Turbine rotor blade and gas turbine including the same

Abstract

A turbine rotor blade and a gas turbine including the same, wherein the turbine rotor blade includes a blade body, the blade body includes a cold air channel and an impact plate; the cold air channel is arranged inside the blade body; the impact plate is arranged inside the blade body; wherein the impact plate is provided with an impact hole, the impact hole is connected to the cold air channel, and is used to pass the cooling air in the cold air channel through the impact hole to perform impact-enhanced cooling on the top area of ​​the blade body. The turbine rotor blade of the present invention adopts a complex cold air channel structure inside, and impact-enhanced cooling is adopted in the cold air channel inside the blade body near the tip area, and the characteristics of high cooling air pressure margin and high heat transfer coefficient of impact cooling of the rotor blade are utilized to reduce the metal temperature in the tip area of ​​the rotor blade, thereby improving the service life of the turbine rotor blade.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a turbine rotor blade and a gas turbine comprising the same. Background Art

[0002] With the improvement of gas turbine design technology, the temperature of gas at the inlet of gas turbine turbine is increasing, and the thermal load faced by turbine components is extremely high, which has long exceeded the limit that high-temperature materials can withstand. In order to ensure the safe and reliable operation of turbine blades, complex cooling design is required to keep the temperature and stress distribution of the blade body at a reasonable level.

[0003] Among various internal cooling heat exchange technologies, impingement cooling has the highest heat transfer coefficient and the best heat transfer effect, but the pressure loss is also the largest, so a higher cooling air pressure is required.

[0004] In the process of turbine blade cooling design, there are three-dimensional flow structures such as leakage flow in the blade tip area. Since the blade tip area is far away from the cold air inlet, the air used for cooling has been heated up, and the internal convection cooling structure has a relatively low heat transfer coefficient, so the cooling effect is often poor. Under the influence of the above factors, the blade tip area of ​​the turbine rotor blade is very likely to cause high temperature oxidation due to poor cooling effect or excessive thermal stress, resulting in cracks, or even ablation and other failure phenomena. Summary of the invention

[0005] In view of this, the main object of the present invention is to provide a turbine rotor blade and a gas turbine including the same, in order to at least partially solve at least one of the above-mentioned technical problems.

[0006] To achieve the above object, the technical solution of the present invention is as follows:

[0007] As one aspect of the present invention, a turbine rotor blade is provided, comprising a blade body, wherein the blade body comprises a cold air passage and an impingement plate;

[0008] A cold air channel is arranged inside the blade body;

[0009] An impact plate, arranged inside the blade body;

[0010] The impact plate is provided with an impact hole, which is connected with the cold air channel and is used for passing the cooling air in the cold air channel through the impact hole to perform impact-enhanced cooling on the tip area of ​​the blade body.

[0011] As another aspect of the present invention, a gas turbine is also provided, comprising the turbine rotor blade as described above.

[0012] Based on the above technical solution, compared with the prior art, the present invention has at least one or part of the following beneficial effects:

[0013] Without increasing the total cooling air volume, the present invention utilizes the characteristics of high cold air pressure and high heat load in the blade tip area, and adopts an impingement cooling structure to enhance heat exchange between the blade tip and the wall of the post-impact chamber, thereby effectively reducing the metal temperature in the blade tip area. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 is a three-dimensional schematic diagram of a turbine rotor blade according to Embodiment 1-3 of the present invention;

[0015] Figure 2 is a schematic cross-sectional view of the internal structure of a turbine rotor blade according to Embodiment 1 of the present invention;

[0016] Figure 3 yes Figure 2 AA section view;

[0017] Figure 4 yes Figure 2 BB cross-sectional view;

[0018] Figure 5 yes Figure 2 The CC section view;

[0019] Figure 6 is a schematic cross-sectional view of the internal structure of a turbine rotor blade according to Embodiment 2 of the present invention;

[0020] Figure 7 yes Figure 6 DD cross-sectional view;

[0021] Figure 8 yes Figure 6 EE cross-sectional view;

[0022] Fig. 9 yes Figure 6 FF cross-sectional view.

