Reverse thrust spray pipe and non-coaxial part integrated cementing assembly method thereof

Abstract

The invention provides an integrated cementing assembly method for a thrust reverser nozzle and non-coaxial parts of the thrust reverser nozzle. The integrated cementing assembly method comprises the following steps: S1, preparing a pre-processing carbon / carbon throat liner, a convergence ring and a nozzle shell; s2, the carbon / carbon throat liner before machining is installed on a turning tool, and the turning tool conducts axis adjustment on the carbon / carbon throat liner before machining; s3, turning the unprocessed carbon / carbon throat liner by the turning tool to form a random curved surface, and controlling the size of the random curved surface in the turning process to obtain a processed carbon / carbon throat liner; and S4, the processed carbon / carbon throat liner, the convergence ring and the spray pipe shell are subjected to integrated cementing assembly. The number of times of transferring the parts in the production process is reduced due to reduction of production procedures, the risk that the parts are damaged due to collision, abrasion and the like possibly occurring in the transferring process is reduced, meanwhile, the production efficiency is improved, and the stability of the product quality is guaranteed.

Description

Technical Field

[0001] This invention relates to the field of nozzle manufacturing technology, specifically to a method for integrally bonding and assembling a thrust reverser nozzle and its non-coaxial parts. Background Technology

[0002] A Chinese patent with publication number CN116398321B discloses an array-distributed vertical nozzle reverse thrust structure, including a compartment shell, a reverse thrust engine, connecting rods, and an ignition system. The reverse thrust engines are symmetrically arrayed circumferentially along the inner wall of the compartment shell and connected to the compartment shell via connecting rods and a flanged structure of the nozzle shell. The ignition system is a non-electrically driven detonation ignition system, including an igniter and detonating cords. The non-electrically driven detonation ignition system is connected to the compartment cable via the igniter end and connected to the reverse thrust engine one-to-one via multiple detonating cords. The axis of the nozzle assembly is perpendicular to the axis of the combustion chamber. An insulating ring is bonded to the inner wall of the combustion chamber shell, and a convergent ring is bonded to the interface of the combustion chamber shell. A throat liner is bonded to the inlet of the nozzle assembly.

[0003] In the manufacturing process of thrust reverser nozzles, the carbon-carbon throat liner and converging ring are critical non-coaxial components, and their assembly quality directly affects the nozzle's performance. The traditional assembly method involves first bonding the nozzle housing to the throat liner, then machining the conformal surface of the throat liner before bonding it to the converging ring. This traditional method has several problems. Because the throat liner and converging ring are non-coaxial parts, it not only increases production steps and costs but also raises the risk of component damage due to frequent handling, thus affecting production efficiency and product quality stability. Furthermore, it is difficult to guarantee the accuracy of the assembly clearance during bonding assembly, often requiring multiple machining operations to adjust the dimensions.

[0004] Therefore, how to solve the problem of integral adhesive bonding assembly of non-coaxial parts (throat liners, converging rings), reduce production processes, and lower transportation risks has become an urgent problem for those skilled in the art. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method for integrally bonding and assembling a thrust reverser nozzle and its non-coaxial parts.

[0006] A method for integral bonding and assembly of non-coaxial parts of a thrust reverser nozzle according to the present invention includes: Step S1: Prepare the carbon / carbon throat liner, convergent ring, and nozzle housing before machining; Step S2: Install the pre-processed carbon / carbon throat liner on the machining fixture, and the machining fixture adjusts the axis of the pre-processed carbon / carbon throat liner. Step S3: The machining fixture will machine the carbon / carbon throat liner into a conformal surface before machining, and control the size of the conformal surface during the machining process to obtain the machined carbon / carbon throat liner. Step S4: The processed carbon / carbon throat liner, the convergent ring, and the nozzle housing are integrally bonded and assembled.

[0007] Preferably, the side hole at the conical surface of the converging ring is coaxial with the processed carbon / carbon throat liner, and the outer circle of the converging ring is not coaxial with the processed carbon / carbon throat liner.

