Hypersonic wind tunnel nozzle with a card slot structure and a method of manufacturing the same

Abstract

The application provides a hypersonic wind tunnel nozzle with a clamping groove structure and a manufacturing method thereof, and belongs to the technical field of rocket jet propulsion devices, and comprises a nozzle outer wall, a nozzle inner wall and a deformation prevention structure, wherein the outer surface of the nozzle inner wall is provided with an inner wall protrusion, the inner surface of the nozzle outer wall is outwardly recessed to form an outer wall groove, so that the nozzle inner wall is clamped to the nozzle outer wall; the deformation prevention structure comprises a stress receiving portion arranged on the nozzle inner wall and a matching portion arranged on the nozzle outer wall; a cooling medium channel is arranged between the nozzle outer wall and the nozzle inner wall, the stress receiving portion and the matching surface are matched, and the inward deformation of the nozzle inner wall under the pressure of the cooling medium is prevented. The application can keep the nozzle inner wall in the strengthened state of forging or spinning deformation of the raw material, the high-temperature process of diffusion bonding or brazing is omitted, the manufacturing period of the wind tunnel nozzle is greatly shortened, the manufacturing cost is reduced, the replaceability of the nozzle inner wall is realized by adopting the connection mode of the threaded connection structure + sealing ring.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket jet propulsion devices, and in particular to a hypersonic wind tunnel nozzle with a slot structure and a manufacturing method thereof. Background Art

[0002] Hypersonic wind tunnels are crucial for conducting aerodynamic performance tests on hypersonic vehicles. The nozzle profile determines the quality of the flow field in the test area and is one of the most critical components in the entire wind tunnel system. Traditional wind tunnel nozzles typically consist of a copper inner wall and a steel outer wall, which are typically joined by brazing or diffusion bonding. The copper alloy used in wind tunnel nozzles cannot typically be strengthened through heat treatment. Therefore, after diffusion bonding or brazing, the inner wall copper alloy remains in a soft state, with yield strength and tensile strength significantly reduced compared to the original material in its deformation-hardened state. Summary of the Invention

[0003] The object of the present invention is to provide a hypersonic wind tunnel nozzle with a slot structure. The hypersonic wind tunnel nozzle with a slot structure adopts a snap-on connection method so that the inner wall of the nozzle can maintain the strengthened state of the raw material after forging or spinning deformation, thereby improving the stress-bearing capacity and service life of the inner wall of the nozzle, eliminating the high-temperature process of diffusion bonding or brazing, greatly shortening the manufacturing cycle of the wind tunnel nozzle, and reducing manufacturing costs.

[0004] Another object of the present invention is to provide a method for manufacturing a hypersonic wind tunnel nozzle.

[0005] To achieve the purpose of the present invention, the present invention adopts the following technical solutions:

[0006] According to one aspect of the present invention, a hypersonic wind tunnel nozzle with a slot structure is provided. The hypersonic wind tunnel nozzle with a slot structure comprises:

[0007] nozzle outer wall;

[0008] The nozzle inner wall is sleeved inside the nozzle outer wall, wherein the outer surface of the nozzle inner wall is provided with an inner wall protrusion, and the inner surface of the nozzle outer wall is recessed outward to form an outer wall groove corresponding to the inner wall protrusion, so that the nozzle inner wall is clamped to the nozzle outer wall;

[0009] An anti-deformation structure, comprising a force-bearing portion and a matching portion, wherein the force-bearing portion is provided on the inner wall of the nozzle, and the matching portion is provided on the outer wall of the nozzle;

[0010] A cooling medium channel is provided between the outer wall of the nozzle and the inner wall of the nozzle, and the force-bearing portion and the matching portion cooperate with each other to prevent the inner wall of the nozzle from deforming inwards under the pressure of the cooling medium.

[0011] According to one embodiment of the present invention, the inner wall protrusion is provided with an inner wall groove, the bottom of the outer wall groove is provided with an outer wall protrusion corresponding to the inner wall groove, and the outer wall protrusion is inserted into the inner wall groove, so that the inner wall of the nozzle is clamped to the outer wall of the nozzle;

[0012] The force-bearing portion includes a plurality of force-bearing surfaces, wherein the force-bearing surfaces are arranged in the inner wall groove, and the groove wall of the inner wall groove that contacts the outer wall protrusion serves as the force-bearing surface;

[0013] The mating portion includes a plurality of mating surfaces, wherein the mating surfaces are arc-shaped and are provided on the outer wall protrusion, and the surface where the outer wall protrusion contacts the inner wall groove is the mating surface, and the mating surfaces are arc-shaped to facilitate assembly between the inner wall groove and the outer wall protrusion;

[0014] A surface perpendicular to the axis of the inner wall of the nozzle intersects with the outer surface of the outer wall of the nozzle to form a circular plane. Multiple force-bearing surfaces are evenly distributed along the circumference of the circular plane. Multiple mating surfaces are evenly distributed along the circumference of the circular plane. The force-bearing surfaces and the mating surfaces correspond one to one to generate circumferential prestress on the inner wall of the nozzle.

