EP3988767A1 - Turbine radiale à gaz avec support d'appui - Google Patents

Turbine radiale à gaz avec support d'appui Download PDF

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Publication number
EP3988767A1
EP3988767A1 EP21203258.5A EP21203258A EP3988767A1 EP 3988767 A1 EP3988767 A1 EP 3988767A1 EP 21203258 A EP21203258 A EP 21203258A EP 3988767 A1 EP3988767 A1 EP 3988767A1
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EP
European Patent Office
Prior art keywords
bearing
wing
spring
gas turbine
axial
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.)
Withdrawn
Application number
EP21203258.5A
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German (de)
English (en)
Inventor
Viktor Kühne
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.)
3be Berliner Beratungs und Beteiligungs GmbH
Original Assignee
3be Berliner Beratungs und Beteiligungs GmbH
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Filing date
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Application filed by 3be Berliner Beratungs und Beteiligungs GmbH filed Critical 3be Berliner Beratungs und Beteiligungs GmbH
Publication of EP3988767A1 publication Critical patent/EP3988767A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • 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
    • F05D2220/40—Application in turbochargers
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position

Definitions

  • the invention relates to a radial gas turbine with (a) a turbine wheel and (b) a gas supply device for supplying a gas to the turbine wheel, which has (i) a first boundary plate, (ii) a second boundary plate, (iii) adjustable guide vanes between the first boundary plate and the second restriction plate, and (iv) a pitch mechanism for collectively rotating the guide vanes, (c) the guide vanes each having (i) a vane for directing the gas and (ii) a pitch axis for rotating the vane, and (iii ) are stored in a main bearing on the first boundary plate.
  • Such radial gas turbines are often components of exhaust gas turbochargers.
  • exhaust gas turbochargers are used in cylinder engines, for example in diesel or gasoline engines, usually in vehicles.
  • the task of radial gas turbines is to extract energy from the inflowing gas flow, usually the exhaust gas flow. This energy is often used to compress charge air.
  • gas supply devices are known. The guide vanes can be adjusted collectively by means of the adjusting device in such a way that the inflow onto the turbine wheel can be varied.
  • a disadvantage of known radial gas turbines is that they have suboptimal efficiency compared to the maximum possible efficiency.
  • One of the reasons for this is that comparatively large gaps have to be provided between the vanes and the boundary plates.
  • the reason for this, in turn, is that vibrations and transverse forces that occur during operation of the radial gas turbine, as well as temperature fluctuations with corresponding component distortions, could otherwise lead to the blades becoming stiff and/or jamming. This can lead to significant wear and even destruction of the radial gas turbines.
  • the object of the invention is to reduce the disadvantages of the prior art.
  • the invention solves the problem by means of a generic radial gas turbine in which at least one guide vane is mounted in a support bearing on the second boundary plate and is prestressed against the second boundary plate by means of an axial spring.
  • this radial gas turbine is that the at least one guide vane is mounted on two sides. This limits the tendency of the wings to tilt and minimizes the tolerance chains, so that smaller gaps between the wings and the limiter plates can be set. This in turn increases the efficiency of the radial gas turbine.
  • the second bearing is usually comparatively less complex.
  • the support bearing is not a roller bearing, that is, a bearing with roller bearing bodies.
  • the bearing system consisting of a main bearing and a support bearing, is designed such that a force acting on the support bearing in the axial direction simultaneously has a force component acting radially inward, which acts on the adjustment axis in the area of the main bearing.
  • the adjustment axis can wobble to a limited extent in the support bearing.
  • a support bearing can usually be manufactured comparatively easily.
  • such a support bearing is often robust and relatively insensitive to component distortions in the event of temperature fluctuations.
  • the boundary plates are understood to mean those elements between which the guide vanes are arranged.
  • the boundary plates are disc-shaped, which means that they have a larger dimension in two surface areas than in one area perpendicular to them.
  • the delimiting plate it is possible, for example, for the delimiting plate to have projections which can be larger than the extension of the surface area.
  • Guide vanes are devices that have a vane that is designed to conduct the gas.
  • the wings preferably have an airfoil geometry. This means in particular that they are designed to divert the gas.
