Sealing comb tooth structure, double-side sealing structure and bearing cavity sealing assembly

Abstract

The present invention provides a sealing grate structure, including an annular grate, which is arranged on the outer peripheral side of the rotating shaft and protrudes toward the stator ring. The sealing grate structure is used to prevent the fluid from flowing from the first end side of the annular grate to the second end side. The annular grate is inclined toward the first end side, and the sealing grate structure also includes a guide bar, which is arranged on the first end face of the annular grate at the first end side and extends from the bottom side of the annular grate toward the top side. The guide bar has a windward side surface on the windward side relative to the turning of the rotating shaft, and the windward side surface guides the bottom fluid on the bottom side to flow from the bottom side to the top side and out from the top side, so that the outflow velocity of the bottom fluid out of the top side has a velocity component pointing from the windward side to the leeward side. The present invention also provides a double-sided sealing structure and an aircraft engine bearing cavity sealing assembly including the above-mentioned sealing grate structure. The above-mentioned sealing grate structure can improve the sealing performance.

Description

Technical Field

[0001] The invention relates to a sealing comb tooth structure, and also relates to a double-side sealing structure and an aero-engine bearing cavity sealing component. Background Art

[0002] With the development of aviation, the requirements for aircraft maneuverability, reliability and economy are getting higher and higher. Therefore, it is urgent to improve the various components of aircraft engines to ensure the high performance of the engine. Low fuel consumption, high thrust-to-weight ratio, high reliability and durability are the development trends of modern aviation gas turbine engines. However, the internal temperature and pressure ratio of the engine are gradually increasing, making the leakage of the internal flow coefficient more and more serious, and the performance of the seal directly affects the working performance of the aircraft engine fuel consumption rate, flight cost, thrust-to-weight ratio, etc. In order to reduce leakage losses and improve the overall performance of the engine, it is particularly important to improve the original sealing devices in many parts. Domestic and foreign studies have shown that half of the improvement in the performance of aircraft engines in the future will depend on the improvement of sealing technology and the reduction of leakage. Therefore, people's requirements for high-performance sealing structures are becoming more and more urgent. Improving and developing new sealing devices has important practical value in reducing fuel consumption and improving engine efficiency.

[0003] In order to ensure the sealing of the air path between the rotor and the stator, the most widely used sealing grate structure in current engines is also called grate sealing structure. It is a non-contact dynamic seal that uses the sudden expansion and contraction of the channel to increase the flow resistance to limit fluid leakage. The main function of the bearing cavity lubricating oil seal is to effectively isolate the bearing cavity of the engine rotor system from the airflow environment of the engine, protect the bearing and lubricating oil from damage to the airflow path, and prevent lubricating oil leakage. Therefore, in order to avoid the occurrence of reverse pressure difference at the seal, the lubricating oil in the cavity leaks from the sealing flow gap and increases the air pressure outside the bearing cavity, but this will also lead to an increase in air leakage and higher lubricating oil consumption, and even high-temperature and high-pressure gas leaks into the bearing cavity, increasing the risk of burning and coking of the lubricating oil in the bearing cavity.

[0004] Therefore, it is very important to improve the sealing comb tooth structure to enhance its sealing performance. Summary of the invention

[0005] The object of the present invention is to provide a sealing comb tooth structure which can improve the sealing performance.

[0006] Another object of the present invention is to provide a double-sided sealing structure that can improve the sealing performance.

[0007] Another object of the present invention is to provide an aircraft engine bearing cavity sealing assembly that can improve sealing performance.

[0008] The present invention provides a sealing grate structure, comprising an annular grate, which is arranged on the outer peripheral side of a rotating shaft and protrudes toward a stator ring. The sealing grate structure is used to prevent fluid from flowing from a first end side of the annular grate to a second end side. The annular grate is inclined toward the first end side, and the sealing grate structure also includes a guide bar, which is arranged on a first end face of the annular grate on the first end side and extends from a bottom side of the annular grate toward a top side. The guide bar has a windward side surface on the windward side relative to the turning direction of the rotating shaft, and the windward side surface guides the bottom fluid on the bottom side to flow from the bottom side to the top side and out from the top side, so that an outflow velocity of the bottom fluid flowing out from the top side has a velocity component directed from the windward side to the leeward side.

[0009] In one embodiment, the windward side surface is configured such that the outflow velocity of the bottom fluid flowing out from the top side also has a velocity component flowing toward the stator ring.

[0010] In one embodiment, the windward side has a windward side contour line that is perpendicular to the axial direction of the rotating shaft, and the windward side contour line has an outflow tangent vector at the windward side vertex on the top side for guiding the outflow of fluid, and the angle between the outflow tangent vector and the reverse tangent vector at the windward side vertex pointing from the windward side to the leeward side is α3, 0°<α3≤45°.

