• 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:
    A turbine vane (36) adapted to be disposed in a turbine includes a suction side (50), a pressure side (48) and a bulge (52) disposed on the suction side (50). The suction side (50) extends between a leading edge (44) and a trailing edge (46) in an axial direction (28) and transverse to a longitudinal axis of the turbine vane (36) and extends beyond a height of the turbine vane (36) a radial direction (32) along the longitudinal axis. The pressure side (48) is disposed opposite the suction side (50) and extends between the leading edge (44) of the turbine vane (36) and the trailing edge (46) of the turbine vane (36) in the axial direction (28) and extends over the height (54) of the turbine vane (36) in the radial direction (32). The bulge (52) is located on the suction side (50) and projects relative to the other part of the suction side (50) in a direction transverse to both the radial (32) and axial directions (28). The turbine vane (36) has a first circumference defined at a first cross section at a first location along the height of the turbine vane (36) by selected sets of co-ordinates listed in Table 1.
    公开号:CH711695A2
    申请号:CH01266/16
    申请日:2016-09-27
    公开日:2017-04-28
    发明作者:Kumar Bhaumik Soumyik；Chouhan Rohit
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    description
    BACKGROUND TO THE INVENTION
    The subject matter disclosed herein relates to turbomachinery, and more particularly to the last vane stage in the turbine of a turbomachine.
    A turbomachine, such as a gas turbine engine, may include a compressor, a combustor, and a turbine. Gases are compressed in the compressor, mixed with a fuel and then fed into the combustion chamber, in which the gas / fuel mixture is burned. The high temperature and high energy exhaust fluids are then conveyed to the turbine where the energy of the fluids is converted to mechanical energy. In the last stage of a turbine, a small reaction at the foot can cause secondary flows transverse to the main flow direction. The secondary flows can adversely affect the final stage efficiency and lead to local turbulence at the hub which adversely affects the performance of the diffuser. As such, it would be beneficial to boost the reaction at the foot to control the secondary flow and reduce local swirl at the hub.
    BRIEF DESCRIPTION OF THE INVENTION
    Certain embodiments that correspond to the scope of the originally claimed subject matter are briefly summarized below. These embodiments are not intended to limit the scope of the claim, but rather are merely intended to provide a brief summary of possible forms of the disclosed subject matter. In fact, the article may take many forms, which may be similar to or different from the embodiments discussed below.
    In a first aspect, a turbine vane configured to be disposed in a turbine has a suction side, a pressure side, and a bulge disposed on the suction side. The suction side extends between a leading edge of the turbine vane and a trailing edge of the turbine vane in an axial direction and transverse to a longitudinal axis of the turbine vane and extends over a height of the turbine vane in a radial direction along the longitudinal axis. The pressure side is disposed opposite to the suction side and extends between the leading edge of the turbine vane and the trailing edge of the turbine vane in the axial direction and extends the height of the turbine vane in the radial direction. The bulge is disposed on the suction side of the turbine vane and projects relative to the other portion of the suction side in a direction transverse to both the radial and axial directions. The turbine vane has a first circumference defined at a first cross section at a first location along the height of the turbine vane by selected sets of coordinates listed in Table 1.
    The aforementioned turbine vane may have a second circumference defined at a second cross section at a second location along the height of the turbine vane different from the first location by selected coordinate sets listed in Table 2.
    [0006] Further, the turbine vane may have a third circumference at a third cross section at a third location along the height of the turbine vane that differs from both the first and second locations by selected coordinate sets listed in Table 3 are defined.
    Still further, the turbine vane may have a fourth circumference formed at a fourth cross section at a fourth location along the height of the turbine vane different from the first, second, and third locations by selected sets of coordinates shown in Table 4 are defined.
    Still further, the turbine vane may have a fifth circumference formed at a fifth cross section at a fifth location along the height of the turbine vane different from the first, second, third and fourth locations by selected sets of coordinates in Table 5 is defined.
    [0009] In any turbine nozzle mentioned above, the bulge may begin to protrude at an initial height at a first percentage of the height of the vane, may reach a maximum overhang at a second percentage of the height of the vane, and may terminate at a final height at a third percent height the vane stop protruding.
    In preferred embodiments of any of the turbine vanes mentioned above, the bulge may extend at least more than half a length of the suction side between the leading edge and the trailing edge.
    In certain embodiments, the bulge may extend along the entire length of the suction side.
    In some embodiments of any of the turbine vanes mentioned above, the vane may have a slope to the pressure side relative to a plane extending from a rotational axis of the turbine in the radial direction.
    In certain embodiments, the slope to the pressure side may be greater than about 0 degrees and equal to or less than about 5 degrees.