[0008] Preferably, the nozzle housing includes a large-end axis and a small-end axis, the large-end axis being coaxial with the converging ring, and the small-end axis being coaxial with the processed carbon / carbon throat liner.

[0009] Preferably, the machining fixture includes a spindle, locking screws, pressure blocks, a first measuring reference surface, a second measuring reference surface, and a carbon / carbon throat liner positioning surface; The specific steps for installing the pre-processed carbon / carbon throat liner on the machining fixture include: fitting the non-machined end face of the pre-processed carbon / carbon throat liner to the positioning surface of the carbon / carbon throat liner, and fixing the pre-processed carbon / carbon throat liner with locking screws and pressure blocks.

[0010] Preferably, the fit gap between the unprocessed end face of the carbon / carbon throat liner and the positioning surface of the carbon / carbon throat liner before processing is 0 to 0.05 mm.

[0011] Preferably, the central axis of the conformal surface of the processed carbon / carbon throat liner is aligned with the central axis of the main shaft.

[0012] Preferably, during the machining process of the carbon / carbon throat liner before machining, the height H of the conformal curved surface end face to the measuring reference surface of the tooling is measured and its tolerance range is controlled between 0 and 0.1 mm.

[0013] Preferably, the gap between the processed carbon / carbon throat liner and the converging ring is controlled to be 0-0.2 mm.

[0014] Preferably, step S4 specifically includes: Positioning marks are made on the non-bonded surfaces of the pre-assembled carbon / carbon throat liner and the converging ring according to the pre-installed state; the bonded surfaces of the nozzle housing 10 are sandblasted, and adhesive is applied to the bonded surfaces of the pre-assembled carbon / carbon throat liner and the converging ring; the bonding assembly is performed according to the positioning marks.

[0015] According to the present invention, a thrust reverser nozzle is manufactured by the integral bonding assembly method for non-coaxial parts of the thrust reverser nozzle described in any of the above-mentioned methods.

[0016] Compared with the prior art, the present invention has the following beneficial effects: This invention achieves the axis adjustment and conformal surface turning of the carbon-carbon throat liner in a single machining operation using a machining fixture, eliminating the need for multiple machining operations to adjust dimensions as in traditional methods, thus reducing machining steps. Precise machining ensures assembly clearance, eliminating the need for a separate sandblasting process to treat the part surface and adjust dimensions, further reducing production steps. By reducing the number of steps and the frequency of operation, the risk of transport risks is significantly reduced. The reduction in production steps also decreases the number of times parts are transported during production, lowering the risk of damage due to collisions, wear, etc., during transport, while simultaneously improving production efficiency and ensuring product quality stability. Attached Figure Description

[0017] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram illustrating the structure of the machining tooling of this invention. Figure 2 This is a schematic diagram illustrating the connection structure between the carbon / carbon throat liner and the machining tooling before processing, which is the main feature of this invention. Figure 3 This is a schematic diagram illustrating the connection structure between the processed carbon / carbon throat liner and the machining tooling of this invention. Figure 4 This is a schematic diagram illustrating the structure of the thrust reverser nozzle, which is the main feature of this invention.

[0018] The figure shows: 1. Spindle; 2. First measuring reference surface; 3. Locking screw; 4. Pressure block; 5. Second measuring reference surface; 6. Carbon / carbon throat liner positioning surface; 7. Machining fixture; 8. Carbon throat liner before machining; 9. Carbon throat liner after machining; 10. Nozzle housing; 11. Converging ring. Detailed Implementation

[0019] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0020] like Figure 1 As shown, a method for integral bonding and assembly of non-coaxial parts of a thrust reverser nozzle according to the present invention includes: Step S1: Prepare the carbon / carbon throat liner 8, convergent ring 11 and nozzle housing 10 before machining, ensuring that the basic dimensions of the parts meet the preliminary requirements and that there are no obvious defects.

