Grate tooth sealing structure, sealing method and aero-engine

Abstract

The invention provides a labyrinth sealing structure, a sealing method and an aero-engine. The labyrinth sealing structure comprises a rotor part which comprises a first thin-wall part extending from an engine rotor, and labyrinth is arranged on the radial outer wall of the first thin-wall part; the stator part comprises a second thin-wall part extending from the engine stator, and the radial inner wall of the second thin-wall part is provided with a sealing part corresponding to the labyrinth; wherein the extension length of the first thin-wall part is larger than that of the second thin-wall part; a flow stopping element is arranged on the radial inner wall of the first thin-wall part, and the stopping direction of the flow stopping element is that airflow flowing from one side of an engine rotor to the labyrinth sealing structure is stopped from flowing on one side of the radial inner wall of the first thin-wall part along the radial inner wall of the first thin-wall part after passing through the labyrinth sealing structure.

Description

Technical Field

[0001] The invention relates to the field of aeroengines, and in particular to a comb tooth sealing structure, a sealing method and an aeroengine. Background Art

[0002] In the field of aircraft engine design, the form of grate sealing is widely used. For example, the grate is set at the connection between the engine interstage casing and the low-pressure turbine rotor. The part connected to the stator part is generally a sealing part, and the grate rotor side connected to the rotor part is generally connected to the low-pressure turbine rotating shaft.

[0003] The key issue in the design of the grate seal is to ensure that the gap between the grate teeth is within the design range. Too large or too small a gap will have an adverse effect on the engine. For example, if the gap is too large, the seal will be lost, and if the gap is too small, scratches will occur, resulting in adverse effects.

[0004] Under steady-state conditions, the comb tooth clearance can be designed with a suitable initial clearance value to ensure that the rotor-stator clearance matches in all operating conditions.

[0005] However, when the engine undergoes a transient process of increasing or decreasing speed, the inconsistent thermal response between the rotor and the stator leads to uncoordinated deformation of the comb teeth on both sides of the rotor and the stator. This will cause the comb teeth clearance to fluctuate within a large range, resulting in friction or excessive clearance, which will cause serious damage to the performance and even safety of the engine. Summary of the invention

[0006] One object of the present invention is to provide a comb tooth sealing structure which, by setting a baffle element, can increase the heat capacity on the rotor side while reducing the heat exchange intensity on the rotor side, effectively slowing down the thermal response rate of the rotor parts, thereby improving the transient clearance fit between the rotor and the stator, so that the change of the comb tooth clearance of the comb tooth sealing structure during the operation of the engine meets the engine safety requirements.

[0007] According to the first aspect of the present application, the comb teeth sealing structure comprises:

[0008] The rotor part comprises a first thin-walled member extending from the engine rotor, and comb teeth are arranged on the radial outer wall of the first thin-walled member;

[0009] The stator part comprises a second thin-walled member extending from the engine stator, wherein a sealing member corresponding to the comb teeth is provided on a radial inner wall of the second thin-walled member;

[0010] Among them, the extension length of the first thin-walled part is greater than the extension length of the second thin-walled part; the radial inner wall of the first thin-walled part is provided with a flow blocking element, and the blocking direction of the flow blocking element is: to block the airflow flowing from one side of the engine rotor to the comb tooth sealing structure from flowing along the radial inner wall of the first thin-walled part on one side of the radial inner wall of the first thin-walled part after passing through the comb tooth sealing structure.

[0011] In one or more embodiments, the flow blocking element vertically extends from the radial inner wall of the first thin-walled member along a radially inward direction.

[0012] In one or more embodiments, the axial position of the blocking element corresponds to a front region of the axial position of the comb teeth.

[0013] In one or more embodiments, the seal comprises a honeycomb liner.

[0014] In one or more embodiments, the flow blocking element is a ring-shaped structure.

