CN117216890A - Method for designing cold-hot state throat area of high-pressure turbine guide vane - Google Patents
Method for designing cold-hot state throat area of high-pressure turbine guide vane Download PDFInfo
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Abstract
The invention relates to the field of high-pressure turbine guide vane design, and discloses a method for designing the cold-hot state throat area of a high-pressure turbine guide vane.
Description
Technical Field
The invention relates to the field of high-pressure turbine guide vane design, and discloses a method for designing the cold and hot state throat area of a high-pressure turbine guide vane.
Background
The working principle of the aero-engine is basically similar, and the aero-engine mainly comprises a low-pressure compression system, a high-pressure compression system, a combustion system, a high-pressure turbine system, a low-pressure turbine system and the like. After air at the inlet of the engine is compressed in the compression system, the air enters the combustion chamber and is mixed with fuel, and high-temperature gas generated by fuel combustion drives the turbine to do work so as to drive the compression system. In order to improve the thrust of the engine and reduce the oil consumption of the engine, a double-rotor turbofan engine is usually adopted, a high-pressure turbine rotor drives a high-pressure compressor to rotate, and a low-pressure turbine rotor drives a low-pressure compressor to rotate. As the interception position of the outlet of the high-pressure air system, the size of the throat area of the high-pressure turbine guide vane directly influences the working point and the efficiency of the high-pressure air system, while the high-pressure turbine guide vane is positioned at the outlet of the combustion chamber, has high working temperature and large thermal stress of a matrix, and generally adopts a fan-shaped structure form to release the thermal deformation of the vane edge plate and the vane body.
Reducing the throat area difference of each blade window without changing the total area of the high pressure turbine guide blades is a continuing goal to improve gas stability and reduce excitation to the high pressure turbine rotor blades. The casting variability of the blades is reduced by the early designer through improving the profile control requirement of the high-pressure turbine guide blades, improving the casting level and the like, and as the temperature of the engine is higher and higher, the area variability of each window of the high-pressure turbine guide blades is increased, and uncertainty exists for vibration damage of the turbine rotor blades.
Disclosure of Invention
The invention aims to provide a design method for the cold and hot state throat areas of high-pressure turbine guide blades, which can ensure that the hot state throat areas are equal, reduce the throat area difference between adjacent blades and further improve the gas stability.
In order to achieve the technical effects, the technical scheme adopted by the invention is as follows:
a method for designing the cold-hot state throat area of a high-pressure turbine guide vane comprises the following steps:
according to the working temperature, the thermal design size and the blade material characteristics of the high-pressure turbine guide blade, analyzing and obtaining the cold-hot state radial deformation of the upper edge plate, the cold-hot state circumferential deformation of the upper edge plate, the cold-hot state radial deformation of the lower edge plate and the cold-hot state circumferential deformation of the lower edge plate of the high-pressure turbine guide blade;
calculating the circumferential rotation angle variation of the blade close to the upper edge plate according to the cold-hot state radial deformation of the upper edge plate; calculating the circumferential rotation angle variation of the blade close to the lower edge plate according to the cold-hot state radial deformation of the lower edge plate; the method comprises the steps of using an average value of the circumferential rotation angle variation of the blades close to the upper edge plate and the circumferential rotation angle variation of the blades close to the lower edge plate as a correction value, correcting the circumferential included angle between adjacent blades, and obtaining a cold state axial included angle which enables the corrected thermal state circumferential included angle between the adjacent blades to be equal;
calculating the change of the blade mounting angle close to the upper edge plate according to the cold-hot state circumferential deformation of the upper edge plate; calculating the change of the blade mounting angle close to the lower edge plate according to the cold-hot state circumferential deformation of the lower edge plate; and correcting the width of the thermal throat area between adjacent blades by taking the average value of the blade installation angle variation close to the upper edge plate and the blade installation angle variation close to the lower edge plate as a correction value to obtain a cold state installation angle which enables the thermal throat areas of the adjacent blades to be equal.
Further according toCalculating to obtain the circumferential rotation angle variation of the blade close to the upper edge plate, wherein beta 1 For the variation of the circumferential rotation angle of the blade close to the upper edge plate, N is the number of high-pressure turbine guide blades or the number of fan-shaped sections of the high-pressure turbine guide blades, r 1 For the cold radius of the upper edge plate of the blade, a 1 Is the linear expansion coefficient, T, of the upper edge plate material 1 For the working temperature of the upper edge plate, deltaH 1 Is the radial deformation of the upper edge plate.
