CN113916539B - Sensing part mounting structure passing through three layers of casings - Google Patents
Sensing part mounting structure passing through three layers of casings Download PDFInfo
- Publication number
- CN113916539B CN113916539B CN202111539281.4A CN202111539281A CN113916539B CN 113916539 B CN113916539 B CN 113916539B CN 202111539281 A CN202111539281 A CN 202111539281A CN 113916539 B CN113916539 B CN 113916539B
- Authority
- CN
- China
- Prior art keywords
- layer
- ring
- floating
- layer casing
- inlayer
- 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.)
- Active
Links
Images
Classifications
-
- 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
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The application relates to the field of engine testing, in particular to a mounting structure of a sensed part penetrating through three layers of casings, wherein the sensed part is mounted in a mounting hole between the three layers of casings, a middle layer mounting seat is arranged on the middle layer casing, a middle layer floating ring in sliding fit with a first floating groove is arranged in the middle layer mounting seat, and the inner side of the middle layer floating ring is connected with the sensed part to realize deformation compensation; an inner-layer mounting seat is arranged on the inner-layer casing, an inner-layer floating ring in sliding fit with the second floating groove is arranged in the inner-layer mounting seat, and the inner-layer floating ring is connected with the middle-layer mounting seat to realize deformation compensation; through closely laminating the inner wall of middle level floating ring and the outside of receiving the portion of feeling, the inner wall of inlayer floating ring and the closely laminating of middle level mount pad realize mutual sealedly between the three quick-witted casket, set up the mounting panel and be connected with outer quick-witted casket in receiving the portion of feeling, guarantee to receive that the portion of feeling can be more convenient ann tear open and overhaul, realize effectively promoting work efficiency to the inside high-efficient measurement of engine.
Description
Technical Field
The application belongs to the field of engine testing, and particularly relates to a sensing part mounting structure passing through a three-layer casing.
Background
In the working process of the aero-engine, a plurality of section parameters in the engine need to be measured, and the engine state is controlled by combining the measurement results. Therefore, the installation and fixation of each section test sensing part need to be considered in the design process. The structure of a new research and development motivation is complex, the position of a sensitive part to be tested is in a high-temperature gradient area, the sensitive part needs to penetrate through three layers of casings to carry out parameter measurement, the penetrating part of the sensitive part between the casings of each layer needs to be sealed, and the technical difficulty is high.
As shown in fig. 1, an outer layer casing, a middle layer casing and an inner layer casing are respectively arranged from top to bottom in the drawing, and a similar technical implementation scheme is that the middle layer casing is fixed, and the inner layer casing and the outer layer casing have a floating adjustment function.
The existing installation structure scheme has the defects that:
1) poor maintainability
The sensor is required to be installed before the outer-layer casing is installed, an additional maintenance opening cover is required for disassembly and installation in the whole machine state after the outer-layer casing is installed, the operation space is limited, the maintenance is difficult, and only the disassembly and the maintenance can be performed if the space is limited and cannot be matched with the corresponding maintenance opening cover.
2) Poor economy
The sensing part structure is located in a high-temperature area, the sensing part is easy to be damaged due to ablation and the like, maintenance and replacement are often needed, due to the fact that maintenance is inconvenient, in-situ replacement cannot be achieved, more hardware is often needed to be decomposed for replacement, next-stage decomposition is needed, replacement period is long, replacement workload is large, economy is poor, and efficiency is low.
Therefore, how to more conveniently and efficiently assemble and disassemble the sensitive part into and disassemble the casing and measure data is a problem to be solved.
Disclosure of Invention
The utility model aims at providing a pass through three-layer cartridge receiver's portion mounting structure that receives to solve among the prior art because middle level cartridge receiver and the portion that receives are fixed, the two-layer cartridge receiver specifically float the adjustment function and lead to receive the portion that receives to install and tear inconvenience, the inconvenient problem of maintenance.
