A test layout method for capturing two-stage turbine vane transition point information

Abstract

This application provides a test layout method for capturing the transition point information of a two-stage turbine guide vane, comprising: selecting several adjacent second-stage guide vanes in the entire ring, and arranging surface hot film measuring points on the suction surface of the guide vanes at different blade heights for dynamic testing; selecting several adjacent second-stage guide vanes in the entire ring, and setting wall static pressure holes on the suction surface of the guide vanes at different blade heights for steady-state testing. The test layout method for capturing the transition point information of a two-stage turbine guide vane proposed in this application can realize the testing of the transition point of the suction surface of the second-stage guide vane in turbine component testing, solving the problem of capturing the transition point of the guide vane suction surface in turbine component testing. It can realize the steady-state and dynamic correlation analysis of the internal flow field of the turbine second-stage guide vane, and can effectively help to effectively identify the influencing factors and obtain the influence law of the guide vane suction surface transition point in turbine component testing, providing support for obtaining the influence law of upstream and downstream rotors on the second-stage guide vane.

Description

Technical Field

[0001] This application belongs to the field of aero-turbine engine technology, and specifically relates to a test layout method for capturing the transition point information of a two-stage turbine guide vane. Background Technology

[0002] As a core component of aero-engine gas turbines, the efficiency of the turbine directly determines the design level of the aero-engine. Effectively obtaining the aerodynamic characteristics of turbine components is crucial for both the forward design of the turbine and the overall engine matching. Considering that the turbine is a hot-end component in an aero-engine, it is difficult to test it at the whole-engine level. Therefore, conducting turbine component model tests is an important means to obtain the overall aerodynamic characteristics and internal flow details of the turbine.

[0003] For a two-stage turbine, the second-stage guide vane is affected not only by the turbine inlet environment, the overall turbine load level, and the Reynolds number, but also by factors such as the upstream rotor wake, the transmission of upstream rotor / static interference downstream, and the potential field of the downstream moving blade's reaction upstream. Its secondary flow structure is complex, and the flow pattern changes on the blade surface are diverse. Accurately capturing the guide vane transition point is the key to analyzing the influence of turbine flow field and is an essential path for advanced high-load airfoil design.

[0004] Existing tests on guide vane transition are mainly conducted in the cascade environment by adding an upstream interference rod. The test environment is very different from that of a real turbine, and the test layout method is not suitable for the turbine component environment, nor can it take into account the effects of rotation-stationary interference. Summary of the Invention

[0005] The purpose of this application is to provide a test layout method for capturing the transition point information of a two-stage turbine guide vane, so as to solve or mitigate at least one of the problems in the background art.

[0006] The technical solution of this application is: a test layout method for capturing the transition point information of a two-stage turbine guide vane, the test layout method comprising:

[0007] Several adjacent secondary guide vanes were selected in the entire circle, and surface thermal film measuring points were arranged on the suction surface of the guide vanes at different blade heights for dynamic testing.

[0008] Several adjacent secondary guide vanes were selected from the entire circle, and static pressure holes were set on the suction surface of the guide vanes at different blade heights to conduct steady-state tests.

[0009] Furthermore, the number of secondary guide vanes arranging surface hot film measuring points is the same as the number of secondary guide vanes arranging wall static pressure holes.

[0010] Furthermore, there are three secondary guide vanes for arranging surface hot film measuring points and three secondary guide vanes for arranging wall static pressure holes.

[0011] Furthermore, the secondary guide vanes with surface thermal film measuring points and the secondary guide vanes with wall static pressure holes are positioned at the same height.

[0012] Furthermore, the secondary guide vanes with surface thermal film measuring points and the secondary guide vanes with wall static pressure holes are arranged at 5%, 50%, and 95% of the blade height, respectively.

[0013] Furthermore, based on the basic blade shape at different blade height positions, the arrangement and densification methods of surface thermal film measuring points are as follows:

[0014] The location of the maximum thickness of the suction surface of the second-stage guide vane is determined as point C. The endpoints of the suction surface profile of the second-stage guide vane are determined as points A and E.

[0015] Projecting from the leading edge of the second-stage guide vane to the suction surface of the adjacent second-stage guide vane, the perpendicular point is point F; projecting from the trailing edge of the second-stage guide vane to the suction surface of the same adjacent guide vane, the perpendicular point is point G.

[0016] Draw a circle with the perpendicular point F as the center and line segment FC as the radius. The other intersection point with the suction surface of the second-stage guide vane is point B. Draw a circle with the perpendicular point G as the center and line segment GC as the radius. The other intersection point with the suction surface of the second-stage guide vane is point D.

[0017] Surface thermal film measuring points are arranged between the suction surfaces AE of the secondary guide vane. The density of thermal film measuring points in each region satisfies AB:BC:CD:DE = 1:2:3:1, and the distance between two adjacent thermal film measuring points in region CD of the guide vane suction surface does not exceed 2mm.

