• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    What is provided is a turbine bucket blade (10) having a pressure surface (12) and a suction surface (11), the characteristics of the pressure and suction surfaces at a local span position of the turbine airfoil (10) being such as to define a turbine blade airfoil curvature CR and CR or to define a thickness distribution line TR of the turbine airfoil (10) such that the curvature line CR and / or the thickness distribution line TR has a line profile with at least two curvature sign changes. In this case, based on the installation orientation of the turbine blade (10) in the gas turbine, the curvature line CR and the thickness distribution line TR at the local span position correspond to the axial course of the respective center point or the respective distance between two corresponding points on the pressure and suction surfaces (12, 11 ) which oppose each other in a cross-section through the turbine blade (10) at the local span position at the same axial position. Starting from the local span position, for further local span positions along a radial direction of the turbine airfoil (10), the number of curvature sign alternations of respective curvature lines C R and / or thickness distribution lines T R decreases.
    公开号:CH702109B1
    申请号:CH01706/10
    申请日:2010-10-19
    公开日:2016-01-15
    发明作者:Kevin Richard Kirtley
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Background to the invention
    The invention described herein relates to a turbine blade leaf construction.
    Conventional turbine blade constructions use an arcuate curve whose radius of curvature changes continuously from the leading edge to the trailing edge, but always has one and the same sign, so that it is purely concave. Moreover, in the case of conventional gas turbine blades, the thickness distribution along the line of curvature is also curved with a radius of curvature that changes continuously from the leading edge to the trailing edge, but always has the same sign, so that it is also purely concave. Such configurations result in energy extraction and relatively efficient flow through the turbine when the gas flow is two-dimensional in the plane defined by the curvature line in a cylindrical polar coordinate frame.
    It has often been observed that the flow is substantially three-dimensional and non-planar, and that the pure concavity of turbine blades may be less efficient in these cases than in the two-dimensional case. The desire to increase the efficiency of a turbine airfoil in which the flow is three-dimensional has therefore caused conventional airfoils to have radial pressure gradients with a view to thin trailing edges, specially adapted trailing load curves, and pitch and deflection to modulate the distribution of the flow traversing the channel.
    Often, however, mechanical limitations limit the thinness of the trailing edge, and the rotation of the blade blades requires the use of radial blade elements to avoid high bending loads during rotation, precluding aggressive deflection and tilt. In view of these results, formation of the contour of the end wall with bumps and grooves in the sheet channel and extensions upstream and downstream have been described to modulate the development of the secondary flow in the vicinity of the end wall of the blade root. The disadvantage is that the contouring of the end wall can cause manufacturing and use problems, e.g. with regard to the casting of the grooves or the need for a corrugated sub-platform friction damper for blades.
    Object of the present invention is therefore to provide an improved turbine blade with contoured pressure and suction sides, which is easy to manufacture and allows an increase in the efficiency of three-dimensional flows.
    Brief description of the invention
    According to the invention, the turbine blade for extracting energy in a gas turbine on a pressure and a suction surface, wherein the properties of the pressure and suction surfaces are formed at a local span position of the turbine blade to form a curvature CR of the turbine blade and / or to define a thickness distribution line TR of the turbine blade so that the line of curvature CR and / or the thickness distribution line TR has a line course with at least two changes of curvature. Here, based on the installation orientation of the turbine airfoil in the gas turbine, the curvature line CR and the thickness distribution line TRan of the local span position correspond to the axial course of the respective center and the respective distance between two corresponding points on the pressure and suction surfaces, which are in a cross section through the turbine blade at the local span position each at the same axial position. According to the invention, starting from the local span position for further local span positions along a radial direction of the turbine airfoil, the number of curvature sign alternations of respective curvature lines CR and / or thickness distribution lines TRab increases.
    Further, a method for forming a pressure and a suction surface of a turbine blade according to the invention is disclosed, comprising the steps of: analyzing a three-dimensional flow path of fluid flowing over the turbine blade; and designing surface characteristics of the pressure and suction surfaces at a local span position of the turbine airfoil to cooperatively define, according to the analysis, at least one of a curvature line CR and a thickness distribution line TR of the turbine airfoil such that the curvature line CR and / or the thickness distribution line TR comprises at least two directional turns , According to the method, the step of designing further includes, starting from the local span position, changing the area characteristics for further local span positions along a radial direction of the turbine blade so that the number of curvature sign alternations of respective curvature lines CR and / or thickness distribution lines TR decreases.
    These and other features will become more apparent from the following description taken in conjunction with the drawings.