[0023] Fig.10 is a schematic cross-sectional view of the internal structure of a turbine rotor blade according to Embodiment 3 of the present invention;

[0024] Fig.11 yes Fig.10 GG cross-sectional view;

[0025] Fig.12 yes Fig.10 HH cross-sectional view;

[0026] Fig.13 yes Fig.10 JJ section cutaway view.

[0027] In the above drawings, the meanings of the reference numerals are as follows:

[0028] 1-root cold air channel entrance; 2-film cooling hole; 3, 17-impact hole; 4-trailing edge injection hole; 5-film hole; 8-top cover plate; 9-impact plate; 11-blade root; 12-blade platform; 13-blade body; 14-cold air channel; 15-trailing edge cold air channel; 16-impact cold air channel; 18-leading edge channel; 20-blade profile mid-arc line; 21-air collecting cavity; 22-impact rear chamber; 23-blade top groove; 24-blade root cavity; 31-suction surface; 32-pressure surface; 33-blade leading edge; 34-blade trailing edge; 41-rib structure; 42-column rib structure; 101-first cold air channel entrance; 102-second cold air channel entrance; 103-third cold air channel entrance; A-high-temperature combustion gas; B-cooling air. DETAILED DESCRIPTION

[0029] In view of the fact that the top area of ​​the blade has a higher pressure margin and a higher heat load due to the effect of centrifugal force, the present invention adopts impingement cooling to enhance heat exchange without increasing the total cooling air volume, thereby enhancing heat exchange in the tip area of ​​the turbine blade and effectively reducing the temperature and thermal stress level of the blade tip area.

[0030] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings.

[0031] As one aspect of the present invention, a turbine rotor blade is provided, comprising a blade body, the blade body comprising a cold air passage and an impact plate;

[0032] A cold air channel is arranged inside the blade body;

[0033] An impact plate is arranged inside the blade body;

[0034] Among them, an impact hole is arranged on the impact plate, and the impact hole is connected with the cold air channel, and is used for passing the cooling air in the cold air channel through the impact hole to perform impact intensive cooling on the tip area of ​​the blade body.

[0035] In an embodiment of the present invention, a plurality of impact holes are arranged on the impact plate, and the diameter of the impact holes is smaller than the inner diameter of the cold air passage.

[0036] In an embodiment of the present invention, the blade body further comprises a top cover plate, which forms a top space in communication with the cold air passage at the top of the blade body; the impact plate is arranged in the top space, dividing the top space into a gas collecting cavity and a post-impact cavity;

[0037] Among them, the air collecting cavity is connected with the cold air channel; the impact rear chamber is connected with the air collecting cavity through the impact hole;

[0038] A cooling air hole is arranged on the wall of the post-impact chamber, which is used to cool the tip area of ​​the blade body through the cooling air in the post-impact chamber. The flow rate and pressure of the cooling air in the post-impact chamber in the tip area of ​​the turbine rotor blade can be adjusted.

[0039] In an embodiment of the present invention, the top cover plate is fixed to the blade body by a brazing process and the blade cooling air passage is blocked to form a post-impact chamber; the impact plate structure is fixed to the blade body by a brazing process.

[0040] In an embodiment of the present invention, the impact hole processing method includes casting, electric spark, laser or mechanical processing;

[0041] The hole shape of the impact hole includes one or more of round, oval, square, and diamond;

[0042] The plurality of impact holes are arranged on the impact plate in a sequential or staggered arrangement.

[0043] The impact hole can be processed before brazing, or after the impact plate and the blade body are fixed by brazing.

[0044] In an embodiment of the present invention, the cooling air hole is provided on the top cover plate;

[0045] The cooling air holes are arranged on the pressure surface and / or suction surface of the blade body corresponding to the rear impact chamber; and / or

[0046] The cooling air hole is arranged on the trailing edge of the blade body corresponding to the rear impact chamber.