[0021] Step S2: Install the pre-processed carbon / carbon throat liner 8 on the machining fixture 7. The machining fixture 7 achieves precise positioning of the pre-processed carbon / carbon throat liner 8 through a specific positioning structure. The machining fixture 7 adjusts the axis of the pre-processed carbon / carbon throat liner 8 to match the assembly position of the convergent ring 11.

[0022] In step S3, the machining fixture 7 machines the carbon / carbon throat liner 8 before machining to form a conformal curved surface, and controls the dimensions of the conformal curved surface during the machining process to ensure the assembly gap with the convergent ring 11, thus obtaining the machined carbon / carbon throat liner 9; specifically, the assembly gap between the machined carbon / carbon throat liner 9 and the convergent ring 11 is controlled within the range of 0 to 0.2 mm to ensure the quality of subsequent adhesive bonding assembly.

[0023] Step S4: The processed carbon / carbon throat liner 9, convergent ring 11 and nozzle housing 10 are integrally bonded and assembled, and then cured in a curing device at the specified temperature and time.

[0024] By using machining fixtures, the axis of the pre-processed carbon / carbon throat liner 8 is changed and a conformal curved surface is machined out. The corresponding dimensions are precisely controlled to ensure the assembly gap between the convergent ring 11 and the post-processed carbon / carbon throat liner 9, thus solving the problem of integral bonding assembly of the non-coaxial pre-processed carbon / carbon throat liner 8 and the convergent ring 11.

[0025] Specifically, this invention completes the axis adjustment and conformal surface turning of the carbon-carbon throat liner in one step using a machining fixture, eliminating the need for multiple machining operations to adjust dimensions as in traditional methods, thus reducing machining steps. Precise machining ensures assembly clearance, eliminating the need for a separate sandblasting process to treat the part surface and adjust dimensions, further reducing production steps. By reducing steps and lowering the frequency of operation, the risk of damage during transport is significantly reduced: fewer production steps mean fewer times the part is transported during production, reducing the risk of damage due to collisions, wear, etc., during transport, while also improving production efficiency and ensuring product quality stability.

[0026] In one feasible embodiment, the side hole at the conical surface of the converging ring 11 is coaxial with the machined carbon / carbon throat liner 9, while the outer circle of the converging ring 11 is not coaxial with the machined carbon / carbon throat liner 9.

[0027] In one feasible embodiment, the nozzle housing 10 includes a large-end axis and a small-end axis, the large-end axis being coaxial with the converging ring 11 and the small-end axis being coaxial with the processed carbon / carbon throat liner 9.

[0028] In one feasible embodiment, the machining fixture includes a spindle 1, a locking screw 3, a pressure block 4, a first measuring reference surface 2, a second measuring reference surface 5, and a carbon / carbon throat liner positioning surface 6, which clamps the spindle 1 onto the lathe.

[0029] The specific steps for installing the pre-processed carbon / carbon throat liner 8 on the machining fixture 7 include: fitting the non-machined end face of the pre-processed carbon / carbon throat liner 8 against the carbon / carbon throat liner positioning surface 6, and fixing the pre-processed carbon / carbon throat liner 8 with locking screws 3 and pressure blocks 4.

[0030] In one feasible embodiment, the fit gap between the unprocessed end face of the carbon / carbon throat liner 8 and the positioning surface 6 of the carbon / carbon throat liner before processing is 0 to 0.05 mm.

[0031] In one feasible implementation, the central axis of the conformal surface of the processed carbon / carbon throat liner 9 is aligned with the central axis of the spindle 1.

[0032] In one feasible implementation, during the turning process of the pre-machined carbon / carbon throat liner 8 by the machining fixture 7, the height H from the end face of the conformal curved surface to the measuring reference surface of the fixture is measured, and its tolerance range is controlled between 0 and 0.1 mm.

[0033] In one feasible embodiment, the assembly gap between the processed carbon / carbon throat liner 9 and the converging ring 11 is controlled to be 0 to 0.2 mm.

