Rectification section structure and turbine tester rectification chamber

Abstract

The invention provides a rectification section structure and a turbine tester rectification chamber, and relates to the technical field of aero-engine turbine tests. The rectifying section structure comprises a rectifying section shell, a rectifying pore plate and a honeycomb grid structure. The rectification section shell is provided with a rectification channel, a rectification inlet and a rectification outlet. The rectification pore plate and the honeycomb grid structure are arranged in the rectification channel at intervals, and the honeycomb grid structure intersects with the rectification pore plate and is close to the rectification outlet. A plurality of inclined through holes which mutually form an angle are formed in a rectifying pore plate, and an included angle is formed between the axis of each inclined through hole and the axis of the rectifying pore plate, so that airflow passing through the rectifying pore plate generates a large number of vortex structures under the action of the inclined through holes, and then the vortex structures are effectively eliminated when the airflow with the large number of vortex structures passes through a honeycomb grid structure; through the combined use of the rectifying pore plate and the honeycomb grid structure, the total temperature non-uniformity, the total pressure non-uniformity and the turbulence degree of the main flow at the outlet section of the rectifying chamber are all effectively reduced, and the quality of the inlet main flow is improved.

Description

Technical Field

[0001] The invention relates to the technical field of aero-engine turbine testing, and in particular to a rectifier section structure and a rectifier chamber of a turbine tester. Background Art

[0002] In order to test and verify the performance of the hot end components of the turbine under controllable cost conditions, it is necessary to build a turbine tester that can simulate a high temperature and high pressure environment that is closer to the actual working conditions. However, on the one hand, in the process of increasing the total temperature and total pressure level of the turbine tester, it is inevitable to bring about greater total temperature and total pressure non-uniformity and greater turbulence; on the other hand, whether it is conducting uniform inlet turbine test research or non-periodic inlet turbine test research under the influence of combustion chamber-turbine interaction, the tester is required to provide uniform incoming flow field conditions with lower total temperature, total pressure non-uniformity and turbulence. The above contradictions require that the turbine tester reduce the total temperature, total pressure non-uniformity and turbulence of the mainstream to an acceptable range while providing higher parameter mainstream conditions, that is, it is necessary to set a rectifier in the upstream section of the mainstream to adjust the flow field structure.

[0003] At present, the rectification section of the turbine tester generally uses honeycomb grids and wire meshes for flow adjustment. The honeycomb grids are used to break up the mainstream large-scale vortex structure, while the wire meshes are used to further break up the mainstream vortex structure, thereby obtaining a low-turbulence mainstream with uniform velocity and pressure distribution. However, this design cannot meet the rectification requirements of the turbine tester under high temperature and high pressure conditions. Analysis shows that there are two main defects:

[0004] 1. Insufficient structural strength. The wire mesh used in the current design is prone to structural failure under high temperature (above 1000K) and high pressure (above 1.7MPa) conditions. If the failed part is separated from the main structure and becomes redundant, it will greatly threaten the safety of the tester and the test piece.

[0005] 2. Insufficient total temperature homogenization capability. Through simulation calculations, it was found that the combination of honeycomb grid and wire mesh can effectively reduce the total pressure, velocity non-uniformity and turbulence, but its rectifying effect on total temperature non-uniformity is very limited, and it is difficult to eliminate the total temperature non-uniformity introduced by the upstream heater. Summary of the invention

[0006] The object of the present invention is to provide a straightening section structure which can effectively reduce the non-uniformity of the total intake temperature in a turbine test and improve the quality of the intake mainstream.

[0007] Another object of the present invention is to provide a turbine tester rectifier chamber, which can effectively reduce the non-uniformity of the total intake temperature in the turbine test and improve the quality of the intake mainstream.

[0008] The embodiments of the present invention can be implemented in the following ways:

[0009] A rectifying section structure, a rectifying section shell, wherein the rectifying section shell has a rectifying channel and a rectifying inlet and a rectifying outlet located at both ends of the rectifying channel;

[0010] A rectifying orifice plate, wherein the rectifying orifice plate is arranged in the rectifying channel and is provided with a plurality of oblique through holes which are angled with each other, wherein the axes of the oblique through holes are at an angle to the axis of the rectifying orifice plate, so that the airflow passing through the rectifying orifice plate generates a vortex structure through the plurality of oblique through holes; and

[0011] A honeycomb grid structure is arranged in the rectification channel, and the honeycomb grid structure is arranged at intervals on a side of the rectification orifice plate close to the rectification outlet.

