Turbine guider annular cascade test device and method

Abstract

The invention discloses a turbine guider annular blade cascade test device and method, the test device comprises an annular blade cascade, the annular blade cascade comprises an outer ring, an inner ring and an annular channel formed by the outer ring and the inner ring, M groups of blades uniformly distributed in the circumferential direction are arranged in the annular channel, the number of each group of blades is N, M is less than or equal to 5, and N is greater than or equal to 5; a plurality of total pressure probes and static pressure measuring points are arranged at the air inlet end and the air outlet end of the annular blade grid in the circumferential direction, the distance between the total pressure probes and the static pressure measuring points and the annular blade grid can be preset, and the static pressure measuring points are arranged on the surface of the blade and used for testing the pneumatic performance of the annular blade grid. A plurality of blades are installed on the annular blade cascade at the same time, the aerodynamic performance and the downstream flow field of turbine guide blades with a plurality of specific profiles can be obtained through testing in the same annular blade cascade test piece, and therefore the low-aerodynamic-loss turbine blades suitable for the engine are obtained, and meanwhile the machining cost and the machining period of the test piece can be reduced.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, and in particular to a turbine guide vane ring cascade test device and method. Background Art

[0002] The three major components of an aircraft engine include a compressor, a combustion chamber and a turbine, among which the turbine is one of the core components of an aircraft engine. After being pressurized and heated by the compressor and the combustion chamber, the gas flows into the channel composed of turbine blades, which can convert the thermal energy and potential energy of the fuel gas into kinetic energy and then drive other devices. The aerodynamic performance of the turbine blades determines the overall performance design level of the engine, and the annular blade blowing test is one of the important means to verify the aerodynamic performance of the blades. The test can be used to obtain key aerodynamic parameters such as the total pressure loss of the blade and the outlet airflow angle.

[0003] Patent application CN111649947A discloses an annular blade performance tester, which can only obtain the aerodynamic performance of one blade at a time. If the aerodynamic performance of other blades is to be tested, different annular blades need to be processed and replaced, and the test piece processing cycle is long and the cost is high. Summary of the invention

[0004] The invention provides a turbine guide annular blade cascade test device to solve the technical problem that different annular blade cascades need to be replaced when testing different blades in the existing device, which results in high cost.

[0005] The present invention also provides a turbine guide vane ring cascade testing method, which adopts the turbine guide vane ring cascade testing device.

[0006] According to one aspect of the present invention, a turbine guide vane ring test device is provided, the test device comprising an annular vane ring, the annular vane ring comprising an outer ring, an inner ring and an annular channel formed by the outer ring and the inner ring, M groups of blades uniformly distributed in the circumferential direction are built into the annular channel, the number of blades in each group is set to N, wherein M≤5, N≥5; The inlet end and the exhaust end of the annular blade are both circumferentially arranged with a plurality of total pressure probes and static pressure measuring points. The distances between the total pressure probes and the static pressure measuring points relative to the annular blade can be preset. At the same time, static pressure measuring points are arranged on the blade surface to test the aerodynamic performance of the annular blade.

[0007] Furthermore, the outer ring of the annular blade grid forms an upper flow channel, and the inner ring forms a lower flow channel. A number of first total pressure probes are evenly distributed along the circumferential direction at the inlet end of the annular blade grid at 0.5 to 1.0 times the axial chord length from the leading edge of the blade, and a number of total temperature probes are arranged at 0.2 to 0.4 times the axial chord length of the first total pressure probe in the direction away from the annular blade grid. The circumferential positions of the total temperature probes are staggered from the positions of the first total pressure probes, and a number of static pressure measuring points are respectively arranged in the upper flow channel and the lower flow channel at the same axial position as the first total pressure probe.

[0008] Furthermore, a plurality of second total pressure probes are evenly distributed along the circumferential direction at the exhaust end of the annular blade grid at a distance of 0.5 to 1.0 times the axial chord length from the trailing edge of the blade, a plurality of static pressure measuring points are respectively arranged in the upper flow channel and the lower flow channel at the same axial position as the second total pressure probe, and a three-phase displacement mechanism is arranged directly above the same axial position as the second total pressure probe, so as to measure the outlet total pressure, outlet static pressure and outlet airflow angle during the test.

[0009] Furthermore, a plurality of adjacent blades are selected in each group of blades to arrange static pressure holes on the blade surface, and a number of static pressure measuring points are arranged in the root section, mid-section and tip section of the blade in turn to measure the static pressure on the blade surface.