The technical scheme of the application is as follows: a mounting structure of a sensed part penetrating through a three-layer casing comprises an outer-layer casing, a middle-layer casing and an inner-layer casing which are sequentially arranged from outside to inside, wherein mounting holes which are coaxially arranged and mutually communicated are formed in the outer-layer casing, the middle-layer casing and the inner-layer casing, the sensed part is arranged in the mounting holes, the diameter of the sensed part is smaller than that of the mounting holes, a mounting plate is arranged at the outer end of the sensed part, the diameter of the mounting plate is larger than that of the mounting holes, and the mounting plate is detachably and fixedly connected with the outer-layer casing; the middle-layer cartridge receiver is provided with a middle-layer mounting seat, a first floating groove is formed in the inner ring surface of the middle-layer mounting seat, a middle-layer floating ring is in sliding fit in the first floating groove, and the inner wall of the middle-layer floating ring is tightly attached to the outer wall of the sensed part; the inner-layer casing is provided with an inner-layer mounting seat, a second floating groove is formed in the inner ring surface of the inner-layer mounting seat, an inner-layer floating ring is matched in the second floating groove in a sliding mode, and the inner wall of the inner-layer floating ring is tightly attached to the middle-layer mounting seat.
Preferably, the sensed part is in a cylindrical stepped structure, and the diameters of the sensed part at the positions corresponding to the outer-layer casing, the middle-layer casing and the inner-layer casing are gradually reduced.
Preferably, the middle-layer mounting seat is provided with a compensation ring located on one side close to the inner-layer casing, the outer wall of the compensation ring is attached to the inner wall of the mounting hole corresponding to the middle-layer casing, the compensation ring extends into the inner side of the inner-layer floating ring, and the inner wall of the inner-layer floating ring is tightly attached to the compensation ring.
Preferably, an annular outer arc surface is arranged on an outer ring surface of an end portion of the compensation ring, which is close to one end of the inner-layer casing, and an annular inner arc surface is arranged on the inner wall of the inner-layer mounting seat and can be attached to the outer arc surface.
Preferably, the inner side of the middle layer floating ring extends inwards along the radial direction of the aircraft engine to form an L shape.
Preferably, a compensation groove is formed in the inner side wall of the compensation ring, and the middle-layer floating ring can be inserted into the compensation groove.
Preferably, the outer side of the outer casing is provided with an annular boss, and the mounting plate is attached to the outer end face of the annular boss and connected with the outer end face of the annular boss through a bolt.
The mounting structure of the sensitive part penetrating through the three-layer case comprises an outer-layer case, a middle-layer case and an inner-layer case which are sequentially arranged from outside to inside, wherein the sensitive part is mounted in a mounting hole between the three-layer case, a middle-layer mounting seat is arranged on the middle-layer case, a middle-layer floating ring in sliding fit with a first floating groove is arranged in the middle-layer mounting seat, and the inner side of the middle-layer floating ring is connected with the sensitive part to realize deformation compensation between the middle-layer case and the outer-layer case; an inner-layer mounting seat is arranged on the inner-layer casing, an inner-layer floating ring which is in sliding fit with the second floating groove is arranged in the inner-layer mounting seat, and the inner-layer floating ring is connected with the middle-layer mounting seat to realize deformation compensation between the middle-layer casing and the inner-layer casing; through closely laminating the inner wall of middle level floating ring and the outside of receiving the portion of feeling, the inner wall of inlayer floating ring and the closely laminating of middle level mount pad realize mutual sealedly between the three quick-witted casket, set up the mounting panel and be connected with outer quick-witted casket in receiving the portion of feeling, guarantee to receive that the portion of feeling can be more convenient ann tear open and overhaul, realize effectively promoting work efficiency to the inside high-efficient measurement of engine.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of a background art structure;
fig. 2 is a schematic view of the overall structure of the present application.
1. An outer casing; 2. a middle-layer case; 3. an inner casing; 4. a middle layer mounting base; 5. a middle layer floating ring; 6. an inner layer mounting base; 7. an inner floating ring; 8. mounting a plate; 9. a compensation ring; 10. an outer arc surface; 11. an inner arc surface; 12. a compensation groove; 13. an annular boss; 14. a sensed portion.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
A mounting structure of a sensed part penetrating through a three-layer casing comprises an outer-layer casing 1, a middle-layer casing 2 and an inner-layer casing 3 which are sequentially arranged from outside to inside, wherein the middle-layer casing 2 and the inner-layer casing 3 are used for containing gas, the middle-layer casing 2 and the outer-layer casing 1 are used for containing gas, mounting holes which are coaxially arranged and mutually communicated are formed in the outer-layer casing 1, the middle-layer casing 2 and the inner-layer casing 3, and a sensed part 14 for measuring data such as internal temperature and pressure of an engine is mounted in each mounting hole.
