CN113607119B - Marine gas turbine blade throat area measurement method based on characteristic dimension - Google Patents
Marine gas turbine blade throat area measurement method based on characteristic dimension Download PDFInfo
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- 238000005259 measurement Methods 0.000 claims abstract description 21
- 238000009423 ventilation Methods 0.000 claims description 3
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/28—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring areas
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Abstract
The invention aims to provide a measuring method for the throat area of a marine gas turbine blade based on characteristic dimensions, which comprises the steps of firstly finding a throat plane in the turbine blade, then selecting a characteristic length H and two characteristic widths X, Y which meet the area conservation in the throat window plane, and measuring the three characteristic dimensions to obtain the measuring method for the throat area of the turbine during actual measurement. The invention solves the problems that the prior measuring method has complex early programming, the quality and the difference of the actual blade profile easily cause certain deviation of the measured throat area value, and the measuring method depends on a large three-coordinate device. The measuring method has the advantages that the measured face value is the same as the theoretical value, the change condition of the throat area can be correctly reflected, the measuring operation is simple, and the accurate measurement can be realized only by a measuring tool which is not larger than the blade.
Description
Technical Field
The invention relates to a gas turbine measuring method, in particular to a turbine blade measuring method.
Background
Marine gas turbines are complex and accurate products that operate in severe environments with high temperature, high pressure, high rotational speeds, and high salt spray corrosion. The throat area of the turbine blade refers to the area of the smallest part of the through flow surface between two adjacent blades of the turbine, and the shape of the throat of the blade is a quadrangle with four corners rounded.
The throat area index has important influence on the power, efficiency and even the performance parameters of the turbine component, and when the performance of the whole turbine, especially the axial force, efficiency and other parameters, cannot meet the design requirements, the adjustment of the throat area is one of important means. Therefore, the accuracy of the throat area measurement is critical, and the throat area measurement is required to have good repeatability and stability.
In order to measure the area of an irregular quadrilateral, the current method for measuring the throat area of the turbine blade of the engine mostly adopts a three-coordinate modeling method to measure the coordinates of each point on the blade, a three-dimensional model of an actual blade is obtained by fitting a spatial surface of the throat of the blade, and then the throat area is obtained by programming treatment. The method has complex early programming, the quality and the difference of the actual blade profile easily cause certain deviation of the measured throat area value, and the measurement is dependent on large three-coordinate equipment.
In summary, the existing method for measuring the throat area of the turbine blade of the marine gas turbine has the problems of complex flow and dependence on large-scale test equipment.
Disclosure of Invention
The invention aims to provide a method for measuring the throat area of the marine gas turbine blade based on characteristic dimensions, which can solve the problems of more measurement points, dependence on large-scale equipment, poor repeatability and the like of the conventional method for measuring the throat area of the turbine blade.
The purpose of the invention is realized in the following way:
The invention discloses a method for measuring the throat area of a turbine blade of a marine gas turbine based on characteristic dimensions, which is characterized by comprising the following steps of:
(1) Connecting the upper end point and the lower end point of the tail edge of each blade to form a straight line, taking an angle as a plane through the straight line, and intercepting the part surrounded by the two blades and the upper edge plate and the lower edge plate as a ventilation part;
(2) The plane angle is changed, and a plane with the smallest flow area is found to obtain the theoretical area S of the throat part of the blade;
(3) Selecting a measurement characteristic height H at a position which is 1-3mm away from the center of the throat according to the throat plane;
(4) Selecting a position 10% -35% of the length of the upper end point and the lower end point of the distance H as a point through which the characteristic width dimension X, Y passes;
(5) The feature points are used as line segments with the shortest length on two sides in the throat plane, namely the feature size X, Y;
(6) Judging whether the feature size satisfies S= (X+Y)/2×H; when the criterion is met, the selected characteristic size is proper, and the next step is carried out to measure the actual blade by adopting the method; returning to the step (4) to readjust X, Y when the criterion cannot be met;
(7) For an actual blade, the actual characteristic dimension is measured by means of a measuring tool to obtain the throat area of the turbine blade.
