CN211819519U

CN211819519U - Turbine static disk, turbine and gas turbine

Info

Publication number: CN211819519U
Application number: CN202020241758.5U
Authority: CN
Inventors: 蒋洪德; 任静; 李雪英; 吴康; 杨笑宇; 薛启超
Original assignee: Tsinghua University
Current assignee: Tsinghua University
Priority date: 2020-03-03
Filing date: 2020-03-03
Publication date: 2020-10-30
Anticipated expiration: 2030-03-03

Abstract

The utility model relates to a turbine quiet wheel dish, the play discharge orifice on its end wall is applied to the obturage of mainstream high temperature gas, and turbine quiet wheel dish includes rim plate body and quiet rim. The static wheel rim is arranged on the outer periphery of the wheel disc body, a plurality of outflow holes are formed in the static wheel rim along at least one axial end wall of the wheel disc body at intervals in the rotating direction, the outflow holes at least form a first outflow region and a second outflow region, the first outflow regions correspond to the tail edges of the turbine stationary blades respectively in the rotating direction of the wheel disc body, the second outflow regions are located between every two adjacent turbine stationary blades respectively in the rotating direction of the wheel disc body, and the exhaust volume of the first outflow regions is larger than that of the second outflow regions. The utility model discloses still relate to turbine and gas turbine including above-mentioned quiet rim plate of turbine, can improve the regional sealed effect of quiet leaf trailing edge under the condition that does not influence whole sealed efficiency, be applicable to all gas turbine models that have end wall side direction outflow hole in the rim clearance of obturating.

Description

Turbine static disk, turbine and gas turbine

Technical Field

The utility model relates to a gas turbine technical field especially relates to a turbine stator disc, turbine and gas turbine.

Background

The high temperature component cooling technology is a key ring in the development process of the modern gas turbine, and the emergence and development of the high temperature component cooling technology enable hot end components of the gas turbine to stably operate under higher parameters, and the cooling structures adopted by different components are different. A cavity formed by the high-temperature turbine rotating and static wheel disc needs to be sealed for a wheel rim gap so as to avoid overheating of the wheel disc caused by invasion of high-temperature and high-pressure main stream gas. In addition to the containment gas from the low radius chamber, near the rim of some gas turbines, a stream of fluid with a lower temperature and higher momentum exiting the end wall can also have a significant effect on the flow field near the rim. The traditional end wall lateral outflow hole structure leads axial outflow to be led into the wheel rim gap, so that the invading gas is extruded in the wheel rim gap. The central line position of the intruding vortex system is obviously raised after being extruded by the outflow of the end wall, and the size of the vortex system is also inhibited, so that the degree of gas intrusion is weakened. However, the traditional outflow hole structure still has poor sealing effect, so that the gas at a part of gaps invades seriously. At the same time, the large amount of end wall side outflow reduces the amount of containment gas used to cool the end wall surface, which is undesirable in engineering practice.

SUMMERY OF THE UTILITY MODEL

Therefore, the turbine and the gas turbine which can effectively seal the wheel rim gap need to be provided for solving the problem of poor sealing effect of the existing end wall side outflow hole structure.

A turbine stator disk having an outlet orifice in an end wall for application in sealing against a mainstream hot gas stream, said turbine stator disk comprising:

a wheel disc body;

the quiet rim, set up in the outer peripheral edges of rim plate body, follow on the quiet rim set up a plurality ofly on at least one axial end wall of rim plate body the outflow hole, it is a plurality of the outflow hole is followed the direction of rotation interval distribution of rim plate body, it is a plurality of the outflow hole is followed the direction of rotation of rim plate body forms first outflow district and second outflow district at least, and is a plurality of first outflow district is followed the direction of rotation of rim plate body is corresponding with the trailing edge of a plurality of stationary vanes respectively, and is a plurality of the second outflow district is followed the direction of rotation of rim plate body is located between two adjacent stationary vanes respectively, the displacement in first outflow district is greater than the displacement in second outflow district.

