A wide-adaptability compressor inlet guide vane profile

Abstract

The application belongs to the field of aero-engine design, and particularly relates to a wide-adaptability compressor inlet guide vane profile, wherein a cross section of the profile is a circle, and the circle is swept along a center of the circle and a middle camber line to form a variable-diameter profile; the middle camber line comprises a front circular arc and a rear circular arc, an arc length of the front circular arc is smaller than that of the rear circular arc; a diameter of the circle gradually increases from a front end to a rear end of the front circular arc; and the diameter of the circle gradually decreases from a front end to a rear end of the rear circular arc; the profile can consider the working state of the compressor in a full speed range, and a separation zone of a blade back is obviously reduced or disappears when working in a 0-40 degree attack angle range. The following benefits can be obtained: the separation of the blade back is eliminated to improve the flow field quality in the compressor, and the compressor efficiency and surge margin are improved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aero-engine design, and particularly relates to a wide-adaptability compressor inlet guide vane profile. BACKGROUND

[0002] In order to widen the flow regulation range of a multi-stage compressor, the inlet guide vane needs to have a larger angle regulation range, which makes it work in a larger positive attack angle state in some working conditions. When the inlet guide vane works in a larger positive attack angle state, the trailing edge separation occurs with a traditional profile. In order to solve the problem, a wide-adaptability inlet guide vane profile is invented, which can work without separation in a larger attack angle range, and is beneficial to improve the flow field quality of the compressor inlet. When the existing profile works in a larger attack angle state, the trailing edge separation reduces the flow field quality inside the compressor, which leads to the decrease of the compressor efficiency and surge margin. SUMMARY

[0003] In order to solve the above problems, the profile comprises:

[0004] The profile section of the profile is formed by a circle sweep with a diameter changing, and the locus of the center of the circle is a mean camber line;

[0005] The mean camber line comprises a front circular arc and a rear circular arc, and the arc length of the front circular arc is smaller than that of the rear circular arc;

[0006] The diameter of the circle gradually increases from the front end to the rear end along the front circular arc, and the diameter of the circle gradually decreases from the front end to the rear end along the rear circular arc.

[0007] Preferably, the maximum diameter CMAX of the circle in the diameter changing process satisfies:

[0008] CMAX / B=(-0.4Ma)+0.19;

[0009] Wherein, B is the length of the profile section along the axial direction of the compressor; Ma is the inlet guide vane inlet Mach number Ma; Ma is 0.25-0.35.

[0010] When the diameter of the circle becomes the maximum, the axial distance XMAX between the center of the circle and the front end of the front circular arc satisfies:

[0011] XMAX / B=Ma-0.05.

[0012] Preferably, the diameter RL of the circle at the front end of the front circular arc satisfies:

[0013] RL / CMAX=(-1.0Ma)+0.5;

[0014] The diameter RT of the circle at the rear end of the rear circular arc satisfies:

[0015] RT / CMAX = (-0.4Ma) + 0.3.

[0016] Preferably, the arc length ARC01 of the front arc satisfies:

[0017] ARC01 / (ARC01+ARC02) = Ma - 0.05;

[0018] ARC02 is the arc length of the rear arc; Ma is the inlet Mach number Ma of the guide vane; Ma is 0.25-0.35.

[0019] The curvature ALF1 of the front arc satisfies:

[0020] ALF1 / (ALF1+ALF2) = (-1.0Ma) + 0.8;

[0021] ALF2 is the curvature of the rear arc.

[0022] Preferably, the value of XL and the value of CL of the airfoil section at any point of the front arc satisfy any one of the following combinations:

[0023] (0.0, 0.0), (0.03, 0.45), (0.06, 0.56), (0.09, 0.65), (0.12, 0.71), (0.15, 0.76), (0.2, 0.81), (0.3, 0.87), (0.4, 0.91), (0.6, 0.96), (0.8, 0.99) or (1.0, 1.0);

[0024] XL = (X-XS) / (XMAX-XS), CL = (C-2*RL) / (CMAX-2*RL), XS is the axial distance between the front end of the mean camber line and the inlet of the compressor; X is the axial coordinate of any point on the mean camber line, and C is the thickness of the airfoil section at X.

[0025] The value of XH and the value of CH of the airfoil section at any point of the rear arc satisfy any one of the following combinations:

[0026] (0.0, 0.0), (0.2, 0.33), (0.4, 0.6), (0.6, 0.815), (0.8, 0.95) or (1.0, 1.0);

[0027] XH = (X-XE) / (XMAX-XE); CH = (C-2*RT) / (CMAX-2*RT); XE is the axial distance between the rear end of the mean camber line and the inlet of the compressor.

