A shell-shaped four-hole pressure probe for measuring cross-sonic three-dimensional flow fields

Abstract

The present application relates to a kind of shell-shaped four-hole pressure probes for measuring transonic three-dimensional flow field, including shell sector, transition neck, connecting column, four independent pressure measuring holes are set in the joint arc of two shell sectors, wherein one right hole and one left hole are set in each of the two shell sectors as pressure measuring hole, the right hole and the left hole are connected with right hole pressure guide channel and left hole pressure guide channel respectively, middle hole and lower hole are set in the joint arc of the two shell sectors as pressure measuring hole, and the middle hole and the lower hole are connected with middle hole pressure guide channel and lower hole pressure guide channel respectively.Compared with the existing pressure probe, the present application can effectively reduce the influence of blockage effect, reduce the influence of shock wave on pressure measurement in transonic flow field, realize the measurement of a larger range of flow field angle, and provide a reliable method for testing transonic three-dimensional flow field between gas turbine turbine and compressor stage.

Description

Technical Field

[0001] This invention relates to a gas turbine internal flow field testing probe, specifically a shell-shaped four-hole pressure probe, which is suitable for measuring transonic three-dimensional flow field parameters such as total pressure, static pressure, deflection angle, pitch angle, and Mach number between gas turbine and compressor stages. Background Technology

[0002] Reliable flow field measurements of turbine and compressor blades are crucial for validating the numerical design process of gas turbines. Transonic turbine characteristics are a focus of many research projects, aiming to investigate the performance improvements resulting from increased turbine rotor speeds in applications. A major challenge in using porous aerodynamic probes for measurements inside gas turbines is that shock waves are generated in front of the probe in transonic flow fields with Mach numbers close to 1. The flow behind these shock waves is subsonic, leading to a deviation between the pressure measured at the pressure orifice and the actual pressure in the flow field. This reduces the probe's sensitivity to Mach number changes, making it difficult to obtain accurate three-dimensional flow field information. Summary of the Invention

[0003] The problem to be solved by this invention is to provide a shell-shaped four-hole pressure probe for measuring transonic three-dimensional flow fields. This probe has excellent performance, can reduce the blocking effect of probe measurement, reduce the influence of shock waves on pressure measurement, and realize the measurement of flow field angles over a large range. It can be applied to the transonic three-dimensional flow field test between gas turbine turbine and compressor stages to obtain parameters such as total pressure, static pressure, deflection angle, pitch angle, and Mach number.

[0004] To achieve the above objectives, the technical solution of the present invention is: a shell-shaped four-hole pressure probe for measuring transonic three-dimensional flow fields, comprising shell fan surfaces, a transition neck, and a connecting post. Four independent pressure measuring holes are opened at the two shell fan surfaces and their connecting arc. Each of the two shell fan surfaces has a right hole and a left hole as pressure measuring holes, and the right hole and the left hole are respectively connected to the right hole pressure guiding channel and the left hole pressure guiding channel. A middle hole and a lower hole are respectively opened at the connecting arc of the two shell fan surfaces as pressure measuring holes, and the middle hole and the lower hole are respectively connected to the middle hole pressure guiding channel and the lower hole pressure guiding channel.

[0005] Furthermore, the connecting post is a cylinder, and the upper rear part of the shell fan is connected to the connecting post through a transition neck.

[0006] Furthermore, the radius of curvature of the edge of the shell fan is 4 mm to 9 mm, the arc where the two shell fan surfaces meet is rounded with a radius of 0.030 mm to 0.046 mm, the included angle between the two fan surfaces is 20° to 26°, and the thickness is 2 mm to 3.5 mm.

[0007] Furthermore, the right and left holes are at the same height and are located on the fan-shaped surfaces of the two shells, with the angle between the central axis of the hole outlet and the normal direction of the fan-shaped surface being 40° to 50°.

[0008] The middle hole and the lower hole are located on the arc where the fan surfaces of the two shells meet. The central axis of the hole outlet is in the same direction as the normal to the arc. The angle between the lower hole and the middle hole is 35° to 39°.

