Arched stator blade and closed blisk structure of aero-engine compressor

Abstract

The invention belongs to the technical field of aero-engine compressor design, and particularly relates to an aero-engine compressor arched stator blade and closed blisk structure, the front edge of the stator blade is sequentially provided with a sweepback area A1, a transition area A2, a sweepforward area A3 and a sweepforward area A4 from bottom to top; the sweepback area A1, the transition area A2, the sweepforward area A3 and the sweepforward area A4 account for 0-30%, 30%-60%, 60%-95% and 95%-100% of the radial height of the stator blade respectively; the sweep angle of the sweepback area A1 is 0-20 degrees, and the sweep angle of the sweep-forward area A4 is 22-24 degrees; and the middle part of the front edge of the stator blade shrinks backwards and is arched, so that a gap between the front edge and the rear edge of the rotor blade can be increased, a good speed-reducing and pressure-diffusing function is achieved, the pressure-diffusing property can be improved, the large-bending-sweep pressure-diffusing requirement of the rotor blade can be met, and excitation caused by the influence of the rotor blade can be reduced.

Description

Technical Field

[0001] This application belongs to the technical field of aero-engine compressor design, and specifically relates to an aero-engine compressor bow-shaped stator blade and a closed integral blisk structure. Background Technique

[0002] The stator blades of an aero-engine compressor are formed by stacking blade profiles. The blade profile consists of a pressure surface and a suction surface that face each other front and back. The chord length extends from the leading edge to the trailing edge, and the radial height extends from the blade root to the blade tip. The blade root and the blade tip are covered by upper and lower flange plates.

[0003] With the increase in the total pressure ratio and the single-stage pressure ratio of the new generation of aero-engine compressors, the compressor load gradually increases. In the traditional stator configuration, the stator blades are connected to the upper and lower flange plates in a plug-in or welded form. The overall strength, vibration resistance, and bending resistance are poor, and there are welds, which will seriously affect the aerodynamic performance of the compressor and are difficult to meet the usage requirements of the new generation of aero-engines. It is gradually being replaced by a closed integral blisk structure.

[0004] In the closed integral blisk structure of the compressor stator, the stator blades and the upper and lower flange plates are integrally formed. There are transition fillets at the intersection positions of the blade root, blade tip and the upper and lower flange plates. The overall strength, vibration resistance, and bending resistance are good, and there are no welds, which can meet the usage requirements of the new generation of aero-engines to a certain extent. However, there is still a problem that the large bend and sweep diffusion requirements of the rotor blades cannot be met.

[0005] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0006] The purpose of this application is to provide an aero-engine compressor bow-shaped stator blade and a closed integral blisk structure to overcome or mitigate at least one aspect of the known technical defects.

[0007] The technical solution of this application is as follows:

[0008] On the one hand, an aero-engine compressor bow-shaped stator blade is provided, including:

[0009] The leading edge of the stator blade is successively a swept-back area A1, a transition area A2, a forward-swept area A3, and a forward-swept area A4 from bottom to top;

[0010] The ranges of the swept-back area A1, the transition area A2, the forward-swept area A3, and the forward-swept area A4 accounting for the radial height of the stator blade are 0-30%, 30%-60%, 60%-95%, and 95%-100% respectively;

[0011] The sweep angle of the swept-back area A1 is 0°-20°, and the sweep angle of the forward-swept area A4 is 22°-24°;

[0012] The middle part of the leading edge of the stator blade contracts backward and is bow-shaped.

[0013] According to at least one embodiment of the present application, in the above-mentioned bow-shaped stator blade of an aero-engine compressor, the leading edge of the stator blade is successively a forward-swept area B1, a transition area B2, and a backward-swept area B3 from bottom to top;

[0014] The ranges of the forward-swept area B1, the transition area B2, and the backward-swept area B3 accounting for the radial height of the stator blade are 0-10%, 10%-90%, and 90%-100% respectively.

[0015] According to at least one embodiment of the present application, in the above-mentioned bow-shaped stator blade of an aero-engine compressor, the sweep angle of the forward-swept area B1 is 20°-30°, and the sweep angle of the backward-swept area B3 is 10°-20°.

[0016] According to at least one embodiment of the present application, in the above-mentioned bow-shaped stator blade of an aero-engine compressor, the position of the mid-span of the trailing edge of the stator blade is straight.

[0017] The stator blade is further designed as a combined airfoil structure of "swept shape" and "dihedral angle".

[0018]

[0019]

[0020] Among them,

[0021] β is the sweep angle, and α is the dihedral angle;

[0022] is the meridian plane angle, μ is the local axial tilt angle, η is the local tangential tilt angle, and γ is the cylindrical flow angle.

