阅读说明：本技术 一种变几何低压涡轮导向叶片 (Variable-geometry low-pressure turbine guide vane ) 是由 陶一鸾 王焘 万发君 尤宏德 于 2021-07-30 设计创作，主要内容包括：本申请属于低压涡轮导向叶片领域,特别涉及一种变几何低压涡轮导向叶片。包括：叶身(1)、上转台(2)、进气部以及下转台(3)。本申请在保证不影响内部冷却通道的基础上针对上下转台的主体部进行沿周向局部挖空设计,具有叶型相适配的形状,并且,保留预定厚度的实体；通过设计凸台结构可以近似形成单道篦齿结构,具有一定的封严功能,防止燃气向外泄露,从配合间隙流入挖空区域。本申请的变几何低压涡轮导向叶片,考虑了叶片冷却、铸造工艺性、封严、重量以及摩擦产生的扭矩等多方面因素。在满足可调叶片功能性要求的基础上,通过局部挖空设计,有效降低叶片重量,提高工艺性,降低摩擦阻力矩,增强柱面配合封严效果。(The application belongs to the field of low-pressure turbine guide vanes, and particularly relates to a variable-geometry low-pressure turbine guide vane. The method comprises the following steps: blade body (1), go up revolving stage (2), air inlet portion and lower revolving stage (3). The design of local hollowing along the circumferential direction is carried out on the main body parts of the upper rotary table and the lower rotary table on the basis of ensuring that an internal cooling channel is not influenced, the main body parts have shapes matched with the blade profiles, and entities with preset thicknesses are reserved; the boss structure can be designed to approximately form a single-channel labyrinth structure, has a certain sealing function, prevents gas from leaking outwards, and flows into a hollowed area from a fit clearance. The variable geometry low pressure turbine guide vane of the application considers various factors such as vane cooling, casting manufacturability, sealing, weight and torque generated by friction. On the basis of meeting the functional requirement of the adjustable blade, the weight of the blade is effectively reduced through the local hollow design, the manufacturability is improved, the friction resistance moment is reduced, and the cylindrical surface matching sealing effect is enhanced.)

1. A variable geometry low pressure turbine guide vane comprising:

the cooling structure comprises a blade body (1), wherein a first cooling channel is arranged inside the blade body (1);

an upper rotary table (2), wherein the upper rotary table (2) is arranged at the upper end of the blade body (1), a second cooling channel communicated with the first cooling channel is arranged in the upper rotary table (2), the upper rotary table (2) comprises a first main body part (21), a first upper end plate (22) and a first lower end plate (23),

the first main body part (21) is locally hollowed along the circumferential direction and is provided with a solid body matched with the blade profile;

the first upper end plate (22) is arranged at the upper end of the first main body part (21), and the first upper end plate (22) is connected with a rotating shaft of the adjustable mechanism;

the first lower end plate (23) is arranged at the lower end of the first main body part (21), the first lower end plate (23) is parallel to the corresponding flow passage surface, a first boss (24) is arranged on the gas side of the first lower end plate (23), and the first boss (24) is connected with the blade body (1);

the air inlet part is arranged on the first upper end plate (22), an air collecting cavity communicated with the second cooling channel is arranged in the air inlet part, and an air inlet hole is formed in the wall surface of the air inlet part;

a lower rotary table (3), the lower rotary table (3) is arranged at the lower end of the blade body (1), a third cooling channel communicated with the first cooling channel is arranged in the lower rotary table (3), the lower rotary table (3) comprises a second main body part (31), a second upper end plate (32) and a second lower end plate (33), wherein,

the second main body part (31) is locally hollowed along the circumferential direction and is provided with a solid body matched with the blade profile;

the second upper end plate (32) is arranged at the upper end of the second main body part (31), the second upper end plate (32) is parallel to the corresponding flow passage surface, a second boss (34) is arranged on the gas side of the second upper end plate (32), and the second boss (34) is connected with the blade body (1);

the second lower end plate (33) is arranged at the lower end of the second main body part (31), and the second lower end plate (33) is connected with a rotating shaft of the adjustable mechanism.