[0012] Optionally, the rectifying orifice plate is a centrally symmetrical structure.

[0013] Optionally, the plurality of inclined through holes include a plurality of first inclined through holes and a plurality of second inclined through holes, and the first inclined through holes and the second inclined through holes have opposite inclination directions.

[0014] Optionally, the plurality of inclined through holes are spaced apart circumferentially along the rectifying orifice plate to form an inclined through hole ring; the rectifying orifice plate is provided with a plurality of inclined through hole rings, the plurality of inclined through hole rings are coaxially distributed, and two adjacent inclined through hole rings are respectively a first inclined through hole ring and a second inclined through hole ring; the plurality of inclined through holes in the first inclined through hole ring are all the first inclined through holes, and the plurality of inclined through holes in the second inclined through hole ring are all the second inclined through holes.

[0015] Optionally, the axis of the inclined through hole intersects with the axis of the rectifying orifice plate, and the intersection of the axis of the first inclined through hole and the axis of the rectifying orifice plate is a first intersection, and the intersection of the axis of the second inclined through hole and the rectifying orifice plate is a second intersection, and the first intersection and the second intersection are respectively located on both sides of the rectifying orifice plate.

[0016] Optionally, the rectifying orifice plate is further provided with a plurality of straight through holes.

[0017] Optionally, part of the straight through holes are arranged at the center of the rectifying orifice plate, and another part of the straight through holes are arranged at the periphery of the rectifying orifice plate, and are distributed at intervals along the circumference of the rectifying orifice plate.

[0018] Optionally, the honeycomb grid structure includes a first honeycomb grid and a second honeycomb grid that are arranged at intervals, and the rectifying orifice plate, the first honeycomb grid and the second honeycomb grid are arranged in sequence along the direction from the rectifying inlet to the rectifying outlet.

[0019] Optionally, the wall thickness of the first honeycomb grid is greater than the wall thickness of the second honeycomb grid.

[0020] Optionally, the flow channel length of the first honeycomb grid is smaller than the flow channel length of the second honeycomb grid.

[0021] Optionally, the distance between the first honeycomb grid and the rectifying orifice plate is greater than the distance between the first honeycomb grid and the second honeycomb grid.

[0022] A turbine tester fairing chamber, the turbine tester fairing chamber comprises a diffuser section, a contraction section and the above-mentioned fairing section structure, the diffuser section is connected to the fairing inlet side of the fairing section structure, and the contraction section is connected to the fairing outlet side of the fairing section structure.

[0023] The beneficial effects of the fairing section structure and the fairing chamber of the turbine tester provided by the embodiments of the present invention include:

[0024] An embodiment of the present invention provides a rectifying section structure, which includes a rectifying section shell, a rectifying orifice plate and a honeycomb grid structure. The rectifying section shell has a rectifying channel and a rectifying inlet and a rectifying outlet located at both ends of the rectifying channel. The rectifying orifice plate and the honeycomb grid structure are arranged at intervals in the rectifying channel, and the honeycomb grid structure intersects the rectifying orifice plate close to the rectifying outlet, so that the airflow entering the rectifying channel from the rectifying inlet first passes through the rectifying orifice plate and then passes through the honeycomb grid structure, and finally flows out from the rectifying outlet. A plurality of oblique through holes at an angle to each other are arranged on the rectifying orifice plate, and the axis of the oblique through hole is at an angle to the axis of the rectifying orifice plate, so that under the action of the plurality of oblique through holes, a large number of vortex structures are generated in the airflow passing through the rectifying orifice plate, and then the vortex structures are effectively eliminated when the airflow with a large number of vortex structures passes through the honeycomb grid structure. Through the combined use of the rectifying orifice plate and the honeycomb grid structure, the total temperature non-uniformity, total pressure non-uniformity and turbulence of the mainstream at the outlet section of the rectifying chamber are effectively reduced, and the quality of the intake mainstream is improved, thereby helping to improve the reliability and test accuracy of the turbine tester.