The inner side and the inner side referred to in the present application refer to a position close to the centerline of the aircraft engine, that is, a position close to the inner-layer casing 3 in the drawing, and the outer side referred to in the present application refer to a position close to the outer side of the aircraft engine, that is, a position close to the outer-layer casing 1 in the drawing.
For an engine, a large number of section test parameters need to be installed in an engine test, particularly, a high-temperature gradient region relates to installation of a sensitive part 14 of a multilayer casing, thermal deformation uncoordinated displacement compensation is considered, sealing functions among the casings of all layers are considered, gas cannot enter other chambers, and meanwhile, the maintainability requirement of in-situ replacement is considered.
Based on the above considerations, the specific design of the present application includes: the diameter of the sensed part 14 is smaller than the diameter of each mounting hole in the three gaps, the outer end of the sensed part 14 is provided with a mounting plate 8, the diameter of the mounting plate 8 is larger than that of the mounting hole, and the mounting plate 8 is detachably and fixedly connected with the outer casing 1; the middle-layer casing 2 is provided with a middle-layer mounting seat 4, the inner ring surface of the middle-layer mounting seat 4 is provided with a first floating groove, a middle-layer floating ring 5 is in sliding fit in the first floating groove, and the inner hole of the middle-layer floating ring 5 is tightly attached to the outer wall of the sensed part 14; the inner-layer casing 3 is provided with an inner-layer mounting seat 6, a second floating groove is formed in the inner ring surface of the inner-layer mounting seat 6, an inner-layer floating ring 7 is in sliding fit in the second floating groove, and the inner wall of the inner-layer floating ring 7 is tightly attached to the middle-layer mounting seat 4.
Through the design, the sensing part 14 is detachably and fixedly connected with the outer-layer casing 1 and is not connected with the middle-layer casing 2 and the inner-layer casing 3, so that the sensing part 14 does not need to be installed firstly and then the outer-layer casing 1 does not need to be installed when the outer-layer casing 1 is detached and installed, all casings can be installed, and then the outer-layer casing 1 is connected with the sensing part 14, and the installation is convenient; when the sensing part 14 is detached, the outer casing 1 and the sensing part 14 are separated from each other on the outer side, the detachment is convenient, and the outer casing 1 and the sensing part 14 can be detachably mounted in a conventional manner, such as screws, bolts and the like.
The inner wall of the middle-layer floating ring 5 is tightly attached to the outer wall of the sensitive part 14, so that the outer-layer casing 1 and the middle-layer casing 2 are mutually sealed; the inner wall of the inner floating ring 7 is tightly attached to the middle mounting seat 4, so that the inner casing 3 and the middle casing 2 are mutually sealed, the casings are mutually sealed, and the contained gas cannot enter other chambers.
By arranging the middle-layer floating ring 5, the outer-layer casing 1 and the middle-layer casing 2 can be displaced mutually along the axial direction, so that the displacement compensation between the outer-layer casing 1 and the middle-layer casing 2 is realized; by arranging the inner floating ring 7, the middle-layer casing 2 and the inner-layer casing 3 can be displaced mutually along the axial direction, so that the displacement compensation between the middle-layer casing 2 and the inner-layer casing 3 is realized, and the thermal deformation incoordination between the casings can be compensated.
While meeting the requirements of sealing and displacement compensation, the sensitive part 14 and the outer casing 1 can be conveniently mounted and dismounted, and the maintainability requirement of in-situ reloading can be realized, so that the in-situ reloading of the sensitive part 14 on a rack in an installed state is realized, the loading and separating workload and reloading difficulty of the casing caused by replacing the sensitive part 14 are reduced, the working efficiency is improved, and the workload and the period are saved; and the installation structure of the sensing part 14 is simple, and because the high-temperature resistant material of the sensing part 14 for measuring the high-temperature area needs to be additionally protected, the structure can effectively prevent the risk of damage to the sensing part 14 caused by installing the sensing part 14 first and then installing the outer casing 1.
