Shunting ring, aero-engine and shunting ring modification method

Abstract

The invention provides a shunting ring, an aero-engine and a shunting ring modification method, the shunting ring is provided with an inner wall surface and an outer wall surface which are arranged around the axial direction, and a front edge line is formed at the joint of the inner wall surface and the outer wall surface. The front edge line is in a periodically changing wave shape, the axial positions of all the positions of the front edge line are the same in the circumferential direction, the radial positions of all the positions of the front edge line are changed in a wave shape, and therefore concave-convex shapes distributed in the circumferential direction are formed at the front edge. The shunting ring can influence a nearby flow field through a front edge wave-shaped structure to form potential disturbance waves, the potential disturbance waves are linearly superposed with potential disturbance waves existing in front of a booster stage guide vane, the mutually counteracted unsteady coupling effect is generated, the potential interference effect between a fan and a booster stage is weakened, and the pneumatic performance of the booster stage of the fan is improved. Meanwhile, when the airflow passes through the front edge line of the shunting ring, the airflow is induced by the front edge line to form a flow direction vortex, and the flow direction vortex is mixed with secondary vortexes such as a large-size fan wake falling vortex, so that the wake interference effect between the fan and the booster stage is weakened, and the flow loss is reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular, to a splitter ring, an aero-engine, and a method for modifying the splitter ring. Background Art

[0002] In a large bypass ratio civil aero-engine fan booster stage, the booster stage is coaxial with the fan, and its radius and blade size are much smaller than those of the fan. The width of the fan outlet wake even exceeds half of the inlet guide vane passage of the booster stage. Therefore, there is a strong large-scale rotor-stator interference effect between the fan, the splitter ring, and the booster stage blades: on the one hand, the large-scale wide wake at the fan outlet will generate strong unsteady flow interference with the flow near the wall surface of the splitter ring, the flow at the inlet of the booster stage, and even the flow of the subsequent stages; on the other hand, there is a mutual potential interference between the fan and the booster stage blade rows due to the propagation of pressure disturbance waves. Both aspects seriously affect the inter-stage matching and aerodynamic performance of the fan booster stage.

[0003] In the fan booster stage, there are two types of flow control technologies: active control and passive control. The advantage of the passive control technology is that it has a simple structure and is easy to implement, and it is more widely applied to aero-engines than the active control technology. At present, few researchers at home and abroad use flow control technology to weaken the harmful effects of the rotor-stator interference effect.

[0004] The inventor's research found that the existing flow control technology is difficult to solve the problem of the deterioration of aerodynamic performance caused by the large-scale unsteady rotor-stator interference effect in the fan booster stage. Summary of the Invention

[0005] The purpose of the present invention is to provide a splitter ring, which can solve the problem of the deterioration of aerodynamic performance caused by the large-scale unsteady rotor-stator interference effect in the fan booster stage existing in the prior art.

[0006] The purpose of the present invention is also to provide an aero-engine, which can solve the problem of the deterioration of aerodynamic performance caused by the large-scale unsteady rotor-stator interference effect in the fan booster stage existing in the prior art.

[0007] The purpose of the present invention is also to provide a method for modifying the splitter ring, which can solve the problem of the deterioration of aerodynamic performance caused by the large-scale unsteady rotor-stator interference effect in the fan booster stage existing in the prior art.

[0008] The embodiments of the present invention can be implemented in the following ways:

[0009] A splitter ring, the splitter ring has an axial direction, a radial direction, and a circumferential direction, and the splitter ring has an inner wall surface and an outer wall surface disposed around the axial direction, and a leading edge line is formed at the connection between the inner wall surface and the outer wall surface;

[0010] The leading edge line is wavy with periodic variations; along the circumferential direction, the axial positions of all points on the leading edge line are the same, and the radial dimensions vary in a wavy pattern.

[0011] Optionally, the leading edge line is a periodic sine curve, and the leading edge line has a plurality of periodic segments distributed along the circumferential direction; within the periodic segment, there are a first leading edge point, a second leading edge point, and a third leading edge point arranged in sequence along the circumferential direction. The first leading edge point is the point with the largest radial dimension within the periodic segment, the third leading edge point is the point with the smallest radial dimension within the periodic segment, and the second leading edge point is the midpoint between the first leading edge point and the third leading edge point.

[0012] Optionally, the outer wall surface and the inner wall surface form an upper cross-sectional profile on the longitudinal section passing through the first leading edge point; the outer wall surface and the inner wall surface form a middle cross-sectional profile on the longitudinal section passing through the second leading edge point, and the outer wall surface and the inner wall surface form a lower cross-sectional profile on the longitudinal section passing through the third leading edge point;

[0013] wherein, the longitudinal section is the plane formed by the axial direction and the radial direction; at least one of the upper cross-sectional profile, the middle cross-sectional profile, and the lower cross-sectional profile is a cubic spline curve.

[0014] Optionally, the upper cross-sectional profile, the middle cross-sectional profile, and the lower cross-sectional profile have a first common tangent point on the inner wall surface;

[0015] The upper cross-sectional profile, the middle cross-sectional profile, and the lower cross-sectional profile have a second common tangent point on the outer wall surface.

