CN114964788A - Aeroengine test lead sealing device - Google Patents
Aeroengine test lead sealing device Download PDFInfo
- Publication number
- CN114964788A CN114964788A CN202210519113.7A CN202210519113A CN114964788A CN 114964788 A CN114964788 A CN 114964788A CN 202210519113 A CN202210519113 A CN 202210519113A CN 114964788 A CN114964788 A CN 114964788A
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- CN
- China
- Prior art keywords
- test lead
- rubber containing
- cylinder
- sealing device
- aircraft engine
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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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
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/062—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces characterised by the geometry of the seat
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/10—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing
- F16J15/102—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing characterised by material
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- General Physics & Mathematics (AREA)
- Geometry (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The invention provides a sealing device for a test lead of an aircraft engine, which comprises a test lead seat, a rubber containing cylinder, a pressing cap, a rubber containing cover and a sealing ring, wherein a filler for sealing at high temperature is arranged in the rubber containing cylinder, the rubber containing cylinder is of two halved cylinder structures with the same structure, U-shaped grooves for bundling and fixing test wires are respectively arranged on the bottom surfaces of the two halved cylinder structures, and the U-shaped grooves on the two halved cylinder structures are oppositely arranged. The test leads in the sealing device are dispersedly fixed in the U-shaped grooves of the rubber containing cylinder, the assembly and disassembly processes are simpler, the manual operation on the test leads is reduced, and the survival rate of the test points is improved; the sealing device has the advantages of convenient lead, reliable sealing, easy assembly and disassembly and the like, and can realize the sealing function of the test lead hole under different test conditions.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to a sealing device for a test lead of an aero-engine.
Background
The working principle of the aero-engine is that heat energy generated after compressed air of an air compressor and fuel are mixed and combusted is used for driving a turbine to rotate at a high speed, and the turbine drives the air compressor through a turbine shaft, so that continuous operation is formed. During the test of the aeroengine, holes are often required to be formed in the casing so as to lead out the test wires from the casing. Therefore, a sealing device having a lead and a sealing function is required.
As shown in fig. 4, the structure of the conventional test lead sealing device is composed of 5 parts, namely 1 test lead tube, 2 press caps, 5 pore plates, 4 glue pore plates and 6 lock wires. Wherein, 1 test lead tube passes through the welded form and connects on the machine casket, 4 hold the gluey orifice plate assembly on 1 test lead tube, 5 orifice plate assemblies on 4 hold the gluey orifice plate, 2 press the threaded connection of cap through the hole on 1 test lead tube.
During the assembly, the test lead is concentrated fixedly, wears out from 1 test lead pipe hole, loops through the hole of 4 appearance orifice plates and 5 orifice plates, and 4 appearance orifice plates and 5 orifice plates monolithic stationary compress tightly the after-fixing fix on 1 test lead pipe, will concentrate fixed test lead to pass 2 and press the cap hole, and the internal thread that presses the cap at last even realizes 6 test lead to fix with the external screw thread connection of 1 test lead pipe through 2. When the test lead tube is decomposed, the 2 pressing cap, the 5 hole plate, the 4 containing glue hole plate and the 1 test lead tube are required to be taken out from the 6 test lead tubes in sequence. Since the 1 test lead tube is welded to the casing, it cannot be disassembled from the casing.
As can be seen from the above working procedure, the test lead sealing device of the prior art structure has the following disadvantages: 1. the test lead sealing device is connected with the casing through welding, so that the test lead sealing device is difficult to disassemble from the casing, and the assembling and disassembling processes are complicated; 2. during assembly, the test lead needs to be fixed in a concentrated manner and sequentially passes through the inner holes of the glue containing hole plate and the hole plate, so that the test lead is operated more, and the process is complicated; during decomposition, the test lead also needs to sequentially penetrate through the press cap, the pore plate and the inner hole of the glue containing pore plate, and the process is complicated; 3. the test lead is subjected to more operations in the assembling and disassembling processes, and is easily damaged, so that the survival rate of a test point is reduced; 4. sealing measures are not needed among the centralized and fixed test leads, air leakage risks exist, engine performance test parameters are distorted, and even the development of engine test work is influenced in severe cases, so that the sealing reliability is poor.
Disclosure of Invention
In order to solve the above problems, an object of the present invention is to provide a test lead sealing device with high reliability; at the same time, the device also needs to have good assembly, operability, interchangeability and economy.