Preferably, the sensing part 14 is a cylindrical stepped structure, and the diameter of the sensing part 14 at the corresponding positions of the outer casing 1, the middle casing 2 and the inner casing 3 is gradually reduced. By providing the stepped structure, the space between the middle-layer casing 2 and the inner-layer casing 3 and the sensing part 14 is larger, and a sufficient space can be more simply reserved for the design of the sealing and displacement compensation structure.
Preferably, the middle layer mounting seat 4 is provided with a compensation ring 9 positioned on one side close to the inner layer casing 3, the outer wall of the compensation ring 9 is attached to the inner wall of the mounting hole corresponding to the middle layer casing 2, the compensation ring 9 extends into the inner side of the inner layer floating ring 7, and the inner wall of the inner layer floating ring 7 is closely attached to the compensation ring 9. By arranging the compensating ring 9 to be tightly attached to the inner-layer floating ring 7 and attaching the compensating ring 9 to the inner wall of the mounting hole of the middle-layer casing 2, the position of the compensating ring 9 under the limiting of the middle-layer mounting seat 4 and the middle-layer casing 2 is accurate, and the sealing property between the compensating ring 9 and the inner-layer floating ring 7 can be effectively ensured.
Preferably, an annular outer arc surface 10 is arranged on the outer ring surface of the end part of the compensation ring 9 close to one end of the inner-layer casing 3, an annular inner arc surface 11 is arranged on the inner wall of the inner-layer mounting seat 6, and the inner arc surface 11 can be attached to the outer arc surface 10. Through setting up interior arc surface 11 and outer arc surface 10, when inlayer floating ring 7 floated arbitrary one side, interior arc surface 11 and outer arc surface 10 homoenergetic are closely laminated, have guaranteed that the cooperation of compensating ring 9 and inlayer mount pad 6 is stable when inlayer floating ring 7 has enough big floating space.
Preferably, the inner side of the middle layer floating ring 5 extends inwards along the radial direction of the aircraft engine to form an L shape, so that the contact area of the middle layer floating ring 5 and the sensitive part 14 is larger, and the sealing performance is better.
Preferably, the inner side wall of the compensation ring 9 is provided with a compensation groove 12, the middle floating ring 5 can be inserted into the compensation groove 12, and the compensation groove 12 is arranged to ensure that the middle floating ring 5 has a large enough floating space.
Preferably, the outer side of the outer casing 1 is provided with an annular boss 13, the mounting plate 8 is attached to the outer end face of the annular boss 13 and is connected with the outer end face of the annular boss 13 through a bolt, and the mounting plate 8 is connected with the annular boss 13 on the outer side of the outer casing 1 through the bolt, so that the mounting is convenient and stable.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. The utility model provides a pass through three-layer machine casket receive sense portion mounting structure, includes outer machine casket (1), middle level machine casket (2) and the inlayer machine casket (3) that set gradually from outer to interior, set up coaxial arrangement and the mounting hole that communicates each other on outer machine casket (1), middle level machine casket (2) and inlayer machine casket (3), be equipped with in the mounting hole and receive sense portion (14), its characterized in that: the diameter of the sensed part (14) is smaller than that of the mounting hole, the outer end of the sensed part (14) is provided with a mounting plate (8), the diameter of the mounting plate (8) is larger than that of the mounting hole, and the mounting plate (8) is detachably and fixedly connected with the outer-layer casing (1);
the middle-layer casing (2) is provided with a middle-layer mounting seat (4), the inner ring surface of the middle-layer mounting seat (4) is provided with a first floating groove, a middle-layer floating ring (5) is in sliding fit in the first floating groove, and the inner wall of the middle-layer floating ring (5) is tightly attached to the outer wall of the sensitive part (14);
be equipped with inlayer mount pad (6) on inlayer machine casket (3), the second floating groove has been seted up on the interior anchor ring of inlayer mount pad (6), sliding fit has inlayer floating ring (7) in the second floating groove, the inner wall and middle level mount pad (4) of inlayer floating ring (7) closely laminate.
2. The mounting structure of the sensitive part passing through the three-layer casing according to claim 1, wherein: the sensing part (14) is of a cylindrical stepped structure, and the diameters of the sensing part (14) at the positions corresponding to the outer-layer casing (1), the middle-layer casing (2) and the inner-layer casing (3) are gradually reduced.
