CN218030298U - Turbine stator blade, turbine stator blade ring, turbine and gas turbine - Google Patents

Abstract

The utility model relates to a quiet leaf of turbine, quiet leaf ring of turbine, turbine and gas turbine. The turbine stationary blade comprises an outer edge plate, a blade body, a rear hook and a front hook, wherein the blade body is arranged on the inner side of the outer edge plate and is provided with a front edge and a tail edge; the rear hook comprises a rear main body and a rear boss part, the rear boss part is arranged at the outer end part of the rear main body, and the rear boss part comprises a first boss and a second boss; the front hook comprises a front main body and a front boss part, the front boss part is arranged at the outer end part of the front main body and comprises a third boss and a fourth boss, and the third boss and/or the fourth boss are opposite to the front edge of the blade body in a first preset direction; each of the front and rear hooks is for connecting a retaining ring. The utility model discloses a too big problem of local stress that turbine stationary blade can effectually alleviate the outer fringe board makes the stress of whole outer fringe board more balanced, increases the operation security and the life-span of turbine stationary blade then.

Description

Turbine stator blade, turbine stator blade ring, turbine and gas turbine

Technical Field

The utility model belongs to the technical field of gas turbine technique and specifically relates to a quiet leaf of turbine, quiet leaf ring of turbine, turbine and gas turbine are related to.

Background

The turbine stator blade of the combustion engine is mounted on the turbine holding ring through the outer edge plate hook structure, and under the hot state, the stator blade has larger expansion amount in the radial direction, and meanwhile, the radial expansion amount of the blade is higher than that of the holding ring because the temperature of the blade is higher than that of the holding ring. And because blade and outer fringe board are irregular for the expansion volume of blade everywhere is different, and outer fringe board atress is inhomogeneous, and the not restricted department of deformation of outer fringe board then easily produces great distortion, leads to the stress maximum value in the stress concentration region of outer fringe board very big, and then influences the operational safety and the life-span of quiet leaf.

SUMMERY OF THE UTILITY MODEL

The present invention aims at solving at least one of the technical problems in the related art to a certain extent. Therefore, the embodiment of the utility model provides a turbine stationary blade, the too big problem of local stress that can effectual alleviate the outer fringe board makes the stress of whole outer fringe board more balanced, increases the operation security and the life-span of turbine stationary blade then.

The embodiment of the utility model also provides a quiet leaf ring of turbine.

Embodiments of the present invention also provide a turbine.

The embodiment of the utility model also provides a gas turbine.

A turbine stator blade according to an embodiment of the invention comprises:

an outer edge plate;

a blade body disposed inboard of the outer edge panel, the blade body having a leading edge and a trailing edge;

the rear hook comprises a rear main body and a rear boss part, the rear main body is arranged on the outer side of the outer edge plate, the rear boss part is arranged at the outer end part of the rear main body, and the rear boss part comprises a first boss and a second boss; and

the front hook comprises a front main body and a front boss part, the front main body is arranged on the outer side of the outer edge plate, the front boss part is arranged at the outer end part of the front main body, the front boss part comprises a third boss and a fourth boss, and the third boss and/or the fourth boss is opposite to the front edge of the blade body in a first preset direction; each of the front and rear hooks is for connecting a retaining ring.

The utility model discloses the too big problem of local stress that the quiet leaf of turbine can effectually alleviate the outer fringe board makes the stress of outer fringe board more balanced, increases the operation security and the life-span of quiet leaf of turbine then.

In some embodiments, the number of lobes is one; optionally, the third boss and the fourth boss are connected.

In some embodiments, the number of said lobes is two, two said lobes being spaced apart in a second predetermined direction;

the front main body comprises a first hook section and a second hook section, the first hook section and the second hook section are spaced in the second preset direction, the third boss is arranged on the first hook section, the fourth boss is arranged on the second hook section, the third boss is arranged on the first preset direction and opposite to the front edge of one of the blade bodies, and the fourth boss is arranged on the first preset direction and opposite to the front edge of the other of the blade bodies.

