CN114678826A - Temperature test lead sealing structure in aircraft engine cartridge receiver - Google Patents
Temperature test lead sealing structure in aircraft engine cartridge receiver Download PDFInfo
- Publication number
- CN114678826A CN114678826A CN202210316141.9A CN202210316141A CN114678826A CN 114678826 A CN114678826 A CN 114678826A CN 202210316141 A CN202210316141 A CN 202210316141A CN 114678826 A CN114678826 A CN 114678826A
- Authority
- CN
- China
- Prior art keywords
- lead
- hole
- temperature test
- aeroengine
- casing
- Prior art date
- 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.)
- Pending
Links
- 238000007789 sealing Methods 0.000 title claims abstract description 84
- 238000012360 testing method Methods 0.000 title claims abstract description 60
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 claims abstract description 24
- 239000000565 sealant Substances 0.000 claims description 6
- 230000000694 effects Effects 0.000 description 8
- 238000000034 method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000003670 easy-to-clean Effects 0.000 description 1
- 230000007717 exclusion Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 125000003003 spiro group Chemical group 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G15/00—Cable fittings
- H02G15/013—Sealing means for cable inlets
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The application belongs to the technical field of the temperature test lead seal design in the aeroengine casing, concretely relates to temperature test lead seal structure in aeroengine casing, include: the lead wire seat is connected to the aeroengine casing and is provided with a lead wire through hole; the lead through hole is communicated with a temperature test lead hole on the aeroengine casing; one end of the lead block extends into the lead through hole, the end is matched with the conical surface between the lead through holes, and a lead through hole is arranged on the lead block; a plurality of annular sealing grooves are formed in the lead through holes; the nut is screwed on the lead seat and compresses the other end of the lead block, and a lead through hole is formed in the nut; the lead through hole is communicated with the lead through hole and is matched with the lead through hole and the lead through hole to lead out a temperature test lead in the aircraft engine casing; the elastic sealing rings are sleeved on the temperature testing lead; each elastic sealing ring is correspondingly arranged in one annular sealing groove.
Description
Technical Field
The application belongs to the technical field of the sealing design of a temperature testing lead in an aircraft engine casing, and particularly relates to a sealing structure of the temperature testing lead in the aircraft engine casing.
Background
The method comprises the following steps that when an aero-engine is tested, temperature testing in an aero-engine casing is mostly involved, currently, a temperature testing lead hole is mostly formed in the aero-engine casing, a lead of a temperature testing sensor in the aero-engine casing is led out, and a lead sealing structure is designed to ensure the sealing performance of the aero-engine casing and specifically comprises a lead seat and a nut, wherein the lead seat is connected to the aero-engine casing and is provided with a lead through hole communicated with the temperature testing lead hole; the nut spiro union has the lead wire via hole with lead wire perforation intercommunication on the lead wire seat, and the temperature test lead wire is drawn forth through lead wire perforation, lead wire via hole, and the lead wire perforation is filled with sealed glue, as shown in figure 1, this kind of technical scheme has following defect:
1) the sealing effect on the aero-engine case is damaged when the aero-engine case is subjected to high temperature, high pressure and vibration, and long-term effectiveness cannot be guaranteed;
2) in order to ensure the sealing effect on the aeroengine casing, a large amount of sealant needs to be filled in the lead through hole, so that the lead cannot be cleaned and the temperature test lead is difficult to disassemble.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft engine case internal temperature test lead seal configuration that overcomes or alleviates at least one of the technical deficiencies of the known prior art.