  • the vanes are designed to vary an inflow direction under which the gas flows onto the turbine wheel.
  • the boundary plates are preferably held together and/or positioned relative to one another by connecting elements.
  • the support bearing has a concave bearing shell and a spherical cap that is accommodated in the bearing shell.
  • the spherical cap is in particular a spherical structure.
  • a cap is understood to mean a convexly curved section of a component.
  • the spherical cap is a part of an object with a circular border.
  • the bearing shell can be arranged on the second delimiting plate and the spherical cap on the adjustment axis of the wing or vice versa.
  • the support bearing - as provided for in a preferred embodiment - a separate spherical element, namely a so-called Bearing ball, the second delimiting plate and the adjustment axis of the wing each have a bearing shell. If there is a bearing ball, it is preferably made of steel or ceramic.
  • the radius of curvature of the bearing shell is at least as large as the radius of curvature of the bearing shell at the point at which the bearing shell and the bearing shell are in contact with one another.
  • the spherical cap can preferably wobble in the bearing shell.
  • a deflection of the adjustment axis from its desired position causes a restoring force, which can be achieved, for example, via parabolic geometries in the bearing shell and spherical cap.
  • the axial spring is bent in a wave shape.
  • This waveform is related to the radial component.
  • the axial spring is curved in a wavy shape in cross section.
  • the axial spring can be a plate spring, for example, which can have recesses.
  • the axial spring has an outer ring to which the individual shaft elements are connected and have a rectangular or trapezoidal geometry. This also makes it possible to press the axial spring into the bore of the first delimiting plate.
  • the shaft elements can also be connected via an inner ring, which can be fixed in the area of the adjustment axis of the guide vane.
  • the axial spring is made of steel. It is particularly advantageous if the prestressed axial spring has a limited setting behavior at high temperatures above 800 °C and adapts to the counter-contour while maintaining a residual prestressing force, which can be done with suitable types of steel. This increases the surface contact and reduces the surface pressure, which has a favorable effect on wear. However, it is also possible to produce the axial spring from a different material.
  • This bearing bush is preferably made of steel and/or ceramic. This enables optimization of the friction pairing.
  • the ceramic is preferably zirconium oxide, since this has a similar coefficient of expansion as steel.
  • the main bearing preferably has a disc element.
  • This disk element supports the wing and prevents the wing from tilting too much.
  • an end face of the disc element - connected or unconnected - on the wing It is possible that the end face is connected or not connected to the wing.
  • the axial spring is arranged to press the disc element in the direction of the wing.
  • the disc element it is possible, but not necessary, for the disc element to be movable relative to the wing.
  • the axial spring is arranged to exert a spring force between the first delimiting plate and the support bearing.
  • the axial spring is designed in such a way that a spring curve, which describes the dependency of a spring force on a deflection of the axial spring from a zero position, has a first section with a first spring constant and a second section with a second spring constant, with the first spring constant is less than the second spring constant.
  • the axial tolerances of the components are compensated for by means of small forces and the spring force in the second section has the desired higher forces, so that a suitable restoring force is generated on the wing, which pushes the wing back towards the target position. This counteracts jamming of the wings.
  • the first section runs from the beginning of the spring curve to the point at which the first derivative of the spring curve after the deflection has an inflection point. It is favorable if the axial spring is mounted in such a way that it is activated at low deflection, ie when the spring curve is in the first section a predetermined number of support points on an axial spring bearing structure. If the deflection becomes greater, then the axial spring rests against at least one further support point on the axial bearing spring structure, which means that the spring constant increases. In other words, the axial spring becomes harder.
  • the first spring constant can be calculated, for example, from the straight line in the first section, the second spring constant from a second straight line through the second section.
  • the axial spring preferably has an outer or inner axial spring ring and two or more axial spring elements are arranged on the axial spring ring.
  • the disk element is preferably designed as a sealing disk which rests against the wing.
  • This sealing washer is designed in particular in such a way that it reduces a gas flow past the side of the wing.
  • the disk element has a sealing section which extends in the axial and circumferential direction and lengthens a gas flow path past the wing.