2. Variable geometry low pressure turbine guide vane according to claim 1, characterized in that the blade body (1), the upper turret (2), the air intake and the lower turret (3) are of one-piece construction.

3. The variable geometry low pressure turbine guide vane of claim 1 wherein the wall of the inlet portion has four inlet holes formed therein uniformly along the circumferential direction.

4. The variable geometry low pressure turbine guide vane of claim 1,

the first cooling channel of the blade body (1) is provided with three flow paths, including a first flow path close to the leading edge, a second flow path in the middle and a third flow path close to the trailing edge;

the second cooling channel of the upper turntable (2) is provided with three flow paths, including a fourth flow path communicated with the first flow path, a fifth flow path communicated with the second flow path, and a sixth flow path communicated with the third flow path;

the third cooling channel of the lower rotary table (3) has a flow path which communicates with the second flow path of the blade body (1).

5. The variable geometry low pressure turbine guide vane of claim 1 wherein the first body portion (21) and the second body portion (31) have a thickness of 1 to 1.5 times the thickness of the vane wall.

6. The variable geometry low pressure turbine guide vane of claim 5 wherein the first upper end plate (22) and the second lower end plate (33) are each circular in shape, the first upper end plate (22) and the second lower end plate (33) having a thickness that is 1.5 times the thickness of the vane wall.

7. The variable geometry low pressure turbine guide vane of claim 6 wherein the first lower end plate (23) and the second upper end plate (32) have a thickness of 1 to 1.5 times the thickness of the vane wall.

8. The variable geometry low pressure turbine guide vane of claim 7 wherein the first boss (24) and the second boss (34) have a thickness of 1 to 1.5 times the thickness of the vane wall.

9. The variable geometry low pressure turbine guide vane of claim 1,

the joint of the first main body part (21) and the first upper end plate (22) and the joint of the first main body part (21) and the first lower end plate (23) are provided with roundings;

the junction of the second main body part (31) and the second upper end plate (32), and the junction of the second main body part (31) and the second lower end plate (33) are both provided with a rounding.

10. The variable geometry low pressure turbine guide vane of claim 9 wherein the junction of the first boss (24) and the airfoil (1), and the junction of the second boss (34) and the airfoil (1), are each provided with a radius.

Technical Field

The application belongs to the field of low-pressure turbine guide vanes, and particularly relates to a variable-geometry low-pressure turbine guide vane.

Background

With the improvement of the combat capability requirement of fighters, aeroengines with the characteristics of large takeoff thrust, excellent high-speed flight thrust characteristic, low-speed flight oil consumption and the like need to be developed. The self-adaptive engine can realize large-range thermodynamic cycle adjustment and optimization, so that the engine has good performance in various working states, and is an important direction for the development of future aeroengines. The variable geometry low-pressure turbine is an important part of the self-adaptive engine, the flow of the low-pressure turbine is adjusted by adjusting the installation angle of the guide vanes, the distribution of turbine power among the high-pressure and low-pressure turbines is enhanced, and the rotating speed adjusting capacity of a high-pressure rotor and a low-pressure rotor is improved.

