A method for designing hot and cold state throat area of high-pressure turbine guide vane

Abstract

The present application relates to the field of high-pressure turbine guide vane design, and discloses a high-pressure turbine guide vane cold and hot state throat area design method, which is based on the initial design of the high-pressure turbine guide vane profile and the hot state size of the flow passage, and obtains the cold and hot state radial deformation of the upper edge plate, the cold and hot state radial deformation of the lower edge plate, the blade installation angle change close to the upper edge plate and the blade installation angle change close to the lower edge plate through cold and hot state conversion. Finally, the circumferential angle between adjacent blades and the width of the throat area between adjacent blades are corrected to obtain the high-pressure turbine guide vane cold state profile and flow passage size after the cold and hot state throat area correction, which can ensure that the hot state throat areas of each window of the blade are equal, reduces the throat area difference between adjacent blades, thereby improving the consistency of the outlet gas flow parameters of the high-pressure turbine guide vane and the aeroelastic stability of the downstream rotor blade, and reducing the dispersion of the aerodynamic excitation frequency and the risk of high-cycle fatigue cracks of the rotor blade.

Description

Technical Field

[0001] This invention relates to the field of high-pressure turbine guide vane design, and discloses a method for designing the throat area of ​​a high-pressure turbine guide vane in both hot and cold states. Background Technology

[0002] The basic working principles of aero engines are similar, mainly consisting of low-pressure and high-pressure compression systems, combustion systems, and high-pressure and low-pressure turbine systems. Air entering the engine inlet is compressed in the compression system, then enters the combustion chamber and mixes with fuel. The high-temperature combustion gases drive the turbine to perform work, thus powering the compression system. To increase engine thrust and reduce fuel consumption, dual-rotor turbofan engines are often used. The high-pressure turbine rotor drives the high-pressure compressor, and the low-pressure turbine rotor drives the low-pressure compressor. As the outlet of the high-pressure compression system, the throat area of ​​the high-pressure turbine guide vanes directly affects the operating point and efficiency of the high-pressure compression system. Since the high-pressure turbine guide vanes are located at the combustion chamber outlet, operating at high temperatures and experiencing significant thermal stress, they typically employ a fan-shaped structure to release the thermal deformation of the blade edges and blade body.

[0003] Without changing the total area of ​​the high-pressure turbine guide vanes, reducing the throat area difference of each vane window is a continuous goal to improve gas combustion stability and reduce excitation on the high-pressure turbine working blades. Early designers reduced casting variability by increasing the profile control requirements of the high-pressure turbine guide vanes and improving casting quality. However, as engine temperatures rise, the area difference between the various windows of the high-pressure turbine guide vanes increases, leading to uncertainty regarding vibration damage to the turbine rotor blades. Summary of the Invention

[0004] The purpose of this invention is to provide a method for designing the throat area of ​​high-pressure turbine guide vanes in both hot and cold states, which can ensure that the throat area is equal in the hot state, reduce the throat area difference between adjacent blades, and thus improve the stability of the combustion gas.

[0005] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:

[0006] A method for designing the throat area of ​​a high-pressure turbine guide vane in both hot and cold states, comprising:

[0007] Based on the operating temperature, hot design dimensions, and material properties of the high-pressure turbine guide vane, the radial deformation, circumferential deformation, radial deformation, and circumferential deformation of the upper edge plate and the lower edge plate under hot and cold conditions are analyzed and obtained.

[0008] Based on the radial deformation of the upper edge plate in both hot and cold states, calculate the change in the circumferential rotation angle of the blades near the upper edge plate; based on the radial deformation of the lower edge plate in both hot and cold states, calculate the change in the circumferential rotation angle of the blades near the lower edge plate; use the average of the changes in the circumferential rotation angle of the blades near the upper edge plate and the changes in the circumferential rotation angle of the blades near the lower edge plate as a correction value to correct the circumferential angle between adjacent blades, thus obtaining the cold axial angle that makes the hot circumferential angle between adjacent blades equal after correction.