[0025] An embodiment of the present invention also provides a turbine tester straightening chamber, which includes the above-mentioned straightening section structure, and therefore has the beneficial effect of effectively reducing the total temperature non-uniformity, total pressure non-uniformity and turbulence of the mainstream at the outlet section of the straightening chamber, improving the quality of the intake mainstream, and thus helping to improve the reliability and test accuracy of the turbine tester. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The above features and advantages of the present invention can be better understood after reading the detailed description of the embodiments of the present disclosure in conjunction with the following drawings. In the drawings, the components are not necessarily drawn to scale, and components with similar related properties or features may have the same or similar reference numerals.

[0027] Figure 1A schematic diagram of the internal structure of a turbine tester rectifier chamber provided according to one aspect of the present invention is shown;

[0028] Figure 2 A schematic structural diagram of the internal structure of the turbine tester rectifier chamber provided according to one aspect of the present invention is shown in another perspective;

[0029] Figure 3 A schematic structural diagram of a rectifying orifice plate in a rectifying section structure provided according to one aspect of the present invention is shown;

[0030] Figure 4 A schematic structural diagram of a first honeycomb grid in a rectifying section structure provided according to one aspect of the present invention is shown;

[0031] Figure 5 A partial structure enlarged schematic diagram of a first honeycomb grid in a rectifying section structure provided according to one aspect of the present invention is shown;

[0032] Figure 6 A schematic structural diagram of a second honeycomb grid in a rectifying section structure provided according to one aspect of the present invention is shown;

[0033] Figure 7 A partial structural enlarged schematic diagram of a second honeycomb grid in a rectifying section structure provided according to one aspect of the present invention is shown.

[0034] Reference numerals:

[0035] 10-turbine tester rectifier chamber; 100-rectifier section structure; 110-rectifier section shell; 111-outer shell; 112-inner shell; 113-rectifier channel; 120-rectifier orifice plate; 121-oblique through hole; 122-first oblique through hole; 123-second oblique through hole; 124-straight through hole; 125-first straight through hole; 126-second straight through hole; 130-honeycomb grid structure; 131-first honeycomb grid; 132-second honeycomb grid; 133-hexagonal hole; 211-diffuser section; 212-contraction section. DETAILED DESCRIPTION

[0036] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. Note that the aspects described below in conjunction with the accompanying drawings and specific embodiments are only exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0037] In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", "vertical" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the product of the invention is usually placed when used, rather than indicating or implying that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0038] At the same time, it should be noted that the terms "first", "second", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

[0039] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified or limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, an integral connection, or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or the internal communication of two components, etc. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0040] Figure 1 The internal structure schematic diagram of the turbine tester rectifier chamber 10 provided in this embodiment is shown. Figure 2 The schematic diagram of the internal structure of the turbine tester rectifier chamber 10 provided in this embodiment is shown in another perspective. Figure 1 and Figure 2 This embodiment provides a flow straightening section structure 100, and also provides a turbine tester flow straightening chamber 10.

[0041] The turbine tester fairing chamber 10 includes a fairing section structure 100, and also includes a diffuser section 211 and a contraction section 212. The diffuser section 211 and the contraction section 212 are respectively arranged at the two ends of the fairing section structure 100. When in use, the airflow enters the turbine tester fairing chamber 10 from the diffuser section 211, and then passes through the diffuser section 211, the fairing section structure 100 and the contraction section 212 in sequence before leaving.

[0042] Specifically, along the airflow direction, the opening area of ​​the diffuser section 211 increases gradually. When the airflow passes through the diffuser section 211, the flow velocity of the airflow decreases, and the kinetic energy of the airflow itself is converted into pressure energy, thereby reducing the energy loss of the airflow when it passes through the straightening section structure 100. Along the airflow direction, the opening area of ​​the contraction section 212 decreases gradually, and the airflow is accelerated to the test required speed through the contraction section 212, and the contraction section 212 can prevent the flow from separating.