[0009] Furthermore, the central axis of the middle hole pressure guiding channel and the lower hole pressure guiding channel is located in the YZ plane, the diameter of the middle hole and the lower hole pressure tapping hole is 0.3 mm to 0.5 mm, and the diameter of the pressure guiding channel is 0.2 mm to 0.4 mm.

[0010] Furthermore, the transition neck is located between the shell fan surface and the connecting post, with a length of 4mm to 6mm, and the connecting post has a length of 30mm to 40mm.

[0011] The beneficial effects of this invention are:

[0012] Compared with existing pressure probes, this invention can effectively reduce the impact of blockage effects, reduce the influence of shock waves on pressure measurement in transonic flow fields, and achieve flow field angle measurement over a larger range, providing a reliable method for testing transonic three-dimensional flow fields between gas turbine turbine and compressor stages. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the structure of a shell-shaped four-hole pressure probe for measuring transonic three-dimensional flow fields in an embodiment of the present invention;

[0014] Figure 2 This is the main view of 1;

[0015] Figure 3 This is a YZ cross-sectional view of line 1;

[0016] Figure 4 This is the XY cross-sectional view of 1;

[0017] In the diagram: 1-shell fan surface, 2-transition neck, 3-connecting post, 4-middle hole, 5-lower hole, 6-right hole, 7-left hole, 8-middle hole pressure guiding channel, 9-lower hole pressure guiding channel, 10-right hole pressure guiding channel, 11-left hole pressure guiding channel. Detailed Implementation

[0018] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0019] like Figures 1 to 4As shown in this embodiment, a shell-shaped four-hole pressure probe for measuring transonic three-dimensional flow fields includes a shell fan 1, a transition neck 2, and a connecting post 3. Four independent pressure measuring holes are opened at the two shell fan surfaces 1 and their connecting arc. One pressure measuring hole (right hole 6 and left hole 7) is opened on each of the two shell fan surfaces, which are respectively connected to the right hole pressure guiding channel 10 and the left hole pressure guiding channel 11. Two pressure measuring holes (middle hole 4 and lower hole 5) are opened at the connecting arc of the two shell fan surfaces 1, which are respectively connected to the middle hole pressure guiding channel 8 and the lower hole pressure guiding channel 9.

[0020] Preferably, the connecting post 3 is a cylinder, and the upper rear part of the shell fan 1 is connected to the connecting post 3 through the transition neck 2.

[0021] Preferably, the radius of curvature of the edge of the shell fan 1 is 4 mm to 9 mm, the arc where the two shell fan 1 meet is rounded with a radius of 0.030 mm to 0.046 mm, the included angle between the two fan 1 is 20° to 26°, and the thickness is 2 mm to 3.5 mm.

[0022] Preferably, the radius of curvature of the edge of the shell fan 1 is 8 mm, the arc where the two shell fan 1 meet is rounded with a radius of 0.038 mm, the included angle between the two fan 1s is 23°, and the thickness is 2.5 mm.

[0023] Preferably, the right hole 6 and the left hole 7 are at the same height and are located on the fan surface 1 of the two shells respectively, and the angle between the central axis of the hole outlet and the normal direction of the fan surface is 40° to 50°.

[0024] Preferably, the right hole 6 and the left hole 7 are at the same height and are located on the fan surface 1 of the two shells respectively, with the central axis of the hole outlet at an angle of 45° to the normal direction of the fan surface.

[0025] Preferably, the middle hole 4 and the lower hole 5 are located on the arc where the two shell fan surfaces 1 meet, and the central axis of the hole outlet is aligned with the normal direction of the arc. The angle between the lower hole 8 and the middle hole 4 is 35° to 39°.

[0026] Preferably, the middle hole 4 and the lower hole 5 are located on the arc where the two shell fan surfaces 1 meet, and the central axis of the hole outlet is aligned with the normal direction of the arc. The angle between the lower hole 8 and the middle hole 4 is 37°.

