A double-layer casing test probe installation structure for an aero-engine and its assembly method

Abstract

This application belongs to the technical field of probe testing in the double-layer casing of aeroengines, and specifically relates to an installation structure and an assembly method of a test probe for the double-layer casing of an aeroengine. Through the design of small gaps between components, the sealing performance between the probe and the outer casing and the inner casing is ensured. In addition, with the clearance fit design between components, when the outer casing and the inner casing undergo relatively large deformations during the operation of the aeroengine, excessive extrusion stress on the probe is avoided, thus preventing damage to the probe. Furthermore, by designing the clearance fit between the probe and the test hole of the inner casing, the installation of the probe is facilitated, and it is not necessary for the test holes of the outer casing and the inner casing to be strictly aligned. Moreover, it can be adapted to probes of various model sizes for assembly.

Description

Technical Field

[0001] This application belongs to the technical field of probe testing in the double-layer casing of aero-engines, and particularly relates to an installation structure and an assembly method of a test probe for the double-layer casing of an aero-engine. Background Art

[0002] The double-layer casing structure of an aero-engine includes an outer casing and an inner casing disposed within the outer casing. During test runs, the temperature and pressure inside the inner casing are mostly measured using probes. For this purpose, test holes are drilled in the outer casing and the inner casing. The probe tip is installed by passing through the test hole in the outer casing and the test hole in the inner casing in sequence. To ensure the sealing between the probe and the outer casing and the inner casing, prevent the leakage of high-temperature gas inside the inner casing, and prevent the leakage of cooling gas between the inner casing and the outer casing, the test holes in the outer casing and the inner casing are designed to have as small a size as possible to reduce the gap between the probe and the outer casing and the inner casing. However, this technical solution has the following drawbacks:

[0003] 1) The probe is a rigid rod, and the test holes in the outer casing and the inner casing need to be strictly aligned for installation. Otherwise, large contact stresses are likely to be generated during the probe installation process, resulting in damage to the probe. However, the current technology makes it difficult to achieve strict alignment of the test holes in the outer casing and the inner casing.

[0004] 2) There is no clearance for movement between the probe and the test holes in the outer casing and the inner casing. When the outer casing and the inner casing are operating in an aero-engine, they are very likely to undergo relatively large deformations, generating large extrusion stresses on the probe and causing damage to the probe.

[0005] 3) The test holes in the outer casing and the inner casing can only accommodate probes of specific model sizes, and their versatility is poor.

[0006] In view of the existence of the above technical drawbacks, this application is proposed.

[0007] It should be noted that the disclosure of the above background art content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this application. Without clear evidence indicating that the above content was publicly available on the filing date of this application, the above background art should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0008] The purpose of this application is to provide an installation structure and an assembly method of a test probe for the double-layer casing of an aero-engine to overcome or mitigate at least one aspect of the known technical drawbacks.

[0009] The technical solution of this application is as follows:

[0010] On the one hand, a test probe mounting structure for a double-layer casing of an aero-engine is provided, including:

[0011] An outer casing, on which an outer casing test hole is opened;

[0012] An inner casing, which is arranged inside the outer casing and has an inner casing test hole opened thereon;

[0013] An adapter tube, which is arranged between the outer casing and the inner casing, and one end of the outer wall has an annular adapter edge;

[0014] A crimping tube, which is arranged between the outer casing and the inner casing, one end is connected to the inner casing, and the inner wall of the other end has an annular crimping edge; the annular crimping edge presses the annular adapter edge on the inner casing, and there is a small clearance fit therebetween; there is a clearance fit between the crimping tube and the annular adapter edge;

[0015] A support tube, one end of which passes through the outer casing test hole and extends between the outer casing and the inner casing, the inner wall of this end has an inner annular support edge, and the outer wall of the other end has an outer annular support edge; the inner annular support edge surrounds the adapter tube and has a clearance fit with the adapter tube; the outer annular support edge is connected to the outer casing;

[0016] A sliding tube, which is arranged inside the support tube, has a clearance fit with the support tube, is sleeved on the other end of the adapter tube, and has a small clearance fit with this end of the adapter tube;

[0017] An intermediate tube, one end of which extends into the support tube, this end presses the sliding tube on the inner annular support edge, and there is a small clearance fit therebetween, and the outer wall of the other end has an intermediate annular connection edge; the intermediate annular connection edge is connected to the outer annular support edge;

[0018] A probe, the head of which sequentially passes through the intermediate tube, the sliding tube, the adapter tube, and the inner casing test hole and extends into the inner casing, has a clearance fit with the inner casing test hole, and has a small clearance fit with the intermediate tube, and the outer wall has an outer annular connection edge; the outer annular connection edge is connected to the intermediate annular connection edge and has a small clearance fit with the intermediate annular connection edge.

