A fixing structure of a turbine guide vane, an aero-engine

Abstract

A turbine guide fixing structure, an aero-engine, the fixing structure comprises a connecting cylinder, a hollow cylinder structure with both ends open, used for connecting with high guide vanes on the turbine guide; a connecting disc, a circular ring shape, used for connecting with an outer casing; a bellows, one end of which is welded with the end of the connecting cylinder, and the other end is welded with the inner ring surface of the connecting disc. The aero-engine comprises the turbine guide fixing structure. In the application, by using the connecting cylinder with both ends open, it is used for connecting with the high guide vanes on the turbine guide, and at the same time, by using the connecting disc, it can be used for connecting with the outer casing. The connecting cylinder and the connecting disc are connected through the bellows, so that when the turbine guide is hot deformed, by using the bellows structure, radial displacement can be achieved, and at the same time, when the turbine guide is subjected to axial force, axial displacement can be achieved, and vibration energy can be absorbed, and the vibration of the turbine guide is relieved.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more particularly to turbine guide vane technology in aero-engines, specifically to a fixed structure for a turbine guide vane and an aero-engine. Background Technology

[0002] The turbine is one of the key components of an aero-engine, and the turbine guide is a key part of the turbine component. The design of the turbine guide's fixed structure is an important part of the turbine component design.

[0003] Modern aero engines and gas turbines are developing towards higher thrust-to-weight ratios, resulting in fewer stages in their high- and low-pressure turbines and smaller spatial dimensions, leading to increasingly compact structures. To adapt to these development trends, turbine guide vanes have undergone modifications in structural form, connection methods, and sealing. Currently, fourth-generation engines have achieved turbine inlet temperatures of 1850–1950 K, and development is progressing towards 2200 K for fifth-generation engines. Under such high inlet temperatures and pressures, the design of the turbine guide vane's fixing structure is one of the key aspects of turbine design.

[0004] In the prior art, patent application CN115539136A discloses a turbine guide assembly structure and its design method, as well as an aero-engine. In this assembly structure, the first end of the first mounting part is connected to the mounting ring along the axial direction of the inner cavity, and the second end of the first mounting part is connected to the guide along the radial direction of the inner cavity. The first mounting part is designed as an arc-shaped structure so that the first end and the second end of the first mounting part can transition through the arc-shaped structure.

[0005] In the aforementioned prior art, although the first mounting part can effectively reduce stress concentration and increase the thermal conductivity length of the blade tip sealing ring, thus greatly reducing the thermal deformation of the blade tip sealing ring caused by the temperature of the guide vane, when the turbine inlet temperature is around 1950K, radial and axial displacements will occur during thermal deformation of the turbine guide vane. The existing fixing structure cannot simultaneously solve the problems of radial and axial displacements during thermal deformation, and cannot better alleviate the vibration of the turbine guide vane. Summary of the Invention

[0006] This invention provides a fixing structure for a turbine guide, which simultaneously solves the problems of radial and axial displacement during thermal deformation and alleviates the vibration of the turbine guide.

[0007] The present invention also provides an aircraft engine employing the aforementioned turbine guide fixing structure.

[0008] To achieve the above objectives, the present invention proposes a fixing structure for a turbine guide, comprising: a connecting cylinder, which is a hollow cylindrical structure with open ends, for connecting to the high-guide blades on the turbine guide; a connecting disc, which is annular in shape, for connecting to the outer casing; and a bellows, one end of which is welded to the end of the connecting cylinder and the other end of which is welded to the inner annular surface of the connecting disc.

[0009] Preferably, the corrugated pipe has an S-shaped cross-section.

[0010] Preferably, a plurality of first bolt holes are evenly distributed on the end of the connecting cylinder away from the bellows, and a plurality of second bolt holes are evenly distributed on the end of the connecting cylinder near the bellows; a first screw is inserted into the first bolt hole and a second screw is inserted into the second bolt hole, respectively for bolting connection with the high-guide blade.

[0011] Preferably, a stop ring is provided on the outer peripheral surface of the connecting cylinder, and a second annular washer is provided on the second screw. The second annular washer is located in the area between the stop ring and the bellows, and the outer peripheral surface of the second annular washer abuts against the stop ring.

[0012] Preferably, a first annular washer and a stop washer are sequentially fitted onto the first screw. The end of the stop washer near the bellows is bent upward and abuts against the first annular washer, and the end of the stop washer away from the bellows is bent downward and extends downward beyond the lower edge of the high guide vane edge plate.

[0013] Preferably, a plurality of third bolt holes are evenly distributed on the connecting plate.

[0014] Preferably, a plurality of first cold air holes are provided on the connecting cylinder, the shape of the first cold air holes is consistent with the shape of the inner cavity opening of the high-conductivity blade, and the first cold air holes are used to connect to the inner cavity of the high-conductivity blade.

[0015] Preferably, a plurality of second air vents are provided near the first air vent.

[0016] Preferably, multiple rows of third air vents are provided on the connecting cylinder near the bellows.