[0016] Optionally, one end of the inner wall surface away from the leading edge line has an end point, and the distance between the second leading edge point and the end point in the axial direction is G 1 ; the distance between the second leading edge point and the first common tangent point in the axial direction is G 2 , G 2 ≤G 1 .

[0017] Optionally, the distance between the end point and the first common tangent point in the axial direction is G 3 , 0≤G 3 ≤10%G 1 .

[0018] Optionally, the distance between the first leading edge point and the second leading edge point in the radial direction is H; the distance between the second leading edge point and the third leading edge point in the radial direction is H; 0<H≤50%G 2 .

[0019] Optionally, the distance between the second common tangent point and the second leading edge point in the axial direction is G4 , G 4 = 4G 2 .

[0020] An aeroengine, the aeroengine includes an outer casing, a booster stage hub, a booster stage inlet guide vane, and the above-mentioned splitter ring. The splitter ring is arranged between the outer casing and the booster stage hub, and an outer flow passage is formed between the splitter ring and the outer casing, and an inner flow passage is formed between the splitter ring and the booster stage hub. The booster stage inlet guide vane is arranged at the entrance of the inner flow passage; the number of cycles of the leading edge line in the splitter ring is the same as the number of the booster stage inlet guide vanes.

[0021] A method for modifying a splitter ring, the method for modifying the splitter ring includes:

[0022] Obtain the longitudinal section profile line in the prototype splitter ring to obtain the middle section profile line; the middle section profile line has a second leading edge point, an inner wall profile line, and an outer wall profile line;

[0023] Select the axial position of the first common tangent point according to the axial distance between the second leading edge point and the end point on the side of the inner wall profile line away from the second leading edge point; the first common tangent point is located on the inner wall profile line;

[0024] Determine the second common tangent point on the outer wall profile line according to the position of the first common tangent point;

[0025] Select the positions of the first leading edge point and the third leading edge point according to the position of the second leading edge point and the position of the first common tangent point; wherein, the axial position of the first leading edge point is the same as the axial position of the second leading edge point, and the radial dimension of the first leading edge point is greater than the radial dimension of the second leading edge point; the axial position of the third leading edge point is the same as the axial position of the second leading edge point, and the radial dimension of the third leading edge point is less than the radial dimension of the second leading edge point;

[0026] Construct the upper section profile line according to the first common tangent point, the first leading edge point, and the second common tangent point;

[0027] Construct the lower section profile line according to the first common tangent point, the third leading edge point, and the second common tangent point;

[0028] Determine the circumferential positions among the upper section profile line, the middle section profile line, and the lower section profile line according to the circumferential angle corresponding to one cycle of the leading edge line on the splitter ring; wherein, along the circumferential direction of the splitter ring, the upper section profile line and the lower section profile line are respectively located on both sides of the middle section profile line;

[0029] Construct a leading edge line based on the first leading edge point position, the second leading edge point position, and the third leading edge point position, and the leading edge line is a wave shape with periodic changes;

[0030] Obtain a new type of splitter ring configuration based on the upper cross-sectional profile line, the middle cross-sectional profile line, the lower cross-sectional profile line, and the leading edge line.

[0031] The beneficial effects of the splitter ring, aeroengine, and splitter ring modification method provided by the embodiments of the present invention include:

[0032] The embodiments of the present invention provide a splitter ring. The splitter ring has an axial direction, a radial direction, and a circumferential direction, and the splitter ring has an inner wall surface and an outer wall surface arranged around the axial direction. The connection between the inner wall surface and the outer wall surface forms a leading edge line. The leading edge line is a wave shape with periodic changes, and along the circumferential direction, the axial positions of each part of the leading edge line are the same, and the radial positions change in a wave shape. Thus, an uneven shape distributed along the circumferential direction is formed at the leading edge. By shaping the leading edge line of the splitter ring as described above, on the one hand, the potential disturbance wave can be formed in the nearby flow field through the leading edge wave structure, and linearly superposed with the potential disturbance wave existing in front of the guide vane of the booster stage, generating an unsteady coupling effect of mutual cancellation, weakening the potential interference effect between the fan and the booster stage, and improving the aerodynamic performance of the fan booster stage; on the other hand, when the airflow passes through the leading edge line of the splitter ring, a flow vortex is induced by the leading edge line, and it mixes with secondary vortices such as the shedding vortex of the large-size fan wake, which is beneficial to weakening the wake interference effect between the fan and the booster stage and reducing the flow loss.

[0033] The embodiments of the present invention also provide an aeroengine, which includes the above-mentioned splitter ring. Since this aeroengine includes the above-mentioned splitter ring, it also has the beneficial effects of being able to effectively weaken the large-scale unsteady rotor-stator interference effect, reduce the flow loss, and improve the performance of the aeroengine.