    In a second aspect, a system includes a turbine having a first annular wall, a second annular wall, and a final stage. The last stage includes a plurality of stator vanes disposed annularly about a rotational axis of the turbine between the first and second annular walls. Each vane of the plurality of vanes includes a height extending between the first and second annular walls, a leading edge, a trailing edge disposed downstream of the leading edge, a suction side extending between the leading edge and the trailing edge in an axial direction and extending over the height of the vane in a radial direction, a pressure side disposed opposite to the suction side and extending between the leading edge of the vane and the trailing edge of the vane in the axial direction and extending beyond the height of the vane into the radial direction Direction extends, and a bulge. The bulge is located on the suction side of the vane and protrudes in a direction transverse to a radial plane extending from the axis of rotation. Each vane of the plurality of vanes includes a first perimeter defined at a first cross section at a first location along the height of each vane of the plurality of vanes by selected sets of co-ordinates listed in Table 1.
    In the aforementioned system, each vane of the plurality of vanes may have a second circumference formed at a second cross section at a second location along the height of each vane of the plurality of vanes different from the first location by selected sets of coordinates in Table 2 is defined.
    Further, each vane of the plurality of vanes may have a third circumference formed at a third cross section at a third location along the height of each vane of the plurality of vanes that differs from both the first and second locations through selected sets of coordinates , which are listed in Table 3, is defined.
    Still further, each vane of the plurality of vanes may have a fourth circumference selected by a selected one at a fourth cross-section at a fourth location along the height of each vane of the plurality of vanes that is different from the first, second, and third locations Coordinate sets listed in Table 4 are defined.
    Still further, each vane of the plurality of vanes may have a fifth circumference that is at a fifth cross section at a fifth location along the height of each vane of the plurality of vanes that is different from the first, second, third, and fourth locations , defined by selected sets of coordinates listed in Table 5.
    In the system of any kind mentioned above, the leading edge and the trailing edge may have an inclination to the pressure side relative to the radial plane extending from the rotational axis in the radial direction.
    In certain embodiments, each vane of the plurality of vanes may extend to the pressure side at an angle of about 3 degrees relative to the radial plane.
    In preferred embodiments of any of the aforementioned systems, the maximum protrusion of the bulge may be between about 0.5% and about 5.0% of the height of the vane.
    In some embodiments, the maximum protrusion of the bulge may occur at between about 20% and about 40% of the height of the vane.
    In a third aspect, a system includes a turbine having a first annular wall, a second annular wall, and a final stage. The last stage includes a plurality of vanes annularly disposed between the first and second annular walls about an axis of rotation of the turbine. Each vane of the plurality of vanes includes a height between the first and second annular walls, a leading edge, a trailing edge disposed downstream of the leading edge, a suction side extending between the leading edge and the trailing edge in an axial direction and extending across the first and second annular walls Extending the height of the vane in a radial direction, a pressure side, which is arranged opposite to the suction side and extends between the leading edge of the vane and the trailing edge of the vane in the axial direction and extending over the height of the vane in the radial direction, and a bulge. The bulge is located on the suction side of the vane and protrudes in a direction transverse to a radial plane extending from the axis of rotation. Each vane of the plurality of vanes includes first, second, third, fourth and fifth circumferences.
    The first perimeter is defined at a first cross section at a first location along the height of each vane of the plurality of vanes by selected sets of co-ordinates listed in Table 1. The second perimeter is defined at a second cross-section at a second location along the height of each vane of the plurality of vanes different from the first location by selected sets of co-ordinates listed in Table 2. The third circumference is defined at a third cross section at a third location along the height of each vane of the plurality of vanes, which differs from both the first and second locations, by selected sets of co-ordinates listed in Table 3. The fourth circumference is at a fourth cross-section at a fourth location along the height of each vane of the plurality of vanes extending from the first, second and third
    Location is defined by selected sets of coordinates listed in Table 4. The fifth circumference is defined at a fifth cross section at a fifth location along the height of each vane of the plurality of vanes, which is different from the first, second, third, and fourth locations, by selected sets of coordinates listed in Table 5 , In addition, each vane of the plurality of vanes is inclined relative to the radial plane to the pressure side.
    BRIEF DESCRIPTION OF THE DRAWINGS
    These and other features, aspects and advantages of the present invention will become better understood when the following detailed description is read with reference to the accompanying drawings, in which like reference characters designate like parts throughout the drawings, in which:
    1 is a schematic representation of one embodiment of a turbomachine in accordance with aspects of the present disclosure;
    FIG. 2 is a front perspective view of one embodiment of a vane in accordance with aspects of the present disclosure; FIG.
