Rotor disc back seal structure and aero-engine

Abstract

The application provides a rotor disc rear sealing structure and an aero-engine, and relates to the technical field of aero-engines.The rotor disc rear sealing structure comprises a rotor disc, a rear baffle and an inter-stage disc.The rotor disc comprises a tenon and a trailing edge plate arranged at the rear side of the tenon.A clamping protrusion is arranged below the trailing edge plate.The clamping protrusion is arranged in a spaced manner with the tenon, so that a clamping opening is formed between the clamping protrusion and the tenon.The radial outer end of the rear baffle is clamped and matched with the clamping opening, so that the radial outer end of the rear baffle is pressed on the tenon by the clamping protrusion to limit the radial outer end of the rear baffle.The radial inner end of the rear baffle is pressed against the tenon by the inter-stage disc, so that the axial deformation of the rear baffle is limited by the combined action of the clamping opening and the inter-stage disc, thereby reducing the risk of the rear baffle being separated from the rotor disc, and improving the problems of sealing failure and cold gas leakage caused by the separation of the sealing structure.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and more specifically, to a rotor disc rear sealing structure and an aero-engine. Background Technology

[0002] An aero-engine is a device that provides power for aviation activities; generally, it refers specifically to an aircraft engine. In an aero-engine, the rotor disk and the sealing structure behind it typically seal the airflow path of the moving blades, thereby reducing or controlling cold air leakage. This creates a sealing cavity behind the rotor disk sealing structure, which communicates with the main airflow path of the aero-engine. It should be noted that in the aero-engine structure, the forward / backward direction can be roughly determined according to the direction of the main airflow path. Specifically, the side closer to the direction of the main airflow path is the forward direction, and correspondingly, the side farther from the direction of the main airflow path is the rearward direction.

[0003] However, the existing rotor disc rear sealing structure is prone to detachment, which leads to sealing failure and cold air leakage. Summary of the Invention

[0004] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.

[0005] The purpose of this invention is to provide a rotor disc rear sealing structure that can improve the technical problem of easy detachment in the prior art, which leads to sealing failure and cold air leakage.

[0006] The present invention also aims to provide an aero engine that can improve the technical problem in the prior art where the rotor disc rear sealing structure is prone to detachment, leading to sealing failure and cold air leakage.

[0007] Embodiments of the present invention can be implemented in the following ways:

[0008] A rotor disc rear sealing structure, the rotor disc rear sealing structure comprising:

[0009] The rotor disk includes a tenon and a rear edge plate disposed behind the tenon, and a snap-fit ​​protrusion is provided below the rear edge plate; the snap-fit ​​protrusion is spaced apart from the tenon, and a locking groove is formed between the snap-fit ​​protrusion and the tenon;

[0010] A rear baffle, the radially outer end of which engages with the bayonet to press the radially outer end of the rear baffle against the tenon via the engaging protrusion; and

[0011] Interstage plate, the interstage plate being pressed against the radially inner end of the rear baffle to press the radially inner end of the rear baffle against the tenon.

[0012] Optionally, the snap-fit ​​protrusion has a first side surface for defining at least a portion of the bayonet, and the distance between the first side surface and the tenon decreases in a radially outward direction along the rear baffle.

[0013] Optionally, the first side surface is an inclined surface.

[0014] Optionally, the snap-fit ​​protrusion further has a second side surface for defining the portion of the snap-fit, the second side surface being disposed radially inside the first side surface, and the distance between the second side surface and the tenon remains constant along the radial direction of the rotor disk.

[0015] Optionally, the connection between the first side and the second side is smoothly transitioned by an arc surface.

[0016] Optionally, the rear baffle includes a plate body, the two axial side walls of the plate body being a first end face and a second end face, respectively. A first protrusion is provided at the radially outer end of the first end face, and the first protrusion protrudes in a direction away from the second end face. The side of the first protrusion away from the second end face engages with the tenon, and the radially outer end of the second end face engages with the snap-fit ​​protrusion. There is a gap between the first end face and the tenon.

[0017] Optionally, the rear baffle further includes a second protrusion disposed on the first end face, the second protrusion being spaced apart from the first protrusion and located radially inside the first protrusion; the second protrusion is interference-fitted with the tenon.

[0018] Optionally, the rear baffle has a bending structure at its radial inner end. The bending structure includes a first bending portion and a second bending portion connected to each other. The first bending portion bends towards the tenon along the axial direction of the rear baffle and abuts against the tenon. The second bending portion is located below the tenon and extends radially along the rear baffle.