[0043] The opening area of ​​the rectifying section structure 100 is the same at all places. Specifically, the rectifying section structure 100 includes a rectifying section housing 110, a rectifying orifice plate 120 and a honeycomb grid structure 130. The rectifying section housing 110 has a rectifying channel 113 and a rectifying inlet and a rectifying outlet located at both ends of the rectifying channel 113. The rectifying orifice plate 120 and the honeycomb grid structure 130 are arranged in the rectifying channel 113 at intervals, and the honeycomb grid structure 130 intersects the rectifying orifice plate 120 close to the rectifying outlet, so that the airflow entering the rectifying channel 113 from the rectifying inlet first passes through the rectifying orifice plate 120 and then passes through the honeycomb grid structure 130, and finally flows out from the rectifying outlet. The rectifying orifice plate 120 is provided with a plurality of oblique through holes 121 which are at an angle to each other, and the axis of the oblique through hole 121 is at an angle to the axis of the rectifying orifice plate 120, so that the airflow passing through the rectifying orifice plate 120 generates a large number of vortex structures under the action of the plurality of oblique through holes 121, and then the vortex structures are effectively eliminated when the airflow having a large number of vortex structures passes through the honeycomb grid structure 130. By using the rectifying orifice plate 120 and the honeycomb grid structure 130 in combination, the total temperature non-uniformity, total pressure non-uniformity and turbulence of the mainstream at the outlet section of the rectifying chamber are effectively reduced, and the quality of the intake mainstream is improved, thereby helping to improve the reliability and test accuracy of the turbine tester.

[0044] The rectifying orifice plate 120 is a circular plate consistent with the circumferential contour of the rectifying channel 113, and the outer periphery of the rectifying orifice plate 120 is fixedly connected to the rectifying section housing 110, so that the space on both sides of the rectifying orifice plate 120 is connected only through the holes on the rectifying orifice plate 120 (including the oblique through hole 121 and the straight through hole 124 mentioned later). Similarly, the honeycomb grid structure 130 is a circle consistent with the circumferential contour of the rectifying channel 113, and the outer periphery of the honeycomb grid structure 130 is fixedly connected to the rectifying section housing 110, so that the gas in the rectifying channel 113 needs to pass through the honeycomb grid structure 130. It can be understood that the circumferential contour shape of the rectifying orifice plate 120 and the circumferential contour shape of the honeycomb grid structure 130 can be adjusted according to the needs of the rectifying channel 113.

[0045] Further, the fairing section housing 110 includes an inner housing 112 and an outer housing 111, the inner housing 112 is arranged inside the outer housing 111, and the inner housing 112 includes a plurality of inner housing segments spliced ​​along the axial direction of the outer housing 111. The fairing orifice plate 120 and the honeycomb grid structure 130 are clamped and fixed in the inner housing 112. It can be understood that in some other embodiments, the structure of the fairing section housing 110 and the fixed connection method of the fairing orifice plate 120 and the honeycomb grid structure 130 to the fairing section housing 110 can also be specifically described.

[0046] Figure 3 This is a structural diagram of the rectifying orifice plate 120 in the rectifying section structure 100 provided in this embodiment. Figure 1-Figure 3In this embodiment, the plurality of oblique through holes 121 at angles to each other are arranged on the rectifying orifice plate 120. After the airflow passes through the oblique through holes 121, the flow directions are different, and then the airflow mixes with each other, generating a large number of vortex structures. Before the airflow flows along the rectifying channel 113 to the honeycomb grid structure, the large number of vortex structures make the fluid mixing gradually complete, and as the fluid mixing is complete, the total temperature uniformity is improved. The degree of complete mixing is positively correlated with the distance between the rectifying orifice plate 120 and the honeycomb grid structure 130, so the distance can be set according to demand.

[0047] In this embodiment, the rectifying orifice plate 120 is a centrosymmetric structure. By setting the rectifying orifice plate 120 as a centrosymmetric structure, the rectifying orifice plate 120 can have a high uniformity capability for different total temperature distributions of incoming flows, that is, it can play a good role in improving the total temperature uniformity problem in different conditions, and is highly versatile and easy to install.