[0009] Based on the circumferential deformation of the upper edge plate under both hot and cold conditions, calculate the change in the blade mounting angle near the upper edge plate; based on the circumferential deformation of the lower edge plate under both hot and cold conditions, calculate the change in the blade mounting angle near the lower edge plate; use the average of the changes in the blade mounting angle near the upper edge plate and the changes in the blade mounting angle near the lower edge plate as a correction value to correct the width of the hot throat area between adjacent blades, thus obtaining the cold mounting angle that makes the hot throat area of ​​adjacent blades equal.

[0010] Furthermore, according to The change in the circumferential rotation angle of the blade near the upper edge plate is calculated, where β1 is the change in the circumferential rotation angle of the blade near the upper edge plate, N is the number of high-pressure turbine guide blades or the number of fan-shaped segments of high-pressure turbine guide blades, r1 is the cold radius of the upper edge plate of the blade, a1 is the linear expansion coefficient of the upper edge plate material, T1 is the operating temperature of the upper edge plate, and ΔH1 is the radial deformation of the upper edge plate.

[0011] Furthermore, according to The change in the circumferential rotation angle of the blade near the lower edge plate is calculated, where β2 is the change in the circumferential rotation angle of the blade near the lower edge plate, N is the number of high-pressure turbine guide vanes or the number of fan-shaped segments of high-pressure turbine guide vanes, r2 is the cold radius of the lower edge plate of the blade, a2 is the linear expansion coefficient of the lower edge plate material, T2 is the operating temperature of the lower edge plate, and ΔH2 is the radial deformation of the lower edge plate.

[0012] Furthermore, according to The change in blade mounting angle β3 near the upper edge plate is calculated, where ΔC1 is the circumferential deformation of the upper edge plate in both hot and cold states, L1 is the cold distance between the throat point on the upper edge plate of the blade and the stacking axis, and L2 is the cold distance between the throat point on the upper edge plate of the adjacent blade forming the throat and the stacking axis.

[0013] Furthermore, according to The change in blade mounting angle β4 near the lower edge plate is calculated, where ΔC2 is the circumferential deformation of the lower edge plate in both hot and cold states, L3 is the cold distance between the throat point on the blade's lower edge plate and the stacking axis, and L4 is the cold distance between the throat point on the blade's lower edge plate of the adjacent blade forming the throat and the stacking axis.

[0014] Furthermore, for high-pressure turbine guide vanes composed of fan-shaped segments with multiple blades, keeping the cold radius r2 of the lower edge plate constant and the cold radius r1 of the upper edge plate of the complete blade window constant, the radius of the upper edge plate on the side of the blade splicing window is increased by [missing value]. Where r1 is the cold radius of the upper edge plate of the blade, a1 is the linear expansion coefficient of the upper edge plate material, T1 is the operating temperature of the upper edge plate, r2 is the cold radius of the lower edge plate of the blade, a2 is the linear expansion coefficient of the lower edge plate material, and T2 is the operating temperature of the lower edge plate; the complete window is the gap window between two adjacent blades in the same sector segment, and the spliced ​​window is the gap window between two adjacent blades in adjacent sector segments.

[0015] Furthermore, for high-pressure turbine guide vanes composed of fan-shaped segments with multiple blades, the cold-state radius r1 of the upper edge plate of the blade remains constant, and the cold-state radius r2 of the lower edge plate of the complete blade window remains constant. The radius of the lower edge plate on the side of the blade splicing window is reduced to [value missing]. Where r1 is the cold radius of the upper edge plate of the blade, a1 is the linear expansion coefficient of the upper edge plate material, T1 is the operating temperature of the upper edge plate, r2 is the cold radius of the lower edge plate of the blade, a2 is the linear expansion coefficient of the lower edge plate material, and T2 is the operating temperature of the lower edge plate; the complete window is the gap window between two adjacent blades in the same sector segment, and the spliced ​​window is the gap window between two adjacent blades in adjacent sector segments.