[0019] Optionally, the interstage disc is pressed against the second bend along the axial direction of the rear baffle.

[0020] An aircraft engine comprising the aforementioned rotor disk back seal structure.

[0021] The beneficial effects of the rotor disk back seal structure and aero-engine provided by the embodiments of the present invention include:

[0022] An embodiment of the present invention provides a rotor disk rear sealing structure, which includes a rotor disk, a rear baffle, and an interstage disk. The rotor disk includes a tenon and a rear edge plate disposed behind the tenon, with a snap-fit ​​protrusion below the rear edge plate. The snap-fit ​​protrusion is spaced apart from the tenon, thus forming a locking slot between them. The radially outer end of the rear baffle engages with the locking slot, thereby pressing the radially outer end of the rear baffle against the tenon through the snap-fit ​​protrusion, thus limiting the radially outer end of the rear baffle. The interstage disk presses against the radially inner end of the rear baffle, pressing the radially inner end of the rear baffle towards the tenon. Thus, through the combined action of the locking slot and the interstage disk, the axial deformation of the rear baffle is limited, thereby reducing the risk of the rear baffle detaching from the rotor disk, and thus improving the problems of sealing failure and cold air leakage caused by the detachment of the sealing structure.

[0023] Embodiments of the present invention also provide an aero-engine including the aforementioned rotor disk rear sealing structure. Because this aero-engine includes the aforementioned rotor disk rear sealing structure, it also has the beneficial effect of reducing the risk of the rear baffle detaching from the rotor disk, thereby improving the problems of sealing failure and cold air leakage caused by sealing structure detachment. Attached Figure Description

[0024] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.

[0025] Figure 1 A schematic diagram of the rotor disk back seal structure provided according to one aspect of the present invention is shown;

[0026] Figure 2 It shows Figure 1 Enlarged schematic diagram of the local structure at point I;

[0027] Figure 3 An airflow diagram of a rotor disk back seal structure according to one aspect of the present invention is shown.

[0028] Figure label:

[0029] 100 - Rotor disc rear sealing structure; 110 - Rotor disc; 111 - Tenon; 112 - Rim; 113 - Rear edge plate; 114 - Snap-fit ​​protrusion; 116 - Bayonet; 117 - First side; 118 - Second side; 120 - Rear baffle; 121 - Plate body; 122 - Guide surface; 123 - First protrusion; 124 - Second protrusion; 125 - First end face; 126 - Second end face; 127 - First bend; 128 - Second bend; 130 - Interstage disc; 140 - Blade; 151 - First flow path; 152 - Second flow path; 153 - Leakage cavity; 154 - Sealing cavity; 161 - First sealing position; 162 - Second sealing position; 163 - Third sealing position. Detailed Implementation

[0030] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0031] In the description of this invention, it should be noted that if terms such as "upper," "lower," "inner," "outer," or "vertical" appear, the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of this invention is usually placed when in use, and does not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0032] At the same time, it should be noted that the terms "first" and "second" are used only for distinguishing descriptions and should not be interpreted as indicating or implying relative importance.

[0033] In the description of this invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, an integral connection, or a detachable connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or a connection within two components, etc. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0034] In current aero-engines, a sealing cavity is formed behind the rotor disk's rear sealing structure, while the cold airflow path is located in front of the rear sealing structure. The inventors discovered that during rapid engine speed reduction in aero-engines, the sealing cavity's temperature drops rapidly along with the engine's main airflow path, causing the sealing structure to cool down quickly. However, the temperature in the cold airflow path does not change significantly. This leads to the sealing structure being prone to axial deformation towards the sealing cavity, causing it to detach from the rotor disk and resulting in sealing failure.

[0035] To address the aforementioned problems, the inventors proposed a rotor disc rear sealing structure, which effectively improves these issues.

[0036] Figure 1 This is a schematic diagram of the rotor disk rear sealing structure 100 provided in this embodiment. Figure 2 for Figure 1 A magnified view of the local structure at point I. Please refer to the diagram. Figure 1 and Figure 2 This embodiment provides a rotor disk rear sealing structure 100, and also provides an aero engine (not shown in the figure).

[0037] The aero-engine includes the rotor disk and back seal structure 100, as well as conventional aero-engine structures such as moving blades and stationary blades.