In one embodiment, the first outflow region comprises a plurality of outflow holes, and the number of outflow holes in the first outflow region is greater than the number of outflow holes in the second outflow region.

In one embodiment, the second outflow region comprises a plurality of outflow holes, and the outflow holes in the second outflow region are distributed at equal intervals along the revolution direction of the wheel disc body; and the outflow holes in the first outflow area are distributed at equal intervals along the rotation direction of the wheel disc body.

In one embodiment, the circumferential hole distance between the outflow holes in the first outflow area is lm, the circumferential hole distance between the outflow holes in the second outflow area is ln, and lm is less than or equal to ln.

In one embodiment, the circumferential center position of each first outflow region coincides with the trailing edge of each turbine stationary blade in the rotation direction of the disk body.

In one embodiment, the number of the outlet holes in each first outlet flow region is singular, and the outlet holes in each first outlet flow region located at the circumferential center position coincide with the trailing edge of one turbine stationary blade in the rotation direction of the disk body.

In one embodiment, the diameter of the outflow hole in the first outflow region is equal to the diameter of the outflow hole in the second outflow region.

In one embodiment, the turbine static disc can form a rim gap with other adjacent discs, and the ratio of the diameter of the outflow hole to the width of the rim gap is between 0.2 and 0.5.

In one embodiment, all the outflow holes on the static rim are distributed in a circle with equal radius around the axis of the wheel disc body.

In one embodiment, the diameter of the outflow hole in the first outflow region is larger than the diameter of the outflow hole in the second outflow region.

A turbine using a turbine stator disc according to any of the above aspects.

A gas turbine comprises a compressor, a combustion chamber and the turbine, wherein the compressor, the combustion chamber and the turbine are sequentially connected along the gas flowing direction.

The turbine static wheel disc, the turbine and the gas turbine adjust the displacement of different circumferential positions according to the main flow pressure distribution near the wheel rim on the basis of the traditional outflow hole structure. Compared with the traditional structure, the main flow invasion degree of the stator blade tail edge area and the whole temperature distribution of the rim gap are obviously improved, and the sealing efficiency can be improved by about 3%. Meanwhile, under the action of larger sealing flow, the turbine static wheel disc enables a low-temperature area downstream of the wheel rim gap (in the direction of the radial direction of the wheel disc to the axis) to be more continuous and uniform. The utility model provides a quiet rim plate of turbine, turbine and gas turbine can improve the regional sealed effect of quiet leaf trailing edge under the condition that does not influence whole sealed efficiency, is applicable to all gas turbine models that have end wall side direction outflow hole in the rim clearance of obturating.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification.

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

Fig. 1 is a schematic view of a non-uniform outflow hole according to an embodiment of the present invention;

FIG. 2 is a schematic view of a non-uniform outlet orifice structure for a high temperature turbine wheel rim gap according to an embodiment of the present invention;

fig. 3 is a schematic diagram illustrating the sealing effect comparison between the non-uniform outflow hole structure and the conventional uniform outflow hole structure according to an embodiment of the present invention.

Wherein: 1. a first outflow region; 2. a second outflow region; 3. an outflow hole; 4. a rim gap; 5. a turbine static wheel disc; 6. a trailing edge of the stationary blade; 7. mainstream gas; 8. a turbine stator vane; 9. sealing the gas; 10. a wheel disc body; 11. a static rim.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. The following description of the embodiments is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses.

It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. In contrast, when an element is referred to as being "directly on" another element, there are no intervening elements present. In contrast, when an element is referred to as being "directly connected" to another element, there are no intervening elements present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.

In the description of the present invention, it is to be understood that the terms "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are merely for convenience of description and simplicity of description, and 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, are not to be construed as limiting the present invention.