[0048] Specifically, the plurality of oblique through holes 121 on the rectifying orifice plate 120 include a plurality of first oblique through holes 122 and a plurality of second oblique through holes 123, and the first oblique through holes 122 and the second oblique through holes 123 are inclined in opposite directions. By designing the inclined directions of the first oblique through holes 122 and the second oblique through holes 123, it is helpful to increase the mixing intensity, thereby improving the mixing efficiency and ensuring complete mixing.

[0049] The distribution of multiple oblique through holes 121 along the circumferential interval of the rectifying orifice plate 120 forms an oblique through hole ring. The rectifying orifice plate 120 is provided with multiple oblique through hole rings, and the multiple oblique through hole rings are coaxially distributed, and two adjacent oblique through hole rings are respectively a first oblique through hole ring and a second oblique through hole ring. The multiple oblique through holes 121 in the first oblique through hole ring are all first oblique through holes 122, and the multiple oblique through holes 121 in the second oblique through hole ring are all second oblique through holes 123, so that the multiple oblique through holes 121 in the same oblique through hole ring have the same inclination direction, and at the same time, along the radial direction of the rectifying orifice plate 120, the first oblique through holes 122 and the second oblique through holes 123 are staggeredly distributed.

[0050] Further, the axis of the oblique through hole 121 is compared with the axis of the rectifying orifice plate 120, and the intersection of the axis of the first oblique through hole 122 and the axis of the rectifying orifice plate 120 is the first intersection, and the intersection of the axis of the second oblique through hole 123 and the rectifying orifice plate 120 is the second intersection, and the first intersection and the second intersection are respectively located on both sides of the rectifying orifice plate 120. Specifically, the intersection of the axes of the multiple oblique through holes 121 of the same oblique through hole ring and the axis of the rectifying orifice plate 120 is the same point.

[0051] Furthermore, a plurality of straight through holes 124 are provided on the rectifying orifice plate 120. By providing the straight through holes 124, the flow resistance of the airflow when flowing through the rectifying orifice plate 120 can be effectively reduced, which helps to enhance the structural strength of the rectifying orifice plate 120.

[0052] Optionally, part of the straight through holes 124 are arranged at the center of the rectifying orifice plate 120, and another part of the straight through holes 124 are arranged at the periphery of the rectifying orifice plate 120, and are distributed at intervals along the circumference of the rectifying orifice plate 120. Specifically, the straight through holes 124, as the name implies, are holes whose flow direction is consistent with the flow direction of the rectifying channel 113. In other words, in this embodiment, the axis of the straight through hole 124 is parallel to the axis of the rectifying orifice plate 120. A straight through hole 124 is arranged at the center of the rectifying orifice plate 120, and the straight through hole 124 is a first straight through hole 125. Specifically, the first straight through hole 125 is coaxially arranged with the rectifying orifice plate 120. A plurality of straight through holes 124 are arranged at the periphery of the rectifying orifice plate 120, and the plurality of straight through holes 124 are second straight through holes 126. The axes of the plurality of second straight through holes 126 are parallel to the axis of the rectifying orifice plate 120.

[0053] Figure 4 This is a schematic structural diagram of the first honeycomb grid 131 in the rectifying section structure 100 provided in this embodiment. Figure 5 This is a schematic diagram of the partial structure of the first honeycomb grid 131 in the rectifying section structure 100 provided in this embodiment. Figure 6 This is a schematic diagram of the structure of the second honeycomb grid 132 in the rectifying section structure 100 provided in this embodiment. Figure 7 This is an enlarged schematic diagram of the partial structure of the second honeycomb grid 132 in the rectifying section structure 100 provided in this embodiment. Figure 1-Figure 7 In this embodiment, the honeycomb grid structure 130 includes a first honeycomb grid 131 and a second honeycomb grid 132 arranged at intervals, and the rectifying orifice plate 120, the first honeycomb grid 131 and the second honeycomb grid 132 are arranged in sequence from the rectifying inlet to the rectifying outlet. The honeycomb structure of the honeycomb grid breaks the vortex structure developed upstream, reduces the non-uniformity of the total pressure and turbulence of the airflow, and helps to further reduce the non-uniformity of the total temperature.

