CN115898567A - Guide cooling blade and turbine guider - Google Patents

Abstract

The application discloses a guide cooling blade and a turbine guider. The guide cooling blade comprises a blade base body, a cavity is arranged in the blade base body, an impact pipe is arranged in the cavity, and the impact pipe is provided with an impact hole facing the inner wall of the front edge of the blade base body and a cold air inlet used for introducing cold air. The turbine guider comprises the guide cooling blade, and further comprises an inner ring and an outer ring which are coaxially arranged from inside to outside, an annular airflow channel is formed between the outer ring and the inner ring, an outer ring hole is formed in the outer ring in a penetrating mode, an inner ring hole penetrating to the annular airflow channel is formed in the inner ring, the guide cooling blade sequentially penetrates through the inner ring hole, the annular airflow channel and the outer ring hole, and the blade base body is arranged in the annular airflow channel. The application is used for solving the following problems: the existing cooling technology for the guide vane has the technical problems of poor cooling stability and low cold air utilization rate.

Description

Guide cooling blade and turbine guider

Technical Field

The application relates to the technical field of gas turbine engines, in particular to a guide cooling blade and a turbine guider.

Background

An Auxiliary Power Unit (APU) is one of the branches of a gas turbine engine, and is mainly used for starting a main engine of an aircraft, supplying power to the aircraft, and the like. The APU in the earlier stage can meet the requirements of aircraft manufacturers by adopting the turbine guider with a non-cooling structure, but with the development of scientific technology and the change of world pattern, the aircraft manufacturers have higher and higher requirements on the performance of the main engine and the APU, and the non-cooling turbine guider cannot meet the development requirements of the advanced APU in the prior art. To accommodate the higher pre-turbine temperatures of advanced APUs, it is necessary to take appropriate cooling measures for the turbine guide. The current gas turbine engine has a great development trend towards higher power-to-weight ratio and higher thermodynamic cycle parameters, and in order to improve the power-to-weight ratio of the engine, the temperature of gas before the turbine is increased year by year. The turbine guider is usually arranged behind high-temperature gas, the working condition of the turbine guider is quite severe, the turbine guider is the part with the largest heat load in an engine, the temperature distribution of guide blades is uneven, and the turbine guider is subjected to larger aerodynamic force and unstable pulsating load. Therefore, effective cooling measures are adopted, the working temperature of the blade is reduced, and the thermal stress of the blade is reduced, so that the safe and reliable work of the engine is effectively guaranteed.

In order to cool the guide vane, the conventional method is intensified convection cooling, in which fins or turbulence columns are arranged in an internal channel of the vane to increase the heat exchange area between the cold air and the inner wall surface of the guide vane and improve the turbulence of the cold air flow, the turbulence refers to the turbulence degree of the flow, and the more turbulent the flow is, the stronger the heat exchange is, so as to perform rapid and uniform heat exchange on the guide vane, but the intensified convection cooling is difficult to rapidly cool the front edge of the vane and to rapidly eliminate the thermal stress of the front edge of the vane. After that, in order to effectively reduce the thermal stress of the leading edge of the blade, the blade can be cooled by adopting an impact cooling mode, wherein the impact cooling mode is to use one or more cold air jets to impact the inner surface of the blade, the impact cooling mode is characterized in that a jet stagnation area has a high heat exchange coefficient, the temperature of an impact area can be rapidly reduced, but the jet structure can weaken the structural strength of the inner surface of the blade. At present, the most effective cooling mode is air film cooling, air film cooling means offers one row or multirow air film hole at the blade, air conditioning is flowed by the spout, prevent gas and blade direct contact, though air film cooling can eliminate the thermal stress of blade leading edge fast, also be difficult for weakening the structural strength of blade internal surface, but air film cooling's cooling effect receives the velocity of flow of high temperature gas air current, the influence of factors such as flow direction, and job stabilization nature is relatively poor, need consume more air conditioning simultaneously, the air conditioning rate of use is lower.

Disclosure of Invention

Therefore, the present application is to solve: the prior cooling technology for the guide vane has the technical problems of poor cooling stability and low utilization rate of cold air. Thereby providing a guide cooling blade and turbine guide.

In order to solve the technical problem, the technical scheme of the application is as follows: the utility model provides a direction cooling blade, includes the blade base member, the inside cavity that is equipped with of blade base member, be equipped with in the cavity and strike the pipe, it is equipped with the orientation on the pipe to strike the cold air entry that is equipped with towards the hole of strikeing of blade base member leading edge inner wall and is used for letting in air conditioning.

