CN2816771Y - External compressed-spring screw-fixing type armoured thermal electric coupler - Google Patents
External compressed-spring screw-fixing type armoured thermal electric coupler Download PDFInfo
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- CN2816771Y CN2816771Y CN200520024785.2U CN200520024785U CN2816771Y CN 2816771 Y CN2816771 Y CN 2816771Y CN 200520024785 U CN200520024785 U CN 200520024785U CN 2816771 Y CN2816771 Y CN 2816771Y
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- stainless steel
- hex bolts
- steel pillar
- seat
- spring
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Abstract
The utility model relates to an external compressed-spring screw-fixing type armoured thermal electric coupler which comprises an armoured electric coupler, a stainless steel protective pipe, compensating wires, a screw compression spring, a spring fastener, a hexagon bolt holder and an aviation socket, wherein the armoured electric coupler is on the front end of the stainless steel protective pipe, and the measuring end of the armoured electric coupler is respectively connected with two compensating wires; the hexagon bolt holder is provided with a hexagon head and a seal ring on one end of a threaded tube. The utility model is characterized in that the armoured electric coupler is welded on the front end of the stainless steel protective pipe and sealed. The spring fastener and the screw compression spring are covered outside the stainless steel protective pipe. The spring fastener is welded together with the stainless steel protective pipe. The hexagon bolt holder is covered outside the stainless steel protective pipe. Two ends of the screw compression spring respectively prop up the spring fastener and the hexagon bolt holder. The seal ring is installed between the inner side of the hexagon bolt holder and the stainless steel protective pipe and is pressed by a through hole pressure piece covering the stainless steel protective pipe. The utility model is isolated from vapor erosion, guarantees the insulating property of the electric coupler, and prevents measurement errors caused by debasing the insulating property.
Description
Technical field
The utility model relates to the fixed armoured thermocouple of a kind of stage clip screw thread, particularly 3 millimeters armoured thermocouples of K calibration diameter of phi.
Background technology
The fixed armoured thermocouple of stage clip screw thread is widely used in smelter continuous casting of molten steel machine crystallizer bleed-out early warning system, is crucial temperature probe.By being evenly distributed on many fixed armoured thermocouples of stage clip screw thread on the crystallizer cooled copper, the temperature of continuous coverage heat eliminating medium such as copper coin and cooling circulating water.And by the conversion transmission system show at the pulpit terminal, in order to monitor temperature field changes in distribution situation and trouble free service situation on the crystallizer cooled copper, instruct the continuous casting billet pulling rate to adjust and the cooling cooling down operation, prevent the generation of bleed-out accident when molten steel burns copper coin.The fixed armoured thermocouple of stage clip screw thread be with the spiral compression spring fixed form with the elongated armouring galvanic couple of 3 millimeters of diameter of phi measure front end as the spring probe roof pressure on measured object, and be fixed on the testee outer wall with the screw thread cutting ferrule, the accuracy of improve measuring is even be installed in the optimality that has measurement effect on the conticaster crystallizer cooled copper of periodic vibration too.The fixed armoured thermocouple of stage clip screw thread can be applicable on the high object of vibration frequency, as the temperature of the bearing shell of measuring cluster engine.The structure of the fixed armoured thermocouple of existing stage clip screw thread is that the spiral compression spring of 8 millimeters of diameter of phi is enclosed within outside the galvanic couple armouring of 3 millimeters of diameter of phi, and together be embedded in the stainless steel pillar of 10 millimeters of diameter of phi, make the galvanic couple armouring can be in the stainless steel pillar elastic shrinkage, gapped between galvanic couple armouring and the stainless steel pillar, because the fixed armoured thermocouple of stage clip screw thread is immersed in the water, the compensating line that is connected with the galvanic couple silk also is immersed in the water, has reduced resistance and insulativity and measurement accuracy between two compensating lines.