3. The mounting structure of the sensitive part passing through the three-layer casing according to claim 1, wherein: be equipped with on middle level mount pad (4) and be located compensation ring (9) that are close to inlayer machine casket (3) one side, the mounting hole internal wall that the outer wall of compensation ring (9) and middle level machine casket (2) correspond pastes mutually, compensation ring (9) stretch into the inboard of inlayer floating ring (7), the inner wall and the compensation ring (9) of inlayer floating ring (7) closely laminate.
4. The mounting structure of the sensitive part passing through the three-layer casing according to claim 3, wherein: an annular outer arc surface (10) is arranged on the outer ring surface of the end part of the compensation ring (9) close to one end of the inner-layer casing (3), an annular inner arc surface (11) is arranged on the inner wall of the inner-layer mounting seat (6), and the inner arc surface (11) can be attached to the outer arc surface (10).
5. The mounting structure of the sensitive part passing through the three-layer casing according to claim 3, wherein: the inner side of the middle-layer floating ring (5) extends inwards along the radial direction of the aircraft engine to form an L shape.
6. The mounting structure of a sensitive part passing through a three-layer casing according to claim 5, wherein: the inner side wall of the compensation ring (9) is provided with a compensation groove (12), and the middle-layer floating ring (5) can be inserted into the compensation groove (12).
7. The mounting structure of the sensitive part passing through the three-layer casing according to claim 1, wherein: the outer side of the outer-layer casing (1) is provided with an annular boss (13), and the mounting plate (8) is attached to the outer end face of the annular boss (13) and connected with the outer end face of the annular boss through a bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111539281.4A CN113916539B (en) | 2021-12-16 | 2021-12-16 | Sensing part mounting structure passing through three layers of casings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111539281.4A CN113916539B (en) | 2021-12-16 | 2021-12-16 | Sensing part mounting structure passing through three layers of casings |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113916539A CN113916539A (en) | 2022-01-11 |
| CN113916539B true CN113916539B (en) | 2022-03-04 |
Family
ID=79248975
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111539281.4A Active CN113916539B (en) | 2021-12-16 | 2021-12-16 | Sensing part mounting structure passing through three layers of casings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113916539B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114427873A (en) * | 2022-01-21 | 2022-05-03 | 中国航发沈阳发动机研究所 | External insertion type test sensitive part mounting structure for three-layer casing |
| CN114877851B (en) * | 2022-04-14 | 2024-02-23 | 中国航发沈阳发动机研究所 | Adjustable guide vane angle measuring mechanism for compensating deformation difference of double-layer casing |
| CN116008090B (en) * | 2023-02-16 | 2023-06-23 | 北京成立科技有限公司 | Aeroengine combustion chamber casing internal pressure test device |
| CN118088792B (en) * | 2024-04-22 | 2024-07-02 | 成都中科翼能科技有限公司 | Bleed air assembly of double-layer runner casing of gas turbine |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3727927A (en) * | 1968-09-06 | 1973-04-17 | Int Harvester Co | Ring manufacture, productive of line contact seal |
| CA2445891A1 (en) * | 2001-06-14 | 2002-12-27 | Airbus Uk Limited | Construction for routing a conduit or the like through a structural member |
| CN202360903U (en) * | 2011-11-21 | 2012-08-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Connection structure of ventilation pipeline passing through case |
| CN103133784A (en) * | 2011-11-23 | 2013-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | Ventilating pipeline connection structure penetrating through gear box |
| CN103133783A (en) * | 2011-11-24 | 2013-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | Pipeline double-thread connection structure penetrating through cartridge receiver |
| CN106460538A (en) * | 2014-04-08 | 2017-02-22 | 赛峰直升机发动机公司 | Turbine engine compressor with variable-pitch blades |
| CN108387377A (en) * | 2018-02-06 | 2018-08-10 | 中国航发沈阳发动机研究所 | A kind of engine stock class testing equipment mounting assembly |