[0054] Furthermore, the wall thickness of the first honeycomb grid 131 is greater than the wall thickness of the second honeycomb grid 132. It should be noted that in the description of this embodiment, the honeycomb grid is a grid structure with hexagonal holes. At the same time, the "wall thickness of the honeycomb grid" mentioned in this embodiment is the distance L between two adjacent hexagonal holes 133 in the honeycomb grid (such as Figure 5 shown).

[0055] By setting the wall thickness of the first honeycomb grid 131 to be large, the first honeycomb grid 131 can withstand a greater impact from a strong mixed mainstream in the process of breaking the vortex structure than the second honeycomb grid 132, and has a higher structural strength. After the airflow passes through the first honeycomb grid 131, the large-sized vortex structure is broken, and the non-uniformity and turbulence are reduced. Since the first honeycomb grid 131 is closer to the rectifying orifice plate 120 than the second honeycomb grid 132, that is, the first honeycomb grid 131 is arranged upstream of the second honeycomb grid 132, the airflow passes through the first honeycomb grid 131 before reaching the second honeycomb grid 132, so the second honeycomb grid 132 faces the mainstream that has passed through the first honeycomb grid 131 and obtained preliminary homogenization, so the wall thickness of the second honeycomb grid 132 can be set to be smaller than that of the first honeycomb grid 131.

[0056] Furthermore, the flow channel length of the first honeycomb grid 131 is less than the flow channel length of the second honeycomb grid 132. It should be noted that in the description of this embodiment, the flow channel length of the honeycomb grid is the length of the honeycomb grid along the direction from the rectification inlet to the rectification outlet. In this way, the second honeycomb grid 132 can ensure the rectification ability of the airflow, ensuring that the rectified airflow can meet the test requirements.

[0057] Furthermore, the distance between the first honeycomb grid 131 and the rectifying orifice plate 120 is greater than the distance between the first honeycomb grid 131 and the second honeycomb grid 132, thereby leaving a sufficient distance between the first honeycomb grid 131 and the rectifying orifice plate 120 so that the vortex structure formed after flowing through the rectifying orifice plate 120 can completely mix the airflow.

[0058] Optionally, the rectifying orifice plate 120 is disposed at the rectifying inlet, in other words, in this embodiment, the rectifying orifice plate 120 is the rectifying inlet of the rectifying channel 113. The end of the second honeycomb grid 132 away from the first honeycomb grid 131 is located at the rectifying outlet, so that the distance between the second honeycomb grid 132 and the rectifying orifice plate 120 is the largest, which helps to reserve a sufficient distance between the rectifying orifice plate 120 and the first honeycomb grid 131.

[0059] It should be noted that, in the present embodiment, the honeycomb grid structure 130 includes two honeycomb grids arranged at intervals. By setting the two honeycomb grids, the airflow with a large number of vortex structures is rectified to ensure the rectification capability. It can be understood that in other embodiments, for example, when there is a sufficiently long space to set the honeycomb grid structure 130, only one honeycomb grid may be set.

[0060] The embodiment of the present invention provides a straightening section structure 100 and a turbine tester straightening chamber 10. After the mainstream enters the turbine tester straightening chamber 10, it first passes through the diffuser section 211 to convert its own kinetic energy into pressure energy, thereby reducing the energy loss in the straightening process. Then the mainstream enters the straightening section structure 100 through the straightening orifice plate 120. When passing through the straightening orifice plate 120, a large number of vortex structures are formed under the action of multiple oblique through holes 121 on the orifice plate, thereby enhancing the mixing ability. Then the mainstream gradually improves the total temperature uniformity in the space between the straightening orifice plate 120 and the first honeycomb grid 131 as the fluid is fully mixed. Then the fully mixed mainstream passes through the first honeycomb grid 131 and the second honeycomb grid 132 in turn, and the vortex structure formed by the honeycomb structure of the first honeycomb grid 131 and the second honeycomb grid 132 reduces the non-uniformity of the total pressure and turbulence of the mainstream, and further reduces the non-uniformity of the total temperature. Finally, the mainstream enters the contraction section 212 after leaving the straightening section structure 100, and the mainstream velocity is increased to the required level.

