EP3431708A1 - Dispositif d'écoulement autour, turbomachine et application associées - Google Patents

Dispositif d'écoulement autour, turbomachine et application associées Download PDF

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Publication number
EP3431708A1
EP3431708A1 EP18178413.3A EP18178413A EP3431708A1 EP 3431708 A1 EP3431708 A1 EP 3431708A1 EP 18178413 A EP18178413 A EP 18178413A EP 3431708 A1 EP3431708 A1 EP 3431708A1
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EP
European Patent Office
Prior art keywords
umströmungsstruktur
bypass
flow
trailing edge
turbomachine
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
EP18178413.3A
Other languages
German (de)
English (en)
Other versions
EP3431708B1 (fr
Inventor
Martin Hoeger
Fadi Maatouk
Günter RAMM
Yavuz Gündogdu
Irene Raab
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.)
MTU Aero Engines AG
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MTU Aero Engines AG
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
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Publication of EP3431708A1 publication Critical patent/EP3431708A1/fr
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Publication of EP3431708B1 publication Critical patent/EP3431708B1/fr
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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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/34—Arrangement of components translated

Definitions

  • the present invention relates to a Umströmungsan extract with Umströmungs Modellen for arranging in the hot gas duct of a turbomachine.
  • turbomachine When the turbomachine may, for example.
  • the turbomachine is divided into compressor, combustion chamber and turbine.
  • sucked air is compressed by the compressor and burned in the downstream combustion chamber with added kerosene.
  • the resulting hot gas a mixture of combustion gas and air, flows through the downstream turbine and is thereby expanded.
  • the volume flowed through by the hot gas ie the path from the combustion chamber via the turbine to the nozzle, is referred to as "hot gas channel".
  • Umströmungsan is provided for arranging in the hot gas channel and has a plurality of Umströmungs Modellen. Of these, at least some are designed as turning vanes, while others are preferably struts or corresponding linings. Like the above reference to a jet engine, this is intended to illustrate the present subject matter, but not to limit its generality at first.
  • the turbomachine may, for example, also be a stationary gas or steam turbine.
  • the present invention is based on the technical problem of specifying a particularly advantageous flow-through arrangement for arranging in the hot gas duct of a turbomachine.
  • the Umströmungsan extract according to claim 1.
  • This has a first and a second Umströmungs Design, wherein the second Umströmungs Cook is provided as a Umlenkschaufel and has a smaller profile thickness than the first Umströmungs Cook, which is arranged on the suction side of the second Umströmungs Modell.
  • the Umströmungs Designen are arranged with a partial axial overlap, but at the same time the trailing edge of the second Umströmungs Medical offset from the first Umströmungs Vietnamese axially downstream.
  • the present Umströmungsan initially different Umströmungs Cook that are provided axially successively in a conventional design in separate sections, pushed a piece far into each other (axial overlap), but not completely.
  • the rear edge of the second Umströmungs Vietnamese (hereinafter also “thin turning vane”) is offset to the rear, at the trailing edge of the first Umströmungs Quilt (hereinafter also “thick blade”), a suction can be generated.
  • the flow can be accelerated away from the trailing edge of aerodynamically unfavorable thick blade and can refine the caster or even, which, for example, reduce harmful secondary flows and can also reduce noise.
  • the thin turning vane causes a discharge and a smooth outflow at the trailing edge of the thick blade (Kutta condition). This can be advantageous in view of the uniformity of the flow to the downstream rotor or also help improve the efficiency of the turbine as a whole, for example. By about 0.25% to 0.5%.
  • Each of the Umströmungs Cooken has a front and a rear edge, in between each extending two opposite side surfaces of the respective Umströmungs Medical.
  • the profile thickness is taken between the side surfaces.
  • the skeleton line extends centrally between the side surfaces between the leading and trailing edges of the respective flow structure, and then the profile thickness results as the largest circle diameter on the skeleton line (the circle touches the side surfaces, the center is on the skeleton line).
  • the thin deflecting blade may, for example, have a profile thickness that is at least 50%, 60%, 70% or 80% lower than the first circulating structure, with possible (independent) upper limits at, for example, at most 99%, 97% or 95% ( each increasingly preferred in the order of entry).
  • the design of the respective structure is based in their respective radial center.