[0047] More specifically, in an embodiment of the present invention, the cooling holes include film holes arranged on the top cover plate, trailing edge injection holes arranged on the trailing edge of the blade body, and film cooling holes arranged on the pressure surface, the leading edge of the blade and the suction surface.

[0048] In an embodiment of the present invention, the root of the turbine rotor blade may be a cavity structure, and multiple radial cooling air passages inside are connected to the cavity. The cooling air may first enter the cavity and then enter the multiple radial cooling air passages.

[0049] There is at least one complex cooling air channel inside the turbine rotor blade, and the complex cooling air channel is integrally formed during the precision casting process of the turbine rotor blade.

[0050] In the embodiment of the present invention, the ends of the plurality of cold air channels are all connected to a gas collecting cavity, and the gas collecting cavity is correspondingly provided with an impact plate and a post-impact chamber.

[0051] More specifically, multiple complex cooling air passages inside the turbine rotor blades converge into an air collecting cavity, and the cooling air cools the top cover plate and the wall of the chamber after the impact through the impact holes on the impact plate.

[0052] In other embodiments of the present invention, the ends of the plurality of cold air channels are respectively connected to at least two air collecting cavities; each air collecting cavity is individually provided with a corresponding impact plate and a post-impact chamber.

[0053] More specifically, the multiple complex cold air channels inside the turbine rotor blades do not all correspond to one air collecting cavity; instead, they can be designed so that each cold air channel corresponds to a separate air collecting cavity, or multiple cold air channels correspond to at least two air collecting cavities, and each air collecting cavity is separately provided with an impact plate and a post-impact chamber, and the cooling air cools the top cover plate and the wall of the post-impact chamber through the impact holes on the impact plate.

[0054] In an embodiment of the present invention, cold air channel film cooling holes are provided on the wall surface corresponding to the cold air channel, so as to discharge the cooling air in the cold air channel through the cold air channel film cooling holes to cool the tip area of ​​the blade body.

[0055] In summary, the cooling air inside the cavity after the turbine rotor blade impacts enters the blade tip groove through the air film holes and dust removal holes on the top cover plate to further cool the blade tip area; or enters the mainstream combustion gas through the trailing edge injection hole; or enters the mainstream combustion gas through the air film cooling holes on the pressure surface or the suction surface. In addition, the cooling air in at least one complex cold air channel inside the turbine rotor blade can be directly discharged to the outside of the turbine rotor blade through the cold air channel air film cooling holes without entering the air collecting cavity.

[0056] In an embodiment of the present invention, the cold air passage is radially arranged inside the blade body;

[0057] The processing methods of cold air channels include casting, electrochemical or electric spark;

[0058] The cold air passage includes a section of through holes in the extending direction, but is not limited thereto, and may also include multiple sections of through holes that are interconnected; wherein the inner diameters of the multiple sections of through holes are different;

[0059] More specifically, when the turbine rotor blades are greatly twisted along the blade height direction, two-stage butt-joint hole forming can be used.

[0060] A fin structure and / or a column fin structure for enhancing heat exchange is arranged in the cold air passage;

[0061] The turbine rotor blade also includes a turbulence generating device, which is arranged inside the cold air passage to enhance convection cooling and improve the heat exchange capacity of the area.

[0062] As another aspect of the present invention, a gas turbine is also provided, comprising the turbine rotor blade as described above.

[0063] The technical solution of the present invention will be further described below in conjunction with specific embodiments. However, it should be noted that the following embodiments are only used to illustrate the technical solution of the present invention, but the present invention is not limited thereto.

[0064] Example 1

[0065] like Figure 1 As shown in FIG. 1 , the turbine rotor blade includes a blade body 13, a blade root 11, and a blade platform 12 between the blade body 13 and the blade root 11. By cutting the blade along the blade profile mid-camber line 20, the internal structure of the blade can be obtained, such as Figure 2 As shown. The blade has a plurality of cooling air channels 14 for cooling gas flow inside. The cooling gas is delivered to the root cooling air channel inlet 1 of the turbine rotor blade. The size and number of the root cooling air channel inlet 1 are designed based on the required cooling gas flow and the blade structure. Figure 3 As shown, the root cold air passage inlet 1 includes a first cold air passage inlet 101 , a second cold air passage inlet 102 , and a third cold air passage inlet 103 .

