10/002,633 US20020062945A1 (en) 1997-09-30 2001-12-05 Wall part acted upon by an impingement flow

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP97810718.3 1997-09-30
EP97810718A EP0905353B1 (de) 1997-09-30 1997-09-30 Prallanordnung für ein konvektives Kühl- oder Heizverfahren
US15676098A 1998-09-18 1998-09-18
US10/002,633 US20020062945A1 (en) 1997-09-30 2001-12-05 Wall part acted upon by an impingement flow

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US15676098A Continuation 1997-09-30 1998-09-18

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EP (1) EP0905353B1 (ja)
JP (1) JPH11159301A (ja)
DE (1) DE59709158D1 (ja)

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US20030049125A1 (en) * 2000-03-22 2003-03-13 Hans-Thomas Bolms Reinforcement and cooling structure of a turbine blade
US20080037221A1 (en) * 2006-08-07 2008-02-14 International Business Machines Corporation Jet orifice plate with projecting jet orifice structures for direct impingement cooling apparatus
EP2143883A1 (de) * 2008-07-10 2010-01-13 Siemens Aktiengesellschaft Turbinenschaufel und entsprechender Gusskern
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Cited By (75)

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Publication number Priority date Publication date Assignee Title
US20030049125A1 (en) * 2000-03-22 2003-03-13 Hans-Thomas Bolms Reinforcement and cooling structure of a turbine blade
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EP0905353A1 (de) 1999-03-31
JPH11159301A (ja) 1999-06-15
DE59709158D1 (de) 2003-02-20

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