Preferably, a cold air channel for allowing the cold air after impact to flow out is reserved between the outer wall of the impact pipe and the inner wall of the cavity.

Preferably, the inner wall of the cavity is provided with a first perturbation structure, and a gap smaller than or equal to 0.1mm is reserved between the first perturbation structure and the outer wall of the impact tube.

Preferably, a second perturbation structure is arranged on the inner wall of one end face of the cavity, and one end face of the second perturbation structure is tightly attached to the end face of the impact tube.

Preferably, a process boss is arranged on the outer wall of one end face of the cavity, and a gap smaller than or equal to 0.1mm is reserved between the outer wall of one end face of the impact tube and the inner wall of the process boss.

Preferably, blade base member afterbody be equipped with "L" type breach and with the trailing edge hole that "L" type breach is connected, the entry in trailing edge hole with the cavity intercommunication, the export in trailing edge hole is located the short side in "L" type breach, a long limit in trailing edge hole with the long limit coplane in "L" type breach.

The application still provides a turbine director, including above-mentioned arbitrary item direction cooling blade, still include inner ring and the outer loop of from inside to outside coaxial setting, the outer loop with form annular airflow channel between the inner ring, wear to be equipped with outer annular ring on the outer loop, be equipped with on the inner ring and wear to establish extremely annular airflow channel's inner ring hole, direction cooling blade wears to establish in proper order the inner ring hole annular airflow channel outer annular ring hole sets up, just the blade base member sets up in the annular airflow channel.

Preferably, the outer ring is provided with a vent hole, the outer edges of the outer ring and the inner ring are in lap joint with the air outlet end of the flame tube, and gaps are reserved at the lap joint part of the outer ring, the inner ring and the air outlet end of the flame tube.

Preferably, the flame tube further comprises a containing ring coaxially arranged on the inner side of the inner ring, the containing ring is connected with one outer edge of the inner ring, and the other outer edge of the inner ring is overlapped with the gas outlet end of the flame tube.

Preferably, the thickness of the part of the inner ring, which is in contact with the containing ring, is greater than the thickness of other parts of the inner ring, and the inner ring and the containing ring are connected through a fastener.

The technical scheme of the application has the following advantages:

1. the application provides a direction cooling blade, the impact pipe is equipped with towards the impact hole of blade base member leading edge inner wall, flows out from the impact hole after cold air gets into the impact pipe, and cold air is direct to carry out the heat transfer to blade base member leading edge inner wall, carries out accurate, quick cooling to blade base member leading edge, reaches the purpose that reduces blade base member leading edge thermal fatigue damage. In addition, compare in the direct heat transfer mode that carries out the air conditioning and strike to blade base member leading edge inner wall, in the heat transfer mode that this application provided, air conditioning gets into and strikes the pipe after again from strikeing the hole outflow, and the impact strength of air conditioning has reduced by a wide margin, can not lead to the fact strong impact to blade base member leading edge inner wall, consequently can not lead to the fact the destruction to the structural strength of blade base member leading edge internal surface. Moreover, compare in the air film cooling mode that mentions in the background art, the cooling mode that this application provided does not receive the influence of outside high temperature gas, can provide stable cooling effect for blade base member leading edge, simultaneously, in the technical scheme of this application, air conditioning continues to cool off inside the blade base member cavity after to blade base member leading edge internal cooling, has improved the rate of utilization of air conditioning, reduces extravagantly.

2. The application provides a direction cooling blade, air conditioning carries out even cooling to blade base member cavity inner wall along the air conditioning passageway after cooling to blade base member leading edge inner wall, can cool off the whole of blade base member, helps reducing the thermal stress of blade base member.

3. The application provides a direction cooling blade, the effect of vortex is played to the air conditioning air current to the first disturbance structure in the cavity, can increase the heat transfer area of air conditioning air current and cavity inner wall, improves the turbulent degree that air conditioning flows to improve heat exchange efficiency. The clearance between the first perturbation structure and the outer wall of the impact pipe is set to be less than or equal to 0.1mm, so that the first perturbation structure is prevented from clamping the impact pipe, and the assembly between the impact pipe and the guide cooling blade is prevented from being influenced.

4. The application provides a direction cooling blade, second disturbance structure can play limiting displacement to strikeing the pipe, also can play the vortex effect to strikeing the intraduct air conditioning air current for the speed of flow of air conditioning improves heat exchange efficiency.