[0034] The embodiments of the present invention also provide a splitter ring modification method. Through this splitter ring modification method, the prototype splitter ring can be modified into a new type of splitter ring with a wave-shaped leading edge line, so as to produce the beneficial effects of effectively weakening the large-scale unsteady rotor-stator interference effect, reducing the flow loss, and improving the performance of the aeroengine through this new type of splitter ring. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] After reading the detailed description of the embodiments of the present disclosure in combination with the following drawings, the above features and advantages of the present invention can be better understood. In the drawings, the components are not necessarily drawn to scale, and components with similar related characteristics or features may have the same or similar reference numerals.

[0036] Figure 1 Shows a schematic structural diagram at the fan booster stage of an aeroengine provided according to an aspect of the present invention;

[0037] Figure 2 Shows a three-dimensional schematic diagram of the shunt ring part structure provided according to one aspect of the present invention;

[0038] Figure 3 Shows a schematic diagram of the structure at the longitudinal section position of the shunt ring provided according to one aspect of the present invention;

[0039] Figure 4 Shows a schematic diagram of the longitudinal section position in the three-dimensional image of the flow ring provided according to one aspect of the present invention;

[0040] Figure 5 Shows a superimposed schematic diagram of the upper section profile, the middle section profile, and the lower section profile on the same longitudinal section provided according to one aspect of the present invention.

[0041] Reference numerals:

[0042] 10 - Aeroengine; 100 - Shunt ring; 111 - Outer wall surface; 112 - Inner wall surface; 113 - Leading edge line; 114 - First leading edge point; 115 - Second leading edge point; 116 - Third leading edge point; 117 - Periodic segment; 118 - End point; 121 - Upper section profile; 122 - Middle section profile; 123 - Lower section profile; 124 - First common tangent point; 125 - Second common tangent point; 126 - First longitudinal section; 127 - Second longitudinal section; 128 - Third longitudinal section; 211 - Outer casing; 212 - Booster stage hub; 213 - Booster stage inlet guide vane; 214 - Outer flow path; 215 - Inner flow path; 216 - Fan; 217 - Booster stage casing; 218 - Outer hub; 219 - First stage rotor of booster stage; 220 - First stage stator of booster stage; 221 - Second stage rotor of booster stage; 222 - Second stage stator of booster stage. Detailed implementation manners

[0043] The following describes the present invention in detail 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 imposing any limitation on the protection scope of the present invention.

[0044] In the description of the present invention, it should be noted that if terms such as "upper", "lower", "inner", "outer", "vertical", etc. are used to indicate the orientation or positional relationship, it is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of the present invention is usually placed during use, 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. Therefore, it should not be construed as a limitation to the present invention.

[0045] At the same time, it should be noted that if terms such as "first", "second", etc. are only used for differential description and should not be construed as indicating or implying relative importance.

[0046] In the description of the present invention, it should also be noted that unless otherwise clearly specified or limited, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it may be a fixed connection, an integral connection, or a detachable connection; it may be a mechanical connection or an electrical connection; it may be a direct connection or an indirect connection through an intermediate medium, or the communication inside two components, etc. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0047] The explanations of the terms that may appear in the description of the present invention are as follows:

[0048] Fan booster: A key component of an aeroengine, including an inner flow path and an outer flow path. The main function of the inner flow path is to pressurize the air flow and introduce it into the high-pressure compressor, and the main function of the outer flow path is to discharge the pressurized air flow outside the engine to provide thrust for the engine.

[0049] Splitter: A ring structure in the fan booster that separates the inner and outer flow path air flows.

[0050] Rotor-stator interaction: The fan booster is generally composed of an alternating arrangement of rotor blade rows and stator blade rows. When adjacent blade rows move relative to each other, there is an unsteady interaction between the rotor and the stator, which is also called rotor-stator interaction and is an inherent unsteady phenomenon in the fan booster.

[0051] Figure 1 The structural schematic diagram of the fan booster of the aeroengine 10 provided in this embodiment is shown. Figure 2 The three-dimensional schematic diagram of a partial structure of the splitter 100 provided in this embodiment is shown. Please refer to Figure 1 and Figure 2 , this embodiment provides a splitter 100, and correspondingly, also provides an aeroengine 10.

[0052] The aeroengine 10 includes a splitter ring 100. Meanwhile, the aeroengine 10 further includes an outer casing 211, a booster stage hub 212, and a booster stage inlet guide vane 213. The splitter ring 100 is disposed between the outer casing 211 and the booster stage hub 212. An outer duct passage 214 is formed between the splitter ring 100 and the outer casing 211, and an inner duct passage 215 is formed between the splitter ring 100 and the booster stage hub 212. In other words, the space between the outer casing 211 and the booster stage hub 212 is divided into the inner duct passage 215 and the outer duct passage 214 by the splitter ring 100. The booster stage inlet guide vane 213 is disposed at the entrance of the inner duct passage 215, so as to boost the gas entering the inner duct passage 215 through the booster stage inlet guide vane 213. Meanwhile, the aeroengine 10 further includes a booster stage casing 217 and an outer duct hub 218. The outer wall surface 111 of the splitter ring 100 is connected to the outer duct hub 218, and the inner wall surface 112 of the splitter ring 100 is connected to the booster stage casing 217.