  • the sealing section of the disk element acts like a labyrinth seal.
  • the sealing section runs at least in sections and at least partially in the axial direction.
  • the feature that the sealing section extends in the circumferential direction means in particular that it is at least predominantly designed to be continuous in the circumferential direction. In principle, it is possible for the sealing section to have gaps, but this generally leads to a lower sealing effect, which is why it is favorable if the disk element is largely continuous, in particular completely continuous, in the circumferential direction.
  • the disc element preferably engages in a recess, in particular a circular one, in the first delimiting plate.
  • the recess preferably has an outer contour which essentially corresponds to an outer contour of the disk element.
  • the outer contour of the sealing disk is smaller by a small amount than the outer contour of the recess. The smaller the difference between the outer contour of the recesses and the outer contour of the sealing disc, the greater the flow resistance for gas that flows past the wing.
  • the recess preferably also has a cylindrical border.
  • the difference in the radii is preferably less than 10%, in particular less than 5%.
  • the sealing washer preferably has an outer diameter of the sealing washer which is at least 50% larger than the diameter of the adjustment axis of the guide vane. A good sealing effect is thus achieved with a comparatively small diameter of the adjustment axis.
  • the outer diameter of the sealing disk is at most 20% smaller than the inner diameter of the recess.
  • the recess inner diameter is the diameter of the compensating circle through the edge of the recess. As described above, this leads to a good sealing effect.
  • a rotation axis distance between two adjacent adjustment axis rotation axes is at most 1.5 times, preferably 1.2 times or less, the outer diameter of the sealing disk. This contributes to an increased sealing effect.
  • the outer diameter of the sealing disk also exists if the sealing disk is not cylindrical in the strict mathematical sense. In this case it is the outside diameter of a perimeter.
  • the circumcircle is the minimum diameter circle that can be placed around the cross section of the recesses.
  • the disc element preferably has a collar towards the adjustment axis of the wing, which collar counteracts the tilting of the wing. It is advantageous if the collar has a greater axial height and thus forms a bearing bush at the same time.
  • the bushing has a bushing collar of greater radial extent towards the vane, located within the circular recess of the first restriction plate is arranged. In other words, the collar of the bearing bush forms the disc element or the sealing disc.
  • the bearing bushing collar of the bearing bushing is preferably arranged within the circular recess.
  • the distance between the adjustment axis of the guide vane and the wing trailing edge of the wing is at least as large as the sealing disk radius. In other words, the trailing edge of the wing protrudes beyond the sealing disk or closes with it.
  • the disk element in particular the sealing disk, has a wing support surface facing the wing and is connected to the wing in a rotationally fixed manner, the wing support surface having a local axial depression to prevent a collision with the wing trailing edge of the adjacent wing.
  • the background to this preferred feature is that the trailing edge of the wing always hits the sealing washer of the adjacent guide vane at the same point when rotating back (closing rotation) from the maximum open position.
  • the sealing disk preferably has the indentation and a ramp which rises in the direction of the closing rotation.
  • the sealing washer preferably has an essentially circular outer contour. Under is to be understood in particular that a deviation from an ideal circular outer contour is preferably on average at most 10%, in particular at most 5%.
  • the sum of the wing lengths of all guide vanes is preferably greater than the circumference on which the adjustment axes are arranged.
  • the vanes are designed in such a way that the trailing edges of the vanes sweep over the adjacent sealing discs when the gas supply device is closed and/or (b) during the transition, when the trailing edges of the vanes move from the axial depression to the planar vane support surface, the Guide vanes and the sealing washers are collectively leveled.
  • a first limiting plate thickness of the first limiting plate is at most 30%, in particular at most 20%, larger than a second limiting plate thickness of the second limiting plate and/or (b) a first limiting plate mass of the first limiting plate is at most 50%, in particular at most 20% larger as a second constraint plate mass of the second constraint plate.
  • a sealing disk radius of the sealing disk in the area of a wing leading edge of the wing is larger than the average radius of the sealing disk.
  • a radius means the ray that runs radially outwards from the axis of rotation of the turntable.