    3 is a front view of one embodiment of a subset of vanes configured with a suction-side bulge in a stage of a turbine in accordance with aspects of the present disclosure;
    4 is a rear elevational view of one embodiment of a subset of vanes configured with a suction-side bulge in a stage of a turbine in accordance with aspects of the present disclosure;
    5 is a top sectional view of two adjacent vanes in accordance with aspects of the present disclosure;
    6 is a graphical representation of a dimensionless distribution of the restriction defined by adjacent vanes in a stage of a turbine, in accordance with aspects of the present disclosure;
    7 is a graphical representation of a dimensionless distribution of the maximum vane thickness divided by the maximum vane thickness at 50% of the span in accordance with aspects of the present disclosure;
    8 is a graphical representation of a dimensionless distribution of the maximum vane thickness divided by the axial chord, in accordance with aspects of the present disclosure;
    9 is a sectional view of a vane with a suction-side bulge in accordance with aspects of the present disclosure;
    10 shows five levels at five span locations intersecting the vane with a suction-side lobe in accordance with aspects of the present disclosure;
    11 is a cross-sectional view of a vane having a suction-side protrusion at a first height in accordance with aspects of the present disclosure;
    12 is a graphical representation of the perimeter of a cross-section of a vane having a suction-side protrusion at a second height in accordance with aspects of the present disclosure;
    13 is a graphical representation of the perimeter of a cross-section of a vane having a suction-side protrusion at a third height in accordance with aspects of the present disclosure;
    14 is a graphical representation of the perimeter of a cross-section of a nozzle having a suction-side protrusion at a fourth height in accordance with aspects of the present disclosure;
    15 is a graphical representation of the perimeter of a cross-section of a vane having a suction-side protrusion at a fifth height according to aspects of the present disclosure;
    16 is a schematic illustration of a vane inclined relative to a radially stacked airfoil toward the pressure side in accordance with aspects of the present disclosure; and
    FIG. 17 is a perspective view of a nozzle having a pressure-side slope of 3 degrees compared to a radially-stacked airfoil in accordance with aspects of the present disclosure. FIG.
    DETAILED DESCRIPTION OF THE INVENTION
    One or more specific embodiments of the present subject matter will be described below. In an effort to provide a concise description of these embodiments, not all features of an actual implementation may be described in the description. It should be appreciated that in developing any such implementation, as in any engineering or design project, numerous implementation-specific decisions must be made to meet the specific objectives of the developers, such as compliance with systemic and business constraints vary from one implementation to another. In addition, it should be recognized that while such a development effort may be complex and time consuming, it would nonetheless be a routine design, fabrication, and manufacturing endeavor for ordinary professionals having the benefit of this disclosure.
    When elements of various embodiments of the present subject are introduced, the articles "a," "an," "the," and "the" mean that there are one or more of the elements. The expressions "comprising", "containing" and "having" are to be understood in the inclusive sense and mean that there can be additional elements besides the listed elements.
    After combustion in a gas turbine, exhaust fluids exit the combustion chamber and enter the turbine. A slight reaction on the foot can cause strong secondary flows (i.e., flows transverse to the main flow direction) in the last stage of the turbine which reduce the efficiency of the final stage. In addition, secondary flows in or around the downstream rotating airfoil hub may cause undesirable turbulence, which may appear as a swirl tip in the flow orifice profile of a rotating airfoil, adversely affecting the performance of the diffuser. A vane construction having a suction side bight, a slight dip to the pressure side implemented in the last stage, and an orifice of the nozzle throat near the hub region may be used to allow reaction at the root, thereby creating secondary flows and an undesirable turbulence can be reduced.
    Referring now to the figures, Figure 1 is a schematic representation of one embodiment of a turbomachine 10 (e.g., a gas turbine). The turbomachine 10 illustrated in FIG. 1 includes a compressor 12, a combustor 14, and a turbine 16. Air, or any other gas, is compressed in the compressor 12, mixed with fuel, fed into the combustor 14, and then combusted. The exhaust fluids are conveyed to the turbine 16 where the energy from the exhaust fluids is converted into mechanical energy. The turbine includes a plurality of stages 18, including a final stage 20. Each stage 18 may include a rotating shaft coupled rotor having an annular array of axially aligned blades, blades or blades rotating about a pivot 26 and a stator having a rotor ring-shaped row of vanes included. Accordingly, the last stage 20 may include a last vane stage 22 and a last airfoil stage 24. For the sake of clarity, FIG. 1 includes a coordinate system including an axial direction 28, a radial direction 32, and a circumferential direction 34. In addition, a radial plane 30 is illustrated. The radial plane 30 extends in the axial direction 28 (along the axis of rotation 26) in one direction and then extends outwardly in the radial direction.
    FIG. 2 shows a front perspective view (ie, looking substantially in the downstream direction) of one embodiment of a vane 36. The vanes 36 in a final stage 20 are configured to intercommunicate between a first annular wall 40 and a second annular wall 42 in FIG to extend a radial direction 32. Each vane 36 may have an airfoil shape and be configured to aerodynamically interact with the exhaust gases from the combustor 14 as the exhaust fluids flow substantially downstream through the turbine 16 in the axial direction 28. Each vane 36 has a leading edge 44, a trailing edge 46 disposed downstream in the axial direction 28 from the leading edge 44, a pressure side 48, and a suction side 50. The pressure side 48 extends in the axial direction 28 between the leading edge 44 and the trailing edge 46 and in the radial direction 42 between the first annular wall 40 and the second annular wall 42. The suction side 50 extends in the axial direction 28 between the leading edge 44 and the trailing edge 46 and in the radial direction 32 between the first annular wall 40 and the second annular wall 42, the pressure side 48 opposite. The vanes 36 in the last stage 20 are arranged such that the pressure side 48 of a single vane 36 faces the suction side 50 of an adjacent vane 36. As the exhaust fluids flow to and through the passageway 38 between vanes 36, the exhaust fluids aerodynamically interact with the vanes 36 such that the exhaust fluids flow at an angular momentum relative to the axial direction 28. A slight reaction on the foot can cause strong secondary flows and undesirable turbulence in the last blade stage 20 of the turbine, which reduces the efficiency of the last blade stage 20 and the performance of the diffuser. A final vane stage 24 equipped with vanes 36 having a bulge 52 projecting from the lower portion of the suction side, which opens the nozzle throat near the hub portion (and in some embodiments a slight slope toward the pressure side 48) promote a reaction on the foot, reducing secondary flows and unwanted turbulence.
