CN107701247A - A kind of gas turbine guider inner ring impinging cooling structure, gas turbine - Google Patents

Abstract

The invention relates to an impingement cooling structure for the inner ring of a gas turbine guide, comprising an impingement cooling box plate, a gas turbine guide and a combustion chamber outlet wall, the combustion chamber outlet wall is overlapped with the inner ring gas side wall of the gas turbine guide and There is a gap formed at the lap joint, and the impact cooling box plate, the wall surface of the combustion chamber outlet and the inner ring wall of the guider form a cold air chamber, and the inner ring cold air side wall of the guider is provided with an impact cooling boss, which impacts the cylindrical surface of the cooling box plate There are multiple rows of impact cold air holes distributed on the top; the high-pressure cold air impacts the boss on the inner ring of the guide through the impact cooling holes, and then flows out through the gap to form a cooling air film on the gas side wall of the inner ring of the guide, so as to reach the inside of the guide. Efficient cooling of the ring prevents the risk of high temperature gas corrosion. The popularization and use in modern gas turbines has a positive effect on improving the performance and reliability of the engine.

Description

A gas turbine guide inner ring impingement cooling structure, gas turbine

technical field

The invention relates to the field of high-temperature parts of gas turbine turbines, and more specifically relates to an impingement cooling structure for the inner ring of the guider of the gas turbine, which can realize efficient cooling of the inner ring of the guider of the turbine, reduce thermal stress, and improve the service life and reliability of the engine. sex.

Background technique

In order to improve the performance of the gas turbine, the temperature before the high pressure turbine is continuously increased. The turbine inlet gas temperature of advanced aviation turbofan engines has reached 1800K-2050K, far exceeding the allowable temperature of existing superalloys. In order to ensure the safe operation of the high-pressure turbine, effective cooling must be implemented to reduce the metal wall temperature of the high-pressure turbine guide.

Usually, there is a gap between the combustion chamber of an aero-engine and the high-pressure turbine. In order to prevent high-temperature gas from invading through the gap and causing high-temperature corrosion to the internal structure, a high-pressure secondary airflow is introduced to seal it tightly. At the same time, the high-pressure secondary cooling airflow can cool the wall surface of the inner and outer rings of the high-pressure turbine guider through this structure. However, the gap between the combustion chamber and the high-pressure turbine guide is caused by the installation and cooperation. The outflow form of the cold air is limited by the cooperation between the two, and it cannot be well attached to the metal wall and cannot be well connected to the inner and outer ring casings. cool down. Therefore, a reasonable design of the sealing structure and cooling structure has an important impact on protecting the service life of the high-pressure turbine and the overall performance of the engine. In order to ensure the safe operation of the engine in the past, the cooling air volume is usually increased to achieve sealing and effective cooling, but increasing the cooling air volume will inevitably reduce the overall performance of the engine. In order to further improve the performance and competitiveness of the engine, a new structure is urgently needed to achieve efficient cooling of the turbine leading edge and reduce the cooling air consumption.

Contents of the invention

In view of the shortcomings and deficiencies in the above-mentioned prior art, the present invention aims to provide an arrangement for cooling the high-temperature components of modern gas turbines, especially the inner ring of the gas turbine guide, by designing a new type of cooling structure, changing the traditional The cooling method improves the cooling effect of the metal wall surface of the inner ring of the gas turbine guide, and improves the performance and reliability of the engine.

For realizing this goal, the technical scheme that the present invention adopts is:

An impingement cooling structure for the inner ring of a gas turbine guide, comprising a gas turbine guide and a combustion chamber outlet wall, the combustion chamber outlet wall overlaps with the inner ring gas side wall of the gas turbine guide and is formed at the overlap There is a gap, characterized in that,

The cooling structure also includes an impingement cooling casket with an overall annular cylindrical surface structure, the impingement cooling casket is connected upstream to the combustion outlet wall, and downstream is connected to the inner ring mounting joint of the gas turbine guider, and The impingement cooling box plate is spaced from the cold air side wall surface of the inner ring of the cooling guide by a certain distance, so that the impingement cooling box plate, the outlet wall surface of the combustion chamber and the inner ring wall surface of the gas turbine guider enclose a cold air chamber;

On the inner cold air side wall surface of the gas turbine guide, there are several bosses which are basically the same shape as the guide vane, and there are many rows of impact cold air holes distributed on the cylindrical surface of the impingement cooling box plate. The outlet direction of the impacting cold air hole is opposite to the boss;

The high-pressure cold air of the air system impacts the boss on the inner ring cold air side wall surface of the cooling guide through the impact cooling hole on the impact cooling box plate, and the cold air after impact cooling stabilizes in the cold air chamber, and then The cooling gas film is formed on the gas side wall surface of the inner ring of the gas turbine guide by flowing out through the gap.