The high-temperature turbine is a key step in the working process of the gas turbine, and in the high-temperature turbine process, when high-temperature main stream gas flows through turbine blades (including turbine stationary blades and turbine movable blades), the heat energy of the high-temperature main stream gas is converted into the kinetic energy of an impeller, so that other structures in transmission connection with the gas turbine are driven to rotate. In the process of the turbine, a cavity formed by the high-temperature turbine rotating and static wheel disc needs to tightly seal a wheel rim gap so as to avoid overheating of the wheel disc caused by invasion of high-temperature and high-pressure main stream gas. The utility model provides a can effectively seal design method in quiet rim plate, turbine, gas turbine and the end wall side direction outflow hole in wheel flange clearance, effectively avoid the overheated inefficacy of turbine rim plate in the course of the work, and then guarantee that gas turbine lasts, efficient work.

As shown in fig. 1 and 2, an embodiment of the present invention provides a turbine static wheel disc 5, in which an outflow hole 3 on an end wall is applied to seal a mainstream high-temperature gas, and it can be understood that the turbine static wheel disc 5 forms a static chamber with a turbine dynamic wheel disc in a use process. The turbine stator disk 5 provided in this embodiment includes a disk body 10 and a stator rim 11. The static wheel rim 11 is arranged on the outer periphery of the wheel disc body 10, a plurality of outflow holes 3 are formed in at least one end wall of the static wheel rim 11 in the axial direction of the wheel disc body 10, the outflow holes 3 are distributed at intervals in the rotating direction of the wheel disc body 10, the outflow holes 3 at least form a first outflow region 1 and a second outflow region 2 in the rotating direction of the wheel disc body 10, the first outflow regions 1 correspond to the trailing edges of the turbine stationary blades 8 respectively in the rotating direction of the wheel disc body 10 (namely the first outflow regions 1 and the trailing edges of the turbine stationary blades 8 at least partially coincide in the rotating direction of the wheel disc body 10), the second outflow regions 2 are located between two adjacent turbine stationary blades 8 respectively in the rotating direction of the wheel disc body 10, and the exhaust volume of the first outflow region 1 is larger than that of the second outflow region 2.

The turbine stator disk 5 according to the above embodiment adjusts the amount of exhaust gas at different circumferential positions according to the distribution of the main flow pressure near the rim based on the structure of the conventional outlet hole 3. Compared with the traditional structure, the main flow invasion degree of the stator blade tail edge 6 area and the whole temperature distribution of the rim gap 4 are obviously improved, and the sealing efficiency can be improved by about 3%. Meanwhile, under the action of larger sealing flow, the turbine static wheel disc 5 enables a low-temperature area downstream of the rim gap 4 (in the direction of pointing to the axis along the radial direction of the wheel disc) to be more continuous and uniform. And the utility model provides a quiet rim plate 5 of completing can improve the sealed effect of quiet leaf trailing edge 6 region under the condition that does not influence whole sealed efficiency, is applicable to all gas turbine models that have end wall side direction outflow hole 3 in the rim clearance of obturating.

For convenience of description, as shown in fig. 1 and 2, a rotation direction of the turbine movable disk 5 (i.e., a rotation direction of the turbine movable disk) is defined as a circumferential direction, a diameter direction of the turbine movable disk 5 is defined as a radial direction, and an extension direction of a rotation shaft of the turbine movable disk (i.e., a thickness direction of the turbine movable disk 5, or a spaced arrangement direction of the turbine movable disk 5 and the turbine movable disk) is defined as an axial direction. It can be understood that, when only one end of the turbine static wheel disk 5 in the axial direction has a turbine movable wheel disk, the static chamber is only formed at the corresponding end of the turbine static wheel disk 5, and the static rim 11 also forms the rim gap 4 with the movable rim at the corresponding end, and in this case, only one end wall of the static rim 11 in the axial direction needs to be provided with a plurality of outflow holes 3. When the two ends of the turbine static wheel disc 5 along the axial direction are respectively provided with the turbine movable wheel disc, the two ends of the turbine static wheel disc 5 along the axial direction are respectively formed with a static rotating chamber, the two ends of the static wheel rim 11 along the axial direction are respectively formed with the movable wheel rim to form a rim gap 4, and at the moment, the two end walls of the static wheel rim 11 along the axial direction are respectively provided with a plurality of outflow holes 3. Hereinafter, the description will be given by taking an example of "a plurality of outlet holes 3 are formed in one end wall of the stationary flange 11 in the axial direction", and the same applies to "a plurality of outlet holes 3 are formed in each of both end walls of the stationary flange 11 in the axial direction".