[0011] In one embodiment, the windward side surface has a windward side contour line that is perpendicular to the axial direction of the rotating shaft, and the windward side contour line is a smooth curve in an outwardly convex form.

[0012] In one embodiment, the windward side has a windward side contour line that is perpendicular to the axial direction of the rotating shaft, and the windward side contour line has an inflow tangent vector at the bottom point of the windward side on the bottom side for guiding the inflow of fluid, and the inflow tangent vector is consistent with the reverse tangent vector at the bottom point of the windward side pointing from the windward side to the leeward side.

[0013] In one embodiment, the windward side surface is parallel to the axial direction of the rotating shaft.

[0014] In one embodiment, the guide strip has a leeward side surface on the leeward side relative to the deflection direction, and the leeward side surface is parallel to the windward side surface.

[0015] In one embodiment, the sealing comb tooth structure includes a plurality of guide strips evenly distributed along the circumference of the rotating shaft.

[0016] The present invention also provides a double-sided sealing structure, comprising two of the aforementioned sealing comb tooth structures, the annular comb teeth of the two sealing comb tooth structures are distributed on the outer peripheral side of the rotating shaft along the axial direction of the rotating shaft, and the first end sides of the annular comb teeth of the two sealing comb tooth structures are respectively relative to the two outer end sides of the two sealing comb tooth structures.

[0017] The present invention also provides an aircraft engine bearing cavity sealing assembly, comprising a stator component and a rotor component, and also comprising the aforementioned double-sided sealing structure, wherein the stator component and the rotor component respectively provide a stator ring and a rotating shaft, and one of the two sealing grate structures of the double-sided sealing structure is used to prevent compressed gas outside the bearing cavity from flowing from the outside of the bearing cavity to the inside of the bearing cavity via the double-sided sealing structure, and the other of the two sealing grate structures is used to prevent oil and gas in the bearing cavity from flowing from the inside of the bearing cavity to the outside of the bearing cavity via the double-sided sealing structure.

[0018] In the above-mentioned sealing comb tooth structure, the outwardly inclined annular comb teeth can make the fluid return in the direction away from the sealing comb tooth structure, which can itself enhance the sealing effect. Moreover, the outwardly inclined annular comb teeth cooperate with the guide strips that guide the fluid from the bottom of the teeth to the top of the teeth, thereby forming a spiral flow away from the sealing comb tooth structure, which can resist the flow from the top of the teeth, further enhance the sealing effect, and improve the sealing performance.

[0019] The double-sided sealing structure and the aero-engine bearing cavity sealing assembly can achieve double-sided sealing, which can further improve the sealing performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] 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:

[0021] Figure 1 is a schematic diagram showing an aircraft engine bearing cavity.

[0022] Figure 2 is a perspective view showing an exemplary double-sided sealing structure.

[0023] Figure 3 is a plan view showing an exemplary sealing comb tooth structure.

[0024] Figure 4 is a cross-sectional view showing an exemplary double-sided sealing structure. DETAILED DESCRIPTION

[0025] The present invention is further described below in conjunction with specific implementation methods and accompanying 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 this description. 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 scope of protection of the present invention should not be limited by the content of this specific implementation method.

[0026] For example, a first feature described later in the specification as being formed above or on a second feature may include an embodiment in which the first feature and the second feature are formed by direct connection, and may also include an embodiment in which an additional feature is formed between the first feature and the second feature, so that the first feature and the second feature may not be directly connected. Further, when a first element is described as being connected or combined with a second element, the description includes an embodiment in which the first element and the second element are directly connected or combined with each other, and also includes an embodiment in which one or more other intervening elements are added to indirectly connect or combine the first element and the second element.

[0027] Figure 1 The relevant structure of the bearing cavity B1 of the aircraft engine is shown as an example. In the aircraft engine 100, a bearing cavity B1 is formed between the rotor and the stator, and is usually sealed with compressed air to ensure that the lubricating oil used for lubrication and cooling of the bearings 101 and 102 does not leak. During the operation of the aircraft engine 100, the lubricating oil in the bearing cavity B1 usually exists in the form of oil gas. Figure 1 In the bearing cavity B1, the outer cavity B2 will introduce a stream of compressed gas G1 with a certain pressure to block the oil and gas G2 that is trying to leak out and build up the pressure in the bearing cavity B1. Usually, a comb tooth sealing structure 10' is provided between the rotor component 200 and the stator component 300 to improve the sealing effect of the compressed gas G1 on the oil and gas G2, and even reduce the amount of compressed gas G1 used.