[0010] Furthermore, the radial measuring point of each total pressure probe in the annular blade cascade meets the following conditions: ; Where n is the number of measuring points of each total pressure probe, R Tip is the radial height of the upper flow channel, R Hub is the radial height of the lower flow channel, R i is the radial height of the measuring point, i is the measuring point number, starting from the measuring point numbered 1 near the lower flow channel and n near the upper flow channel, i=1, 2, …, n.

[0011] Furthermore, the turbine guide vane annular blade test device also includes an intake section, a test section and an exhaust section composed of a bell-shaped fairing and an outer casing. The intake section is provided with an intake support plate for allowing the airflow to enter the annular flow channel; the annular blade is arranged in the test section for measuring the aerodynamic performance of the blades by utilizing the airflow passing through the annular blade; the exhaust section is provided with anti-pre-swirl blades for allowing the airflow to flow smoothly into the exhaust duct.

[0012] Furthermore, the inner and outer rings of the air intake section are smoothly connected to the inner and outer flow channels of the test section, and the inner and outer rings of the test section are smoothly connected to the inner and outer ring flow channels of the exhaust section.

[0013] Furthermore, the anti-pre-rotation blades are mounted on the bell-shaped fairing and form a certain angle with the bell-shaped fairing. Gaps for airflow to pass through are provided between the anti-pre-rotation blades.

[0014] According to another aspect of the present invention, a turbine guide vane ring cascade test method is provided. The turbine guide vane ring cascade test device is used. The turbine guide vane ring cascade test method comprises the following steps: The first wind blowing test: adjust the angle of the annular cascade so that the first group of blades are placed directly above, arrange static pressure holes on the blade surface on adjacent blades, and arrange several static pressure measuring points on the root section, middle section and tip section of the blade in turn to measure the static pressure on the blade surface; A plurality of first total pressure probes are uniformly distributed along the circumferential direction at a distance of 0.5 to 1.0 times the axial chord length from the leading edge of the blade at the inlet end of the annular blade cascade, and a plurality of total temperature probes are arranged at a distance of 0.2 to 0.4 times the axial chord length from the first total pressure probe in a direction away from the annular blade cascade. The circumferential position of the total temperature probe is staggered from the position of the first total pressure probe, and a plurality of static pressure measuring points are respectively arranged in the upper flow channel and the lower flow channel at the same axial position as the first total pressure probe; a plurality of second total pressure probes are uniformly distributed along the circumferential direction at a distance of 0.5 to 1.0 times the axial chord length from the trailing edge of the blade at the exhaust end of the annular blade cascade, and a plurality of static pressure measuring points are respectively arranged in the upper flow channel and the lower flow channel at the same axial position as the second total pressure probe, and a three-phase displacement mechanism is arranged directly above the same axial position as the second total pressure probe, and the first blowing test is carried out to obtain a first group of blade aerodynamic performance parameters and its downstream flow field cloud map; Second wind test: rotate the annular cascade to place the second set of blades directly above, repeat the first wind test process, and obtain the aerodynamic performance parameters of the second set of blades and the cloud diagram of the downstream flow field; The Mth blowing test: rotate the annular cascade to place the Mth group of blades directly above, repeat the first blowing test process, and obtain the aerodynamic performance parameters of the Mth group of blades and its downstream flow field cloud map.

[0015] Furthermore, the blowing test includes changing the guide valve outlet Mach number Ma1 by adjusting the inlet total pressure, and measuring the inlet equivalent flow rate under several conditions of the outlet Mach number Ma1=0.3~0.8 during the test. , static pressure distribution on blade surface and the total pressure recovery coefficient of the cascade Characteristic law curve that changes with the outlet Mach number Ma1.

[0016] The present invention has the following beneficial effects: The annular cascade provided by the present invention is provided with several different types of blades installed at the same time, and the aerodynamic performance and downstream flow field of several turbine guide blades with specific profiles can be tested in the same annular cascade test piece, thereby obtaining low aerodynamic loss turbine blades suitable for the engine, and at the same time can reduce the test piece processing cost and cycle.