Preferably, the upstream of the impingement cooling casket is fixed on the wall of the combustion chamber in the form of flanges or slopes, and the downstream is provided with a mounting edge, which is used to fix it on the inner ring mounting joint of the gas turbine guide.

Preferably, the impingement cooling box plate and the outlet wall of the combustion chamber are connected together by welding to prevent cold air from leaking from the overlapping joint.

Optionally, the impingement cooling box plate and the outlet wall of the combustion chamber are overlapped together through an interference fit, and the mated surfaces of the two have certain flatness and parallelism requirements to prevent cold air from leaking from the overlap.

Preferably, the thickness of the impingement cooling box plate is about 0.8 mm, so as to reduce the weight as much as possible and improve the performance of the engine while ensuring the strength requirements.

Preferably, the impingement cooling holes are periodically distributed on the impingement cooling box plate, and the impingement cooling holes are facing the inner ring boss of the gas turbine guider.

Preferably, the impingement cooling holes are distributed along the lower side of the boss edge in each cycle, densely distributed on the front edge, pressure surface and trailing edge of the boss, and sparsely distributed on the suction surface.

Preferably, the impingement cooling holes are partly distributed below the channel of the gas turbine guide where the heat load is high.

Preferably, the diameter of the impingement cooling hole is about 0.6mm, so as to achieve a better cooling effect.

Preferably, the distance between the impingement cooling casket plate and the inner ring wall of the gas turbine guider is between 2mm and 8mm, which is related to the amount of cold air and the diameter of the impingement cooling hole, so as to ensure a better impingement cooling effect.

Preferably, the outlet wall of the combustion chamber overlaps the gas side wall of the gas turbine guide, and the cooling air flows through the gap between the two to directly cool the downstream wall.

Preferably, the impingement cooling casket and the gas turbine guide inner ring mounting section are connected together by bolts.

The present invention also provides an impingement cooling casket, which is suitable for the impingement cooling structure of the inner ring of the gas turbine guide of the present invention.

The present invention also provides a gas turbine comprising the impingement cooling structure for the inner ring of the gas turbine guide.

The impingement cooling casket structure of the present invention and the combustor outlet wall surface combined with it and the inner ring structure of the gas turbine guider improve the cooling effect of the inner ring of the gas turbine. Compared with the existing form, it has the following advantages: 1. Cooling air flow The inner ring of the gas turbine guide is impinged and cooled by the impingement cooling box plate, which improves the cooling efficiency compared with the traditional convective heat exchange, thereby reducing the temperature of the metal wall and reducing the thermal stress. 2. The cooling structure is simple, easy to install and disassemble, and it is convenient to implement impingement cooling for areas with different cooling requirements. 3. Block the risk of direct contact between high-temperature gas and the internal structure. Even if there is gas intrusion, the impingement cooling box plate can block the risk of direct contact between high-temperature gas and the internal structure.

Description of drawings

Fig. 1 is the schematic diagram of impingement cooling structure of the gas turbine guide inner ring of the present invention;

Fig. 2 is a cross-sectional view of the impingement cooling box plate of the present invention.

detailed description

Below in conjunction with embodiment the present invention is described in further detail, and following example is explanation of the present invention and the present invention is not limited to following example.

As shown in FIG. 1 , the structure of the present invention for impingement cooling of the inner ring of a gas turbine guide includes an impingement cooling box plate 1 , a gas turbine guide 2 and a combustion chamber outlet wall 3 . The upstream of the impingement cooling box plate 1 is provided with a flange 101, which can be fixed on the outlet 301 of the combustion chamber by welding, or overlapped by interference fit. When the interference fit is used, it is necessary to ensure that the matching flange 101 and the outlet wall of the combustion chamber have a certain flatness requirement, as well as a parallelism requirement for the cooperation between the two, so as to prevent cold air from leaking there. A mounting edge 102 is provided downstream of the impingement cooling casket 1, and the mounting edge 102 is connected to the gas turbine guide inner ring mounting section 202 by bolts. The impingement cooling box plate 1 is provided with an impingement cooling hole 103 for impingement cooling the boss 203 provided on the cold air side wall surface of the inner ring of the guide. The impingement cooling boss 203 is formed by the internal cooling design of the guide and is in the shape of a leaf. Therefore, the arrangement of the impingement cooling holes 103 on the impingement cooling box plate is also in the shape of a leaf. The impingement cooling box plate 1 , the gas turbine guider inner ring 2 and the combustion chamber outlet wall 3 form a cold air chamber 4 . The outlet wall surface 301 of the combustion chamber overlaps the gas side of the inner ring 201 of the gas turbine guide, forming a gap between the two, and a circumferentially arranged boss can also be arranged on the inner ring 201 of the gas turbine guide to increase the size of the gap .