[0028] The example structure of the sealing comb tooth structure 1 provided by the present invention is as follows: Figures 2 to 4 As shown, Figure 2 A three-dimensional diagram of the sealing comb tooth structure 1 is shown. Figure 3 The front view of the sealing comb tooth structure 1 is shown. Figure 4 A cross-sectional view of the sealing comb tooth structure 1 is shown. Figures 2 to 4 In the figures, the double-sided sealing structure 10 is used as an example to illustrate the exemplary structure of the sealing grate structure 1. The double-sided sealing structure 10 includes two sealing grate structures 1. Figure 4 In the figure, they are respectively the left sealing grate tooth structure 1a and the right sealing grate tooth structure 1b. When not distinguished in the text, they can be collectively referred to as the sealing grate tooth structure 1, and when described separately, a or b is added after the same number to distinguish them. Figures 2 to 4 The sealing grate tooth structure 1 is described by taking the sealing grate tooth structure 1a in FIG. 1 as an example.

[0029] It should be understood that the 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.

[0030] Combination Figures 2 to 4The sealing grate structure 1 includes an annular grate 4, which can also be called a circumferential grate or a circumferential grate. The annular grate 4 is arranged on the outer peripheral side of the rotating shaft 2 and protrudes toward the stator ring 3.

[0031] The rotating shaft 2 may be a part of the rotor component 200 in the aircraft engine 100, and the stator ring 3 may be a part of the stator component 300 in the aircraft engine 100. The stator ring 3 is sleeved outside the rotating shaft 2, and there is an annular gap between the stator ring 3 and the rotating shaft 2, and the annular comb teeth 4 are arranged in the annular gap, and there is still a small annular tooth tip gap SG between the tooth top of the annular comb teeth 4 and the stator ring 3 (the inner wall surface). The annular tooth tip gap SG can prevent the rotor and stator from rubbing against each other, and when applied to the aircraft engine bearing cavity 101, it can also reduce the circulation of air inside and outside the bearing cavity to achieve a sealing effect. The stator ring 3 can be called a sealing ring, and the inner wall surface of the stator ring 3 can be provided with an easy-to-wear coating or honeycomb.

[0032] For ease of description, the rotating shaft 2 can define its rotation direction, which can be called the steering RT, and can also define the rotation direction RV opposite to the steering RT, and can also define the axial direction X0 consistent with the extension direction of the central axis O2 of the rotating shaft 2, and can also define the radial direction R0 pointing from the radial inside to the radial outside, and can also define the circumferential direction C0 around its central axis O2, wherein the circumferential direction C0 can also be considered as a steering RT or rotation direction RV without unilateral direction or with bilateral direction. The rotating shaft 2 rotates around the steering RT, and the surrounding fluid rotates around the rotation direction RV relative to the rotating shaft 2.

[0033] The sealing comb tooth structure 1 is used to prevent the fluid F from flowing from the first end side S1 of the annular comb tooth 4 to the second end side S2 .

[0034] In the sealing comb tooth structure 1 provided by the present invention, the annular comb tooth 4 is inclined toward the first end side S1. It can be understood that the annular comb tooth 4 is inclined toward the first end side S1, that is, it is inclined so that the tooth top 43 of the annular comb tooth 4 is closer to the first end side S1 than the tooth bottom 44. The tooth top 43 of the annular comb tooth 4 is also far away from the free end of the rotating shaft 2, that is, closer to the radially outer end, and the tooth bottom 44 of the annular comb tooth 4 is also the base end connected to the rotating shaft 2, that is, closer to the radially inner end. The annular comb tooth 4 has a first end face 41 on the first end side S1.

[0035] It can be understood that the use of words such as "first" and "second" to limit features is only to facilitate the distinction between corresponding features. Unless otherwise stated, the above words have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0036] The sealing comb structure 1 provided by the present invention also includes a guide bar 5. The guide bar 5 is arranged on the first end face 41 of the annular comb 4 at the first end side S1, that is, the guide bar 5 is arranged on the end face of the annular comb 4 located on the upstream side relative to the flow direction of the fluid F that it is intended to prevent. In addition, the guide bar 5 extends from the bottom side S4 (that is, the radial inside) of the annular comb 4 toward the top side S3 (that is, the radial outside). In the illustrated embodiment, the guide bar 5 extends from the tooth bottom (or, tooth root) of the annular comb 4 to the tooth top. In one embodiment, the guide bar 5 may also extend from a certain position on the top of the tooth bottom 44 of the annular comb 4 to a certain position below the tooth top 43, that is, it may not extend along the tooth height of the entire annular comb 4.