[0015] According to one embodiment of the present invention, when the inner wall groove and the outer wall protrusion just come into contact, the contact between the inner wall groove and the outer wall protrusion forms a plurality of first contact points, and the plurality of first contact points form a first circle perpendicular to the axis of the outer wall of the nozzle, the radius of the first circle is R0, and the axial clearance between the inner wall groove and the outer wall protrusion is T z0 The gap between the non-matching surface of the inner wall groove and the non-matching surface of the outer wall protrusion is T n0 , the matching length between the force-bearing surface and the matching surface is L0;

[0016] When the inner wall groove and the outer wall protrusion are engaged, the contact between the notch of the inner wall groove and the outer wall protrusion forms a plurality of second contact points, and the plurality of second contact points form a second circle perpendicular to the axis of the nozzle outer wall. The radius of the second circle is R1, and the axial clearance between the inner wall groove and the outer wall protrusion is T z1 The gap between the non-matching surface of the inner wall groove and the non-matching surface of the outer wall protrusion is T n1 , the matching length between the force-bearing surface and the matching surface is L1;

[0017] Among them, 0.2 mm≤T z1 <T z0 ≤0.6mm, 0.1 mm≤T n1 <T n0≤0.25mm, the slope of the mating surface is α, 5°≤a≤20°, and the circumferential prestress generated by the inner wall (2) of the nozzle is σ,

[0018] σ=(L1-L0)×E×Tanα / R0;

[0019] In the formula: E is the elastic modulus of the material of the inner wall of the nozzle.

[0020] According to one embodiment of the present invention, there are a plurality of inner wall protrusions, and the plurality of inner wall protrusions are arranged along the extension direction of the generatrix of the inner wall of the nozzle to form an inner wall protrusion row;

[0021] There are at least two inner wall protrusion rows, and two adjacent inner wall protrusion rows are evenly distributed along the circumferential direction of the outer surface of the inner wall of the nozzle.

[0022] According to one embodiment of the present invention, there are a plurality of inner wall protrusions, and the plurality of inner wall protrusions are evenly distributed along the outer circumference of the circular plane to form a protrusion annular array;

[0023] There are multiple raised annular arrays, and adjacent raised annular arrays are parallel to each other.

[0024] According to one embodiment of the present invention, a plurality of cooling grooves for accommodating the cooling medium are provided along a generatrix direction of the inner wall of the nozzle, and the plurality of cooling grooves are evenly distributed along the circumference of the inner wall of the nozzle.

[0025] According to one embodiment of the present invention, the input end of the inner wall of the nozzle is provided with a first inner wall L-shaped groove, the input end of the outer wall of the nozzle is provided with a first outer wall L-shaped groove corresponding to the first inner wall L-shaped groove, the output end of the inner wall of the nozzle is provided with a second inner wall L-shaped groove, and the output end of the outer wall of the nozzle is provided with a second outer wall L-shaped groove corresponding to the second inner wall L-shaped groove;

[0026] Among them, the first inner wall L-shaped groove is inserted into the first outer wall L-shaped groove, and the second inner wall L-shaped groove is inserted into the second outer wall L-shaped groove. Sealing rings are provided between the first inner wall L-shaped groove and the first outer wall L-shaped groove, and between the second inner wall L-shaped groove and the second outer wall L-shaped groove to ensure the sealing between the outer wall and the inner wall of the nozzle.

[0027] According to one embodiment of the present invention, the first inner wall L-shaped groove and the first outer wall L-shaped groove, and the second inner wall L-shaped groove and the second outer wall L-shaped groove are both connected by bolts.

[0028] According to one aspect of the present invention, a method for manufacturing a hypersonic wind tunnel nozzle is provided. The method for manufacturing a hypersonic wind tunnel nozzle comprises:

[0029] Processing the inner surface of the outer wall of the nozzle to form an outer wall groove;

[0030] Processing the outer surface of the inner wall of the nozzle to form an inner wall bulge;

[0031] A plurality of cooling grooves are provided on the outer surface of the inner wall of the nozzle along the longitudinal direction;

[0032] cleaning the surface of the inner wall of the nozzle and the surface of the outer wall of the nozzle;

[0033] The nozzle inner wall and the nozzle outer wall are assembled to form a hypersonic wind tunnel nozzle.

[0034] According to one embodiment of the present invention, the method further comprises:

[0035] The end surface of the inner wall of the nozzle is processed to form a first inner wall L-shaped groove and a second inner wall L-shaped groove,

[0036] Processing the end surface of the outer wall of the nozzle to form a first outer wall L-shaped groove and a second outer wall L-shaped groove, and providing sealing rings between the first inner wall L-shaped groove and the first outer wall L-shaped groove, and between the second inner wall L-shaped groove and the second outer wall L-shaped groove, to thread the end surface of the hypersonic wind tunnel nozzle;

[0037] The end surface of the outer wall of the nozzle and the end surface of the inner wall of the nozzle are both left with a margin of 1 mm to 2 mm. After the end surface of the hypersonic wind tunnel nozzle is threaded, the margin of the end surface of the outer wall of the nozzle and the end surface of the inner wall of the nozzle are removed;

[0038] The assembled hypersonic wind tunnel nozzle is subjected to a performance test.