    Figures 3 and 4 show a front perspective view (ie, substantially looking downstream in the axial direction 28) and a rear perspective view (ie, looking substantially upstream against the axial direction 28) of a subset of vanes 36 which extending in a radial direction 32 between first and second annular walls 40, 42 and configured with a suction-side bulge 52 in a last vane stage 24 of a turbine 16. It should be noted that the width of the passages 38 between the vanes 36 near the lowermost end of the vanes 36 begins with a width W-i. The width W2 of the passage 38 is smallest when the bulge 52 is largest, near 20-40% along the height 54 of the guide blade 36 upwards and in the radial direction 32, and then the width W3, W4 the passage 38 toward the upper end of the vanes 36 increases, while the bulge decreases.
    Fig. 5 shows a top plan view of two adjacent vanes 36. It should be noted how the suction side 50 of the lower vane 36 faces the pressure side 48 of the upper vane. The axial chord 56 is the dimension of the vane 36 in the axial direction. The passage 38 between two adjacent vanes 36 of a stage 18 defines a (nozzle) throat D0 measured in the narrowest portion of the passage 38 between adjacent vanes 36. A fluid flows through the passage 38 in the axial direction 28. This distribution of D0 along the height of the vane 36 is explained in greater detail with respect to FIG. 6 below. The maximum thickness of each vane 36 at a given height is illustrated as Tmax. The Tmax distribution over the height of the vane 36 is explained in more detail below with reference to FIGS. 7 and 8.
    FIG. 6 shows a plot 58 of a distribution of the restriction D0 defined by adjacent vanes 36 in the last stage 20 and illustrated as a curve 60. The vertical axis 62, x, represents the percentage of the span between the first annular wall 40 and the second annular wall in the radial direction 32 or the percentage of the span along the height 54 of the vane 36 in the radial direction 32. That is, 0% of Span represents the first annular wall 40, and 100% of the span represents the second annular wall 42, and any point between 0% and 100% corresponds to a percentage distance between the annular walls 40, 42 in the radial direction 32 along the height of the vane. The horizontal axis 64, y, represents D0, the shortest distance between two adjacent vanes 36 for a given percentage of the span divided by D0, Avg, the average D0 over the entire height of the vane 36. D0 divided by the D0, Avg renders the plot 58 dimensionless so that the curve 60 remains the same when the vane stage 22 is scaled up or down for different applications. One could create a similar plot for a single size of turbine in which the horizontal axis is just D0.
    As can be seen from Fig. 6, and moving in the radial direction 32 from the first wall 40 or point 66, the bulge 52 maintains the D0 at about 80% of the mean do. At the point 68, at about the middle of the bulge 52 (eg, at about 30% along the height 54 of the vane upward), the bulge 52 begins to recover, and D0 increases to about 1.3 times the mean D0 at the second annular wall 42 or the point 70 too. This distribution of the restriction D0 promotes a reaction at the root in the last blade stage 20 which improves the efficiency of the last blade stage and the performance of the diffuser, which can result in a significant increase in power output to the turbine. In some embodiments, this may increase the power output by more than 1.7MW.
    Fig. 7 shows a graph 72 of the distribution of Tmax / Tmax at 50% of the span as a curve 74 compared to a vane of a conventional construction 76. The vertical axis 78, x, represents the percentage of span between the the first annular wall 40 and the second annular wall in the radial direction 32 or the percentage of the span along the height 54 of the vane 36 in the radial direction 32. The horizontal axis 80, y, Tmax, represents the maximum thickness of the vane 3-6 at a given percentage of the span divided by the Tmax at 50% of the span. A division of Tmax / Tmax at 50% of the span makes the plot 72 dimensionless so that the curve 74 remains the same when the vane stage 22 is scaled up or down for other applications. One could create a similar plot for a single size turbine in which the horizontal axis is just Tmax.
    As can be seen from Figure 7, as one moves in the radial direction 32 from the first ring wall 40 or point 82, Tmax begins at approximately 83% of Tmax at 50% of the span and then approaches fast Tmax at 50% of the span. From 35% of the span to about 60% of the span, Tmax is substantially equal to Tmax at 50% of the span. At point 84, or about 60% of the span, Tmax deviates from Tmax at 50% of the span and remains greater than Tmax at 50% of the span until the vane 22 reaches the second ring wall 42 or point 86.