[0018] Furthermore, the secondary guide vanes with wall static pressure holes and the secondary guide vanes with surface hot film measuring points are completely or not completely symmetrical in the circumferential direction, and the relative positions of the wall static pressure hole secondary guide vanes with the surface hot film measuring points and the upstream guide vanes are consistent at the same blade height position.

[0019] Furthermore, in the secondary guide vanes with wall static pressure holes and the secondary guide vanes with hot film measuring points, the opening positions and densification methods of the wall static pressure holes and the surface hot film measuring points at the same blade height are consistent, and the opening direction is consistent with the normal of the blade profile.

[0020] The test layout method for capturing the transition point information of a two-stage turbine guide vane proposed in this application involves steady-state and dynamic testing on the front and rear of the guide vane and on the blade surface. This method enables the testing of the transition point of the suction surface of the second-stage guide vane in turbine component testing, solving the problem of capturing the transition point of the guide vane suction surface in turbine component testing. It also enables steady-state and dynamic correlation analysis of the internal flow field of the turbine's second-stage guide vane, effectively helping to identify the influencing factors and obtain the influence law of the guide vane suction surface transition point in turbine component testing, and providing support for obtaining the influence law of the upstream and downstream rotors on the second-stage guide vane. Attached Figure Description

[0021] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0022] Figure 1 This is a flowchart of the test layout method for capturing the transition point information of a two-stage turbine guide vane according to this application.

[0023] Figure 2 This is a schematic diagram showing the location of the thermal film measuring points in this application.

[0024] Figure 3 This is a schematic diagram showing the positions of the wall static pressure hole guide vane and the hot film measuring point guide vane in this application.

[0025] Figure 4 This is a schematic diagram showing the arrangement of the 50% wall static pressure hole guide vane and the 50% hot film measuring point guide vane in one embodiment of this application.

[0026] Figure 5 This is a schematic diagram showing the multiple arrangement positions of the 50% wall static pressure hole guide vane in one embodiment of this application. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0028] In order to obtain the transition information of the second-stage guide vane surface of a two-stage turbine and realize the capture of the transition point information of the guide vane suction surface in turbine component tests and the comprehensive correlation analysis of the steady-state or dynamic test results of the flow field in turbine component tests, this application proposes a test layout method for capturing the transition point information of the two-stage turbine guide vane.

[0029] like Figure 1 As shown, the test layout method for capturing the transition point information of a two-stage turbine guide vane proposed in this application includes the following:

[0030] 1. Select several adjacent secondary guide vanes in the entire circle, and arrange surface thermal film measuring points on the suction surface of the guide vanes at different blade heights for dynamic testing.

[0031] For example, in some embodiments of this application, three adjacent secondary guide vanes can be selected in the entire circle of secondary guide vanes, and surface thermal film measuring points can be arranged at 5%, 50% and 95% of their blade height, respectively.

[0032] In the preferred embodiment of this application, considering the torsion of the guide vane, the arrangement method and densification process of the hot film measuring points are as follows, based on the basic blade profiles at different blade height positions:

[0033] 1.1) As Figure 2 As shown, point C is the location of the maximum thickness of the guide vane suction surface, and points A and E are the endpoints of the guide vane suction surface profile.

[0034] 1.2) Project the guide vane from the leading edge point to the suction surface of the adjacent blade, with the perpendicular point being point F; project the guide vane from the trailing edge point to the suction surface of the adjacent blade, with the perpendicular point being point G.

[0035] 1.3) Draw a circle with the perpendicular point F as the center and line segment FC as the radius. The other intersection point with the guide vane suction surface is point B; draw a circle with the perpendicular point G as the center and line segment GC as the radius. The other intersection point with the guide vane suction surface is point D.

[0036] 1.4) Surface thermal film measuring points are arranged between the suction surfaces AE of the guide vane. The density of thermal film measuring points in each region satisfies AB:BC:CD:DE=1:2:3:1, and the distance between two adjacent thermal film measuring points in region CD of the suction surface of the guide vane does not exceed 2mm.

[0037] 2. Select several adjacent secondary guide vanes in the entire circle, and set wall static pressure holes on the suction surface of the guide vanes at different blade height positions to conduct steady-state tests.

[0038] In some embodiments of this application, the number of wall static pressure orifice guide vanes 2 (also called steady-state test vanes) is the same as the number of hot-film measuring point guide vanes 1 (also called dynamic test vanes), and the two are distributed circumferentially, such as... Figure 3 As shown, three adjacent secondary guide vanes are selected in the entire circle to set the wall static pressure holes. The arrangement of the wall static pressure holes of the guide vanes in the blade height direction is the same as that of the guide vanes with hot film measuring points, that is, the wall static pressure holes of the three guide vanes are arranged at 5%, 50% and 95% of their blade height, respectively.

[0039] In a preferred embodiment of this application, the wall static pressure hole guide vane 2 and the hot film measuring point guide vane 1 are not necessarily completely symmetrical in the circumferential direction, but the relative positions of the wall static pressure hole guide vane 2 and the hot film measuring point guide vane 1 at the same blade height position with the upstream guide vane must be consistent.