[0053] Further, a fan 216 is disposed in front of the splitter ring 100. An air flow flowing rightward (such as the left - right direction shown in Figure 1 ) is generated by the fan 216. Due to the effect of the splitter ring 100, this air flow is divided into two paths at the splitter ring 100. One path continues to flow along the outer duct passage 214, and the other path continues to flow along the inner duct passage 215. A plurality of booster stage stator - rotors are also disposed in the inner duct passage 215. The plurality of booster stage stator - rotors are sequentially disposed along the inner duct passage 215. Specifically, a booster stage first - stage rotor 219, a booster stage first - stage stator 220, a booster stage second - stage rotor 221, and a booster stage second - stage stator 222 are sequentially disposed backward from the booster stage inlet guide vane 213. The booster stage inlet guide vane 213, the booster stage first - stage rotor 219, the booster stage first - stage stator 220, the booster stage second - stage rotor 221, and the booster stage second - stage stator 222 can be collectively referred to as the booster stage.

[0054] The splitter ring 100 has an axial direction (such as the Z - direction shown in Figure 1 ), a radial direction (such as the R - direction shown in Figure 1 and Figure 2 ), and a circumferential direction (such as the direction shown in Figure 2in the described C direction), and the splitter ring 100 has an inner wall surface 112 and an outer wall surface 111 arranged around the axis. The connection between the inner wall surface 112 and the outer wall surface 111 forms a leading edge line 113. The leading edge line 113 is a wavy shape with periodic changes, and along the circumferential direction, the axial positions of each part of the leading edge line 113 are the same, and the radial positions change in a wavy shape, so that an uneven shape distributed along the circumferential direction is formed at the leading edge. By shaping the leading edge line 113 of the splitter ring 100 in the above way, on the one hand, the potential disturbance wave can be formed in the nearby flow field through the leading edge wavy structure, and linearly superposed with the potential disturbance wave existing in front of the inlet guide vane 213 of the booster stage, generating an unsteady coupling effect of mutual cancellation, weakening the potential interference effect (i.e., an unsteady rotor-stator interference effect) between the fan 216 and the booster stage, and improving the aerodynamic performance of the fan booster stage; on the other hand, when the air flow passes through the leading edge line 113 of the splitter ring 100, a flow vortex is induced to form through the leading edge line 113, and is mixed with secondary vortices such as the wake shedding vortex of the large-size fan 216, which is beneficial to weakening the wake interference effect between the fan 216 and the booster stage and reducing the flow loss. It should be noted that in the description of this embodiment, if "leading edge" is mentioned, it means the part where the leading edge line 113 is located.

[0055] Specifically, the splitter ring 100 is in a ring shape, Figure 2 Only the structure under a partial central angle is shown.

[0056] In this embodiment, the leading edge line 113 is a sine curve with periodic changes, which has a plurality of periodic segments 117 distributed along the circumferential direction. Each periodic segment 117 has a first leading edge point 114, a second leading edge point 115, and a third leading edge point 116 arranged in sequence along the circumferential direction. The first leading edge point 114 is the point with the largest radial dimension within the periodic segment 117, that is, the peak point of the sine curve; the third leading edge point 116 is the point with the smallest radial dimension within the periodic segment 117, that is, the trough point of the sine curve; the second leading edge point 115 is the midpoint between the first leading edge point 114 and the second leading edge point 115, that is, the leading edge point with the same radial dimension as the initial phase point of the sine curve.

[0057] Specifically, the number of periods T of the leading edge line 113 is the same as the number of inlet guide vanes 213 of the booster stage, so that the potential disturbance wave formed in the flow field near the uneven structure formed by the leading edge line 113 of the splitter ring 100 is linearly superposed with the potential disturbance wave existing in front of the inlet guide vane 213 of the booster stage, achieving the best cancellation effect. Since the number of periods T of the leading edge line 113 is the same as the number of inlet guide vanes 213 of the booster stage, the phase angle θ corresponding to each periodic segment 117 = 360 / T.

[0058] Meanwhile, the sine curve formed by the leading edge line 113 is highly smooth, avoiding the deterioration of the aerodynamic performance of the flow splitting ring 100 caused by the non-smooth problem. At the same time, the three-dimensional coordinates R(s), C(s), and Z(s) of this curve in the radial-circumferential-axial cylindrical coordinate system satisfy the following functional relationships:

[0059] 1) The dimensionless independent variable s varies within the interval [0, 1], representing the process of the sine curve changing from the starting point to the ending point within the entire ring range;

[0060] 2) R(s) = R 0 -Hsin(360sT); C(s) = 360s; Z(s) = Z 0 .

[0061] In the formula: R 0 and Z 0 respectively represent the radial coordinate and the axial coordinate of the second leading edge point 115 in the radial-circumferential-axial cylindrical coordinate system.