    Fig. 8 shows a plot 86 of the distribution of Tmax / axial chord as a curve 88 versus a guide vane of a conventional construction 90. The vertical axis 92, x, represents the percentage of the span between the first ring wall 40 and the second annular wall 42 in the radial direction 32 or the percentage of span along the height 54 of the vane 36 in the radial direction 32. The horizontal axis 94, y, Tmax, divides the maximum thickness of the vane 36 for a given percentage of span by the axial chord 56, the dimension of the vane 36 in the axial direction 28. Division of Tmax by the axial chord 56 renders the plot 86 dimensionless such that the curve 88 remains the same when the vane stage 22 is for various applications - or scaled down.
    As can be seen from Fig. 8, and moving in the radial direction 32 from the first ring wall 40 or the point 96, Tmax starts smaller than in the conventional construction, but increases more than the conventional construction when the bulge reaches its maximum deviation from the conventional design at point 98. From the point 98 down to the second ring wall 42 (point 100), the Tmax approaches the Tmax of the conventional design. This maximum thickness distribution Tmax promotes a reaction at the root in the last blade stage 20 which improves the efficiency of the last blade stage and the performance of the diffuser, which can result in a significant increase in power output to the turbine. In some embodiments, this may increase the power output by more than 1.7MW.
    Fig. 9 shows a side sectional view of a vane 36 having a bulge 52 on a suction side 50. The dashed lines 102 in Fig. 9 represent the suction side wall 102 of a radially stacked vane (i.e., a similar vane construction without a bulge 52). The bulge 52 projects from the suction side 50 in a direction transverse to the radial plane 30 which extends outwardly from the axis of rotation 36 in the radial direction 32 in one direction and in the axial direction 28 in a second direction. A distance 104 represents the distance that the bulge protrudes from the hypothetical suction side 102 of a radially stacked vane without a bulge 52 at the point along the height 54 of the vane 36 where the bulge 52 has its maximum overhang. As can be seen in Figure 9, the bulge 52 may begin to protrude at a position between about 0-20% of the height of the vane 36 (i.e., 0-20% of the span from the first annular wall 40 to the second annular wall 42). That is, the profile of a vane 36 having a bulge 52 may begin from the hypothetical suction sidewall 102 of a radially stacked vane at any point from the lower end of the vane 36 (ie, where the vane 36 communicates with the first ring wall 40) coincides) to about 20% of the height 54 of the vane 36 to deviate. For example, the bulge 52 may begin protruding at approximately 0%, 2%, 5%, 15% or 20% of the height 54 of the vane 36 or anywhere therebetween. In other embodiments, the bulge may begin protruding at between about 1% and 15% of the height 54 of the vane 36 or between about 5% and 10% of the height 54 of the vane 36. The bulge 52 may have a maximum protrusion 104 (i.e., the maximum deviation from the suction sidewall 102 of a radially stacked vane) between about 0.5% and 10% of the height 54 of the vane 36. Alternatively, the maximum bulge supernatant 104 may be at between about 0.5% and 5.0% or between 1.0% and 4.0% of the height 54 of the vane 36. The bulge 52 may reach its maximum protrusion 104 at between about 20% and 40% of the height 54 of the vane 36 (i.e., between about 20% and 40% of the span from the first annular wall 40 to the second annular wall 42). For example, maximum bulge supernatant may occur at approximately 20%, 22%, 24%, 26%, 28%, 30%, 32%, 34%, 38%, or 40% of the height 54 of the vane 36 or anywhere in between , In some embodiments, the bulge 52 may reach its maximum protrusion 104 at between about 20% and 40%, between 22% and 38%, between 25% and 35%, or between 28% and 32% of the height 54 of the vane 36. Upon reaching maximum bulge supernatant 104, the profile of vane 36 with suction side bulge 52 begins to converge with suction side wall 102 of the radially stacked vane. The bulge 52 may terminate at a point between about 50% and 60% of the height 54 of the vane 36 (ie, between about 50% and 60% of the span from the first annular wall 40 to the second annular wall 42) (ie, the profile of the vane 36 there with the suction-side bulge 52 converges there with the suction side wall 102 of the radially stacked vane). In other embodiments, the bulge 52 may terminate at a location between about 52% and 58%, 53%, and 57%, or 54%, and 56% of the height 54 of the vane 36. That is, the bulge 52 may terminate at a location at approximately 50%, 52%, 54%, 56%, 58%, or 60% of the height 54 of the vane 36 or anywhere therebetween. In some embodiments, the bulge 52 may extend along the entire length of the suction side 50 in the axial direction 28 from the leading edge 44 to the trailing edge 46. In other embodiments, the bulge 52 may extend only along a portion of the suction side 50 between the leading edge 44 and the trailing edge 46. A last-stage stator 22, equipped with vanes 36 having bulges 52 on the suction side 50, promotes a reaction on the foot which helps to reduce secondary flows and unwanted turbulence. An implementation of the disclosed techniques can increase the performance of both the last stage and the diffuser, resulting in a significant gain in the output of the turbomachine. In some embodiments, the disclosed techniques may improve the performance of the last blade stage by about 200 kW or more, and may improve the diffuser performance by about 1500 kW or more for a total gain of about 1700 kW or more. It should be understood, however, that the benefits derived from an implementation of the disclosed techniques may vary from turbomachine to turbomachine.