    Brief description of the drawings
    The treated as the invention treated subject matter is specifically shown in the claims attached to the specification and claimed separately. The foregoing and other features and advantages of the invention will become apparent upon reading the following detailed description taken in conjunction with the accompanying drawings, in which:<Tb> FIG. 1 <SEP> shows a radial view of a turbine blade;<Tb> FIG. 2 <SEP> is a graph of a thickness change line of the turbine airfoil of FIG. 1;<Tb> FIG. Fig. 3 <SEP> shows a schematic three-dimensional radial view of a turbine airfoil;<Tb> FIG. FIG. 4 shows the turbine bucket blade of FIG. 3 in a perimetric view; FIG.<Tb> FIG. FIGS. 5-8 <SEP> show radial views of the turbine airfoil of FIG. 5 at increasing radial positions; and<Tb> FIG. FIG. 9 shows a schematic three-dimensional radial view of a turbine airfoil. FIG.
    The detailed description, by way of non-limiting example with reference to the drawings, illustrates embodiments of the invention, together with advantages and features.
    Detailed description of the invention
    Referring to Figures 1 and 2, a turbine blade 10 is shown which serves to recover energy in a gas turbine, and which has a suction surface 11 and a pressure surface 12. The suction surface 11 and the pressure surface 12 each have radially corresponding surface properties at a local span position of the turbine airfoil 10 which cooperatively define at least either a curvature CR and / or a thickness distribution line TR with respect to an axial chord of the turbine airfoil 10 to have a line of at least have two curvature sign changes. The number of curvature sign changes decreases along a radial direction of the turbine airfoil 10 from the local span position for further local span positions. In some cases, the number of sign changes decreases to zero.
    The convex and concave curvature of the curvature line CR and / or the thickness distribution TR for a turbine bucket blade 10 having an end wall only at the root point will be located substantially within about 10% of the span of the turbine bucket blade 10 near its root. The same applies in the opposite way to turbine blade blades having end walls at their tip. For turbine airfoils having end walls at both their root and tip, the convex and concave curvature may be applied within 10% of the span of each end wall. In some cases, the convex and concave curvature of the curvature line CR and / or the thickness distribution TR (see, for example, FIG. 9) may extend beyond the above-described ranges.
    Referring to Figure 3, the turbine blade 10 having a line of curvature CR and / or a thickness distribution TR that is both convex and concave may have varying surface characteristics at increasing radial positions. In one embodiment, the turbine bucket blade 10 has at least first, second, third, and fourth topographies 20, 30, 40, and 50, respectively, along a radial direction of the turbine airfoil 10. As shown in FIGS. 4-8, these topographies correspond to section lines 5-5 (topography 20, shown in FIG. 5), 6-6 (topography 30, shown in FIG. 6), 7-7 (topography 40, in FIG 7 and 8-8 (topography 50 shown in FIG. 8) each cut by the perimetric view of the span of the turbine airfoil 10 of FIG.
    In one embodiment, the area characteristics of the suction surface 11 and the pressure surface 12, as shown in FIG. 5, at the local span position of the turbine airfoil 10 that corresponds to the topography 20, form near the leading edge and trailing edge of the turbine airfoil 10 a relatively irregular nose portion 21 and a relatively irregular end portion 22. That is, the nose portion 21 is at the local span portion of the turbine blade 10, which corresponds to the topography 20, formed at its inlet opening with opposite recessed areas 23 and 24, while the end portion 22 through a single recessed area 25 is characterized.
    As shown sequentially in FIGS. 6-8, the turbine bucket blade 10 at the span positions corresponding to the topographies 30, 40, and 50 of the turbine airfoil 10 has features that become increasingly insignificant as it progresses along the radial direction of the turbine airfoil 10 become. For example, the corresponding shapes of the nose portion 21 and the end portion 22 become increasingly even. That is, the nose portion 21 may be relatively bead-shaped at a radial position of the turbine airfoil 10 and gradually lose its bead shape along a radial direction of the turbine airfoil 10. Similarly, the end portion 22 may be curved at a radial position of the turbine airfoil 10 in the direction of turbine stage rotation, with the curvature decreasing along a radial direction of the turbine airfoil 10 and / or possibly reversing the direction. Finally, as shown in FIG. 8, the number of curvature sign changes measured along a radial direction of the turbine airfoil 10 measured from the local span position corresponding to the topography 20 may decrease to zero. Accordingly, the turbine bucket blade 10 at the span position corresponding to the topography 50 is largely similar to a conventional turbine bucket blade.
    While FIGS. 4-8 collectively illustrate how the number of turns of sign changes at least the line of curvature CR and / or the plot of the thickness distribution TR decreases towards zero, it should be understood that this is merely illustrative and that other forms may be used. For example, in some cases, the number of curvature sign changes may only decrease to 1 or more. In other instances, some topographical features at a particular chord position of a turbine airfoil along a radial direction of the turbine airfoil may become increasingly insignificant without causing the curvature line CR or the thickness distribution line TR of the turbine airfoil to change the sign of curvature at that particular chord position.