  • the shape at half the height (taken radially) of the corresponding circulating structure or the deflecting blade or of the airfoil is considered. Radially in the middle of the gas channel, the influence on the flow can be greatest.
  • the respective structures are nevertheless configured correspondingly over their entire height relative to one another (in any case when compared in each case with the same percentage of height).
  • axial refers to the longitudinal axis of the turbomachine, which, for example, coincides with an axis of rotation of the rotors.
  • Ring refers to the perpendicular to it, pointing away radial directions, and a “circulation” or “circumferential” or the “direction of rotation” relate to the rotation about the longitudinal axis.
  • the first and the second flow around structure are, for example, due to the axial overlap, arranged successively in the direction of rotation.
  • "axial" overlap for example, means that a projection of the first circulating structure radially on the longitudinal axis with a projection of the second circulating structure radially on the longitudinal axis has an overlap.
  • first and second Umströmungs Designen are to be read as indefinite articles and thus always as “at least one” or “at least one”.
  • first and second Umströmungs Designen are to be read as indefinite articles and thus always as “at least one” or “at least one”.
  • first and second Umströmungs Designen are to be read as indefinite articles and thus always as “at least one” or “at least one”.
  • first and second Umströmungs Designen are at least 4, 5 or 6, with possible (independent) upper limits for example.
  • the first and the second Umströmungs Designen then preferably identical and arranged rotationally symmetrical.
  • third and possibly fourth or even further Umströmungs Modellen which are then also designed as thin deflection vanes.
  • the first flow around structure is provided as a supporting strut or as a lining, in particular as a lining of a supporting strut support.
  • the support strut is a load-bearing component of the turbomachine, preferably it (together with further peripherally arranged support struts) supports the bearing of the turbine shaft, in particular the high-pressure turbine shaft.
  • the bearing is preferably arranged in the turbine intermediate housing, in the so-called. Mid Turbine Frame.
  • the support struts can each extend away from the bearing radially outward and keep the bearing centered in the housing, so to speak spoke-shaped.
  • the first Umströmungs Vietnamese is a panel in which, for example.
  • a supply line may be performed, it is preferably a panel of a support strut, it is therefore attached for aerodynamic reasons to the actually bearing component. Also in this case, additional supply lines etc. can then be performed.
  • Such a panel is also known as fairing.
  • the supporting function or enclosing the support strut require a certain structure size, ie large profile thickness. This is aerodynamically disadvantageous, but this is at least partially compensated by the combination with the thin turning vane.
  • the first flow-around structure may generally also be non-deflecting, preferably it is slightly deflecting at less than 5 °, but it has no effect on the flow (due to radius change and spin set, no momentum is transferred to the flow).
  • the thin turning vane is the first flow around structure (thick vane) with its bottom surface facing. At the bottom of the thick blade more deflection is necessary because its bottom surface due to the high thickness substantially axially into the trailing edge runs, for example. Not tilted by more than 10 ° or 5 ° to the axial direction. The thin turning vane creates at the trailing edge the thick blade once an acceleration (nozzle effect). Next, the tail is "sucked away" from the trailing edge.
  • the thin turning vane has its maximum curvature where it has the axial overlap with the first flow around structure.
  • This high-curvilinear design is similar to a wing with the Fowler flap extended, further increasing the suction created at the trailing edge of the thick blade.
  • the trailing edge of the thin turning vane is at least 0.5 times, more, and most preferably at least 0.7 or 0.9 times the axial length of the blading of a downstream rotor directly downstream of the trailing edge first Umströmungs Modell offset (axially downstream).
  • Preferred upper limits which in general may also be of interest independently of the lower limits, are at most 4 times, more, and particularly preferably at most 2.6 or 2.2 times.
  • the "axial length" results as the axial portion of the chord length of the blades of the rotor (if it is equipped with different blades, a mean value formed over this is considered).
  • the leading edge of the thin turning vane is offset axially downstream of that of the thick vane.
  • Advantageous upper limits are (also independent of) at preferably at most 1.2 times, more preferably at most 0.9 times.
  • the thin turning vane has a chord length that is at least 1 times, preferably at least 1.5 times, a chord length of the blading of the downstream immediately downstream rotor. Should this be equipped with different blades, again an average value is considered.