[0040] For example in Figure 4 In the illustrated embodiment, the upstream guide vane 4 (dashed line) and the secondary guide vane 3 (solid line) have different numbers of blades, thus creating an angle between them. The 50% blade height hot film measuring point guide vane 11 in the hot film measuring point guide vane 1 is located above the entire ring of secondary guide vanes 3. The 50% blade height hot film measuring point guide vane 11 and its corresponding upstream guide vane 4 have a clamp α. Therefore, the 50% blade height wall static pressure hole guide vane 21 in the wall static pressure hole guide vane 2 is selected at a position with the same angle α as its corresponding upstream guide vane 4. Figure 4 The guide vanes at the lower middle position, and at the remaining 5% and 95% of the blade height, are not described in detail.

[0041] like Figure 5 As shown, when there are multiple suitable positions for the 50% blade height wall static pressure hole guide vane 21 selected according to the above embodiment, the 50% blade height wall static pressure hole guide vane 21 can be arranged at any position.

[0042] In a preferred embodiment of this application, the method for opening the static pressure holes in the wall static pressure hole guide vane is the same as the method for arranging the hot film measuring points in the hot film measuring point guide vane. That is, the opening position and densification method of the steady-state test blade and the dynamic test blade at the same blade height position are consistent, and the opening direction is consistent with the normal of the blade profile.

[0043] The test layout method for capturing the transition point information of a two-stage turbine guide vane proposed in this application involves steady-state and dynamic testing on the front and rear of the guide vane and on the blade surface. This method enables the testing of the transition point of the suction surface of the second-stage guide vane in turbine component testing, solving the problem of capturing the transition point of the guide vane suction surface in turbine component testing. It also enables steady-state and dynamic correlation analysis of the internal flow field of the turbine's second-stage guide vane, effectively helping to identify the influencing factors and obtain the influence law of the guide vane suction surface transition point in turbine component testing, and providing support for obtaining the influence law of the upstream and downstream rotors on the second-stage guide vane.

[0044] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A test layout method for capturing the transition point information of a two-stage turbine guide vane, characterized in that, The test layout method includes: Several adjacent secondary guide vanes are selected within the entire ring of guide vanes, and surface thermal film measurement points are arranged on the suction surface of the guide vanes at different blade heights for dynamic testing. The arrangement and densification methods of the surface thermal film measurement points are as follows: The location of the maximum thickness of the suction surface of the second-stage guide vane is determined as point C. The endpoints of the suction surface profile of the second-stage guide vane are determined as points A and E. Projecting from the leading edge of the second-stage guide vane to the suction surface of the adjacent second-stage guide vane, the perpendicular point is point F; projecting from the trailing edge of the second-stage guide vane to the suction surface of the same adjacent guide vane, the perpendicular point is point G. Draw a circle with the perpendicular point F as the center and line segment FC as the radius. The other intersection point with the suction surface of the second-stage guide vane is point B. Draw a circle with the perpendicular point G as the center and line segment GC as the radius. The other intersection point with the suction surface of the second-stage guide vane is point D. Surface thermal film measuring points are arranged between the suction surfaces AE of the secondary guide vane. The density of thermal film measuring points in each region satisfies AB:BC:CD:DE=1:2:3:1, and the distance between two adjacent thermal film measuring points in region CD of the guide vane suction surface does not exceed 2mm. Several adjacent secondary guide vanes were selected in the entire circle, and wall static pressure holes were set on the suction surface of the guide vanes at different blade heights for steady-state testing. Among them, the opening positions and densification methods of the wall static pressure holes and the surface hot film measuring points at the same blade height were consistent in the secondary guide vanes with wall static pressure holes and the secondary guide vanes with hot film measuring points, and the opening direction was consistent with the normal of the blade profile.

2. The test layout method for capturing the transition point information of a two-stage turbine guide vane as described in claim 1, characterized in that, The number of secondary guide vanes for arranging surface hot film measuring points is the same as the number of secondary guide vanes for arranging wall static pressure holes.

3. The test layout method for capturing the transition point information of a two-stage turbine guide vane as described in claim 2, characterized in that, There are three secondary guide vanes for arranging surface thermal film measuring points and three secondary guide vanes for arranging wall static pressure holes.

4. The test layout method for capturing the transition point information of a two-stage turbine guide vane as described in claim 3, characterized in that, The secondary guide vanes with surface thermal film measuring points and the secondary guide vanes with wall static pressure holes are positioned at the same height.

5. The test layout method for capturing the transition point information of a two-stage turbine guide vane as described in claim 4, characterized in that, Secondary guide vanes with surface thermal film measuring points and secondary guide vanes with wall static pressure holes are arranged at 5%, 50%, and 95% of the blade height, respectively.

6. The test layout method for capturing the transition point information of a two-stage turbine guide vane as described in claim 5, characterized in that, The secondary guide vanes with wall static pressure holes and the secondary guide vanes with surface hot film measuring points are completely or not completely symmetrical in the circumferential direction, and the relative positions of the wall static pressure hole secondary guide vanes and the surface hot film measuring point secondary guide vanes at the same blade height are consistent with those of the upstream guide vanes.

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