[0037] The guide bar 5 has a windward side surface 51 on the windward side SR1 relative to the turning RT of the rotating shaft 2. It can be understood that the guide bar 5 has a windward side SR1 and a leeward side SR2 relative to the turning RT of the rotating shaft 2. Figure 3 Taking the clockwise turning RT as an example, the windward side SR1 is located on the downstream side on the clockwise turning RT, and the leeward side SR2 is located on the upstream side on the clockwise turning RT. In addition, the description of "windward side SR1" and "leeward side SR2" is only for expressing the direction, but not for limiting the flow medium rotating around the rotating shaft 2. The fluid can be liquid or gas, and the most common one in the aircraft engine 100 is airflow.

[0038] The windward side surface 51 guides the bottom fluid F1 on the bottom side S4 to flow from the bottom side S4 to the top side S3 and out of the top side S3, so that the outflow velocity V3 of the bottom fluid F1 out of the top side S3 has a velocity component directed from the windward side SR1 to the leeward side SR2. That is, the windward side surface 51 not only guides the bottom fluid F1 from the bottom side S4 to the top side S3, but also makes the bottom fluid F1 have a velocity component rotating along the rotation direction RV relative to the rotation axis 2 when it flows out of the windward side surface 51 on the top side S3.

[0039] It can be understood that the outflow velocity V3 is a vector with velocity magnitude and direction. The outflow velocity V3 has a velocity component from the windward side SR1 to the leeward side SR2, which means that the outflow velocity V3 is Figure 3 When it is decomposed into two perpendicular velocity components on a two-dimensional page, or when it is decomposed into three mutually perpendicular velocity components in three-dimensional space, one of the velocity components points from the windward side SR1 to the leeward side SR2.

[0040] Combination Figure 3 and Figure 4In the sealing comb structure 1, the guide bar 5 has a guiding effect on the bottom fluid F1, and guides the oncoming bottom fluid F1 from the bottom side S4 to the top side S3. The bottom fluid F1 flowing to the bottom side S4 will flow out from the top side S3 under the guiding effect of the guide bar 5 and has a speed component rotating along the rotation direction RV relative to the rotating shaft 2.

[0041] In the above-mentioned sealing comb tooth structure 1, the annular comb teeth 4 are inclined toward the first end side S1, so the annular comb teeth 4 will give the bottom fluid F1 an axial velocity component that pushes back toward the first end side S1. Therefore, the bottom fluid F1 flowing to the bottom side S4 flows out from the top side S3 and forms a spiral flow H that pushes back along the spiral direction under the joint action of the velocity component rotating along the rotation direction RV and the returned axial velocity component. Therefore, the bottom fluid F1 flowing to the bottom side S4 can be pushed back to the fluid inlet side, and the spiral flow H can push against the top fluid F2 flowing to the top side S3.

[0042] In the illustrated embodiment, the windward side surface 51 makes the outflow velocity V3 of the bottom fluid F1 flowing out from the top side S3 also have a velocity component flowing toward the stator ring 3. In other words, the windward side surface 51 also makes the outflow velocity V3 of the bottom fluid F1 flowing out from the top side S3 have a velocity component pointing from the radial inside to the radial outside along the radial direction R0.

[0043] In this way, when the bottom fluid F1 flows out of the guide strip 5 from the top side S3, the outflow velocity V3 also has a certain component in the radial direction R0. Therefore, the bottom fluid F1 can be blown toward the inner wall surface of the stator ring 2 and form turbulence in the tooth tip gap SG, which can enhance the sealing effect. Moreover, with the inclined annular comb teeth 4, the kinetic energy loss of the bottom fluid F1 can be reduced and the tooth tip flow can be resisted positively, which can further enhance the sealing effect.

[0044] In the illustrated embodiment, the windward side surface 51 may have a windward side contour line 510 perpendicular to the axial direction X0 of the rotating shaft 2. In other words, the windward side surface 51 may have a windward side contour line 510 extending from the bottom side S4 of the annular comb teeth 4 toward the top side S3, and the windward side contour line 510 is perpendicular to the axial direction X0 of the rotating shaft 2.

[0045] The windward side contour line 510 has an outflow tangent vector T13 for guiding the outflow of the fluid at the windward side vertex 513 of the top side S3. Generally, the direction of the outflow tangent vector T13 determines the direction of the outflow velocity V3 flowing out from the position, and typically, the direction of the outflow tangent vector T13 is consistent with the direction of the outflow velocity V3 at the corresponding position.

[0046] There is also a reverse tangent vector TV3 pointing from the windward side SR1 to the leeward side SR2 at the windward side vertex 513. It can be understood that the specific directions of the turning direction RT or the opposite rotation direction RV at each point are different, and are specifically manifested as tangent vectors at each point. The tangent vector specifically manifested by the turning direction RT at each point can be called a rotating tangent vector, and the tangent vector specifically manifested by the rotation direction RV at each point can be called a reverse tangent vector. The reverse tangent vector TV3 pointing from the windward side SR1 to the leeward side SR2 at the windward side vertex 513 is also the tangent vector specifically manifested by the rotation direction RV at the windward side vertex 513.

