Rotor disc rear sealing structure and aero-engine

Abstract

The invention 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 interstage disc. The rotor disc comprises a tenon and a rear edge plate arranged on the rear side of the tenon, and a clamping protrusion is arranged below the rear edge plate. And the clamping bulges and the tenons are arranged at intervals, so that bayonets are formed between the clamping bulges and the tenons. The radial outer end of the rear baffle is matched with the clamping opening in a clamping mode, so that the radial outer end of the rear baffle is pressed on the tenon through the clamping protrusion, and limiting of the radial outer end of the rear baffle is achieved. The interstage disc is tightly pressed at the radial inner end of the rear baffle so as to press the radial inner end of the rear baffle towards the tenon, so that the axial deformation of the rear baffle is limited through the combined action of the bayonet and the interstage disc, and the risk that the rear baffle is separated from the rotor disc can be further reduced; and therefore, the problems of sealing failure and cold air leakage caused by disengagement of the sealing structure can be solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to a rotor disc rear sealing structure and an aero-engine. Background Art

[0002] An aircraft engine is a device that provides power for aviation activities. Generally, an aircraft engine refers to an aircraft engine in particular. In an aircraft engine, generally, the engine rotor disk and the sealing structure behind the rotor disk play a role in sealing the cold air flow path of the moving blades, thereby reducing or controlling cold air leakage. In this way, a sealing cavity is formed on the rear side of the sealing structure behind the rotor disk, and the sealing cavity is connected to the mainstream flow path of the aircraft engine. It should be noted that in the structure of the aircraft engine, the front and rear directions can be roughly determined according to the flow direction of the mainstream flow path of the aircraft engine. Specifically, the side close to the flow direction of the mainstream flow path of the aircraft engine is the front, and correspondingly, the side away from the flow direction of the mainstream flow path of the aircraft engine is the rear.

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

[0004] A brief summary of one or more aspects is given below to provide a basic understanding of these aspects. This summary is not an exhaustive overview of all conceived aspects, and is neither intended to identify the key or critical elements of all aspects nor to define the scope of any or all aspects. Its only purpose is to give some concepts of one or more aspects in a simplified form as a prelude to a more detailed description that will be given later.

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

[0006] Another object of the present invention is to provide an aircraft engine that can improve the technical problem in the prior art that the sealing structure behind the rotor disk is prone to detachment, which in turn leads to sealing failure and cold air leakage.

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

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

[0009] A rotor disk, the rotor disk comprising a tenon and a trailing edge plate arranged at the rear side of the tenon, a clamping protrusion being arranged below the trailing edge plate; the clamping protrusion being arranged at a distance from the tenon, and a clamping notch being formed between the clamping protrusion and the tenon;

[0010] a rear baffle, wherein the radial outer end of the rear baffle is engaged with the bayonet, so that the radial outer end of the rear baffle is pressed against the tenon through the engaging protrusion; and

[0011] An interstage disc is pressed against the radial inner end of the rear baffle to press the radial inner end of the rear baffle toward the tenon.

[0012] Optionally, the locking protrusion has a first side surface for defining at least a portion of the locking slot, and the distance between the first side surface and the tenon decreases along the radial outward direction of the rear baffle.

[0013] Optionally, the first side surface is a slope.

[0014] Optionally, the locking protrusion further has a second side surface for defining a portion of the locking hole, the second side surface is arranged radially inside the first side surface, and along the radial direction of the rotor disk, the distance between the second side surface and the tenon is constant.

[0015] Optionally, the connection between the first side surface and the second side surface is smoothly transitioned through a curved surface.

[0016] Optionally, the rear baffle includes a plate body, and the axial side walls of the plate body are respectively a first end face and a second end face, the radial outer end of the first end face is provided with a first protrusion, 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 cooperates with the tenon, and the radial outer end of the second end face cooperates with the snap-in 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 surface, the second protrusion being spaced apart from the first protrusion and being located radially inward of the first protrusion; the second protrusion is interference fit with the tenon.

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

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

[0020] An aircraft engine comprises the above-mentioned rotor disk rear sealing structure.

[0021] The rotor disc rear sealing structure and the aircraft engine provided by the embodiments of the present invention have the following beneficial effects:

[0022] An embodiment of the present invention provides a rear sealing structure of a rotor disk, which includes a rotor disk, a rear baffle and an interstage disk. The rotor disk includes a tenon and a rear edge plate arranged at the rear side of the tenon, and a snap-in protrusion is arranged below the rear edge plate. The snap-in protrusion is arranged at an interval from the tenon, so that a snap-in notch is formed between the snap-in protrusion and the tenon. The radial outer end of the rear baffle is snap-fitted with the snap-in notch, so that the radial outer end of the rear baffle is pressed against the tenon through the snap-in protrusion, thereby achieving the limitation of the radial outer end of the rear baffle. The interstage disk is pressed against the radial inner end of the rear baffle to press the radial inner end of the rear baffle toward the tenon, so that the axial deformation of the rear baffle is limited through the joint action of the snap-in notch and the interstage disk, thereby 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 the detachment of the sealing structure.