[0023]

[0024] γ = arctan(Vy / Vx);

[0025] Among them,

[0026] Vx, Vy, and Vz are the components of the streamline velocity V in the X, Y, and Z directions, and the initial velocity V0 corresponds to the leading edge position.

[0027] On the other hand, a closed integral bladed disk structure of an aero-engine compressor stator is provided, and the stator blade thereof adopts any one of the above-mentioned bow-shaped stator blades of an aero-engine compressor.

[0028] The present application has at least the following beneficial technical effects:

[0029] Provided is a bow-shaped stator blade of an aero-engine compressor and a closed integral blisk structure. The sweep of the stator blade is designed in a segmented manner. The sweep at the leading edge and the mid-span of the stator blade is relatively small, and the trailing edge at the mid-span is straight, forming a semi-waisted shape. The middle part of the leading edge contracts backward, presenting a bow shape, which can increase the clearance between the trailing edge of the rotor blade. With good deceleration and diffusing functions, it can improve the diffusing performance, meet the large sweep and diffusing requirements of the rotor blade, and reduce the excitation vibration affected by the rotor blade. Brief Description of the Drawings

[0030] Figure 1 is a schematic diagram of the closed integral blisk structure of the aero-engine compressor stator provided by the embodiment of the present application;

[0031] Figure 2 is Figure 1 a partial view of

[0032] Figure 3 is Figure 2 a sectional view taken along the D-D direction of

[0033] Figure 4 is Figure 3 a sectional view taken along the E-E direction of

[0034] Figure 5 is a schematic diagram of the sweep distribution on the stator blade provided by the embodiment of the present application;

[0035] Figure 6 is a curve of the sweep distribution on the stator blade provided by the embodiment of the present application;

[0036] Figure 7 is a schematic diagram of the 2D modeling of the stator blade provided by the embodiment of the present application;

[0037] Figure 8 is a schematic diagram of the 3D modeling of the stator blade provided by the embodiment of the present application;

[0038] Figure 9 is a schematic diagram of the meridional plane angle and the local axial inclination angle of the streamline surface under the meridional plane projection view of the stator blade provided by the embodiment of the present application;

[0039] Figure 10 is a schematic diagram of the stacking method of the blade profiles of the bow-shaped stator blade of the aero-engine compressor provided by the embodiment of the present application.

[0040] For better illustration of this embodiment, some contents of the drawings are omitted, enlarged or reduced, and are only used for exemplary illustration and should not be construed as a limitation to the present application. Detailed Description of the Embodiment

[0041] To make the technical solutions and advantages of this application clearer, the following will further describe the technical solutions of this application clearly and completely in conjunction with the accompanying drawings. It can be understood that the specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application and not to limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design.

[0042] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the ordinary meaning understood by those of ordinary skill in the art to which this application belongs. The "including" used in the description of this application means that the concept appearing before this word covers the concepts and equivalents listed after this word, without excluding other related concepts.

[0043] In addition, the words indicating directions used in the description of this application are only used to indicate the relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that unless otherwise clearly specified and limited, the "installation", "connection" and other similar words used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific situation.

[0044] Compared with the traditional stator configuration, the compressor stator closed integral blisk structure has no welds, has better overall strength, vibration resistance and bending resistance, and can be subjected to a greater degree of sweep design to fully exert the potential of the closed integral blisk structure and meet the large sweep and diffusing requirements of the rotor blades.

[0045] Based on the above, this application embodiment provides an aero-engine compressor bow-shaped stator blade and a closed integral blisk structure, as Figures 1 - 4 shown.

[0046] Designing the stator blade sweep in regions can effectively control the airflow bending, generate the required airflow bending effect, and improve the compressor performance.

[0047] On the basis of the closed integral blisk structure, for the blade root and tip regions of the stator blade, a forward and backward sweep configuration is mainly adopted for design.

[0048] The leading edge of the stator blade is successively a backward sweep region A1, a transition region A2, a forward sweep region A3, and a forward sweep region A4 from bottom to top, and the ranges of the radial height occupied are 0-30%, 30%-60%, 60%-95%, and 95% - 100% respectively.

[0049] The trailing edge of the stator blade is successively the forward-swept region B1, the transition region B2, and the rear-swept region B3 from bottom to top, and the ranges accounting for the radial height are 0-10%, 10%-90%, and 90%-100% respectively.

[0050] The sweep angle of the rear-swept region A1 is 0°-20°, the sweep angle of the forward-swept region A4 is 22°-24°, the sweep angle of the forward-swept region B1 is 20°-30°, and the sweep angle of the rear-swept region B3 is 10°-20°. The sweep pattern is mainly concentrated at the blade root and the blade tip, and the rest of the interval is mainly the sweep transition region. As Figure 5 shown, it can improve the air flow mobility at the blade tip and the blade root of the stator blade.