| CN112228872A (en) * | 2020-11-09 | 2021-01-15 | 成都轩鼎能源科技有限公司 | Air-cooled high-temperature alloy carbon black reaction furnace and carbon black preparation method |
| CN213599366U (en) * | 2020-11-09 | 2021-07-02 | 成都轩鼎能源科技有限公司 | Air-cooled high-temperature alloy carbon black reaction furnace |
-
2021
- 2021-12-16 CN CN202111539281.4A patent/CN113916539B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3727927A (en) * | 1968-09-06 | 1973-04-17 | Int Harvester Co | Ring manufacture, productive of line contact seal |
| CA2445891A1 (en) * | 2001-06-14 | 2002-12-27 | Airbus Uk Limited | Construction for routing a conduit or the like through a structural member |
| CN202360903U (en) * | 2011-11-21 | 2012-08-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Connection structure of ventilation pipeline passing through case |
| CN103133784A (en) * | 2011-11-23 | 2013-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | Ventilating pipeline connection structure penetrating through gear box |
| CN103133783A (en) * | 2011-11-24 | 2013-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | Pipeline double-thread connection structure penetrating through cartridge receiver |
| CN106460538A (en) * | 2014-04-08 | 2017-02-22 | 赛峰直升机发动机公司 | Turbine engine compressor with variable-pitch blades |
| CN108387377A (en) * | 2018-02-06 | 2018-08-10 | 中国航发沈阳发动机研究所 | A kind of engine stock class testing equipment mounting assembly |
| CN112228872A (en) * | 2020-11-09 | 2021-01-15 | 成都轩鼎能源科技有限公司 | Air-cooled high-temperature alloy carbon black reaction furnace and carbon black preparation method |
| CN213599366U (en) * | 2020-11-09 | 2021-07-02 | 成都轩鼎能源科技有限公司 | Air-cooled high-temperature alloy carbon black reaction furnace |
Non-Patent Citations (2)
| Title |
|---|
| Stress Analysis of the Integrity of Casing-Cement Ring-Structural Consolidation Body by Volume Fracturing;OUYANG Yong;《Advances in Petroleum Exploration and Development》;20180630;全文 * |
| 基于机匣应变信号的航空发动机转静碰摩;于明月等;《航空学报》;20130625;全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113916539A (en) | 2022-01-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113916539B (en) | Sensing part mounting structure passing through three layers of casings | |
| CN209214669U (en) | It is a kind of to detect Vibration Meter for monitoring slewing vibration and the wireless communication point of temperature | |
| CN206789648U (en) | A kind of safeguard construction of power battery pack | |
| CN110185733A (en) | A kind of vibration isolator monitored on-line | |
| CN116481742B (en) | Lithium battery rotary kiln sealing leakage detection system and method | |
| CN101576552A (en) | Device and method for online monitoring of gas in oil immersed electric apparatus oil | |
| CN201514309U (en) | Leakage test device for exhaust manifold gasket of engine | |
| CN210037167U (en) | Double-layer thin-wall casing measuring probe fixing structure | |
| CN211783713U (en) | Sensor circuit board support | |
| CN207123573U (en) | A kind of photomultiplier equipment for testing service life | |
| CN210037012U (en) | Temperature measurement system of engine piston | |
| CN218887294U (en) | Battery pack | |
| CN207439469U (en) | A kind of set damage corrosion and temperature and pressure comprehensive tester | |
| CN110600646A (en) | Battery box of electric forklift and electric forklift using battery box | |
| CN205951628U (en) | Sensor is pressed to activestandby formula twins | |
| CN218867236U (en) | Battery structure and shared vehicle | |
| CN111879423A (en) | Temperature measurement end cap that cooperation looped netowrk cabinet end cap temperature measurement system used | |
| CN207456590U (en) | A kind of embedded piezoelectricity Wheel axle identifier of suitable dynamic weight calculation weighing apparatus | |
| CN220751478U (en) | Hydrogen monitoring device of hydrogen supply system | |
| CN214698817U (en) | Taper sleeve, oil film bearing and supporting roller matched with oil film bearing | |
| CN214066849U (en) | Atmosphere sampling monitor | |
| CN115628807A (en) | Split type vibration measuring device and mounting method thereof | |
| CN220603598U (en) | Dehumidification module testing device | |
| CN209855774U (en) | Non-bearing indicator diagram testing device | |
| CN214748128U (en) | Air spring intelligent monitoring installation device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |