Method for measuring non-steady velocity field distribution before and after turbine component test secondary guide vanes

Abstract

The application belongs to the technical field of two-stage turbine component test two-stage guide vane front and back unsteady velocity field distribution measurement, and particularly relates to a turbine component test two-stage guide vane front and back unsteady velocity field distribution measurement method. The method determines the circumferential and radial fluctuation velocity measurement point distribution by using the middle-arc line extension line of adjacent two-stage guide vanes, front and back edge lines, and front and back rotor blade trailing edges and leading edges, and performs dynamic measurement of flow velocity, so that efficient and accurate measurement of two-stage guide vane front and back unsteady velocity field distribution can be realized in limited space.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of measuring the unsteady velocity field distribution in front of and behind the secondary guide vane in a two-stage turbine component test, and particularly relates to a method for measuring the unsteady velocity field distribution in front of and behind the secondary guide vane in a turbine component test. BACKGROUND

[0002] A turbine is a core hot end component of an aero-engine or a gas turbine, and its internal flow, heat exchange, geometry and other changes under a transition state are extremely complex, and it is the part that faces the highest risk.

[0003] A turbine component test can directly obtain effective data of changes in aerodynamic, thermal, structural and other parameters in the turbine, and can be used to support the matching design of an aero-engine or a gas turbine.

[0004] In a turbine component test, the measurement of the surface parameters of the guide vane is involved, including temperature, pressure and the like. For this purpose, a certain guide vane is usually modified into a test modified blade, and temperature, pressure and other measuring points are arranged on the back of the blade to measure the surface parameters. For a two-stage turbine, the surface parameters of the secondary guide vane are not only affected by the turbine inlet environment, the overall load level of the turbine, the Reynolds number and other factors, but also related to the flow velocity distribution in front of and behind the blade. At present, there is a lack of accurate means for measuring the unsteady velocity field distribution in front of and behind the secondary guide vane, and it is difficult to analyze the correlation of the surface parameters of the secondary guide vane, which limits the application of the test results.

[0005] The present application is proposed in view of the above technical defects.

[0006] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present patent application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0007] The purpose of the present application is to provide a method for measuring the unsteady velocity field distribution in front of and behind the secondary guide vane in a turbine component test, so as to overcome or alleviate at least one aspect of the known technical defects.

[0008] The technical solution of the present application is:

[0009] A method for measuring the unsteady velocity field distribution in front of and behind the secondary guide vane in a turbine component test, comprising:

[0010] Selecting adjacent secondary guide vanes as a first blade and a second blade;

[0011] A point S is taken as the intersection of the first blade mid-arc line extension and the first-stage guide vane leading edge ordinate line, a vertical line is drawn from the point S to the rotor blade trailing edge ordinate line, the midpoint of the vertical line is a point B, a parallel line is drawn through the point B and parallel to the first-stage guide vane trailing edge ordinate line, the intersection of the parallel line and the first blade mid-arc line extension is a point F, and the intersection of the parallel line and the second blade mid-arc line extension is a point A, and the midpoint of the line connecting the point F and the point A is a point H;

[0012] A point S' is taken as the intersection of the first blade mid-arc line extension and the first-stage guide vane trailing edge ordinate line, a vertical line is drawn from the point S' to the rotor blade leading edge ordinate line, the midpoint of the vertical line is a point B', a parallel line is drawn through the point B' and parallel to the first-stage guide vane trailing edge ordinate line, the intersection of the parallel line and the first blade mid-arc line extension is a point F', and the intersection of the parallel line and the second blade mid-arc line extension is a point A', and the midpoint of the line connecting the point F' and the point A' is a point H';

[0013] In the double-stage turbine, dynamic flow velocity measuring points are arranged along the line connecting the point A and the point B and the line connecting the point A' and the point B' in the circumferential direction, and the dynamic flow velocity measuring points are arranged along the blade height through the point H and the point H' in the radial direction, so as to measure the first-stage guide vane leading and trailing flow velocity distribution.

[0014] According to at least one embodiment of the present application, in the method for measuring the first-stage guide vane leading and trailing unsteady velocity field distribution of the turbine component, the first blade is located in the suction side direction of the second blade;

[0015] The second blade is a test retrofit blade;

[0016] The dynamic flow velocity measuring points are arranged along the line connecting the point A and the point B and the line connecting the point A' and the point B' in the circumferential direction, and the dynamic flow velocity measuring points are arranged at the blade height of the test retrofit blade in the radial direction.