5. The application provides a direction cooling blade has set up the technology boss at the outer wall of cavity terminal surface, rethread technology boss with strike union coupling, reduced the degree of difficulty of being connected of will assaulting pipe and technology boss, the assembly of being convenient for.

6. The application provides a direction cooling blade, all air conditioning in the cavity are discharged by the trailing edge hole, and the long limit of L type breach is hugged closely to exhaust air conditioning flows, implements the air film cooling to blade base member trailing edge. The long edge of the tail edge hole is coplanar with the long edge of the L-shaped notch, so that the stability of a cold airflow field can be ensured, and the air film can be uniformly covered.

7. The application provides a turbine guider, high temperature gas flow along annular airflow channel, and air conditioning can carry out quick cooling to guide vane, outer loop, inner ring, avoids high temperature gas to cause the destruction to turbine guider's structural strength.

8. The utility model provides a turbine guider has two cold air sources to cool off to the front and the back of turbine guider, and two cold air sources carry out the primary cooling back to the front and the back of turbine guider, from outer loop, inner ring and the flame tube give vent to anger the clearance between the end and flow into annular airflow channel and carry out the secondary cooling to inner ring, outer loop. The inner ring and the outer ring are used as main heating parts, and the secondary cooling is carried out on the inner ring and the outer ring, so that the structural strength of the inner ring and the outer ring can be prevented from being damaged, and the service life of the turbine guider can be prolonged.

9. The application provides a turbine guider, the containing ring is surrounded by cold air, and the temperature is lower, and the containing ring can absorb the heat of inner ring transmission, is favorable to reducing inner ring's operating temperature. In addition, the contact part of the inner ring and the containing ring is thickened, which is beneficial to improving the heat transfer efficiency of the inner ring and the containing ring.

Drawings

In order to more clearly illustrate the detailed description of the present application or the technical solutions in the prior art, the drawings used in the detailed description or the prior art description will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative efforts.

FIG. 1 is a schematic illustration of a turbine nozzle and liner assembly according to an embodiment of the present disclosure;

FIG. 2 is a schematic view of the overall construction of a turbine nozzle in an embodiment of the present application;

FIG. 3 is a schematic illustration of the positional relationship of the guide cooling blades to the turbine guide in an embodiment of the present application;

FIG. 4 is a schematic view of the overall structure of a guide cooling blade in an embodiment of the present application;

FIG. 5 is a schematic view of the overall construction of an impingement tube in an embodiment of the present application;

FIG. 6 is a longitudinal sectional view of a guide cooling blade in the embodiment of the present application;

FIG. 7 is an enlarged view of the portion C of FIG. 6 in an embodiment of the present application;

FIG. 8 is a cross-sectional view of a guide cooling blade taken along line B in an embodiment of the present application;

FIG. 9 is a sectional view of a guide cooling blade taken along line A in an embodiment of the present application.

Description of the reference numerals: 1. a blade base body; 2. an impingement tube; 3. an outer ring; 4. an inner ring; 5. a vent hole; 6. an annular gas flow passage; 7. an impingement hole; 8. a first perturbation structure; 9. a second perturbation structure; 10. a turbulence column; 11. a trailing edge aperture; 12. a middle cambered surface; 13. a process boss; 14. a partition rib; 15. an outer ring of the flame tube; 16. an inner ring of the flame tube; 17. a flare beak; 18. a containment ring; 19. an inner annular ring; 20. and (4) an outer ring hole.

Detailed Description

The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in this application will be understood to be a specific case for those of ordinary skill in the art.

Example 1

The guide cooling blade provided by the embodiment comprises a blade base body 1, wherein the shape of the blade base body 1 is as shown in fig. 1 and fig. 4-9, line a of fig. 6 is a cambered surface 12 of a cavity, arrow a in fig. 1 represents the flow direction of high-temperature fuel gas, and arrows b and c represent the flow direction of a cooling gas source. The front edge of the blade base body 1 is thicker than the tail edge of the blade base body 1, a cavity is arranged inside the blade base body 1, the shape of the cavity is similar to that of the blade base body 1, an impact pipe 2 is arranged in the cavity, the impact pipe 2 is inserted into the blade base body 1 from one end face of the blade base body 1, and the cross section of the impact pipe 2 is similar to that of the cavity. The impact pipe 2 is provided with an impact hole 7 and a cold air inlet for introducing cold air, the impact hole 7 is arranged towards the inner wall of the front edge of the blade matrix 1, and the cold air inlet is arranged towards the end face of the impact pipe 2 inserted into the blade matrix 1. The number of the impact holes 7 in each row is 4-8, the impact holes 7 in the middle row of the three rows of the impact holes 7 face to the middle of the front edge of the blade matrix 1, the impact holes 7 in the upper row face to the upper side wall of the front edge of the blade matrix 1, and the impact holes 7 in the lower row face to the lower side wall of the front edge of the blade matrix 1. In addition, the hole diameter, the number of holes, the arrangement mode and the like of the impact holes 7 can be selectively changed according to different guides, and the impact holes 7 can be arranged at other parts of the impact pipe 2.

