CN114382555A

CN114382555A - Guide vane edge plate, guide vane, turbine guide and design method of guide vane edge plate

Info

Publication number: CN114382555A
Application number: CN202011110761.4A
Authority: CN
Inventors: 董明; 侯伟涛; 方力
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2020-10-16
Filing date: 2020-10-16
Publication date: 2022-04-22

Abstract

It is an object of the present invention to provide a stator vane edge plate that reduces aerodynamic losses and decreases in turbine efficiency. The invention also provides a guide vane, a turbine guide and a design method of the guide vane edge plate. The guide vane edge plate for achieving the aforementioned object has a flow passage surface, the boundary of which is delimited in one direction by a top edge close to the trailing edge of the guide vane and a bottom edge close to the leading edge and in the other direction by a first side edge close to the back side of the guide vane and a second side edge close to the basin side. The first side edge is provided with a first guide part, and the second side edge is provided with a second guide part. When one of the first side edge and the second side edge is projected towards the surface of the other side edge, the first guide part and the second guide part are overlapped for one section, and the overlapped section has the length matched with the covered area of the airflow limit streamline flow path above the flow channel surface under different working conditions.

Description

Guide vane edge plate, guide vane, turbine guide and design method of guide vane edge plate

Technical Field

The invention relates to the field of aero-engines, in particular to a guide vane edge plate, a guide vane, a turbine guider and a design method of the guide vane edge plate.

Background

The high-pressure turbine is a key component of an aircraft engine, a typical working environment has the characteristics of high temperature, high pressure, high rotating speed and the like, and the performance of the high-pressure turbine directly determines the thrust, the oil consumption level and the working reliability of the engine. The high-pressure turbine primary guider is positioned at the outlet of the combustion chamber, directly bears high-temperature gas far higher than the material capacity, needs a complex cooling design to improve the service life, and needs a fine design to improve the pneumatic performance.

The primary guider is formed by assembling a plurality of guide vanes in an inner support through pins to form a whole ring structure. The stator contains inner flange board, outer flange board, stator blade etc. adopts the simply to ally oneself with the casting usually, forms the pair structure through the welding flange board. In consideration of thermal expansion occurring in the working state, a slot with a certain width is designed between the edge plates of the adjacent guide vane assemblies, and the slot is sealed by cold air led from the compressor. The flange plate design that current engineering generally adopted guarantees that each subassembly flange plate radial height of same axial position is the exact same, and there is not radial step difference at the flange plate in the ideal conditions in week, and smooth transition when making the gas pass through the slot to make pneumatic loss minimum.

However, due to the inevitable presence of machining and assembly tolerances, adjacent vane edge plates may form radial step differences. The height and the position of the step difference depend on the processing deviation of the edge plates, the assembly deviation between the edge plates and the assembly deviation of the guide vane assembly arranged in the inner support, and the deviations are superposed with each other, so that the height and the position of the step difference have uncertainty.

If the gas flow direction is along the steps, the gas can still keep flowing smoothly after flowing through the slots between the flanges; if for contrary step for the gas flow direction, the gas direct impact is in the flange side, then can increase aerodynamic loss, reduce turbine efficiency, and under the impact of high temperature gas, the increase of the marginal plate edge local heat transfer leads to changeing the ablation to reduce the operational reliability and the life of director.

It is desirable to provide a vane edge plate to reduce aerodynamic losses due to the "reverse step" of the combustion gas flow path and the reduction in turbine efficiency.

Disclosure of Invention

It is an object of the present invention to provide a stator vane edge plate that reduces aerodynamic losses and decreases in turbine efficiency.

Another object of the present invention is to provide a guide vane comprising the aforementioned vane edge plate.

It is a further object of the present invention to provide a turbine nozzle comprising the aforementioned vane.

It is still another object of the present invention to provide a method of designing a vane edge plate capable of reducing aerodynamic loss and reduction of turbine efficiency.