[0038] The rotor disk rear sealing structure 100 includes a rotor disk 110, a rear baffle 120, and an interstage disk 130. The rotor disk 110 includes a tenon 111 and a rear edge plate 113 disposed behind the tenon 111. A locking protrusion 114 is provided below the rear edge plate 113. The locking protrusion 114 is spaced apart from the tenon 111, thus forming a notch 116 between the locking protrusion 114 and the tenon 111. The radially outer end of the rear baffle 120 engages with the notch 116, thereby pressing the radially outer end of the rear baffle 120 against the tenon 111 through the locking protrusion 114, thus limiting the radially outer end of the rear baffle 120. The interstage plate 130 is pressed against the radial inner end of the rear baffle 120 to press the radial inner end of the rear baffle 120 against the tenon 111. In this way, the axial deformation of the rear baffle 120 is restricted by the joint action of the latch 116 and the interstage plate 130, thereby reducing the risk of the rear baffle 120 detaching from the rotor plate 110. This can also improve the problem of sealing failure and cold air leakage caused by the detachment of the sealing structure.

[0039] It should be noted that the rear baffle 120 is a ring-shaped component, and its axial direction is as follows: Figure 1 The radial direction of direction A described in the text is as follows: Figure 1 The BC direction shown in the figure Figure 1 and Figure 2 The rear baffle 120 structure shown is only a portion of the cross-section of the rear baffle 120 structure obtained by the plane passing through the axis. In other words, the overall structure of the rear baffle 120 is as follows: Figure 1 The structure shown is formed by rotating the cross-sectional structure of the rear baffle 120 around its axis for one revolution. Specifically, direction B is the radially outward direction of the rear baffle 120, and direction C is the radially inward direction of the rear baffle 120.

[0040] In the description of this embodiment, "the radial outer end of the rear baffle" refers to the rear baffle 120 along... Figure 1 One end in the B direction; "the radial inner end of the rear baffle 120" is the end of the rear baffle 120 along the B direction. Figure 1 One end in the C direction.

[0041] Specifically, one end of the tenon 111 is provided with a rim 112, and the trailing edge plate 113 is the part of the rim 112 located behind the tenon 111. In other words, the trailing edge plate 113 can be a part of the integral rim 112. The aero-engine also includes blades 140, which are mounted on the tenon 111.

[0042] Please continue to refer to the reference. Figure 1 and Figure 2 In this embodiment, the snap-fit ​​protrusion 114 has a first side surface 117 that defines at least a portion of the snap-fit ​​opening 116, in a radially outward direction along the rear baffle 120 (i.e., as shown in the image). Figure 1 As shown in direction B), the distance between the first side 117 and the tenon 111 decreases, in other words, the opening size of the formed latch 116 decreases. Thus, when the radially outer end of the rear baffle 120 moves relative to the rotor disk 110 in the radially outward direction (direction B) (for example, during the operation of an aero engine, the rear baffle 120 expands, causing the radially outer end to extend upward), the clamping force applied by the latch 116 to the rear baffle 120 is greater. Therefore, the rear baffle 120 is less likely to experience axial (direction A) deformation and thus detach from the rotor disk 110. At the same time, the temperature of the rim 112 and the snap-fit ​​protrusion 114 provided thereon changes synchronously with that of the rear baffle 120, resulting in a large temperature difference at the wall stop, which ensures that the radially outer end of the rear baffle 120 can always be pressed against the rotor disk 110.

[0043] Optionally, the first side surface 117 is a slope. It is understood that in some other embodiments, the type of the first side surface 117 can also be specifically set, for example, the first side surface 117 can be set as a curved surface.

[0044] It should be noted that, in the description of this embodiment, "inclined surface" refers to a surface with a straight line shape obtained by intersecting the surface with a plane passing through the axis. It can be a plane obtained by stretching the cross-sectional shape along a straight line, or it can be a part of a conical surface obtained by stretching along the circumferential direction. Similarly, the "arc surface" mentioned above refers to a surface with an arc shape obtained by intersecting the cover surface with a plane passing through the axis.

[0045] Furthermore, the snap-fit ​​protrusion 114 also includes a second side surface 118 for defining the portion of the latch 116. The second side surface 118 is located radially inside the first side surface 117, that is, the second side surface 118 is located on one side of the first side surface 117 along the C direction. The distance between the second side surface 118 and the tenon 111 remains unchanged, that is, the second side surface 118 is parallel to the side of the tenon 111 used to define the latch 116. Thus, the opening size between the second side surface 118 and the tenon 111 is larger than the opening size between the first side surface 117 and the tenon 111. To ensure a reliable snap-fit ​​between the rear baffle 120 and the latch 116, the radially outer end of the rear baffle 120 and the latch 116 are fitted with an interference fit. The larger opening size formed by the second side surface 118 helps to achieve the snap-fit ​​installation of the rear baffle 120 and the latch 116.