[0015] According to a second aspect of the present application, a comb teeth sealing method comprises:

[0016] A first thin-walled member is extendedly arranged on the rotor portion, and comb teeth are arranged on the radial outer wall of the first thin-walled member;

[0017] A second thin-walled member is extendedly arranged on the stator part, and a sealing member corresponding to the comb teeth is arranged on the radial inner wall of the second thin-walled member;

[0018] Wherein, the extension length of the first thin-walled member is greater than the extension length of the second thin-walled member;

[0019] A flow-blocking element is arranged on the radial inner wall of the first thin-walled member, and the blocking direction of the flow-blocking element is:

[0020] The airflow flowing from one side of the engine rotor toward the comb teeth sealing structure is prevented from flowing along the radial inner wall of the first thin-walled part on one side of the radial inner wall of the first thin-walled part after passing through the comb teeth sealing structure.

[0021] In one or more embodiments, the fluid is configured to be blocked by the flow blocking element and stay away from the radial inner wall of the first thin-walled part after passing through the sealing structure of the comb teeth and the sealing part.

[0022] In one or more embodiments, the flow blocking element vertically extends from the radial inner wall of the first thin-walled member along a radially inward direction.

[0023] In one or more embodiments, the axial position of the blocking element corresponds to a front region of the axial position of the comb teeth.

[0024] According to a third aspect of the present application, an aircraft engine comprises the comb teeth sealing structure as described in the first aspect of claim 1.

[0025] In one or more embodiments, the comb teeth sealing structure is located at the connection between the engine interstage casing and the low-pressure turbine rotor, the first thin-walled member extends from the low-pressure turbine rotor, and the second thin-walled member extends from the interstage casing.

[0026] The above-mentioned comb tooth sealing structure has a blocking effect on the fluid through the setting of the flow-blocking element, and no fluid passes through the lower wall, thereby reducing the heat transfer coefficient on the rotor side, thereby slowing down the thermal response of the rotor; at the same time, since the thickened part increases the volume of the rotor, the rotor heat capacity is increased, and the thermal response of the rotor is further slowed down, thereby improving the transient clearance fit between the rotor and the stator. The aircraft engine using this comb tooth sealing structure has better safety and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0028] Figure 1 is a schematic diagram of a partial structure of an aircraft engine according to an embodiment;

[0029] Figure 2 Schematic diagram of a comb teeth sealing structure according to an embodiment;

[0030] Figure 3 It is a schematic diagram of the comb tooth sealing structure of a comparison scheme.

[0031] Reference numerals:

[0032] 100-comb teeth sealing structure

[0033] 101-Engine interstage casing

[0034] 102-Low pressure turbine rotor

[0035] 1-Rotor part

[0036] 11-First thin-walled part

[0037] 111-comb teeth

[0038] 112-Blocking element

[0039] 2-Station part

[0040] 21-Sealing parts

[0041] 22-Second thin-walled part. DETAILED DESCRIPTION

[0042] The present invention is further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0043] It should be noted that these and other subsequent drawings are only examples and are not drawn to scale, and should not be used to limit the actual scope of protection required by the present invention.

[0044] The present application uses specific words to describe the embodiments of the present application. For example, "one embodiment", "an embodiment", and / or "some embodiments" refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" or "an alternative embodiment" mentioned twice or multiple times in different positions in this specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0045] The comb teeth sealing structure of the comparison scheme is as follows Figure 3 As shown, after passing through the grate teeth, the fluid flows directly through the lower wall, and the fluid and the wall have a large heat exchange intensity. Since the rotor part with the grate teeth side is an elongated thin-walled part with a fast thermal response, there will be a problem of incoordination of deformation during the engine lifting and lowering process.

[0046] Specifically, during the acceleration of the engine, the comb teeth rotor side heats up and expands rapidly, the radial deformation of the rotor side changes rapidly, the comb teeth clearance decreases rapidly, and collision and wear are prone to occur; on the contrary, during the deceleration process, the comb teeth clearance increases rapidly and loses the sealing effect.