A guide vane platform for a guide vane, having a flow passage surface over which a gas flow flows, the boundary of the flow passage surface being defined in one direction by a top edge of the platform near a trailing edge of the guide vane and a bottom edge near a leading edge of the guide vane, and in the other direction by a first side edge of the platform near a back side of the guide vane and a second side edge near a basin side of the guide vane;

the first side edge is provided with a first guide part, and the first guide part extends from the top edge to the bottom edge; a second guide part is arranged on the second side edge, the second guide part extends from the bottom edge to the top edge, and airflow can be guided by the first guide part and/or the second guide part;

when one of the first side edge and the second side edge is projected towards the surface of the other side edge, the first guide part and the second guide part are provided with an overlapped section, the overlapped section is formed by overlapping a first transition section in the first guide part and a second transition section in the second guide part, and the overlapped section has a length matched with the covered area of the airflow limit streamline flow path above the flow channel surface under different working conditions.

In one or more embodiments, the first guide portion is a rounded corner or a chamfered corner provided on the first side edge, and the second guide portion is a rounded corner or a chamfered corner provided on the second side edge.

In one or more embodiments, the first guide portion and the second guide portion are chamfers, and an included angle between the chamfers and the flow channel surface is 30 ° to 45 ° in a region other than the first transition section or the second transition section.

In one or more embodiments, in the first transition section, the included angle between the chamfer and the flow channel face gradually decreases from the top edge to the bottom edge to 0 °;

in the second transition section, an angle between the chamfer and the flow channel surface gradually decreases to 0 ° from the bottom edge to the top edge.

In one or more embodiments, the first side and the second side are oblique sides that incline from the blade back side toward the blade basin side, and the first side and the second side have the same inclination angle.

In order to achieve the above another object, the guide vane comprises a blade body, and an outer edge plate and an inner edge plate which are arranged at the top and the bottom of the blade body, wherein the outer edge plate and/or the inner edge plate are/is the guide vane edge plate as described above.

A turbine guide for achieving the aforementioned further object, comprising an inner support and a plurality of guide vanes assembled on the inner support, the plurality of guide vanes being in an assembled state in a full ring structure, characterized in that the guide vanes are as described above.

In one or more embodiments, a slot is arranged between two adjacent guide vane edge plates, the slot has a central line, and the limit streamline on the edge plates in the long-term operation condition of the engine has a tangent point with the central line;

wherein the first transition section and the second transition section are centrosymmetric with respect to the point of tangency.

To achieve the above-mentioned further object, a method of designing a guide vane edge plate for use in a guide vane of a turbine guide, the guide vane edge plate having a flow passage surface over which an air flow flows, the flow passage surface being bounded in one direction by a top edge of the edge plate near a leading edge of the guide vane and a bottom edge of the edge plate near a trailing edge of the leading edge of the guide vane and in another direction by a first side edge of the edge plate near a back side of the guide vane and a second side edge of the edge plate near a basin side of the guide vane, the turbine guide having a slot between adjacent guide vane edge plates, the slot having a center line;

the design method comprises the following steps:

obtaining an airflow flow path above the flow passage surface of the inner edge plate under typical working conditions;

determining the working condition of the long-term operation of the engine, and obtaining a first tangent point of the limiting streamline of the flange plate tangent to the central line under the working condition of the long-term operation;

obtaining a plurality of second tangent points of the limiting streamline of the flange plate tangent to the center line under other typical working conditions;

adding a first guide part to a first side edge and adding a second guide part to a second side edge, wherein when one of the first side edge and the second side edge is orthographically projected towards the surface where the other side edge is located, the first guide part and the second guide part have a section which is overlapped;

and setting the length of the overlapped section according to the coverage range of the second tangent point by taking the first tangent point as the center.

In one or more embodiments, the first guide portion and the second guide portion are chamfers, and the designing method further includes: the chamfer is designed with a chamfer width and depth.