[0039] An embodiment of the present invention has the following advantages or beneficial effects:

[0040] The hypersonic wind tunnel nozzle with a slot structure of the present invention adopts a snap-fitting method between the nozzle outer wall and the nozzle inner wall, so that the nozzle inner wall can maintain the strengthened state of the raw material after forging or spinning deformation, thereby improving the stress-bearing capacity and service life of the nozzle inner wall, eliminating the high-temperature process of diffusion bonding or brazing, greatly shortening the manufacturing cycle of the wind tunnel nozzle, and reducing manufacturing costs.

[0041] By providing an anti-deformation structure between the nozzle outer wall and the nozzle inner wall, a certain prestress can be provided for the nozzle inner wall to prevent the nozzle inner wall from deforming inwards under the pressure of the cooling medium.

[0042] The inner wall of the nozzle is cooled by the cooling groove, thereby protecting the inner wall of the nozzle and improving the performance of the inner wall of the nozzle.

[0043] Since the outer wall of the nozzle and the inner wall of the nozzle do not need to be welded, the inner wall of the nozzle can be replaced when it is worn after long-term use. BRIEF DESCRIPTION OF DRAWINGS

[0044] The above and other features and advantages of the present application will become more apparent by describing in detail exemplary embodiments thereof with reference to the attached drawings in which:

[0045] Figure 1 is a schematic diagram of a hypersonic wind tunnel nozzle with a card slot structure according to an exemplary embodiment.

[0046] Figure 2 is Figure 1 is a sectional view of the A-A portion in FIG. 1.

[0047] Figure 3 is a schematic diagram of an outer wall of a nozzle according to an exemplary embodiment.

[0048] Figure 4 is a schematic diagram of an inner wall of a nozzle according to an exemplary embodiment.

[0049] Figure 5 is a schematic diagram of an inner wall groove and the outer wall protrusion in contact according to an exemplary embodiment.

[0050] Figure 6 is a schematic diagram of an inner wall groove and the outer wall protrusion in contact according to an exemplary embodiment.

[0051] In the drawings:

[0052] 1, outer wall of nozzle; 11, outer wall groove; 12, outer wall protrusion; 13, first outer wall L-shaped groove; 14, second outer wall L-shaped groove; 2, inner wall of nozzle; 21, inner wall protrusion; 22, inner wall groove; 23, cooling groove; 24, first inner wall L-shaped groove; 25, second inner wall L-shaped groove; 3, force receiving surface; 4, mating surface; 5, sealing ring; 6, bolt. DETAILED DESCRIPTION

[0053] Example embodiments now will be described more fully hereinafter with reference to the accompanying drawings; however, the example embodiments can be implemented in many different forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the example embodiments to those skilled in the art. Like reference numerals refer to like elements throughout the several views.

[0054] The terms "a", "an", "the", and "said" are used to indicate the presence of one or more elements / components / etc.; the terms "including" and "having" are used to express an open-ended inclusive meaning and mean that additional elements / components / etc. may be present in addition to the listed elements / components / etc.

[0055] like Figures 1 to 6 As shown, Figure 1 A schematic diagram of a hypersonic wind tunnel nozzle with a slot structure provided by the present invention is shown. Figure 2 yes Figure 1 Cross-sectional view of section AA. Figure 3 A schematic diagram of the nozzle outer wall 1 provided by the present invention is shown. Figure 4 A schematic diagram of the nozzle inner wall 2 provided by the present invention is shown. Figure 5 1 is a schematic diagram showing the inner wall groove 22 and the outer wall protrusion 12 provided by the present invention when they just come into contact. Figure 6 It shows a schematic diagram of the inner wall groove 22 and the outer wall protrusion 12 provided by the present invention after being engaged with each other.

[0056] A hypersonic wind tunnel nozzle with a slot structure according to an embodiment of the present invention includes:

[0057] Nozzle outer wall 1;

[0058] The nozzle inner wall 2 is sleeved inside the nozzle outer wall 1, wherein the outer surface of the nozzle inner wall 2 is provided with an inner wall protrusion 21, and the inner surface of the nozzle outer wall 1 is recessed outward to form an outer wall groove 11 corresponding to the inner wall protrusion 21, so that the nozzle inner wall 2 is clamped to the nozzle outer wall 1;

[0059] The anti-deformation structure includes a force-bearing portion and a matching portion, wherein the force-bearing portion is arranged on the inner wall 2 of the nozzle and the matching portion is arranged on the outer wall 1 of the nozzle;

[0060] A cooling medium channel is provided between the nozzle outer wall 1 and the nozzle inner wall 2, and the force-bearing portion and the matching portion cooperate with each other to prevent the nozzle inner wall 2 from deforming inwards under the pressure of the cooling medium.