[0017] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 It is a schematic diagram of the structure of the annular cascade test device; Figure 2 It is a schematic diagram of the three-dimensional structure of the annular cascade; Figure 3 It is a schematic diagram of the front view structure of the annular cascade; Figure 4 It is a schematic diagram of the three-dimensional structure of the blade; Figure 5 It is a schematic diagram of the structure of the exhaust section; Figure 6 This is a schematic diagram of the anti-pre-swirl support plate in the exhaust section; Figure 7 This is a schematic diagram of radial measuring points of the total pressure probe; Figure 8 This is a schematic diagram of the axial measurement point arrangement of the annular cascade test device; Fig. 9 This is a schematic diagram of the circumferential distribution of the total pressure probes on the inlet section; Fig.10 This is a schematic diagram of the circumferential distribution of static pressure measurement points on the inlet section; Fig.11 This is a schematic diagram of the circumferential distribution of the total pressure and static pressure measuring points at the outlet section; Fig.12 This is a schematic diagram of the distribution of flow field measurement points at the outlet section along the airflow direction; Fig.13 It is a schematic diagram of the radial position of the static pressure measuring points on the surface of the annular cascade blade; Fig.14 This is a schematic diagram of the static pressure measurement points on the blade surface (taking the mid-section of the blade as an example); Fig.15 The static pressure distribution diagram of the blade surface at 10% blade height section (positive twist); Fig.16 The static pressure distribution diagram of the blade surface at the 50% blade height section (positive twist); Fig.17 The static pressure distribution diagram of the blade surface at 90% blade height (positive twist); Fig.18 It is the total pressure contour diagram of the outlet section; Fig.19 This is the Mach number cloud diagram of the exit section.

[0019] In the figure: 1, intake section, 2, test section, 3, exhaust section, 4, bell-shaped fairing, 5, intake support plate, 6, annular blade cascade, 7, anti-pre-swirl blade, 8, outer ring, 9, inner ring, 10, blade, 11, static pressure measurement point, 12, first fan-shaped segment, 13, second fan-shaped segment, 14, third fan-shaped segment, 15, positive twist blade, 16, reverse twist blade, 17, reference blade, 18, trailing edge, 19, in front of blade, 20, behind blade, 21, blade tip section, 22, blade mid-section, 23, blade root section. DETAILED DESCRIPTION

[0020] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0021] See also Figures 1 to 14 , an embodiment of the first aspect of the present invention provides a turbine guide vane ring test device, the turbine guide vane ring test device comprises an annular vane ring 6, the annular vane ring 6 comprises an outer ring 8, an inner ring 9 and an annular channel formed by the outer ring 8 and the inner ring 9, M groups of blades 10 are evenly distributed in the circumferential direction, and the number of blades 10 in each group is set to N, wherein M≤5, N≥5; The air inlet end and the exhaust end of the annular blade cascade 6 are both arranged with a plurality of total pressure probes and static pressure measuring points 11 along the circumferential direction and the front and rear radial directions. The distances between the total pressure probes and the static pressure measuring points 11 and the annular blade cascade 6 can be preset. At the same time, the static pressure measuring points 11 are arranged on the surface of the blade 10 to test the aerodynamic performance of the annular blade cascade 6.

[0022] The test object of the test device described above is the stator blade. A variety of different blades are set in the annular cascade 6, and the aerodynamic performance and downstream flow field of M kinds of blades with different shapes can be obtained through a wind blowing test in the same set of annular cascade 6 test device. Among them, M≤5, that is, 1-5 kinds of blades can be set in the annular cascade 6, and the number of each blade is more than 5, to ensure the periodicity of the flow field measured by the outlet three-phase mechanism, and the number of blades with the same shape within the 72° angular range is more than 5; for example, 4 kinds of blades can be set, and each blade is set with 5, 6 or 7, etc., or 3 kinds of blades can be set, and each blade is set with 6, 7 or 8, etc.

[0023] Schematic diagram of three-dimensional modeling of annular cascade 6 Figure 2 , the front view of the annular blade cascade 6 is shown in Figure 3 , the schematic diagram of blade 3D modeling is shown in Figure 4 .