The advanced effects of the invention include one or a combination of the following:

1) through setting up first guide portion and second guide portion, the length of first guide portion and second guide portion overlap part simultaneously and under the different operating modes the region phase-match that the air current flow path covered above the flow path to guaranteed that the air current under the different operating modes flows to downstream position listrium border from upstream position listrium border, the water conservancy diversion that the homoenergetic received first guide portion and/or second guide portion, reduced because of the pneumatic loss that leads to against the step, avoid the downstream listrium to directly receive the gas impact.

2) Through setting up first guide portion and second guide portion for the local heat transfer reinforcing has been avoided in the higher smoothness in low reaches listrium edge, thereby improves the operational reliability and the life of director.

Drawings

The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:

FIG. 1 is a schematic view showing a relative positional relationship between two adjacent vane edge plates in an ideal state;

FIG. 2 is a schematic view showing the relative positional relationship between adjacent vane edge plates in another state;

FIG. 3 is a schematic view showing the relative positional relationship between adjacent vane platform panels in yet another condition;

FIG. 4 illustrates a schematic view under one embodiment of the present vane platform;

FIG. 5 illustrates a schematic view of an embodiment between two adjacent vane platform plates;

FIG. 6 illustrates a schematic view of an embodiment of a chamfered structure;

FIG. 7 shows a schematic view under an embodiment of a guide vane;

fig. 8 is a partially enlarged schematic view of fig. 5.

Detailed Description

The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and are not intended to limit the scope of the present disclosure. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.

It should be noted that, where used, the following description of upper, lower, left, right, front, rear, top, bottom, positive, negative, clockwise, and counterclockwise are used for convenience only and do not imply any particular fixed orientation. In fact, they are used to reflect the relative position and/or orientation between the various parts of the object.

It is noted that these and other figures which follow are merely exemplary and not drawn to scale and should not be considered as limiting the scope of the invention as it is actually claimed. Further, the conversion methods in the different embodiments may be appropriately combined.

Fig. 1 shows a schematic diagram of a relative position relationship between two adjacent vane edge plates 1a in an ideal state. In this state, there is no radial step difference in the circumferential direction of the vane edge plate 1a, and the air flow 2a smoothly passes when flowing from the upstream side vane edge plate 1a to the downstream side vane edge plate 1a, and does not interfere with the end surface of the downstream side vane edge plate 1a, and aerodynamic loss is small.

However, due to the inevitable presence of machining and assembly tolerances, adjacent vane edge plates may form radial step differences. As shown in fig. 2, which is a schematic diagram illustrating the relative positional relationship between adjacent vane edge plates in another state, there is a radial step difference between adjacent vane edge plates 1b in the circumferential direction, wherein the radial height of the vane edge plate 1b on the downstream side of the gas flow 2b is lower than the radial height of the vane edge plate 1b on the upstream side, and a "down-step" relative positional relationship is formed between the adjacent vane edge plates 1 b. The air flow 2b can keep smooth flow even when flowing from the upstream guide vane edge plate 1b to the downstream guide vane edge plate 1b, and does not interfere with the end surface of the downstream guide vane edge plate 1b, so that aerodynamic loss is small.

But as described in the background, there is uncertainty in the step difference height and location. As fig. 3 shows a schematic view of the relative positional relationship between adjacent vane edge plates in a further state, there is a radial step difference between adjacent vane edge plates 1c in the circumferential direction, wherein the radial height of the vane edge plate 1c on the downstream side of the gas flow 2c is higher than the radial height of the vane edge plate 1c on the upstream side, and a relative positional relationship of "reverse step" is formed between the adjacent two vane edge plates 1 c. When the air flow 2c flows from the upstream-side vane edge plate 1c to the downstream-side vane edge plate 1c, it interferes with the end surface 11c of the downstream-side vane edge plate 1 c. Airflow 2c impacts on flange plate end face 11c, aerodynamic loss can be increased, turbine efficiency is reduced, and under the impact effect of high-temperature gas, local heat exchange enhancement at the edge of the flange plate leads to easier ablation, so that the working reliability and the service life of the guider are reduced.