[0061] Among them, the nozzle inner wall 2 is inserted into the nozzle outer wall 1, and an inner wall protrusion 21 is provided on the outer surface of the nozzle inner wall 2, and the inner surface of the nozzle outer wall 1 is recessed outward to form an outer wall groove 11, so that the nozzle inner wall 2 is clamped to the nozzle outer wall 1. The material of the nozzle outer wall 1 is steel, and the material of the nozzle inner wall 2 is copper alloy. Copper alloy cannot usually be strengthened by heat treatment. After brazing or diffusion bonding, it is in a soft state, and its yield strength and tensile strength are greatly reduced compared with the deformation strengthening state of the raw material. Therefore, the present invention can not only avoid the high temperature process of brazing or diffusion bonding scheme, but also improve the strength of the nozzle inner wall 2; hypersonic wind The hypersonic wind tunnel nozzle is the core section of the supersonic wind tunnel. The shape of the hypersonic wind tunnel nozzle is the key to obtaining the test Mach number. Its change will not only lead to changes in the actual test Mach number, but also affect the full flow field or local flow field in the space, which will affect the reliability of the test data; the cooling medium channel is arranged between the nozzle outer wall 1 and the nozzle inner wall 2. The cooling medium is introduced into the cooling medium channel to cool the hypersonic wind tunnel nozzle; by utilizing the anti-deformation structure, the nozzle inner wall 2 can be prevented from deforming inward under the pressure of the cooling medium, thereby avoiding the impact of the deformation of the nozzle inner wall 2 on the wind tunnel experiment and improving product performance.

[0062] In a preferred embodiment of the present invention, the inner wall protrusion 21 is provided with an inner wall groove 22, and the bottom of the outer wall groove 11 is provided with an outer wall protrusion 12 corresponding to the inner wall groove 22, and the outer wall protrusion 12 is inserted into the inner wall groove 22, so that the nozzle inner wall 2 is clamped to the nozzle outer wall 1;

[0063] The force-bearing portion includes a plurality of force-bearing surfaces 3, wherein the force-bearing surfaces 3 are arranged in the inner wall groove 22, and the groove wall of the inner wall groove 22 that contacts the outer wall protrusion 12 is the force-bearing surface 3;

[0064] The mating portion includes a plurality of mating surfaces 4, wherein the mating surfaces 4 are arc-shaped and are provided on the outer wall protrusion 12, and the surface where the outer wall protrusion 12 contacts the inner wall groove 22 is the mating surface 4, and the mating surface 4 is arc-shaped to facilitate assembly between the inner wall groove 22 and the outer wall protrusion 12;

[0065] A surface perpendicular to the axis of the nozzle inner wall 2 intersects with the outer surface of the nozzle outer wall 1 to form a circular plane. Multiple force-bearing surfaces 3 are evenly distributed along the circumference of the circular plane. Multiple mating surfaces 4 are evenly distributed along the circumference of the circular plane. The force-bearing surfaces 3 and the mating surfaces 4 correspond one to one to generate circumferential prestress on the nozzle inner wall 2.

[0066] like Figures 1-6As shown, by providing an inner wall groove 22 on the inner wall protrusion 21 and providing an outer wall protrusion 12 at the bottom of the outer wall groove 11, the nozzle inner wall 2 can be stably connected to the nozzle outer wall 1. In addition, the contact surfaces between the outer wall protrusion 12 and the inner wall groove 22 are the mating surface 4 and the force-bearing surface 3, respectively. Because the mating surface 4 is a conical surface, as the inner wall protrusion 21 is engaged with the outer wall groove 11, the inner wall groove 22 moves axially along the mating surface 4 on the inner wall protrusion 21, causing the nozzle inner wall 2 to undergo elastic deformation with an increased diameter. In addition, the multiple force-bearing surfaces 3 and multiple mating surfaces 4 are evenly distributed along the circumference of the circular plane, which creates circumferential pre-tension stress in the inner wall material, preventing the medium in the cooling groove 23 from exerting pressure on the nozzle inner wall 2 and causing inward deformation.