[0016] Compared with existing technologies, the beneficial effects of this invention are as follows: In the design process of high-pressure turbine guide vanes, cold and hot state conversions are performed based on the initial design of the blade profile and hot-state dimensions of the flow channel. This yields the cold and hot state radial deformation of the upper and lower edge plates of the high-pressure turbine guide vane, as well as the changes in the blade mounting angle near the upper and lower edge plates. The circumferential angle between adjacent blades and the width of the throat area between adjacent blades are corrected. By comprehensively considering the multi-dimensional deformations existing between the cold and hot states of the high-pressure turbine guide vane, the blade profile and cold-state dimensions of the flow channel after correction of the cold and hot throat area are finally obtained. This method is suitable for engineering applications. This invention can ensure that the hot-state throat area of ​​each window of the high-pressure turbine guide vane is equal, reducing the large differences in throat area between adjacent blades. This improves the consistency of the outlet gas flow parameters of the high-pressure turbine guide vane, reduces the dispersion of aerodynamic excitation frequency, improves the aeroelastic stability of the downstream rotor blades, and reduces the risk of high-cycle fatigue cracks in the rotor blades. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the cold and hot state structure of the high-pressure turbine guide vane in Example 1 or 2;

[0018] Figure 2 This is a schematic diagram of the cold-state design width of the throat area of ​​the blade near the upper edge plate in Example 1 or 2.

[0019] Figure 3 This is a schematic diagram of the cold-state design width of the throat area near the lower edge plate of the blade in Example 1 or 2;

[0020] Among them, 1. upper edge plate; 2. lower edge plate; 3. stacking shaft. Detailed Implementation

[0021] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0022] Example 1

[0023] See Figures 1-3 A method for designing the throat area of ​​a high-pressure turbine guide vane in both hot and cold states, comprising:

[0024] Based on the operating temperature, hot design dimensions, and material properties of the high-pressure turbine guide vane, the radial deformation ΔH1, circumferential deformation ΔC1, radial deformation ΔH2, and circumferential deformation ΔC2 of the upper edge plate 1 and the lower edge plate 2 in both hot and cold states are analyzed and obtained.

[0025] Based on the radial deformation of the upper edge plate 1 in both hot and cold states, calculate the change in the circumferential rotation angle of the blades near the upper edge plate 1; based on the radial deformation of the lower edge plate 2 in both hot and cold states, calculate the change in the circumferential rotation angle of the blades near the lower edge plate 2; use the average value of the changes in the circumferential rotation angle of the blades near the upper edge plate 1 and the changes in the circumferential rotation angle of the blades near the lower edge plate 2 as a correction value to correct the circumferential angle between adjacent blades, thus obtaining the cold axial angle that makes the hot circumferential angle between adjacent blades equal after correction;

[0026] Based on the circumferential deformation of the upper edge plate 1 under both hot and cold conditions, the change in the blade mounting angle near the upper edge plate 1 is calculated; based on the circumferential deformation of the lower edge plate 2 under both hot and cold conditions, the change in the blade mounting angle near the lower edge plate 2 is calculated; the average value of the change in the blade mounting angle near the upper edge plate 1 and the change in the blade mounting angle near the lower edge plate 2 is used as a correction value to correct the width of the hot throat area between adjacent blades, thereby obtaining the cold mounting angle that makes the hot throat area of ​​adjacent blades equal.

[0027] In this embodiment, during the design of the high-pressure turbine guide vane, cold and hot state conversions are performed based on the initial design of the blade profile and flow channel hot state dimensions of the high-pressure turbine guide vane. This yields the cold and hot state radial deformation of the upper edge plate 1 and the lower edge plate 2 of the high-pressure turbine guide vane, as well as the changes in the blade mounting angle near the upper edge plate 1 and the lower edge plate 2. The circumferential angle between adjacent blades and the width of the throat area between adjacent blades are then corrected. By comprehensively considering the multi-dimensional deformations existing between the cold and hot states of the high-pressure turbine guide vane, the blade profile and flow channel cold state dimensions of the high-pressure turbine guide vane after the cold and hot state throat area correction are finally obtained. This ensures that the hot state throat area of ​​each window of the high-pressure turbine guide vane is equal, reducing the large differences in throat area between adjacent blades. This improves the consistency of the outlet gas flow parameters of the high-pressure turbine guide vane, reduces the dispersion of aerodynamic excitation frequency, improves the aeroelastic stability of the downstream rotor blades, and reduces the risk of high-cycle fatigue cracks in the rotor blades.