[0061] The straightening section structure 100 and the straightening chamber 10 of the turbine tester provided in the embodiment of the present invention adopt a straightening chamber structure of a diffuser section 211, a straightening section structure 100 and a contraction section 212, and set a straightening orifice plate 120, a first honeycomb grid 131 and a second honeycomb grid 132 in the straightening section structure 100, which effectively reduces the non-uniformity of the total temperature, the non-uniformity of the total pressure and the turbulence of the mainstream, improves the intake uniformity of the downstream test piece (not shown in the figure), reduces the influence of the incoming flow non-uniformity on the turbine test, reduces the demand for parameter measurement points at the inlet of the test piece, and improves the economy, reliability and test data accuracy of the turbine tester under high temperature and high pressure conditions.

[0062] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technology in the field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A rectifying section structure, characterized in that: The rectifying section structure comprises: A rectifying section housing, wherein the rectifying section housing has a rectifying channel and a rectifying inlet and a rectifying outlet located at two ends of the rectifying channel; A rectifying orifice plate, wherein the rectifying orifice plate is arranged in the rectifying channel and is provided with a plurality of oblique through holes which are angled with each other, wherein the axes of the oblique through holes are at an angle to the axis of the rectifying orifice plate, so that the airflow passing through the rectifying orifice plate generates a vortex structure through the plurality of oblique through holes; and A honeycomb grid structure is arranged in the rectification channel, and the honeycomb grid structure is arranged at intervals on a side of the rectification orifice plate close to the rectification outlet.

2. The rectifying section structure according to claim 1, characterized in that: The rectifying orifice plate is a centrally symmetrical structure.

3. The rectifying section structure according to claim 1, characterized in that: The plurality of inclined through holes include a plurality of first inclined through holes and a plurality of second inclined through holes, and the first inclined through holes and the second inclined through holes have opposite inclined directions.

4. The rectifying section structure according to claim 3, characterized in that: The plurality of inclined through holes are spaced apart along the circumference of the rectifying orifice plate to form an inclined through hole ring; the rectifying orifice plate is provided with a plurality of inclined through hole rings, the plurality of inclined through hole rings are coaxially distributed, and two adjacent inclined through hole rings are respectively a first inclined through hole ring and a second inclined through hole ring; the plurality of inclined through holes in the first inclined through hole ring are all the first inclined through holes, and the plurality of inclined through holes in the second inclined through hole ring are all the second inclined through holes.

5. The rectifying section structure according to claim 3, characterized in that: The axis of the inclined through hole intersects with the axis of the rectifying orifice plate, and the intersection of the axis of the first inclined through hole and the axis of the rectifying orifice plate is a first intersection, and the intersection of the axis of the second inclined through hole and the rectifying orifice plate is a second intersection, and the first intersection and the second intersection are respectively located on both sides of the rectifying orifice plate.

6. The rectifying section structure according to claim 1, characterized in that: The rectifying orifice plate is also provided with a plurality of straight through holes.

7. The rectifying section structure according to claim 6, characterized in that: Part of the straight through holes are arranged at the center of the rectifying orifice plate, and another part of the straight through holes are arranged at the periphery of the rectifying orifice plate and are distributed at intervals along the circumference of the rectifying orifice plate.

8. The rectifying section structure according to claim 1, characterized in that: The honeycomb grid structure comprises a first honeycomb grid and a second honeycomb grid arranged at intervals, and the rectifying orifice plate, the first honeycomb grid and the second honeycomb grid are arranged in sequence along the direction from the rectifying inlet to the rectifying outlet.

9. The rectifying section structure according to claim 8, characterized in that: The wall thickness of the first honeycomb grid is greater than the wall thickness of the second honeycomb grid.

10. The rectifying section structure according to claim 8, characterized in that: The flow channel length of the first honeycomb grid is shorter than the flow channel length of the second honeycomb grid.

11. The rectifying section structure according to claim 8, characterized in that: The distance between the first honeycomb grid and the rectifying orifice plate is greater than the distance between the first honeycomb grid and the second honeycomb grid.

12. A turbine tester rectifier chamber, characterized in that: The turbine tester fairing chamber includes a diffuser section, a contraction section and a fairing section structure as described in any one of claims 1 to 11, wherein the diffuser section is connected to a fairing inlet side of the fairing section structure, and the contraction section is connected to a fairing outlet side of the fairing section structure.

Images