In order to reduce the aerodynamic loss phenomenon in the existing guide vane edge plate caused by the position of the reversed step, the invention provides a guide vane edge plate. FIG. 4 illustrates a schematic view of an embodiment of the present vane platform. The stator vane edge plate 1 has a flow surface 10, above which the gas flows. It is understood that the guide vane edge plate 1 is used in a guide vane, and fig. 4 not only shows the structure of the guide vane edge plate 1, but also shows the positional relationship between the vane body 3 and the guide vane edge plate 1 in the guide vane. The positional relationship of features in the guide vane platform 1 is described below in terms of the orientation of the features in the guide vane. The guide vane has a leading edge 32 and a trailing edge 31 in one direction and a bowl side 33 and a back side 34 in the other direction. The boundary of the flow passage face 10 is, as shown in the figure, delimited in one direction by a top edge 12 of the rim plate close to the guide blade trailing edge 31 and a bottom edge 13 close to the guide blade leading edge 32, and in the other direction by a first side edge 14 of the rim plate close to the guide blade back side 34 and a second side edge 15 close to the guide blade basin side 33. It will be understood from the drawings and the foregoing description that the foregoing one direction refers to a direction from the leading edge 32 to the trailing edge 31 or vice versa, and the foregoing another direction refers to a direction from the basin side 33 to the back side 34 or vice versa.

It should be noted that the top and bottom edges are only used to reflect the relative position of the edges in the flange, and do not refer to a specific top or bottom meaning. Meanwhile, the "edge" referred to herein may be a structure having a certain thickness.

A first guide portion 141 is provided on the first side edge 14, and the first guide portion 141 extends from the top edge 12 toward the bottom edge 13. The second side edge 15 is provided with a second guide portion 151, and the second guide portion 151 extends from the bottom edge 13 toward the top edge 12. Wherein the air flow may be guided by the first guide portion 141 and/or the second guide portion 151, so that when flowing from the rim plate upstream in the flow direction to the rim plate downstream, it can be guided by the first guide portion 141 and/or the second guide portion 151 to reduce the aerodynamic loss phenomenon due to the "reverse step".

When the first side 14 and the second side 15 are orthographically projected toward the other side, the first guide portion 141 and the second guide portion 151 have a segment that overlaps with each other. To further embody the above-mentioned features, fig. 5 shows a schematic view of an embodiment between two adjacent vane edge plates, which is more easily shown in fig. 5, in the orthographic projection, the first guide portion 141 and the second guide portion 151 have a section 100 overlapped with each other, and the overlapped section is formed by overlapping the first transition section 142 in the first guide portion 141 and the second transition section 152 in the second guide portion 151.

Since the airflow 10 flows from the guide vane's blade bowl side 33 to the blade back side 34 at the guide vane's leading edge 32 and the airflow 10 flows from the guide vane's blade back side 34 to the blade bowl side 33 at the guide vane's trailing edge 31 when the guide vane is in operation. Thus, as schematically illustrated in FIG. 5, the flow paths of the two gas flows 10, the region of the gas flow 10 near the leading edge 32 of the guide blade, will flow from the left-hand vane edge plate 1 to the right-hand vane edge plate 1 as shown in the figure, where the left-hand vane edge plate 1 is in an upstream position in the flow path of the gas flow 10 and the right-hand vane edge plate 1 is in a downstream position in the flow path of the gas flow 10. The region of the air flow 10 near the trailing edge 31 of the guide blade will flow from the vane edge plate 1 on the right side to the vane edge plate 1 on the left side as shown in the figure, where the vane edge plate 1 on the left side is in the downstream position of the flow path of the air flow 10 and the vane edge plate 1 on the right side is in the upstream position of the flow path of the air flow 10. The first guide portion 141 and the second guide portion 151 are provided to allow the airflow 10 to be guided by the first guide portion 141 or the second guide portion 151 regardless of whether the airflow is flowing near the leading edge 32 of the guide vane or near the trailing edge 31 of the guide vane, thereby reducing the reverse step effect.