[0062] Figure 3 FIG. shows a schematic structural view of the longitudinal section position of the flow splitting ring 100 provided in this embodiment. Figure 4 This is a schematic view of the longitudinal section position in the three-dimensional image of the flow splitting ring 100 provided in this embodiment. And in Figure 3 and Figure 4 , the part between two adjacent dotted lines is used to represent a periodic segment 117. In other words, the central angle formed by two adjacent dotted lines is θ. Figure 5 FIG. shows a superimposed schematic view of the upper section profile 121, the middle section profile 122, and the lower section profile 123 on the same longitudinal section. Please refer to Figures 1 - 5 . In this embodiment, the outer wall surface 111 and the inner wall surface 112 form the upper section profile 121 on the longitudinal section passing through the first leading edge point 114. Correspondingly, the upper section profile 121 includes the first leading edge point 114, the profile part located at the outer wall surface 111, and the profile part located at the inner wall surface 112. At the same time, the longitudinal section where the upper section profile 121 is located is the first longitudinal section 126; the outer wall surface 111 and the inner wall surface 112 form the middle section profile 122 on the longitudinal section passing through the second leading edge point 115. Correspondingly, the middle section profile 122 includes the second leading edge point 115, the profile part located at the outer wall surface 111, and the profile part located at the inner wall surface 112. At the same time, the longitudinal section where the middle section profile 122 is located is the second longitudinal section 127; the outer wall surface 111 and the inner wall surface 112 form the lower section profile 123 on the longitudinal section passing through the third leading edge point 116. Correspondingly, the lower section profile 123 includes the third leading edge point 116, the profile part located at the outer wall surface 111 (which can also be called the outer wall profile) and the profile part located at the inner wall surface 112 (which can also be called the inner wall profile). At the same time, the longitudinal section where the lower section profile 123 is located is the third longitudinal section 128.

[0063] It should be noted that in the description of this embodiment, the "longitudinal section" is the plane formed by the axial direction and the radial direction. Different longitudinal sections can be formed at different circumferential positions, that is, the first longitudinal section 126, the second longitudinal section 127, and the third longitudinal section 128 are longitudinal sections at different circumferential positions. Therefore, on the flow splitting ring 100, the upper section profile line 121, the middle section profile line 122, and the lower section profile line 123 are located on different longitudinal sections. Therefore, in this embodiment Figure 5 The superimposed schematic diagram of the upper section profile line 121, the middle section profile line 122, and the lower section profile line 123 shown on the same longitudinal section can be regarded as the schematic diagram formed by projecting the upper section profile line 121 and the lower section profile line 123 along the circumferential direction onto the second longitudinal section 127.

[0064] At least one of the upper section profile line 121, the middle section profile line 122, and the lower section profile line 123 is a cubic spline curve. Specifically, the cubic spline curve is a spline curve composed of a cubic spline function. The cubic spline curve is given a partition a = x 0 <x 1 <...<x n-1 <x n = b on the interval [a, b]. The function F(x) on this interval satisfies the following conditions:

[0065] 1) In each small interval [x i-1 , x i (i = 1, 2,..., n), F(x) is a cubic polynomial function respectively, that is, F(x) = a 3 x 3 + a 2 x 2 + a 1 x 1 + a 0 , where a 0 , a 1 , a2 and a 3 are all constants, and a 3 ≠0;

[0066] 2) At the node F(x), F (k) (x i - 0) = F (k) (x i + 0), k = 0, 1, 2, that is, the cubic polynomial function on the small interval is second-order continuous at the node x i ;

[0067] 3) The node (x i , y i ) satisfies the condition y i = F(x i)(i = 0, 1, 2, ..., n); where y i represents the ordinate corresponding to x i in the function F(x).

[0068] In this embodiment, the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123 are all cubic spline curves.

[0069] Furthermore, the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123 have a first common tangent point 124 on the inner wall surface 112. It should be noted that since the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123 are actually on different longitudinal sections, the so-called first common tangent point 124 in this embodiment is the intersection point generated after the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123 are projected onto the same longitudinal section (such as Figure 5 the superimposed schematic diagram shown). In other words, the axial coordinates and radial coordinates of the first common tangent point 124 on the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123 are the same, while the circumferential coordinates are different. At the same time, as Figure 5 shown, the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123 have a common tangent line L1 at the first common tangent point 124.

[0070] Since the axial positions of all points on the leading-edge line 113 are the same, the axial coordinates of the first leading-edge point 114, the second leading-edge point 115, and the third leading-edge point 116 are the same. As Figure 5 shown, the distances G 2 from the first leading-edge point 114, the second leading-edge point 115, and the third leading-edge point 116 to the first common tangent point 124 in the axial direction are the same. Specifically, one end of the inner wall surface 112 away from the leading-edge line 113 has an end point 118, and the distance between the second leading-edge point 115 and the end point in the axial direction is G 1 , G 2 ≤G 1 , that is, the first common tangent point 124 can coincide with the end point 118 or can be set on the front side of the end point 118. In this embodiment, the first common tangent point 124 coincides with the end point 118.

[0071] Furthermore, the distance between the end point 118 and the first common tangent point 124 in the axial direction is G 3 , 0 ≤ G 3 ≤ 10%G 1 . Specifically, the first common tangent point 124 is preferably set close to the end point 118, and the distance from it to the end point 118 does not exceed the distance G 110%. In this embodiment, since the first common tangent point 124 coincides with the end point 118, the distance G between the end point 118 and the first common tangent point 124 in the axial direction 3 is 0. It can be understood that in some other embodiments, the first common tangent point 124 can also be set at 5% G1 or 10% G1 in the axial direction according to requirements.