The discharge of more sealed gas 9 at the position corresponding to the trailing edge of the turbine stator blade 8 in the axial direction on the end wall of the stationary flange 11 is a key feature of the turbine stationary disk 5 in the above embodiment, and it can be understood that the structure as long as the above feature can be realized should be regarded as the protection scope of the present invention. As a practical matter, the diameter of the outflow hole 3 in the first outflow region 1 is larger than the diameter of the outflow hole 3 in the second outflow region 2, and when the outflow hole 3 in the first outflow region 1 and the outflow hole 3 in the second outflow region 2 are respectively filled with the sealing gas 9 at the same flow rate, the outflow hole 3 in the first outflow region 1 discharges more sealing gas 9 in the first outflow region 1 due to the larger diameter. In actual conditions, the pressure of the main flow gas 7 near the static clearance is non-uniformly distributed, the pressure of the main flow gas 7 at the tail edge 6 of each static blade is high, the pressure of the main flow gas 7 between the adjacent static blades 8 is low, the sealing effect at the tail edge 6 of each static blade is poor, and the region with the most serious gas invasion still exists near the tail edge 6 of each static blade. In the embodiment, the diameter of the outflow hole 3 in the first outflow region 1 is designed to be larger than that of the outflow hole 3 in the second outflow region 2, so that the gas outlet amount of the sealed gas 9 in the position, corresponding to the trailing edge 6 of the stationary blade, of the rim gap 4 along the axial direction is effectively increased, and the invasion of the main flow gas 7 near the trailing edge 6 of the stationary blade to the stationary chamber is reduced or even avoided.

As shown in fig. 1 and fig. 2, as another realizable way, a plurality of outflow holes 3 are included in the first outflow region 1, the number m of the outflow holes 3 in the first outflow region 1 is greater than the number n of the outflow holes 3 in the second outflow region 2, and further the first outflow region 1 appears as a dense region on the end wall of the fixed rim 11 in the circumferential direction, the second outflow region 2 appears as a sparse region on the end wall of the fixed rim 11 in the circumferential direction, and the dense region and the sparse region are alternately distributed in the circumferential direction. It is understood that the third outflow region may be designed on the endwall of the stationary rim 11 according to the actual operating conditions, and the embodiment is not particularly limited, corresponding to other positions of the turbine vane 8. In the present embodiment, according to the main flow pressure distribution near the rim gap 4, a plurality of outflow holes 3 are provided in the region of the stationary blade trailing edge 6 with a high pressure, and a relatively small number of outflow holes 3 are provided in the region of the flow passage with a low pressure, so that the uneven outflow hole 3 structure significantly improves the main flow invasion degree in the region of the stationary blade trailing edge 6 and the temperature distribution of the entire rim gap 4, and the sealing efficiency can be improved by about 3%. Another advantage of the structure of the laterally non-uniform outlet orifice 3 provided by the present embodiment is that: under the action of larger sealing flow, the non-uniform outlet hole 3 structure enables the low-temperature area downstream of the rim gap 4 to be more continuous and uniform.

It will be understood that the diameter of the outlet orifice 3 in the first outlet flow area 1 is still larger than the diameter of the outlet orifice 3 in the second outlet flow area 2 in the above embodiments, or the diameter of the outlet orifice 3 in the first outlet flow area 1 may be equal to the diameter of the outlet orifice 3 in the second outlet flow area 2. In an embodiment of the present invention, as shown in fig. 1 and 2, the diameter of the outflow hole 3 in the first outflow region 1 is equal to the diameter of the outflow hole 3 in the second outflow region 2, which can facilitate the machining of the outflow hole 3 on the end wall of the stationary rim 11. In addition, all the outflow holes 3 on the static rim 11 are distributed in a circle with an equal radius around the axis of the wheel disc body 10, so that the mechanical processing of the outflow holes 3 on the end wall of the static rim 11 is further facilitated, and the change of the main flow pressure between the static blade tail edge 6 and the turbine static blade 8 under different working conditions is adapted only by adjusting the difference of the number of the outflow holes 3 in the first outflow area 1 and the second outflow area 2.