  • a radius is also spoken of when the sealing washer is not strictly circular. Because the sealing washer radius in the area of the wing leading edge of the wing is larger than the average radius, the axial gap between the wing and the first boundary plate minimized and become.
  • the sealing disk radius in the region of the leading edge of the wing corresponds at least essentially to a distance between the leading edge of the wing and the sealing disk.
  • the relative deviation between the two is at most 10%, in particular at most 5%.
  • a deviation of 0% would be ideal, but this is practically unattainable from a technical point of view.
  • the seal radius equals the distance of the wing leading edge of the wing from the axis of rotation of the seal, and there is no gap between the wing and the seal for gas leakage to occur. This is particularly cheap.
  • sealing disk radius of the sealing disk in the area of the leading edge of the wing is greater than the average radius of the sealing disk means in particular that this is present over an angular range of up to 25°.
  • the wing has a more strongly curved upper side of the wing and a less curved lower side of the wing.
  • the upper surface of the wing and the lower surface of the wing are separated by the chord of the wing.
  • the angular range in which the sealing washer radius is greater than average is preferably on the wing top side.
  • the adjustment device preferably has levers for rotating the guide vanes about their respective adjustment axis and also has a connecting ring, by means of which the levers are connected to one another without play.
  • the levers are connected to the connecting ring with play. This has the disadvantage that the vibrations that occur during operation of the radial gas turbine due to the pulsating gas forces lead to wear between the connecting ring and the levers. However, the greater the play, the greater the wear. With increasing service life of the radial gas turbine, there is not only progressive wear, but also an increasing rate of wear, which is undesirable. Because the connecting ring is connected to the levers without play, Vibrations of the wings are greatly dampened or even suppressed. This reduces wear.
  • a radial gas turbine of the generic type which has (a) levers for rotating the guide vanes about the adjustment axis and (b) a connecting ring, by means of which the levers are connected to one another without play.
  • the connecting ring has spring sections between which the levers are clamped without play. This allows the connection ring to be connected to the levers without play, despite production-related tolerances.
  • a preferred design has spring elements that are more rigid in the circumferential direction, i.e. in the direction of actuation, than in the radial direction.
  • the higher spring constant in the circumferential direction than in the radial direction eliminates the vibrations that occur and the lower spring constant of the spring elements in the radial direction provides the desired flexibility when the point of application between the lever and spring element moves downwards or upwards from the central position when actuated.
  • the connecting ring is open at the ends and is designed in the form of a loop there. This makes assembly easier. It is advantageous if the gas supply device has an actuating element that has two pin-shaped elements and engages with them in a form-fitting manner in the loops. It is then only necessary for assembly to introduce the pin-shaped elements into the loops in a form-fitting manner.
  • the actuating element can have a holder and pin-shaped sections.
  • the pin-shaped sections are preferably with the holder positively and/or non-positively connected.
  • the pin-shaped sections can be designed in one piece as a U-part.
  • the holder can have a holder slot into which the U-part engages in a positive and/or non-positive manner.
  • the actuating element can have a holder and a U-part on which the pin-shaped sections are formed and which is positively connected to the holder.
  • Such an actuator is particularly easy to manufacture and assemble.
  • the dimensions or thickness and in particular the mass of the first delimiting plate is at most 30%, in particular at most 20%, greater than that of the second delimiting plate.
  • the first delimiting plate is designed to be significantly stronger than the second delimiting plate, since the one-sided bearing of the guide vanes is arranged in the first delimiting plate and, for technical reasons, has a greater axial length.
  • this has the disadvantage that different thermal expansions occur between the delimiting plates during heating and cooling, which leads to an offset of the delimiting plates and promotes jamming of the guide vanes.
  • this is avoided by the support bearing, which makes it possible to design the main bearing to be compact in the axial direction.
  • an exhaust gas turbocharger with an exhaust gas turbine according to the invention.
  • a land vehicle in particular a passenger car or a truck, with an exhaust gas turbocharger according to the invention.
  • Figure 1a shows a partially sectioned side view of a radial gas turbine 10 according to the invention with a turbine wheel 12 and a gas supply device 14.
  • the gas supply device 14 can be used to direct gas 16 from a supply channel 18 to the turbine wheel 12 at different angles of attack.