[0072] Furthermore, as Figure 5 shown, the distance between the first leading edge point 114 and the second leading edge point 115 in the radial direction is H, and the distance between the second leading edge point 115 and the third leading edge point 116 in the radial direction is also H, where 0 < H ≤ 50% G 2 . In other words, the amplitude of the leading edge line 113 is H. In this embodiment, the amplitude H is set to 40% G 2 . It can be understood that in some other embodiments, the amplitude H can also be set to 10% G 2 , 30% G 2 or 50% G 2 .

[0073] In this embodiment, the upper cross-sectional profile 121, the middle cross-sectional profile 122, and the lower cross-sectional profile 123 have a second common tangent point 125 on the outer wall surface 111. It should be noted that since the upper cross-sectional profile 121, the middle cross-sectional profile 122, and the lower cross-sectional profile 123 are actually in different longitudinal sections, the second common tangent point 125 referred to in this embodiment is the common tangent point generated after the upper cross-sectional profile 121, the middle cross-sectional profile 122, and the upper cross-sectional profile 121 are projected onto the same longitudinal section (such as Figure 5 the superimposed schematic diagram shown). In other words, the axial coordinates and radial coordinates of the second common tangent point 125 on the upper cross-sectional profile 121, the middle cross-sectional profile 122, and the lower cross-sectional profile 123 are the same, and the circumferential coordinates are different. At the same time, as Figure 5 shown, the upper cross-sectional profile 121, the middle cross-sectional profile 122, and the lower cross-sectional profile 123 have a common tangent L2 at the second common tangent point 125.

[0074] Furthermore, the distance between the second common tangent point 125 and the second leading edge point 115 in the axial direction is G 4 , G 4 = 4G 2 .

[0075] The embodiment of the present invention also provides a method for modifying a flow splitting ring. By this method for modifying a flow splitting ring, it is helpful to modify an existing prototype flow splitting ring into a structure as Figure 2The novel flow dividing ring shown. Specifically, in this embodiment, the prototype flow dividing ring is a flow dividing ring with a circular leading edge line, where the axial positions and radial dimensions at various points on the leading edge line are the same. The novel flow dividing ring is a flow dividing ring with a leading edge line 113 in the shape of a sine curve, where the axial positions at various points on the leading edge line 113 are the same and the radial dimensions vary periodically.

[0076] The specific steps of the flow dividing ring modification method provided in this embodiment include:

[0077] S01: Obtain the longitudinal section profile line in the prototype flow dividing ring to obtain the middle section profile line 122.

[0078] Make a radial-axial plane on the prototype flow dividing ring to intercept the longitudinal section. The inner wall surface 112, outer wall surface 111, and leading edge line 113 of the prototype flow dividing ring form a longitudinal section profile line on this longitudinal section. Take this longitudinal section profile line as the middle section profile line 122 of the novel flow dividing ring. The intersection point of the middle section profile line 122 and the leading edge line 113 is the second leading edge point 115, and the part of it located on the inner wall surface 112 is the inner wall surface 112 profile line, and the part of it located on the outer wall surface 111 is the outer wall surface 111 profile line.

[0079] S02: Select the axial position of the first common tangent point 124 according to the axial distance between the second leading edge point 115 and the end point on the side of the inner wall surface 112 profile line away from the second leading edge point 115.

[0080] When the end point position and the second leading edge point 115 position are determined, the axial distance G between the second leading edge point 115 and the end point can be obtained from the middle section profile line 122. 1 The specific value. The axial position of the first common tangent point 124 needs to be located on the front side of the end point (i.e., the left side as in Figure 5 ), and is set close to the end point. Specifically, the axial distance between the first common tangent point 124 and the second leading edge point 115 is G 2 , G 2 ≤G 1 ; The axial distance between the first common tangent point 124 and the end point is G 3 , 0≤G 3 ≤10%G 1 . Select a point that meets the above dimensional requirements from the inner wall surface 112 profile line as the first common tangent point 124. In other words, the axial position of the first common tangent point 124 can be selected according to the above requirements and its own needs. After the axial position of the first common tangent point 124 is determined, the specific position of the first common tangent point 124 can be determined on the inner wall surface 112 profile line.

[0081] S03: Determine the second common tangent point 125 on the outer wall surface 111 profile line according to the position of the first common tangent point 124.

[0082] At the rear side of the second leading edge point 115 (i.e., the right side as in Figure 5 ), make a vertical line at an axial distance of 4G from the second leading edge point 115 to obtain the intersection point of this vertical line and the profile line of the outer wall surface 111, and this intersection point is used as the second common tangent point 125. 2

[0083] S04: Select the positions of the first leading edge point 114 and the third leading edge point 116 according to the position of the second leading edge point 115 and the position of the first common tangent point 124.