[0067] In a preferred embodiment of the present invention, when the inner wall groove 22 and the outer wall protrusion 12 just come into contact, the contact between the inner wall groove 22 and the outer wall protrusion 12 forms a plurality of first contact points, and the plurality of first contact points form a first circle perpendicular to the axis of the nozzle outer wall 1, the radius of the first circle is R0, and the axial clearance between the inner wall groove 22 and the outer wall protrusion 12 is T z0 The gap between the non-matching surface of the inner wall groove 22 and the non-matching surface of the outer wall protrusion 12 is T n0 , the matching length between the force-bearing surface 3 and the matching surface 4 is L0;

[0068] When the inner wall groove 22 and the outer wall protrusion 12 are engaged, the contact between the notch of the inner wall groove 22 and the outer wall protrusion 12 forms a plurality of second contact points, and the plurality of second contact points form a second circle perpendicular to the axis of the nozzle outer wall 1. The radius of the second circle is R1, and the axial clearance between the inner wall groove 22 and the outer wall protrusion 12 is T z1 The gap between the non-matching surface of the inner wall groove 22 and the non-matching surface of the outer wall protrusion 12 is T n1 , the matching length between the force-bearing surface 3 and the matching surface 4 is L1;

[0069] Among them, 0.2 mm≤T z1 <T z0 ≤0.6mm, 0.1 mm≤T n1 <T n0 ≤0.25mm, the slope of the mating surface 4 is α, 5°≤a≤20°, the circumferential prestress generated by the nozzle inner wall 2 is σ,

[0070] σ=(L1-L0)×E×Tanα / R0;

[0071] In the formula: E is the elastic modulus of the material of the nozzle inner wall 2.

[0072] like Figures 5-6As shown in the figure, as the inner wall groove 22 and the outer wall protrusion 12 are just in contact and fully engaged, the length of the mating surface 4 on the inner wall groove 22 is continuously increased, and the axial clearance between the inner wall groove 22 and the outer wall protrusion 12, and the clearance between the non-mating surface of the inner wall groove 22 and the non-mating surface of the outer wall protrusion 12 are continuously reduced. When 0.2 mm ≤ T z1 <T z0 ≤0.6mm, 0.1 mm≤T n1 <T n0 ≤0.25mm, which can make the assembly of the nozzle outer wall 1 and the nozzle inner wall 2 smoother.

[0073] In addition, the radius R0 of the first circle is smaller than the radius R1 of the second circle, and the slope of the mating surface 4 is α, 5°≤a≤20°. During assembly, the slope and axial displacement of the mating surface 4 cause the inner wall 2 of the nozzle to undergo elastic deformation with an increased diameter, thereby generating circumferential pre-tension stress on the inner wall 2 of the nozzle, thereby preventing the inner wall 2 of the nozzle from deforming inward under the pressure of the medium in the cooling groove 23, thereby improving the strength of the product.

[0074] In a preferred embodiment of the present invention, there are multiple inner wall protrusions 21, and the multiple inner wall protrusions 21 are arranged along the generatrix extension direction of the nozzle inner wall 2 to form an inner wall protrusion row;

[0075] There are at least two inner wall protrusion rows, and two adjacent inner wall protrusion rows are evenly distributed along the circumferential direction of the outer surface of the nozzle inner wall 2.

[0076] like Figure 1 、 3 -4, a plurality of inner wall protrusions 21 are arranged longitudinally along the busbar of the nozzle inner wall 2. The plurality of inner wall protrusions 21 may be arranged at equal intervals or at unequal intervals. The plurality of inner wall protrusions 21 on the same busbar form an inner wall protrusion row, and the plurality of inner wall protrusion rows are arranged at equal intervals on the outer surface of the nozzle inner wall 2. The inner wall protrusions 21 and the outer wall grooves 11 are in one-to-one correspondence.

[0077] In a preferred embodiment of the present invention, there are multiple inner wall protrusions 21, and the multiple inner wall protrusions 21 are evenly distributed along the outer circumference of the circular plane to form a protrusion annular array.

[0078] There are multiple raised annular arrays, and adjacent raised annular arrays are parallel to each other.

[0079] like Figure 1 、 3-4, a plurality of inner wall protrusions 21 are provided on the same circular plane of the nozzle inner wall 2 to form a protrusion annular array, and the plurality of inner wall protrusions 21 are evenly distributed along the outer circumference of the circular plane, so as to ensure that the nozzle inner wall 2 generates a uniform circumferential pre-tension force, and there are a plurality of protrusion annular arrays, and the plurality of protrusion annular arrays are distributed parallel to each other up and down along the outer surface of the nozzle inner wall 2, and the plurality of protrusion annular arrays can be arranged at equal intervals or at unequal intervals, and the inner wall protrusions 21 and the outer wall grooves 11 are in one-to-one correspondence, so that a circumferential pre-tension stress is generated on the nozzle inner wall 2.

[0080] In a preferred embodiment of the present invention, a plurality of cooling grooves 23 for circulating the cooling medium are provided along the generatrix direction of the nozzle inner wall 2, and the plurality of cooling grooves 23 are distributed at equal intervals.

[0081] like Figure 2 As shown, a plurality of cooling grooves 23 are provided along the generatrix direction of the nozzle inner wall 2 , and a cooling medium can flow through the cooling grooves 23 to cool the nozzle inner wall 2 , protect the nozzle inner wall 2 , and improve the performance of the nozzle inner wall 2 .