  • the guide vanes 24.i can be rotated collectively about a respective adjustment axis Ai by means of an adjustment device 26.
  • Each vane 24.i has a wing 28.i (cf. Figure 1b ) for conducting the gas 16.
  • the guide vanes 24.i are mounted on the first delimiting plate 20 in a respective main bearing 30.i.
  • the first restricting plate 20 is arranged on a turbine shaft side with respect to a turbine shaft 32 , whereas the second restricting plate 22 has a greater distance from the turbine shaft 32 .
  • Figure 1b shows a partially exploded view of the gas supply device 14 with connecting elements 23 and spherical bearings 40.
  • the connecting elements position the limiting plates 20 and 22 relative to one another, have a shoulder and act as spacers. Spacers are cheap but not necessary.
  • the boundary plates 20 and 22 can be held together as in Figure 1b Type shown take place directly via the connecting elements, for example via a rivet or indirectly via adjacent components.
  • the masses of the delimiting plates are used to optimize the size, it also being the case that the mass deviation is preferably not more than 30%.
  • Figure 2a shows a schematic view of the gas supply device 14, in which the support bearing 34 is also shown schematically.
  • the guide vane 24 is prestressed against the second delimiting plate 22 by means of an axial spring.
  • Figure 2b shows a further schematic cross-sectional view through a part of the gas supply device 14 according to a further embodiment.
  • the support bearing 34 (reference numerals without a suffix refer to all corresponding objects) comprises a concave bearing shell 38 and a bearing cap 40 , with the bearing cap 40 being formed on a bearing ball 42 in the present case.
  • the bearing ball 42 can be firmly connected to an adjustment axis 44 of the vane. Alternatively, it is accommodated in a second bearing shell 46 which is formed on the adjustment axis 44 .
  • Figure 2b also shows that the main bearing 30 has a disk element 48, the end face 50 of which bears against the vane 28 and thermally shields the inner region of the main bearing 30 from the extremely hot gas flow 16, which protects the functionality of the axial spring.
  • a disc element 48 made of ceramic, for example, provides excellent shielding effects.
  • the limiting plates are positioned and held together by a connecting element 23 so that the axial spring 36 presses the bearing ball 42 into the bearing shell 38 .
  • the connecting element 23 has shoulders as spacers, which is cheap but not necessary. It can be seen that the disc element has a ramp 52 so that the axial spring 36 exerts a radially inward centering force on the adjustment axis 44 when the latter is deflected from its desired position.
  • Figure 2b also shows that the contour of the axial spring 36 and the contour of the disk element 48 are matched in the area of the ramp, which is particularly favored by a limited setting behavior of the axial spring.
  • Figure 2c shows the axial spring 36 in a preferred design, which has a closed axial spring ring 37.1 as the outer ring, on which rectangular wave-shaped axial spring elements 37.2 are arranged.
  • Figure 2d shows the axial spring 36 in the same preferred design as in FIG Figure 2c , in which the axial spring elements 37.2 have a trapezoidal shape, which has a harder spring characteristic.
  • Figure 3a shows another part of a gas supply device 14, in which the disk element 48 is designed without a ramp and has a counter disk 49 with a collar. It can be seen that the axial spring 36 bears against the collar of the disk element 48 and the counter disk 49 in the circumferential direction, which leads to the increase in the spring rate.
  • the thermal shielding of the axial spring is particularly favorable here if the disk element (48) and the counter disk (49) are made of well-insulating materials, for example ceramics
  • Figure 3b shows another part of a gas supply device 14, in which the disk element 48 is designed as a sealing disk.
  • this sealing disk has a sealing section 54 which extends in the axial direction.
  • the sealing disc is accommodated in a recess 56, which preferably has a circular border. In other words, a cross section with respect to a plane perpendicular to the adjustment axis 44 is circular.
  • the inner diameter of the recess D 56 is greater than the outer diameter of the sealing disk D 48 .
  • Figure 3b also shows that the main bearing 30 has a bearing bushing 58 with a pronounced collar.
  • the axial spring 36 presses the bearing bush against the disk element in the form of the sealing disk 48 via the collar, which in turn presses against the vane 28 .