The working process of the guide cooling blade provided by the embodiment is as follows: the guide cooling blades are generally used in conjunction with a guide, which positions the leading edge of the guide cooling blade toward the hot gas. When the high-temperature gas rushes to the guide vane, the high-temperature gas carries out thermal shock on the front edge of the vane base body 1, the temperature of the front edge of the vane base body 1 is higher than that of other parts of the vane base body 1, and the front edge of the vane base body 1 is easy to generate thermal fatigue after the high-temperature gas is kept in the state for a long time. Accessible air conditioning entry lets in air conditioning to strikeing 2 this moment in, flows out from strikeing hole 7 after air conditioning gets into strikeing 2, and air conditioning is direct to carrying out the heat transfer to 1 leading edge inner wall of blade base member, carries out accurate, quick cooling to 1 leading edge of blade base member, reaches the purpose that reduces 1 leading edge thermal fatigue damage of blade base member. In addition, compare in the direct heat transfer mode that carries out the air conditioning and assault to blade base member leading edge inner wall, in the heat transfer mode that this application provided, air conditioning gets into and flows out from assault hole 7 again behind the pipe 2, and the impact strength of air conditioning has reduced by a wide margin, can not lead to the fact strong impact to 1 leading edge inner wall of blade base member, consequently can not lead to the fact the destruction to the structural strength of 1 leading edge internal surface of blade base member. Moreover, compare in the air film cooling mode that mentions in the background art, the cooling mode that this application provided does not receive the influence of outside high temperature gas, can provide stable cooling effect for blade base member 1 leading edge, simultaneously, in the technical scheme of this application, air conditioning continues to cool off inside the cavity of blade base member 1 after to the inside cooling of blade base member 1 leading edge, has improved the rate of utilization of air conditioning, reduces extravagantly.

Example 2

This embodiment is a further improvement of embodiment 1, and a cold air channel for allowing the cold air after impact to flow out is reserved between the outer wall of the impact tube 2 and the inner wall of the cavity. The inner wall of the cavity of the blade base body 1 is uniformly cooled along the cold air channel after the inner wall of the front edge of the blade base body 1 is cooled by the cold air, so that the whole body of the blade base body 1 is cooled, and the reduction of the thermal stress of the blade base body 1 is facilitated.

The inner wall of the cavity is provided with a first perturbation structure 8, and a gap smaller than or equal to 0.1mm is reserved between the first perturbation structure 8 and the outer wall of the impact tube 2. The shape of first perturbation structure 8 is the hemisphere boss, and the hemisphere boss in the cavity plays the effect of vortex to the air conditioning air current, can increase the heat transfer area of air conditioning air current and cavity inner wall, improves the turbulent degree that air conditioning flows to improve heat exchange efficiency. The gap between the hemispherical boss and the outer wall of the impingement tube 2 is set to be less than or equal to 0.1mm, so as to avoid the hemispherical boss from blocking the impingement tube 2 and influencing the assembly between the impingement tube 2 and the guide cooling blades.

The inner wall of the end face of the cavity far away from the cold air inlet is provided with a second disturbance structure 9, and one end face of the second disturbance structure 9 is tightly attached to the end face of the impact tube 2. The structure of second disturbance structure 9 is semi-cylindrical boss, and second disturbance structure 9 can play limiting displacement to strikeing pipe 2, also can play the vortex effect to the inside air conditioning air current of strikeing pipe 2 for the flow speed of air conditioning improves heat exchange efficiency.

The outer wall of the end face of the cavity corresponding to the cold air inlet is provided with a process boss 13, and one end face of the impact tube 2 is connected with the process boss 13. In a general process, the impact tube 2 is connected with the blade base body 1 in a welding mode, and the process boss 13 is arranged, so that the difficulty in welding the impact tube 2 and the blade base body 1 is reduced, and the impact tube 2 and the blade base body 1 are convenient to assemble.

