An aero-engine turbine stator case sealing structure

Abstract

The application belongs to the technical field of the seal design of the stator casing of an aero-engine, and particularly relates to a seal structure of the turbine stator casing of an aero-engine, which comprises a whole ring structure formed by a plurality of support pieces, and utilizes a corrugated structure to tightly press the seal pieces in a whole circle, seals the axial gap between the front casing and the rear casing, and can press the seal pieces forward when the relative position of the casing changes due to the temperature load and the aerodynamic seal is insufficient, so that the effectiveness of the seal structure is ensured.

Description

Technical Field

[0001] This application belongs to the field of aero-engine stator casing sealing technology, specifically relating to an aero-engine turbine stator casing sealing structure. Background Technology

[0002] The gaps between the stator casings of aero engines can cause gas leakage, affecting engine efficiency. Therefore, a sealing structure is typically designed between the stator casings, and a sealing gas is used to seal the gaps to prevent gas leakage. Common sealing structures use sealing plates or sealing rings, which overlap axially between the stator casings. Sealing rings have high structural requirements, while sealing plates have a wide range of applications but require a dedicated sealing plate fixing structure.

[0003] The sealing position of the turbine stator casing in an aero-engine is affected by temperature loads, causing relative axial movement between the casings. The sealing structure must move with the relative axial deformation of adjacent casings to ensure sealing effectiveness. Currently, turbine stator casing sealing structures often use pins to fix the sealing plates, and some use spring clamps or other methods to tighten the sealing plates locally against the stator casing. This results in insufficient sealing adhesion and a risk of gas leakage.

[0004] In view of the aforementioned technical deficiencies, this application is hereby filed. Summary of the Invention

[0005] The purpose of this application is to provide a sealing structure for the turbine stator casing of an aero-engine to overcome or mitigate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] A turbine stator casing sealing structure for an aero-engine includes a front casing and a rear casing arranged along the axial direction, and is equipped with pins, support plates, and sealing plates;

[0008] The front casing has a ring structure, and the rear end is provided with a front casing flange. The outer edge of the front casing flange has a rearward folded edge.

[0009] The rear casing has a ring structure with a rear casing flange at the front end. An annular groove is provided on the rear casing flange. The height of the front wall of the annular groove is less than the height of the rear wall and less than the height of the front casing flange, and it is located inside the rear fold.

[0010] There are multiple pins, which are arranged circumferentially on the rear wall of the annular groove;

[0011] There are multiple support plates, which are corrugated and fan-shaped, and are set in an annular groove. Each support plate is fitted onto the pin with multiple through holes, and the support plates together form an annular structure.

[0012] There are multiple sealing plates, which are fan-shaped and set in an annular groove. Each sealing plate is fitted onto the pin with multiple through holes, and the sealing plates together form an annular structure.

[0013] Each support piece is supported between each sealing piece and the rear wall of the annular groove, with the sealing piece pressing against the front wall and the rearward folded edge of the annular groove.

[0014] According to at least one embodiment of this application, in the above-mentioned sealing structure of the turbine stator casing of the aero-engine, the various support plates and sealing plates form a sealing air chamber. When the aero-engine is operating in a steady state, sealing gas is introduced into the sealing air chamber and acts on the sealing plates in the axial direction. At the same time, the flow channel gas in the front casing and the rear casing acts on the sealing plates in the axial direction through the gap between the front casing and the rear casing. The sealing gas pressure is greater than the flow channel gas pressure, and each sealing plate remains attached to the front wall and the rearward folded edge of the annular groove.

[0015] According to at least one embodiment of this application, in the above-described turbine stator casing sealing structure of the aero-engine, during the transitional operation of the aero-engine, the front casing and the rear casing undergo relative axial displacement, the sealing gas pressure is lower than the flow channel gas pressure, and under the elastic support of each support plate, each sealing plate abuts against the front wall and rear folded edge of the annular groove.

[0016] According to at least one embodiment of this application, in the above-described sealing structure of the turbine stator casing of an aero-engine, there is a small gap between adjacent support plates;

[0017] There is a small gap between adjacent sealing plates, and this small gap is no larger than the small gap between adjacent support plates.

