CN116124438A - Double-layer case test probe mounting structure of aero-engine and assembly method thereof - Google Patents
Double-layer case test probe mounting structure of aero-engine and assembly method thereof Download PDFInfo
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- CN116124438A CN116124438A CN202310157840.8A CN202310157840A CN116124438A CN 116124438 A CN116124438 A CN 116124438A CN 202310157840 A CN202310157840 A CN 202310157840A CN 116124438 A CN116124438 A CN 116124438A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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Abstract
The utility model belongs to the technical field of the test of probe in the double-deck receiver of aeroengine, concretely relates to double-deck receiver of aeroengine test probe mounting structure and assembly method thereof, its leakproofness between probe and outer receiver, the interior receiver is guaranteed through the design of little clearance between the part, and the clearance fit design between the cooperation part, avoid outer receiver, interior receiver when aeroengine takes place relative great deformation, produce great extrusion stress to the probe, cause the damage to the probe, in addition, design probe and interior receiver test hole clearance fit, can be convenient for install the probe, and need not outer receiver test hole, interior receiver test hole are strictly aligned, and the probe of adaptable multiple model size is assembled.
Description
Technical Field
The application belongs to the technical field of probe testing in an aeroengine double-layer casing, and particularly relates to an aeroengine double-layer casing test probe mounting structure and an assembly method thereof.
Background
The utility model provides an aeroengine double-deck cartridge receiver structure, including outer cartridge receiver, the cartridge receiver that sets up in outer cartridge receiver, when carrying out experimental test, the test of temperature, pressure in the interior cartridge receiver is carried out with the probe in most, for this, set up outer cartridge receiver test hole on outer cartridge receiver, set up interior cartridge receiver test hole on interior cartridge receiver, pass outer cartridge receiver test hole in proper order with the probe head, interior cartridge receiver test hole installs, in order to guarantee the leakproofness between probe and outer cartridge receiver, interior cartridge receiver, prevent the high temperature gas leakage in the interior cartridge receiver, and prevent the cooling gas leakage between interior cartridge receiver, the outer cartridge receiver of many designs, interior cartridge receiver test hole has as little size as possible, in order to reduce the clearance between probe and outer cartridge receiver, interior cartridge receiver, this kind of technical scheme has following defect:
1) The probes are rigid rods, the outer casing test holes and the inner casing test holes are required to be strictly aligned, otherwise, larger contact stress is easy to generate in the process of installing the probes, the probes are damaged, and the outer casing test holes and the inner casing test holes are difficult to be strictly aligned in the current process;
2) The probe lacks a movable allowance between the outer casing test hole and the inner casing test hole, and the outer casing and the inner casing are extremely easy to generate relatively large deformation and generate large extrusion stress with the probe when the aeroengine works, so that the probe is damaged;
3) The outer casing test hole and the inner casing test hole can only be matched with probes of specific model sizes, and the universal shape is poor.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
The invention aims to provide an aeroengine double-layer casing test probe mounting structure and an assembly method thereof, which overcome or alleviate the technical defects of at least one aspect of the prior art.
The technical scheme of the application is as follows:
in one aspect, an aeroengine double-layer casing test probe mounting structure is provided, including:
the outer casing is provided with an outer casing test hole;
the inner casing is arranged in the outer casing, and an inner casing test hole is formed in the inner casing;
the switching cylinder is arranged between the outer casing and the inner casing, and the outer wall of one end of the switching cylinder is provided with an annular switching edge;
the crimping barrel is arranged between the outer casing and the inner casing, one end of the crimping barrel is connected to the inner casing, and the inner wall of the other end of the crimping barrel is provided with an annular crimping edge; the annular pressure joint edge presses the annular pressure joint edge on the inner casing, and the annular pressure joint edge is in small clearance fit with the inner casing; the compression joint cylinder is in clearance fit with the annular transfer edge;
one end of the supporting cylinder penetrates through the outer casing testing hole and extends between the outer casing and the inner casing, the inner wall of the supporting cylinder is provided with an inner annular supporting edge, and the outer wall of the supporting cylinder is provided with an outer annular supporting edge; the inner annular supporting edge surrounds the switching cylinder and is in clearance fit with the switching cylinder; the outer annular supporting edge is connected to the outer casing;
the sliding cylinder is arranged in the supporting cylinder and is in clearance fit with the supporting cylinder, and is sleeved at the other end of the switching cylinder and is in small clearance fit with the end of the switching cylinder;
one end of the middle cylinder extends into the supporting cylinder, the end presses the sliding cylinder on the inner annular supporting edge, the sliding cylinder is in small clearance fit with the inner annular supporting edge, and the outer wall of the other end of the middle cylinder is provided with a middle annular connecting edge; the middle annular connecting edge is connected with the outer annular supporting edge;
the head of the probe sequentially passes through the middle cylinder, the sliding cylinder, the switching cylinder and the inner casing test hole to extend into the inner casing, is in clearance fit with the inner casing test hole, is in clearance fit with the middle cylinder and is in small clearance fit with the middle cylinder, and the outer wall is provided with an outer annular connecting edge; the outer annular connecting edge is connected to the middle annular connecting edge and is in small clearance fit with the middle annular connecting edge.