Near the trailing edge of the cavity, a turbulence column 10 is provided. Two trailing edge lateral walls of blade base member 1 are a long one short, therefore the trailing edge of blade base member 1 forms the breach of L type, and blade base member 1 afterbody is equipped with the trailing edge hole 11 of being connected with "L" type breach, and the entry and the cavity intercommunication of trailing edge hole 11, the export of trailing edge hole 11 are located the short edge of "L" type breach, and a long limit of trailing edge hole 11 and the long limit coplane of "L" type breach. Trailing edge hole 11 is for following a plurality of rectangular holes of 1 radial distributions of blade base member, separates by separating rib 14 between the hole, and trailing edge hole 11 and cavity intercommunication, air conditioning in the cavity discharge along L type breach after passing through trailing edge hole 11, and air conditioning keeps even stable circulation along the long limit of 1 trailing edge of blade base member after discharging from L type breach, helps discharging the heat in the cavity fast. And (3) the turbulence of the turbulence column 10 implements intensified convection cooling on the inner part of the cavity, other part of cold air implements convection cooling on the cavity through the cold air channel, finally all the cold air is discharged from the tail edge hole 11, the discharged cold air flows closely to the long edge of the L-shaped notch, and air film cooling is implemented on the tail edge of the blade substrate 1. The long edge of the tail edge hole 11 is coplanar with the long edge of the L-shaped notch, so that the stability of a cold air flow field can be ensured, and the air film can be uniformly covered.

Example 3

The present embodiment provides a turbine nozzle comprising the guide cooling blade of embodiment 1 or 2. As shown in fig. 1-3, the turbine nozzle further includes an inner ring 4 and an outer ring 3 coaxially disposed from inside to outside, and an annular airflow channel 6 is formed between the outer ring 3 and the inner ring 4, as shown in fig. 1, the annular airflow channel 6 is substantially in an inverted L shape when viewed from a central cross section, and after the turbine nozzle inlet extends along an axial direction for a certain length, the annular airflow channel 6 is folded in a 90 ° direction to form airflow channels distributed along a radial direction. As shown in fig. 3, an outer ring hole 20 is formed in the outer ring 3, an inner ring hole 19 formed in the annular airflow channel 6 is formed in the inner ring 4, guide cooling blades are sequentially arranged in the annular airflow channel 6, the inner ring hole 19 and the outer ring hole 20, and the blade base 1 is arranged in the annular airflow channel 6. High temperature gas strikes towards annular airflow channel 6, and high temperature gas flows along annular airflow channel 6, and cold air can carry out quick cooling to guide blade, outer loop 3, inner ring 4, avoids high temperature gas to cause the destruction to the structural strength of turbine director.

Example 4

In this embodiment, as a further supplement to embodiment 3, the outer ring 3 is provided with a plurality of vent holes 5 along the circumferential direction, the outer edges of the outer ring 3 and the inner ring 4 of the turbine guide are overlapped with the air outlet end of the flame tube, and gaps are reserved in the overlapping parts of the outer ring 3, the inner ring 4 and the air outlet end of the flame tube. The air outlet end of the flame tube comprises a flame tube outer ring 15, a flame tube inner ring 16 and a flame tube beak 17, the outer ring 3 is lapped with the flame tube outer ring 15, and the lapping gap delta 1 is not less than 0.2-0.4mm. The two sides of the inner ring 4 are respectively lapped with the inner ring 16 of the flame tube and the beak 17 of the flame tube, wherein the lapping gap delta 2 of the inner ring 4 and the inner ring 16 of the flame tube is 0.2-0.4mm, and the lapping gap of the inner ring 4 and the beak 17 of the flame tube is not specifically limited. As shown in FIG. 1, two cold air sources b and c cool the front and the back of the turbine guider, the cold air source c flows into the annular airflow channel 6 from the joint of the outer ring 3 and the outer ring 15 of the flame tube to cool the outer ring 3 for the second time after primarily cooling the back of the outer ring 3, one part of the cold air source b flows into the impact tube 2 through a cold air inlet, and the other part flows into the annular airflow channel 6 from the joint of the inner ring 4, the inner ring 16 of the flame tube and the beak 17 of the flame tube to cool the inner ring 4 for the second time. The inner ring 4 and the outer ring 3 are used as main heating parts, and the secondary cooling is carried out on the inner ring 4 and the outer ring 3, so that the structural strength of the inner ring 4 and the outer ring 3 can be prevented from being damaged, and the service life of the turbine guider can be prolonged. Part of the cold air source c also enters the annular airflow channel 6 through the vent holes 5 to perform air film cooling on the front surface of the outer ring 3, and the damage of the turbine guider due to high-temperature gas impact is reduced.