[0018] According to at least one embodiment of this application, in the above-described sealing structure of the turbine stator casing of an aero-engine, the small gaps between the sealing plates and the small gaps between the supporting plates are staggered in the circumferential direction.

[0019] According to at least one embodiment of this application, in the above-described sealing structure of the turbine stator casing of an aero-engine, each pin is welded or riveted to the rear wall of the annular groove.

[0020] This application has at least the following beneficial technical effects:

[0021] A sealing structure for the turbine stator casing of an aero-engine is provided, which consists of multiple support plates forming a complete ring structure. The corrugated structure is used to tighten the sealing plates around the entire ring, sealing the axial gap between the front and rear casings. When the relative position of the casing changes due to temperature load or when the aerodynamic sealing is insufficient, the sealing plates can be pushed forward to ensure the effectiveness of the sealing structure. Attached Figure Description

[0022] Figure 1This is a schematic diagram of the turbine stator casing sealing structure of an aero-engine provided in an embodiment of this application;

[0023] Figure 2 This is a schematic diagram of the support sheet provided in an embodiment of this application;

[0024] Figure 3 This is a schematic diagram of the sealing sheet provided in an embodiment of this application;

[0025] in:

[0026] 1-Front casing; 2-Rear casing; 3-Pin; 4-Support plate; 5-Sealing plate; 6-Sealing gas; 7-Flow channel gas.

[0027] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0028] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0029] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0030] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0031] A turbine stator casing sealing structure for an aero-engine, such as Figure 1 As shown, it includes a front casing 1 and a rear casing 2 arranged along the axial direction, and is equipped with a pin 3, a support plate 4, and a sealing plate 5.

[0032] The front casing 1 has a ring structure, and the rear end is provided with a front casing flange. The outer edge of the front casing flange has a rearward folded edge.

[0033] The rear casing 2 has a ring structure with a rear casing flange at the front end. An annular groove is provided on the rear casing flange. The height of the front wall of the annular groove is less than the height of the rear wall and less than the height of the front casing flange, and it is located inside the rear fold.

[0034] There are multiple pins 3, which are arranged circumferentially on the rear wall of the annular groove and are welded or riveted to the rear wall of the annular groove.

[0035] There are multiple support plates 4, which are corrugated plates, such as... Figure 2 As shown, the support plates are fan-shaped and set within an annular groove. Each support plate 4 is fitted onto the pin 3 with multiple through holes. The through holes can be opened at the crest of the support plate 4 for radial and circumferential limiting. All the support plates 4 together form an annular structure, with small gaps between adjacent support plates 4. The specific size can be designed according to the circumferential extension requirements of the support plates to facilitate assembly and disassembly.

[0036] There are multiple sealing plates 5, arranged in a fan shape, such as... Figure 3 As shown, each sealing piece 5 is fitted onto the pin 3 with multiple through holes in the annular groove for radial and circumferential positioning. The sealing pieces 5 together form an annular structure, and there is a small gap between adjacent sealing pieces 5. This small gap is no larger than the small gap between adjacent support pieces 4.

[0037] Each support piece 4 is supported between each sealing piece 5 and the rear wall of the annular groove, and the sealing piece 5 is pressed against the front wall and the rear folded edge of the annular groove. That is, relying on the elastic force of the corrugated structure, each sealing piece 5 is pressed against the front wall and the rear folded edge of the annular groove, forming a seal between the front casing 1 and the rear casing 2.

[0038] Each support plate 4 and sealing plate 5 forms a sealing air chamber. When the aero-engine is operating in a steady state, sealing gas 6 is introduced into the sealing air chamber and acts on the sealing plate 5 axially forward. At the same time, the flow channel gas 7 in the front casing 1 and the rear casing 2 acts on the sealing plate 5 axially backward through the gap between the front casing 1 and the rear casing 2. Since the sealing gas pressure is greater than the flow channel gas pressure, each sealing plate 5 will reliably remain against the front wall and the rearward folded edge of the annular groove, ensuring the sealing effect between the front casing 1 and the rear casing 2 and preventing gas leakage.