[0019] According to at least one embodiment of the present application, in the above test probe mounting structure for a double-layer casing of an aero-engine, the end of the adapter tube extending into the sliding tube is spherical.

[0020] According to at least one embodiment of the present application, in the above test probe mounting structure for a double-layer casing of an aero-engine, the outer wall of the end of the intermediate tube extending into the support tube has an annular protrusion, and the annular protrusion abuts inside the support tube.

[0021] According to at least one embodiment of the present application, in the above test probe mounting structure for a double-layer casing of an aero-engine, the crimping tube is connected to the annular boss of the inner casing by bolts;

[0022] The outer annular support edge, together with the middle annular connection edge and the outer annular connection edge, is bolted to the outer casing.

[0023] On the other hand, a method for assembling an installation structure of a double-layer casing test probe for an aero-engine is provided, including:

[0024] Assemble the adapter barrel and the crimping barrel onto the inner casing;

[0025] Assemble the outer casing outside the inner casing;

[0026] Assemble the support barrel onto the outer casing;

[0027] Assemble the sliding barrel into the support barrel and cooperate with the adapter barrel;

[0028] Assemble the middle barrel into the support barrel, cooperate with the sliding barrel, and assemble it onto the outer casing;

[0029] Insert the probe head into the inner casing and assemble it onto the outer casing. Description of the Drawings

[0030] Figure 1 FIG. is a schematic diagram of an installation structure of a double-layer casing test probe for an aero-engine provided by an embodiment of the present application;

[0031] Figure 2 FIG. is a schematic diagram of a small clearance part in the installation structure of a double-layer casing test probe for an aero-engine provided by an embodiment of the present application;

[0032] Figure 3 FIG. is a schematic diagram of the adapter barrel provided by an embodiment of the present application;

[0033] Wherein:

[0034] 1 - outer casing; 2 - inner casing; 3 - adapter barrel; 4 - crimping barrel; 5 - support barrel; 6 - sliding barrel; 7 - middle barrel; 8 - probe.

[0035] For better illustration of this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product. In addition, the drawings are only for illustrative purposes and should not be construed as a limitation to the present application. Detailed Embodiments

[0036] To make the technical solution and its advantages of this application clearer, the following will further describe the technical solution of this application clearly and completely in conjunction with the accompanying drawings. It can be understood that the specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application rather than limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0037] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words indicating directions such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of this application are only used to represent relative directions or positional relationships, rather than implying that the device or element must have a specific orientation, be constructed and operated in a specific orientation. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. Therefore, it cannot be understood as a limitation to this application. The terms "first", "second", "third" and similar terms used in the description of this application are only for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The similar words such as "a", "one" or "the" used in the description of this application should not be understood as an absolute limitation on the quantity, but should be understood as having at least one. The similar words such as "including" or "comprising" used in the description of this application are intended to indicate that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0038] In addition, it should also be noted that unless otherwise clearly specified and limited, the similar words such as "installed", "connected", "joined" used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and can also be the communication inside two elements. Those skilled in the art can understand its specific meaning in this application according to the specific situation.

[0039] The following will further describe this application in detail Figures 1 to 3 in conjunction with the accompanying drawings.