[0047] refer to Figure 1 as well as Figure 2 As shown, in some embodiments, the comb seal structure 100 in the aircraft engine is Figure 1 Taking the comb seal structure 100 shown at the connection between the engine interstage casing 101 and the low-pressure turbine rotor 102 as an example, the first thin-walled part 11 of the rotor part 1 of the comb seal structure 100 extends from the low-pressure turbine rotor 102, and the second thin-walled part 22 of the stator part 2 extends from the interstage casing 101, but this is not limiting. The comb seal structure 100 introduced in the following embodiments can also be used in other occasions of aircraft engines that require comb seals, as well as any occasions in fluid machinery that require comb seals.

[0048] Continue to refer Figure 1 as well as Figure 2 As shown, in some embodiments, the comb seal structure 100 includes a rotor part 1 and a stator part 2 .

[0049] The rotor part 1 comprises a first thin-walled member 11 extending from the engine rotor, and comb teeth 111 are arranged on the radial outer wall of the first thin-walled member 11 .

[0050] The stator part 2 includes a second thin-walled member 22 extending from the engine stator, and a sealing member 21 corresponding to the comb teeth 111 is provided on the radial inner wall of the second thin-walled member 22;

[0051] like Figure 1 As shown, the extension length W1 of the first thin-walled member 11 is greater than the extension length W2 of the second thin-walled member 22 .

[0052] like Figure 1 as well as Figure 2 As shown, a flow-blocking element 112 is provided on the radial inner wall of the first thin-walled part 11, and the blocking direction of the flow-blocking element 112 is: to block the airflow flowing from one side of the engine rotor toward the comb tooth sealing structure 100 from flowing along the radial inner wall of the first thin-walled part 11 on the radial inner wall side of the first thin-walled part 11 after passing through the comb tooth sealing structure 100.

[0053] Preferably, the flow blocking element 112 extends vertically from the radial inner wall of the first thin-walled member 11 in the radially inward direction, which has a good blocking effect and a simple structure. In addition, the flow blocking element 112 can be a ring-shaped structure, which can further improve the blocking effect.

[0054] Preferably, in some embodiments, the axial position of the flow-blocking element 112 corresponds to the front region of the axial position of the comb teeth 111, for example Figure 1 as well as Figure 2 As shown, it is near the first tooth in the axial direction from front to back, so that it can play a blocking role when the fluid initially enters.

[0055] In some embodiments, the sealing member 21 includes a honeycomb liner, which has a better sealing effect.

[0056] The above structure has a blocking effect on the fluid through the setting of the flow-blocking element. Less fluid passes through the radially inner side wall, which reduces the heat transfer coefficient on the rotor side, thereby slowing down the thermal response of the rotor; at the same time, since the thickened part increases the volume of the rotor, the rotor heat capacity is increased, and the thermal response of the rotor is further slowed down, thereby improving the transient clearance fit between the rotor and the stator.

[0057] Combined with the above introduction to the comb tooth sealing structure, it can also be understood that an aircraft engine includes the above comb tooth sealing structure, which can delay the thermal response of the comb tooth stator side under transient and steady-state conditions such as accelerated takeoff and rapid rotation, optimize the comb tooth clearance in the operating state, and provide protection for the safe operation of the engine.

[0058] It can be understood that the present application also provides a comb teeth sealing method, comprising:

[0059] A first thin-walled member 11 is extendedly provided on the rotor part 1, and comb teeth 111 are provided on the radial outer wall of the first thin-walled member 11;

[0060] A second thin-walled member 22 is extendedly provided on the stator part 2, and a sealing member 21 corresponding to the comb teeth 111 is provided on the radial inner wall of the second thin-walled member 22;

[0061] Wherein, the extension length of the first thin-walled member 11 is greater than the extension length of the second thin-walled member 22;

[0062] A flow-blocking element 112 is provided on the radial inner wall of the first thin-walled member 11, and the blocking direction of the flow-blocking element 112 is:

[0063] The airflow flowing from the engine rotor side toward the comb teeth sealing structure 100 is blocked from flowing along the radial inner wall of the first thin-walled part 11 on the radial inner wall side of the first thin-walled part 11 after passing through the comb teeth sealing structure 100 .