[0027] Preferably, the central hole 4 is connected to the central hole pressure guiding channel 8, and the lower hole 5 is connected to the lower hole pressure guiding channel 9. The central axis of the central hole pressure guiding channel 8 and the lower hole pressure guiding channel 9 is located in the YZ plane. The diameter of the pressure tapping hole of the central hole 4 and the lower hole 5 is 0.3 mm to 0.5 mm, and the diameter of the pressure guiding channel is 0.2 mm to 0.4 mm.

[0028] Preferably, the middle hole 4 is connected to the middle hole pressure guiding channel 8, and the lower hole 5 is connected to the lower hole pressure guiding channel 9. The central axis of the middle hole pressure guiding channel 8 and the lower hole pressure guiding channel 9 is located in the YZ plane. The diameter of the pressure tapping hole of the middle hole 4 and the lower hole 5 is 0.4 mm, and the diameter of the pressure guiding channel is 0.3 mm.

[0029] Preferably, the right hole 6 is connected to the right hole pressure channel 10, and the left hole 7 is connected to the left hole pressure channel 11.

[0030] Preferably, the transition neck 2 is located between the shell fan surface 1 and the connecting post 3, with a length of 4mm to 6mm, and the connecting post 3 has a length of 30mm to 40mm.

[0031] Preferably, the transition neck 2 is located between the shell fan surface 1 and the connecting post 3, with a length of 5 mm, and the connecting post 3 has a length of 35 mm.

[0032] This invention provides a shell-shaped four-hole pressure probe for measuring transonic three-dimensional flow fields. It can effectively reduce the impact of blockage effects, reduce the influence of shock waves on pressure measurement in transonic flow fields, and achieve flow field angle measurement over a wide range. It can be applied to transonic three-dimensional flow field testing between gas turbine turbine and compressor stages.

Claims

1. A shell-shaped four-hole pressure probe for measuring transonic three-dimensional flow fields, characterized in that: The device includes shell-shaped fan surfaces, a transition neck, and a connecting post. Four independent pressure testing holes are provided at the junction of the two shell-shaped fan surfaces and their connecting arc. Each of the two shell-shaped fan surfaces has a right hole and a left hole as pressure testing holes, connected to the right hole pressure guiding channel and the left hole pressure guiding channel, respectively. At the junction of the two shell-shaped fan surfaces, a middle hole and a lower hole are provided as pressure testing holes, connected to the middle hole pressure guiding channel and the lower hole pressure guiding channel, respectively. The radius of curvature of the edge of the shell-shaped fan surface is 4 mm to 9 mm. The corners are rounded, with a radius of 0.030 mm to 0.046 mm, an included angle of 20° to 26° between the two shells, and a thickness of 2 mm to 3.5 mm. The right and left holes are at the same height, located on the two shell shells respectively, with the angle between the central axis of the hole outlet and the normal direction of the shell shell being 40° to 50°. The central axes of the middle hole pressure guiding channel and the lower hole pressure guiding channel are located in the YZ plane. The diameter of the pressure tapping hole of the middle hole and the lower hole is 0.3 mm to 0.5 mm, and the diameter of the pressure guiding channel is 0.2 mm to 0.4 mm.

2. The shell-shaped four-hole pressure probe for measuring transonic three-dimensional flow fields according to claim 1, characterized in that: The connecting post is a cylinder, and the upper rear part of the shell fan is connected to the connecting post through a transition neck.

3. The shell-shaped four-hole pressure probe for measuring transonic three-dimensional flow fields according to claim 1, characterized in that: The middle hole and the lower hole are located on the arc where the fan surfaces of the two shells meet. The central axis of the hole outlet is in the same direction as the normal to the arc. The angle between the lower hole and the middle hole is 35° to 39°.

4. The shell-shaped four-hole pressure probe for measuring transonic three-dimensional flow fields according to claim 1, characterized in that: The transition neck is located between the shell fan and the connecting post, with a length of 4mm to 6mm, and the connecting post has a length of 30mm to 40mm.

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