The technical scheme of the application is as follows:
the utility model provides a temperature test lead seal structure in aeroengine machine casket, includes:
the lead wire seat is connected to the aeroengine casing and is provided with a lead wire through hole; the lead through hole is communicated with a temperature test lead hole on the aeroengine casing;
one end of the lead block extends into the lead through hole, the end is in conical surface fit with the lead through hole, and a lead through hole is formed in the lead block; a plurality of annular sealing grooves are formed in the lead through hole;
the nut is screwed on the lead seat and compresses the other end of the lead block, and a lead through hole is formed in the nut; the lead through hole is communicated with the lead through hole and is matched with the lead through hole and the lead through hole to lead out a temperature test lead in the aircraft engine casing;
the elastic sealing rings are sleeved on the temperature testing lead; each elastic sealing ring is correspondingly arranged in one annular sealing groove.
According to at least one embodiment of the application, in the above-mentioned aircraft engine case internal temperature test lead sealing structure, the lead via hole is filled with a sealant.
According to at least one embodiment of the application, in the temperature test lead sealing structure in the aircraft engine casing, the lead block is formed by two halves which are butted along the radial direction.
According to at least one embodiment of the application, in the sealing structure of the temperature test lead in the aircraft engine casing, each elastic sealing ring is provided with a notch;
a first sealing sheet is arranged on the side wall of one side of the notch on each elastic sealing ring, and a second sealing sheet is arranged on the side wall of the other side of the notch on each elastic sealing ring;
the side walls of the first sealing sheet and the second sealing sheet are jointed and can slide relatively.
According to at least one embodiment of the present application, in the above-mentioned sealing structure for a temperature testing lead in an aircraft engine casing, further comprising:
and the anti-ripple sleeve is sleeved on the periphery of the temperature test lead.
The application has at least the following beneficial technical effects:
the sealing structure is a mechanical sealing structure, can keep the sealing effect on the aero-engine case for a long time under the high-temperature, high-pressure and vibration environments, and can easily disassemble the temperature testing lead.
Drawings
FIG. 1 is a schematic view of a prior art temperature test lead seal arrangement within an aircraft engine case;
FIG. 2 is a schematic view of a temperature test lead seal structure within an aircraft engine case provided by an embodiment of the present application;
FIG. 3 is a schematic diagram of a wire holder provided in an embodiment of the present application;
fig. 4 is a schematic diagram of a lead block provided by an embodiment of the present application;
FIG. 5 is a schematic view of a nut provided in accordance with an embodiment of the present application;
FIG. 6 is a schematic view of an elastomeric seal ring provided in accordance with an embodiment of the present application;
wherein:
1-a lead wire seat; 2-an aircraft engine case; 3-a lead block; 4-a screw cap; 5-temperature testing lead; 6-elastic sealing ring; 7-a first seal piece; 8-a second sealing sheet; 9-anti-ripple sleeve.
For a better understanding of the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced, and do not represent actual product dimensions, and the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1 to 6.
The utility model provides a temperature test lead seal structure in aeroengine machine casket, includes:
the lead wire seat 1 is connected to the aeroengine casing 2 and is provided with a lead wire through hole; the lead through hole is communicated with a temperature test lead hole on the aeroengine casing 2;
a lead block 3, one end of which extends into the lead through hole, the end is matched with the conical surface between the lead through holes, and the lead block is provided with a lead through hole; a plurality of annular sealing grooves are formed in the lead through holes;
the nut 4 is screwed on the lead wire seat 1, compresses the other end of the lead wire block 3 and is provided with a lead wire through hole; the lead through hole is communicated with the lead through hole and is matched with the lead through hole and the lead through hole to lead out a temperature test lead 5 in the aircraft engine casing 2;
a plurality of elastic sealing rings 6 which are sleeved on the temperature testing lead 5; each elastic sealing ring 6 is arranged in an annular sealing groove.
With respect to the aero-engine case internal temperature test lead seal structure disclosed in the above embodiments, it will be understood by those skilled in the art that, the sealing of the aeroengine casing 2 is realized by the conical surface matching between one end of the lead block 3 extending into the lead perforation and the lead perforation, and the labyrinth formed by the elastic sealing rings 6 sleeved on the temperature test lead 5 and the annular sealing rings in the lead through hole of the lead block 3, it is a mechanical sealing structure, can keep the sealing effect on the aeroengine casing for a long time under the high-temperature, high-pressure and vibration environment, and the number and the distribution positions of the temperature test lead 5, the elastic sealing ring 6 and the corresponding annular sealing groove thereof can be easily disassembled, the technical solutions disclosed in the present application can be determined by those skilled in the art according to specific practices, and will not be further described herein.
In some optional embodiments, in the above-mentioned aircraft engine casing internal temperature test lead sealing structure, the lead via hole is filled with a sealant.
For the temperature test lead sealing structure in the aircraft engine casing disclosed in the above embodiment, those skilled in the art can understand that each elastic sealing ring 6 cooperates with a labyrinth formed by each annular sealing groove in the lead through hole of the lead block 3, and the temperature and pressure of the gas in the aircraft engine casing 2 can be reduced step by step, so as to realize the sealing of the low aircraft engine casing 2, and the lead through hole on the nut 4 is filled with the sealant, so that the sealing effect on the low aircraft engine casing 2 can be further ensured, and the amount of the sealant is filled, so as to be easy to clean, and facilitate the disassembly of the temperature test lead 5 therefrom as a limit, and the specific amount can be determined by related technical personnel according to specific and detailed practice when applying the technical scheme disclosed in the application, and no more explanation is performed here.
In some alternative embodiments, in the above-described aero-engine case temperature test lead sealing structure, the lead block 3 is formed of two halves that are butted in the radial direction.
With respect to the sealing structure for the temperature testing lead wire in the casing of the aircraft engine disclosed in the above embodiment, it can be understood by those skilled in the art that the lead block 3 is designed to be composed of two halves which are butted in the radial direction, when the sealing structure of the temperature testing lead in the aircraft engine casing is assembled, the elastic sealing ring 6 can be sleeved on the temperature testing lead 5, then, the two half lead blocks 3 are butted along the radial direction, so that each elastic sealing ring 6 is sunk into the corresponding annular sealing groove, and simultaneously the temperature test lead 5 is clamped, then the lead block 3 is assembled in the lead through hole of the lead seat 1 and is tightly pressed by the nut 4, so that the conical surfaces between the lead block 3 and the lead through hole are tightly matched, the sealing effect on the aeroengine case 2 is ensured, the operation is convenient and fast, when being disassembled, the process can be performed in reverse of the above process, and will not be further described herein.
In some alternative embodiments, in the above-mentioned sealing structure for the temperature test lead in the aircraft engine casing, each elastic sealing ring 6 has a notch;
a first sealing sheet 7 is arranged on the side wall of one side of the notch on each elastic sealing ring 6, and a second sealing sheet 8 is arranged on the side wall of the other side of the notch;
the side walls of the first seal fin 7 and the second seal fin 8 are bonded to each other and can slide relative to each other.
For the sealing structure for the temperature test lead in the aero-engine casing disclosed by the embodiment, as can be understood by a person skilled in the art, each elastic sealing ring 6 is designed to have a notch, and two side walls of the notch are slidably connected through the first sealing sheet 7 and the second sealing sheet 8, so that on one hand, allowance can be provided for the elastic sealing ring 6 to stretch and retract along the radial direction, the elastic sealing ring 6 can be rapidly and effectively contracted when being extruded by the two lead blocks 3 along the radial direction, and the temperature test lead 5 is clamped, and on the other hand, the side walls of the first sealing sheet 7 and the second sealing sheet 8 are attached together, so that the sealing performance of the notch part of the elastic sealing ring 6 can be ensured, and therefore, the sealing effect on the aero-engine casing 2 can be effectively ensured.