[0024] This embodiment takes M=3 and N=8 as an example for explanation: See also Figures 2 to 4, 24 blades are evenly distributed circumferentially in the annular channel of the annular cascade 6, among which three kinds of blades with different shapes are respectively distributed in three equally divided fan-shaped segments; the blades built into the first fan-shaped segment 12 are positive twist blades 15, and the blade characteristic is that the trailing edge 18 is radially in an "inverted C" shape when the three-dimensional blade is projected on the meridian plane; the blades built into the second fan-shaped segment 13 are reverse twist blades 16, and the blade characteristic is that the trailing edge 18 is radially in a "positive C" shape when the three-dimensional blade is projected on the meridian plane; the blades built into the third fan-shaped segment 14 are reference blades 17, and the blade characteristic is that the trailing edge 18 is radially straight when the three-dimensional blade is projected on the meridian plane.

[0025] In the embodiment of the present invention, the outer ring 8 of the annular blade cascade 6 forms an upper flow passage, and the inner ring 9 forms a lower flow passage.

[0026] See also Figures 7 to 14 In the embodiment of the present invention, 3 to 5 first total pressure probes are evenly distributed along the circumferential direction at the inlet end of the annular cascade 6 at 0.5 to 1.0 times the axial chord length of the front of the blade 19, and 3 to 5 total temperature probes are arranged at 0.2 to 0.4 times the axial chord length in front of the first total pressure probe. The total temperature probes are staggered from the first total pressure probes along the circumferential direction, and 4 to 6 static pressure measuring points 11 are arranged in the upper and lower flow passages at the same axial position as the first total pressure probe. 4 to 6 second total pressure probes are evenly distributed along the circumferential direction at the exhaust end of the annular cascade 6 at 0.5 to 1.0 times the axial chord length of the rear of the blade 20, and 4 to 6 static pressure measuring points 11 are arranged in the upper and lower flow passages at the same axial position as the second total pressure probe, and a three-phase displacement (5-hole total pressure probe) mechanism is arranged directly above the same axial position as the second total pressure probe, which is used to measure the outlet total pressure, outlet static pressure and outlet airflow angle during the test.

[0027] In the present application, if the distance between the total pressure probe and the blade is smaller than the above-defined range, it will affect the performance of the blade cascade, and if the distance is larger than the above-defined range, the measurement accuracy is not high.

[0028] Furthermore, three adjacent blades in the middle of the three fan-shaped segments are selected for arranging static pressure holes on the blade surface, and 14 static pressure measuring points 11 are arranged in the blade root section 23, the blade mid-section 22 and the blade tip section 21, respectively, for a total of 42 static pressure measuring points 11, for measuring the static pressure on the blade surface. The present application arranges the 42 static pressure measuring points 11 on three adjacent blades, which can ensure the accuracy of blade performance monitoring while reasonably allocating processing and assembly space.

[0029] The radial measuring point of each total pressure probe in the annular blade cascade 6 satisfies the following conditions: ; Where n is the number of measuring points of each total pressure probe, R Tipis the radial height of the upper flow channel, R Hub is the radial height of the lower flow channel, R i is the radial height of the measuring point, i is the measuring point number, starting from the measuring point numbered 1 near the lower flow channel and n near the upper flow channel, i=1, 2, …, n.

[0030] The number of radial measuring points of the total pressure probe and total temperature probe arranged in the present application is determined by the flow channel height (the height between the outer ring 8 and the inner ring 9), and the radial measuring point of each probe must meet the "equal ring area" condition to ensure that the distribution of the measuring points can represent the characteristics of the entire monitoring area.

[0031] In an embodiment of the present invention, the test device also includes an intake section 1, a test section 2 and an exhaust section 3 composed of a bell-shaped fairing 4 and an outer casing. The intake section 1 is provided with an intake support plate 5 for allowing the airflow to enter the annular flow channel; the annular blade 6 is arranged in the test section 2, for measuring the aerodynamic performance of the blade by using the airflow passing through the annular blade 6; the exhaust section 3 is provided with an anti-pre-rotation blade 7 for allowing the airflow to flow smoothly into the exhaust duct.

[0032] The air intake section 1 mainly includes an inner ring bell-shaped fairing 4 and an air intake support plate 5. The inner and outer rings of the air intake section 1 are smoothly connected to the inner and outer flow channels of the test section 2; the test section 2 mainly includes the test object annular blade 6, and there is a long straight section behind the annular blade 6 to ensure the stability of the airflow in the measurement section. The inner and outer rings of the test section 2 are smoothly connected to the inner and outer ring flow channels of the exhaust section 3. In the test section 2, a number of total pressure and static pressure measuring points 11 are arranged circumferentially and radially before and after the annular blade 6 to obtain aerodynamic parameters such as the total pressure loss of the blade; the exhaust section 3 mainly includes anti-pre-rotation blades 7, which are conducive to the smooth flow of air into the exhaust pipe to prevent blockage. The structural schematic diagram is shown in Figure 5 and Figure 6 .