    Another way to formulate the shape of the vane 36 is based on the coordinates Y, Z a number of different points along the circumference of the vane at different cross sections. 10 shows five planes 106, 114, 122, 130, 138 at five spans above the height of the vane 36. The plane 106 is at 6% of the span, the plane 114 is at 26% of the span, the plane 122 is 46% of the span, the 130 level is 66% of the span, and the 138 level is 86% of the span. The shape of the vane may be defined by the cross-sectional shape of the vane at these five levels 106, 114, 122, 130, 138. Cross-sectional shapes of the vane at these planes and the coordinates Y, Z of the outer circumference of the vane are illustrated in Figures 11-15 and Tables 1-5. It should be understood, however, that this is only a single embodiment and that the dimensions may vary as the vane 36 for various turbomachinery 10 (eg, from a 50 Hz machine to a 60 Hz machine or a gear machine, etc.). or is scaled down.
    Figures 11-15 show cross-sectional views of the shape of the periphery of the vane 36 at the five planes 106, 114, 122, 130, 138 at various span locations above the height 54 of the vane 36. Tables 1-5, which are shown in Figs. 11-15, respectively, the coordinates Y, Z indicate fifty points around the circumference of the vane 36 for each of the five cross sections.
    Fig. 11 is a graph 106 illustrating a cross-sectional view of a periphery or edge of the vane 36 (indicated by reference numeral 112) at a first cross-section at approximately 6% of the span. The horizontal axis of the graphical representation 106 is the y-axis 108 in meters. The vertical axis of the representation 106 is the z-axis 110 in meters and corresponds to the axis of rotation 26, as illustrated in FIG. The XZ plane corresponds to the radial plane 30, as illustrated in FIG. The circumference of the vane 36 is represented by a plane located at approximately 6% of the span. Table 1 provides the coordinates Y, Z for 50 points located along the circumference or edge 112 of the vane 36 in a plane that is about 6% of the span.
    [0042]
    Table 1
    Fig. 12 is a graph 114 illustrating a cross-sectional view of the periphery or edge of the vane 36 (indicated by reference numeral 120) at a second cross-section at approximately 26% of the span. The horizontal axis of the representation 114 is the y-axis 116 in meters. The vertical axis of the representation 114 is the z-axis 118 in meters and corresponds to the axis of rotation 26, as illustrated in FIG. The XZ plane corresponds to the radial plane 30, as illustrated in FIG. The circumference of the vane 36 is represented by a plane located at approximately 26% of the span. Table 2 provides the coordinates Y, Z for 50 points located along the circumference or edge 120 of the vane 36 in a plane that is about 26% of the span.
    [0044]
    Table 2
    Fig. 13 is a graph 122 illustrating a cross-sectional view of the periphery or edge of the vane 36 (indicated by reference numeral 128) at a third cross-section at approximately 46% of the span. The horizontal axis of the representation 122 is the y-axis 124 in meters. The vertical axis of the representation 122 is the z-axis 126 in meters and corresponds to the axis of rotation 26, as illustrated in FIG. The XZ plane corresponds to the radial plane 30, as illustrated in FIG. The circumference of the vane 36 is represented by a plane at approximately 46% of the span. Table 3 provides the coordinates Y, Z of 50 points located along the periphery or edge 128 of the vane 36 in a plane that is about 46% of the span.
    [0046]
    Table 3
    Fig. 14 shows a graphical representation 130 illustrating a cross-sectional view of a periphery or edge of the vane 36 (indicated by reference numeral 136) at a fourth cross-section at approximately 66% of the span. The horizontal axis of the representation 130 is the y-axis 132 in meters. The vertical axis of the representation 130 is the z-axis 134 in meters and corresponds to the axis of rotation 26, as illustrated in FIG. The XZ plane corresponds to the radial plane 30, as illustrated in FIG. The circumference of the vane 36 is represented by a plane at approximately 66% of the span. Table 4 provides the coordinates Y, Z for 50 points located along the circumference or edge 136 of the vane 36 in a plane that is about 66% of the span.
    [0048]
    Table 4
    Fig. 15 is a graph 138 illustrating a cross-sectional view of the periphery or edge of the vane 36 (indicated by reference numeral 144) at a fifth cross-section at approximately 86% of the span. The horizontal axis of the representation 138 is the y-axis 140 in meters. The vertical axis of the representation 138 is the z-axis 142 in meters and corresponds to the axis of rotation 26, as illustrated in FIG. The XZ plane corresponds to the radial plane 30, as illustrated in FIG. The circumference of the vane 36 is represented by a plane located at approximately 86% of the span. Table 5 provides the coordinates Y, Z for 50 points located along the periphery or edge 144 of the vane 36 in a plane that is about 86% of the span.