In an embodiment of the present invention, as shown in fig. 1 and fig. 2, the number of the outflow holes 3 in each first outflow region 1 is between 5 and 20, and the outflow holes 3 in the first outflow region 1 are distributed at equal intervals along the rotation direction of the wheel disc body 10. The circumferential center position of each first outflow area 1 is respectively superposed with the trailing edge of one turbine stationary blade 8 along the rotation direction of the wheel disc body 10, so that the sealing gas 9 discharged from the first outflow area 1 can seal the rim gap 4 at the trailing edge 6 of the stationary blade to the maximum extent. As a practical matter, the number of the outlet holes 3 in each first outlet flow region 1 is singular, the outlet hole 3 in the circumferential center position exists in each first outlet flow region 1, and this outlet hole 3 coincides with the trailing edge of one turbine vane 8 in the rotation direction of the disk body 10. As another way to achieve the above, the number of the outlet holes 3 in each first outlet flow region 1 is a double number, the position of the circumferential center in each first outlet flow region 1 is between two adjacent outlet holes 3, and the position of the circumferential center in each first outlet flow region 1 coincides with the trailing edge of one turbine stationary blade 8 along the rotation direction of the disk body 10.

Further, as shown in fig. 1 and fig. 2, the second outflow region 2 also includes a plurality of outflow holes 3, the number of the outflow holes 3 in each second outflow region 2 is between 2 and 4, and the plurality of outflow holes 3 in the second outflow region 2 are distributed at equal intervals along the rotation direction of the wheel disc body 10, the circumferential hole distance between the plurality of outflow holes 3 in the first outflow region 1 is lm, the circumferential hole distance between the plurality of outflow holes 3 in the second outflow region 2 is ln, and lm is not more than ln, and more outflow holes 3 can be opened in the first outflow region 1 with a smaller hole distance between the plurality of outflow holes 3. Furthermore, it is reasonable to design the size of the diameter of the outlet hole 3 according to the width L of the rim gap 4, specifically, the turbine static wheel disc 5 can form the rim gap 4 with other adjacent wheel discs, and the ratio of the diameter of the outlet hole 3 to the width L of the rim gap 4 is between 0.2 and 0.5. It can be understood that the circumferential hole distance s between the outflow holes 3 in the first outflow region 1 and the outflow holes 3 in the second outflow region 2 can be designed according to actual working conditions, and the embodiment is not limited.

An embodiment of the present invention further provides a turbine using the turbine stator disk 5 according to any one of the above embodiments. Correspondingly, an embodiment of the present invention further provides a gas turbine, which comprises a compressor, a combustion chamber and the above-mentioned embodiment, wherein the compressor, the combustion chamber and the turbine are sequentially connected along the direction of gas flow. The turbine and the gas turbine adjust the exhaust gas volume at different circumferential positions according to the main flow pressure distribution near the wheel rim on the basis of the traditional structure of the outflow hole 3. Compared with the traditional structure, the main flow invasion degree of the stator blade tail edge 6 area and the whole temperature distribution of the rim gap 4 are obviously improved, and the sealing efficiency can be improved by about 3%. Meanwhile, under the action of larger sealing flow, the design method of the turbine static wheel disc 5 and the end wall lateral outflow hole 3 enables a low-temperature area downstream of the rim gap 4 (in the direction of the radial direction of the wheel disc pointing to the axis) to be more continuous and uniform. The turbine and the gas turbine provided by the embodiment can improve the sealing effect of the region of the stator blade trailing edge 6 under the condition of not influencing the whole sealing efficiency, and are suitable for all gas turbine models with end wall lateral outflow holes 3 in the rim sealing clearance.

