A compressor stator vane cascade with a ribbed vortex generator array arranged on the endwall of the channel.

Abstract

This invention belongs to the field of aero-engine technology, specifically relating to a compressor stator blade cascade with a ribbed vortex generator array arranged on the endwall of the passageway. It includes a passageway endwall and multiple stator blades and blade root leading edges disposed on the endwall. Multiple micro-ribbed vortex generator arrays are also disposed on the endwall. Each micro-ribbed vortex generator array includes multiple equidistant parallel oblique ribs, with 6 to 16 oblique ribs per array. The perpendicular distance between the leading edge of the micro-ribbed vortex generator array and the tangent of the mid-arc line at the corresponding blade root leading edge is 0.05l to 0.15l, and the tangential distance between the leading edge of the ribbed vortex generator array and the corresponding blade root leading edge is -0.1l to 0.1l. The width of the ribbed vortex generator array is 0.3δ to 0.6δ. This invention suppresses boundary layer separation and the formation of corner passage vortices, thereby achieving the purpose of controlling corner separation.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine technology, specifically relating to a compressor stator vane cascade with a ribbed vortex generator array arranged on the endwall of the channel. Background Technology

[0002] The demand for high thrust-to-weight ratio in aero-engines is driving the development of compressors towards higher loads and lower aspect ratios. Increased stage load manifests as enhanced axial and lateral pressure gradients, causing low-energy fluid within the flow path to accumulate on the blade suction surface and endwall corner regions, inducing corner separation. Corner flow separation leads to flow path blockage, blade load, and reduced diffuser capacity, resulting in decreased total pressure loss and efficiency, and in severe cases, engine stall and surge. Therefore, suppressing compressor corner separation is crucial for improving compressor performance and operational safety.

[0003] Currently, flow control technologies for compressor stator vane cascade corner separation can be divided into two main categories: active control and passive control.

[0004] Active flow control technology requires external energy injection to control the flow field. It mainly includes boundary layer suction technology, plasma excitation technology, and synthetic jet technology. Active control technology requires monitoring the operating status of the compressor and relies on additional adjustment mechanisms to control flow separation, which makes it difficult to promote in engineering applications.

[0005] Passive flow control technology does not require external energy and relies on structural design to achieve flow control. It mainly includes vortex generators, blade fences, blade root slots, and endwall shapes. Traditional vortex generators with blade or wedge-shaped structures introduce additional losses to varying degrees while separating the control angle region. How to find a balance between aerodynamic gain and additional losses has always been a technical bottleneck that passive control methods need to overcome.

[0006] The purpose of this invention is to suppress boundary layer separation and the formation of corner channel vortices with almost no additional losses, thereby effectively suppressing corner separation of the compressor stator vane cascade. Therefore, a compressor stator vane cascade with a ribbed vortex generator array arranged on the channel endwall is proposed. Summary of the Invention

[0007] The purpose of this invention is to provide a compressor stator vane cascade with a ribbed vortex generator array arranged on the endwall of the channel, which can suppress boundary layer separation and the formation of corner channel vortices, thereby achieving the purpose of controlling corner separation.

[0008] The specific technical solution adopted by this invention is as follows:

[0009] A compressor stator blade cascade with a ribbed vortex generator array arranged on the endwall of the channel includes a channel endwall and multiple stator blades and blade root leading edges disposed on the channel endwall. The channel endwall is also provided with multiple micro ribbed vortex generator arrays, each comprising multiple equidistant parallel oblique ribs. Compared with traditional "vortex generators", the micro ribbed vortex generator array used in this invention utilizes the accumulation effect of multiple micro vortex generators to accumulate and form large-scale, high-intensity induced vortices downstream. Therefore, the geometric dimensions can be smaller than those of traditional vortex generators, resulting in less additional losses and further improving the aerodynamic performance of the blade cascade.

[0010] The micro ribbed eddy current generator array includes 6 to 16 oblique ribs.

[0011] The vertical distance between the leading edge of the micro ribbed vortex generator array and the tangent of the middle arc line at the corresponding leading edge of the blade root is 0.05l to 0.15l.

[0012] The distance between the leading edge of the ribbed vortex generator array and the corresponding leading edge of the blade root in the tangential direction is -0.1l to 0.1l.

[0013] The width of the ribbed eddy current generator array is 0.3δ to 0.6δ.