  • the axial spring 36 can be designed as a disk spring.
  • Figure 3c shows the analog structure Figure 3b , wherein the sealing washer 48 is integrated into the vane 24, ie the vane 24 and sealing washer 48 form one part, the integrated sealing washer having a shoulder which protrudes into the recess 56.
  • Figure 3d shows a guide vane 24 with an integrated sealing disk 48 as a one-piece component according to FIG Figure 3c .
  • Figure 4a shows a schematic sectional view in relation to a plane perpendicular to the adjustment axis 44.1.
  • the sealing disks 48 are arranged flush, taking into account a minimum distance, ie the possible continuous radius of the sealing disks has a maximum value. Starting from the wing leading edge in the opening direction, a circle segment can be seen that has a larger radius r than the continuous radius rd and completely covers the wing leading edge, i.e. the radius r corresponds to the distance between the tip of the wing leading edge and the center of the Adjustment axis 44 of guide vane 24.
  • the sealing disks 48 are arranged in recesses 56 in the first delimiting plate 20, the recess similar to the sealing disk also locally having a larger radius than the continuous radius.
  • the circular segment of the recess 56 with the larger radius is dimensioned in such a way that no collision between the sealing disk and the recess occurs over the permissible angle of rotation ⁇ .
  • the sealing disk radius r can depend on a rotation angle ⁇ , but this is not necessary.
  • Figure 4a 12 shows the position of the vanes with the blade trailing edges 62 positioned just prior to an overlap with the sealing washer 48.
  • FIG. If the angle of rotation ⁇ changes in the closing direction, the trailing edge 62.i of the wing begins to sweep over the adjacent sealing disk 48.i-1.
  • the sealing disk 48 locally has a recess 64 which is designed with a continuous transition as a type of wing support surface 66 .
  • Figure 4a shows that the sealing disk 48 has a substantially circular outer contour.
  • the recess 56 in the first delimiting plate 20 also has an essentially circular inner contour.
  • Figure 4b shows an example of a way to connect the sealing disk 48 in a rotationally fixed manner to the wing, which is favorable for the under Figure 4a described advantageous functionality of the sealing disk in interaction with the wing, ie that the wing trailing edge 62 always comes into contact with the adjacent sealing disk at the same point.
  • the sealing disk 48 has a pin on the side facing the wing, which engages in a pin bore 70 of the wing 28 .
  • the reverse design with a pin on the wing side or the use of a separate component in the form of a pin is also conceivable, which then engages in bores in the wing and the sealing disk.
  • Figure 4c Figure 12 shows the position of the vanes where all vanes 28 and washers 48 are engaged and collectively aligned, which is particularly beneficial for uniform and narrow gaps. It can also be seen that this favorable position is half-open to closed, which is particularly advantageous for efficiency.
  • Figure 5a shows that the adjustment device 26 has a lever 76.i for each guide vane 24.i, by means of which the guide vane 24.i can be rotated about the respective adjustment axis 44.i.
  • the levers 76.i are connected to one another without play by means of a connecting ring 78.
  • Each lever 76.i is clamped resiliently without play between two spring sections 80a.i, 80b.i.
  • All spring sections 80a.i, 80b.i are integrally formed on a connecting web 82, preferably on two connecting webs. It is possible, but not necessary, for the spring sections to be formed in one piece on the connecting ring; other fastening options, for example insertion, are also possible.
  • Figure 5a also shows an actuating element 84, by means of which, when rotated about its actuating axis, the movement via the connecting ring 78 in the circumferential direction is transmitted simultaneously to all levers 76.i and all levers can thus be actuated simultaneously.
  • the actuating axis which in the present case belongs to the scope of parts of the actuator (not shown), engages in an axis bore 85 of the actuating element 84 and is connected here in a rotationally fixed manner, for example by welding. It is also conceivable that the actuation axis is part of the actuation element 84 . It can also be seen that the actuating element 84 engages in the ends of the connecting ring 78, which are designed as loops 92 for this purpose. As can be seen, the connecting ring 78 is not firmly connected at the ends, which can be advantageous in terms of manufacturing technology. However, a fixed connection of the ends of the connecting ring is also possible, which results in greater rigidity.