[0066] There is at least one cooling flow path inside the blade to provide cooling air to the blade tip area, such as Figure 2 , Figure 4 As shown, Figure 4 for Figure 2 The BB cross-sectional view includes: three radial cold air channels 14 and a first cold air channel inlet 101, a second cold air channel inlet 102, and a third cold air channel inlet 103 that provide cooling air for the three cold air channels 14; after the cooling air enters the cold air channel 14 from the first cold air channel inlet 101, the second cold air channel inlet 102, and the third cold air channel inlet 103, after convection heat exchange occurs with the blades on the inner surface of the cold air channel 14, the cooling air enters the air collecting cavity 21.

[0067] like Figure 2 and Figure 5 As shown, the high-pressure cooling air in the air collecting cavity 21 impacts and cools the top cover plate 8 through the impact holes 3 on the impact plate 9 and enters the impact rear chamber 22, enters the blade top groove 23 from the air film holes 5 on the top cover plate 8, further cools the blade tip area and mixes with the blade tip leakage flow; the cooling air entering the impact rear chamber 22 can be directly discharged into the mainstream combustion gas through the trailing edge injection holes 4 on the blade trailing edge 34; the cooling air entering the impact rear chamber 22 can enter the mainstream combustion gas through the air film cooling holes 2 arranged on the pressure surface 32, the suction surface 31 and the blade leading edge 33.

[0068] Example 2

[0069] like Figure 6-9 As shown, the turbine rotor blade includes: three radial cold air channels 14 and a blade root cavity 24 that provides cooling air for the three cold air channels 14; the cooling air enters the blade root cavity 24 from the first cold air channel inlet 101, and then enters the cold air channel 14, and after convective heat exchange occurs with the blade on the inner surface of the cold air channel 14, it enters the air collecting cavity 21.

[0070] The high-pressure cooling air in the air collecting cavity 21 performs impact cooling on the top cover plate 8 through the impact holes 3 on the impact plate 9 and enters the rear impact chamber 22, enters the blade top groove 23 from the air film holes 5 on the top cover plate 8, further cools the blade tip area and mixes with the leakage flow at the blade tip; the cooling air entering the rear impact chamber 22 can be directly discharged into the mainstream combustion gas through the trailing edge injection holes 4 on the blade trailing edge 34; the cooling air entering the rear impact chamber 22 can enter the mainstream combustion gas through the air film cooling holes 2 arranged on the pressure surface 32, the suction surface 31 and the blade leading edge 33.

[0071] Example 3

[0072] like Figure 10-13 As shown, the turbine rotor blade includes: three complex cold air channels, a leading edge cold air channel 14, a trailing edge cold air channel 15, an impingement cold air channel 16, and a first cold air channel inlet 101, a second cold air channel inlet 102, and a third cold air channel inlet 103 for providing cooling air for these three cold air channels; after the cooling air enters the cold air channel 14, the trailing edge cold air channel 15, and the impingement cold air channel 16 from the first cold air channel inlet 101, the second cold air channel inlet 102, and the third cold air channel inlet 103, convection heat exchange occurs with the blade on the inner surfaces of the cold air channel 14, the trailing edge cold air channel 15, and the impingement cold air channel 16.

[0073] Among them, after the cooling air in the first cold air channel inlet 101 enters the impact cold air channel 16, it enters the leading edge channel 18 along the impact hole 17 and impact-cools the leading edge 33 of the blade, and the cooling air enters the mainstream combustion gas from the air film cooling hole 2 at the leading edge (i.e., the cold air channel air film cooling hole); after the cooling air in the third cold air channel inlet 103 enters the trailing edge cold air channel 15, it undergoes enhanced heat exchange with the fin structure 41, enters the column rib structure 42 in the blade trailing edge 34 area to continue enhanced heat exchange, and then is ejected from the trailing edge injection hole 4 and enters the mainstream combustion gas.