Further according toCalculating to obtain the circumferential rotation angle variation of the blade close to the lower edge plate, wherein beta 2 For the variation of the circumferential rotation angle of the blade close to the lower edge plate, N is the number of high-pressure turbine guide blades or the number of fan-shaped sections of the high-pressure turbine guide blades, r 2 For the cold radius of the lower edge plate of the blade, a 2 For the linear expansion coefficient, T, of the lower edge plate material 2 For the working temperature of the lower edge plate, deltaH 2 Is the radial deformation of the lower edge plate.
Further according toCalculating to obtain the change quantity beta of the blade mounting angle close to the upper edge plate 3 Wherein ΔC 1 K is the cold-hot state circumferential deformation of the upper edge plate 1 L is the cold state distance between the throat point of the blade back of the upper edge plate of the blade and the stacking shaft 2 To form the cold state distance between the throat point of the blade basin and the stacking shaft of the upper edge plate of the adjacent blade of the throat.
Further according toCalculating to obtain the change quantity beta of the blade mounting angle close to the lower edge plate 4 Wherein ΔC 2 Is the cold-hot state circumferential direction of the lower edge plateDeflection, L 3 L is the cold state distance between the throat point of the blade back of the blade lower edge plate and the stacking axis 4 To form the cold state distance between the throat point of the blade basin of the adjacent blade lower edge plate of the throat and the stacking shaft.
Further, for a high-pressure turbine guide vane formed by splicing sector sections containing a plurality of vanes, the cold radius r of the lower edge plate of the vane is maintained 2 The cold state radius r of the upper edge plate of the complete window of the blade is kept unchanged 1 The radius of the upper edge plate at the side of the splicing window of the blade is increased unchanged to beWherein r is 1 For the cold radius of the upper edge plate of the blade, a 1 Is the linear expansion coefficient, T, of the upper edge plate material 1 R is the working temperature of the upper edge plate 2 For the cold radius of the lower edge plate of the blade, a 2 Is the linear expansion coefficient, T, of the upper edge plate material 2 The working temperature of the lower edge plate; the complete window is a gap window between two adjacent blades in the same sector, and the splicing window is a gap window between two adjacent blades of the adjacent sector.
Further, for the high-pressure turbine guide vane formed by splicing the sector sections containing a plurality of vanes, the cold radius r of the upper edge plate of the vane is maintained 1 The cold state radius r of the upper edge plate of the complete window of the blade is kept unchanged 2 The radius of the lower edge plate at the side of the splicing window of the blade is reduced to be unchangedWherein r is 1 For the cold radius of the upper edge plate of the blade, a 1 Is the linear expansion coefficient, T, of the upper edge plate material 1 R is the working temperature of the upper edge plate 2 For the cold radius of the lower edge plate of the blade, a 2 Is the linear expansion coefficient, T, of the upper edge plate material 2 The working temperature of the lower edge plate; the complete window is a gap window between two adjacent blades in the same sector, and the splicing window is a gap window between two adjacent blades of the adjacent sector.
Compared with the prior art, the invention has the following beneficial effects: in the design process of the high-pressure turbine guide vane, the cold-hot state conversion is carried out on the basis of the initial design vane shape and the hot state size of the runner of the high-pressure turbine guide vane, so that the cold-hot state radial deformation of the upper edge plate and the cold-hot state radial deformation of the lower edge plate of the high-pressure turbine guide vane are obtained, and the vane mounting angle variation of the high-pressure turbine guide vane close to the upper edge plate and the vane mounting angle variation of the high-pressure turbine guide vane close to the lower edge plate are obtained through analysis; the circumferential angle between adjacent vanes and the width of the throat area between adjacent vanes are corrected. The multi-dimensional deformation existing between the cold state and the hot state of the high-pressure turbine guide vane is comprehensively considered, and finally the vane shape of the high-pressure turbine guide vane and the cold state size of the flow passage after the area of the throat of the cold state and the hot state is corrected are obtained. The method can ensure that the thermal state throat areas of all windows of the high-pressure turbine guide vane are equal, and reduces the condition that the throat areas between adjacent vanes are large in difference, so that the consistency of outlet gas flow parameters of the high-pressure turbine guide vane is improved, the dispersity of pneumatic excitation frequency is reduced, the aeroelastic stability of the downstream rotor vane is improved, and the risk of high-cycle fatigue cracks of the rotor vane is reduced.