[0084] Make a vertical line through the second leading edge point 115. The axial positions of all points on this vertical line are the same, while the radial positions are different. Take the point at a distance of H above the second leading edge point 115 on the vertical line as the first leading edge point 114, and at the same time take the point at a distance of H below the second leading edge point 115 on the vertical line as the third leading edge point 116. In this way, the first leading edge point 114, the second leading edge, and the third leading edge point 116 have the same axial position. At the same time, the radial dimension of the first leading edge point 114 is greater than the radial dimension of the second leading edge point 115, and the radial dimension of the third leading edge point 116 is less than the radial dimension of the second leading edge point 115. Optionally, 0 < H ≤ 50%G 2 , in this embodiment, H = 40%G 2 .

[0085] S05: Construct the upper cross-section profile line 121 according to the first common tangent point 124, the first leading edge point 114, and the second common tangent point 125.

[0086] The upper cross-section profile line 121 is a cubic spline curve. Construct a cubic spline curve passing through the first common tangent point 124, the first leading edge point 114, and the second common tangent point 125 according to the first common tangent point 124, the first leading edge point 114, and the second common tangent point 125. And the tangent of this cubic spline curve at the first common tangent point is the common tangent line L1, and the tangent at the second common tangent point 125. is the common tangent line L2. Take the cubic spline curve meeting the above conditions as the upper cross-section profile line 121.

[0087] S06: Construct the lower cross-section profile line 123 according to the first common tangent point 124, the third leading edge point 116, and the second common tangent point 125.

[0088] The upper cross-section profile line 121 is a cubic spline curve. Construct a cubic spline curve passing through the first common tangent point 124, the third leading edge point 116, and the second common tangent point 125 according to the first common tangent point 124, the third leading edge point 116, and the second common tangent point 125. And the tangent of this cubic spline curve at the first common tangent point is the common tangent line L1, and the tangent at the second common tangent point 125. is the common tangent line L2. Take the cubic spline curve meeting the above conditions as the lower cross-section profile line 123.

[0089] ​S07: Determine the circumferential positions of the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123 according to the circumferential angle corresponding to one period of the leading-edge line 113 on the flow-dividing ring 100.

[0090] The number of periods of the leading-edge line 113 is the number of blades of the inlet guide vane 213 of the booster stage. Thus, according to the number of blades of the inlet guide vane 213 of the aero-engine 10 to which the flow-dividing ring 100 is applied, the circumferential angle θ corresponding to one period can be obtained. Within this circumferential angle θ range, the middle-section profile line 122, the upper-section profile line 121, the middle-section profile line 122, the lower-section profile line 123, and the middle-section profile line 122 are evenly distributed, so as to determine the circumferential positions of the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123 within one period, and further obtain the circumferential positions of the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123 on one week of the flow-dividing ring 100.

[0091] S08: Construct the leading-edge line 113 according to the positions of the first leading-edge point 114, the second leading-edge point 115, and the third leading-edge point 116.

[0092] When the axial positions of the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123 are determined, the positions of the first leading-edge point 114, the second leading-edge point 115, and the third leading-edge point 116 are also determined. Thus, a smooth periodically varying wavy curve passing through the first leading-edge point 114, the second leading-edge point 115, and the third leading-edge point 116 can be constructed as the leading-edge line 113.

[0093] It should be noted that in this embodiment, the positions of the first leading-edge point 114, the second leading-edge point 115, and the third leading-edge point 116 are obtained by determining the circumferential positions of the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123. It can be understood that in other embodiments, the positions of the first leading-edge point 114, the second leading-edge point 115, and the third leading-edge point 116 can also be directly determined by the circumferential angle, and then the circumferential positions of the upper-section profile line 121, the middle-section profile line 122, and the lower-section profile line 123 are determined according to the positions of the first leading-edge point 114, the second leading-edge point 115, and the third leading-edge point 116. In other words, the execution order of step S07 and step S08 is not limited by this embodiment.

[0094] S09: Obtain the configuration of the new flow-dividing ring 100 according to the upper-section profile line 121, the middle-section profile line 122, the lower-section profile line 123, and the leading-edge line 113.

[0095] The upper cross-section profile line 121, the middle cross-section profile line 122, and the lower cross-section profile line 123 are arranged in the longitudinal sections at different circumferential positions, and then stacked along the leading edge line 113, so as to obtain the new splitter ring 100 with a concave-convex structure in the radial direction at the leading edge.

[0096] The splitter ring 100, the aeroengine 10, and the modification method of the splitter ring 100 provided by the embodiments of the present invention. By setting the leading edge of the splitter ring 100 to a new configuration with a concave-convex structure in the radial direction and the leading edge line 113 being a sinusoidal curve with periodic changes, on the one hand, the potential disturbance wave can be formed by the leading edge wavy protrusion affecting the nearby flow field, and linearly superposed with the potential disturbance wave existing in front of the inlet guide vane 213 of the booster stage, generating an unsteady coupling effect of mutual cancellation, weakening the potential interference effect between the fan 216 and the booster stage, and improving the aerodynamic performance of the fan 216 booster stage; on the other hand, the air flow passing through the leading edge protrusion structure of the splitter ring 100 will induce the formation of streamwise vortices, which will mix with the secondary vortices such as the wake shedding vortices of the large-size fan 216, being beneficial to weakening the wake interference effect between the fan 216 and the booster stage and reducing the flow loss.