[0028] like Figure 1 The diagram shows the cold and hot structural features of a high-pressure turbine guide vane. Solid lines represent the cold dimensions of the vane, while dashed lines represent its hot dimensions during operation. This embodiment is based on... The change in the circumferential rotation angle of the blade near the upper edge plate 1 is calculated, where β1 is the change in the circumferential rotation angle of the blade near the upper edge plate 1, N is the number of high-pressure turbine guide blades or the number of fan-shaped segments of high-pressure turbine guide blades, r1 is the cold radius of the upper edge plate 1, a1 is the linear expansion coefficient of the material of the upper edge plate 1, T1 is the operating temperature of the upper edge plate 1, and ΔH1 is the radial deformation of the upper edge plate 1.

[0029] In this embodiment, according to The change in the circumferential rotation angle of the blade near the upper edge plate 1 is calculated, where β2 is the change in the circumferential rotation angle of the blade near the lower edge plate 2, N is the number of high-pressure turbine guide vanes or the number of fan-shaped segments of high-pressure turbine guide vanes, r2 is the cold radius of the lower edge plate 2, a2 ​​is the linear expansion coefficient of the material of the lower edge plate 2, T2 is the operating temperature of the lower edge plate 2, and ΔH2 is the radial deformation of the lower edge plate 2.

[0030] In this embodiment, according to The change in the blade mounting angle β3 near the upper edge plate 1 is calculated, where ΔC1 is the circumferential deformation of the upper edge plate 1 under hot and cold conditions, L1 is the cold distance between the throat point on the back of the upper edge plate 1 and the stacking axis 3, and L2 is the cold distance between the throat point on the upper edge plate 1 of the adjacent blade forming the throat and the stacking axis 3. The circumferential deformation ΔC1 of the upper edge plate 1 under hot and cold conditions can be calculated according to the formula ΔC1=a1T1S1, where a1 is the linear expansion coefficient of the upper edge plate material, T1 is the operating temperature of the upper edge plate, and S1 is the cold design width of the throat area of ​​the blade near the upper edge plate.

[0031] according to The change in blade mounting angle β4 near the lower edge plate 2 is calculated, where ΔC2 is the circumferential deformation of the lower edge plate 2 in both hot and cold states, L3 is the cold distance between the throat point on the back of the blade lower edge plate 2 and the stacking axis 3, and L4 is the cold distance between the throat point on the blade base of the adjacent blade lower edge plate 2 forming the throat and the stacking axis 3. The circumferential deformation ΔC2 of the lower edge plate 2 in both hot and cold states can be calculated according to the formula ΔC2=a2T2S2, where a2 is the linear expansion coefficient of the lower edge plate material, T2 is the operating temperature of the lower edge plate, and S2 is the cold design width of the throat area of ​​the blade near the lower edge plate.

[0032] By calculating the deformation of the blades during cold and hot operation, the cold deformation, installation angle change, and circumferential rotation angle change of the upper and lower edge plates of the high-pressure turbine guide vane, which directly affect the throat area window length value of the blade, were obtained. Based on the different changes in these areas of the blade, the corresponding cold and hot size conversions and corrections can be carried out in combination with the structural characteristics, manufacturing methods, and application scenarios of each high-pressure turbine guide vane, so as to obtain the cold installation angle and circumferential angle of the high-pressure turbine guide vane.

[0033] Example 2

[0034] See Figures 1-3 A method for designing the throat area of ​​a high-pressure turbine guide vane in both hot and cold states, comprising:

[0035] Based on the operating temperature, hot design dimensions, and material properties of the high-pressure turbine guide vane, the radial deformation ΔH1, circumferential deformation ΔC1, radial deformation ΔH2, and circumferential deformation ΔC2 of the upper edge plate 1 and the lower edge plate 2 in both hot and cold states are analyzed and obtained.