[0028] The present application can consider the working state of the compressor in the whole speed range, and the separation zone of the blade back is obviously reduced or disappeared when working in the range of 0-40 degree attack angle. The following benefits can be obtained: the elimination of blade back separation improves the flow field quality inside the compressor, which is beneficial to improve the compressor efficiency and surge margin. BRIEF DESCRIPTION OF DRAWINGS

[0029] Figure 1 is a schematic diagram of the cross-sectional parameters of the blade profile of the present application;

[0030] Figure 2 is a schematic diagram of the camber parameters of the cross section of the blade profile of the present application;

[0031] Figure 3 is a schematic diagram of the working state of the traditional blade profile;

[0032] Figure 4 is a schematic diagram of the working state of the blade profile of the present application. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical scheme and advantages of the present application clearer, the technical scheme in the embodiments of the present application will be described in more detail below in combination with the drawings in the embodiments of the present application. In the drawings, the same or similar reference signs represent the same or similar elements or elements with the same or similar functions throughout. The described embodiments are part of the embodiments of the present application, not all of the embodiments. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as a limitation of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below in combination with the drawings.

[0034] In order to solve the problem of the traditional blade profile, the key is to improve the inlet guide vane profile so that it does not separate when working in a larger attack angle state. The adjustment range of the inlet guide vane angle of the compressor is close to 40 degrees in the whole speed range. The blade profile should be designed to consider all states, and the blade back should not separate when working in the range of 0-40 degree attack angle. Therefore, the present application provides a wide adaptability compressor inlet guide vane profile, comprising:

[0035] The cross section of the blade profile is a circle, which is formed by sweeping along the center of the circle and the middle arc line;

[0036] The middle arc line includes a front circular arc and a rear circular arc, and the arc length of the front circular arc is less than the arc length of the rear circular arc.

[0037] The diameter of the circle gradually increases from the front end to the rear end along the front circular arc; and the diameter of the circle gradually decreases from the front end to the rear end along the rear circular arc.

[0038] As shown in the figure, the axial position of the compressor inlet is taken as the origin, the axial direction of the compressor is taken as the X direction, and the direction perpendicular to the X direction is taken as the Y direction; Figures 1-2

[0039] In some optional embodiments, the maximum diameter CMAX of the circle satisfies:

[0040] CMAX / B=(-0.4Ma)+0.19;

[0041] wherein B is the length of the blade profile section along the axial direction of the compressor; Ma is the inlet Mach number Ma of the guide vane; Ma is 0.25-0.35.

[0042] In the above embodiments, preferably, the value range of CMAX / B is 0.05-0.09.

[0043] The position of the maximum diameter of the circle satisfies:

[0044] XMAX / B=Ma-0.05.

[0045] In the above embodiments, preferably, the value range of XMAX / B is 0.2-0.3.

[0046] In some optional embodiments, the diameter RL of the circle at the front end of the front circular arc satisfies:

[0047] RL / CMAX=(-1.0Ma)+0.5;

[0048] The diameter RT of the circle at the rear end of the rear circular arc satisfies:

[0049] RT / CMAX=(-0.4Ma)+0.3.

[0050] In the above embodiments, preferably, the value range of RL / CMAX is 0.15-0.25; the value range of RT / CMAX is 0.16-0.20.

[0051] In some optional embodiments, the arc length ARC01 of the front circular arc satisfies:

[0052] ARC01 / (ARC01+ARC02)=Ma-0.05; preferably, the value of ARC01 / (ARC01+ARC02) is 0.2-0.3;

[0053] ARC02 is the arc length of the rear circular arc; Ma is the inlet Mach number Ma of the guide vane; Ma is 0.25-0.35.

[0054] The curvature ALF1 of the front circular arc satisfies:

[0055] ​ALF1 / (ALF1+ALF2)=(-1.0Ma)+0.8; preferably, ALF1 / (ALF1+ALF2) is in the range of 0.45 to 0.55.

[0056] wherein ALF2 is the curvature of the mean camber line.