[0033] The working mode of the annular blade test device is as follows: a high-pressure air enters from the front end of the device, and the airflow speed and pressure will change after passing through the annular blade cascade 6. By arranging static pressure holes on the blade surface and arranging static pressure measuring points 11 and total pressure probes at the front and rear of the blade, the total pressure loss coefficient of the blade and the surface pressure distribution under different working conditions are measured. Figure 1 As shown by the middle arrow, the air enters the channel composed of the inner bell-shaped fairing 4 and the outer casing from the front end of the intake section 11, flows through the annular channel composed of the outer ring 8 of the annular blade cascade and the inner ring 9 of the annular blade cascade in the test section 22, and finally flows out from the outlet channel of the exhaust section 3.

[0034] In the embodiment of the present invention, the anti-pre-rotation blades 7 are mounted on the bell-shaped fairing 4 and form a certain angle with the bell-shaped fairing 4. Gaps for airflow to pass through are provided between the anti-pre-rotation blades 7.

[0035] According to an embodiment of the second aspect of the present invention, there is provided a method for testing a turbine guide vane ring, comprising the following steps: First wind blowing test: adjust the angle of the annular cascade 6 so that the first group of blades are placed directly above, arrange static pressure holes on the blade surface on adjacent blades, and sequentially arrange a number of static pressure measuring points 11 on the blade root section 23, the blade mid-section 22 and the blade tip section 21 of the blade to measure the static pressure on the blade surface; 3 to 5 first total pressure probes are evenly distributed along the circumferential direction at a distance of 0.5 to 1.0 times the axial chord length from the leading edge of the blade at the inlet end of the annular blade cascade 6, 3 to 5 total temperature probes are arranged at a distance of 0.2 to 0.4 times the axial chord length from the first total pressure probe in the direction away from the annular blade cascade, the circumferential position of the total temperature probe is staggered from the position of the first total pressure probe, and 4 to 6 static pressure measuring points 11 are respectively arranged in the upper flow channel and the lower flow channel at the same axial position as the first total pressure probe; 4 to 6 second total pressure probes are evenly distributed along the circumferential direction at a distance of 0.5 to 1.0 times the axial chord length from the trailing edge of the blade at the exhaust end of the annular blade cascade 6, 4 to 6 static pressure measuring points 11 are respectively arranged in the upper flow channel and the lower flow channel at the same axial position as the second total pressure probe, and a three-phase displacement mechanism is arranged directly above the same axial position as the second total pressure probe, and the first blowing test is carried out to obtain a first group of blade aerodynamic performance parameters and its downstream flow field cloud map; Second wind blowing test: rotate the annular cascade 6 to place the second set of blades directly above, repeat the first test process, and obtain the aerodynamic performance parameters of the second set of blades and the cloud diagram of the downstream flow field; The Mth blowing test: rotate the annular cascade 6 to place the Mth group of blades directly above, repeat the first test process, and obtain the aerodynamic performance parameters of the Mth group of blades and its downstream flow field cloud map.

[0036] In the first test, the annular cascade 6 was installed on the test device (the reference blade 17 was located directly above), and the Mach number Ma1 of the guide vane outlet was changed by adjusting the inlet total pressure. During the test, the inlet equivalent flow rate was measured at several states of the outlet Mach number Ma1 = 0.3~0.8. , static pressure distribution on blade surface and the total pressure recovery coefficient of the cascade Characteristic curve of performance parameters changing with outlet Mach number Ma1.

