A method for testing the aerodynamic performance of a full-size large-curvature runner intermediate casing

Abstract

The application provides a method for testing the aerodynamic performance of a full-size large-curvature runner intermediate casing, and belongs to the technical field of testing the aerodynamic performance of an intermediate casing component of an aero-engine. The method comprises the following steps: installing an upper test piece on a test piece, wherein the test piece is a full-size test piece; installing a sensing part, connecting a pressure measuring hose to the sensing part, connecting to a test system, carrying out system debugging, and installing the sensing part, which comprises the following steps: installing at least four total static pressure compound probes on the inlet section and the outlet section of the test piece, wherein each total static pressure compound probe is provided with at least five measuring points, which are used for measuring the total pressure and the static pressure of the inlet and the outlet, and obtaining the total pressure radial distribution and the static pressure radial distribution of the inlet section and the outlet section; supplying air to the test piece; adjusting the state of the test piece; and collecting test data under different states. Through the processing scheme, the rationality of the design of the important performance influence parameter branch plate profile and the wall surface profile can be effectively verified.

Description

Technical Field

[0001] This application relates to the field of aerodynamic performance testing of intermediate casing components for aero engines, and in particular to a method for aerodynamic performance testing of a full-size, large-curvature flow channel intermediate casing. Background Technology

[0002] The intermediate casing is the connecting component between the fan and high-pressure compressor components of a turbofan aero-engine. It is an important transition channel connecting the high and low pressure compression components. There is a huge difference in the radial dimension of the flow channel. In order to accommodate the difference in flow channel height between the upstream fan and the downstream high-pressure compressor, an "S" shape is usually adopted. Through reasonable flow channel and support plate design, channel and support plate losses are minimized as much as possible. Large airflow separation and vortices do not occur in the flow channel. The airflow from the fan outlet enters the high-pressure compressor with a small pressure loss. A relatively uniform flow field is formed at the high-pressure compressor inlet to reduce the possibility of surge in the high-pressure compressor.

[0003] To verify the flow field and performance parameters of the intermediate casing, aerodynamic performance tests were conducted to assess the overall performance of the intermediate casing and ensure that the design parameters meet the requirements of the aero-engine.

[0004] Existing experimental methods use scaled-down test specimens or sector-shaped test sections as carriers to conduct relevant experimental studies and obtain more relevant parameters of the intermediate mechanism. This experimental method is more suitable for basic mechanism research, but it has a large deviation in the radial distribution of parameters of the inlet and outlet flow fields, and it is quite difficult to obtain accurate radial distribution of the support plate wake.

[0005] It cannot meet the requirements for full-size, full-flow test research and performance evaluation during the engineering development phase. Summary of the Invention

[0006] In view of this, this application provides a method for testing the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing, which solves the problems in the prior art and can effectively verify the rationality of the design of important performance-influencing parameters such as the support plate profile and the wall profile.

[0007] This application provides a test method for the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing, employing the following technical solution:

[0008] A method for testing the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing, comprising:

[0009] Step 1: Install the test specimen on the test platform. The test specimen is a full-size intermediate casing test specimen.

[0010] Step 2: Install the sensing element, connect the pressure measuring hose to the sensing element, connect it to the test system, and perform test system commissioning. The installation of the sensing element includes: installing at least four total static pressure composite probes at the inlet and outlet sections of the test piece, with at least five measuring points on each probe, to measure the total pressure and static pressure at the inlet and outlet, and to obtain the radial distribution of total pressure and radial distribution of static pressure at the inlet and outlet sections.

[0011] Step 3: Supply gas to the test specimen;

[0012] Step 4: Adjust the state of the test specimen and collect test data under different states.

[0013] Optionally, in step 2, the total static pressure composite probes at the inlet section are distributed circumferentially along the test piece, and the total static pressure composite probes at the outlet section are distributed circumferentially along the test piece.

[0014] Optionally, the measuring points on the total static pressure composite probe are distributed in a toroidal pattern.