[0057] In some alternative embodiments,

[0058] The airfoil section before the maximum diameter of the circle satisfies:

[0059] (XL,CL)={(0.0,0.0);(0.03,0.45);(0.06,0.56);(0.09,0.65);(0.12,0.71);(0.15,0.76);(0.2,0.81);(0.3,0.87)(0.4,0.91);(0.6,0.96);(0.8,0.99);(1.0,1.0)}

[0060] wherein XL=(X-XS) / (XMAX-XS), CL=(C-2*RL) / (CMAX-2*RL), XS is the axial distance between the leading end of the mean camber line and the compressor inlet; X is the axial coordinate of any point on the mean camber line, and C is the thickness of the airfoil section at X;

[0061] The airfoil section after the maximum diameter of the circle satisfies:

[0062] (XH,CH)={(0.0,0.0)(0.2,0.33)(0.4,0.6)(0.6,0.815)(0.8,0.95)(1.0,1.0)};

[0063] wherein XH=(X-XE) / (XMAX-XE); CH=(C-2*RT) / (CMAX-2*RT); XE is the axial distance between the trailing end of the mean camber line and the compressor inlet.

[0064] The airfoil can take into account the working state of the compressor in the full speed range, and the separation zone of the airfoil back is obviously reduced or disappeared when working in the range of 0-40 degrees attack angle. Figure 4 As shown in the figure, the following benefits can be obtained: the elimination of the airfoil back separation improves the flow field quality inside the compressor, which is beneficial to improve the compressor efficiency and surge margin.

[0065] The above is merely a specific implementation of the present application, but the protection scope of the present application is not limited thereto, and any person skilled in the art can easily think of changes or replacements within the technical range disclosed in the present application, which shall be covered in the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A wide-adaptability compressor inlet guide vane profile, characterized in that, include: The blade profile is formed by sweeping a circle with varying diameter, and the trajectory of the center of the circle is a mid-arc line. The middle arc includes a front arc and a rear arc, wherein the arc length of the front arc is less than the arc length of the rear arc. The diameter of the circle gradually increases from the front end to the rear end of the front arc; the diameter of the circle gradually decreases from the front end to the rear end of the rear arc. As the diameter of the circle changes, the maximum diameter CMAX satisfies: CMAX / B = (-0.4Ma) + 0.19; Where B is the length of the blade section along the compressor axial direction; Ma is the Mach number at the guide vane inlet; Ma takes a value of 0.25 to 0.35; when the diameter of the circle becomes the maximum, the axial distance XMAX between the center of the circle and the front end of the leading arc satisfies: XMAX / B = Ma - 0.

05.

2. The wide adaptability compressor inlet guide vane profile as described in claim 1, characterized in that, The diameter RL of the circle satisfies the following at the front end of the first segment of the arc: RL / CMAX = (-1.0Ma) + 0.5; The diameter RT of the circle satisfies the following at the rear end of the latter segment of the arc: RT / CMAX = (-0.4Ma) + 0.

3.

3. The wide adaptability compressor inlet guide vane profile as described in claim 1, characterized in that, The arc length ARC01 of the front arc satisfies: ARC01 / (ARC01+ARC02)=Ma-0.05; ARC02 is the arc length of the rear section; Ma is the Mach number at the guide inlet; Ma ranges from 0.25 to 0.35; the curvature ALF1 of the front section satisfies: ALF1 / (ALF1+ALF2)= (-1.0Ma)+0.8; Wherein, ALF2 is the curvature of the latter part of the arc.

4. The wide adaptability compressor inlet guide vane profile as described in claim 2, characterized in that, At any point on the leading arc of the airfoil section, the values ​​of XL and CL satisfy any of the following combinations: (0.0, 0.0), (0.03, 0.45), (0.06, 0.56), (0.09, 0.65), (0.12, 0.71), (0.15, 0.76), (0.2, 0.81), (0.3, 0.87), (0.4, 0.91), (0.6, 0.96), (0.8, 0.99) or (1.0, 1.0); Where: XL=(X-XS) / (XMAX-XS), CL=(C-2*RL) / (CMAX-2*RL), XS is the axial distance between the front end of the middle arc and the compressor inlet; X is the axial coordinate of any point on the middle arc, and C is the thickness of the airfoil section at X; At any point on the rear arc of the airfoil section, the values ​​of XH and CH satisfy any of the following combinations: (0.0, 0.0), (0.2, 0.33), (0.4, 0.6), (0.6, 0.815), (0.8, 0.95) or (1.0, 1.0); Where: XH=(X-XE) / (XMAX-XE;CH=(C-2*RT) / (CMAX-2*RT;XE is the axial distance between the rear end of the middle arc and the compressor inlet.

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