Summary of the invention
In order to overcome the above-mentioned deficiency of the existing fixed armoured thermocouple of stage clip screw thread, when providing a kind of the use, the utility model do not influence the fixed armoured thermocouple of stage clip screw thread of insulativity and measurement accuracy between two compensating lines.
The technical solution of the utility model is to adopt outer spring external structure, and the spiral compression spring of 12 millimeters of diameter of phi is enclosed within outside 10 millimeters stainless steel pillars of diameter of phi, 3 millimeters armouring galvanic couples of diameter of phi is contained in the welding of 10 millimeters stainless steel pillars of Φ front end fixes.
The utility model comprises 3 millimeters armouring galvanic couples of diameter of phi, the stainless steel pillar, compensating wire, spiral compression spring, the spring cutting ferrule, hex bolts seat and aviation socket, the armouring galvanic couple is at stainless steel pillar front end, armouring galvanic couple measuring junction connects with two compensating wires respectively in the stainless steel pillar through two galvanic couple silks, the compensating wire output terminal is drawn from the aviation socket, the hex bolts seat is at the end with externally threaded threaded line pipe a hexagon head to be set, O-ring seal at the threaded line pipe overcoat, at the middle part of hex bolts seat one through hole is arranged, the tail end of stainless steel pillar and aviation socket are fixed together, it is characterized in that: the armouring galvanic couple is to be welded on stainless steel pillar front end and sealing between the two, spring cutting ferrule and spiral compression spring are enclosed within outside the stainless steel pillar, spring cutting ferrule and stainless steel pillar weld together, the hex bolts cover for seat is outside the stainless steel pillar, the two ends of spiral compression spring withstand on an end and the hex bolts seat of spring cutting ferrule respectively, between the inboard and stainless steel pillar of hex bolts seat O-ring seal are installed and are pushed down by the through hole casting die that is enclosed within the stainless steel pillar.
The through hole casting die of the above-mentioned fixed armoured thermocouple of stage clip screw thread is divided into two kinds of structures, wherein a kind of hex head end of hex bolts seat of structure has an inner bolt hole, the through hole casting die is to have externally threaded threaded line pipe, end at threaded line pipe is being fixed hexagon head, and this threaded line pipe is screwed in the inner bolt hole of hex bolts seat.Another kind of structure is a side that the through hole casting die is laminated on the threaded line pipe of hex bolts seat, and spiral compression spring via through holes casting die withstands on the hex bolts seat.
The utility model is taked said structure, and galvanic couple and stainless steel pillar integral, flexible are shunk, and can make galvanic couple silk and compensating wire welding end be sealed in the stainless steel pillar again, the erosion of isolated steam.For example can prevent the erosion of conticaster crystallizer cooling circulating water, guarantee the insulativity of galvanic couple, avoid falling end insulativity and cause measuring error, be specially adapted to metallurgical rugged environment.
Description of drawings
Fig. 1 is the structural drawing of the fixed armoured thermocouple embodiment one of the external screw thread of this stage clip, hex bolts seat partly cut-away among the figure.
Fig. 2 is the axial cut-open view of fixed armoured thermocouple embodiment one front end of the external screw thread of this stage clip, and Fig. 1 amplifies relatively.
Fig. 3 is the structural drawing of the fixed armoured thermocouple embodiment two of the external screw thread of this stage clip, hex bolts seat partly cut-away among the figure.
Among the above-mentioned figure:
1, armouring galvanic couple 2, place 3, stainless steel pillar 4, spring cutting ferrule are connected and fixed
5, spiral compression spring 6, hex bolts seat 7, threaded line pipe 8, O RunddichtringO
9, hexagon head 10, O RunddichtringO 11, packing ring 12, inner bolt hole
13, threaded line pipe 14, through hole casting die 15, hexagon head 16, patch
17, aviation socket 18, armouring galvanic couple measuring junction 19, galvanic couple silk
20, pad sealed packet 21, electric insulating sealant 22, pad 23, compensating wire
24, through hole casting die 25, inside groove 26, ring groove 27, O RunddichtringO
Embodiment
Embodiment of the present utility model is provided by embodiment and accompanying drawing thereof, but embodiment of the present utility model is not limited to following embodiment.