[0017] On the other hand, the present invention proposes an aero-engine including the aforementioned turbine guide vane fixing structure.

[0018] Due to the adoption of the above technical solution, the beneficial effects of the present invention are as follows:

[0019] (1) In this invention, a connecting cylinder with open ends is used to connect with the high-guide blades on the turbine guide, and a connecting plate is used to connect with the outer casing. The connecting cylinder and the connecting plate are connected by a bellows, so that when the turbine guide is thermally deformed, it can be radially displaced by utilizing the bellows' corrugated structure. At the same time, when the turbine guide is subjected to axial force, it can be axially displaced, and vibration energy can be absorbed to alleviate the vibration of the turbine guide.

[0020] (2) By utilizing the fixed structure of the turbine guide provided by the present invention, the high-pressure turbine guide can work normally under the condition of turbine inlet temperature of about 1950K, and the cooling effect, hot deformation, vibration and other aspects meet the requirements of use.

[0021] (3) In this invention, by providing a first bolt hole and a second bolt hole on the connecting cylinder, the high-guide blade is connected by bolts, resulting in a simple structure and convenient installation of the high-guide blade. Furthermore, by using a retaining ring on the outer circumference of the connecting cylinder to abut against the outer circumference of the second annular washer, the axial movement of the second screw can be further limited, ensuring the relative position of the high-guide blade and the connecting cylinder under high-temperature operating conditions. Similarly, by providing a first annular washer and a retaining washer, and by using the bending structure at both ends of the retaining washer to form a limiting structure to limit the position of the first screw, the relative position of the high-guide blade and the connecting cylinder is further ensured.

[0022] (4) In this invention, by providing a first cooling air hole that connects to the inner cavity of the high-guide-force blade, cooling air can enter the inner cavity of the high-guide-force blade for cooling the blade. By providing multiple second cooling air holes near the first cooling air hole, the edge plate of the high-guide-force blade can be cooled. By providing multiple rows of third cooling air holes, cooling air can enter the gap between two adjacent high-guide-force blades for cooling the blade body. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0024] Figure 1 A schematic diagram of the fixing structure of the turbine guide provided by the present invention;

[0025] Figure 2 A three-dimensional structural diagram of the fixing structure of the turbine guide provided by the present invention;

[0026] Figure 3A schematic diagram showing the location of the cooling air vents on the fixing structure of the turbine guide provided by the present invention;

[0027] Figure 4 This is a schematic diagram of the fixed structure of the turbine guide vane provided by the present invention during assembly with the high-guide blades and outer casing.

[0028] Explanation of reference numerals in the attached diagram: 1. Connecting cylinder; 2. Bellows; 3. Connecting disc; 4. Stop ring; 5. First screw; 6. Second screw; 7. First air vent; 8. Second air vent; 9. First bolt hole; 10. Third air vent; 11. Second bolt hole; 12. Outer casing; 13. Third bolt hole; 14. High-guide vane; 15. Stop washer; 16. First annular washer; 17. Second annular washer; A. Inner cavity of the high-guide vane. Detailed Implementation

[0029] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0030] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0031] Furthermore, the use of terms such as "first" and "second" in this invention is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed by this invention.

[0032] As shown in the accompanying drawings, as a first aspect, embodiments of the present invention provide a fixing structure for a turbine guide, comprising:

[0033] The connecting cylinder 1 is a hollow cylindrical structure with open ends, used to connect with the high-guide blades 14 on the turbine guide vane;

[0034] The connecting plate 3 is ring-shaped and is used to connect to the outer casing 12;

[0035] The bellows 2 is welded at one end to the end of the connecting cylinder 1 and at the other end to the inner ring surface of the connecting disc 3.

[0036] Since the connecting cylinder 1 and the connecting disc 3 are connected by the bellows 2, the turbine guide can be radially displaced when it is thermally deformed by utilizing the corrugated structure of the bellows 2. At the same time, when the turbine guide is subjected to axial force, it can be axially displaced. In addition, the bellows 2 can absorb vibration energy and alleviate the vibration of the turbine guide.

[0037] Combination Figure 1 As shown, the corrugated pipe 2 has an S-shaped cross-section. The S-shape can avoid the appearance of sharp edges on the surface of the corrugated pipe 2, making the surface of the corrugated pipe 2 a smooth transition structure, avoiding stress concentration, and further ensuring the effect of the corrugated pipe 2 in absorbing vibration energy.

[0038] Combination Figure 3 , Figure 4 As shown, multiple first bolt holes 9 are evenly distributed on the end of the connecting cylinder 1 away from the bellows 2, and multiple second bolt holes 11 are evenly distributed on the end of the connecting cylinder 1 near the bellows 2. A first screw 5 passes through the first bolt hole 9, and a second screw 6 passes through the second bolt hole 11, respectively, for bolting connection with the high-guide blade 14. By using bolt connection to connect with the high-guide blade, the structure is simple and the high-guide blade is easy to install.