    [0050]
    Table 5
    权利要求:
    Claims (10)
    [1]
    A turbine vane (36) adapted to be mounted in a turbine (16) and comprising: a suction side (50) extending between a leading edge (44) of the turbine vane (36) and a trailing edge (46) of the turbine vane (36) Turbine vane (36) extends in an axial direction (28) and transverse to a longitudinal axis (150) of the turbine vane (36) and extends over a height (54) of the turbine vane (36) in a radial direction (32) along the longitudinal axis (150) ) extends; a pressure side (48) disposed opposite the suction side (50) and extending in the axial direction (28) between the leading edge (44) of the turbine vane (36) and the trailing edge (46) of the turbine vane (36) the height (54) of the turbine vane (36) extends in the radial direction (32); and a bulge (52) disposed on the suction side (50) of the turbine vane (36) and in a direction transverse to both the radial (32) and axial (28th) relative to the other portion of the suction side (50) ) Projecting direction; wherein the turbine vane (36) has a first periphery (112) defined at a first cross section (106) at a first location along the height (54) of the turbine vane (36) by selected sets of coordinates listed in Table 1 ,
    [2]
    The turbine nozzle (36) of claim 1, wherein the turbine nozzle (36) has a second periphery (120) located at a second cross-section (114) at a second location along the height of the turbine nozzle (36) extending from the first Differs by selected coordinate sets listed in Table 2.
    [3]
    The turbine nozzle (36) of claim 2, wherein the turbine nozzle (36) has a third periphery (128) disposed at a third cross-section (122) at a third location along the height (54) of the turbine nozzle (36) that extends distinguished from both the first and second digits is defined by selected sets of coordinates listed in Table 3.
    [4]
    The turbine nozzle (36) of claim 3, wherein the turbine nozzle (36) has a fourth circumference (136) located at a fourth cross-section (130) at a fourth location along the height (54) of the turbine nozzle (36) that extends from the first, second, and third digits defined by selected sets of coordinates listed in Table 4.
    [5]
    The turbine nozzle (36) of claim 4, wherein the turbine nozzle (36) has a fifth circumference (144) formed at a fifth cross-section (138) at a fifth location along the height (54) of the turbine nozzle (36) that extends from the first, second, third and fourth digits defined by selected sets of coordinates listed in Table 5.
    [6]
    The turbine nozzle (36) of any one of the preceding claims, wherein the bulge (52) at an initial height at a first percentage of the height (54) of the vane (36) begins to protrude, a maximum projection (104) at a second percentage of the height (54) reaches the vane (36) and stops protruding at a final height at a third percentage of the height (54) of the vane (36).
    [7]
    A turbine nozzle (36) according to any one of the preceding claims, wherein the bulge (52) extends over at least more than half of a length of the suction side (50) between the leading edge (44) and the trailing edge (46); wherein the bulge (52) preferably extends along an entire length of the suction side (50).
    [8]
    A turbine nozzle (36) according to any one of the preceding claims, wherein the nozzle (36) has a slope (148) to the pressure side (48) relative to a plane (30) extending from an axis of rotation (26) of the turbine (16 ) extends in the radial direction (32); wherein the slope (148) to the pressure side (48) is preferably greater than about 0 degrees and equal to or less than about 5 degrees.
    [9]
    A system comprising: a turbine (16) comprising: a first annular wall (40); a second annular wall (42); and a final stage (20) having a plurality of vanes (36) annularly disposed between the first and second annular walls (40, 42) about an axis of rotation (26) of the turbine (16), each vane (36 ) of the plurality of vanes (36) comprises: a height (54) extending between the first and second annular walls (40, 42); a leading edge (44); a trailing edge (46) disposed downstream of the leading edge (44); a suction side (50) extending between the leading edge (44) and the trailing edge (46) in an axial direction (28) and extending across the height (54) of the vane (36) in a radial direction (32); a pressure side (48) disposed opposite the suction side (50) and extending in the axial direction (28) between the leading edge (44) of the vane (36) and the trailing edge (46) of the vane (36) the height (54) of the vane (36) extends in the radial direction (32); a bulge (52) disposed on the suction side (50) of the vane (36) and projecting in a direction transverse to a radial plane (30) extending from the axis of rotation (26); and a first perimeter (112) defined at a first cross section (106) at a first location along the height (54) of each vane (36) of the plurality of vanes (36) by selected sets of co-ordinates listed in Table 1 ,
    [10]
    A system comprising: a turbine (16) comprising: a first annular wall (40); a second annular wall (42); and a final stage (20) having a plurality of stator vanes (36) disposed annularly about a rotational axis (26) of the turbine (16) between the first and second annular walls (40, 42), each stator blade (36 ) of the plurality of vanes (36) comprises: a height (54) extending between the first and second annular walls (40, 42); a leading edge (44); a trailing edge (46) disposed downstream of the leading edge (44); a suction side (50) extending between the leading edge (44) and the trailing edge (46) in an axial direction (28) and extending across the height (54) of the vane (36) in a radial direction (32); a pressure side (48) disposed opposite the suction side (50) and extending in the axial direction (28) between the leading edge (44) of the vane (36) and the trailing edge (46) of the vane (36) the height (54) of the vane (36) extends in the radial direction (32); a bulge (52) disposed on the suction side (50) of the vane (36) and projecting in a direction transverse to a radial plane (30) extending from the axis of rotation (26); and a first perimeter (112) defined at a first cross section (106) at a first location along the height (54) of each vane (36) of the plurality of vanes (36) by selected sets of co-ordinates listed in Table 1 ; a second perimeter (120) formed at a second cross-section (114) at a second location along the height (54) of each vane (36) of the plurality of vanes (36) different from the first location by selected sets of co-ordinates are listed in Table 2; a third perimeter (128) formed at a third cross-section (122) at a third location along the height (54) of each vane (36) of the plurality of vanes (36) that differs from both the first and second locations , defined by selected sets of coordinates listed in Table 3; a fourth perimeter (136) formed at a fourth cross-section (130) at a fourth location along the height (54) of each vane (36) of the plurality of vanes (36) different from the first, second and third locations , defined by selected sets of coordinates listed in Table 4; and a fifth circumference (144) formed at a fifth cross section (138) at a fifth location along the height (54) of each vane (36) of the plurality of vanes (36) extending from the first, second, third and third the fourth digit is defined by selected sets of coordinates listed in Table 5; wherein each vane (36) of the plurality of vanes (36) is inclined relative to the radial plane (30) towards the pressure side.