[0046] Optionally, the connection between the first side 117 and the second side 118 is smoothly transitioned by an arc surface, which helps to reduce the radial outer end of the rear baffle 120 from the bayonet 116 portion corresponding to the second side 118 into the bayonet 116 portion corresponding to the first side 117.

[0047] Furthermore, a guide surface 122 is provided at the radial outer end of the rear baffle 120. By providing the guide surface 122, the axial dimension of the rear baffle 120 decreases along the B direction, which helps to insert the radial outer end of the rear baffle 120 into the bayonet 116.

[0048] Specifically, the rear baffle 120 has a plate 121, which has a first end face 125 and a second end face 126 arranged opposite to each other along the axial direction (direction A). The first end face 125 is the wall surface of the plate 121 on the side close to the tenon 111, and correspondingly, the second end face 126 is the wall surface of the plate 121 on the side away from the tenon 111.

[0049] In this embodiment, a first protrusion 123 is provided at the radially outer end of the first end face 125, and the first protrusion 123 protrudes in a direction away from the second end face 126. When the radially outer end of the rear baffle 120 engages with the latch 116, the side wall of the first protrusion 123 away from the second end face 126 engages with the tenon 111, and the radially outer end of the second end face 126 engages with the latching protrusion 114, as shown below. Figure 1 and Figure 2 In the state shown, the second end face 126 engages with the second side face 118 of the snap-fit ​​protrusion 114, and at this time, there is a gap between the first end face 125 and the tenon 111.

[0050] With the above structure, a first sealing position 161 is formed at the mating point of the first protrusion 123 and the tenon 111, and a second sealing position 162 is formed at the mating point of the second end face 126 and the snap-fit ​​protrusion 114. A leakage cavity 153 is formed between the first end face 125 and the tenon 111. Cold air entering the leakage cavity 153 must pass through the first sealing position 161 and the second sealing position 162 before it can leak into the sealing cavity 154, resulting in a good sealing effect.

[0051] Furthermore, the rear baffle 120 also includes a second protrusion 124 disposed on the first end face 125, the second protrusion 124 also being formed to protrude in a direction away from the second end face 126. The second protrusion 124 is spaced apart from the first protrusion 123, and the second protrusion 124 is located radially inside the first protrusion 123, that is, the second protrusion 124 is located on the side of the first protrusion 123 facing the C direction. The second protrusion 124 is interference-fitted with the tenon 111. By providing the second protrusion 124, on the one hand, the interaction force between the rear baffle 120 and the tenon 111 can be increased; on the other hand, the mating point of the second protrusion 124 and the tenon 111 forms a third sealing position 163. Thus, the cold air entering between the rear baffle 120 and the tenon 111 must pass through the third sealing position 163, the first sealing position 161 and the second sealing position 162 before leaking into the sealing cavity 154, reducing the possibility of leakage and further improving the sealing effect.

[0052] Figure 3 The diagram illustrates the airflow direction of the rotor disk rear sealing structure 100 provided in this embodiment. Specifically, as shown... Figure 3 As shown, the cold airflow path is divided into two paths at the tenon 111. These two airflow paths are the first flow path 151 and the second flow path 152. The first flow path 151 is the cooling flow path entering the blade 140. The second flow path 152 passes through the leakage cavity 153 between the rear baffle 120 and the tenon 111. By setting the structure of the rear baffle 120, the flow resistance is increased, thereby further reducing the leakage and helping to ensure the cooling airflow of the blade 140.

[0053] It should be noted that in this embodiment, the number of the second protrusion 124 is set to one. It is understood that in some other embodiments, the number of the second protrusion 124 can also be set according to the requirements, such as setting the number of the second protrusion 124 to two, and the two second protrusions 124 are distributed radially at intervals along the rear baffle 120.

[0054] Please refer to the reference. Figures 1-3In this embodiment, the radially inner end of the rear baffle 120 is provided with a bending structure, which includes a first bending portion 127 and a second bending portion 128 connected to each other. The first bending portion 127 bends along the axial direction of the rear baffle 120 toward the tenon 111, and the first bending portion 127 abuts against the tenon 111, thereby limiting the relative position between the radially inner end of the rear baffle 120 and the tenon 111. The second bending portion 128 is located below the tenon 111 and extends radially along the rear baffle 120.