In some embodiments, the outer edge plate has a seal groove with a gap;

the first hook section is close to the notch relative to the second hook section in the second preset direction, the end, close to the notch, of the third boss in the extending direction of the third boss is provided with a first end face, the end, close to the notch, of the first hook section in the extending direction of the first hook section is provided with a second end face, and the first end face and the second end face are spaced in the second preset direction.

In some embodiments, the fourth boss is located in a middle of the second hooking section in the second preset direction; optionally, a projection of the fourth boss on the outer edge plate along the first preset direction is a first projection plane, a projection of the leading edge of the other of the two blade bodies on the outer edge plate along the first preset direction is a second projection plane, and the first projection plane covers the second projection plane in the second preset direction.

In some embodiments, the first boss and the second boss are respectively located at both ends in the second preset direction.

In some embodiments, the number of said lobes is n, wherein n > 2, n of said lobes are spaced apart in said second predetermined direction;

the front boss part further comprises m fifth bosses, wherein m = n-2, the third bosses, the fourth bosses and the m fifth bosses are sequentially arranged at intervals in the second preset direction, and the third bosses, the fourth bosses and the m fifth bosses are in one-to-one correspondence with the n blade bodies in the first preset direction.

According to an embodiment of the utility model, include:

holding a ring; and

a plurality of turbine stationary blades, at least one of the turbine stationary blades being the turbine stationary blade, the plurality of turbine stationary blades being sequentially arranged along the second preset direction, each of the plurality of turbine stationary blades being located inside the holding ring, each of the front and rear hooks of the turbine stationary blade being connected to the holding ring.

The utility model discloses quiet leaf ring of turbine's operation security is better, the life-span is longer.

The turbine according to the embodiment of the invention comprises the turbine stationary blade ring.

The utility model discloses turbine operation security is better, the life-span is longer.

The gas turbine according to the embodiment of the invention comprises the turbine.

The utility model discloses gas turbine operation security is better, the life-span is longer.

Drawings

FIG. 1 is a schematic cross-sectional view of a turbine vane ring according to an embodiment of the present invention.

FIG. 2 is a schematic structural view of a turbine vane (example one) according to an embodiment of the present invention;

FIG. 3 is a schematic structural view of a turbine vane (example two) according to another embodiment of the present invention;

FIG. 4 is a schematic structural view of a turbine vane of a comparative example;

FIG. 5 is one of the area designations taken from a three-dimensional finite element analysis of a turbine vane (example one) of an embodiment of the present invention;

FIG. 6 is a second area identification plot taken from a three-dimensional finite element analysis of a turbine vane (example one) according to an embodiment of the present invention;

fig. 7 is a graph comparing structural stresses for example one, example two, and a comparative example.

Reference numerals:

a turbine stator vane ring 1000;

a turbine vane 100;

a blade body 1, a first blade body 11, a second blade body 12, a leading edge 101, a trailing edge 102;

the outer edge plate 2, the sealing groove 21 and the notch 211;

the front hook 3, the front body 31, the first hook section 311, the second end face 3111, the second hook section 312, the front boss portion 32, the third boss 321, the first end face 3211, the fourth boss 322, and the ventilation channel 33;

the rear hook 4, the rear body 41, the rear boss portion 42, the first boss 421, the second boss 422;

a retaining ring 200.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present invention, and should not be construed as limiting the present invention.

As shown in fig. 1-3, a turbine vane ring 1000 according to an embodiment of the present invention includes a support ring 200 and a plurality of turbine vanes 100. The plurality of turbine vanes 100 are sequentially arranged in a second predetermined direction (i.e., a circumferential direction of the carrier ring 200), and each of the plurality of turbine vanes 100 is located inside the carrier ring 200.

The turbine vane 100 includes an outer edge plate 2, a blade body 1, a rear hook 4, and a front hook 3.

The blade body 1 is arranged inside the outer edge panel 2, the blade body 1 having a leading edge 101 and a trailing edge 102.

The rear hook 4 includes a rear main body 41 provided outside the outer edge panel 2, and a rear boss portion 42 provided at an outer end portion of the rear main body 41, the rear boss portion 42 including a first boss 421 and a second boss 422.