    As shown in Figure 9, a second turbine bucket blade 100 according to another embodiment may have a chordal length CL substantially equal at two or more radial (or span) positions where the surface properties cooperatively at least the line of curvature CR and / or define the thickness distribution line TRso to have a line trace with at least two curvature sign changes. In this case, the convex and concave curvature of the curvature line CR and / or the thickness distribution line TR of the turbine airfoil 100 extend beyond the above-described ranges. Accordingly, the additional topographies 200, 300, 400, and 500, which are not necessarily located near the root or the peak, become progressively insignificant with the progression along the radial direction.
    The invention further relates to an unclaimed method for forming a pressure and a suction surface of a turbine blade according to the invention, comprising the steps of: analyzing a three-dimensional flow path of fluid flowing over the turbine blade; and designing surface characteristics of the pressure and suction surfaces at a local span position of the turbine airfoil to cooperatively define, according to the analysis, at least one of a curvature line CR and a thickness distribution line TR of the turbine airfoil such that the curvature line CR and / or the thickness distribution line TR comprises at least two directional turns ,
    According to the method, the step of designing further includes, starting from the local span position, changing the area characteristics for further local span positions along a radial direction of the turbine blade so that the number of curvature sign alternations of respective curvature lines CR and / or thickness distribution lines TR decreases. In some cases, these changes will cause the number of sign changes to decrease to one or more sign changes. In other cases, the changes will cause the number of sign changes to decrease to zero.
    What is provided is a turbine bucket blade 10 having a pressure surface 12 and a suction surface 11, wherein the characteristics of the pressure and suction surfaces at a local span position of the turbine airfoil 10 are formed to a turbine blade curvature line CR and / or a turbine blade airfoil thickness TR 10 so that the line of curvature CR and / or the thickness distribution line TR has a line course with at least two changes of curvature. Here, based on the installation orientation of the turbine blade 10 in the gas turbine, the curvature CR and the thickness distribution line TRan of the local span position corresponds to the axial course of the respective center or the respective distance between two corresponding points on the pressure and suction surface 12, 11, which in a Cross section through the turbine blade 10 at the local span position opposite each other at the same axial position. From the local span position, for further local span positions along a radial direction of the turbine airfoil 10, the number of curvature sign alternations of respective curvature lines CR and / or thickness distribution lines TRab decreases.
    LIST OF REFERENCE NUMBERS
    [0021]<Tb> turbine blade <September> 10<Tb> suction <September> 11<Tb> pressure area <September> 12<Tb> line of curvature <September> CR<Tb> thickness distribution line <September> TR<tb> Topography <SEP> 20<Tb> nose section <September> 21<Tb> end <September> 22<tb> Reset areas <SEP> 23, 24, 25<tb> Second Topography <SEP> 30<tb> Third Topography <SEP> 40<tb> Fourth Topography <SEP> 50<tb> Second turbine blade <SEP> 100<tb> Additional Topographies <SEP> 200, 300, 400, 500<Tb> chord <September> CL
    权利要求:
    Claims (4)
    [1]
    A turbine blade (10) for depleting energy in a gas turbine, comprising:a printing surface (12) having printing surface properties; anda suction surface (11) with suction surface properties,wherein the properties of the pressure and suction surfaces at a local span position of the turbine airfoil (10) are configured to define a turbine blade curvature line CR and / or a turbine blade airfoil thickness distribution line (10) such that the curvature line CR and / or the thickness distribution line TR curve having at least two curvature sign changes,wherein, with respect to the installation orientation of the turbine airfoil (10) in the gas turbine, the curvature line CR and the thickness distribution line TRan of the local span position correspond to the axial course of the respective center and the respective distance between two corresponding points on the pressure and suction surfaces (12, 11) are opposite each other at the same axial position in a cross section through the turbine blade (10) at the local span position,wherein, starting from the local span position for further local span positions along a radial direction of the turbine airfoil (10), the number of curvature sign alternations of respective curvature lines CR and / or thickness distribution lines TR decreases.
    [2]
    The turbine bucket blade (10) of claim 1, wherein from the local span position for further local span positions along a radial direction of the turbine airfoil (10), the number of curvature sign alternations of respective curvature lines CR and / or thickness distribution lines TR to zero decreases.
    [3]
    The turbine bucket blade (10) of claim 1 or 2, wherein a chord length CL of the turbine airfoil (10) is axially spaced at the local span position and at least one further span position spaced from the local span position along the radial direction of the turbine airfoil (10) , is essentially the same.
    [4]
    A turbine blade according to any one of claims 1 to 3, wherein a chord length CL of the turbine blade (10) in the axial direction is substantially equal at two or more local span positions where the respective surface characteristics of the pressure and suction surfaces are a respective line of curvature CR and / or a respective one Thickness distribution line TRso define that the respective curvature line CRund / or the respective thickness distribution line TR has a line course with at least two changes in curvature.
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2021-05-31| PL| Patent ceased|
    优先权:
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    US12/605,054|US8393872B2|2009-10-23|2009-10-23|Turbine airfoil|
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