[0034] In one feasible implementation, step S4 specifically includes: making positioning marks on the non-bonded surfaces of the processed carbon / carbon throat liner 9 and the convergent ring 11 according to the pre-installed state; sandblasting the bonded surfaces of the nozzle housing 10; applying adhesive to the bonded surfaces of the processed carbon / carbon throat liner 9 and the convergent ring 11; and performing bonded assembly according to the positioning marks.

[0035] According to the present invention, a thrust reverser nozzle is manufactured by the integral bonding assembly method for non-coaxial parts of the thrust reverser nozzle described in any of the above-mentioned methods.

[0036] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0037] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for assembling a non-coaxial part of a reverse jet nozzle by adhesive bonding, characterized in that, The application relates to a method for integrally bonding a non-coaxial part of a reverse thrust nozzle. The method comprises the following steps: S1, preparing a pre-machining carbon / carbon throat insert (8), a convergent ring (11) and a nozzle shell (10); S2, mounting the pre-machining carbon / carbon throat insert (8) on a turning tool (7) for adjusting the axial line of the pre-machining carbon / carbon throat insert (8); S3, the turning tool (7) turns the pre-machining carbon / carbon throat insert (8) into a profiled curved surface, and controls the size of the profiled curved surface during the turning process to obtain a post-machining carbon / carbon throat insert (9); 2. The method of claim 1, wherein S4, integrally bonding the post-machining carbon / carbon throat insert (9), the convergent ring (11) and the nozzle shell (10).

3. The method of claim 1, wherein The side hole at the conical surface of the convergent ring (11) is coaxial with the post-machining carbon / carbon throat insert (9), and the outer circle of the convergent ring (11) is non-coaxial with the post-machining carbon / carbon throat insert (9).

4. The method of claim 1, wherein The nozzle shell (10) comprises a large-end axial line and a small-end axial line, the large-end axial line is coaxial with the convergent ring (11), and the small-end axial line is coaxial with the post-machining carbon / carbon throat insert (9). The turning tool comprises a main shaft (1), locking screws (3), a pressing block (4), a first measuring reference surface (2), a second measuring reference surface (5) and a carbon / carbon throat insert positioning surface (6); 5. The method of claim 4, wherein the non-coaxial parts of the thrust-reverser nozzle are integrally bonded by glue. 5 The mounting of the pre-machining carbon / carbon throat insert (8) on the turning tool (7) comprises the following steps: the non-machining end surface of the pre-machining carbon / carbon throat insert (8) is attached to the carbon / carbon throat insert positioning surface (6), and the pre-machining carbon / carbon throat insert (8) is fixed by the locking screws (3) and the pressing block (4).

6. The method of claim 4, wherein the non-coaxial parts of the thrust-reverser nozzle are integrally bonded by glue. The gap between the non-machining end surface of the pre-machining carbon / carbon throat insert (8) and the carbon / carbon throat insert positioning surface (6) is 0-0.05 mm.

7. The method of claim 1, wherein The central axis line of the profiled curved surface of the post-machining carbon / carbon throat insert (9) is consistent with the central axis line of the main shaft (1).

8. The method of claim 1, wherein, During the turning process of the turning tool (7) on the pre-machining carbon / carbon throat insert (8), the height H of the profiled curved surface end surface to the tool measuring reference surface is measured, and the tolerance range is controlled to be 0-0.1 mm.

9. The method of claim 1, wherein The gap between the post-machining carbon / carbon throat insert (9) and the convergent ring (11) is controlled to be 0-0.2 mm. S4 specifically comprises the following steps:

10. A retrorocket nozzle characterized in that, According to the pre-assembly state, a positioning mark is made on the non-bonding surface of the post-machining carbon / carbon throat insert (9) and the convergent ring (11); the bonding surface of the nozzle shell (10) is sandblasted, the bonding surface of the post-machining carbon / carbon throat insert (9) and the convergent ring (11) is smeared with adhesive; and the bonding assembly is carried out according to the positioning mark. The method is made by the method for integrally bonding a non-coaxial part of a reverse thrust nozzle according to any one of claims 1 to 9.

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