[0039] During the transitional operation of the aero-engine, the front casing 1 and the rear casing 2 undergo relative axial displacement. At the same time, the pressure of the sealing gas 6 will be lower than that of the flow channel gas 7. However, due to the elastic support of each support plate 4, each sealing plate 5 will abut against the front wall and rear folded edge of the annular groove to ensure the sealing between the front casing 1 and the rear casing 2 and reduce gas leakage.

[0040] The small gaps between each sealing plate 5 and the small gaps between each support plate 4 are staggered in the circumferential direction to ensure the sealing effect between the front casing 1 and the rear casing 2.

[0041] The turbine stator casing sealing structure of the aero-engine disclosed in the above embodiments uses multiple support plates 4 to form a complete ring structure. A corrugated structure is used to tighten the sealing plate 5 around the entire ring, providing a better tightening effect than structures with evenly distributed angular springs or clips. This seals the axial gap between the front casing 1 and the rear casing 2. Even when temperature loads cause relative positional changes in the casings or when aerodynamic sealing is insufficient, the sealing plate 5 can be pushed forward to ensure the effectiveness of the sealing structure. Furthermore, the structure is simple, and the fan-shaped support plates 4 and sealing plates 5 facilitate installation, disassembly, repair, and maintenance.

[0042] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A sealing structure for a turbine stator casing of an aero-engine, characterized in that, It includes a front casing (1) and a rear casing (2) arranged along the axial direction, and is equipped with pins (3), support plates (4) and sealing plates (5); The front casing (1) is a ring structure, and the rear end is provided with a front casing flange. The outer edge of the front casing flange has a rearward folded edge. The rear casing (2) is a ring structure. The front end is provided with a rear casing flange. An annular groove is provided on the rear casing flange. The height of the front wall of the annular groove is less than the height of the rear wall and less than the height of the front casing flange, and it is located inside the rear fold. There are multiple pins (3), which are arranged circumferentially on the rear wall of the annular groove; There are multiple support plates (4), which are corrugated plates in the shape of a fan and are set in an annular groove. Each support plate (4) is fitted onto the pin (3) with multiple through holes. All the support plates (4) together form an annular structure. There are multiple sealing plates (5), which are fan-shaped and set in an annular groove. Each sealing plate (5) is fitted onto the pin (3) with multiple through holes. All sealing plates (5) together form an annular structure. Each support piece (4) is supported between each sealing piece (5) and the rear wall of the annular groove, and the sealing piece (5) is pressed against the front wall and the rear folded edge of the annular groove.

2. The sealing structure of the turbine stator casing of an aero-engine according to claim 1, characterized in that, Each support plate (4) and sealing plate (5) forms a sealing air chamber. When the aero-engine is in steady state, sealing gas (6) is introduced into the sealing air chamber and acts on the sealing plate (5) in the axial direction. At the same time, the flow channel gas (7) in the front casing (1) and rear casing (2) acts on the sealing plate (5) in the axial direction through the gap between the front casing (1) and rear casing (2). The pressure of sealing gas (6) is greater than the pressure of flow channel gas (7). Each sealing plate (5) remains attached to the front wall and rearward fold of the annular groove.

3. The turbine stator casing sealing structure for an aero-engine according to claim 2, characterized in that, When the aero-engine is in transitional operation, the front casing (1) and the rear casing (2) undergo relative axial displacement. The pressure of the sealing gas (6) is lower than that of the flow channel gas (7). Under the elastic support of each support plate (4), each sealing plate (5) abuts against the front wall and rear fold of the annular groove.

4. The turbine stator casing sealing structure for an aero-engine according to claim 3, characterized in that, There is a small gap between adjacent support plates (4); There is a small gap between adjacent sealing plates (5), and this small gap is no larger than the small gap between adjacent support plates (4).

5. The turbine stator casing sealing structure for an aero-engine according to claim 4, characterized in that, The small gaps between each sealing piece (5) and the small gaps between each supporting piece (4) are staggered in the circumferential direction.

6. The sealing structure of the turbine stator casing of an aero-engine according to claim 5, characterized in that, Each pin (3) is welded or riveted to the rear wall of the annular groove.

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