[0036] Based on the radial deformation of the upper edge plate 1 in both hot and cold states, calculate the change in the circumferential rotation angle of the blades near the upper edge plate 1; based on the radial deformation of the lower edge plate 2 in both hot and cold states, calculate the change in the circumferential rotation angle of the blades near the lower edge plate 2; use the average value of the changes in the circumferential rotation angle of the blades near the upper edge plate 1 and the changes in the circumferential rotation angle of the blades near the lower edge plate 2 as a correction value to correct the circumferential angle between adjacent blades, thus obtaining the cold axial angle that makes the hot circumferential angle between adjacent blades equal after correction;

[0037] Based on the circumferential deformation of the upper edge plate 1 under both hot and cold conditions, the change in the blade mounting angle near the upper edge plate 1 is calculated; based on the circumferential deformation of the lower edge plate 2 under both hot and cold conditions, the change in the blade mounting angle near the lower edge plate 2 is calculated; the average value of the change in the blade mounting angle near the upper edge plate 1 and the change in the blade mounting angle near the lower edge plate 2 is used as a correction value to correct the width of the hot throat area between adjacent blades, thereby obtaining the cold mounting angle that makes the hot throat area of ​​adjacent blades equal.

[0038] In the design of high-pressure turbine guide vanes, the entire ring blade is usually divided into N sector segments, such as double or triple blade structures, to reduce thermal stress and reduce cold gas leakage. However, due to the large expansion of high-pressure turbine guide vanes at high temperatures, the throat area difference between different windows of the blade increases in both hot and cold states. This window area difference alters the pressure and velocity of the combustion gas, which is detrimental to the vibration of the high-pressure turbine working blades. Therefore, in this embodiment, for high-pressure turbine guide vanes composed of sector segments spliced ​​together with multiple blades, while keeping the cold radius r2 of the lower edge plate 2 and the cold radius r1 of the upper edge plate 1 of the complete blade window unchanged, the radius of the upper edge plate 1 on the side of the blade splicing window is increased by [missing information]. Wherein, r1 is the cold radius of the upper edge plate 1 of the blade, a1 is the linear expansion coefficient of the material of the upper edge plate 1, T1 is the operating temperature of the upper edge plate 1, r2 is the cold radius of the lower edge plate 2 of the blade, a2 is the linear expansion coefficient of the material of the lower edge plate 2, and T2 is the operating temperature of the lower edge plate 2; the complete window is the gap window between two adjacent blades in the same sector segment, and the spliced ​​window is the gap window between two adjacent blades in adjacent sector segments.

[0039] In this embodiment, besides increasing the radius of the upper edge plate 1 on the blade splicing window side, for high-pressure turbine guide blades composed of fan-shaped segments spliced ​​together with multiple blades, the radius of the lower edge plate 2 on the blade splicing window side can be reduced while keeping the cold-state radius r1 of the upper edge plate 1 and the cold-state radius r2 of the lower edge plate 2 of the complete blade window unchanged. Where r1 is the cold radius of the upper edge plate 1 of the blade, a1 is the linear expansion coefficient of the material of the upper edge plate 1, T1 is the operating temperature of the upper edge plate 1, r2 is the cold radius of the lower edge plate 2 of the blade, a2 is the linear expansion coefficient of the material of the lower edge plate 2, and T2 is the operating temperature of the lower edge plate 2.

[0040] It should be noted that, in this embodiment, for a high-pressure turbine guide vane composed of fan-shaped segments with multiple blades, after correcting the circumferential angle between adjacent blades and the width of the throat area between adjacent blades, either increasing the radius of the upper edge plate 1 on the side of the blade splicing window or decreasing the radius of the lower edge plate 2 on the side of the blade splicing window can be chosen.

[0041] The other parts of this embodiment are the same as those in Embodiment 1, and will not be described again here.