According to at least one embodiment of the application, in the double-layer casing test probe mounting structure of the aeroengine, one end of the adapter cylinder, which extends into the sliding cylinder, is spherical.
According to at least one embodiment of the application, in the double-layer casing test probe mounting structure of the aeroengine, the outer wall of one end of the middle cylinder extending into the supporting cylinder is provided with an annular bulge, and the annular bulge is abutted in the supporting cylinder.
According to at least one embodiment of the present application, in the above-mentioned dual-layer casing test probe mounting structure of an aeroengine, the crimp barrel is connected to the annular boss of the inner casing by a bolt;
the outer annular supporting edge, the middle annular connecting edge and the outer annular connecting edge are connected to the outer casing through bolts.
On the other hand, the assembling method of the double-layer case test probe mounting structure of the aeroengine comprises the following steps:
assembling the switching cylinder and the crimping cylinder on the inner casing;
assembling an outer casing outside the inner casing;
assembling the support cylinder to the outer casing;
assembling the sliding cylinder into the supporting cylinder and matching with the switching cylinder;
the middle cylinder is assembled into the supporting cylinder and is matched with the sliding cylinder to be assembled on the outer casing;
the probe head is extended into the inner casing and fitted to the outer casing.
Drawings
Fig. 1 is a schematic view of an aeroengine double-layer casing test probe mounting structure provided in an embodiment of the present application;
fig. 2 is a schematic diagram of a small gap part in an aeroengine double-layer casing test probe mounting structure according to an embodiment of the present application;
FIG. 3 is a schematic view of an adapter provided in an embodiment of the present application;
wherein:
1-an outer casing; 2-an inner casing; 3-an adapter cylinder; 4-crimping a cylinder; 5-a support cylinder; 6-a sliding cylinder; 7-an intermediate cylinder; 8-probe.
For better illustration of the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the actual product size, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present application.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below in conjunction with fig. 1-3.
In one aspect, an aeroengine double-layer casing test probe mounting structure is provided, as shown in fig. 1, including:
the outer casing 1 is provided with an outer casing test hole;
the inner casing 2 is arranged in the outer casing 1, and an inner casing test hole is formed in the inner casing 2;
the switching cylinder 3 is arranged between the outer casing 1 and the inner casing 2, and the outer wall of one end is provided with an annular switching edge;
the compression joint cylinder 4 is arranged between the outer casing 1 and the inner casing 2, one end of the compression joint cylinder is connected to the inner casing 2, and the inner wall of the other end of the compression joint cylinder is provided with an annular compression joint edge; the annular pressure joint edge presses the annular pressure joint edge on the inner casing 2, and the annular pressure joint edge is in small clearance fit with the inner casing 2; the compression joint cylinder 4 is in clearance fit with the annular transfer edge;
one end of the supporting cylinder 5 penetrates through the outer casing test hole and extends between the outer casing 1 and the inner casing 2, the inner wall of the supporting cylinder is provided with an inner annular supporting edge, and the outer wall of the supporting cylinder is provided with an outer annular supporting edge; the inner annular supporting edge surrounds the switching cylinder 3 and is in clearance fit with the switching cylinder 3; the outer annular supporting edge is connected to the outer casing 1;
the sliding cylinder 6 is arranged in the supporting cylinder 5 and is in clearance fit with the supporting cylinder 5, sleeved at the other end of the switching cylinder 3 and is in small clearance fit with the end of the switching cylinder 3;
an intermediate cylinder 7, one end of which extends into the support cylinder 5, presses the sliding cylinder 6 against the inner annular support edge with a small clearance fit therebetween, and the other end outer wall has an intermediate annular connecting edge; the middle annular connecting edge is connected with the outer annular supporting edge;
the head of the probe 8 sequentially passes through the middle cylinder 7, the sliding cylinder 6, the adapter cylinder 3 and the inner casing test hole to extend into the inner casing 2, is in clearance fit with the inner casing test hole, is in clearance fit with the middle cylinder 7 and is in small clearance fit with the middle cylinder 7, and the outer wall is provided with an outer annular connecting edge; the outer annular connecting edge is connected to the middle annular connecting edge and is in small clearance fit with the middle annular connecting edge.