Because under different operating conditions, the flow path of the airflow 10 will change, for example, when a limit streamline in the airflow 10 may flow from the blade basin side 33 to the blade back side 34 at the leading edge 32 of the blade in one operating condition, the limit streamline may not flow through the adjacent edge plate, but turns back at the first transition section 142, or only flows through the position of the second transition section 152 of the adjacent edge plate, that is, turns back, by providing the first transition section 142 and the second transition section 152, it is ensured that under different operating conditions, the airflow can be guided by the first guide portion 141 or the second guide portion 151 when flowing through the boundary of the guide blade edge plate 1, and the inverse step effect is reduced. The first transition section 142 and the second transition section 152 respectively have lengths matched with the coverage areas of the airflow limit streamline flow paths above the flow channel surface under different working conditions, that is, the overlapping sections have lengths L as shown in the figure, and the lengths L are matched with the coverage areas of the airflow limit streamline flow paths above the flow channel surface under different working conditions, so that the effective guidance of the airflow under different working conditions is realized, and the reverse step effect is further reduced. It is understood that a certain margin may be added to the length L in order to match the machining tolerance generated by machining the first guide portion 141 and the second guide portion 151.

The limiting streamline is a flow path closest to the edge of the rim plate when the air flows on the flow path surface.

While one embodiment of the present vane platform is described above, in other embodiments of the present vane platform, the present vane platform may have more details in many respects than the embodiments described above, and at least some of these details may vary widely. At least some of these details and variations are described below in several embodiments.

In one embodiment of the stator vane edge plate, the first guide 141 is a fillet or chamfer opening on the first side 14 and the second guide 151 is a fillet or chamfer opening on the second side 15. Through seting up the chamfer or the fillet structure at the side, can reduce the radial height that is located downstream side stator flange board at the edge to the active manufacturing is as before "in the same direction as the step" structure, and then reduces aerodynamic loss. In other embodiments of the vane edge plate, the structure of the first guide portion 141 and/or the second guide portion 151 may have many suitable deformations or variations, but not limited thereto, for example, the first guide portion 141 and/or the second guide portion 151 may have an arc structure with one side open and the other side concave. In one embodiment, the chamfer/fillet configuration is formed by machining after the platform is cast.

In an embodiment of the vane edge plate, the first guide portion 141 and the second guide portion 151 are chamfered, and as fig. 6 shows a schematic view of an embodiment of the chamfered structure, it can be understood that as the chamfered structure in fig. 6 schematically shows the structure of the second guide portion 151, the structure of the first guide portion 141 may be the same as that of the second guide portion 151, and details thereof are not repeated. In the first guide portion 141 and the second guide portion 151 except for the first transition section 142 and the second transition section 152, an included angle x between the chamfer and the flow path surface 10 is 30 ° to 45 °. Thereby ensuring smooth transition of the air flow 10 at the chamfer structure as shown in fig. 6, reducing or even eliminating collision with the end surface of the guide vane edge plate 1 at the downstream position, and reducing aerodynamic loss. It can be understood that if the included angle x is too small, a part of the airflow still collides with the end surface of the guide vane edge plate 1 to cause aerodynamic loss; if the included angle x is too large, interference and collision between the airflow and the chamfer part can be caused, and unnecessary aerodynamic loss can also be caused. After a plurality of tests, the included angle x between the chamfer and the flow passage surface 10 is preferably 30-45 degrees.

In one embodiment of the guide vane edge plate, in the first transition section 142, the included angle x between the chamfer and the flow surface 10 gradually decreases from the top edge 12 to the bottom edge 13 to 0 ° in the second transition section 152, and the included angle x between the chamfer and the flow surface 10 gradually decreases from the bottom edge 13 to the top edge 12 to 0 °, thereby ensuring that the flow path of the flow path 10 between two adjacent edge plates can keep "smooth step".