The utility model provides an embodiment still provides a design method of end wall side direction discharge orifice 3, an outflow orifice 3 for set up the side direction on the end wall of turbine wheel dish among gas turbine, set up a plurality of outflow orifices 3 on self axial at least one end wall on the turbine wheel dish, the direction of rotation interval distribution of a plurality of outflow orifices 3 along the turbine wheel dish, a plurality of outflow orifices 3 form first outflow district 1 and second outflow district 2 at least along the direction of rotation of turbine wheel dish, a plurality of first outflow districts 1 are corresponding with the trailing edge of a plurality of turbine stationary blades 8 respectively along the direction of rotation of turbine wheel dish, a plurality of second outflow districts 2 are located between two adjacent turbine stationary blades 8 respectively along the direction of rotation of turbine wheel dish, the air displacement of first outflow district 1 is greater than the air displacement of second outflow district 2. In a practical manner, the second outflow region 2 is located circumferentially between the vane trailing edges 6 of two adjacent turbine vanes 8.

According to the design method of the end wall lateral outflow hole 3, on the basis of the structure of the traditional outflow hole 3, the air displacement at different circumferential positions is adjusted according to the main flow pressure distribution near the wheel rim. Compared with the traditional structure, the main flow invasion degree of the stator blade tail edge 6 area and the whole temperature distribution of the rim gap 4 are obviously improved, and the sealing efficiency can be improved by about 3%. Meanwhile, under the action of larger sealing flow, the design method of the turbine static wheel disc 5 and the end wall lateral outflow hole 3 enables a low-temperature area downstream of the rim gap 4 (in the direction of the radial direction of the wheel disc pointing to the axis) to be more continuous and uniform. The design method of the endwall lateral outflow hole 3 provided by the embodiment can improve the sealing effect of the region of the stationary blade trailing edge 6 under the condition of not influencing the whole sealing efficiency, and is suitable for all gas turbine models with the endwall lateral outflow holes 3 in the rim sealing gap.

As shown in fig. 1 and 2, a plurality of outflow holes 3 are included in the first outflow region 1, and the number of outflow holes 3 in the first outflow region 1 is greater than the number of outflow holes 3 in the second outflow region 2. As a further possibility, the number of outlet openings 3 in the first outlet flow region 1 is equal to the number of outlet openings 3 in the second outlet flow region 2. In the following, the description will be given by taking an example that the number of outflow holes 3 in the first outflow region 1 is greater than the number of outflow holes 3 in the second outflow region 2. Further, all the outflow holes 3 are distributed around the axis of the turbine disk in a circle with an equal radius, the outflow holes 3 in the first outflow region 1 are distributed at equal intervals along the rotation direction of the turbine disk, and the outflow holes 3 in the second outflow region 2 are distributed at equal intervals along the rotation direction of the turbine disk. The circumferential hole distance between the outflow holes 3 in the first outflow area 1 is lm, the circumferential hole distance between the outflow holes 3 in the second outflow area 2 is ln, and lm is not more than ln, so that more outflow holes 3 can be conveniently designed in the first outflow area 1. Furthermore, the circumferential center position of each first outflow region 1 is respectively superposed with the trailing edge of one turbine stator blade 8 along the rotation direction of the turbine wheel disc, so that the sealing gas 9 discharged from the first outflow region 1 can seal the rim gap 4 at the trailing edge 6 of the stator blade to the maximum extent. In an embodiment of the present invention, the diameter of the outflow hole 3 in the first outflow region 1 is equal to the diameter of the outflow hole 3 in the second outflow region 2, the turbine wheel disc can form the rim gap 4 with other adjacent wheel discs, and the ratio of the diameter of the outflow hole 3 to the width L of the rim gap 4 is between 0.2 and 0.5.