  • Figure 5b shows the actuating element 84, which preferably has a holder 86 with two pin-shaped elements 90 and an axle bore 85 for receiving the actuating axle. It is particularly favorable to design the two pin-shaped elements in one piece as a U-part 88 on which a first section 90.1 and a second section 90.2 are formed.
  • the U-part 88 is accommodated in a slot 87 of the holder 86, preferably in a form-fitting manner, for example by means of a press fit.
  • Sections 90.1, 90.2 engage in loops 92.1, 92.2 and thus cause the connecting ring 82 to close with a positive fit.
  • Figure 5c shows a particularly advantageous design of the connecting ring 78, in which the spring sections 80 have the desired different spring constants in the circumferential direction and in the radial direction, such that the spring sections 80 have a higher spring constant in the circumferential direction than in the radial direction.
  • Figure 1b 12 shows that the first constraint plate 20 has a first constraint plate thickness d 20 .
  • the second constraint plate 22 has a second constraint plate thickness d 22 . If the boundary plates 20, 22 are not disc-shaped, as in the present case, then a compensating cylinder is used to determine the thicknesses d 20 , d 22 used, in which 90% of the mass of the respective boundary plate 20 or 22 is added.
  • the plate thicknesses d 20 , d 22 preferably deviate from one another by at most 30%.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
EP21203258.5A 2020-10-21 2021-10-18 Turbine radiale à gaz avec support d'appui Withdrawn EP3988767A1 (fr)

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DE202020005442 2020-10-21

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EP3988767A1 true EP3988767A1 (fr) 2022-04-27

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US4050844A (en) * 1976-06-01 1977-09-27 United Technologies Corporation Connection between vane arm and unison ring in variable area stator ring
JPS6314843U (fr) * 1986-07-14 1988-01-30
JPS6361545U (fr) * 1986-10-09 1988-04-23
JPS6415704U (fr) * 1987-07-17 1989-01-26
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WO2004099573A1 (fr) * 2003-05-08 2004-11-18 Honeywell International Inc. Turbocompresseur a systeme d'ajutages variables
EP1561007A1 (fr) * 2002-11-15 2005-08-10 Honeywell International, Inc. Injecteur ajustable pour turbocompresseur
EP1895106A1 (fr) * 2006-08-28 2008-03-05 ABB Turbo Systems AG Joint pour des aubes variables de guidage
DE102008005658A1 (de) * 2008-01-23 2009-07-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
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EP2199570A2 (fr) * 2008-12-20 2010-06-23 Bosch Mahle Turbo Systems GmbH & Co. KG Dispositif de chargement
EP2215340A1 (fr) * 2007-11-28 2010-08-11 Continental Automotive GmbH Écran thermique et turbocompresseur muni d'un écran thermique
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EP2236773A2 (fr) * 2009-03-11 2010-10-06 General Electric Company Bouton profilé d'aube de stator variable
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US20130216361A1 (en) * 2012-02-22 2013-08-22 Propheter-Hinckley Tracy A Vane assembly for a gas turbine engine
EP2960461A1 (fr) * 2013-02-21 2015-12-30 Mitsubishi Heavy Industries, Ltd. Turbine à gaz d'échappement à capacité variable
DE102015222598A1 (de) * 2014-11-21 2016-05-25 Borgwarner Inc. Schaufel für variable turbinengeometrie mit einachsigem, selbstzentrierendem schwenkmerkmal