[0014] The multiple oblique ribs are arranged parallel to the tangent direction of the arc line of the corresponding stator blade at the leading edge of the blade root.

[0015] The angle γ between the extension direction of the oblique rib and the tangent direction of the middle arc at the corresponding leaf root leading edge is 30° to 60°.

[0016] The cross-section of each of the oblique ribs is triangular, with the height n of the triangle being 0.05δ to 0.15δ and the base m being 0.05δ to 0.15δ.

[0017] The spacing p between two adjacent oblique ribs is 0.04δ to 0.12δ.

[0018] The technical effects achieved by this invention are as follows:

[0019] The present invention discloses a compressor stator blade cascade with a ribbed vortex generator array arranged on the endwall of the stator passage. By arranging a micro ribbed vortex generator array on the endwall of the stator passage, on the one hand, the wake vortex generated by the oblique rib array can agitate the airflow in the separation zone, allowing the high-energy airflow in the upper boundary layer to mix with the low-energy airflow near the wall, thereby increasing the momentum and energy of the near-wall fluid and delaying downstream separation; on the other hand, the wake vortex generated by the oblique rib array can be used to block the accumulation of low-energy fluid from the pressure surface of the blade cascade to the corner region of the suction surface of the blade cascade, delaying and weakening the passage vortex, thereby achieving the purpose of controlling corner separation.

[0020] The present invention discloses a compressor stator blade cascade with a ribbed vortex generator array arranged on the endwall of the channel. By utilizing the accumulation effect of multiple micro vortex generators, a large-scale, high-intensity induced vortex is formed downstream. Therefore, the geometric size can be smaller than that of conventional vortex generators, resulting in less additional loss and further improving the aerodynamic performance of the blade cascade. Attached Figure Description

[0021] Figure 1 This is a front view of the compressor stator vane grid of the present invention;

[0022] Figure 2 This is a partially enlarged view of the micro ribbed eddy current generator array of the present invention;

[0023] Figure 3 This is a cross-sectional view of the oblique rib of the present invention;

[0024] Figure 4 This is the limiting streamline diagram of the stator vane cascade of an existing compressor;

[0025] Figure 5 This is a limiting streamline diagram of the compressor stator vane cascade of the present invention;

[0026] Figure 6 This is a comparison chart of the performance parameters of the compressor stator vane grid of the present invention and the existing compressor stator vane grid.

[0027] The attached diagram lists the components represented by each number as follows:

[0028] 1. Stator blade; 2. Channel end wall; 3. Leading edge of blade root; 4. Micro-ribbed vortex generator array; 5. Oblique ribs. Detailed Implementation

[0029] To make the objectives and advantages of this invention clearer, the invention will be specifically described below with reference to embodiments. It should be understood that the following text is merely used to describe one or more specific embodiments of the invention and does not strictly limit the scope of protection specifically claimed by the invention.

[0030] Example 1:

[0031] like Figure 1-3As shown, a compressor stator blade cascade with a ribbed vortex generator array arranged on the endwall of the channel includes a channel endwall 2 and multiple stator blades 1 and blade root leading edges 3 disposed on the channel endwall 2. Multiple micro-ribbed vortex generator arrays 4 are also disposed on the channel endwall 2. The perpendicular distance d1 between the leading edge of the micro-ribbed vortex generator array 4 and the tangent of the mid-arc line at the corresponding blade root leading edge 3 is 0.05l to 0.15l, preferably 0.11l. The tangential distance d2 between the leading edge of the ribbed vortex generator array 4 and the corresponding blade root leading edge 3 is -0.1l to 0.1l, preferably 0l, where l is the chord length of the stator blade 1. The width w of the ribbed vortex generator array 4 is 0.3δ to 0.6δ, preferably 0.3δ, where δ is the length of the channel endwall. 2. The thickness of the boundary layer: The ribbed vortex generator array 4 includes multiple equidistant parallel oblique ribs 5. The number of oblique ribs 5 in the micro ribbed vortex generator array 4 is 6 to 16. The multiple oblique ribs 5 are arranged parallel to the tangent direction of the arc line of the corresponding stator blade 1 at the leading edge 3 of the blade root. The angle γ between the extension direction of the oblique rib 5 and the tangent direction of the arc line at the leading edge 3 of the corresponding blade root is 30° to 60°, preferably 30°. The cross-section of the oblique rib 5 is triangular. The height n of the triangle is 0.05δ to 0.15δ and the base m is 0.05δ to 0.15δ, preferably 0.1δ and preferably 0.075δ. The distance p between two adjacent oblique ribs 5 is 0.04δ to 0.12δ, preferably 0.075δ.