Fig. 1, the fixed armoured thermocouple of the external screw thread of the stage clip of describing among Fig. 2 has 3 millimeters armouring galvanic couples 1 of diameter of phi, 10 millimeters stainless steel pillars 3 of diameter of phi, compensating wire 23, spiral compression spring 5, spring cutting ferrule 4, hex bolts seat 6 and aviation socket 17, armouring galvanic couple 1 is at stainless steel pillar front end 3, armouring galvanic couple measuring junction 18 connects with two compensating wires 23 respectively through pad 22 in stainless steel pillar 3 through two galvanic couple silks 19, pad 22 is sealed by electric insulating sealant 21 in pad sealed packet 20, compensating wire 23 output terminals are connected with patch 16, patch 16 is drawn from aviation socket 17, hex bolts seat 6 is at the right-hand member with externally threaded threaded line pipe 7 hexagon head 9 to be set, overlapping O RunddichtringO 8 outside threaded line pipe 7 and between the hexagon head 9, at the middle part of hex bolts seat 6 through hole is arranged, the tail end of stainless steel pillar 3 and aviation socket 17 are fixed together, it is characterized in that: armouring galvanic couple 1 is to be welded on stainless steel pillar 3 front ends and sealing between the two, spring cutting ferrule 4 is enclosed within outside the stainless steel pillar 3 with spiral compression spring 5, spring cutting ferrule 4 welds together with stainless steel pillar 3, hex bolts seat 6 is enclosed within outside the stainless steel pillar 3, the two ends of spiral compression spring 5 withstand on the right-hand member of spring cutting ferrule 4 and the left end of hex bolts seat 6 respectively, between hex bolts seat 6 endoporus and the stainless steel pillar 3 O O-ring seal 10 is installed, and pushes down by the through hole casting die 14 that is enclosed within stainless steel pillar 3.
The hexagon head 9 of the hex bolts seat 6 of present embodiment has one section inner bolt hole 12, O RunddichtringO 10 is installed in the left end of inner bolt hole 12, packing ring 11 overlaps together with O RunddichtringO 10, through hole casting die 14 is to have externally threaded threaded line pipe 13, fixing hexagon head 15 at the right-hand member of threaded line pipe 13, threaded line pipe 13 is screwed in the inner bolt hole 12 of hex bolts seat 6 packing ring 11 and O RunddichtringO is compressed.
Embodiment of the present utility model sees Fig. 3, the difference of present embodiment and embodiment one is that through hole casting die 24 is arranged in the inside groove 25 of hex bolts seat 6 left ends, and be laminated on the left side of hex bolts seat 6, spiral compression spring 5 via through holes casting dies 24 withstand on hex bolts seat 6, between through hole casting die 24 and hex bolts seat 6 ring groove 26 is arranged, O RunddichtringO 27 is installed in the ring groove 26.The spring cutting ferrule 4 and the through hole casting die 24 of present embodiment are ring-type.
Armouring galvanic couple 1 also can otherwise be fixed on stainless steel pillar 3 front ends, and sealing between the two.