Drawings
FIG. 1 is a schematic view showing a cold state structure of a high pressure turbine guide vane in embodiment 1 or 2;
FIG. 2 is a schematic representation of the cold design width of the throat area of the blade proximate to the upper edge plate in examples 1 or 2;
FIG. 3 is a schematic representation of the cold design width of the throat area of the blade proximate to the lower edge panel in examples 1 or 2;
wherein, 1, upper edge plate; 2. a lower edge plate; 3. the shaft is stacked.
Detailed Description
The present invention will be described in further detail with reference to the following examples and drawings. It should not be construed that the scope of the above subject matter of the present invention is limited to the following embodiments, and all techniques realized based on the present invention are within the scope of the present invention.
Example 1
Referring to fig. 1-3, a method for designing a cold and hot throat area of a high pressure turbine guide vane includes:
according to the working temperature, the thermal design size and the blade material characteristics of the high-pressure turbine guide blade, the cold-hot state radial deformation delta H of the upper edge plate 1 of the high-pressure turbine guide blade is obtained through analysis 1 Cold and hot state circumferential deformation delta C of upper edge plate 1 1 Radial deformation ΔH of lower flange plate 2 in cold and hot state 2 The cold-hot state circumferential deformation amount deltac of the lower edge plate 2 2 ；
Calculating the circumferential rotation angle variation of the blades close to the upper edge plate 1 according to the cold-hot state radial deformation of the upper edge plate 1; calculating the circumferential rotation angle variation of the blades close to the lower edge plate 2 according to the cold-hot state radial deformation of the lower edge plate 2; taking the average value of the circumferential rotation angle variation of the blades close to the upper edge plate 1 and the circumferential rotation angle variation of the blades close to the lower edge plate 2 as a correction value, and correcting the circumferential included angle between the adjacent blades to obtain a cold state axial included angle which enables the corrected thermal state circumferential included angle between the adjacent blades to be equal;
calculating the change of the blade mounting angle close to the upper edge plate 1 according to the cold and hot state circumferential deformation of the upper edge plate 1; calculating the change of the blade mounting angle close to the lower edge plate 2 according to the cold-hot state circumferential deformation of the lower edge plate 2; and correcting the width of the thermal throat area between adjacent blades by taking the average value of the blade installation angle variation close to the upper edge plate 1 and the blade installation angle variation close to the lower edge plate 2 as a correction value to obtain a cold state installation angle for making the thermal throat areas of the adjacent blades equal.
In the present embodiment, during the design process of the high-pressure turbine guiding vane, the cold-hot state conversion is performed on the basis of the initial design vane shape and the hot state size of the runner of the high-pressure turbine guiding vane, so as to obtain the cold-hot state radial deformation of the upper edge plate 1 and the cold-hot state radial deformation of the lower edge plate 2 of the high-pressure turbine guiding vane, and the vane mounting angle variation of the high-pressure turbine guiding vane close to the upper edge plate 1 and the vane mounting angle variation of the high-pressure turbine guiding vane close to the lower edge plate 2 are obtained through analysis; the circumferential angle between adjacent vanes and the width of the throat area between adjacent vanes are corrected. The multi-dimensional deformation existing between the cold state and the hot state of the high-pressure turbine guide vane is comprehensively considered, and finally the vane shape of the high-pressure turbine guide vane and the cold state size of the flow channel after the correction of the cold state throat area are obtained, so that the equal hot state throat areas of all windows of the high-pressure turbine guide vane can be ensured, the condition that the throat area difference between adjacent vanes is large is reduced, the consistency of the outlet gas flow parameters of the high-pressure turbine guide vane is improved, the dispersity of the pneumatic excitation frequency is reduced, the gas-elastic stability of the downstream rotor vane is improved, and the risk of high-cycle fatigue cracks of the rotor vane is reduced.
The cold state structure of the high pressure turbine guide vane is schematically shown in FIG. 1, wherein the solid line part is the cold state size of the vane, and the dotted line part is the hot state size in operation. According to the embodimentCalculating to obtain the circumferential rotation angle variation of the blade close to the upper edge plate 1, wherein beta 1 For the variation of the circumferential angle of rotation of the blade close to the upper edge plate 1, N is the number of high-pressure turbine guide blades or the number of sectors of the high-pressure turbine guide blades, r 1 For the cold radius, a, of the blade upper edge plate 1 1 The linear expansion coefficient, T, of the material of the upper edge plate 1 1 For the operating temperature of the upper edge plate 1 ΔH 1 Is the radial deformation of the upper rim plate 1.