In one embodiment of the stator blade edge panel, the first side edge 14 and the second side edge 15 are oblique edges which are inclined from the blade back side 34 to the blade basin side 33 as shown in the figure, and the first side edge 14 and the second side edge 15 have the same inclination angle to ensure that the assembly trailing edge panels can be matched with each other. In other embodiments different from those shown, the first side edge 14 and the second side edge 15 have other suitable modifications or variations, but not limited thereto. As in one embodiment, the first side edge 14 and the second side edge 15 are each perpendicular to the top edge 12.

The guide vane platform as in one or more of the previous embodiments may be applied in a guide vane as shown in fig. 7, the guide vane 4 comprising a main body 40 and outer and

inner platforms

41 and 42 arranged at the top and bottom of the main body 40, the outer platform 41 being in some documents referred to as a tip shroud. Wherein the outer and/or

inner edge plates

41, 42 are vane edge plates 1 as in one or more of the previous embodiments. It is understood that in the guide vane shown in the figures, the outer edge plate 41 and the inner edge plate 42 are both the guide vane edge plate 1 with the guide portions described above, and the guide vane edge plate 1 may also be applied only as the outer edge plate 41 or the inner edge plate 42 in the guide vane.

Further, the guide vane structure as shown in fig. 7 may be a part schematically showing a turbine guide, the turbine guide including an inner support and a plurality of guide vanes assembled on the inner support, the plurality of guide vanes may be circumferentially distributed along an outer circumferential side of the inner support as shown in fig. 7 so as to be in a full ring structure in an assembled state. The direction of the airflow at the outlet of the combustion chamber is axial, and the gas expands and accelerates through the guide vanes 4 and changes the direction of the airflow, and then enters the downstream rotor blades at a certain angle to expand and do work to output power.

Fig. 8 is a partial enlarged view of fig. 5, and referring to fig. 5 and 8, in an embodiment of the turbine vane, a slot 18 is formed between two adjacent vane edge plates 1, the slot 18 is schematically shown in the figure, and in the actual assembly process, the width of the slot 18 is actually small, such as a slot with a width of about 0.5mm after assembly in some embodiments, but the slot is expanded after the engine runs, and becomes smaller. The slot 18 has a center line 19, and a tangent point 17 is formed between the limiting streamline 110 on the edge plate and the center line 19 under the long-term operation condition of the engine, wherein the first transition section 142 and the second transition section 152 are centrosymmetric by taking the tangent point 17 as a center. Meanwhile, since the included angle x between the chamfer and the flow passage surface 10 in the first transition section 142 gradually decreases from the top edge 12 to the bottom edge 13 to 0 ° in the second transition section 152, the included angle x between the chamfer and the flow passage surface 10 gradually decreases from the bottom edge 13 to the top edge 12 to 0 °. The arrangement is such that from any position, the flow from the first transition section 142 toward the second transition section 152 from the tangent point 17 toward the position on the side of the bottom edge 13 is "down step", and the flow from the second transition section 152 toward the first transition section 142 from the tangent point 17 toward the position on the side of the top edge 14 is also "down step". Therefore, the air flow passing through the slot 18 is ensured to be 'smooth step' under the working condition of long-term operation of the engine, so that the pneumatic loss is reduced.

Another aspect of the present invention also provides a method of designing a vane platform for use in designing a vane platform in a turbine nozzle guide vane. The stator plate 1 has a flow surface 10, as shown in fig. 4, over which the gas flows. The boundary of the flow passage face 10 is, as shown in the figure, delimited in one direction by a top edge 12 of the rim plate close to the guide blade trailing edge 31 and a bottom edge 13 close to the guide blade leading edge 32, and in the other direction by a first side edge 14 of the rim plate close to the guide blade back side 34 and a second side edge 15 close to the guide blade basin side 33. In the assembled state of the stator plate 1 in the turbine guide, a slot 18 is provided between two adjacent stator plates 1, the slot 18 having a centre line 19.