[0039] Combination Figure 4 As shown, a stop ring 4 is provided on the outer circumferential surface of the connecting cylinder 1, and a second annular washer 17 is provided on the second screw 6. The second annular washer 17 is located in the area between the stop ring 4 and the bellows 2, and the outer circumferential surface of the second annular washer 17 abuts against the stop ring 4. By using the stop ring 4, the axial movement of the second screw 6 can be further limited, ensuring the relative position of the high-guide vane 14 with the connecting cylinder 1 under high-temperature working conditions.

[0040] Furthermore, a first annular washer 16 and a stop washer 15 are sequentially fitted onto the first screw 5. The end of the stop washer 15 near the bellows 2 is bent upwards and abuts against the first annular washer 16, while the end of the stop washer 15 away from the bellows 2 is bent downwards and extends downwards beyond the lower edge of the high guide vane 14 edge plate. By setting the first annular washer 16 and the stop washer 15, and using the bending structure at both ends of the stop washer 15 to form a limiting structure to limit the position of the first screw 5, the relative position of the high guide vane 14 and the connecting cylinder 1 is further guaranteed.

[0041] Combination Figure 2As shown, multiple third bolt holes 13 are evenly distributed on the connecting plate 3. The third bolt holes 13 facilitate bolt connection between the connecting plate 3 and the outer casing 12, making disassembly and assembly simple and convenient.

[0042] Combination Figure 3 , Figure 4 As shown, a plurality of first cooling air holes 7 are provided on the connecting cylinder 1. The shape of the first cooling air holes 7 is consistent with the shape of the inner cavity opening of the high-conductivity blade 14, and the first cooling air holes 7 are used to connect to the inner cavity A of the high-conductivity blade 14. Cooling gas can enter the inner cavity A of the high-conductivity blade 14 to cool the high-conductivity blade 14. The flow direction of the cooling gas is as follows: Figure 4 As indicated by the dashed arrow.

[0043] Furthermore, multiple second cooling air holes 8 are provided near the first cooling air hole 7 to cool the edge plates of the high-guide-rate blades. Multiple rows of third cooling air holes 10 are provided on the connecting cylinder 1 near the bellows 2. Cooling air can enter the gap between two adjacent high-guide-rate blades 14 to cool the blade body of the high-guide-rate blade 14.

[0044] As a second aspect, embodiments of the present invention also provide an aero-engine (not shown) with the aforementioned turbine guide vane fixing structure.

[0045] The above description is merely a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A fixing structure for a turbine guide, characterized in that, include: The connecting cylinder (1) is a hollow cylindrical structure with open ends, used to connect with the high-guide blades (14) on the turbine guide vane; The connecting plate (3) is in the shape of a ring and is used to connect with the outer casing (12); The bellows (2) has one end welded to the end of the connecting cylinder (1) and the other end welded to the inner ring surface of the connecting disc (3); Multiple first bolt holes (9) are evenly distributed on the end of the connecting cylinder (1) away from the bellows (2), and multiple second bolt holes (11) are evenly distributed on the end of the connecting cylinder (1) near the bellows (2); a first screw (5) is inserted into the first bolt hole (9), and a second screw (6) is inserted into the second bolt hole (11), which are used to bolt to the high guide vane (14); A stop ring (4) is provided on the outer peripheral surface of the connecting cylinder (1), and a second annular washer (17) is provided on the second screw (6). The second annular washer (17) is located in the area between the stop ring (4) and the bellows (2), and the outer peripheral surface of the second annular washer (17) abuts against the stop ring (4).

2. The fixing structure of a turbine guide as described in claim 1, characterized in that, The corrugated pipe (2) has an S-shaped cross-section.

3. The fixing structure of a turbine guide as described in claim 1, characterized in that, A first annular washer (16) and a stop washer (15) are sequentially fitted on the first screw (5). The end of the stop washer (15) near the bellows (2) is bent upward and abuts against the first annular washer (16). The end of the stop washer (15) away from the bellows (2) is bent downward and extends downward beyond the lower edge of the high guide vane (14) edge plate.

4. The fixing structure of a turbine guide as described in claim 1, characterized in that, Multiple third bolt holes (13) are evenly distributed on the connecting plate (3).

5. The fixing structure of a turbine guide as described in claim 1, characterized in that, A plurality of first cold air holes (7) are provided on the connecting cylinder (1). The shape of the first cold air holes (7) is consistent with the shape of the inner cavity opening of the high-conductivity blade (14), and the first cold air holes (7) are used to connect the inner cavity of the high-conductivity blade (14).

6. The fixing structure of a turbine guide as described in claim 5, characterized in that, Multiple second air vents (8) are also provided near the first air vent (7).

7. The fixing structure of a turbine guide as described in claim 1, characterized in that, Multiple rows of third air vents (10) are provided on the connecting cylinder (1) near the bellows (2).

8. An aircraft engine, characterized in that, Includes the fixing structure of the turbine guide as described in any one of claims 1 to 7.

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