A shell-shaped five-hole pressure probe for measuring transonic three-dimensional flow fields

Abstract

This invention relates to a shell-shaped five-hole pressure probe for measuring transonic three-dimensional flow fields. Its features include: shell-shaped fan surfaces, a transition neck, and a connecting post. Five independent pressure measurement holes are formed on the two shell-shaped fan surfaces and their connecting arc. Specifically, right and left holes are formed on each of the two shell-shaped fan surfaces, respectively, and are connected to right and left pressure guiding channels, respectively. Middle, upper, and lower holes are formed on the connecting arc of the two shell-shaped fan surfaces, respectively, and are connected to middle, upper, and lower pressure guiding channels, respectively. Compared with existing pressure probes, this invention can effectively reduce the influence of blockage effects, reduce the impact of shock waves on pressure measurement in transonic flow fields, and achieve flow field angle measurement over a wider range. It provides a reliable method for testing transonic three-dimensional flow fields between gas turbine turbine and compressor stages.

Description

Technical Field

[0001] This invention relates to a gas turbine internal flow field testing probe, specifically a shell-shaped five-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 five-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 five-hole pressure probe for measuring transonic three-dimensional flow fields, characterized in that: it includes shell fan surfaces, a transition neck, and a connecting post; five independent pressure measuring holes are opened at the two shell fan surfaces and their connecting arc; wherein, a right hole and a left hole are opened on the two shell fan surfaces respectively 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, an upper hole, and a lower hole are opened at the connecting arc of the two shell fan surfaces respectively as pressure measuring holes, and the middle hole, the upper hole, and the lower hole are respectively connected to the middle hole pressure guiding channel, the upper 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 central hole, right hole, and left hole are located in the same XY plane, with the right hole and left hole located on the fan-shaped surfaces of the two shells respectively. The central axis of the hole outlet coincides with the normal direction of the fan-shaped surface, and the distance between the central hole and the front and rear of the central hole is 4 mm to 6 mm.

[0008] Furthermore, the central hole, upper hole, and lower hole are located on the arc where the fan surfaces of the two shells meet, and the central axis of the hole outlet is aligned with the normal direction of the arc. The upper hole and lower hole are located above and below the central hole, with an angle of 35° to 39°.

[0009] Furthermore, the middle hole is connected to the middle hole pressure guiding channel, the upper hole is connected to the upper hole pressure guiding channel, and the lower hole is connected to the lower hole pressure guiding channel. The central axis of the middle hole pressure guiding channel, the upper hole pressure guiding channel, and the lower hole pressure guiding channel is located in the YZ plane. The diameter of the pressure tapping hole of the middle hole, the upper 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.

[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 five-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 the YZ cross-sectional view of 1.

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

[0017] Wherein: 1-shell fan surface, 2-transition neck, 3-connecting post, 4-middle hole, 5-right hole, 6-left hole, 7-upper hole, 8-lower hole, 9-middle hole pressure guiding channel, 10-right hole pressure guiding channel, 11-left hole pressure guiding channel, 12-upper hole pressure guiding channel, 13-lower 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 five-hole pressure probe for measuring transonic three-dimensional flow fields includes a shell fan 1, a transition neck 2, and a connecting post 3. Five independent pressure measuring holes are opened at the two shell fan surfaces 1 and their connecting arc. One pressure measuring hole (right hole 5 and left hole 6) is opened on each of the two shell fan surfaces, which are connected to the right hole pressure guiding channel 10 and the left hole pressure guiding channel 11, respectively. Three pressure measuring holes (middle hole 4, upper hole 7, and lower hole 8) are opened at the connecting arc of the two shell fan surfaces, which are connected to the middle hole pressure guiding channel 9, the upper hole pressure guiding channel 13, and the lower hole pressure guiding channel 12, respectively.

[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 central hole 4, the right hole 5, and the left hole 6 are located in the XY plane. The right hole 5 and the left hole 6 are located on the fan surface 1 of the two shells, respectively. The central axis of the hole outlet coincides with the normal direction of the fan surface and is 4 mm to 6 mm away from the central hole 4.