In order to achieve the above object, the present invention provides a sealing device for testing lead wires of an aircraft engine, the sealing device comprises a hollow testing lead wire seat for lead wires, a rubber containing cylinder placed above the testing lead wire seat, a pressing cap for pressing the rubber containing cylinder onto the testing lead wire seat, a rubber containing cover arranged above the rubber containing cylinder for sealing, and a sealing ring for sealing connection of the testing lead wire seat and a casing of the aircraft engine,
the rubber containing cylinder is internally provided with a filler for sealing at high temperature, the rubber containing cylinder is of two halved cylinder structures with the same structure, the bottom surfaces of the two halved cylinder structures are respectively provided with a U-shaped groove for bundling and fixing a test wire, and the U-shaped grooves on the two halved cylinder structures are oppositely arranged.
The aeroengine test lead sealing device provided by the invention is also characterized in that a plurality of grooves which are uniformly distributed in the circumferential direction are arranged on the upper end surface of the test lead seat, a raised structure with a lock wire hole is arranged on the outer wall surface of the upper end, and threads are arranged on the outer wall surface of the upper side and the outer wall surface of the lower end of the raised structure.
The aeroengine test lead sealing device provided by the invention is also characterized in that the upper end surface and the lower end surface of the halved cylindrical structure are provided with bulges which are respectively matched and installed with the test lead seat and the rubber containing cover, and the two halved cylindrical structures are matched and connected through a second bulge and a square groove.
The sealing device for the test lead of the aero-engine is further characterized in that the pressing cap is of a circular tube structure, a cavity is formed in the pressing cap, the cavity is used for accommodating the rubber accommodating cylinder and the rubber accommodating cover, an internal thread used for being connected with the test lead base is arranged at the lower end of the pressing cap, a screw locking hole is formed in the outer wall of the upper end of the pressing cap, and a through hole used for allowing the test lead to pass through is formed in the upper end face of the pressing cap.
The sealing device for the test lead of the aircraft engine is further characterized in that the rubber containing cover is provided with an installation groove used for being fixed with the rubber containing cylinder and a U-shaped groove used for bundling the test wire.
The sealing device for the test lead of the aircraft engine is further characterized in that the notch of the U-shaped groove is formed in the circumferential direction of the rubber accommodating cover.
The sealing device for the test lead of the aircraft engine is further characterized in that the rubber containing cover is of a semicircular structure corresponding to the rubber containing cylinder, and the U-shaped groove in the rubber containing cover corresponds to the U-shaped groove in the rubber containing cylinder.
The aero-engine test lead sealing device provided by the invention is also characterized in that the sealing ring is of a circular ring structure made of a rubber material.
The aeroengine test lead sealing device provided by the invention also has the characteristic that the filler is high-temperature cement.
The aeroengine test lead sealing device provided by the invention also has the characteristic that the sealing device is connected with a turbine casing through internal threads arranged on the turbine casing of the aeroengine.
Advantageous effects
The test leads in the aeroengine test lead sealing device provided by the invention are dispersedly fixed in the U-shaped grooves of the rubber containing cylinder, the assembly and disassembly processes are simpler, the manual operation on the test leads is reduced, and the survival rate of the test points is improved; meanwhile, the high-temperature cement contained in the sol cylinder enables the fuel gas to be effectively blocked, and the risk of fuel gas leakage is reduced. In addition, the testing lead seat is connected with the casing through threads, and the assembling and disassembling process is simple. In a word, the invention has the advantages of convenient lead wire, reliable sealing, easy assembly and disassembly and the like, and can realize the sealing function of the test lead wire hole under different test conditions.
Drawings
FIG. 1 is a schematic structural diagram of an aircraft engine test lead sealing device provided by an embodiment of the invention;
fig. 2 is a rubber accommodating cylinder for a lead testing device according to an embodiment of the present invention;
fig. 3 is a rubber accommodating cover for a test lead device according to an embodiment of the present invention;
fig. 4 shows a test lead frame structure in the prior art.
Detailed Description
The present invention is further described in detail with reference to the drawings and examples, but it should be understood that these embodiments are not intended to limit the present invention, and those skilled in the art should understand that the functional, methodological, or structural equivalents of these embodiments or substitutions may be included in the scope of the present invention.