JP2017067033A (ja) * 2015-10-01 2017-04-06 株式会社豊田自動織機 ターボチャージャ
EP3315729A1 (fr) * 2016-10-26 2018-05-02 MTU Aero Engines GmbH Palier d'aube directrice interne ellipsoïde
DE112016004635T5 (de) * 2015-10-07 2018-08-16 Ihi Corporation Ventilmechanismus mit variabler strömungsrate und turbolader
WO2019049873A1 (fr) * 2017-09-11 2019-03-14 いすゞ自動車株式会社 Turbocompresseur à buse variable
CN108730025B (zh) * 2018-03-26 2019-08-06 北京理工大学 一种具有无端隙可调喷嘴环叶片组件的涡轮增压器

Patent Citations (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3910716A (en) * 1974-05-23 1975-10-07 Westinghouse Electric Corp Gas turbine inlet vane structure utilizing a stable ceramic spherical interface arrangement
US4050844A (en) * 1976-06-01 1977-09-27 United Technologies Corporation Connection between vane arm and unison ring in variable area stator ring
JPS6314843U (fr) * 1986-07-14 1988-01-30
JPS6361545U (fr) * 1986-10-09 1988-04-23
JPS6415704U (fr) * 1987-07-17 1989-01-26
DE19523287A1 (de) * 1994-06-28 1996-01-04 Usui Kokusai Sangyo K Ltd Verbindungsanordnung zum Verbinden eines Abzweigelementes mit einer Hochdruck-Kraftstoffschiene
DE19959017C1 (de) * 1999-12-08 2000-12-21 Daimler Chrysler Ag Abgasturbolader für eine Brennkraftmaschine
EP1561007A1 (fr) * 2002-11-15 2005-08-10 Honeywell International, Inc. Injecteur ajustable pour turbocompresseur
DE10311205B3 (de) * 2003-03-14 2004-09-16 Man B & W Diesel Ag Leitapparat für eine Radialturbine
WO2004099573A1 (fr) * 2003-05-08 2004-11-18 Honeywell International Inc. Turbocompresseur a systeme d'ajutages variables
EP1895106A1 (fr) * 2006-08-28 2008-03-05 ABB Turbo Systems AG Joint pour des aubes variables de guidage
EP2215340A1 (fr) * 2007-11-28 2010-08-11 Continental Automotive GmbH Écran thermique et turbocompresseur muni d'un écran thermique
DE102008005658A1 (de) * 2008-01-23 2009-07-30 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung
DE102008020932A1 (de) * 2008-04-25 2009-10-29 Continental Automotive Gmbh Turbolader mit einer variablen Turbinengeometrie VTG
EP2199570A2 (fr) * 2008-12-20 2010-06-23 Bosch Mahle Turbo Systems GmbH & Co. KG Dispositif de chargement
DE102009012065A1 (de) * 2009-03-06 2010-09-09 Bosch Mahle Turbo Systems Gmbh & Co. Kg Ladeeinrichtung, insbesondere für ein Kraftfahrzeug, mit einer variablen Turbinengeometrie
EP2236773A2 (fr) * 2009-03-11 2010-10-06 General Electric Company Bouton profilé d'aube de stator variable
JP2012167640A (ja) * 2011-02-16 2012-09-06 Ihi Corp ターボチャージャ
DE102011085703A1 (de) * 2011-11-03 2013-05-08 Bosch Mahle Turbo Systems Gmbh & Co. Kg Variable Turbinen-/Verdichtergeometrie
US20130216361A1 (en) * 2012-02-22 2013-08-22 Propheter-Hinckley Tracy A Vane assembly for a gas turbine engine
EP2960461A1 (fr) * 2013-02-21 2015-12-30 Mitsubishi Heavy Industries, Ltd. Turbine à gaz d'échappement à capacité variable
DE102015222598A1 (de) * 2014-11-21 2016-05-25 Borgwarner Inc. Schaufel für variable turbinengeometrie mit einachsigem, selbstzentrierendem schwenkmerkmal
JP2017067033A (ja) * 2015-10-01 2017-04-06 株式会社豊田自動織機 ターボチャージャ
DE112016004635T5 (de) * 2015-10-07 2018-08-16 Ihi Corporation Ventilmechanismus mit variabler strömungsrate und turbolader
EP3315729A1 (fr) * 2016-10-26 2018-05-02 MTU Aero Engines GmbH Palier d'aube directrice interne ellipsoïde
WO2019049873A1 (fr) * 2017-09-11 2019-03-14 いすゞ自動車株式会社 Turbocompresseur à buse variable
CN108730025B (zh) * 2018-03-26 2019-08-06 北京理工大学 一种具有无端隙可调喷嘴环叶片组件的涡轮增压器

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