[0015] Optionally, the steps for installing the sensing element may also include:

[0016] Static pressure holes are drilled on the surface of the support plate of the test piece to measure the static pressure on the surface of the support plate profile and obtain the pressure distribution on the surface of the support plate.

[0017] Static pressure holes are opened at equal intervals along the flow direction on the casing and hub surfaces of the curved flow channel of the test piece to obtain the static pressure distribution along the flow channel wall.

[0018] The static pressure holes on the surface of the support plate, the casing of the curved flow channel of the test piece, and the static pressure holes on the surface of the hub are connected to the pressure measuring hose through a stainless steel test tube to input the pressure signal into the test system.

[0019] Optionally, the step of opening static pressure holes on the surface of the support plate of the test piece for measuring the static pressure on the support plate profile specifically includes: selecting three support plates of the test piece, and opening static pressure holes at the root section, the middle section, and the tip section of the support plate blades respectively for measuring the static pressure on the support plate surface.

[0020] Optionally, the step of opening static pressure holes at equal intervals along the flow direction on the casing and hub surfaces of the curved flow channel of the test piece specifically includes: opening two rows of static pressure holes at equal intervals along the flow direction on the casing and hub surfaces of the curved flow channel of the test piece, measuring the static pressure along the flow channel wall, and setting the static pressure holes in the middle area of ​​two adjacent support plate flow channels.

[0021] Optionally, installing the sensing element also includes:

[0022] Multiple total pressure measuring rakes are installed in the flow channel at the tail edge of the support plate. The total pressure measuring rakes are located on the side of the flow channel near the inner ring of the flow channel. The total pressure measuring rakes are equipped with multiple measuring points to measure the total pressure in the tail area of ​​the support plate. The total pressure measuring rakes are moved along the radial direction of the test piece using a two-dimensional displacement mechanism to obtain the radial distribution of the tail pressure of the support plate.

[0023] Optionally, the total pressure measuring rake is provided with at least 10 measuring points, and the total measuring width of the total pressure measuring rake is 1.5-2 times the thickness of the measured support plate. The multiple measuring points are distributed along a straight line or along the circumference of the flow channel.

[0024] In summary, this application includes the following beneficial technical effects:

[0025] This application proposes a test method for the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing. This method can effectively verify the rationality of the design of important performance-influencing parameters such as the support plate profile and the wall profile. It can support the improved design of the wall profile and the support plate profile, providing effective data support for in-depth research on the support plate double-duct intermediate casing, thereby improving the flow matching with high and low pressure compressors and enhancing the overall engine performance. Attached Figure Description

[0026] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0027] Figure 1 This is a schematic diagram of the structure of the test specimen in this application.

[0028] Figure 2 This is a schematic diagram of the process for testing the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing, as described in this application.

[0029] Explanation of reference numerals in the attached drawings: 1. Inlet section; 2. Outlet section; 3. Support plate tail mark. Detailed Implementation

[0030] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0031] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0032] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0033] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The drawings only show the components related to this application and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0034] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0035] This application provides a method for testing the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing.

[0036] like Figure 1 As shown, a method for testing the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing includes:

[0037] Step 1: Install the test specimen on the test platform. The test specimen is a full-size intermediate casing test specimen.

[0038] Step 2: Install the sensing element, connect the pressure measuring hose to the sensing element, connect it to the test system, and perform test system commissioning. Installing the sensing element includes: installing at least four total static pressure composite probes at the inlet section 1 and outlet section 2 of the test piece, respectively. Each total static pressure composite probe has at least five measuring points to measure the total pressure and static pressure at the inlet and outlet, and to obtain the radial distribution of total pressure and radial distribution of static pressure at the inlet section 1 and outlet section 2.

[0039] Step 3: Supply gas to the test specimen.

[0040] Step 4: Adjust the state of the test specimen and collect test data under different states.

[0041] In one embodiment, in step 2, the total static pressure composite probes are distributed circumferentially along the test piece, the total static pressure composite probes at the inlet section are distributed circumferentially along the test piece, and the total static pressure composite probes at the outlet section are distributed circumferentially along the test piece.