[0017] According to at least one embodiment of the present application, in the method for measuring the first-stage guide vane leading and trailing unsteady velocity field distribution of the turbine component, the dynamic flow velocity measuring points arranged along the line connecting the point A and the point B in the circumferential direction are less dense between the point B and the point F;

[0018] The dynamic flow velocity measuring points arranged along the line connecting the point A' and the point B' in the circumferential direction are less dense between the point B' and the point F'.

[0019] According to at least one embodiment of the present application, in the method for measuring the first-stage guide vane leading and trailing unsteady velocity field distribution of the turbine component, the first-stage guide vane leading and trailing flow velocity distribution is measured, and specifically:

[0020] The hot wire probe is driven by the displacement mechanism to perform circumferential lock-in scanning field measurement along the line connecting the point A and the point B and the line connecting the point A' and the point B' in the circumferential direction;

[0021] The hot wire probe is driven by the displacement mechanism to perform radial lock-in scanning field measurement along the blade height through the point H and the point H' in the radial direction. Attached Figure Description

[0022] Fig. 1 This is a schematic diagram of the method for measuring the unsteady velocity field distribution before and after the second-stage guide vane of a turbine component test, provided in an embodiment of this application.

[0023] Fig. 2 This is a schematic diagram of the dynamic velocity measurement point distribution in the measurement of the unsteady velocity field distribution before and after the second-stage guide vane of the two-stage turbine component test provided in the embodiments of this application.

[0024] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0025] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0026] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0027] In addition, it needs to be explained that, unless otherwise explicitly specified and limited, the similar words such as "mounting", "connecting", "connecting" and the like used in the description of the application should be understood in a broad sense, for example, the connection can be fixed connection, or detachable connection, or integral connection; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the internal communication of two elements, and the person skilled in the art can understand the specific meaning of the application according to the specific circumstances.

[0028] The application will be further described below in conjunction with the accompanying drawings Figs. 1-2 The application will be further described below in conjunction with the accompanying drawings

[0029] A method for measuring the unsteady velocity field distribution in front of and behind the secondary guide vane of a turbine component test, comprising:

[0030] Selecting adjacent secondary guide vanes as the first vane and the second vane;

[0031] Taking the intersection of the first vane camber line extension and the secondary guide vane leading edge ordinate as point S, drawing a vertical line from point S to the trailing edge ordinate of the upstream rotor vane, the midpoint of the vertical line being point B, drawing a parallel line through point B parallel to the secondary guide vane leading edge ordinate, the intersection of the parallel line and the first vane camber line extension being point F, and the intersection of the parallel line and the second vane camber line extension being point A, the midpoint of the line connecting point F and point A being point H;

[0032] Taking the intersection of the first vane camber line extension and the secondary guide vane trailing edge ordinate as point S', drawing a vertical line from point S' to the leading edge ordinate of the downstream rotor vane, the midpoint of the vertical line being point B', drawing a parallel line through point B' parallel to the secondary guide vane trailing edge ordinate, the intersection of the parallel line and the first vane camber line extension being point F', and the intersection of the parallel line and the second vane camber line extension being point A', the midpoint of the line connecting point F' and point A' being point H';

[0033] In the double-stage turbine, dynamic flow velocity measuring points are arranged along the line connecting point A and point B and the line connecting point A' and point B' in the circumferential direction, and dynamic flow velocity measuring points are arranged along the blade height through point H and point H' in the radial direction, so as to measure the unsteady velocity field distribution in front of and behind the secondary guide vane, and the measured flow velocity distribution can be periodically extended to the entire measurement section in the circumferential direction, that is, the unsteady velocity field distribution in the entire measurement section can be obtained.

[0034] For the method for measuring the unsteady velocity field distribution in front of and behind the secondary guide vane of a turbine component test disclosed in the above embodiment, the person skilled in the art can understand that the design utilizes the camber line extension, the leading edge ordinate and the trailing edge ordinate of the adjacent secondary guide vanes, and the trailing edge ordinate and the leading edge ordinate of the upstream and downstream rotor vanes to determine the distribution of the dynamic flow velocity measuring points in the circumferential direction and the radial direction, and to perform flow velocity measurement, so as to realize efficient and accurate measurement of the unsteady velocity field distribution in front of and behind the secondary guide vane in a limited space.

[0035] In some alternative embodiments of the method for measuring the unsteady velocity field distribution before and after the secondary guide vane in the turbine component test, the first blade is located in the suction side direction of the second blade.

[0036] The second blade is a test retrofit blade.