[0097] The above is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A splitter ring, the splitter ring having an axial direction, a radial direction, and a circumferential direction, and the splitter ring having an inner wall surface and an outer wall surface disposed around the axial direction, a leading edge line being formed at the connection of the inner wall surface and the outer wall surface; Characterized in that, the leading edge line is a wavy shape that changes periodically; along the circumferential direction, the axial positions of each part of the leading edge line are the same, and the radial dimensions change in a wavy shape.

2. The splitter ring according to claim 1, Characterized in that, the leading edge line is a periodic sine curve, and the leading edge line has a plurality of periodic segments distributed along the circumferential direction; within the periodic segment, a first leading edge point, a second leading edge point, and a third leading edge point are sequentially arranged along the circumferential direction, the first leading edge point being the point with the largest radial dimension within the periodic segment, the third leading edge point being the point with the smallest radial dimension within the periodic segment, and the second leading edge point being the midpoint between the first leading edge point and the third leading edge point.

3. The splitter ring according to claim 2, Characterized in that, the outer wall surface and the inner wall surface form an upper section profile in a longitudinal section passing through the first leading edge point; the outer wall surface and the inner wall surface form a middle section profile in a longitudinal section passing through the second leading edge point, and the outer wall surface and the inner wall surface form a lower section profile in a longitudinal section passing through the third leading edge point; wherein, the longitudinal section is a plane formed by the axial direction and the radial direction; at least one of the upper section profile, the middle section profile, and the lower section profile is a cubic spline curve.

4. The splitter ring according to claim 3, Characterized in that, the upper section profile, the middle section profile, and the lower section profile have a first common tangent point on the inner wall surface; the upper section profile, the middle section profile, and the lower section profile have a second common tangent point on the outer wall surface.

5. The splitter ring according to claim 4, Characterized in that, One end of the inner wall surface away from the leading edge line has an end point, and the distance between the second leading edge point and the end point in the axial direction is G 1 ; the distance between the second leading edge point and the first common tangent point in the axial direction is G 2 , G 2 ≤G 1 .

6. The splitter ring according to claim 5, Characterized in that, The distance between the endpoint and the first common tangent point in the axial direction is G 3 , 0 ≤ G 3 ≤ 10%G 1 .

7. The splitter ring according to claim 5, Characterized in that, The distance between the first leading edge point and the second leading edge point in the radial direction is H; the distance between the second leading edge point and the third leading edge point in the radial direction is H; 0 < H ≤ 50%G 2 .

8. The splitter ring according to claim 5, Characterized in that, The distance between the second common tangent point and the second leading edge point in the axial direction is G 4 , G 4 = 4G 2 .

9. An aeroengine, Characterized in that, the aeroengine includes an outer casing, a booster stage hub, a booster stage inlet guide vane, and a splitter ring according to any one of claims 1 - 8, the splitter ring being disposed between the outer casing and the booster stage hub, and an outer bypass passage being formed between the splitter ring and the outer casing, and an inner bypass passage being formed between the splitter ring and the booster stage hub, the booster stage inlet guide vane being disposed at the entrance of the inner bypass passage; the number of periods of the leading edge line in the splitter ring is the same as the number of the booster stage inlet guide vanes.

10. A method for modifying a splitter ring, Characterized in that, the method for modifying the splitter ring includes: acquiring the longitudinal section profile in the prototype splitter ring to obtain the middle section profile; the middle section profile has a second leading edge point, an inner wall surface profile, and an outer wall surface profile; selecting the axial position of a first common tangent point according to the axial distance between the second leading edge point and the end point on the side of the inner wall surface profile away from the second leading edge point; the first common tangent point is located on the inner wall surface profile; Determine a second common tangent point on the outer wall profile line according to the position of the first common tangent point; Select the positions of a first leading edge point and a third leading edge point according to the position of the second leading edge point and the position of the first common tangent point; wherein, the axial position of the first leading edge point is the same as the axial position of the second leading edge point, and the radial dimension of the first leading edge point is greater than the radial dimension of the second leading edge point; the axial position of the third leading edge point is the same as the axial position of the second leading edge point, and the radial dimension of the third leading edge point is less than the radial dimension of the second leading edge point; Construct an upper section profile line according to the first common tangent point, the first leading edge point and the second common tangent point; Construct a lower section profile line according to the first common tangent point, the third leading edge point and the second common tangent point; Determine the circumferential positions among the upper section profile line, the middle section profile line and the lower section profile line according to the circumferential angle corresponding to one period of the leading edge line on the flow splitting ring; wherein, along the circumference of the flow splitting ring, the upper section profile line and the lower section profile line are respectively located on both sides of the middle section profile line; Construct a leading edge line according to the positions of the first leading edge point, the second leading edge point and the third leading edge point, and the leading edge line is a wavy line with periodic changes; Obtain a new flow splitting ring configuration according to the upper section profile line, the middle section profile line, the lower section profile line and the leading edge line.

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