[0042] Due to their small size, scaled or sector-shaped test specimens present certain limitations and difficulties in arranging a large number of measuring points, thus having an advantage in obtaining the radial distribution of total pressure and static pressure in the cross section. This application, by using more measuring points and test locations, can obtain a more realistic radial distribution trend of inlet and outlet pressure.

[0043] The steps for installing the sensor also include:

[0044] Depending on the required amount of test data or test parameters, static pressure holes are opened at equal intervals along the flow direction on the casing and hub surfaces of the curved flow channel of the test piece to obtain the static pressure distribution along the flow channel wall.

[0045] The static pressure holes on the support plate surface, the casing of the curved flow channel of the test piece, and the hub surface are connected to the pressure measuring hose via stainless steel test tubes to transmit pressure signals to the testing system. The diameter of the static pressure holes is 0.5-1.0 mm, and the hole depth is greater than 3 times the hole diameter.

[0046] The specific steps for opening static pressure holes on the surface of the support plate of the test piece to measure the static pressure on the support plate profile include: selecting three support plates of the test piece, and opening static pressure holes at the root section, the middle section, and the tip section of the support plate blades respectively to measure the static pressure on the support plate surface.

[0047] The specific steps of opening static pressure holes at equal intervals along the flow direction on the casing and hub surfaces of the curved flow channel of the test piece include: opening two rows of static pressure holes at equal intervals along the flow direction on the casing and hub surfaces of the curved flow channel of the test piece, measuring the static pressure along the friction wall of the flow channel, and setting the static pressure holes in the middle area of ​​two adjacent support plate flow channels.

[0048] The installation of the sensing element also includes obtaining the radial pressure distribution of the trails 3 of the support plates with different thicknesses.

[0049] For each thickness of support plate, one support plate is selected. Multiple total pressure measuring rakes are installed in the flow channel at the tail edge of the selected support plate. The flow channel of the test piece is annular. The area between the midpoint of the annular flow channel and the outer ring along the radial direction of the test piece is the side closer to the outer ring of the flow channel. The area between the midpoint of the annular flow channel and the inner ring along the radial direction of the test piece is the side closer to the inner ring of the flow channel. The total pressure measuring rake is located in the flow channel on the side closer to the inner ring of the flow channel. The total pressure measuring rake is equipped with multiple measuring points to measure the total pressure in the support plate tail area 3. A two-dimensional displacement mechanism is used to move the total pressure rake along the radial direction of the test piece to obtain the radial distribution of the pressure in the support plate tail.

[0050] The total pressure measuring rake has at least 10 measuring points. The total measuring width of the total pressure measuring rake is 1.5-2 times the thickness of the measured support plate. The multiple measuring points are distributed along a straight line or along the circumference of the flow channel.

[0051] Based on existing aerodynamic performance data of intermediate casings, this application proposes a test method for the aerodynamic performance of intermediate casings with large curvature flow channels, specifically targeting the unique technical characteristics of such casings. This method meets the test requirements of intermediate casings under different test conditions, ensures the smooth conduct of aerodynamic performance tests, obtains more realistic and effective test data, and improves the efficiency of intermediate casing test research.

[0052] This application proposes a test method for the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing. This method can effectively verify the rationality of the design of important performance-influencing parameters such as the support plate profile and the wall profile. It can support the improved design of the wall profile and the support plate profile, providing effective data support for in-depth research on the support plate double-duct intermediate casing, thereby improving the flow matching with high and low pressure compressors and enhancing the overall engine performance.

[0053] This application is applicable to the need for aerodynamic performance testing of full-size large curvature flow channel intermediate casings on a ground-based open-air-breathing intermediate casing tester. The method is simple and easy to operate, and its applicability and effectiveness have been verified by testing on multiple full-size large curvature flow channel intermediate casings. It fills a gap in related technologies in China and has high application value in the development of full-size large curvature flow channel intermediate casings in China. It is expected to generate good social and economic benefits in the field of intermediate casing development in China.