Claims (3)
1, the fixed armoured thermocouple of the external screw thread of a kind of stage clip, it comprises 3 millimeters armouring galvanic couples of diameter of phi, the stainless steel pillar, compensating wire, spiral compression spring, the spring cutting ferrule, hex bolts seat and aviation socket, the armouring galvanic couple is at stainless steel pillar front end, armouring galvanic couple measuring junction connects with two compensating wires respectively in the stainless steel pillar through two galvanic couple silks, the compensating wire output terminal is drawn from the aviation socket, the hex bolts seat is at the end with externally threaded threaded line pipe a hexagon head to be set, O-ring seal at the threaded line pipe overcoat, at the middle part of hex bolts seat one through hole is arranged, the tail end of stainless steel pillar and aviation socket are fixed together, it is characterized in that: the armouring galvanic couple is to be welded on stainless steel pillar front end and sealing between the two, spring cutting ferrule and spiral compression spring are enclosed within outside the stainless steel pillar, spring cutting ferrule and stainless steel pillar weld together, the hex bolts cover for seat is outside the stainless steel pillar, the two ends of spiral compression spring withstand on an end and the hex bolts seat of spring cutting ferrule respectively, between the inboard and stainless steel pillar of hex bolts seat O-ring seal are installed and are pushed down by the through hole casting die that is enclosed within the stainless steel pillar.
2, the fixed armoured thermocouple of stage clip screw thread according to claim 1, it is characterized in that: the hex head end at the hex bolts seat has an inner bolt hole, said through hole casting die is to have externally threaded threaded line pipe, end at threaded line pipe is being fixed hexagon head, and this threaded line pipe is screwed in the inner bolt hole of hex bolts seat.
3, the fixed armoured thermocouple of stage clip screw thread according to claim 1, it is characterized in that: the through hole casting die is laminated on a side of the threaded line pipe of hex bolts seat, and spiral compression spring via through holes casting die withstands on the hex bolts seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200520024785.2U CN2816771Y (en) | 2005-09-01 | 2005-09-01 | External compressed-spring screw-fixing type armoured thermal electric coupler |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200520024785.2U CN2816771Y (en) | 2005-09-01 | 2005-09-01 | External compressed-spring screw-fixing type armoured thermal electric coupler |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2816771Y true CN2816771Y (en) | 2006-09-13 |
Family
ID=36996581
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200520024785.2U Expired - Fee Related CN2816771Y (en) | 2005-09-01 | 2005-09-01 | External compressed-spring screw-fixing type armoured thermal electric coupler |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2816771Y (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103323051A (en) * | 2013-05-13 | 2013-09-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Compound feeling component used for aircraft engine performance test |
| CN106953471A (en) * | 2017-05-24 | 2017-07-14 | 合肥巨动力***有限公司 | Hybrid powder motor stator winding temperature measurement structure |
| CN109612595A (en) * | 2017-09-29 | 2019-04-12 | 富满仪器与控制设备有限公司 | Thermocouple set with expansion pipe |
| CN110823390A (en) * | 2018-08-10 | 2020-02-21 | 日本特殊陶业株式会社 | Temperature sensor |
-
2005
- 2005-09-01 CN CN200520024785.2U patent/CN2816771Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103323051A (en) * | 2013-05-13 | 2013-09-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Compound feeling component used for aircraft engine performance test |
| CN106953471A (en) * | 2017-05-24 | 2017-07-14 | 合肥巨动力***有限公司 | Hybrid powder motor stator winding temperature measurement structure |
| CN109612595A (en) * | 2017-09-29 | 2019-04-12 | 富满仪器与控制设备有限公司 | Thermocouple set with expansion pipe |
| CN110823390A (en) * | 2018-08-10 | 2020-02-21 | 日本特殊陶业株式会社 | Temperature sensor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: SHANXI TAIGANG STAINLESS STEEL CO., LTD. Free format text: FORMER OWNER: TAIYUAN IRON AND STEEL (GROUP) CO LTD Effective date: 20070629 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20070629 Address after: 030003 No. 2, sharp lawn, Taiyuan City, Shanxi Province Patentee after: Shanxi Taigang Stainless Steel Co., Ltd. Address before: 030003 No. 2, sharp lawn, Taiyuan City, Shanxi Province Patentee before: Taiyuan Iron & Steel (Group) Co., Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20060913 Termination date: 20140901 |
|
| EXPY | Termination of patent right or utility model |