[0040] On the one hand, a mounting structure for a double-layer casing test probe of an aeroengine is provided, as Figure 1 shown, including:

[0041] An outer casing 1, on which an outer casing test hole is provided;

[0042] The inner casing 2 is arranged inside the outer casing 1, and an inner casing test hole is formed thereon;

[0043] The adapter tube 3 is arranged between the outer casing 1 and the inner casing 2, and an annular adapter edge is provided on the outer wall of one end;

[0044] The crimping tube 4 is arranged between the outer casing 1 and the inner casing 2, one end is connected to the inner casing 2, and an annular crimping edge is provided on the inner wall of the other end; the annular crimping edge presses the annular adapter edge on the inner casing 2, and there is a small clearance fit therebetween; there is a clearance fit between the crimping tube 4 and the annular adapter edge;

[0045] The support tube 5 has one end extending through the outer casing test hole into the space between the outer casing 1 and the inner casing 2. An inner annular support edge is provided on the inner wall of this end, and an outer annular support edge is provided on the outer wall of the other end; the inner annular support edge surrounds the adapter tube 3, and there is a clearance fit between them; the outer annular support edge is connected to the outer casing 1;

[0046] The sliding tube 6 is arranged inside the support tube 5, has a clearance fit with the support tube 5, is sleeved on the other end of the adapter tube 3, and has a small clearance fit with this end of the adapter tube 3;

[0047] The intermediate tube 7 has one end extending into the support tube 5. This end presses the sliding tube 6 against the inner annular support edge, and there is a small clearance fit therebetween. An intermediate annular connection edge is provided on the outer wall of the other end; the intermediate annular connection edge is connected to the outer annular support edge;

[0048] The probe 8 has its head sequentially passing through the intermediate tube 7, the sliding tube 6, the adapter tube 3, and the inner casing test hole and extending into the inner casing 2, has a clearance fit with the inner casing test hole, and has a small clearance fit with the intermediate tube 7. An outer annular connection edge is provided on the outer wall; the outer annular connection edge is connected to the intermediate annular connection edge and has a small clearance fit with the intermediate annular connection edge.

[0049] For the installation structure of the double-layer casing test probe of the aero-engine disclosed in the above embodiments, those skilled in the art can understand that its sealing performance between the probe 8 and the outer casing 1 and the inner casing 2 is ensured through the small clearance design between components, such as Figure 3As shown, with the clearance fit design between the mating components, when relatively large deformations occur between the outer casing 1 and the inner casing 2 of the aero-engine, excessive extrusion stress on the probe 8 is avoided, preventing damage to the probe 8. For example, when relatively large radial deformations occur between the outer casing 1 and the inner casing 2, the extrusion stress on the probe 8 can be released through the sliding between the adapter tube 3 and the sliding tube 6, protecting the probe 8 from damage. When relatively large axial or circumferential deformations occur between the outer casing 1 and the inner casing 2, the extrusion stress on the probe 8 can be released through the translational movement of the probe 8 during the inner casing test, the translational movement of the annular adapter edge in the crimping tube 4, and the translational movement of the sliding tube 6 between the support tubes 5, protecting the probe 8 from damage. In addition, the clearance fit design between the probe 8 and the inner casing test hole facilitates the installation of the probe 8, does not require strict alignment of the outer casing test hole and the inner casing test hole, and can accommodate probes 8 of various model sizes for assembly.

[0050] In some alternative embodiments, in the above-described aero-engine double-casing test probe mounting structure, one end of the adapter tube 3 extending into the sliding tube 6 is spherical, as Figure 2 shown, with a small clearance fit between the arc surface and the sliding tube 6 to reduce the friction force during sliding relative to the sliding tube 6.

[0051] In some alternative embodiments, in the above-described aero-engine double-casing test probe mounting structure, the outer wall of one end of the intermediate tube 7 extending into the support tube 5 has an annular protrusion that abuts against the inside of the support tube 5.

[0052] In some alternative embodiments, in the above-described aero-engine double-casing test probe mounting structure, the crimping tube 4 is connected to the annular boss of the inner casing 2 by bolts;

[0053] The outer annular support edge, together with the intermediate annular connection edge and the outer annular connection edge, is connected to the outer casing 1 by bolts.

[0054] On the other hand, a method for assembling an aero-engine double-casing test probe mounting structure is provided, including:

[0055] Assembling the adapter tube 3 and the crimping tube 4 onto the inner casing 2;

[0056] Assembling the outer casing 1 outside the inner casing 2;

[0057] Assembling the support tube 5 onto the outer casing 1;

[0058] Assembling the sliding tube 6 into the support tube 5 and mating it with the adapter tube 3;

[0059] Assembling the intermediate tube 7 into the support tube 5, mating it with the sliding tube 6, and assembling it onto the outer casing 1;

[0060] Insert the head of the probe 8 into the inner casing 2 and assemble it onto the outer casing 1.