At present, a solid cylindrical rotary table is connected to the upper end and the lower end of a vane for realizing the adjustable function of the vane, the upper end surface of the rotary table is a plane and is connected with a rotating shaft connected with an adjustable mechanism, and the lower end surface of the rotary table is a gas side and is a meridian flow channel surface corresponding to the axial position. In order to reduce the exposed area of the end face of a blade, reduce the leakage of tip gas and ensure the efficiency of a turbine when a rotary table in the prior art is designed, a cylindrical rotary table can contain the blade profile as much as possible, so that the diameter of the rotary table is large, and the solid part except a cooling channel is more; meanwhile, in order to realize higher efficiency in a limited axial space on the turbine performance, the expansion of the meridian passage is more obvious. According to the matching requirements of the inner ring, the outer ring and the adjustable structure, the cold side end face of the rotary table needs to be designed into a plane perpendicular to the rotating shaft of the blade, and therefore the thickness of the rotary table along the axial direction of the engine is remarkably changed. The above problems have a significant effect on the weight and manufacturability of the blade. Taking a certain adjustable guide vane as an example, the weight of the whole vane is already occupied by 60% of the weight of the whole vane only by the upper turntable part, and a larger moment is needed if the adjustment is realized; meanwhile, in the process, the wall thickness of the blade body is thinner and far smaller than the radial thickness of the upper rotary table, the blade is integrally cast and processed, the cooling of a place with small thickness is fast in the pouring process, the cooling of a place with large thickness is slow, the remarkable cold and heat unevenness can generate large heat stress at the corner position, the casting difficulty is increased, and the structural manufacturability is poor.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Disclosure of Invention

The object of the present application is to provide a variable geometry low pressure turbine guide vane to address at least one of the problems of the prior art.

The technical scheme of the application is as follows:

a variable geometry low pressure turbine guide vane comprising:

the cooling structure comprises a blade body, wherein a first cooling channel is arranged inside the blade body;

an upper turntable arranged at the upper end of the blade body, a second cooling channel communicated with the first cooling channel is arranged in the upper turntable, the upper turntable comprises a first main body part, a first upper end plate and a first lower end plate, wherein,

the first main body part is locally hollowed along the circumferential direction and is provided with a solid body matched with the blade profile;

the first upper end plate is arranged at the upper end of the first main body part and is connected with a rotating shaft of the adjustable mechanism;

the first lower end plate is arranged at the lower end of the first main body part, the first lower end plate is parallel to the corresponding flow passage surface, a first boss is arranged on the gas side of the first lower end plate, and the first boss is connected with the blade body;

the air inlet part is arranged on the first upper end plate, an air collecting cavity communicated with the second cooling channel is arranged in the air inlet part, and an air inlet hole is formed in the wall surface of the air inlet part;

a lower rotary table arranged at the lower end of the blade body, a third cooling channel communicated with the first cooling channel is arranged in the lower rotary table, the lower rotary table comprises a second main body part, a second upper end plate and a second lower end plate, wherein,

the second main body part is locally hollowed along the circumferential direction and is provided with a solid body matched with the blade profile;

the second upper end plate is arranged at the upper end of the second main body part and is parallel to the corresponding flow passage surface, and a second boss is arranged on the gas side of the second upper end plate and is connected with the blade body;

the second lower end plate is arranged at the lower end of the second main body part and is connected with a rotating shaft of the adjustable mechanism.

In at least one embodiment of the present application, the blade body, the upper turntable, the air inlet portion, and the lower turntable are an integrally formed structure.

In at least one embodiment of the present application, four air inlet holes are uniformly formed in the wall surface of the air inlet portion along the circumferential direction.

In at least one embodiment of the present application,

the first cooling passage of the airfoil having three flow paths including a first flow path near the leading edge, a second flow path in the middle, and a third flow path near the trailing edge;

the second cooling channel of the upper turntable is provided with three flow paths, including a fourth flow path communicated with the first flow path, a fifth flow path communicated with the second flow path and a sixth flow path communicated with the third flow path;

the third cooling passage of the lower turntable has one flow path communicating with the second flow path of the blade body.

In at least one embodiment of the present application, the thickness of the first main body portion and the second main body portion is 1 to 1.5 times of the thickness of the wall surface of the blade.

In at least one embodiment of the present application, the first upper end plate and the second lower end plate are both circular, and the thickness of the first upper end plate and the second lower end plate is 1.5 times the thickness of the wall surface of the blade.