In some optional embodiments, in the above aircraft engine casing internal temperature test lead sealing structure, further includes:
the ripple-proof sleeve 9 is sleeved on the periphery of the temperature test lead 5 to protect the temperature test lead 5, and the temperature test lead 5 can be specifically a lead of a thermocouple and can be provided with a plurality of leads.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (5)
1. The utility model provides a temperature test lead wire seal structure in aeroengine machine casket which characterized in that includes:
the lead wire seat (1) is connected to the aeroengine casing (2) and is provided with a lead wire through hole; the lead through hole is communicated with a temperature test lead hole on the aeroengine casing (2);
a lead block (3), one end of which extends into the lead through hole, the end is in conical surface fit with the lead through hole, and a lead through hole is arranged on the lead block; a plurality of annular sealing grooves are formed in the lead through hole;
the nut (4) is screwed on the lead wire seat (1) and tightly presses the other end of the lead wire block (3), and a lead wire through hole is formed in the nut; the lead through hole is communicated with the lead through hole and matched with the lead through hole and the lead through hole to lead out a temperature test lead (5) in the aircraft engine casing (2);
the elastic sealing rings (6) are sleeved on the temperature testing lead (5); each elastic sealing ring (6) is correspondingly arranged in one annular sealing groove.
2. The aeroengine in-case temperature testing lead seal structure of claim 1,
and a sealant is filled in the lead through hole.
3. The aeroengine in-case temperature testing lead seal structure of claim 1,
the lead block (3) is composed of two halves which are butted along the radial direction.
4. The in-case temperature test lead seal structure of an aircraft engine according to claim 1,
each elastic sealing ring (6) is provided with a notch;
a first sealing sheet (7) is arranged on the side wall of one side of the notch of each elastic sealing ring (6), and a second sealing sheet (8) is arranged on the side wall of the other side of the notch of each elastic sealing ring;
the side walls of the first sealing sheet (7) and the second sealing sheet (8) are jointed and can slide relatively.
5. The aeroengine in-case temperature testing lead seal structure of claim 1,
further comprising:
and the anti-ripple sleeve (9) is sleeved on the periphery of the temperature test lead (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210316141.9A CN114678826A (en) | 2022-03-28 | 2022-03-28 | Temperature test lead sealing structure in aircraft engine cartridge receiver |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210316141.9A CN114678826A (en) | 2022-03-28 | 2022-03-28 | Temperature test lead sealing structure in aircraft engine cartridge receiver |
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| Publication Number | Publication Date |
|---|---|
| CN114678826A true CN114678826A (en) | 2022-06-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210316141.9A Pending CN114678826A (en) | 2022-03-28 | 2022-03-28 | Temperature test lead sealing structure in aircraft engine cartridge receiver |
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| Country | Link |
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| CN (1) | CN114678826A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202545801U (en) * | 2012-03-07 | 2012-11-21 | 温州市威格尔科技有限公司 | Seal ring |
| CN206148895U (en) * | 2016-11-11 | 2017-05-03 | 山东达驰阿尔发电气有限公司 | From looks cable outlet sealing device for enclosed bus |
| CN110285268A (en) * | 2019-07-23 | 2019-09-27 | 中国人民解放军军事科学院防化研究院 | It is a kind of to cross linear sealing locking device |
| CN110729680A (en) * | 2019-10-26 | 2020-01-24 | 邳州捷昌新材料有限公司 | PVC electrician's sleeve pipe convenient to connect |
-
2022
- 2022-03-28 CN CN202210316141.9A patent/CN114678826A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202545801U (en) * | 2012-03-07 | 2012-11-21 | 温州市威格尔科技有限公司 | Seal ring |
| CN206148895U (en) * | 2016-11-11 | 2017-05-03 | 山东达驰阿尔发电气有限公司 | From looks cable outlet sealing device for enclosed bus |
| CN110285268A (en) * | 2019-07-23 | 2019-09-27 | 中国人民解放军军事科学院防化研究院 | It is a kind of to cross linear sealing locking device |
| CN110729680A (en) * | 2019-10-26 | 2020-01-24 | 邳州捷昌新材料有限公司 | PVC electrician's sleeve pipe convenient to connect |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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