The front hook 3 includes a front main body 31 and a front boss portion 32, and the front main body 31 is provided on the outer side of the outer edge plate 2. That is, the blade body 1 is provided inside the outer edge plate 2, and the front hook 3 and the rear hook 4 are provided outside the outer edge plate 2. A front boss portion 32 is provided at an outer end portion of the front main body 31, the front boss portion 32 including a third boss 321 and a fourth boss 322, the third boss 321 and/or the fourth boss 322 being opposed to the leading edge 101 of the blade body 1 in the first preset direction (i.e., the radial direction of the retainer ring 200).

Each of the front hook 3 and the rear hook 4 is connected to the holder ring 200. That is, the turbine vane 100 is connected to the retaining ring 200 by the front hook 3 and the rear hook 4. When the turbine vane 100 is assembled with the carrier ring 200, the turbine vane 100 is centered with the carrier ring 200 by the front hook 3 and the rear hook 4, and then the turbine vane 100 is pushed to slide to a set position inside the carrier ring 200.

The utility model discloses quiet leaf ring 1000 of turbine is higher than the temperature of holding ring 200 at the temperature of the blade body 1 of operation in-process, in this first direction of predetermineeing of outer fringe plate 2, because first boss 421 and second boss 422 and the clearance that holds ring 200 are than back main part 41 and the clearance that holds ring 200 little, third boss 321 and fourth boss 322 and the clearance that holds ring 200 before the clearance is than main part 31 and the clearance that holds ring 200 little, the expansion of the blade body 1 warp makes first boss 421, second boss 422, third boss 321 and fourth boss 322 and hold ring 200 at first contact, and maintain dynamic balance with the thermal stress and the aerodynamic force conduction of the blade body 1 to holding on the ring 200.

The contact of the first boss 421, the second boss 422, the third boss 321, and the fourth boss 322 with the retaining ring 200 also restricts the deformation of the outer edge plate 2 at these four places, reducing the amount of expansion displacement of the outer edge plate 2 at these four places, so that a part of the deformation stress of the outer edge plate 2 at these four places is conducted to other positions, thereby changing the stress distribution of the outer edge plate 2. First boss 421, second boss 422, third boss 321 and fourth boss 322 are located the different positions of outer fringe board 2 and are the dispersed state for outer fringe board 2's atress is more balanced, thereby has reduced outer fringe board 2 stress concentration area's stress maximum value.

Moreover, the third boss 321 and/or the fourth boss 322 are opposite to the leading edge 101 of the blade body 1 in the first preset direction of the outer edge plate 2, so that deformation of the corresponding part of the outer edge plate 2 caused by expansion deformation of the leading edge 101 of the blade body 1 is limited, and accordingly, the deformation degree of the area, which is influenced by the expansion deformation of the blade body 1, of the front side of the outer edge plate 2 is restrained, the stress balance degree of the outer edge plate 2 is further increased, and the stress maximum value of the stress concentration area is further reduced.

In addition, the first boss 421, the second boss 422, the third boss 321, and the fourth boss 322 are provided to reduce the weight of the turbine stationary blade 100, increase the gap between the rear body 31 and the front body 31 from the retaining ring 200 in the first predetermined direction of the outer peripheral plate 2, and reduce the sliding resistance of the front hook 3 and the rear hook 4 with respect to the retaining ring 200, thereby increasing the convenience in assembling the turbine stationary blade 100 and the retaining ring 200.

The utility model discloses quiet leaf ring 1000 of turbine and quiet leaf 100 of turbine can effectually alleviate the too big problem of the local stress of outer fringe board 2, make the stress of outer fringe board 2 more balanced, increase quiet leaf 100's of turbine operation security and life-span then.

Specifically, referring to fig. 1 through 3, a turbine stationary blade ring 1000 according to an embodiment of the present invention is described in detail. In fig. 1 to 3, the front-rear direction is the same as the axial direction of the holder ring 200, and the inner-outer direction is the same as the radial direction of the holder ring 200. It should be noted that the first predetermined direction is a radial direction of the holding ring 200, and the second predetermined direction is a circumferential direction of the holding ring 200.