    类似技术:
    公开号 | 公开日 | 专利标题
    DE102007004864B4|2010-08-19|Combustion chamber of a gas turbine and combustion control method for a gas turbine
    DE102016124151A1|2017-06-22|Turbomachine and turbine blade for this
    DE102012104827A1|2012-12-06|Shape of an air scoop for a compressor
    DE102016124148A1|2017-06-22|Turbomachine and turbine nozzle for it
    DE102016123767A1|2017-06-22|Turbomachine and turbine vane for this
    DE102011052596A1|2012-04-19|Airfoil shape for a compressor inlet guide vane
    DE102016124152A1|2017-06-22|Turbomachine and turbine blade for this
    DE102011052236A1|2012-02-09|Profiled axial-radial outlet diffuser
    DE102010037047A1|2011-03-10|Highly deflecting diffuser strut with overflow slots
    DE102010016373A1|2010-12-30|Method and system for reducing the vane swirl angle in a gas turbine engine
    CH698400B1|2013-03-15|Fuel nozzle.
    DE112014006477T5|2017-06-08|Exhaust diffuser with a main support and small supports
    JP2017122439A5|2021-07-29|
    CH697921B1|2012-07-31|Turbine blade.
    DE102017122524A1|2019-03-28|Diffuser for a compressor
    DE112013005501T5|2015-08-20|Exhaust diffuser for a gas turbine
    CH711695A2|2017-04-28|Turbine vane with bulge for secondary flow control and optimal diffuser performance.
    CH709266B1|2020-06-30|Turbine blade and method for balancing a tip shroud of a turbine blade and gas turbine.
    CH701997B1|2015-03-13|Turbo engine with a honeycomb seal.
    DE102011052241A1|2012-05-10|Systems and devices relating to diffusers in gas turbines
    DE102012001777A1|2013-08-01|Gas turbine annular combustion chamber
    WO2005047656A1|2005-05-26|Guide-blade grid and turbomachine provided with a guide-blade grid
    DE102015102560A1|2015-08-27|Exhaust chamber for radial diffuser
    DE112019000898T5|2020-11-05|TURBINE BLADE AND GAS TURBINE
    DE102012002465A1|2013-08-08|Gas turbine combustor with unsymmetrical fuel nozzles
    同族专利:
    公开号 | 公开日
    US20170107835A1|2017-04-20|
    CN106907185A|2017-06-30|
    US9988917B2|2018-06-05|
    CN106907185B|2020-09-11|
    DE102016117958A1|2017-04-20|
    JP2017075601A|2017-04-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2962260A|1954-12-13|1960-11-29|United Aircraft Corp|Sweep back in blading|
    JP3621216B2|1996-12-05|2005-02-16|株式会社東芝|Turbine nozzle|
    US6508630B2|2001-03-30|2003-01-21|General Electric Company|Twisted stator vane|
    US8967959B2|2011-10-28|2015-03-03|General Electric Company|Turbine of a turbomachine|
    US9255480B2|2011-10-28|2016-02-09|General Electric Company|Turbine of a turbomachine|
    US8944774B2|2012-01-03|2015-02-03|General Electric Company|Gas turbine nozzle with a flow fence|
    US10323528B2|2015-07-01|2019-06-18|General Electric Company|Bulged nozzle for control of secondary flow and optimal diffuser performance|US10443392B2|2016-07-13|2019-10-15|Safran Aircraft Engines|Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the second stage of a turbine|
    US10443393B2|2016-07-13|2019-10-15|Safran Aircraft Engines|Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the seventh stage of a turbine|
    法律状态:
    2019-05-31| NV| New agent|Representative=s name: FREIGUTPARTNERS IP LAW FIRM DR. ROLF DITTMANN, CH |
    2019-11-15| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/884,140|US9988917B2|2015-10-15|2015-10-15|Bulged nozzle for control of secondary flow and optimal diffuser performance|
    [返回顶部]