[0051] The forward sweep angle is -, the rear sweep angle is +, and the sweep pattern distribution curve on the stator blade is as Figure 6 shown.

[0052] The sweep pattern at the mid-position of the leading edge of the stator blade is small, and the mid-position of the trailing edge is straight, forming a semi-waisted shape. The middle part of the leading edge contracts backward, showing an arc shape, which can increase the gap with the trailing edge of the rotor blade. With good deceleration and diffuser functions, it can improve the diffuser performance, meet the large bend and sweep diffuser requirements of the rotor blade, and can reduce the excitation vibration affected by the rotor blade.

[0053] The dihedral angle can be used to reduce the aerodynamic loss, secondary flow loss and shock wave in the channel at the blade tip of the stator blade. The stator blade can be further designed into a combined airfoil structure of "sweep pattern" and "dihedral angle", and three-dimensional design of the stator blade can fully explore the potential of the integral bladed disk structure to achieve the best aerodynamic performance.

[0054] The sweep pattern and the dihedral angle of the stator blade have a great influence on the performance and stability of the compressor. The compound sweep pattern of the leading and trailing edges is determined according to the performance and stability of the compressor. The leading-edge aerodynamic dihedral angle is defined with respect to the streamline surface.

[0055] The two-dimensional modeling of the stator blade is as Figure 7 shown, and the three-dimensional modeling is as Figure 8 shown. Under the meridional plane projection view, the meridional plane angle and the local axial tilt angle of the streamline surface are as Figure 9 shown. f1 is the blade tip, f2 is the (streamline surface) airfoil shape, f3 is the blade root, LE is the leading edge, TR is the trailing edge, AK is the streamline surface, CE is the blade stack axis, G point is the intersection point of the meridional plane and f2, t1 is the tangent line passing through the G point and f2, the X axis is the engine axis direction, the Z axis is the positive direction above the radial direction, and the XZ plane is the meridional plane of the engine.

[0056]

[0057]

[0058] Among them,

[0059] β is the grazing angle and α is the dihedral angle;

[0060] is the meridian plane angle, μ is the local axial tilt angle, η is the local tangential tilt angle, and γ is the cylindrical flow angle.

[0061]

[0062] γ = arctan(Vy / Vx);

[0063] wherein,

[0064] Vx, Vy, and Vz are the components of the streamline velocity V in the X, Y, and Z directions, and the initial velocity V0 corresponds to the leading edge position.

[0065] The stators of traditional two-dimensional designs form blades in an almost straight stacking manner, while the blade shape stacking method of the bow-shaped stators of the above aero-engine compressors is stacking along a curve, as Figure 10 shown.

[0066] The bow-shaped stators of the aero-engine compressors disclosed in the above embodiments rely on a closed integral blisk structure and adopt a combined structure design of a swept shape + dihedral angle, which can bring the aerodynamic performance of the stator blades into full play, provide technical reserves for the next generation of high-performance compressors, and provide calculation methods for the grazing angle and dihedral angle, providing a design basis for high-performance high-pressure ratio compressors.

[0067] So far, the technical solutions of the present application have been described in conjunction with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present application.

Claims

1. An arc-shaped stator blade of an aeroengine compressor, characterized in that, Including: The leading edge of the stator blade is successively a swept-back area A1, a transition area A2, a forward-swept area A3, and a forward-swept area A4 from bottom to top; The ranges of the swept-back area A1, the transition area A2, the forward-swept area A3, and the forward-swept area A4 in the radial height of the stator blade are 0-30%, 30%-60%, 60%-95%, and 95%-100% respectively; The sweep angle of the swept-back area A1 is 0°-20°, and the sweep angle of the forward-swept area A4 is 22°-24°; The middle part of the leading edge of the stator blade contracts backward and is in an arc shape.

2. The bowed stator blade of an aero-engine compressor according to claim 1, wherein: The leading edge of the stator blade is successively a forward-swept area B1, a transition area B2, and a swept-back area B3 from bottom to top; The ranges of the forward-swept area B1, the transition area B2, and the swept-back area B3 in the radial height of the stator blade are 0-10%, 10%-90%, and 90%-100% respectively.

3. The bowed stator blade of an aero-engine compressor according to claim 2, wherein: The sweep angle of the forward-swept area B1 is 20°-30°, and the sweep angle of the swept-back area B3 is 10°-20°.

4. The bowed stator blade of an aero-engine compressor according to claim 3, wherein: The middle position of the trailing edge of the stator blade is straight.

5. A closed integrally bladed disk structure of an aeroengine compressor stator, characterized in that, The stator blade adopts the bowed stator blade of an aero-engine compressor according to claim 4.

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