In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
As shown in fig. 1-3, the present embodiment provides an aircraft engine test lead seal assembly, the sealing device comprises a hollow testing lead wire seat 3 for leading wires, a rubber containing cylinder 5 placed above the testing lead wire seat 3, a pressing cap 4 used for pressing the rubber containing cylinder 5 on the testing lead wire seat 3, a rubber containing cover 6 arranged above the rubber containing cylinder 5 for sealing, and a sealing ring 2 used for sealing and connecting the testing lead wire seat 3 with a casing of the aircraft engine, the rubber containing cylinder 5 is internally provided with a filler 7 for sealing at high temperature, the rubber containing cylinder 5 is of two halved cylinder structures with the same structure, the bottom surfaces of the two halved cylinder structures are respectively provided with U-shaped grooves 5-3 for bundling and fixing test wires, and the U-shaped grooves 5-3 on the two halved cylinder structures are oppositely arranged.
In the embodiment, the rubber containing cylinders in the lead testing device are provided with the U-shaped grooves, when leads are led, the test wires are respectively clamped into the rubber containing cylinders in a halved state, the rubber containing cylinders are clamped and connected, the leads can be fixed, and the lead testing device is good in assembly performance; when the test lead is disassembled, only the rubber cylinder is needed to be disassembled and the test wire is needed to be dispersed and taken out from the U-shaped groove, so the disassembly is easier, and the disassembly operability of the lead is better; the operation on the test lead is less in the assembling and disassembling processes, the test lead is difficult to damage, and the survival rate of a test point is improved; high-temperature cement and a sealing ring between the test lead sealing device and the casing are filled between the test leads which are fixed in a dispersing mode, so that fuel gas in the casing is difficult to leak, and the sealing reliability is improved.
In some embodiments, the upper end surface of the test lead seat 3 is provided with a plurality of grooves 2-3 uniformly arranged in the circumferential direction, the outer wall surface of the upper end is provided with a raised structure 2-2 with a lockwire hole, and the outer wall surface of the upper side and the outer wall surface of the lower end of the raised structure 2-2 are both provided with threads.
In some embodiments, the upper and lower end surfaces of the halved cylindrical structure are provided with a protrusion 5-1 matched with the test lead seat 3 and a protrusion 5-2 matched with the glue containing cover 6, and the two halved cylindrical structures are matched and connected through a second protrusion 5-5 and a square groove.
In some embodiments, the pressing cap 4 is a circular tube structure with a cavity inside, the cavity is used for accommodating the rubber containing cylinder 5 and the rubber containing cover 6, the lower end of the pressing cap 4 is provided with an internal thread used for being connected with the test lead base, the outer wall of the upper end of the pressing cap 4 is provided with a screw locking hole, and the upper end face is provided with a through hole used for passing through the test lead. The pressing cap 4 is locked on the test lead base 3 through a locking wire 9. The pressing cap 4 is connected with the testing lead wire base 3 through threads, and after the threads are screwed down, the rubber containing cylinder 5 and the rubber containing cover 6 are tightly pressed at the outer end of the testing lead wire base 3.
In some embodiments, the rubber containing cover 6 is provided with a mounting groove 6-2 for fixing with the rubber containing cylinder and a U-shaped groove 6-1 for bundling the test wire.
In some embodiments, the notch of the U-shaped groove 6-1 is formed in the circumferential direction of the glue containing cover.
In some embodiments, the glue containing cover 6 is a semicircular structure corresponding to the glue containing cylinder 5, and the U-shaped groove 6-1 on the glue containing cover corresponds to the U-shaped groove 5-3 on the glue containing cylinder 5.
In some embodiments, the sealing ring 2 is a circular ring structure made of rubber material.
In some embodiments, the filler 7 is high temperature cement.
In some embodiments, the sealing device is connected to the turbine casing 1 by means of an internal thread provided on the turbine casing of the aircraft engine. The test lead sealing device is connected with the casing through threads, and the assembly and disassembly processes are simple.
When in work:
the test lead is led out from the stepped hole of the turbine casing 1-2, the inner hole of the sealing ring and the inner hole of the test lead seat in sequence; the testing leads are dispersedly fixed in U-shaped grooves 5-3 of the rubber containing cylinder 5, the rubber containing cylinder 5 is fixed on a testing lead seat through a boss 5-1 on the rubber containing cylinder, high-temperature cement 7 is filled in the rubber containing cylinder 5 to realize gas sealing, and the testing leads are finally led out from the U-shaped grooves 6-1 symmetrically distributed on the rubber containing cover 6.