In a specific embodiment of the present invention, as shown in fig. 1 and 2, the radius R of the turbine stator disk 5 is 190mm, and the width L of the rim gap 4 is 2 mm; the outflow holes 3 in the first outflow region 1 and the second outflow region 2 are circular holes with the diameter of 0.5mm and are distributed on the circumference with the radius of 189 mm; each first outflow region 1 comprises 13 outflow holes 3, and the circumferential hole distance lm is 0.8 mm; each second outflow area 2 consists of 2 outflow holes 3, and the circumferential hole distance ln is 2 mm; the middle outflow hole 3 of each first outflow region 1 and the corresponding stator blade tail edge 6 are located at the same circumferential position; the circumferential hole distance s between adjacent first outflow areas 1 and second outflow areas 2 (the circumferential center distance between the two outflow holes 3 closest to each other in the first outflow areas 1 and the second outflow areas 2) is 7 mm. When the main flow gas 7 flows through the turbine stationary blade 8, a large amount of lateral outflow flows in the first outflow region 1, so that the invasion degree of the stationary blade trailing edge 6 is obviously improved, the cooling gas (the seal gas 9) is subjected to circumferential migration along with the rotation of the turbine moving disk, the second outflow region 2 is supplemented, and finally the overall temperature distribution of the rim gap 4 is improved, as shown in the simulation result of fig. 3.

It can be understood that the utility model discloses the distribution mode of outlet orifice 3 has been adjusted according to near rim mainstream pressure distribution, has increased the end wall side direction of quiet leaf trailing edge 6 and has flowed out, makes this regional gas invasion degree obviously improve. The number m and n of the outflow holes 3 in each of the first outflow region 1 and the second outflow region 2, the hole distances lm and ln, and the hole distances s of the adjacent first outflow region 1 and the second outflow region 2 can be properly adjusted according to the pressure distribution, and these parameters are main parameters affecting the sealing efficiency.

The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.

The above-mentioned embodiments only represent some embodiments of the present invention, and the description thereof is specific and detailed, but not to be construed as limiting the scope of the present invention. It should be noted that, for those skilled in the art, without departing from the spirit of the present invention, several variations and modifications can be made, which are within the scope of the present invention. Therefore, the protection scope of the present invention should be subject to the appended claims.

Claims

1. A turbine quiet rim plate, the play discharge orifice on its end wall is applied to the obturating of mainstream high temperature gas, its characterized in that, the quiet rim plate of turbine includes:

a wheel disc body;

2. The turbine stator disk of claim 1 wherein the first outflow region includes a plurality of said outflow holes therein, the number of said outflow holes in said first outflow region being greater than the number of said outflow holes in said second outflow region.

3. The turbine stator disk according to claim 2, wherein the second outflow region includes a plurality of the outflow holes therein, and the plurality of the outflow holes in the second outflow region are equally spaced in a rotation direction of the disk body; the outflow holes in the first outflow area are distributed at equal intervals along the rotation direction of the wheel disc body; the circumferential hole distance between the outflow holes in the first outflow area is lm, the circumferential hole distance between the outflow holes in the second outflow area is ln, and lm is not more than ln.

4. The turbine disk according to claim 3, wherein a circumferential center position of each of the first outflow regions coincides with a trailing edge of one of the turbine vanes in a rotation direction of the disk body.

5. The turbine static disk according to claim 4, wherein the number of the outlet holes in each of the first outlet flow regions is singular, and the outlet holes in each of the first outlet flow regions located at a circumferentially central position are respectively coincident with a trailing edge of one of the turbine stationary blades in a direction of rotation of the disk body.

6. The turbine stator disk according to claim 2 wherein the diameter of the outlet holes in the first outlet region is equal to the diameter of the outlet holes in the second outlet region; the turbine static wheel disc can form a rim gap with other adjacent wheel discs, and the ratio of the diameter of the outflow hole to the width of the rim gap is between 0.2 and 0.5.

7. The turbine stator disk as claimed in claim 1, wherein the diameter of the outlet bore in the first outlet region is greater than the diameter of the outlet bore in the second outlet region.

8. The turbine stator disk according to any one of claims 1 to 7, wherein all of the outlet holes on the stator disk rim are distributed in a circle of equal radius around the axial center of the disk body.

9. A turbine comprising a stator disk according to any one of claims 1 to 8.

10. A gas turbine comprising a compressor, a combustion chamber and the turbine of claim 9, said compressor, said combustion chamber and said turbine being connected in series in the direction of gas flow.