[0037] Annular cascade exit Mach number: ; Relative equivalent flow: ; Static pressure coefficient of blade surface: ; Total pressure recovery coefficient: ; Total pressure loss coefficient: ; Energy loss coefficient: ; : Total temperature of inlet air flow (K); : Total inlet air pressure (Pa); : Total pressure of outlet airflow (Pa), obtained by arithmetic average of all measuring points of total pressure measured by three-phase displacement mechanism; : outlet air flow static pressure (Pa); : Annular cascade inlet flow rate (Kg / s); : Adiabatic index 1.4; : Gas constant 287.26 J / (kg·K); After completing the first blowing test, the aerodynamic performance parameters (inlet flow rate, outlet Mach number, static pressure distribution on the blade surface, total pressure recovery coefficient, etc.) of the reference blade 17 and its downstream flow field cloud map can be obtained; in the second test, the annular blade 6 is rotated 120° clockwise and installed in the annular blade 6 test device (the positive twist blade 15 is located directly above), and the first test process is repeated to obtain the aerodynamic performance parameters (inlet flow rate, outlet airflow angle, total pressure recovery coefficient, etc.) of the positive twist blade 15 and its downstream flow field cloud map; in the last test, the annular blade 6 is rotated 120° clockwise again and installed in the annular blade 6 test device (the reverse twist blade 16 is located directly above), and the first test process is repeated to obtain the aerodynamic performance parameters (inlet flow rate, outlet airflow angle, total pressure recovery coefficient, etc.) of the reverse twist blade 16 and its downstream flow field cloud map.

[0038] Three blade design states (M a1 =0.748) is shown in Table 1. Taking the positive twist blade as an example, the static pressure distribution on the blade surface is shown in Table 1. Figures 15 to 17 The static pressure distribution on the blade surface can show the load distribution form of the blade, the pressure change rate along the flow direction and other parameters. The comparison of the outlet flow field can be seen in Fig.18 and Fig.19 The outlet flow field diagram can show the distribution characteristics of the measured total pressure and Mach number at the outlet of Ye Shan, and whether there is obvious periodicity, so as to verify whether the circumferential angle measured by the outlet three-phase displacement mechanism is selected appropriately, and then provide the outlet section parameter data for the calculation of the total pressure recovery coefficient, total pressure loss coefficient and capacity loss coefficient.

[0039] Table 1 Aerodynamic performance of annular cascade design points ; The present invention has completed the annular blade test verification, and the optimal solution of the final blade has excellent performance in the whole machine test, indicating the feasibility of this method.

[0040] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A turbine guide vane ring cascade test device, It is characterized in that The turbine guide vane ring test device comprises an annular vane ring (6), the annular vane ring (6) comprising an outer ring (8), an inner ring (9) and an annular channel formed by the outer ring (8) and the inner ring (9), wherein M groups of blades (10) are evenly distributed in the circumferential direction and are built into the annular channel, the number of blades in each group (10) being N, wherein M≤5 and N≥5; A plurality of total pressure probes and static pressure measuring points (11) are arranged circumferentially at both the air inlet end and the exhaust end of the annular blade cascade (6); the distances between the total pressure probes and the static pressure measuring points (11) relative to the annular blade cascade (6) can be preset; and static pressure measuring points (11) are arranged on the surface of the blade (10) for testing the aerodynamic performance of the annular blade cascade (6).

2. The turbine guide vane ring cascade test device according to claim 1, It is characterized in that The outer ring (8) of the annular blade cascade (6) forms an upper flow channel, and the inner ring (9) forms a lower flow channel. A plurality of first total pressure probes are evenly distributed along the circumferential direction at a distance of 0.5 to 1.0 times the axial chord length from the leading edge of the blade at the air inlet end of the annular blade cascade (6). A plurality of total temperature probes are arranged at a distance of 0.2 to 0.4 times the axial chord length from the first total pressure probe in a direction away from the annular blade cascade (6). The circumferential positions of the total temperature probes are staggered from the positions of the first total pressure probes. A plurality of static pressure measuring points (11) are respectively arranged in the upper flow channel and the lower flow channel at the same axial position as the first total pressure probe.

3. The turbine guide vane ring cascade test device according to claim 2, It is characterized in that A plurality of second total pressure probes are evenly distributed along the circumferential direction at the exhaust end of the annular blade cascade (6) at a distance of 0.5 to 1.0 times the axial chord length from the blade trailing edge, a plurality of static pressure measuring points (11) are arranged in the upper flow passage and the lower flow passage at the same axial position as the second total pressure probes, and a three-phase displacement mechanism is arranged directly above the same axial position as the second total pressure probes, for measuring the outlet total pressure, outlet static pressure and outlet airflow angle during the test.

4. The turbine guide vane ring cascade test device according to claim 1, It is characterized in that In each group of blades (10), a plurality of adjacent blades (10) are selected to arrange static pressure holes on the blade surface, and a plurality of static pressure measuring points (11) are arranged in sequence on the blade root section (23), the blade midsection (20) and the blade tip section (21) of the blade (10) to measure the static pressure on the blade (10) surface.