[0023] The embodiment of the present invention further provides an aircraft engine, which includes the above-mentioned rotor disk rear sealing structure. Since the aircraft engine includes the above-mentioned rotor disk rear sealing structure, it also has the beneficial effect of reducing the risk of the rear baffle being detached from the rotor disk, thereby also being able to improve the problem of sealing failure and cold air leakage caused by the detachment of the sealing structure. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0025] Figure 1 It shows a schematic structural diagram of a rotor disk rear sealing structure provided according to one aspect of the present invention;

[0026] Figure 2 Shows Figure 1 The enlarged schematic diagram of the local structure at position Ⅰ in the middle;

[0027] Figure 3 The figure shows the airflow direction diagram of the rotor disk rear sealing structure provided according to one aspect of the present invention.

[0028] Reference numerals:

[0029] 100-rotor disc rear sealing structure; 110-rotor disc; 111-tenon; 112-wheel rim; 113-trailing edge plate; 114-clamping protrusion; 116-bayonet; 117-first side; 118-second side; 120-rear baffle; 121-plate body; 122-guide surface; 123-first convex portion; 124-second convex portion; 125-first end face; 126-second end face; 127-first bending portion; 128-second bending portion; 130-interstage disc; 140-blade; 151-first flow path; 152-second flow path; 153-leakage chamber; 154-sealing chamber; 161-first sealing position; 162-second sealing position; 163-third sealing position. DETAILED DESCRIPTION

[0030] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. Note that the aspects described below in conjunction with the accompanying drawings and specific embodiments are only exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0031] In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", "vertical" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the product of the invention is usually placed when used, rather than indicating or implying that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

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

[0033] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified or limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, an integral 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, or the internal communication of two components, etc. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0034] In current aircraft engines, a sealing cavity is formed on the rear side of the sealing structure behind the rotor disk, and the cold air flow path is located on the front side of the sealing structure behind the rotor disk. The inventors have found that during the rapid deceleration of the aircraft engine, the sealing cavity rapidly decreases along with the temperature of the mainstream flow path of the aircraft engine, thereby rapidly cooling the sealing structure, while the temperature in the cold air flow path does not change significantly, which causes the sealing structure to easily deform axially toward the sealing cavity, thereby detaching from the rotor disk, resulting in sealing failure.

[0035] In order to improve the above problems, the inventors proposed a rotor disk rear sealing structure, which can effectively improve the above problems.

[0036] Figure 1 The schematic diagram of the structure of the rotor disk rear sealing structure 100 provided in this embodiment is as follows: Figure 2 for Figure 1 The enlarged schematic diagram of the local structure at position Ⅰ in the middle. Please refer to Figure 1 and Figure 2 This embodiment provides a rotor disk rear sealing structure 100, and also provides an aircraft engine (not shown).

[0037] The aircraft engine includes a rotor disk rear sealing structure 100, and also includes conventional aircraft engine structures such as moving blades and stationary blades.

[0038] The rotor disc rear sealing structure 100 includes a rotor disc 110, a rear baffle 120 and an interstage disc 130. The rotor disc 110 includes a tenon 111 and a rear edge plate 113 arranged at the rear side of the tenon 111, and a clamping protrusion 114 is arranged below the rear edge plate 113. The clamping protrusion 114 is arranged at a distance from the tenon 111, so that a clamping opening 115 is formed between the clamping protrusion 114 and the tenon 111. The radial outer end of the rear baffle 120 is clamped and matched with the clamping opening 115, so that the radial outer end of the rear baffle 120 is pressed against the tenon 111 by the clamping protrusion 114, so that the radial outer end of the rear baffle 120 is limited. The interstage disk 130 is pressed against the radial inner end of the rear baffle 120 to press the radial inner end of the rear baffle 120 toward the tenon 111, so that the axial deformation of the rear baffle 120 is limited through the joint action of the bayonet 115 and the interstage disk 130, thereby reducing the risk of the rear baffle 120 detaching from the rotor disk 110, thereby improving the problems 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 an annular member, and its axial direction is as follows: Figure 1 The A direction described in the figure has a radial direction as follows: Figure 1 The BC direction shown in Figure 1 and Figure 2 The structure of the tailgate 120 shown in FIG. 1 is only a portion of the cross section of the tailgate 120 structure cut through the plane of the axis. In other words, the overall structure of the tailgate 120 is as follows: Figure 1 The cross-sectional structure of the rear baffle 120 shown in FIG is a structure formed by rotating one circle around the axis of the rear baffle 120 . Specifically, the B direction is the direction pointing to the radial outside of the rear baffle 120 , and the C direction is the direction pointing to the radial inside of the rear baffle 120 .