The turbine vane ring 1000 of an embodiment of the present invention includes a retaining ring 200 and a plurality of turbine vanes 100. The plurality of turbine vanes 100 are arranged in series along the circumferential direction of the carrier ring 200, and each of the plurality of turbine vanes 100 is located inside the carrier ring 200.

The turbine vane 100 includes an outer edge plate 2, a blade body 1, a rear hook 4, and a front hook 3. The outer edge plate 2, the blade body 1, the rear hook 4 and the front hook 3 are cast and integrally formed.

The blade body 1 is arranged inside the outer edge panel 2, the blade body 1 having a leading edge 101 and a trailing edge 102. The number of the blades 1 of each turbine stationary blade 100 is two, the two blades 1 are a first blade 11 and a second blade 12, respectively, and the first blade 11 and the second blade 12 are spaced apart in the second preset direction, that is, the first blade 11 and the second blade 12 are spaced apart in the circumferential direction of the retaining ring 200.

The rear hook 4 comprises a rear body 41 and a rear boss portion 42, the rear body 41 being provided on the outer side of the peripheral plate 2, the rear body 41 being opposed to the trailing edge 102 of the blade body 1 in the first predetermined direction, as shown in fig. 1. The rear boss portion 42 is provided at an outer end portion of the rear main body 41 in the first preset direction. The rear boss portion 42 includes a first boss 421 and a second boss 422, and the first boss 421 and the second boss 422 are spaced apart in the second preset direction.

Alternatively, the first boss 421 and the second boss 422 are respectively located at both ends of the outer flange plate 2 in the second preset direction. The contact between the first boss 421 and the second boss 422 and the retaining ring 200 can limit the deformation of the outer edge plate 2 at the two positions, and can prevent the two ends of the rear side of the outer edge plate 2 from tilting during the operation of the turbine stationary blade ring.

The front hook 3 comprises a front body 31 and a front boss portion 32, the front body 31 being provided outside the peripheral plate 2, the front body 31 being opposed to the front edge 101 of the blade body 1 in the first predetermined direction, see fig. 1. The front boss portion 32 is provided at an outer end portion of the front main body 31 in the first preset direction.

The front body 31 includes a first hooking section 311 and a second hooking section 312, and the first hooking section 311 and the second hooking section 312 are spaced apart in the second preset direction. The front body 31 is provided with a ventilation passage 33 between the first hooking section 311 and the second hooking section 312, and the ventilation passage 33 communicates spaces at front and rear sides of the front hooking section 31 to serve as a circulation passage of the cooling gas.

The front boss portion 32 includes a third boss 321 and a fourth boss 322, the third boss 321 is provided at an outer end portion of the first hooking section 311 in the first preset direction, and the fourth boss 322 is provided at an outer end portion of the second hooking section 312 in the first preset direction. The third boss 321 is opposite to the leading edge 101 of the first blade 11 in the first predetermined direction, and the fourth boss 322 is opposite to the leading edge 101 of the second blade 12 in the first predetermined direction.

The utility model discloses turbine stationary blade 100 of embodiment has two blade 1, to the outer fringe plate 2 that is connected with two blade 1, the deformation that outer fringe plate 2 that third boss 321 makes the expansion deformation of the leading edge 101 of first blade 11 lead to is here limited, and shift and disperse this deformation stress, the deformation that outer fringe plate 2 that fourth boss 322 makes the expansion deformation of the leading edge 101 of second blade 12 lead to is here limited and dispersed, thereby the stress distribution of outer fringe plate 2 has been changed, the atress of outer fringe plate 2 is more balanced, thereby the stress maximum value of outer fringe plate 2 stress concentration area has been reduced, and then promote the running life and the security of turbine stationary blade 100, the failure damage risk of turbine stationary blade 100 has been reduced.