According to the embodimentCalculating to obtain the circumferential rotation angle variation of the blade close to the upper edge plate 1, wherein beta 2 For the variation of the circumferential angle of rotation of the blades close to the lower edge plate 2, N is the number of high-pressure turbine guide blades or the number of sectors of the high-pressure turbine guide blades, r 2 For the cold radius, a, of the lower blade edge plate 2 2 The linear expansion coefficient, T, of the material of the upper edge plate 1 2 For the operating temperature of the lower edge plate 2 ΔH 2 Is the radial deformation of the lower rim plate 2.
According to the embodimentCalculating to obtain the upper edge plate 1Blade mounting angle variation beta 3 Wherein ΔC 1 Is the cold-hot state circumferential deformation quantity L of the upper edge plate 1 1 L is the cold state distance between the throat point of the back of the blade of the upper edge plate 1 and the stacking shaft 3 2 In order to form the cold state distance between the throat point of the basin of the upper edge plate 1 of the adjacent blade of the throat and the stacking shaft 3, the cold and hot state circumferential deformation delta C of the upper edge plate 1 1 Can be according to DeltaC 1 ＝ 1 T 1 S 1 Calculated to obtain a 1 Is the linear expansion coefficient, T, of the upper edge plate material 1 Is the working temperature of the upper edge plate, S 1 The width is designed for the cold state of the throat area of the blade near the upper edge plate.
According toCalculating to obtain the change quantity beta of the blade mounting angle close to the lower edge plate 2 4 Wherein ΔC 2 For the cold-hot state circumferential deformation of the lower edge plate 2, L 3 L is the cold state distance between the throat point of the vane back of the vane lower edge plate 2 and the stacking shaft 3 4 To form the cold state distance between the throat point of the basin of the lower edge plate 2 of the adjacent blade of the throat and the stacking shaft 3, the cold state circumferential deformation delta C of the lower edge plate 2 2 Can be according to DeltaC 2 ＝ 2 T 2 S 2 Calculated to obtain a 2 For the linear expansion coefficient, T, of the lower edge plate material 2 For the working temperature of the lower edge plate S 2 The width is designed for the cold state of the throat area of the blade near the lower edge plate.
The cold state deformation, the installation angle change and the circumferential rotation angle change of the upper edge plate and the lower edge plate of the high-pressure turbine guide vane, which directly influence the throat area window length values of the vane, are respectively obtained by calculating a plurality of deformation of the vane one by one in the cold state and hot state working processes, and according to the different change of the vane areas, the structural characteristics, the manufacturing mode and the use scene of each high-pressure turbine guide vane can be combined, the conversion and the correction of the cold state and the hot state of the corresponding dimension are comprehensively carried out, and the cold state installation angle and the circumferential included angle of the high-pressure turbine guide vane are obtained.
Example 2
Referring to fig. 1-3, a method for designing a cold and hot throat area of a high pressure turbine guide vane includes:
according to the working temperature, the thermal design size and the blade material characteristics of the high-pressure turbine guide blade, the cold-hot state radial deformation delta H of the upper edge plate 1 of the high-pressure turbine guide blade is obtained through analysis 1 Cold and hot state circumferential deformation delta C of upper edge plate 1 1 Radial deformation ΔH of lower flange plate 2 in cold and hot state 2 The cold-hot state circumferential deformation amount deltac of the lower edge plate 2 2 ；
Calculating the circumferential rotation angle variation of the blades close to the upper edge plate 1 according to the cold-hot state radial deformation of the upper edge plate 1; calculating the circumferential rotation angle variation of the blades close to the lower edge plate 2 according to the cold-hot state radial deformation of the lower edge plate 2; taking the average value of the circumferential rotation angle variation of the blades close to the upper edge plate 1 and the circumferential rotation angle variation of the blades close to the lower edge plate 2 as a correction value, and correcting the circumferential included angle between the adjacent blades to obtain a cold state axial included angle which enables the corrected thermal state circumferential included angle between the adjacent blades to be equal;
calculating the change of the blade mounting angle close to the upper edge plate 1 according to the cold and hot state circumferential deformation of the upper edge plate 1; calculating the change of the blade mounting angle close to the lower edge plate 2 according to the cold-hot state circumferential deformation of the lower edge plate 2; and correcting the width of the thermal throat area between adjacent blades by taking the average value of the blade installation angle variation close to the upper edge plate 1 and the blade installation angle variation close to the lower edge plate 2 as a correction value to obtain a cold state installation angle for making the thermal throat areas of the adjacent blades equal.