The above description is intended to be illustrative of the preferred embodiment of the present invention and should not be taken as limiting the invention, but rather, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. The aeroengine test lead sealing device is characterized by comprising a hollow test lead seat for a lead, a rubber containing cylinder placed above the test lead seat, a pressing cap used for pressing the rubber containing cylinder on the test lead seat, a rubber containing cover arranged above the rubber containing cylinder for sealing and a sealing ring used for connecting the test lead seat with a casing of the aeroengine in a sealing way, wherein the rubber containing cover is provided with a rubber containing hole for containing the rubber containing cylinder,
the rubber containing cylinder is internally provided with a filler for sealing at high temperature, the rubber containing cylinder is of two halved cylinder structures with the same structure, the bottom surfaces of the two halved cylinder structures are respectively provided with a U-shaped groove for bundling and fixing a test wire, and the U-shaped grooves on the two halved cylinder structures are oppositely arranged.
2. The aircraft engine test lead sealing device according to claim 1, wherein a plurality of grooves are uniformly arranged in the circumferential direction on the upper end surface of the test lead seat, a raised structure with a lock wire hole is arranged on the outer wall surface of the upper end, and threads are arranged on the outer wall surface of the upper side and the outer wall surface of the lower end of the raised structure.
3. The aircraft engine test lead sealing device according to claim 1, wherein the upper and lower end surfaces of the halved cylindrical structure are provided with protrusions which are respectively matched and installed with the test lead seat and the rubber containing cover, and the two halved cylindrical structures are matched and connected through a second protrusion and a square groove.
4. The aircraft engine test lead sealing device according to claim 1, wherein the pressing cap is a round tube structure with a cavity inside, the cavity is used for accommodating the rubber accommodating cylinder and the rubber accommodating cover, the lower end of the pressing cap is provided with an internal thread used for being connected with the test lead seat, the outer wall of the upper end of the pressing cap is provided with a screw locking hole, and the upper end face of the pressing cap is provided with a through hole used for passing through the test lead.
5. The aircraft engine test lead sealing device of claim 1, wherein the glue containing cover is provided with a mounting groove for fixing with the glue containing cylinder and a U-shaped groove for bundling the test wires.
6. The aircraft engine test lead seal of claim 5 wherein the notch of the U-shaped groove is open in the circumferential direction of the glue-receiving cap.
7. The aircraft engine test lead sealing device of claim 5, wherein the glue containing cover is of a semicircular structure arranged corresponding to the glue containing barrel, and the U-shaped groove on the glue containing cover corresponds to the U-shaped groove on the glue containing barrel.
8. The aircraft engine test lead seal arrangement of claim 1 wherein said seal ring is of annular configuration of rubber material.
9. The aircraft engine test lead seal according to claim 1, wherein said filler is high temperature cement.
10. The aircraft engine test lead seal according to claim 1, wherein the seal is connected to a turbine casing of an aircraft engine by internal threads provided on the turbine casing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210519113.7A CN114964788A (en) | 2022-05-12 | 2022-05-12 | Aeroengine test lead sealing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210519113.7A CN114964788A (en) | 2022-05-12 | 2022-05-12 | Aeroengine test lead sealing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114964788A true CN114964788A (en) | 2022-08-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210519113.7A Pending CN114964788A (en) | 2022-05-12 | 2022-05-12 | Aeroengine test lead sealing device |
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| Country | Link |
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| CN (1) | CN114964788A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115950639A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | Dynamic stress test line switching method for rotor blade of disk separation fan |
| CN116951184A (en) * | 2023-09-20 | 2023-10-27 | 成都中科翼能科技有限公司 | Test pipeline sealing structure of gas turbine |
-
2022
- 2022-05-12 CN CN202210519113.7A patent/CN114964788A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115950639A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | Dynamic stress test line switching method for rotor blade of disk separation fan |
| CN115950639B (en) * | 2023-03-09 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Dynamic stress test line switching method for disc separation fan rotor blade |
| CN116951184A (en) * | 2023-09-20 | 2023-10-27 | 成都中科翼能科技有限公司 | Test pipeline sealing structure of gas turbine |
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