The invention may further include:
1. The theoretical area S of the throat of the blade is determined by: two through-flow planes are made by two angles A1 and A2 with larger change, so that the angle corresponding to the minimum area is ensured to be positioned between A1 and A2, a new through-flow plane is established and the area is measured by the angle A3= (A1+A2)/2, the redefined corresponding area in A1 and A2 is A2, A3 is redefined as A1, the process is repeated until the area change of the through-flow plane meets the precision requirement, and at the moment, the plane with the minimum through-flow area is found, and the plane area is the throat plane area S of the blade.
2. The feature size X, Y is determined by the passing feature point, and the position is more than 10% H from the upper edge plate and the lower edge plate of the blade, so that the interference of rounding four corners of the throat window is avoided during measurement, and a measurement space is reserved for measuring the feature size H.
3. In the step (7), a positioning point is searched according to the structure of the actual blade, the positioning is completed by utilizing the front blade and the rear blade, a plane to be measured is found after the positioning is completed, the actual characteristic dimension X k、Yk、Hk is measured in sequence, and then the throat area S k＝(Xk+Yk)/2×Hk with the blades is obtained.
The invention has the advantages that:
1. The method for measuring the throat area of the turbine blade has the advantages that the measurement size is small, only three characteristic sizes are needed, the calculation is simple, and the original data recording is convenient; the traditional measurement method needs to measure coordinate point parameters of the whole throat of the blade, and special programming treatment is needed when the throat area is calculated.
2. The method is simple to operate, and the three measured characteristic dimensions are all in the same plane, so that accurate measurement can be realized only after the measuring tool which is not larger than the blade finds the throat plane, and the traditional method can realize measurement of the throat area only by large-scale equipment.
3. The method ensures that the measured area is consistent with the theoretical throat area in theory through the area conservation principle.
4. The characteristic dimension selected by the method has two circumferential width dimensions and radial height dimensions, and can correctly reflect the out-of-tolerance change condition of the throat area of the blade.
Drawings
FIG. 1 is a schematic diagram of the present invention;
fig. 2 is a flow chart of the present invention.
Detailed Description
The invention is described in more detail below, by way of example, with reference to the accompanying drawings:
1-2, the invention provides a method for measuring the throat area of a turbine blade of a marine gas turbine based on characteristic dimensions, which mainly comprises the following steps:
(1) The upper and lower end points of the tail edge of the connecting blade form a straight line, a plane is formed by a certain angle through the straight line, and the part surrounded by the two blades and the upper and lower edge plates thereof is taken as a ventilation part.
(2) And (3) converting the plane angle, and finding a plane with the minimum flow area to obtain the theoretical area S of the throat part of the blade:
Firstly, two through-flow planes are made at two angles A1 and A2 with larger variation in modeling software, so that the angle corresponding to the minimum area is ensured to be between A1 and A2. A new through-flow plane is established and the area is measured at an angle a3= (a1+a2)/2, wherein a corresponding area in A1 and A2 is redefined as A2, and A3 is redefined as A1. And repeating the process until the area change of the through flow plane reaches the precision requirement, and finding out the plane with the smallest through flow area, wherein the plane area is the throat plane area S of the blade.
(3) The measurement feature height H is selected 1-3mm from the throat center, depending on the throat plane:
In order to ensure that the throat area change rule obtained by measuring according to the characteristic values is consistent with the actual blade throat area change rule, characteristic dimensions are selected in the length direction and the width direction. It is first necessary to determine the measurement location of the feature height H, which must be offset to one side in the circumferential direction as shown in fig. 1, to allow measurement space for the measurement X, Y.
(4) The 10% -35% length of the upper and lower end points of the distance H is selected as the passing point of the characteristic width dimension X, Y:
Feature size X, Y is located by the passing feature point. The position is more than 10% H away from the upper and lower edge plates of the blade to ensure that the interference of rounding at four corners of the throat window is avoided in actual measurement and a measurement space is reserved for measuring the characteristic dimension H.
(5) And (3) making a line segment with the shortest length connecting the two sides in the throat plane by the feature points, namely the feature size X, Y.