  • Advantageous upper limits of the chord length of the thin turning vane are in the order of naming increasingly preferred at most 8, 7, 6, 5, 4, or 3 times the chord length of the subsequent rotor. Thus, a tendon length of about 2 to 3 times is particularly preferred.
  • the Umströmungsan extract on a third Umströmungs which analogous to the second Umströmungs Cook provided as a thin Umlenkschaufel, to the second Umströmungs Quilt but not identical.
  • the third flow-around structure is arranged on the upper side of the thick blade (the thick blade lies on the suction side of the third flow-around structure). Circumferentially between two thick blades, at least two different thin deflection vanes are then provided in each case.
  • the trailing edge of the third flow-around structure is preferably axially offset downstream of that of the thick blade, with respect to that of the second flow-around structure it is preferably axially offset-free (not offset), which preferably also applies to a fourth or generally further flow-around structures.
  • the third circulating structure has a smaller chord length than the second circulating structure. As stated above, more diversion may be required at the bottom of the first bypass structure, which is achieved with the greater chord length of the second bypass structure. If more than two different thin deflection vanes are provided circumferentially between two first flow-around structures, they preferably have a decreasing chord length overall from the underside of one thick blade to the upper side of the other thick blade. With the variable chord length, the free flow cross-section can be adjusted so that a uniform flow of the subsequent rotor is achieved.
  • the third flow structure has a smaller curvature than the second. It is thus achieved with a more curved second Umströmungs Modell at the bottom of the thick blade more deflection, see the front. If more than two different thin deflection blades are provided circumferentially between two first flow-around structures, they preferably have a decreasing curvature overall from the underside of one thick blade to the upper side of the other thick blade.
  • a further thin deflection vane is provided (fourth flow around structure), wherein the second, third and fourth Umströmungs MAY are not identical to each other.
  • the fourth flow around structure is the suction side of the arranged third Umströmungs Modell. If exactly three different thin deflecting vanes are arranged circumferentially between two thick blades, a fourth circulating structure is also arranged on the pressure side of the second circulating structure.
  • the fourth Umströmungs founded has a greater chord length than the third Umströmungs Cook or it is more curved, preferably both.
  • the chord length and / or curvature preferably increases from the third circulating structure via the fourth to the second circulating structure.
  • At least four Umströmungs Cooken are arranged between two first Umströmungs Cooken which are adjacent to each other in the circumferential direction, which are each formed as a Umlenkschaufel.
  • Upper limits independent of this lower limit may be more preferably at most twelve, eleven, ten or nine deflection vanes in the order of entry. Particularly preferred may be exactly four deflecting vanes.
  • the second, third, fourth and fifth bypass flow structures can therefore preferably be arranged between the first bypass flow structures adjacent to one another, cf. also the above description with further details.
  • At least the deflection vanes arranged between the two adjacent first circulation flow structures in the direction of circulation are formed as a multiple segment.
  • the first flow-around structure may also be provided as part of the multiple segment.
  • a subdivision can be advantageous in that only the deflecting vanes are combined in multiple segments or in a ring, wherein the first Umströmungs Modellen are then assembled with it.
  • the first Umströmungs Modell or structures are then poured so for themselves; then to the axial overlap realize, in each case a recess can then be introduced into the trailing edges of the first Umströmungs Designen, z. B., in which then the segment or the wreath is inserted with the turning vanes.
  • the flow-around structures of the multiple segment or ring are integrally with each other, that is not non-destructively separable, preferably they can be monolithic, in particular formed from a cast.
  • the invention also relates to a turbomachine with a presently disclosed Umströmungsan angel, this may be arranged in particular in the turbine intermediate housing.
  • the invention relates to the use of a presently disclosed Umströmungsan extract in a turbomachine, in particular an aircraft engine.
  • FIG. 1a shows a turbomachine 1 in section, specifically a jet engine.
  • FIG. 1b shows a schematic detail view thereto, the following comments relate to both figures.
  • the turbomachine 1 is divided into compressor 1a, combustion chamber 1b and turbine 1c. Both the compressor 1a and the turbine 1c are each constructed of several stages, each stage is usually composed of a guide and a blade ring. During operation, the rotor blade rings rotate about the longitudinal axis 2 of the turbomachine 1.
  • the turbine shaft 3 is guided in a bearing 4, which is held by struts 5 (partially dashed) in the remaining turbomachine 1.