[0061] Regarding the assembly method of the test probe mounting structure for the double-layer casing of an aero-engine disclosed in the above embodiments, which is used to realize the assembly of the test probe mounting structure for the double-layer casing of an aero-engine disclosed in the above embodiments, the description is relatively simple. For specific relevant parts, reference can be made to the relevant descriptions in the part of the test probe mounting structure for the double-layer casing of an aero-engine. Its technical effects can also be referred to the technical effects of the relevant parts of the test probe mounting structure for the double-layer casing of an aero-engine, and will not be elaborated here.

[0062] The various embodiments in the specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. For the same and similar parts among the various embodiments, reference can be made to each other.

[0063] So far, the technical solutions of the present application have been described in conjunction with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present application.

Claims

1. A double-layer casing test probe installation structure for an aero-engine, characterized in that, Comprising: An outer casing (1) with an outer casing test hole provided thereon; An inner casing (2) disposed within the outer casing (1) and having an inner casing test hole provided thereon; An adapter tube (3) disposed between the outer casing (1) and the inner casing (2), with an annular adapter edge on the outer wall of one end; A crimping tube (4) disposed between the outer casing (1) and the inner casing (2), with one end connected to the inner casing (2) and an annular crimping edge on the inner wall of the other end; the annular crimping edge presses the annular adapter edge against the inner casing (2), with a small clearance fit therebetween; there is a clearance fit between the crimping tube (4) and the annular adapter edge; A support tube (5) with one end passing through the outer casing test hole and extending between the outer casing (1) and the inner casing (2), having an inner annular support edge on the inner wall of this end and an outer annular support edge on the outer wall of the other end; the inner annular support edge surrounds the adapter tube (3) with a clearance fit therebetween; the outer annular support edge is connected to the outer casing (1); A sliding tube (6) disposed within the support tube (5), with a clearance fit with the support tube (5), sleeved on the other end of the adapter tube (3), and having a small clearance fit with this end of the adapter tube (3); An intermediate tube (7) with one end extending into the support tube (5), pressing the sliding tube (6) against the inner annular support edge at this end with a small clearance fit therebetween, and having an intermediate annular connection edge on the outer wall of the other end; the intermediate annular connection edge is connected to the outer annular support edge; A probe (8) whose head sequentially passes through the intermediate tube (7), the sliding tube (6), the adapter tube (3), and the inner casing test hole and extends into the inner casing (2), with a clearance fit with the inner casing test hole, a small clearance fit with the intermediate tube (7), and having an outer annular connection edge on the outer wall; the outer annular connection edge is connected to the intermediate annular connection edge with a small clearance fit therebetween.

2. The installation structure of the double-layer casing test probe for an aero-engine according to claim 1, wherein: The end of the adapter tube (3) extending into the sliding tube (6) is spherical.

3. The installation structure of the double-layer casing test probe for an aero-engine according to claim 1, wherein: The outer wall of the end of the intermediate tube (7) extending into the support tube (5) has an annular protrusion that abuts against the inside of the support tube (5).

4. The installation structure of the double-layer casing test probe for an aero-engine according to claim 1, wherein: The crimping tube (4) is connected to the annular boss of the inner casing (2) by bolts; The outer annular support edge together with the intermediate annular connection edge and the outer annular connection edge are connected to the outer casing (1) by bolts.

5. An assembly method for the test probe installation structure of a double-layer casing of an aero-engine, which is used to realize the assembly of the test probe installation structure of the double-layer casing of the aero-engine described in claim 4, is characterized in that, Comprising: Assembling the adapter tube (3) and the crimping tube (4) onto the inner casing (2); Assembling the outer casing (1) outside the inner casing (2); Assembling the support tube (5) onto the outer casing (1); Assembling the sliding tube (6) into the support tube (5) and mating it with the adapter tube (3); Assembling the intermediate tube (7) into the support tube (5), mating it with the sliding tube (6), and assembling it onto the outer casing (1); Inserting the head of the probe (8) into the inner casing (2) and assembling it onto the outer casing (1).

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