[0054] like Figure 2 As shown, in one embodiment, a method for testing the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing includes:

[0055] Step 1: After the test piece is installed on the test bench, install the sensing part, and then connect the pressure measuring hose to the sensing part. The surface pressure of the support plate profile and the wall profile is connected to the pressure measuring hose through the stainless steel test tube, and the pressure signal is connected to the test system.

[0056] Step 2: Instruct the unit to evacuate air from the outlet of the test piece. Match and adjust the main air valve, bypass valve, and make-up air valve to adjust the inlet flow rate or Mach number to the target value. After the state stabilizes, collect test data. At the same time, while maintaining the test state, move the displacement mechanism to measure the support plate wake data at different radial heights.

[0057] Step 3: After completing the data acquisition for one test state, adjust the main air valve, bypass valve, and make-up air valve to adjust the inlet state to the next test target value. After the state stabilizes, collect the test data for each test section.

[0058] Step 4: Repeat Step 3 until all test data collection is completed. Notify the pump to stop, disconnect the pressure measuring hose from the sensing part and the stainless steel test tube, remove the sensing part, seal the test interface, remove the test piece, and restore the equipment.

[0059] 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 method for testing the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing, characterized in that, include: Step 1: Install the test specimen on the test platform. The test specimen is a full-size intermediate casing test specimen. Step 2: Install the sensing element, connect the pressure measuring hose to the sensing element, connect it to the test system, and perform test system commissioning. The installation of the sensing element includes: installing at least four total static pressure composite probes at the inlet and outlet sections of the test piece, with at least five measuring points on each probe, to measure the total pressure and static pressure at the inlet and outlet, and to obtain the radial distribution of total pressure and radial distribution of static pressure at the inlet and outlet sections. Step 3: Supply gas to the test specimen; Step 4: Adjust the state of the test specimen and collect test data under different states; In step 2, the total static pressure composite probes at the inlet section are distributed along the circumference of the test piece, and the total static pressure composite probes at the outlet section are distributed along the circumference of the test piece. The steps for installing the sensor also include: Static pressure holes are drilled on the surface of the support plate of the test piece to measure the static pressure on the surface of the support plate profile and obtain the pressure distribution on the surface of the support plate. Static pressure holes are opened at equal intervals along the flow direction on the casing and hub surfaces of the curved flow channel of the test piece to obtain the static pressure distribution along the flow channel wall. The static pressure holes on the surface of the support plate, the casing of the curved flow channel of the test piece, and the static pressure holes on the surface of the hub are connected to the pressure measuring hose through the lead-out stainless steel test tube, so that the pressure signal can be connected to the test system. The installation of the sensing element also includes: Multiple total pressure measuring rakes are installed in the flow channel at the tail edge of the support plate. The total pressure measuring rakes are located on the side of the flow channel near the inner ring of the flow channel. The total pressure measuring rakes are equipped with multiple measuring points to measure the total pressure in the tail area of ​​the support plate. The total pressure measuring rakes are moved along the radial direction of the test piece using a two-dimensional displacement mechanism to obtain the radial distribution of the tail pressure of the support plate. The specific steps of opening static pressure holes on the surface of the support plate of the test piece for measuring the static pressure on the support plate profile include: selecting three support plates of the test piece, and opening static pressure holes at the root section, the middle section, and the tip section of the support plate blades respectively for measuring the static pressure on the support plate surface; The specific steps of opening static pressure holes at equal intervals along the flow direction on the casing and hub surfaces of the curved flow channel of the test piece include: opening two rows of static pressure holes at equal intervals along the flow direction on the casing and hub surfaces of the curved flow channel of the test piece, measuring the static pressure along the flow channel wall, and setting the static pressure holes in the middle area of ​​two adjacent support plate flow channels.

2. The method for testing the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing according to claim 1, characterized in that, The measuring points on the total static pressure composite probe are distributed in annular pattern.

3. The method for testing the aerodynamic performance of a full-size, large-curvature flow channel intermediate casing according to claim 1, characterized in that, The total pressure measuring rake is equipped with at least 10 measuring points, and the total measuring width is 1.5-2 times the thickness of the measured support plate. Multiple measuring points are distributed along a straight line or along the circumference of the flow channel.

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