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

[0041] Specifically, a rim 112 is disposed at one end of the tenon 111, and the trailing edge plate 113 is the portion of the rim 112 located behind the tenon 111. In other words, the trailing edge plate 113 may be a portion of the integrated rim 112. The aircraft engine further includes a blade 140, which is mounted on the tenon 111.

[0042] Please continue to refer to Figure 1 and Figure 2 In this embodiment, the snap-fit ​​protrusion 114 has a first side surface 117 that defines at least part of the snap-fit ​​opening 115, and extends radially outward from the rear baffle 120 (ie, as shown in FIG. 1 ). Figure 1 In other words, the opening size of the bayonet 115 is gradually reduced, so that when the radial 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 the aircraft engine, the rear baffle 120 expands so that the radial outer end extends upward), the greater the clamping force applied by the bayonet 115 to the rear baffle 120, the less likely the rear baffle 120 will deform axially (direction A) and then detach from the rotor disk 110. At the same time, the temperature of the rim 112 and the clamping protrusion 114 provided thereon is in synchronous change with that of the rear baffle 120, so that a large temperature difference occurs at the wall stop, so that the radial outer end of the rear baffle 120 can always be in a pressed state with the rotor disk 110.

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

[0044] It should be noted that, in the description of this embodiment, "inclined surface" refers to a surface whose shape is a straight line when intercepted by a plane passing through the axis line. 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 whose shape is an arc when intercepted by a plane passing through the axis line.

[0045] Furthermore, the snap-fitting protrusion 114 further includes a second side surface 118 for defining a portion of the snap-fitting hole 115, and the second side surface 118 is disposed radially inward of the first side surface 117, that is, the second side surface 118 is disposed 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 surface of the tenon 111 for defining the snap-fitting hole 115. 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. In order to ensure the secure snap-fitting degree between the rear baffle 120 and the snap-fitting hole 115, the radial outer end of the rear baffle 120 and the snap-fitting hole 115 are interference-fitted, and the larger opening size formed by the second side surface 118 helps to realize the snap-fitting installation of the rear baffle 120 and the snap-fitting hole 115.

[0046] Optionally, the connection between the first side surface 117 and the second side surface 118 is smoothly transitioned through an arc surface, which helps to reduce the radial outer end of the rear baffle 120 extending from the portion of the bayonet 115 corresponding to the second side surface 118 into the portion of the bayonet 115 corresponding to the first side surface 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 is gradually reduced along the B direction, thereby facilitating the insertion of the radial outer end of the rear baffle 120 into the bayonet 115 .

[0048] Specifically, the rear baffle 120 has a plate body 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 body 121 close to the tenon 111, and correspondingly, the second end face 126 is the wall surface of the plate body 121 away from the tenon 111.

[0049] In this embodiment, the radial outer end of the first end surface 125 is provided with a first protrusion 123, and the first protrusion 123 protrudes in a direction away from the second end surface 126. When the radial outer end of the rear baffle 120 is engaged with the bayonet 115, the side wall of the first protrusion 123 away from the second end surface 126 is engaged with the tenon 111, and the radial outer end of the second end surface 126 is engaged with the engaging protrusion 114. Figure 1 and Figure 2 In the state shown, the second end surface 126 is matched with the second side surface 118 of the locking protrusion 114 , and at this time, there is a gap between the first end surface 125 and the tenon 111 .

[0050] Through the above structure, a first sealing position 161 is formed at the cooperation between the first protrusion 123 and the tenon 111, and a second sealing position 162 is formed at the cooperation between the second end surface 126 and the clamping protrusion 114. A leakage cavity 153 is formed between the first end surface 125 and the tenon 111, and the cold air entering the leakage cavity 153 needs to pass through the first sealing position 161 and the second sealing position 162 before leaking into the sealing cavity 154, and the sealing effect is good.

[0051] Further, the rear baffle 120 also includes a second protrusion 124 disposed on the first end surface 125, and the second protrusion 124 is also formed to protrude in a direction away from the second end surface 126. The second protrusion 124 is spaced apart from the first protrusion 123, and the second protrusion 124 is located on the radial inner side of 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 improved, and on the other hand, the third sealing position 163 is formed at the matching position of the second protrusion 124 and the tenon 111, so that the cold air entering between the rear baffle 120 and the tenon 111 needs to 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, and the possibility of leakage is small, which further improves the sealing effect.