[0047] The angle between the outflow tangent vector T13 and the reverse tangent vector TV3 at the windward vertex 513 pointing from the windward side SR1 to the leeward side SR2 is α3, as shown in Figure 3 When 0°≤α3<90°, it can help to make the outflow velocity V3 have a velocity component directed from the windward side SR1 to the leeward side SR2.

[0048] In the illustrated embodiment, 0°<α3≤45°. This helps to make the outflow velocity V3 have both a velocity component directed from the windward side SR1 to the leeward side SR2 and a velocity component flowing toward the stator ring 3, and the velocity component directed from the windward side SR1 to the leeward side SR2 is not smaller than the velocity component flowing toward the stator ring 3.

[0049] It is understood that specific words are used herein to describe embodiments of the present invention, such as "one embodiment", "another embodiment", and / or "illustrated embodiment" to refer to a certain feature, structure or characteristic associated with at least one embodiment of the present invention. Therefore, it should be emphasized and noted that "one embodiment" or "another embodiment" mentioned twice or more in different places in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics of one or more embodiments of the present invention may be appropriately combined.

[0050] In the illustrated embodiment, the windward side contour line 510 may have an inflow tangent vector T14 for guiding the inflow of fluid at a windward side bottom point 514 of the bottom side S4 .

[0051] There may also be an angle between the inflow tangent vector T14 and the reverse tangent vector TV4 pointing from the windward side SR1 to the leeward side SR2 at the windward side bottom point 514, and the angle may be an acute angle. This means that the angle between the guiding direction (indicated by the inflow tangent vector T14) at the initial position (windward side bottom point 514) where the guide strip 5 starts to receive the bottom fluid F1 for guiding at the bottom side S4 and the original flow direction of the bottom fluid F1 at the initial position (indicated by the reverse tangent vector TV4) is small, so the bottom fluid F1 can be easily introduced, and the kinetic energy loss of the bottom fluid F1 is small.

[0052] In the illustrated embodiment, the angle can be 0, that is, the inflow tangent vector T14 can be consistent with the reverse tangent vector TV4 pointing from the windward side SR1 to the leeward side SR2 at the windward side bottom point 514. In this way, the guiding direction of the guide strip 5 at the initial position (windward side bottom point 514) where the bottom side S4 begins to receive the bottom fluid F1 for guiding is completely consistent with the original flow direction of the bottom fluid F1 at the initial position. This can minimize the introduction effect and kinetic energy loss of the bottom fluid F1.

[0053] In the illustrated embodiment, the windward side contour line 510 may be a smooth curve in a convex form. It can be understood that a "smooth curve" means that the first-order derivative of each point of the curve is continuous. The windward side contour line 510 is in a convex form, which can make the guiding direction of the bottom fluid F1 of the guide strip 5 gradually change from having a small component (no component in the figure) in the radial direction R0 to having a certain component in the radial direction R0.

[0054] In the illustrated embodiment, the windward side surface 51 may be parallel to the axial direction X0 of the rotating shaft 2. It can be understood that "the windward side surface 51 is parallel to the axial direction X0" means that the windward side surface 51 may be formed by a straight line parallel to the axial direction X0 moving continuously in space along a predetermined trajectory, and the predetermined trajectory may be a straight line, thereby forming a plane, or a curve, thereby forming a curved surface. Figure 3 As shown, the windward side surface 51 can be an arc surface formed by a straight line parallel to the axial direction X0 continuously moving along an arc curve perpendicular to the axial direction X0, and the arc curve is, for example, a circular arc. The windward side surface 51 is parallel to the axial direction X0, and thus can be consistent with the flow direction of the fluid F without returning part of the fluid F.

[0055] The guide strip 5 may have a leeward side surface 52 on the leeward side SR2 relative to the turn RT. In the illustrated embodiment, the leeward side surface 52 may be parallel to the windward side surface 51. "The leeward side surface 52 is parallel to the windward side surface 51" means that a perpendicular line is drawn along the normal vector at any point on the windward side surface 51, and the distance between the intersection of the perpendicular line and the leeward side surface 52 and the arbitrary point is constant. As mentioned above, the windward side surface 51 may be an arc-shaped surface, and when the leeward side surface 52 is parallel to such a windward side surface 51, the leeward side surface 52 is also a similar arc-shaped surface, such as Figure 3 At this time, the guide strip 5 can also be called an arc-shaped tooth.