In the design process of the high-pressure turbine guide vane configuration, the whole-ring vane is generally and uniformly divided into N sector sections, for example, a double-vane and triple-vane structure is generally adopted to reduce thermal stress and reduce cold air leakage. However, since the expansion amount of the high-pressure turbine guide vane is large in a high-temperature environment, the throat area difference between different windows of the vane can be increased in a cold-hot state, and the window area difference can change the pressure and speed of fuel gas, which is harmful to the vibration of the high-pressure turbine guide vane. Thus, the high-pressure turbine formed by splicing the sector segments containing a plurality of blades in the embodimentGuide vane, maintaining the cold radius r of the lower edge plate 2 of the vane 2 Unchanged, the cold radius r of the upper edge plate 1 for keeping the complete window of the blade 1 On the premise of unchanged, the radius of the upper edge plate 1 on the side of the splicing window of the blade is increased to beWherein r is 1 For the cold radius, a, of the blade upper edge plate 1 1 The linear expansion coefficient, T, of the material of the upper edge plate 1 1 For the working temperature of the upper edge plate 1, r 2 For the cold radius, a, of the lower blade edge plate 2 2 The linear expansion coefficient, T, of the material of the upper edge plate 1 2 The working temperature of the lower edge plate 2; the complete window is a gap window between two adjacent blades in the same sector, and the splicing window is a gap window between two adjacent blades of the adjacent sector.
In this embodiment, besides increasing the radius of the upper edge plate 1 at the side of the blade splicing window, for the high-pressure turbine guiding blade formed by splicing the fan-shaped segments containing a plurality of blades, the method of maintaining the cold radius r of the upper edge plate 1 of the blade can also be adopted 1 The cold state radius r of the upper edge plate 1 of the complete window of the blade is kept unchanged 2 On the premise of unchanged, the radius of the lower edge plate 2 at the side of the blade splicing window is reduced to beWherein r is 1 For the cold radius, a, of the blade upper edge plate 1 1 The linear expansion coefficient, T, of the material of the upper edge plate 1 1 For the working temperature of the upper edge plate 1, r 2 For the cold radius, a, of the lower blade edge plate 2 2 The linear expansion coefficient, T, of the material of the upper edge plate 1 2 Is the operating temperature of the lower edge plate 2.
In this embodiment, for the high-pressure turbine guide vane formed by splicing the fan-shaped segments including a plurality of vanes, on the basis of correcting the circumferential included angle between adjacent vanes and the width of the throat area between adjacent vanes, one of two methods of increasing the radius of the upper edge plate 1 on the side of the vane splicing window or reducing the radius of the lower edge plate 2 on the side of the vane splicing window is optional.
Other portions in this embodiment are the same as those in embodiment 1, and will not be described here again.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (7)
1. A method for designing the cold and hot state throat area of a high-pressure turbine guide vane is characterized by comprising the following steps:
according to the working temperature, the thermal design size and the blade material characteristics of the high-pressure turbine guide blade, analyzing and obtaining the cold-hot state radial deformation of the upper edge plate, the cold-hot state circumferential deformation of the upper edge plate, the cold-hot state radial deformation of the lower edge plate and the cold-hot state circumferential deformation of the lower edge plate of the high-pressure turbine guide blade;
calculating the circumferential rotation angle variation of the blade close to the upper edge plate according to the cold-hot state radial deformation of the upper edge plate; calculating the circumferential rotation angle variation of the blade close to the lower edge plate according to the cold-hot state radial deformation of the lower edge plate; the method comprises the steps of using an average value of the circumferential rotation angle variation of the blades close to the upper edge plate and the circumferential rotation angle variation of the blades close to the lower edge plate as a correction value, correcting the circumferential included angle between adjacent blades, and obtaining a cold state axial included angle which enables the corrected thermal state circumferential included angle between the adjacent blades to be equal;
calculating the change of the blade mounting angle close to the upper edge plate according to the cold-hot state circumferential deformation of the upper edge plate; calculating the change of the blade mounting angle close to the lower edge plate according to the cold-hot state circumferential deformation of the lower edge plate; and correcting the width of the thermal throat area between adjacent blades by taking the average value of the blade installation angle variation close to the upper edge plate and the blade installation angle variation close to the lower edge plate as a correction value to obtain a cold state installation angle which enables the thermal throat areas of the adjacent blades to be equal.