In some embodiments, outer rim plate 2 has a seal groove 21, and seal groove 21 has a notch 211. The first hooking section 311 is adjacent to the notch 211 relative to the second hooking section 312 in the second preset direction, the end of the third boss 321 adjacent to the notch 211 in the extending direction thereof has a first end surface 3211, the end of the first hooking section 311 adjacent to the notch 211 in the extending direction thereof has a second end surface 3111, and the first end surface 3211 and the second end surface 3111 are spaced apart in the second preset direction. That is, the second end face 3111 is located at the edge position of the outer edge panel 2, and in the second preset direction (which is also the extending direction of the first hooking section 311 and the third boss 321), the first end face 3211 is spaced apart from the second end face 3111, that is, the third boss 321 is spaced apart from the edge position of the outer edge panel 2. In other words, the third boss 321 is in a non-edge position of the outer flange plate 2.

During the assembling process of the turbine vane 100 and the retaining ring 200, the third boss 321 is not located at the edge position of the outer edge plate 2, so that the third boss 321 is easy to center and has small sliding resistance during the assembling process of the turbine vane 100 and the retaining ring 200, that is, the assembling process of the turbine vane 100 and the retaining ring 200 is easier to operate.

Optionally, the third boss 321 extends 2-2.5 times as long as its width to ensure that the third boss 321 has a certain area and does not form a large resistance to the assembly of the turbine vane 100 and the retaining ring 200. Specifically, the dimension of the third boss 321 in the second preset direction is the extension length thereof, and the dimension of the third boss 321 in the axial direction of the retaining ring 200 is the width thereof.

In some embodiments, the fourth boss 322 is located in the middle of the second hook section 312 in the second predetermined direction. That is, the fourth boss 322 is not located at the edge of the outer edge plate 2, so that the fourth boss 322 is easily centered and has small sliding resistance during the assembly of the turbine vane 100 and the ring 200, thereby facilitating the assembly of the turbine vane 100 and the ring 200.

Preferably, the projection of the fourth boss 322 on the outer edge plate 2 along the first preset direction is a first projection plane, the projection of the front edge 101 of the second blade body 12 on the outer edge plate 2 along the first preset direction is a second projection plane, and the first projection plane covers the second projection plane in the second preset direction. That is, the fourth boss 322 covers the leading edge 101 of the second blade body 12 in the first predetermined direction, as shown in FIG. 2.

Specifically, the first projection surface has a first edge and a second edge in the second preset direction, the second projection surface has a third edge and a fourth edge in the second preset direction, and the third edge and the fourth edge are located between the first edge and the second edge in the second preset direction. Therefore, the expansion deformation area of the leading edge 101 of the second blade body 12 is covered on the whole in the second preset direction of the outer edge plate 2, the deformation of the outer edge plate 2 caused by the expansion deformation area is restrained and conducted, the stress balance degree of the outer edge plate 2 is further increased, and the maximum stress value of the stress concentration area is further reduced.

The utility model discloses the overall arrangement dispersion of first boss 421, second boss 422, third boss 321 and fourth boss 322 of quiet leaf 100 of turbine is corresponding to the four corners department that distributes at outer fringe 2, and the unbalanced atress of balanced outer fringe 2 has effectively alleviated the stress concentration situation of outer fringe 2, promotes quiet leaf 100 running life of turbine and security, reduces quiet leaf 100's of turbine inefficacy damage risk.

To further illustrate the stress conditions of the outer edge plate 2, the front hook 3 and the rear hook 4 of the turbine vane 100 according to the embodiment of the present invention, a three-dimensional finite element analysis is performed on the outer edge plate 2, the front hook 3 and the rear hook 4 of the turbine vane 100 in the areas where stress concentration is likely to occur, which are shown in (1) -r in fig. 5 and 6, and a comparative example is added.

Specifically, the method comprises the following steps: first, the turbine vane 100 of the embodiment of the present invention has the fourth boss 322 located at the middle of the second hooking section 312 in the second predetermined direction, as shown in fig. 2; second, in the turbine stationary blade 100 according to the embodiment of the present invention, the fourth boss 322 is located on a side of the second hooking section 312 away from the notch 211 in the second predetermined direction, as shown in fig. 3; the comparative example, turbine vane, is substantially the same as the first example, except that the turbine vane of the comparative example does not have the fourth boss 322, as shown in FIG. 4.