[0056] In the illustrated embodiment, the sealing comb structure 1 may include a plurality of guide bars 5 evenly distributed along the circumferential direction C0 of the rotating shaft 2. Adjacent guide bars 5 may define a flow guide channel or a flow guide groove, and the two side surfaces of the flow guide groove may be arc-shaped groove surfaces, and the cross-sectional size of the flow guide groove may gradually expand from the bottom side S4 toward the top side S3. Figure 3In the embodiment, a plurality of guide bars 5 are radially arranged on the first end face 41 of the annular comb teeth 4, and the direction of radial extension outward is consistent with the rotation direction RV. Figure 3 When the steering wheel RT in the embodiment rotates clockwise, the guide bars 5 are arranged radially outward in a counterclockwise direction. When the shaft 2 rotates clockwise, the airflow at the bottom of the tooth is lifted up by the radial guide bars 5 and flows toward the top of the tooth along the arc groove defined between adjacent guide bars 5, so that the airflow at the bottom of the tooth is blown toward the inner wall surface of the stator ring 3 under the disturbance of the rotor.

[0057] Combination Figures 2 to 4 The double-sided sealing structure 10 may include the two aforementioned sealing comb tooth structures 1, namely the sealing comb tooth structures 1a and 1b.

[0058] The annular grate teeth 4a and 4b of the two sealing grate tooth structures 1a and 1b can be distributed on the outer peripheral side of the rotating shaft 2 along the axial direction X0 of the rotating shaft 2. In other words, the annular grate teeth 4a of the sealing grate tooth structure 1a and the annular grate teeth 4b of the sealing grate tooth structure 1b are distributed at intervals along the axial direction X0.

[0059] The first end sides S1a, 11b of the annular comb teeth 4a, 4b of the two sealing comb tooth structures 1a, 1b can be respectively the two outer end sides relative to the two sealing comb tooth structures 1a, 1b. It can be understood that, relative to the two sealing comb tooth structures 1a, 1b, the inner end side means an end side between the two sealing comb tooth structures 1a, 1b, and the outer end side means the two end sides outside the two sealing comb tooth structures 1a, 1b. That is, Figure 4 In the figure, the first end side S1a of the annular comb teeth 4a of the sealing comb tooth structure 1a is the left end side relative to the two sealing comb tooth structures 1a and 1b, and the first end side S1b of the annular comb teeth 4b of the sealing comb tooth structure 1b is the right end side relative to the two sealing comb tooth structures 1a and 1b.

[0060] Figure 4 In the figure, similar reference numerals are used for the sealing comb tooth structures 1a and 1b. Specifically, the preceding numbers are the same but the suffixes are a and b, respectively, to indicate that the features belong to the sealing comb tooth structures 1a and 1b, respectively. It should be understood that similar reference numerals are used to represent similar features, and the descriptions of the same technical contents are selectively omitted and not repeated, so as to simplify the description. For example, the sealing comb tooth structures 1a and 1b can both be used as examples of the sealing comb tooth structure 1 and any of the above descriptions of the sealing comb tooth structure 1 can be applied. For another example, the annular comb teeth 4a and 4b are examples of the annular comb teeth 4, and the fluids Fa and Fb are examples of the fluid F. The spiral airflows Ha and Hb are examples of the spiral airflow H, and so on. In the above-mentioned double-sided sealing structure 10, the sealing comb tooth structures 1a and 1b can be symmetrically distributed.

[0061] The above-mentioned double-sided sealing structure 10 can achieve double-sided sealing, and the fluid Fa can be sealed especially through the sealing comb tooth structure 1a, and the fluid Fb can be sealed especially through the sealing comb tooth structure 1b. Specifically, the two sides of the above-mentioned double-sided sealing structure 10 located at the outermost sides are provided with annular comb teeth 4, and the annular comb teeth 4 are respectively inclined toward their respective outer end sides, and the outer end surface of the annular comb teeth 4 is provided with a series of arc-shaped guide strips 5, and the guide strips 5 can be radially arranged along the circumferential direction C0 on the outer end surface of the annular comb teeth 4, extending from the tooth bottom side (or, tooth root) to the tooth top side and along the rotation direction of the rotor part. As the rotor part rotates, the guide strips 5 on the outer end side of the annular comb teeth 4 on both sides can effectively use their windward side 51 to guide the airflow to flow from the tooth bottom to the tooth top, thereby forming a sealing airflow at the tooth top of the annular comb teeth 4. At the same time, the airflow also makes a spiral motion around the rotor member when flowing from the tooth bottom to the tooth top, so that the spiral airflow pushes the airflow on both sides away from the double-sided sealing structure 10 to block gas leakage. The annular comb teeth 4 on both sides are arranged as inclined teeth inclined outward, which can help guide the airflow to move to both sides, reduce the flow energy consumption of the sealing airflow, thereby enhancing the tooth top sealing effect, and can effectively reduce the comb tooth leakage.