The design method comprises the following steps:

and obtaining the airflow flow path above the flow passage surface of the edge plate in the typical working condition, specifically obtaining the airflow flow path on the edge plate through full three-dimensional CFD calculation.

The long-term engine operating condition is determined and a first tangent point where the platform limit streamline is tangent to the centerline is obtained, which may be a tangent point 17 as shown in fig. 8.

Subsequently, a plurality of second tangent points of the flange limit streamline tangent to the center line under other typical working conditions are obtained.

Subsequently, a first guide portion 141 is added for the first side 14, and a second guide portion 151 is added for the second side 15. When the first side 14 and the second side 15 are orthographically projected toward the other side, the first guide portion 141 and the second guide portion 151 have a single segment overlapping each other.

Then, the length L of the overlapping segment is set according to the coverage of the second tangent point, with the first tangent point, i.e. the tangent point 17, as the center. Centering the tangent point 17 means that the tangent point 17 is centered at the middle of the length L. It is understood that a certain margin may be added to the length L in order to match the machining tolerance generated by machining the first guide portion 141 and the second guide portion 151.

In one embodiment, the first guide part 141 and the second guide part 151 are chamfers, and the design method further includes designing a chamfer width and depth for the chamfers. In one embodiment, the optimal design chamfer width and depth can be obtained by full three-dimensional CFD calculations.

Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.

Claims

1. A guide vane edge plate for a guide vane having a flow passage surface over which a gas flow flows, the boundary of the flow passage surface being defined in one direction by a top edge of the edge plate near a guide vane trailing edge and a bottom edge near a guide vane leading edge and in the other direction by a first side edge of the edge plate near a guide vane back side and a second side edge near a guide vane basin side, characterized in that:

2. The leading vane edge plate of claim 1,

the first guide portion is arranged on a fillet or a chamfer of the first side edge, and the second guide portion is arranged on a fillet or a chamfer of the second side edge.

3. The leading vane edge plate of claim 2,

the first guide portion and the second guide portion are chamfers, and in the region except the first transition section or the second transition section, an included angle between each chamfer and the corresponding flow channel surface is 30-45 degrees.

4. The leading vane edge plate of claim 3,

in the first transition section, the included angle between the chamfer and the flow channel face gradually decreases from the top edge to the bottom edge to 0 °;

5. The leading vane edge plate of claim 1,

the first side edge and the second side edge are oblique edges which face the leaf back side and incline the leaf basin side respectively, and the first side edge and the second side edge have the same inclination angle.

6. A guide vane comprising a main body, and an outer edge plate and an inner edge plate provided on the top and bottom of the main body, characterized in that the outer edge plate and/or the inner edge plate is/are the guide vane edge plate as claimed in any one of claims 1 to 5.

7. A turbine guide comprising an inner support and a plurality of guide vanes assembled on the inner support, the plurality of guide vanes being in an assembled state in a full ring configuration, wherein the guide vane is the guide vane of claim 6.

8. The turbine vane of claim 7 wherein a slot is provided between adjacent vane platforms, said slot having a centerline, and wherein the limiting streamlines on the platforms have tangency points with said centerline during extended engine operation;

9. A method of designing a stator vane panel for use in a turbine nozzle guide vane, the stator vane panel having a flow passage surface over which a gas flow flows, the flow passage surface being bounded in one direction by a top edge of the panel adjacent a leading edge of a guide vane and a bottom edge of the panel adjacent a trailing edge of the leading edge of the guide vane and in another direction by a first side edge of the panel adjacent a back side of the guide vane and a second side edge of the panel adjacent a basin side of the guide vane, in the turbine nozzle a slot having a centerline between adjacent stator vane panels;

the design method is characterized by comprising the following steps:

10. The method of designing a vane edge plate of claim 9,

the first guide portion and the second guide portion are chamfers, and the design method further includes: the chamfer is designed with a chamfer width and depth.