[0082] In a preferred embodiment of the present invention, the input end of the nozzle inner wall 2 is provided with a first inner wall L-shaped groove 24, the input end of the nozzle outer wall 1 is provided with a first outer wall L-shaped groove 13 corresponding to the first inner wall L-shaped groove 24, the output end of the nozzle inner wall 2 is provided with a second inner wall L-shaped groove 25, and the output end of the nozzle outer wall 1 is provided with a second outer wall L-shaped groove 14 corresponding to the second inner wall L-shaped groove 25.

[0083] Among them, the first inner wall L-shaped groove 24 is inserted into the first outer wall L-shaped groove 13, the second inner wall L-shaped groove 25 is inserted into the second outer wall L-shaped groove 14, and a sealing ring 5 is provided between the first inner wall L-shaped groove 24 and the first outer wall L-shaped groove 13, and between the second inner wall L-shaped groove 25 and the second outer wall L-shaped groove 14 to ensure the sealing between the nozzle outer wall 1 and the nozzle inner wall 2.

[0084] The first inner wall L-shaped groove 24 and the first outer wall L-shaped groove 13 , as well as the second inner wall L-shaped groove 25 and the second outer wall L-shaped groove 14 are connected by bolts 5 .

[0085] like Figures 1-4 As shown, the first inner wall L-shaped groove 24 cooperates with the first outer wall L-shaped groove 13, and the second inner wall L-shaped groove 25 cooperates with the second outer wall L-shaped groove 14, so that the end face of the nozzle outer wall 1 and the end face of the nozzle inner wall 2 can be connected. By providing a sealing ring 5 between the first inner wall L-shaped groove 24 and the first outer wall L-shaped groove 13, and between the second inner wall L-shaped groove 25 and the second outer wall L-shaped groove 14, and fixing them with bolts 5, the sealing of the end faces of the nozzle outer wall 1 and the nozzle inner wall 2 is ensured, and a detachable connection is achieved. When there is a problem with the nozzle outer wall 1 or the nozzle inner wall 2, it is convenient to replace it, and the structure is simple and the operation is convenient.

[0086] A method for manufacturing a hypersonic wind tunnel nozzle according to an embodiment of the present invention includes:

[0087] Processing the inner surface of the nozzle outer wall 1 to form an outer wall groove 11;

[0088] Processing the outer surface of the nozzle inner wall 2 to form an inner wall protrusion 21;

[0089] A plurality of cooling grooves 23 are provided on the outer surface of the nozzle inner wall 2 along the longitudinal direction;

[0090] Cleaning the surface of the nozzle inner wall 2 and the surface of the nozzle outer wall 1;

[0091] The nozzle inner wall 2 and the nozzle outer wall 1 are assembled to form a hypersonic wind tunnel nozzle.

[0092] The outer wall groove 11 is machined on the inner surface of the nozzle outer wall 1, and an outer wall protrusion 12 is provided on the outer wall of the outer wall groove 11 near the inner surface of the nozzle outer wall 1. The outer surface of the nozzle inner wall 2 is machined to form an inner wall protrusion 21, an inner wall groove 22, and a cooling groove 23. Impurities and oil stains on the surfaces of the nozzle inner wall 2 and the nozzle outer wall 1 are cleaned. The nozzle inner wall 2 is inserted into the nozzle outer wall 1, and the inner wall protrusion 21 and the outer wall groove 11, and the inner wall groove 22 and the outer wall protrusion 12 at corresponding positions are snap-fitted to complete the assembly of the nozzle inner wall 2 and the nozzle outer wall 1. The manufacturing method of the hypersonic wind tunnel nozzle of the present invention is simple to process, avoids the high-temperature process of brazing or diffusion bonding, ensures the original deformation strengthening state of the product, and has good deformation resistance.

[0093] In a preferred embodiment of the present invention, it also includes:

[0094] The end surface of the nozzle inner wall 2 is processed to form a first inner wall L-shaped groove 24 and a second inner wall L-shaped groove 25.

[0095] The end surface of the nozzle outer wall 1 is processed to form a first outer wall L-shaped groove 13 and a second outer wall L-shaped groove 14. Seal rings are provided between the first inner wall L-shaped groove 24 and the first outer wall L-shaped groove 13 and between the second inner wall L-shaped groove 25 and the second outer wall L-shaped groove 14. The end surface of the hypersonic wind tunnel nozzle is connected by bolts 5.

[0096] Among them, the end surface of the nozzle outer wall 1 and the end surface of the nozzle inner wall 2 are both left with a margin of 1mm to 2mm. After the end surface of the hypersonic wind tunnel nozzle is threaded, the margin of the end surface of the nozzle outer wall 1 and the end surface of the nozzle inner wall 2 is removed;

[0097] Perform performance tests on the assembled hypersonic wind tunnel nozzle.