The results of the comparison of the above three examples are shown in FIG. 7. It should be noted that, for the comparative example, since fourth boss 322 is not provided, region r thereof is a non-stress concentration region.

Comparing the above three examples, it can be seen that the first, second and comparative examples all generate a certain local stress concentration in the region where stress concentration is likely to occur (region (1) to region (9)), and that the first, second and comparative examples generate a certain local stress concentration in region r. However, in the first and second examples, compared with the comparative example, the stress value of the region (1) (i.e., the region where the stress is most concentrated) on the outer edge plate 2 is significantly reduced, and the stress at each stress concentration point is more balanced, so that the operation life and safety of the turbine vane 100 are improved, and the risk of failure and damage of the turbine vane 100 is reduced.

In addition, the numerical value of the region with the maximum stress concentration of the turbine stationary blade 100 of the first example is reduced by 31% compared with the comparative example, the numerical value of the region with the minimum number of low cycle fatigue cycle life times is improved by 16.5 times compared with the comparative example, and the maximum creep strain value of the turbine stationary blade of the first example after 96000 hours is reduced by 45% compared with the turbine stationary blade of the third example, which is qualified for the full-blade creep life.

Additional embodiments of the turbine vane 100 are described below.

The number of the vane bodies 1 of the turbine stationary blade 100 according to the embodiment of the present invention is one. Compared to the turbine vane 100 of the foregoing embodiment in which the number of the blade bodies 1 is two, the size range of the blade bodies 1 can be selectively made larger. Preferably, the size of the blade body 1 of the turbine vane 100 of the embodiment of the present invention is larger than the size of the blade body 1 of the turbine vane 100 of the previous embodiment.

Optionally, the third boss 321 and the fourth boss 322 are connected. That is, the third boss 321 and the fourth boss 322 are of an integral structure.

In other words, when the front boss portion 32 is formed by cutting the front body 3, only one boss needs to be cut.

In other embodiments, the number of blades 1 is n, where n > 2, and n blades 1 are spaced apart in the second predetermined direction. The front boss portion 32 further includes m fifth bosses, where m = n-2, the third boss 321, the fourth boss 322, and the m fifth bosses are spaced apart in the second preset direction, and the third boss 321, the fourth boss 322, and the m fifth bosses are in one-to-one correspondence with the n blade bodies 1 in the first preset direction.

In particular, n may be 3, 4 or 5, i.e. the number of fronds 1 may be 3, 4 or 5.

Accordingly, the number of fifth bosses is 1, 2 or 3. That is to say, the front edge 101 of each vane body 1 corresponds to the boss on the front main body 31, so that the deformation of the outer edge plate 2 caused by the expansion deformation of the front edge 101 of each vane body 1 is limited, the expansion displacement of the outer edge plate 2 is reduced, a part of the deformation stress of the outer edge plate 2 is conducted to other positions, the stress of the outer edge plate 2 is more balanced, the stress maximum value of the stress concentration area of the outer edge plate 2 is reduced, and the operation safety and the service life of the turbine stationary blade 100 are further improved.

The turbine of the present invention includes a turbine vane ring of any of the above embodiments.

The utility model discloses the operation security of turbine is better and the life-span is longer.

The following describes a gas turbine according to an embodiment of the present invention including a turbine according to the above embodiment.

The utility model discloses gas turbine's operational safety is better and the life-span is longer.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description of the present invention and to simplify the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

In the present invention, unless otherwise explicitly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrated; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

In the present application, unless expressly stated or limited otherwise, the first feature may be directly on or directly under the second feature or indirectly via intermediate members. Also, a first feature "on," "above," and "over" a second feature may be directly on or obliquely above the second feature, or simply mean that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Moreover, various embodiments or examples and features of various embodiments or examples described in this specification can be combined and combined by one skilled in the art without being mutually inconsistent.