[0074] After the cooling air in the second cold air channel inlet 102 enters the cold air channel 14 , it undergoes enhanced heat exchange with the fin structure 41 and then enters the air collecting cavity 21 .

[0075] The high-pressure cooling air in the air collecting cavity 21 performs impact cooling on the top cover plate 8 through the impact holes 3 on the impact plate 9 and enters the rear impact chamber 22, enters the blade top groove 23 from the air film holes 5 on the top cover plate 8, further cools the blade tip area and mixes with the blade tip leakage flow; the cooling air entering the rear impact chamber 22 can be directly discharged into the mainstream combustion gas through the trailing edge injection holes 4 on the blade trailing edge 34; the cooling air entering the rear impact chamber 22 can enter the mainstream combustion gas through the air film cooling holes 2 arranged on the pressure surface 32, the suction surface 31 and the leading edge 33.

[0076] The specific embodiments described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A turbine rotor blade, comprising a blade body, It is characterized in that The blade body includes a cold air channel and an impact plate; A cold air channel is arranged inside the blade body; An impact plate is arranged inside the blade body; Wherein, the impact plate is provided with an impact hole, the impact hole is connected with the cold air channel, and is used for passing the cooling air in the cold air channel through the impact hole to perform impact strengthening cooling on the tip area of ​​the blade body; The blade body also includes a top cover plate, wherein the top cover plate forms a top space in communication with the cold air channel at the top of the blade body; the impact plate is arranged in the top space, and divides the top space into a gas collecting cavity and a post-impact cavity; wherein the top cover plate is configured to be fixed to the blade body by a brazing process; Wherein, the gas collecting cavity is connected with the cold air channel; the post-impact chamber is connected with the gas collecting cavity through the impact hole; A cooling air hole is arranged on the wall surface of the post-impact chamber, and is used to cool the tip area of ​​the blade body through the cooling air in the post-impact chamber.

2. The turbine rotor blade according to claim 1, It is characterized in that A plurality of impact holes are arranged on the impact plate, and the diameter of the impact holes is smaller than the inner diameter of the cold air passage.

3. The turbine rotor blade according to claim 1, It is characterized in that The cooling air holes include air film holes arranged on the top cover plate, trailing edge injection holes arranged on the trailing edge of the blade body, and air film cooling holes arranged on the pressure surface, the leading edge of the blade and the suction surface.

4. The turbine rotor blade according to claim 3, It is characterized in that The ends of the plurality of cold air channels are all connected to an air collecting cavity, and the air collecting cavity is correspondingly provided with an impact plate and a post-impact chamber.

5. The turbine rotor blade according to claim 3, It is characterized in that The ends of the plurality of cold air channels are respectively connected to at least two air collecting cavities; each air collecting cavity is individually provided with a corresponding impact plate and a post-impact chamber.

6. The turbine rotor blade according to claim 1, It is characterized in that A cold air channel air film cooling hole is arranged on the wall surface corresponding to the cold air channel, so as to discharge the cooling air in the cold air channel through the cold air channel air film cooling hole to cool the tip area of ​​the blade body.

7. The turbine rotor blade according to claim 1, It is characterized in that The cold air channel is radially arranged inside the blade body; The processing method of the cold air channel includes casting, electrochemistry or electric spark; The cold air passage includes one section of through hole or multiple sections of through holes that are interconnected in the extending direction; wherein the inner diameters of the multiple sections of through holes are different; The cold air passage is provided with a fin structure and / or a column fin structure for enhancing heat exchange; The turbine rotor blade further comprises a turbulence generating device, and the turbulence generating device is arranged inside the cold air passage.

8. The turbine rotor blade according to claim 1, It is characterized in that The impact hole processing method includes casting, electric spark, laser or mechanical processing; The hole shape of the impact hole includes one or more of circular, elliptical, square, and diamond; The plurality of impact holes are arranged on the impact plate in a sequential or staggered arrangement.

9. A gas turbine, It is characterized in that The invention comprises a turbine rotor blade according to any one of claims 1 to 8.

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