[0062] In the illustrated embodiment, the double-sided sealing structure 10 may further include intermediate comb teeth 40 distributed between the annular comb teeth 4a, 4b of the two sealing comb tooth structures 1a, 1b along the axial direction X0. The number of the intermediate comb teeth 40 may be one, two, three or more than four. Figure 4 , a middle comb tooth 40 is shown, that is, the double-sided sealing structure 10 has three comb teeth distributed along the axial direction X0. The middle comb teeth 40 can be straight comb teeth or oblique comb teeth. By providing at least one middle comb tooth 40, the sealing effect can be enhanced.

[0063] Back to Figure 1 The present invention can also provide an aircraft engine bearing cavity sealing assembly 80. The aircraft engine bearing cavity sealing assembly 80 includes a stator component 300 and a rotor component 200. The aircraft engine bearing cavity sealing assembly 80 can also include the aforementioned double-sided sealing structure 10, which can be used as Figure 1 The stator element 300 and the rotor element 200 can provide a stator ring 3 and a rotating shaft 2 respectively.

[0064] One of the two sealing comb structures 1a, 1b of the double-sided sealing structure 10, for example 1a, can be used to prevent the compressed gas G1 outside the bearing cavity B1 from flowing from the outside of the bearing cavity B1 to the inside of the bearing cavity B1 via the double-sided sealing structure 10, while the other of the two sealing comb structures 1a, 1b, for example 1b, is used to prevent the oil and gas G2 in the bearing cavity B1 from flowing from the inside of the bearing cavity B1 to the outside of the bearing cavity B1 via the double-sided sealing structure 10.

[0065] In other words, Figure 4 In the embodiment, the left side fluid Fa of the double-sided sealing structure 10 can be Figure 1 The compressed gas G1 in the right side, and the fluid Fb on the right side can be Figure 1 Oil and gas G2.

[0066] In the above-mentioned aircraft engine bearing chamber sealing assembly 80, as the rotor part 200 (the rotating shaft 20) rotates along the steering RT, when the pressure outside the bearing chamber 101 is greater than the pressure inside the bearing chamber 101, the left side fluid Fa (compressed gas G1) of the double-sided sealing structure 10 will approach the sealing comb tooth structure 1a and try to enter the bearing chamber 101 through the tooth tip gap, but the guide bar 5a that rotates with the rotor part 200 will lift the fluid (compressed gas G1, taking the bottom fluid F1a as an example) within the comb tooth height range and cause the fluid to move along the arc groove toward the tooth top. Since the annular grate teeth 4a are outwardly inclined, the fluid (compressed gas G1, taking the bottom fluid F1a as an example) moves toward the tooth top and also flows in the direction away from the sealing grate teeth along with the inclined annular grate teeth 4a, so that the sealing airflow (compressed gas G1, taking the bottom fluid F1a as an example) can not only blow toward the inner wall surface of the stator ring 3 to form turbulence in the tooth tip gap SG, but also, under the guidance of the inclined annular grate teeth 4a, the kinetic energy loss of the sealing airflow can be reduced to positively resist the tooth top flow (taking Figure 4 At the same time, since the guide strips 5 are arranged radially, the airflow is guided to rotate with the engine rotor 200, thereby forming a spiral airflow Ha in the opposite direction to the rotation direction RT (or, in the same direction as the rotation direction RV). The spiral airflow Ha moves outward due to the kinetic energy given by the rotor 200, as shown in FIG. Figure 4 As shown, it will move around the rotating shaft 2 in the direction away from the grate tooth sealing structure, and the reverse spiral airflow Ha will resist the invading airflow (with Figure 4 In this way, the energy of the flowing gas generated by the pressure difference between the inside and outside of the bearing cavity 101 can be dissipated, so that a gas flow cycle is formed outside the double-sided sealing structure 10, thereby reducing the leakage of gas into the bearing cavity 101.

[0067] When the pressure inside the bearing cavity 101 is greater than the pressure outside the bearing cavity 101, the right side fluid Fb (oil and gas G2) of the double-sided sealing structure 10 will approach the double-sided sealing structure 10 (the sealing grate structure 1b) and try to leak out. Similar to the previous description, the fluid within the grate tooth height range (oil and gas G2, taking the bottom fluid F1b as an example) will be lifted and flow toward the tooth top along the arc groove, and the fluid at the grate tooth tip (oil and gas G2, taking the top fluid F2b as an example) will also be pushed away from the double-sided sealing structure 10 (the sealing grate structure 1b) by the spiral airflow Hb, forming an oil-gas sealed gas flow cycle. At the same time, the spiral airflow Hb that is disturbed by the guide strip 5b and spirally moves will also be separated from the air due to the centrifugal force, thereby reducing the lubricating oil consumption caused by oil and gas leakage.