2. The method for designing cold and hot throat area of high pressure turbine guide vane according to claim 1, wherein the method comprises the steps ofCalculating to obtain the circumferential rotation angle variation of the blade close to the upper edge plate, wherein beta 1 For the variation of the circumferential rotation angle of the blade close to the upper edge plate, N is the number of high-pressure turbine guide blades or the number of fan-shaped sections of the high-pressure turbine guide blades, r 1 For the cold radius of the upper edge plate of the blade, a 1 Is the linear expansion coefficient, T, of the upper edge plate material 1 For the working temperature of the upper edge plate, deltaH 1 Is the radial deformation of the upper edge plate.
3. The method for designing cold and hot throat area of high pressure turbine guide vane according to claim 2, wherein the method comprises the steps ofCalculating to obtain the circumferential rotation angle variation of the blade close to the lower edge plate, wherein beta 2 For the variation of the circumferential rotation angle of the blade close to the lower edge plate, N is the number of high-pressure turbine guide blades or the number of fan-shaped sections of the high-pressure turbine guide blades, r 2 For the cold radius of the lower edge plate of the blade, a 2 For the linear expansion coefficient, T, of the lower edge plate material 2 For the working temperature of the lower edge plate, deltaH 2 Is the radial deformation of the lower edge plate.
4. The method for designing cold and hot throat area of high pressure turbine guide vane according to claim 1, wherein the method comprises the steps ofCalculating to obtain the change quantity beta of the blade mounting angle close to the upper edge plate 3 Wherein ΔC 1 Is the cold-hot state circumferential deformation quantity of the upper edge plate, L 1 L is the cold state distance between the throat point of the blade back of the upper edge plate of the blade and the stacking shaft 2 To form the cold state distance between the throat point of the blade basin and the stacking shaft of the upper edge plate of the adjacent blade of the throat.
5. According toThe method for designing cold and hot throat area of high pressure turbine guide vane as set forth in claim 1, wherein, according to the methodCalculating to obtain the change quantity beta of the blade mounting angle close to the lower edge plate 4 Wherein ΔC 2 Is the cold-hot state circumferential deformation quantity of the lower edge plate, L 3 L is the cold state distance between the throat point of the blade back of the blade lower edge plate and the stacking axis 4 To form the cold state distance between the throat point of the blade basin of the adjacent blade lower edge plate of the throat and the stacking shaft.
6. The method for designing cold and hot throat area of high-pressure turbine guide vane according to claim 1, wherein for the high-pressure turbine guide vane composed of a plurality of spliced segments of vanes, the cold radius r of the lower edge plate of the vane is maintained 2 The cold state radius r of the upper edge plate of the complete window of the blade is kept unchanged 1 The radius of the upper edge plate at the side of the splicing window of the blade is increased unchanged to beWherein r is 1 For the cold radius of the upper edge plate of the blade, a 1 Is the linear expansion coefficient, T, of the upper edge plate material 1 R is the working temperature of the upper edge plate 2 For the cold radius of the lower edge plate of the blade, a 2 Is the linear expansion coefficient, T, of the upper edge plate material 2 The working temperature of the lower edge plate; the complete window is a gap window between two adjacent blades in the same sector, and the splicing window is a gap window between two adjacent blades of the adjacent sector.
7. The method for designing cold and hot throat area of high-pressure turbine guide vane according to claim 1, wherein for the high-pressure turbine guide vane composed of a plurality of spliced segments of vanes, the cold radius r of the upper edge plate of the vane is maintained 1 The cold state radius r of the upper edge plate of the complete window of the blade is kept unchanged 2 Unchanged, reduced blade splicing window sideLower edge plate radiusWherein r is 1 For the cold radius of the upper edge plate of the blade, a 1 Is the linear expansion coefficient, T, of the upper edge plate material 1 R is the working temperature of the upper edge plate 2 For the cold radius of the lower edge plate of the blade, a 2 Is the linear expansion coefficient, T, of the upper edge plate material 2 The working temperature of the lower edge plate; the complete window is a gap window between two adjacent blades in the same sector, and the splicing window is a gap window between two adjacent blades of the adjacent sector.
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