  • each of the support struts 5 is jacketed for aerodynamic and thermal reasons, namely from a first Umströmungs Quilt 6, illustrating a cover and is also known as fairing.
  • This section is a so-called Turbinen formatgeratiuse. In the turbomachine according to the invention this is carried out integrally with the subsequent vane ring.
  • FIG. 2 shows a portion of the Umströmungsan extract 20 of the invention, which is arranged in the turbine intermediate housing in the hot gas duct. Shown is a section, the cut surface is radially in the middle in the hot gas channel and parallel to the longitudinal axis 2.
  • first flow structures 6 fairings
  • second Umströmungs Designen 21 and third Umströmungs Modellen 22 can be seen, each as a Umlenkschaufel with a suction side (in the figure above ) and a pressure side (in the figure below) are formed.
  • the profile thickness of these thin deflection vanes is only about 30% of the profile thickness of the first flow structures 6 (in the schematic representation according to FIG FIG. 2 the thin vanes are simplified as lines without profile thickness reproduced).
  • the flow-around structures 6, 21, 22 each have a front edge 6a, 21a, 22a and, downstream thereof, a respective trailing edge 6b, 21b, 22b.
  • the thin deflecting vanes are provided axially with an overlap with respect to the first circulating structures 6, they are also offset a little.
  • the trailing edges 21b, 22b of the second and third circulating structures 21, 22 are offset axially downstream from the trailing edges 6b of the first circulating structures 6.
  • the second Umströmungs fabricat 21 has its strongest curvature in the axial overlap with As a result, a strong suction is generated and the flow accelerated away from the trailing edge 6b of the aerodynamically rather unfavorable first flow structure 6.
  • the caster becomes finer and more uniform, cf. also the presentation in the introduction to the description.
  • the second bypass structure 21 is more curved than the third bypass structure 22 and has a greater chord length.
  • the first flow around structure 6 is arranged on the pressure side of the third flow around structure 22, this presses the flow at the trailing edge 6b a little way down and thus relieves the trailing edge 6b.
  • FIG. 3 shows an enlarged view of the configuration FIG. 2 with the suction field 23 on the upper side of the thin deflecting vane 21.
  • Both deflecting vanes 21, 22 form with the circulating structure 6 in their inlet region narrowing flow channels 24, 25, which lead to a further relief of the flow at the trailing edge 6b. Downstream of the trailing edge 6b, close to the narrow gap 26, there is a further narrowing flow channel, which generates the suction field together with the blade curvature.
  • Umströmungs Jardin 6 with high thickness and thickness reserves x d / L> 50% possible, which can accommodate more and larger supply lines and support elements. A reduction in the number of blades, friction loss and weight is possible.
  • the bypass arrangement 20 is constructed in total (over the entire circulation) from in each case 9 first, second and third flow-around structures 6, 21, 22, ie has 18 thin deflection vanes. It could also be provided in addition a fourth, also designed as a thin Umlenkschaufel Umströmungs Modell, so that would be arranged between two first Umströmungs Modellen 6 each three different thin deflection vanes (in this case, a total of 27 thin deflection vanes are provided), see. also the description introduction. Independently of this, a group-by-group combination of the flow-around structures 6, 21, 22 in multiple segments is preferred. In this regard, the axial offset manufacturing technology advantageous or would be vice versa sometimes considerably more expensive to achieve the same flow guide at the trailing edge 6b of the first Umströmungs Design 6 by a long drawn back to the first Umströmungs Design 6.
  • the axial offset between the trailing edges 21b, 22b of the second and third flow structures 21, 22 to the trailing edges 6b of the first flow structures 6 corresponds to approximately 1.5 axial lengths of a subsequent rotor 30, specifically its blading 31.
  • the described refinement and homogenization of the flow is also advantageous for the operation of the rotor 30.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP18178413.3A 2017-07-19 2018-06-19 Dispositif d'écoulement environnant, turbomachine et application associée Active EP3431708B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102017212311.7A DE102017212311A1 (de) 2017-07-19 2017-07-19 Umströmungsanordung zum Anordnen im Heißgaskanal einer Strömungsmaschine

Publications (2)

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EP3431708A1 true EP3431708A1 (fr) 2019-01-23
EP3431708B1 EP3431708B1 (fr) 2020-10-14

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US (1) US11371370B2 (fr)
EP (1) EP3431708B1 (fr)
DE (1) DE102017212311A1 (fr)
ES (1) ES2832464T3 (fr)

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US11371370B2 (en) 2022-06-28
ES2832464T3 (es) 2021-06-10
EP3431708B1 (fr) 2020-10-14
DE102017212311A1 (de) 2019-01-24

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