[0037] The flow velocity dynamic measuring points are arranged along the line connecting point A and point B and the line connecting point A' and point B' in the circumferential direction, and are located at the blade height of the test retrofit blade in the radial direction.

[0038] In some alternative embodiments of the method for measuring the unsteady velocity field distribution before and after the secondary guide vane in the turbine component test, the flow velocity dynamic measuring points arranged along the line connecting point A and point B are less dense between point B and point F in the circumferential direction.

[0039] The flow velocity dynamic measuring points arranged along the line connecting point A' and point B' are less dense between point B' and point F' in the circumferential direction, so as to reduce the measurement cost.

[0040] In some alternative embodiments of the method for measuring the unsteady velocity field distribution before and after the secondary guide vane in the turbine component test, the flow velocity dynamic measuring points arranged along the blade height direction through point H in the radial direction cover 5% to 95% of the blade height, and are more dense within 15% of the blade height above and below the blade height of the test retrofit blade.

[0041] The flow velocity dynamic measuring points arranged along the blade height direction through point H' in the radial direction cover 5% to 95% of the blade height, and are more dense within 15% of the blade height above and below the blade height of the test retrofit blade.

[0042] In some alternative embodiments of the method for measuring the unsteady velocity field distribution before and after the secondary guide vane in the turbine component test, the flow velocity distribution before and after the secondary guide vane is measured, and specifically:

[0043] The hot wire probe is driven by the displacement mechanism to perform circumferential phase-locked field scanning along the line connecting point A and point B and the line connecting point A' and point B' in the circumferential direction.

[0044] The hot wire probe is driven by the displacement mechanism to perform radial phase-locked field scanning along the blade height through point H and point H' in the radial direction.

[0045] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other.

[0046] The technical scheme of the present application has been described in combination with the preferred embodiments shown in the drawings, and those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments, and those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application, and the technical schemes after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A method for measuring the distribution of the unsteady velocity field in front of and behind the secondary guide vanes of a turbine component test, characterized in that, The application relates to a turbine component test secondary guide vane front and back unsteady velocity field distribution measurement method. The first blade and the second blade are selected from adjacent secondary guide vanes; A vertical line is drawn from a point S, which is the intersection of the first blade middle arc extension line and the secondary guide vane leading edge ordinate, to the rotor blade trailing edge ordinate, and the midpoint of the vertical line is a point B; a parallel line is drawn through the point B and parallel to the secondary guide vane leading edge ordinate, and the intersection of the parallel line and the first blade middle arc extension line is a point F, and the intersection of the parallel line and the second blade middle arc extension line is a point A; and the midpoint of the line connecting the point F and the point A is a point H; The intersection of the extension line of the middle arc line of the first blade and the leading edge line of the second guide vane is point Point A perpendicular line is drawn to the leading edge line of the downstream rotor blade, and the midpoint of the perpendicular line is point Point A parallel line is drawn parallel to the trailing edge line of the second guide vane, and the intersection of the parallel line and the extension line of the middle arc line of the first blade is point The intersection of the parallel line and the extension of the middle arc line of the second blade is point Point Point The midpoint of the line connecting point and point is point In the double-stage turbine, the dynamic flow measuring points are arranged along the line connecting point A and point B and the line connecting point , point in the circumferential direction, and the dynamic flow measuring points are arranged along the line connecting point H and point in the radial direction along the blade height, so as to measure the unsteady velocity field distribution before and after the secondary guide vane. The secondary guide vane front and back unsteady velocity field distribution is measured, and the measurement method is as follows: The hot-wire probe is driven by a displacement mechanism to make a circumferential phase-locked sweep field measurement along the line connecting point A and point B and the line connecting point A and point B in the circumferential direction ​​ The hot-wire probe is driven by a displacement mechanism. In the radial direction, the probe passes through points H, points Radial phase-locked sweep field measurement is carried out along the height of the blade.

2. The turbine component test secondary guide vane front and back unsteady velocity field distribution measurement method according to claim 1, characterized in that, The first blade is located in the suction side direction of the second blade; The second blade is a test modified blade; The flow velocity dynamic measuring points are arranged along the line connecting point A and point B and the line connecting point , point in the circumferential direction, and are located at the blade height of the measuring modified blade in the radial direction.

3. The turbine component test secondary guide vane front and back unsteady velocity field distribution measurement method according to claim 1, characterized in that, The flow velocity dynamic measurement points are arranged along the line connecting the point A and the point B in the circumferential direction, and the density is low between the point B and the point F. At the circumferential edge point ,point The flow velocity dynamic measurement points are arranged in a line, at point ,point The density is relatively low between them.

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