For the double-layer casing test probe mounting structure of the aeroengine disclosed in the above embodiment, it can be understood by those skilled in the art that the tightness between the probe 8 and the outer casing 1 and the inner casing 2 is ensured by the small gap design between the components, as shown in fig. 3, and the gap fit design between the matched components avoids the larger extrusion stress on the probe 8 when the outer casing 1 and the inner casing 2 are relatively deformed in the aeroengine, for example, when the larger radial deformation occurs between the outer casing 1 and the inner casing 2, the extrusion stress on the probe 8 can be released by the sliding between the adapter sleeve 3 and the sliding sleeve 6, the probe 8 is protected from being damaged by the translational stress of the outer casing 1 and the inner casing 2, when the larger axial or circumferential deformation occurs between the outer casing 1 and the inner casing 2, the translational stress of the probe 8 can be realized by the translational stress of the annular adapter edge in the crimping sleeve 4, and the sliding sleeve 6 between the supporting sleeves 5, the probe 8 is released, for example, the probe 8 can be tightly protected from being matched with the test hole 8, and the test hole can be tightly matched with the test hole, and the test hole is not required for the probe 8.
In some alternative embodiments, in the above-mentioned dual-layer casing test probe mounting structure for an aeroengine, one end of the adapter cylinder 3 extending into the sliding cylinder 6 is spherical, as shown in fig. 2, and the friction force between the adapter cylinder and the sliding cylinder 6 is reduced by small clearance fit between the arc surface and the sliding cylinder 6.
In some alternative embodiments, in the above-mentioned double-layer casing test probe mounting structure for an aeroengine, the outer wall of the end of the intermediate barrel 7 extending into the support barrel 5 has an annular protrusion, and the annular protrusion abuts against the support barrel 5.
In some alternative embodiments, in the above-mentioned double-layer casing test probe mounting structure of the aeroengine, the crimp barrel 4 is connected to the annular boss of the inner casing 2 by bolts;
the outer annular supporting edge, the middle annular connecting edge and the outer annular connecting edge are connected to the outer casing 1 through bolts.
On the other hand, the assembling method of the double-layer case test probe mounting structure of the aeroengine comprises the following steps:
assembling the adapter cylinder 3 and the crimping cylinder 4 on the inner casing 1;
an outer casing 1 is assembled outside the inner casing 1;
assembling the support cylinder 5 to the outer casing 1;
fitting the sliding cylinder 6 into the supporting cylinder 5 and cooperating with the adapter cylinder 3;
the middle cylinder 7 is assembled into the supporting cylinder 5 and is matched with the sliding cylinder 6 to be assembled on the outer casing 1;
the probe 8 is inserted with its head into the inner casing 2 and fitted to the outer casing 1.