[0032] Example 2:

[0033] To verify the effectiveness of the present invention, the inventors conducted numerical simulations of a conventional compressor stator vane cascade and the compressor stator vane cascade provided by the present invention. The specific simulation parameters and results are as follows:

[0034] The prototype stator blade profile parameters used for simulation are shown in Table 1 below:

[0035] Table 1

[0036]

[0037] like Figure 4 and Figure 5 As shown, by comparing the limiting streamline diagram of the endwall of the compressor stator blade cascade in the existing compressor with the limiting streamline diagram of the endwall of the compressor stator blade cascade provided by the present invention, it can be found that after setting the ribbed vortex generator array 4, the lateral migration flow of low-energy fluid near the pressure surface of the blade cascade to the corner region of the suction surface of the blade cascade is effectively blocked, and the formation and intensity of the channel vortex are suppressed. Therefore, arranging the ribbed vortex generator array 4 can delay and suppress the occurrence of corner separation.

[0038] like Figure 6As shown, the comparison results of the total pressure loss coefficient through numerical simulation show that the compressor stator vane cascade provided by the present invention effectively improves the total pressure loss throughout the entire stable operating range compared with the existing compressor stator vane cascade. The best effect can be obtained when the inlet angle is 134°, and the total pressure loss coefficient is reduced by 3%.

[0039] In summary, the compressor stator blade cascade provided by this invention can, on the one hand, stir the airflow in the separation zone by generating a wake vortex in the oblique rib array 5, allowing the high-energy airflow in the upper boundary layer to mix with the low-energy airflow near the wall, thereby increasing the momentum and energy of the near-wall fluid and delaying downstream separation; on the other hand, it can use the wake vortex generated by the oblique rib array 5 to block the accumulation of low-energy fluid from the pressure surface of the blade cascade to the corner region of the suction surface of the blade cascade, delaying and weakening the channel vortex, thereby achieving the purpose of controlling corner separation.

[0040] The above description is merely a preferred embodiment of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention. Structures, devices, and operating methods not specifically described or explained in this invention are implemented according to conventional methods in the art unless otherwise specified or limited.

Claims

1. A compressor stator blade cascade with a ribbed vortex generator array arranged on the endwall of a channel, comprising a channel endwall (2) and a plurality of stator blades (1) and a blade root leading edge (3) disposed on the channel endwall (2), characterized in that: The channel end wall (2) is also provided with a plurality of micro rib vortex generator arrays (4), the micro rib vortex generator arrays (4) including a plurality of equidistant parallel oblique ribs (5). The vertical distance between the leading edge of the micro ribbed vortex generator array (4) and the tangent of the middle arc line at the corresponding leading edge (3) of the blade root is 0.05l to 0.15l; The distance between the leading edge of the micro ribbed vortex generator array (4) and the corresponding leading edge of the blade root (3) in the tangential direction is -0.1l to 0.1l; Where l is the chord length of the stator blade (1); The width of the micro ribbed vortex generator array (4) is 0.3δ~0.6δ; δ is the thickness of the boundary layer of the channel end wall 2; The multiple oblique ribs (5) are arranged in parallel along the tangent direction of the arc line in the corresponding stator blade (1) at the leading edge (3) of the blade root.

2. The compressor stator vane cascade with a ribbed vortex generator array arranged on the channel endwall according to claim 1, characterized in that: The micro ribbed eddy current generator array (4) includes 6 to 16 oblique ribs (5).

3. The compressor stator vane cascade with a ribbed vortex generator array arranged on the channel endwall according to claim 1, characterized in that: The angle γ between the extension direction of the oblique rib (5) and the tangent direction of the middle arc at the corresponding leaf root leading edge (3) is 30º~60º.

4. The compressor stator vane cascade with a ribbed vortex generator array arranged on the channel endwall according to claim 1, characterized in that: The cross-section of each of the oblique ribs (5) is triangular, with the height n of the triangle being 0.05δ~0.15δ and the base m being 0.05δ~0.15δ.

5. A compressor stator vane cascade with a ribbed vortex generator array arranged on the channel endwall according to claim 1, characterized in that: The spacing p between two adjacent oblique ribs (5) is 0.04δ~0.12δ.

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