[0052] Figure 3 FIG. 1 shows the airflow direction diagram of the rotor disk rear sealing structure 100 provided in this embodiment. Specifically, Figure 3 As shown, the cold air flow path is divided into two paths at the tenon 111, and the two air flows are divided into a first flow path 151 and a second flow path 152. The first flow path 151 is a cooling flow path entering the blade 140, and the second flow path 152 passes through a 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, which helps to ensure the cooling air flow of the blade 140.

[0053] It should be noted that in the present embodiment, the number of the second protrusions 124 is set to one. It is understandable that in some other embodiments, the number of the second protrusions 124 can also be set specifically according to needs, for example, the number of the second protrusions 124 is set to two, and the two second protrusions 124 are distributed radially at intervals along the rear baffle 120.

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

[0056] Furthermore, the interstage disc 130 abuts against the second bent portion 128, and applies a pressing force along the axial direction of the rear baffle 120 to the second bent portion 128 through the interstage disc 130, thereby ensuring the reliability of the matching between the radial inner end of the rear baffle 120 and the tenon 111. Under the joint action of the interstage disc 130 and the bayonet 115, the risk of axial deformation of the rear baffle 120 is effectively reduced, thereby helping to ensure the reliability of the sealing.

[0057] The rotor disc rear sealing structure 100 and the aircraft engine provided by the embodiment of the present invention, by setting the rear baffle 120 and the bayonet 115, rely on the cooperation between the bayonet 115 and the rear baffle 120 to effectively limit the axial deformation of the baffle, thereby reducing the risk of disengagement and improving the sealing reliability. At the same time, during the rapid drop of the aircraft engine, the temperature of the rim 112 and the rear baffle 120 changes synchronously, thereby avoiding the generation of a large temperature difference at the bayonet 115, so that the baffle is always in a compressed state with the disc. Moreover, the rotor disc rear sealing structure 100 provided by this embodiment also has a simple structure, which is conducive to the application in aircraft engines, and at the same time has a large leakage flow resistance and can reduce the leakage amount.

[0058] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technology in the field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A rotor disc rear sealing structure, characterized in that: The rotor disc rear sealing structure comprises: A rotor disk, the rotor disk comprising a tenon and a trailing edge plate arranged at the rear side of the tenon, a clamping protrusion being arranged below the trailing edge plate; the clamping protrusion being arranged at a distance from the tenon, and a clamping notch being formed between the clamping protrusion and the tenon; a rear baffle, wherein the radial outer end of the rear baffle is engaged with the bayonet, so that the radial outer end of the rear baffle is pressed against the tenon through the engaging protrusion; and An interstage disc is pressed against the radial inner end of the rear baffle to press the radial inner end of the rear baffle toward the tenon.

2. The rotor disk rear sealing structure according to claim 1 is characterized in that: The locking protrusion has a first side surface for defining at least a portion of the locking opening, and a distance between the first side surface and the tenon gradually decreases along a radially outward direction of the rear baffle.

3. The rotor disk rear sealing structure according to claim 2 is characterized in that: The first side surface is an inclined surface.

4. The rotor disk rear sealing structure according to claim 2 is characterized in that: The engaging protrusion further has a second side surface for defining a portion of the engaging opening, the second side surface is arranged radially inside the first side surface, and along the radial direction of the rotor disk, the distance between the second side surface and the tenon is constant.

5. The rotor disk rear sealing structure according to claim 4 is characterized in that: The connection between the first side surface and the second side surface is smoothly transitioned through an arc surface.

6. The rotor disk rear sealing structure according to claim 1, characterized in that: The rear baffle includes a plate body, and the axial side wall surfaces of the plate body are respectively a first end face and a second end face, and the radial outer end of the first end face is provided with a first protrusion, 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 cooperates with the tenon, and the radial outer end of the second end face cooperates with the clamping protrusion; there is a gap between the first end face and the tenon.

7. The rotor disk rear sealing structure according to claim 6, characterized in that: The rear baffle further includes a second protrusion disposed on the first end surface, the second protrusion being spaced apart from the first protrusion and being located radially inward of the first protrusion; the second protrusion is interference fit with the tenon.

8. The rotor disk rear sealing structure according to claim 1, characterized in that: A bending structure is provided at the radial inner end of the rear baffle, and the bending structure includes a first bending portion and a second bending portion connected to each other, the first bending portion is bent toward the tenon along the axial direction of the rear baffle, and the first bending portion abuts against the tenon; the second bending portion is located below the tenon, and the second bending portion extends radially along the rear baffle.

9. The rotor disk rear sealing structure according to claim 8, characterized in that: The interstage disk is pressed against the second bent portion along the axial direction of the rear baffle.

10. An aircraft engine, characterized in that: The aircraft engine comprises the rotor disk rear sealing structure as described in any one of claims 1-9.

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