The turbine guider also comprises a containing ring 18 which is coaxially arranged on the inner side of the inner ring 4, the containing ring 18 is connected with one outer edge of the inner ring 4, and the other outer edge of the inner ring 4 is overlapped with the air outlet end of the flame tube. The thickness of the contact part of the inner ring 4 and the containing ring 18 is larger than that of other parts of the inner ring 4, the inner ring 4 is connected with the containing ring 18 through a fastening piece, and the fastening piece can be a bolt. The containing ring 18 is surrounded by the cold air source b, the temperature is low, and the containing ring 18 can absorb the heat transferred by the inner ring 4, so that the working temperature of the inner ring 4 is favorably reduced. The contact part of the inner ring 4 and the containing ring 18 is thickened, which is beneficial to improving the heat transfer efficiency of the inner ring 4 and the containing ring 18.

It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. This need not be, nor should it be exhaustive of all embodiments. And obvious variations or modifications of the invention are intended to be covered by the present invention.

Claims (10)

1. The utility model provides a direction cooling blade, includes blade base member (1), its characterized in that, blade base member (1) inside is equipped with the cavity, be equipped with in the cavity and strike pipe (2), be equipped with the orientation on striking pipe (2) the cold air entry that strikes hole (7) and be used for letting in cold air of blade base member (1) leading edge inner wall.

2. Guide cooling blade according to claim 1, characterised in that a cold air channel is reserved between the outer wall of the impingement tube (2) and the inner wall of the cavity, which allows the flow of the impinged cold air.

3. Guide cooling blade according to claim 1, characterised in that the inner wall of the cavity is provided with a first perturbation (8), a gap smaller than or equal to 0.1mm being reserved between the first perturbation (8) and the outer wall of the impingement tube (2).

4. Guide cooling vane according to claim 1, characterized in that the inner wall of one end face of the cavity is provided with a second perturbation (9), and that one end face of the second perturbation (9) is arranged against the end face of the impingement tube (2).

5. Guide cooling blade according to claim 1, characterised in that one end face outer wall of the cavity is provided with a process boss, and a gap smaller than or equal to 0.1mm is reserved between one end face outer wall of the impingement tube (2) and the process boss inner wall.

6. Guide cooling blade according to any of claims 1-5, characterized in that the blade base body (1) is provided with an "L" shaped notch at the rear and a trailing edge hole (11) connected to the "L" shaped notch, the inlet of the trailing edge hole (11) is in communication with the cavity, the outlet of the trailing edge hole (11) is located on the short side of the "L" shaped notch, one long side of the trailing edge hole (11) is coplanar with the long side of the "L" shaped notch.

7. A turbine guider, characterized in that, includes the direction cooling blade of any claim 1-6, still includes inner ring (4) and outer loop (3) from inside to outside coaxial setting, outer loop (3) with form annular airflow channel (6) between inner ring (4), wear to be equipped with outer annular ring (20) on outer loop (3), be equipped with on inner ring (4) and wear to establish to interior annular ring (19) of annular airflow channel (6), direction cooling blade wears to establish in proper order interior annular ring (19) annular airflow channel (6) outer annular ring (20) set up, just blade base member (1) sets up in annular airflow channel (6).

8. The turbine guider according to claim 7, wherein the outer ring (3) is provided with a vent hole (5), the outer edges of the outer ring (3) and the inner ring (4) are overlapped with the air outlet end of the flame tube, and gaps are reserved at the overlapped parts of the outer ring (3), the inner ring (4) and the air outlet end of the flame tube.

9. The turbine guider according to claim 7 or 8, further comprising a containing ring (18) coaxially arranged at the inner side of the inner ring (4), wherein the containing ring (18) is connected with one outer edge of the inner ring (4), and the other outer edge of the inner ring (4) is overlapped with the gas outlet end of the flame tube.

10. The turbine nozzle as claimed in claim 9, characterized in that the thickness of the inner ring (4) in contact with the containment ring (18) is greater than the thickness of the remaining portions of the inner ring (4), the inner ring (4) being connected to the containment ring (18) by fasteners.

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