In at least one embodiment of the present application, the thickness of the first lower end plate and the second upper end plate is 1 to 1.5 times of the thickness of the wall surface of the blade.

In at least one embodiment of the present application, the thickness of the first boss and the second boss is 1 to 1.5 times of the thickness of the wall surface of the blade.

In at least one embodiment of the present application,

rounding is arranged at the joint of the first main body part and the first upper end plate and at the joint of the first main body part and the first lower end plate;

the second main part with second up end plate junction, and the second main part with second end plate junction all is provided with the radius.

In at least one embodiment of the present application, the first boss and the blade body junction, and the second boss and the blade body junction are provided with a radius.

The invention has at least the following beneficial technical effects:

the utility model provides a become how much low pressure turbine guide vane revolving stage structure, on the basis that satisfies adjustable blade functional requirement, through the design of locally digging out, effectively reduce blade weight, improve manufacturability, reduce the frictional resistance moment, reinforcing cylinder cooperation effect of obturaging.

Drawings

FIG. 1 is a schematic backside view of a variable geometry low pressure turbine guide vane of an embodiment of the present application;

FIG. 2 is a schematic view of a variable geometry low pressure turbine guide vane basin side of an embodiment of the present application;

FIG. 3 is a schematic cross-sectional view A-A of FIG. 1;

FIG. 4 is a schematic top turn table of a variable geometry low pressure turbine guide vane of an embodiment of the present application.

Wherein:

1-leaf body; 2-upper rotating platform; 21-a first body portion; 22-a first upper end plate; 23-a first lower end plate; 24-a first boss; 3-lower turntable; 31-a second body portion; 32-a second upper end plate; 33-a second lower end plate; 34-a second boss.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. 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. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

The present application is described in further detail below with reference to fig. 1 to 4.

The application provides a become how much low pressure turbine guide vane includes: blade 1, go up revolving stage 2, inlet air portion and lower revolving stage 3.

Specifically, a first cooling channel is arranged inside the blade body 1, the upper end surface and the lower end surface of the blade body 1 are respectively parallel to the corresponding flow channel surfaces, and a fuel gas flow channel can be formed outside the blade body 1.

The upper rotary table 2 is arranged at the upper end of the blade body 1, a second cooling channel communicated with the first cooling channel is arranged in the upper rotary table 2, and the upper rotary table 2 comprises a first main body part 21, a first upper end plate 22 and a first lower end plate 23. Wherein, the first main body part 21 is locally hollowed along the circumferential direction and is provided with a solid body matched with the blade profile; the first upper end plate 22 is arranged at the upper end of the first main body part 21, and the first upper end plate 22 is connected with a rotating shaft of the adjustable mechanism; the first lower end plate 23 is disposed at the lower end of the first main body 21, the first lower end plate 23 is parallel to the corresponding flow passage surface, a first boss 24 is disposed on the gas side of the first lower end plate 23, and the first boss 24 is connected to the blade body 1.

The air inlet part is arranged on the first upper end plate 22, a gas collecting cavity communicated with the second cooling channel is arranged in the air inlet part, and an air inlet hole is formed in the wall surface of the air inlet part. In this embodiment, the air inlet portion is coaxial with the rotating shaft of the adjustable mechanism, and four air inlets are uniformly formed in the wall surface of the air inlet portion along the circumferential direction.

Further, the lower rotary table 3 is arranged at the lower end of the blade body 1, a third cooling channel communicated with the first cooling channel is arranged inside the lower rotary table 3, the lower rotary table 3 comprises a second main body part 31, a second upper end plate 32 and a second lower end plate 33, wherein the second main body part 31 is locally hollowed along the circumferential direction and is provided with a solid body matched with the blade profile; the second upper end plate 32 is arranged at the upper end of the second main body part 31, the second upper end plate 32 is parallel to the corresponding flow passage surface, a second boss 34 is arranged on the gas side of the second upper end plate 32, and the second boss 34 is connected with the blade body 1; the second lower end plate 33 is disposed at the lower end of the second main body 31, and the second lower end plate 33 is connected to the rotating shaft of the adjustable mechanism.