[0064] In summary, the beneficial effects of the comb tooth sealing structure, sealing method, and aircraft engine introduced in the above embodiments include but are not limited to: through the setting of the flow-blocking element, the fluid is blocked, no fluid passes through the lower wall, the heat transfer coefficient on the rotor side is reduced, and the thermal response of the rotor is slowed down; at the same time, the thickened part increases the volume of the rotor, increases the heat capacity of the rotor, and further slows down the thermal response of the rotor, thereby improving the transient clearance fit between the rotor and the stator. The aircraft engine using this comb tooth sealing structure has better safety and reliability.

[0065] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A comb teeth sealing structure (100), characterized in that: include: The rotor part (1) comprises a first thin-walled member (11) extending from the engine rotor, and comb teeth (111) are arranged on the radial outer wall of the first thin-walled member (11); The stator part (2) comprises a second thin-walled member (22) extending from the engine stator, wherein a sealing member (21) corresponding to the comb teeth (111) is provided on a radial inner wall of the second thin-walled member (22); The extension length of the first thin-walled part (11) is greater than the extension length of the second thin-walled part (22); a flow-blocking element (112) is provided on the radial inner wall of the first thin-walled part (11), and the blocking direction of the flow-blocking element (112) is: to block the airflow flowing from one side of the engine rotor toward the comb tooth sealing structure (100) from flowing along the radial inner wall of the first thin-walled part (11) on one side of the radial inner wall of the first thin-walled part (11) after passing through the comb tooth sealing structure (100).

2. The comb teeth sealing structure (100) according to claim 1, characterized in that: The flow-blocking element (112) vertically extends from the radial inner wall of the first thin-walled member (11) in a radially inward direction.

3. The comb teeth sealing structure (100) according to claim 1, characterized in that: The axial position of the flow-blocking element (112) corresponds to the front region of the axial position of the comb teeth (111).

4. The comb teeth sealing structure (100) according to claim 1, characterized in that: The sealing member (21) comprises a honeycomb liner.

5. The comb teeth sealing structure (100) according to claim 1, characterized in that: The flow-blocking element (112) is a ring-shaped structure.

6. A comb teeth sealing method, characterized in that: include: A first thin-walled member (11) is extendedly arranged on the rotor part (1), and comb teeth (111) are arranged on the radial outer wall of the first thin-walled member (11); A second thin-walled member (22) is extendedly arranged on the stator part (2), and a sealing member (21) corresponding to the comb teeth (111) is arranged on the radial inner wall of the second thin-walled member (22); Wherein, the extension length of the first thin-walled member (11) is greater than the extension length of the second thin-walled member (22); A flow-blocking element (112) is arranged on the radial inner wall of the first thin-walled member (11), and the blocking direction of the flow-blocking element (112) is: The airflow flowing from one side of the engine rotor toward the comb tooth sealing structure (100) is prevented from flowing along the radial inner wall of the first thin-walled part (11) on one side of the radial inner wall of the first thin-walled part (11) after passing through the comb tooth sealing structure (100).

7. The comb teeth sealing method according to claim 6, characterized in that: The fluid is configured to be blocked by the flow blocking element and away from the radial inner wall of the first thin-walled part (11) after passing through the sealing structure of the comb teeth (111) and the sealing part (21).

8. The comb teeth sealing method according to claim 6, characterized in that: The flow-blocking element (112) vertically extends from the radial inner wall of the first thin-walled member (11) in a radially inward direction.

9. The comb teeth sealing method according to claim 6, characterized in that: The axial position of the flow-blocking element (112) corresponds to the front region of the axial position of the comb teeth (111).

10. An aircraft engine, characterized in that: It comprises the comb tooth sealing structure (100) as described in any one of claims 1 to 5.

11. The aircraft engine according to claim 10, characterized in that: The comb teeth sealing structure (100) is located at the connection between the engine interstage casing and the low-pressure turbine rotor, the first thin-walled member (11) extends from the low-pressure turbine rotor, and the second thin-walled member (22) extends from the interstage casing.

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