The flow direction of cold air and gas is indicated in Fig. 1, and the high-pressure cold air of the air system passes through the impact cooling hole 103 of the impact cooling box plate 1 and impacts the inner ring boss 203 of the cooling guide, reducing the temperature of the inner ring of the guide. The cold air after impingement cooling stabilizes in the cold air chamber 4 . Subsequently, the cold air flows out through the gap between the outlet wall surface 301 of the combustion chamber and the inner ring of the guide, and performs film cooling on the gas side wall of the inner ring of the guide, further reducing the temperature of the metal surface, thereby achieving efficient cooling of the inner ring of the guide. At the same time, due to the barrier of the impact cooling box plate, even if there is high-temperature gas intrusion, it will not cause high-temperature corrosion to the internal structure.

In summary, the present invention adopts a new impingement cooling structure, which changes the cooling method of the inner ring of the turbine guide, improves the cooling of the inner ring of the guide, and prevents the risk of high-temperature gas erosion. The popularization and use in modern gas turbines has a positive effect on improving the performance and reliability of the engine.

In addition, it should be noted that the specific embodiments described in this specification may be different in terms of parts, shapes and names of components. All equivalent or simple changes made according to the structure, features and principles described in the patent concept of the present invention are included in the protection scope of the patent of the present invention. Those skilled in the art to which the present invention belongs can make various modifications or supplements to the described specific embodiments or adopt similar methods to replace them, as long as they do not deviate from the structure of the present invention or exceed the scope defined in the claims. All should belong to the protection scope of the present invention.

Claims (9)

1. a kind of gas turbine guider inner ring impinging cooling structure, including gas turbine guider and combustor exit wall, The inner ring combustion gas side wall of the combustor exit wall and the gas turbine guider is overlapped and formed in lap-joint seamed Gap, it is characterised in that

The cooling structure also includes the impinging cooling casket plate of an overall cylindrical surface structure in a ring, the impinging cooling casket plate Upstream is tightly connected with the combustor exit wall, downstream and the inner ring installation section connection of the gas turbine guider, and The inner ring cold air side wall of the impinging cooling casket plate and the cooled guide device is spaced apart, so as to the impinging cooling Casket plate, combustor exit wall and gas turbine guider inner ring wall surround a cold air chamber；

In the inner ring cold air side wall of the gas turbine guider it is circumferentially distributed have it is some basic with guider blade profile shape Identical boss, multiple rows of impact cold air hole is distributed with the face of cylinder of the impinging cooling casket plate, and the impact cold air hole goes out Mouth direction is relative with the boss.

2. the cooling structure according to the claims, it is characterised in that the upstream of the impinging cooling casket plate is by turning over The form on side or inclined-plane is fixed on the combustor exit wall, downstream be provided with installation side, by it is described installation side by its It is fixed on the inner ring installation section of the gas turbine guider.

3. the cooling structure according to the claims, it is characterised in that impinging cooling casket plate upstream flange passes through The form sealing of welding is fixed on combustor exit wall.

4. the cooling structure according to the claims, it is characterised in that impinging cooling casket plate upstream flange passes through The mode of interference is together with combustor exit wall lap hermetically.

5. according to the cooling structure described in the claims 4, it is characterised in that the impinging cooling casket plate upstream flange and combustion The flatness of room outlet wall and the depth of parallelism of both cooperations are burnt, cold air should be caused not let out in the lap-joint of the two Dew.

6. the cooling structure according to the claims, it is characterised in that the impinging cooling hole is periodically distributed in On the impinging cooling casket plate, impinging cooling is carried out to the boss of the gas turbine guider inner ring.

7. the cooling structure according to the claims, it is characterised in that the impinging cooling hole is along the gas turbine The circle of outer rim distribution one or two circles of guider inner ring boss, can implement effective cooling, reducing heat should to guider root Power.

8. the cooling structure according to the claims, it is characterised in that the impinging cooling hole is in the gas turbine Leading edge, trailing edge and the pressure EDS maps comparatively dense of guider inner ring boss, suction surface is more sparse, can also be uniformly distributed, mainly According to the design of guider inner ring thermic load.

9. the cooling structure according to the claims, it is characterised in that also there is part in the impinging cooling hole according to need It is opened in the high region of guide channel thermic load.