Although embodiments of the present invention have been shown and described, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art without departing from the scope of the present invention.

Claims (10)

1. A turbine vane, comprising:

a peripheral plate (2);

a blade body (1), said blade body (1) being arranged inside said outer edge panel (2), said blade body (1) having a leading edge (101) and a trailing edge (102);

a rear hook (4), the rear hook (4) including a rear main body (41) and a rear boss portion (42), the rear main body (41) being provided at an outer side of the outer peripheral panel (2), the rear boss portion (42) being provided at an outer end portion of the rear main body (41), the rear boss portion (42) including a first boss (421) and a second boss (422); and

a front hook (3), the front hook (3) comprising a front main body (31) and a front boss portion (32), the front main body (31) being provided at the outer side of the outer peripheral panel (2), the front boss portion (32) being provided at an outer end portion of the front main body (31), the front boss portion (32) comprising a third boss (321) and a fourth boss (322), the third boss (321) and/or the fourth boss (322) being opposite to the front edge (101) of the vane body (1) in a first preset direction; each of the front hook (3) and the rear hook (4) is used for connecting a retaining ring.

2. Turbine vane according to claim 1, characterized in that the number of the blade bodies (1) is one; optionally, the third boss (321) and the fourth boss (322) are connected.

3. Turbine vane according to claim 1, characterized in that the number of said blades (1) is two, two of said blades (1) being spaced apart in a second preset direction;

the front main body (31) comprises a first hook section (311) and a second hook section (312), the first hook section (311) and the second hook section (312) are spaced apart in the second preset direction, a third boss (321) is arranged on the first hook section (311), a fourth boss (322) is arranged on the second hook section (312), the third boss (321) is opposite to the front edge (101) of one of the two vane bodies (1) in the first preset direction, and the fourth boss (322) is opposite to the front edge (101) of the other of the two vane bodies (1) in the first preset direction.

4. The turbine vane according to claim 3, characterized in that the outer edge plate (2) has a sealing groove (21), the sealing groove (21) having a notch (211);

the first hooking section (311) is adjacent to the notch (211) relative to the second hooking section (312) in the second preset direction, the end of the third boss (321) adjacent to the notch (211) in the extending direction thereof has a first end surface (3211), the end of the first hooking section (311) adjacent to the notch (211) in the extending direction thereof has a second end surface (3111), and the first end surface (3211) and the second end surface (3111) are spaced apart in the second preset direction.

5. The turbine vane of claim 4, characterized in that the fourth boss (322) is located in a middle of the second hanger section (312) in the second preset direction; optionally, a projection of the fourth boss (322) on the outer edge plate (2) along the first preset direction is a first projection plane, a projection of the leading edge (101) of the other of the two blade bodies (1) on the outer edge plate (2) along the first preset direction is a second projection plane, and the first projection plane covers the second projection plane in the second preset direction.

6. A turbine vane according to claim 3, characterized in that the first boss (421) and the second boss (422) are respectively located at both ends in the second preset direction.

7. Turbine vane according to claim 1, characterized in that the number of blades (1) is n, wherein n > 2,n of the blades (1) are spaced apart in a second predetermined direction;

the front boss part (32) further comprises m fifth bosses, wherein m = n-2, the third bosses (321), the fourth bosses (322) and the m fifth bosses are sequentially arranged at intervals in the second preset direction, and the third bosses (321), the fourth bosses (322) and the m fifth bosses are in one-to-one correspondence with the n blade bodies (1) in the first preset direction.

8. A turbine vane ring, comprising:

a holding ring (200); and

a plurality of turbine vanes (100), at least one of the plurality of turbine vanes (100) being the turbine vane of any one of claims 1 to 7, the plurality of turbine vanes (100) being arranged in series along a second predetermined direction, each of the plurality of turbine vanes (100) being located inside the retaining ring (200), each of the forward and aft hooks (3, 4) of the turbine vane (100) being connected to the retaining ring (200).

9. A turbine comprising the turbine vane ring of claim 8.

10. A gas turbine comprising the turbine of claim 9.

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