In the variable geometry low pressure turbine guide vane of the present application, the first cooling channel inside the blade body 1 is divided into three flow paths, including a first flow path near the leading edge, a second flow path in the middle, and a third flow path near the trailing edge. The second cooling channel of the upper turntable 2 is matched with the first cooling channel of the blade body 1, and is also divided into three flow paths, and each flow path comprises a fourth flow path communicated with the first flow path, a fifth flow path communicated with the second flow path, and a sixth flow path communicated with the third flow path. The third cooling channel of the lower turret 3 has one flow path communicating with the second flow path of the blade body 1. The cooling gas flows into the blade from the air inlet of the air inlet part, enters the second cooling channel of the upper rotary table 2 through the gas collecting cavity of the air inlet part, is divided into three paths by the second cooling channel, one path flows into the first flow path of the blade body 1 through the fourth flow path of the upper rotary table 2 and then flows out from the front edge gas film hole, the other path flows into the second flow path of the blade body 1 through the fifth flow path of the upper rotary table 2 and then flows out from the third cooling channel of the lower rotary table 3, and the last path flows into the sixth flow path of the upper rotary table 2 and then flows out from the tail edge cleft seam after flowing into the third flow path of the blade body 1.

In the preferred embodiment of the present application, the blade body 1, the upper turntable 2, the air inlet portion, and the lower turntable 3 are of an integrally molded structure, and are integrally cast.

In the preferred embodiment of the present application, the main body portions of the upper and lower turrets are designed to be partially hollowed out in the circumferential direction while ensuring that the internal cooling passages are not affected, have a shape adapted to the profile of the blade, and retain a solid body of a predetermined thickness. As shown in fig. 3, in one embodiment of the present invention, the thickness of the first body 21 and the second body 31 is 1 to 1.5 times of the thickness of the wall surface of the blade, and in the specific design, the thickness of the turntable is significantly reduced in the axial direction, so that the turntable cannot be completely hollowed in the circumferential direction.

In the preferred embodiment of the present application, in order to ensure a sufficient cylindrical surface fit area for facilitating the connection with the rotating shaft of the adjustable mechanism, the first upper end plate 22 and the second lower end plate 33 are arranged in a circular shape, and the thickness of the first upper end plate 22 and the second lower end plate 33 is preferably set to be 1.5 times the thickness of the wall surface of the blade. In the present embodiment, the thickness of the first lower end plate 23 and the second upper end plate 32 is preferably set to be 1 to 1.5 times the thickness of the blade wall surface.

In a preferred embodiment of the present application, the thickness of the first boss 24 and the second boss 34 is 1 to 1.5 times the thickness of the blade wall surface. The boss structure can be similar to form a single-channel labyrinth structure, has a certain sealing function, and prevents gas from leaking outwards and flowing into a hollowed area from a fit clearance.

In a preferred embodiment of the application, it is possible to ensure that the transfer points do not develop large thermal stresses by providing a rounding. In this embodiment, the joints of the first main body 21 and the first upper end plate 22 and the joints of the first main body 21 and the first lower end plate 23 are rounded. The junction of the second main body 31 and the second upper end plate 32 and the junction of the second main body 31 and the second lower end plate 33 are rounded. The joints of the first bosses 24 and the blade body 1 and the joints of the second bosses 34 and the blade body 1 are provided with rounding circles.

The variable geometry low pressure turbine guide vane of the application considers various factors such as vane cooling, casting manufacturability, sealing, weight and torque generated by friction. On the basis of meeting the functional requirement of the adjustable blade, the weight of the blade is effectively reduced through the local hollow design, the manufacturability is improved, the friction resistance moment is reduced, and the cylindrical surface matching sealing effect is enhanced.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.