[0068] When the sealing assembly of the bearing cavity of an aircraft engine adopts the above-mentioned sealing grate structure or double-sided sealing structure, the sealing effect can be improved at each speed stage, while reducing the demand for the compressor outlet bleed air, and the bearing cavity lubricating oil consumption can be reduced, and the high-temperature sealing gas and lubricating oil cavity oil gas can be blocked. When the compressor bleed air volume is reduced, the overall performance of the machine can be improved, the fuel consumption rate of the engine can be reduced, and the aircraft range can be increased under the same fuel load. The turbine inlet temperature can be reduced, thereby extending the service life of the turbine, extending the engine overhaul and scrapping cycle, and reducing costs. Reducing the bearing cavity lubricating oil consumption can improve the working performance of the bearing and ensure effective lubrication and cooling. At the same time, blocking the high-temperature seal and the lubricating oil cavity oil gas can prevent high-temperature and high-pressure gas from leaking into the bearing cavity, causing the lubricating oil to burn and coke in the bearing cavity.

[0069] 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 sealing grate structure, comprising an annular grate, wherein the annular grate is arranged on the outer peripheral side of the rotating shaft and protrudes toward the stator ring, and the sealing grate structure is used to prevent the fluid from flowing from the first end side of the annular grate to the second end side, characterized in that: The annular comb teeth are inclined toward the first end side; and The sealing comb tooth structure also includes a guide bar, which is arranged on the first end face of the annular comb tooth at the first end side and extends from the bottom side of the annular comb tooth toward the top side. The guide bar has a windward side surface on the windward side relative to the turning direction of the rotating shaft, and the windward side surface guides the bottom fluid on the bottom side to flow from the bottom side to the top side and out from the top side, so that the outflow velocity of the bottom fluid flowing out of the top side has a velocity component pointing from the windward side to the leeward side.

2. The sealing comb tooth structure according to claim 1, characterized in that: The windward side surface enables the outflow velocity of the bottom fluid flowing out from the top side to also have a velocity component flowing toward the stator ring.

3. The sealing comb tooth structure according to claim 1, characterized in that: The windward side has a windward side contour line that is perpendicular to the axial direction of the rotating shaft, and the windward side contour line has an outflow tangent vector at the windward side vertex on the top side for guiding the outflow of fluid, and the angle between the outflow tangent vector and the reverse tangent vector at the windward side vertex pointing from the windward side to the leeward side is α3, 0°<α3≤45°.

4. The sealing comb tooth structure according to claim 1, characterized in that: The windward side surface has a windward side contour line that is perpendicular to the axial direction of the rotating shaft, and the windward side contour line is a smooth curve in an outwardly convex form.

5. The sealing comb tooth structure according to claim 1, characterized in that: The windward side has a windward side contour line that is perpendicular to the axial direction of the rotating shaft. The windward side contour line has an inflow tangent vector at the bottom point of the windward side on the bottom side for guiding the inflow of fluid. The inflow tangent vector is consistent with the reverse tangent vector at the bottom point of the windward side pointing from the windward side to the leeward side.

6. The sealing comb tooth structure according to any one of claims 1 to 5, characterized in that: The windward side surface is parallel to the axial direction of the rotating shaft.

7. The sealing comb tooth structure according to any one of claims 1 to 5, characterized in that: The guide strip has a leeward side surface on the leeward side relative to the deflection point, and the leeward side surface is parallel to the windward side surface.

8. The sealing comb tooth structure according to any one of claims 1 to 5, characterized in that: The sealing comb tooth structure includes a plurality of guide strips evenly distributed along the circumference of the rotating shaft.

9. A double-sided sealing structure, characterized in that: Comprising two sealing comb tooth structures as claimed in any one of claims 1 to 8; The annular grate teeth of the two sealing grate tooth structures are distributed on the outer peripheral side of the rotating shaft along the axial direction of the rotating shaft, and the first end sides of the annular grate teeth of the two sealing grate tooth structures are respectively opposite to the two outer end sides of the two sealing grate tooth structures.

10. An aircraft engine bearing cavity sealing assembly, comprising a stator component and a rotor component, characterized in that: It also includes the double-sided sealing structure as described in claim 9, the stator component and the rotor component respectively provide a stator ring and a rotating shaft, one of the two sealing grate structures of the double-sided sealing structure is used to prevent the compressed gas outside the bearing cavity from flowing from the outside of the bearing cavity to the inside of the bearing cavity through the double-sided sealing structure, and the other of the two sealing grate structures is used to prevent the oil and gas in the bearing cavity from flowing from the inside of the bearing cavity to the outside of the bearing cavity through the double-sided sealing structure.

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