[0098] like Figure 1As shown, the sealing ring is arranged between the first inner wall L-shaped groove 24 and the first outer wall L-shaped groove 13, and between the second inner wall L-shaped groove 25 and the second outer wall L-shaped groove 14, and is fixed by the bolt 5, so that the detachable connection of the outer wall 1 of the nozzle and the inner wall 2 of the nozzle is realized. When the inner wall 2 of the nozzle is worn after long-term use, the inner wall 2 of the nozzle can be replaced. The end surface of the outer wall 1 of the nozzle and the end surface of the inner wall 2 of the nozzle are left with a margin of 1-2 mm. After the end surface of the hypersonic wind tunnel nozzle is threadedly connected, the margin of the end surface of the outer wall 1 of the nozzle and the end surface of the inner wall 2 of the nozzle is removed. After the assembled hypersonic wind tunnel nozzle is tested for performance, including hydraulic strength test and air tightness test, the manufacturing of the hypersonic wind tunnel nozzle is completed.

[0099] In the embodiments of the present application, the term "a plurality of" refers to two or more, unless otherwise explicitly limited. The terms "mounting", "connecting", "fixing" and the like should be understood in a broad sense, for example, "connecting" can be fixed connection, can also be detachable connection, or integrally connected. For those skilled in the art, the specific meaning of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0100] In the description of the embodiments of the present application, it should be understood that the positions or position relationships indicated by the terms "upper", "lower" and the like are based on the positions or position relationships shown in the drawings, and are only for the convenience of describing the embodiments of the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or units referred to must have a specific direction, be constructed and operated in a specific position, and therefore cannot be understood as limiting the embodiments of the present application.

[0101] In the description of the present application, the terms "one embodiment", "one preferred embodiment" and the like mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In the present application, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0102] The above is only the preferred embodiment of the present application, and is not used to limit the embodiments of the present application. For those skilled in the art, the embodiments of the present application can have various modifications and changes. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the embodiments of the present application shall be included in the protection scope of the embodiments of the present application.

Claims

1. A hypersonic wind tunnel nozzle with a slot structure, characterized in that: include: nozzle outer wall (1); The nozzle inner wall (2) is sleeved inside the nozzle outer wall (1), wherein the outer profile of the nozzle inner wall (2) is provided with an inner wall protrusion (21), and the inner profile of the nozzle outer wall (1) is recessed outward to form an outer wall groove (11) corresponding to the inner wall protrusion (21), so that the nozzle inner wall (2) is clamped to the nozzle outer wall (1); An anti-deformation structure comprising a force-bearing portion and a matching portion, wherein the force-bearing portion is arranged on the inner wall (2) of the nozzle, and the matching portion is arranged on the outer wall (1) of the nozzle; A cooling medium channel is provided between the nozzle outer wall (1) and the nozzle inner wall (2), and the force-bearing portion and the matching portion cooperate to prevent the nozzle inner wall (2) from deforming inwards under the pressure of the cooling medium; The inner wall protrusion (21) is provided with an inner wall groove (22), and the bottom of the outer wall groove (11) is provided with an outer wall protrusion (12) corresponding to the inner wall groove (22), and the outer wall protrusion (12) is inserted into the inner wall groove (22), so that the nozzle inner wall (2) is clamped to the nozzle outer wall (1); The force-bearing portion includes a plurality of force-bearing surfaces (3), wherein the force-bearing surfaces (3) are arranged in the inner wall groove (22), and the groove wall of the inner wall groove (22) that contacts the outer wall protrusion (12) serves as the force-bearing surface (3); The mating portion comprises a plurality of mating surfaces (4), wherein the mating surfaces (4) are arc-shaped and are arranged on the outer wall protrusion (12), and the surface where the outer wall protrusion (12) and the inner wall groove (22) contact each other is the mating surface (4), and the mating surface (4) is arc-shaped to facilitate assembly of the inner wall groove (22) and the outer wall protrusion (12); A surface perpendicular to the axis of the nozzle inner wall (2) intersects with the outer surface of the nozzle outer wall (1) to form a circular plane, a plurality of the force-bearing surfaces (3) are evenly distributed along the circumference of the circular plane, a plurality of the matching surfaces (4) are evenly distributed along the circumference of the circular plane, and the force-bearing surfaces (3) and the matching surfaces (4) correspond one to one to generate circumferential prestress on the nozzle inner wall (2).

2. The hypersonic wind tunnel nozzle with a slot structure according to claim 1, characterized in that: When the inner wall groove (22) and the outer wall protrusion (12) just come into contact, the contact between the inner wall groove (22) and the outer wall protrusion (12) forms a plurality of first contact points, and the plurality of first contact points form a first circle perpendicular to the axis of the nozzle outer wall (1), the radius of the first circle is R0, and the axial clearance between the inner wall groove (22) and the outer wall protrusion (12) is T z0 The gap between the non-matching surface of the inner wall groove (22) and the non-matching surface of the outer wall protrusion (12) is T n0 , the matching length between the force-bearing surface (3) and the matching surface (4) is L0; When the inner wall groove (22) and the outer wall protrusion (12) are engaged, the contact between the notch of the inner wall groove (22) and the outer wall protrusion (12) forms a second contact point, and a plurality of second contact points form a second circle perpendicular to the axis of the nozzle outer wall (1), the radius of the second circle is R1, and the axial clearance between the inner wall groove (22) and the outer wall protrusion (12) is T z1 The gap between the non-matching surface of the inner wall groove (22) and the non-matching surface of the outer wall protrusion (12) is T n1 , the matching length between the force-bearing surface (3) and the matching surface (4) is L1; Among them, 0.2 mm≤T z1 <T z0 ≤0.6 mm, 0.1 mm≤T n1 <T n0 ≤0.25 mm, the slope of the mating surface (4) is α, 5°≤a≤20°, and the circumferential prestress generated by the inner wall (2) of the nozzle is σ, σ=(L1-L0)×E×Tanα / R0; Wherein: E is the elastic modulus of the material of the nozzle inner wall (2).