5. The turbine guide vane ring cascade test device according to claim 1, It is characterized in that The radial measuring point of each total pressure probe in the annular blade cascade (6) satisfies the following conditions: ； Where n is the number of measuring points of each total pressure probe, R Tip is the radial height of the upper flow channel, R Hub is the radial height of the lower flow channel, R i is the radial height of the measuring point, i is the measuring point number, starting from the measuring point numbered 1 near the lower flow channel and n near the upper flow channel, i=1, 2,…, n.

6. The turbine guide vane ring cascade test device according to any one of claims 1 to 5, It is characterized in that The turbine guide vane ring test device further comprises an intake section (1), a test section (2) and an exhaust section (3) formed by a bell-shaped fairing (4) and an outer casing, wherein the intake section (1) is provided with an intake support plate (5) for allowing airflow to enter the annular flow channel; the annular vane (6) is arranged in the test section (2) for measuring the aerodynamic performance of the blade (10) by using airflow passing through the annular vane (6); and the exhaust section (3) is provided with an anti-pre-swirl blade (7) for allowing airflow to flow smoothly into the exhaust pipe.

7. The turbine guide vane ring cascade test device according to claim 6, It is characterized in that The inner and outer rings of the air intake section (1) are smoothly connected to the inner and outer flow channels of the test section (2), and the inner and outer rings of the test section (2) are smoothly connected to the inner and outer ring flow channels of the exhaust section (3).

8. The turbine guide vane ring cascade test device according to claim 6, It is characterized in that The anti-pre-rotation blades (7) are mounted on the bell-shaped fairing (4) and form a certain angle with the bell-shaped fairing (4). Gaps for airflow to pass through are provided between the anti-pre-rotation blades (7).

9. A turbine guide vane ring cascade test method, It is characterized in that Using the turbine guide vane ring cascade test device according to any one of claims 1 to 8, the turbine guide vane ring cascade test method comprises the following steps: First wind blowing test: adjusting the angle of the annular blade cascade (6) so that the first group of blades are placed directly above, arranging static pressure holes on the surface of the blades on adjacent blades (10), and sequentially arranging a plurality of static pressure measuring points (11) on the root section (23), the middle section (20) and the tip section (21) of the blade (10) to measure the static pressure on the surface of the blade (10); A plurality of first total pressure probes are evenly distributed along the circumferential direction at a distance of 0.5 to 1.0 times the axial chord length from the leading edge of the blade at the inlet end of the annular blade cascade (6); a plurality of total temperature probes are arranged at a distance of 0.2 to 0.4 times the axial chord length from the first total pressure probe in a direction away from the annular blade cascade (6); the circumferential positions of the total temperature probes are staggered from the positions of the first total pressure probes; a plurality of static pressure measuring points (11) are respectively arranged in the upper flow passage and the lower flow passage at the same axial position as the first total pressure probe; a plurality of second total pressure probes are evenly distributed along the circumferential direction at a distance of 0.5 to 1.0 times the axial chord length from the trailing edge of the blade at the exhaust end of the annular blade cascade (6); a plurality of static pressure measuring points (11) are respectively arranged in the upper flow passage and the lower flow passage at the same axial position as the second total pressure probe; and a three-phase displacement mechanism is arranged directly above the same axial position as the second total pressure probe, and a first blowing test is performed to obtain a first set of blade aerodynamic performance parameters and a cloud diagram of its downstream flow field; Second wind blowing test: rotating the annular blade cascade (6) so that the second set of blades are placed directly above, repeating the first wind blowing test process, and obtaining the aerodynamic performance parameters of the second set of blades and the cloud diagram of the downstream flow field; The Mth blowing test: the annular blade cascade (6) is rotated so that the Mth group of blades is placed directly above, and the first blowing test process is repeated to obtain the aerodynamic performance parameters of the Mth group of blades (10) and the cloud diagram of the downstream flow field.

10. The turbine guide vane ring cascade test method according to claim 9, It is characterized in that The wind blowing test includes changing the guide valve outlet Mach number Ma by adjusting the inlet total pressure 1 , the outlet Mach number Ma is measured during the test 1 =0.3~0.8 The equivalent inlet flow rate under certain conditions , static pressure distribution on blade surface and the total pressure recovery coefficient of the cascade With the exit Mach number Ma 1 The characteristic law curve of change.

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