[0024] Preferably, the central hole 4, right hole 5, and left hole 6 are located in the XY plane. The right hole 5 and left hole 6 are located on the fan surface 1 of the two shells, respectively. The central axis of the hole outlet coincides with the normal direction of the fan surface and is 5 mm away from the central hole 4.

[0025] Preferably, the central hole 4, the upper hole 7, and the lower hole 8 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 upper hole 7 and the lower hole 8 are located above and below the central hole, with an angle of 35° to 39°.

[0026] Preferably, the central hole 4, the upper hole 7, and the lower hole 8 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 upper hole 7 and the lower hole 8 are located above and below the central hole, at an angle of 37°.

[0027] Preferably, the middle hole 4 is connected to the middle hole pressure guiding channel 9, the upper hole 7 is connected to the upper hole pressure guiding channel 13, and the lower hole 8 is connected to the lower hole pressure guiding channel 12. The central axis of the middle hole pressure guiding channel 9, the upper hole pressure guiding channel 13, and the lower hole pressure guiding channel 12 is located in the YZ plane. The diameter of the pressure tapping hole of the middle hole 4, the upper hole 7, and the lower hole 8 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 9, the upper hole 7 is connected to the upper hole pressure guiding channel 13, and the lower hole 8 is connected to the lower hole pressure guiding channel 12. The central axis of the middle hole pressure guiding channel 9, the upper hole pressure guiding channel 13, and the lower hole pressure guiding channel 12 is located in the YZ plane. The diameter of the pressure tapping hole of the middle hole 4, the upper hole 7, and the lower hole 8 is 0.4 mm, and the diameter of the pressure guiding channel is 0.3 mm.

[0029] Preferably, the right hole 5 is connected to the right hole pressure channel 10, and the left hole 6 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 an example of a shell-shaped five-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 five-hole pressure probe for measuring transonic three-dimensional flow fields, characterized in that: The structure includes a shell fan-shaped surface, a transition neck, and a connecting post. Five independent pressure measuring holes are formed at the junction of the two shell fan-shaped surfaces and their connecting arc. Specifically, right and left holes are formed on each of the two shell fan-shaped surfaces as pressure measuring holes, connected to the right and left pressure guiding channels, respectively. Middle, upper, and lower holes are formed at the junction of the two shell fan-shaped surfaces as pressure measuring holes, connected to the middle, upper, and lower pressure guiding channels, respectively. The edge of the shell fan-shaped surface... The radius of curvature of the edge 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. The shell-shaped five-hole pressure probe is used for transonic three-dimensional flow field testing between gas turbine turbine and compressor stages. It can effectively reduce the influence of the blockage effect, reduce the influence of shock waves in the transonic flow field on pressure measurement, and realize a wide range of flow field angle measurement.

2. The shell-shaped five-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 five-hole pressure probe for measuring transonic three-dimensional flow fields according to claim 1, characterized in that: The central hole, right hole, and left hole are located in the XY plane. The right hole and left hole are located on the fan surface of the two shells respectively. The central axis of the hole outlet coincides with the normal direction of the fan surface and is 4 mm to 6 mm away from the central hole.

4. The shell-shaped five-hole pressure probe for measuring transonic three-dimensional flow fields according to claim 1, characterized in that: The middle hole, upper hole, and lower hole are located on the arc where the two shell fan surfaces meet. The central axis of the hole outlet is aligned with the normal direction of the arc. The upper hole and lower hole are located above and below the middle hole, with an angle of 35° to 39°.

5. The shell-shaped five-hole pressure probe for measuring transonic three-dimensional flow fields according to claim 1, characterized in that: The middle hole is connected to the middle hole pressure guiding channel, the upper hole is connected to the upper hole pressure guiding channel, and the lower hole is connected to the lower hole pressure guiding channel. The central axis of the middle hole pressure guiding channel, the upper hole pressure guiding channel, and the lower hole pressure guiding channel is located in the YZ plane. The diameter of the pressure tapping hole of the middle hole, the upper 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.

6. The shell-shaped five-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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