[0042] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for designing the throat area of ​​a high-pressure turbine guide vane in both hot and cold states, characterized in that, include: Based on the operating temperature, hot design dimensions, and material properties of the high-pressure turbine guide vane, the radial deformation, circumferential deformation, radial deformation, and circumferential deformation of the upper edge plate and the lower edge plate under hot and cold conditions are analyzed and obtained. Based on the radial deformation of the upper edge plate under both hot and cold conditions, the change in the circumferential rotation angle of the blades near the upper edge plate is calculated; based on the radial deformation of the lower edge plate under both hot and cold conditions, the change in the circumferential rotation angle of the blades near the lower edge plate is calculated; the average of the changes in the circumferential rotation angle of the blades near the upper edge plate and the changes in the circumferential rotation angle of the blades near the lower edge plate is used as a correction value to correct the circumferential angle between adjacent blades, obtaining the cold-state axial angle that makes the corrected hot-state circumferential angle between adjacent blades equal; where the change in the circumferential rotation angle of the blades near the upper edge plate... , This refers to the number of guide vanes for a high-pressure turbine or the number of sector segments of the guide vanes for a high-pressure turbine. The cold radius of the upper edge plate of the blade. Let be the coefficient of linear expansion of the material of the upper edge plate. The operating temperature of the upper edge plate. This represents the radial deformation of the upper edge plate; Based on the circumferential deformation of the upper edge plate in both hot and cold states, calculate the change in the blade mounting angle near the upper edge plate; based on the circumferential deformation of the lower edge plate in both hot and cold states, calculate the change in the blade mounting angle near the lower edge plate; use the average of the changes in the blade mounting angle near the upper edge plate and the changes in the blade mounting angle near the lower edge plate as a correction value to correct the width of the hot throat area between adjacent blades, thus obtaining the cold mounting angle that makes the hot throat area of ​​adjacent blades equal. The change in blade mounting angle near the upper edge plate , This represents the circumferential deformation of the upper edge plate under both hot and cold conditions. The cold distance between the upper edge of the blade, the back throat point, and the accumulation axis. The cold distance between the throat point and the stacking axis of the adjacent leaf upper edge plate leaf basin throat point that forms the throat.

2. The method for designing the throat area of ​​a high-pressure turbine guide vane in both hot and cold states according to claim 1, characterized in that, according to The change in the circumferential rotation angle of the blade near the lower edge plate was calculated, where, This represents the change in the circumferential rotation angle of the blade near the lower edge plate. This refers to the number of guide vanes for a high-pressure turbine or the number of sector segments of the guide vanes for a high-pressure turbine. Let be the cold radius of the lower edge plate of the blade. Let be the coefficient of linear expansion of the lower edge plate material. This refers to the operating temperature of the lower edge plate. This represents the radial deformation of the lower edge plate.

3. The method for designing the throat area of ​​a high-pressure turbine guide vane in both hot and cold states according to claim 1, characterized in that, according to The change in blade mounting angle near the lower edge plate was calculated. ,in, This represents the circumferential deformation of the lower edge plate under both hot and cold conditions. The cold distance between the lower edge of the blade, the throat point on the back of the blade, and the accumulation axis. The cold distance between the throat point and the stacking axis of the adjacent leaf blades at the lower edge of the throat.

4. The method for designing the throat area of ​​a high-pressure turbine guide vane in both hot and cold states according to claim 1, characterized in that, For high-pressure turbine guide vanes composed of fan-shaped segments with multiple blades, the cold radius of the lower edge plate of the blade should be maintained. The upper edge plate cold-state radius of the blade window remains unchanged. The radius of the upper edge plate on the side of the blade splicing window remains unchanged. ,in, The cold radius of the upper edge plate of the blade. Let be the coefficient of linear expansion of the material of the upper edge plate. The operating temperature of the upper edge plate. Let be the cold radius of the lower edge plate of the blade. Let be the coefficient of linear expansion of the lower edge plate material. The operating temperature of the lower edge plate; the complete window is the gap window between two adjacent blades in the same sector segment, and the spliced ​​window is the gap window between two adjacent blades in adjacent sector segments.

5. The method for designing the throat area of ​​a high-pressure turbine guide vane in both hot and cold states according to claim 1, characterized in that, For high-pressure turbine guide vanes composed of fan-shaped segments with multiple blades, the cold radius of the upper edge plate of the blade should be maintained. The lower edge plate cold radius of the blade window remains unchanged. Remaining unchanged, reduce the radius of the lower edge plate on the blade splicing window side by [value missing]. ,in, The cold radius of the upper edge plate of the blade. Let be the coefficient of linear expansion of the material of the upper edge plate. The operating temperature of the upper edge plate. Let be the cold radius of the lower edge plate of the blade. Let be the coefficient of linear expansion of the lower edge plate material. The operating temperature of the lower edge plate; the complete window is the gap window between two adjacent blades in the same sector segment, and the spliced ​​window is the gap window between two adjacent blades in adjacent sector segments.

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