(6) Judging whether the feature size satisfies s= (x+y)/2×h:
In order to ensure that the area obtained by measuring the feature size is consistent with the theoretical value, the selected feature size needs to meet S= (X+Y)/2 XH. When the criterion is met, the selected characteristic size is considered to be proper, and the next step can be carried out to measure the actual blade by adopting the method; when this criterion is not met, the position of X, Y needs to be readjusted back to step (4). As shown in fig. 1, generally, the throat width in the turbine blade changes monotonically with the height, and when the characteristic size judgment basis cannot be met, the upper and lower positions of X, Y can be readjusted to meet the judgment, so that the throat area measured by the method is consistent with the area of the theoretical throat area.
(7) For an actual blade, the actual characteristic dimension is measured by means of a measuring tool to obtain the throat area of the turbine blade.
The measuring method can adopt a special measuring tool, a tool and a fixture designed for the method to measure. Firstly, locating points are found according to the structure of the actual blade, and the locating should be generally completed by utilizing the front blade and the rear blade. After the positioning is completed, a plane to be measured is found, and the actual feature sizes Xk, yk and Hk are measured in sequence, so that the throat area Sk with the blades is= (Xk+Yk)/2 XHk.
Claims (4)
1. The method for measuring the throat area of the turbine blade of the marine gas turbine based on the characteristic dimension is characterized by comprising the following steps of:
(1) Connecting the upper end point and the lower end point of the tail edge of each blade to form a straight line, taking an angle as a plane through the straight line, and intercepting the part surrounded by the two blades and the upper edge plate and the lower edge plate as a ventilation part;
(2) The plane angle is changed, and a plane with the smallest flow area is found to obtain the theoretical area S of the throat part of the blade;
(3) Selecting a measurement characteristic height H at a position which is 1-3mm away from the center of the throat according to the throat plane;
(4) Selecting a position 10% -35% of the length of the upper end point and the lower end point of the distance H as a point through which the characteristic width dimension X, Y passes;
(5) The feature points are used as line segments with the shortest length on two sides in the throat plane, namely the feature size X, Y;
(6) Judging whether the feature size satisfies S= (X+Y)/2×H; when the criterion is met, the selected characteristic size is proper, and the next step is carried out to measure the actual blade by adopting the method; returning to the step (4) to readjust X, Y when the criterion cannot be met;
(7) For an actual blade, the actual characteristic dimension is measured by means of a measuring tool to obtain the throat area of the turbine blade.
2. The feature size based marine gas turbine blade throat area measurement method of claim 1, wherein: the theoretical area S of the throat of the blade is determined by: two through-flow planes are made by two angles A1 and A2 with larger change, so that the angle corresponding to the minimum area is ensured to be positioned between A1 and A2, a new through-flow plane is established and the area is measured by the angle A3= (A1+A2)/2, the redefined corresponding area in A1 and A2 is A2, A3 is redefined as A1, the process is repeated until the area change of the through-flow plane meets the precision requirement, and at the moment, the plane with the minimum through-flow area is found, and the plane area is the throat plane area S of the blade.
3. The feature size based marine gas turbine blade throat area measurement method of claim 1, wherein: the feature size X, Y is determined by the passing feature point, and the position is more than 10% H from the upper edge plate and the lower edge plate of the blade, so that the interference of rounding four corners of the throat window is avoided during measurement, and a measurement space is reserved for measuring the feature size H.
4. The feature size based marine gas turbine blade throat area measurement method of claim 1, wherein: in the step (7), a positioning point is searched according to the structure of the actual blade, the positioning is completed by utilizing the front blade and the rear blade, a plane to be measured is found after the positioning is completed, the actual characteristic dimension X k、Yk、Hk is measured in sequence, and then the throat area S k＝(Xk+Yk)/2×Hk with the blades is obtained.
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| CN114252035B (en) * | 2021-11-08 | 2023-07-07 | 安徽应流航源动力科技有限公司 | Size detection method for turbine blade disc |
| CN116164695B (en) * | 2023-04-23 | 2023-07-21 | 中国航发沈阳发动机研究所 | Turbine guide and exhaust area measurement method thereof |
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