[0055] Specifically, one end of the first bent portion 127 along the axial direction of the rear baffle 120 is fixedly connected to the plate body 121, and the other end of the second bent portion 128 along the axial direction of the rear baffle 120 is connected to the plate body 121. The plate body 121 and the second bent portion 128 are parallel to each other and extend in opposite directions. The first bent portion 127 forms a stepped structure, and the relative position of the radial inner end of the rear baffle 120 and the tenon 111 is limited by the cooperation of this stepped structure with the tenon 111.

[0056] Furthermore, the interstage plate 130 abuts against the second bend 128, and applies an axial clamping force along the rear baffle 120 to the second bend 128 via the interstage plate 130, thereby ensuring the reliable fit between the radially inner end of the rear baffle 120 and the tenon 111. The combined action of the interstage plate 130 and the latch 116 effectively reduces the risk of axial deformation of the rear baffle 120, thus contributing to ensuring the reliability of the seal.

[0057] The rotor disc rear sealing structure 100 and aero-engine provided in this embodiment of the invention, through the setting of the rear baffle 120 and the bayonet 116, effectively limit the axial deformation of the baffle by relying on the cooperation between the bayonet 116 and the rear baffle 120, thereby reducing the risk of detachment and improving the sealing reliability. At the same time, during the rapid descent of the aero-engine, the temperature of the wheel rim 112 and the rear baffle 120 changes synchronously, thereby avoiding the generation of a large temperature difference at the bayonet 116, so that the baffle is always pressed against the disc. Moreover, the rotor disc rear sealing structure 100 provided in this embodiment also has the advantages of simple structure, which is conducive to the application in aero-engines, and high leakage flow resistance, which can reduce the leakage amount.

[0058] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A rotor disk disk aft seal structure, characterized by: The rotor disc rear sealing structure comprises: a rotor disc comprising a tenon and a rear edge plate arranged at the rear side of the tenon, a clamping protrusion being arranged below the rear edge plate, the clamping protrusion being arranged in a spaced manner with the tenon, and a clamping opening being formed between the clamping protrusion and the tenon; a rear baffle, a radially outer end of the rear baffle being clamped and matched with the clamping opening, so as to press the radially outer end of the rear baffle on the tenon through the clamping protrusion, the rear baffle being used to form a sealing structure with the rotor disc; and an inter-stage disc, the inter-stage disc being pressed on a radially inner end of the rear baffle, so as to press the radially inner end of the rear baffle towards the tenon. The clamping protrusion has a first side surface for defining at least part of the clamping opening, the distance between the first side surface and the tenon decreasing in a radially outward direction of the rear baffle, so as to increase the clamping force applied by the clamping opening on the rear baffle when the rear baffle is expanded and elongated in a radially outward direction, and avoid axial deformation of the rear baffle.

2. The rotor disc rear sealing structure according to claim 1, wherein: the first side surface is a bevel.

3. The rotor disc rear sealing structure according to claim 1, wherein: the clamping protrusion further has a second side surface for defining part of the clamping opening, the second side surface being arranged at a radially inner side of the first side surface, and the distance between the second side surface and the tenon being constant in a radial direction of the rotor disc.

4. The rotor disc rear sealing structure according to claim 3, wherein: a connection between the first side surface and the second side surface is smoothly connected through a curved surface.

5. The rotor disc rear sealing structure according to claim 1, wherein: the rear baffle comprises a plate body, axially opposite wall surfaces of the plate body are respectively a first end surface and a second end surface, a radially outer end of the first end surface is provided with a first protruding part, the first protruding part protruding towards a direction away from the second end surface, a side of the first protruding part away from the second end surface is matched with the tenon, a radially outer end of the second end surface is matched with the clamping protrusion, and the first end surface is spaced apart from the tenon.

6. The rotor disc rear sealing structure according to claim 5, wherein: the rear baffle further comprises a second protruding part arranged on the first end surface, the second protruding part is distributed in a spaced manner with the first protruding part, and the second protruding part is located at a radially inner side of the first protruding part, and the second protruding part is matched with the tenon in an interference manner.

7. The rotor disc rear sealing structure according to claim 1, wherein: a radially inner end of the rear baffle is provided with a bending structure, the bending structure comprises a first bending part and a second bending part connected with each other, the first bending part is bent towards the tenon in an axial direction of the rear baffle, and the first bending part is in abutment with the tenon, and the second bending part is located below the tenon, and the second bending part extends in a radial direction of the rear baffle.

8. The rotor disc rear sealing structure according to claim 7, wherein: the inter-stage disc is pressed on the second bending part in an axial direction of the rear baffle.

9. An aeroengine characterised in that: the aeroengine comprises a disc- aft seal of any one of claims 1 to 8.

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