3. The hypersonic wind tunnel nozzle with a slot structure according to claim 1, characterized in that: There are a plurality of inner wall protrusions (21), and the plurality of inner wall protrusions (21) are arranged along the extension direction of the generatrix of the nozzle inner wall (2) to form an inner wall protrusion row; There are at least two inner wall protrusion rows, and two adjacent inner wall protrusion rows are evenly distributed along the circumferential direction of the outer surface of the nozzle inner wall (2).

4. The hypersonic wind tunnel nozzle with a slot structure according to claim 1, characterized in that: There are a plurality of inner wall protrusions (21), and the plurality of inner wall protrusions (21) are evenly distributed along the outer periphery of the circular plane to form a protrusion annular array; There are multiple raised annular arrays, and adjacent raised annular arrays are parallel to each other.

5. The hypersonic wind tunnel nozzle with a slot structure according to claim 1, characterized in that: A plurality of cooling grooves (23) for circulating and accommodating the cooling medium are provided along the generatrix direction of the nozzle inner wall (2), and the plurality of cooling grooves (23) are evenly distributed along the circumference of the nozzle inner wall (2).

6. The hypersonic wind tunnel nozzle with a slot structure according to claim 1, characterized in that: The input end of the nozzle inner wall (2) is provided with a first inner wall L-shaped groove (24), the input end of the nozzle outer wall (1) is provided with a first outer wall L-shaped groove (13) corresponding to the first inner wall L-shaped groove (24), the output end of the nozzle inner wall (2) is provided with a second inner wall L-shaped groove (25), and the output end of the nozzle outer wall (1) is provided with a second outer wall L-shaped groove (14) corresponding to the second inner wall L-shaped groove (25); The first inner wall L-shaped groove (24) is inserted into the first outer wall L-shaped groove (13), and the second inner wall L-shaped groove (25) is inserted into the second outer wall L-shaped groove (14). A sealing ring (5) is provided between the first inner wall L-shaped groove (24) and the first outer wall L-shaped groove (13), and between the second inner wall L-shaped groove (25) and the second outer wall L-shaped groove (14) to ensure the sealing between the nozzle outer wall (1) and the nozzle inner wall (2).

7. The hypersonic wind tunnel nozzle with a slot structure according to claim 6, characterized in that: The first inner wall L-shaped groove (24) and the first outer wall L-shaped groove (13), as well as the second inner wall L-shaped groove (25) and the second outer wall L-shaped groove (14) are connected via bolts (6).

8. A method for manufacturing a hypersonic wind tunnel nozzle having a slot structure according to any one of claims 1 to 7, characterized in that: include: Processing the inner surface of the nozzle outer wall (1) to form an outer wall groove (11); Processing the outer surface of the nozzle inner wall (2) to form an inner wall protrusion (21); A plurality of cooling grooves (23) are provided on the outer surface of the nozzle inner wall (2) along the longitudinal direction; Cleaning the surface of the nozzle inner wall (2) and the surface of the nozzle outer wall (1); The nozzle inner wall (2) and the nozzle outer wall (1) are assembled to form a hypersonic wind tunnel nozzle.

9. The method for manufacturing a hypersonic wind tunnel nozzle according to claim 8, characterized in that: Also includes: The end surface of the nozzle inner wall (2) is processed to form a first inner wall L-shaped groove (24) and a second inner wall L-shaped groove (25), The end face of the nozzle outer wall (1) is processed to form a first outer wall L-shaped groove (13) and a second outer wall L-shaped groove (14), and sealing rings are provided between the first inner wall L-shaped groove (24) and the first outer wall L-shaped groove (13), and between the second inner wall L-shaped groove (25) and the second outer wall L-shaped groove (14), so as to perform threaded connection on the end face of the hypersonic wind tunnel nozzle; Wherein, the end surface of the nozzle outer wall (1) and the end surface of the nozzle inner wall (2) both have a margin of 1 mm to 2 mm, and after the end surface of the hypersonic wind tunnel nozzle is threadedly connected, the margins of the end surface of the nozzle outer wall (1) and the end surface of the nozzle inner wall (2) are removed; The assembled hypersonic wind tunnel nozzle is subjected to a performance test.

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