For the method for assembling the test probe mounting structure of the double-layer casing of the aeroengine disclosed in the above embodiment, which is used for realizing the assembly of the test probe mounting structure of the double-layer casing of the aeroengine disclosed in the above embodiment, the description is simpler, the specific relevant parts can be referred to the relevant description of the test probe mounting structure part of the double-layer casing of the aeroengine, the technical effects of the relevant parts of the test probe mounting structure of the double-layer casing of the aeroengine can be referred to, and the description is omitted herein.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (5)
1. An aeroengine double-deck receiver test probe mounting structure, characterized by comprising:
the outer casing (1) is provided with an outer casing test hole;
the inner casing (2) is arranged in the outer casing (1), and an inner casing test hole is formed in the inner casing;
the switching cylinder (3) is arranged between the outer casing (1) and the inner casing (2), and the outer wall of one end is provided with an annular switching edge;
the crimping cylinder (4) is arranged between the outer casing (1) and the inner casing (2), one end of the crimping cylinder is connected to the inner casing (2), and the inner wall of the other end of the crimping cylinder is provided with an annular crimping edge; the annular pressure joint edge presses the annular pressure joint edge on the inner casing (2) with small clearance fit therebetween; the compression joint cylinder (4) is in clearance fit with the annular transfer edge;
one end of the supporting cylinder (5) penetrates through the outer casing test hole and extends between the outer casing (1) and the inner casing (2), the inner wall of the supporting cylinder is provided with an inner annular supporting edge, and the outer wall of the supporting cylinder is provided with an outer annular supporting edge; the inner annular supporting edge surrounds the switching cylinder (3) and is in clearance fit with the switching cylinder (3); the outer annular supporting edge is connected to the outer casing (1);
the sliding cylinder (6) is arranged in the supporting cylinder (5) and is in clearance fit with the supporting cylinder (5), sleeved at the other end of the switching cylinder (3) and is in small clearance fit with the end of the switching cylinder (3);
an intermediate cylinder (7), one end of which extends into the support cylinder (5), presses the sliding cylinder (6) against the inner annular support edge with a small clearance fit therebetween, and the other end of which has an intermediate annular connecting edge on the outer wall; the middle annular connecting edge is connected with the outer annular supporting edge;
the head of the probe (8) sequentially passes through the middle cylinder (7), the sliding cylinder (6), the adapter cylinder (3) and the inner casing test hole to extend into the inner casing (2), is in clearance fit with the inner casing test hole, is in clearance fit with the middle cylinder (7) and is in small clearance fit with the middle cylinder (7), and the outer wall is provided with an outer annular connecting edge; the outer annular connecting edge is connected to the middle annular connecting edge and is in small clearance fit with the middle annular connecting edge.
2. The aircraft engine double-layer case test probe mounting structure of claim 1, wherein,
one end of the adapter cylinder (3) extending into the sliding cylinder (6) is spherical.
3. The aircraft engine double-layer case test probe mounting structure of claim 1, wherein,
the outer wall of one end of the middle cylinder (7) extending into the supporting cylinder (5) is provided with an annular bulge, and the annular bulge is propped against the supporting cylinder (5).
4. The aircraft engine double-layer case test probe mounting structure of claim 1, wherein,
the compression joint cylinder (4) is connected to the annular boss of the inner casing (2) through a bolt;
the outer annular supporting edge, the middle annular connecting edge and the outer annular connecting edge are connected to the outer casing (1) through bolts.
5. An assembly method of an aircraft engine double-layer casing test probe mounting structure is characterized by comprising the following steps:
assembling the adapter cylinder (3) and the crimping cylinder (4) on the inner casing (1);
an outer casing (1) is assembled outside the inner casing (1);
assembling the support cylinder (5) to the outer casing (1);
assembling the sliding cylinder (6) into the supporting cylinder (5) and matching with the switching cylinder (3);
the middle cylinder (7) is assembled into the supporting cylinder (5) and is matched with the sliding cylinder (6) to be assembled on the outer casing (1);
the head of the probe (8) extends into the inner casing (2) and is assembled to the outer casing (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310157840.8A CN116124438A (en) | 2023-02-23 | 2023-02-23 | Double-layer case test probe mounting structure of aero-engine and assembly method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310157840.8A CN116124438A (en) | 2023-02-23 | 2023-02-23 | Double-layer case test probe mounting structure of aero-engine and assembly method thereof |
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| Publication Number | Publication Date |
|---|---|
| CN116124438A true CN116124438A (en) | 2023-05-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310157840.8A Pending CN116124438A (en) | 2023-02-23 | 2023-02-23 | Double-layer case test probe mounting structure of aero-engine and assembly method thereof |
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| CN (1) | CN116124438A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118088792A (en) * | 2024-04-22 | 2024-05-28 | 成都中科翼能科技有限公司 | Bleed air assembly of double-layer runner casing of gas turbine |
-
2023
- 2023-02-23 CN CN202310157840.8A patent/CN116124438A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118088792A (en) * | 2024-04-22 | 2024-05-28 | 成都中科翼能科技有限公司 | Bleed air assembly of double-layer runner casing of gas turbine |
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