CN204101109U - Low pressure loss integration movement - Google Patents
Low pressure loss integration movement Download PDFInfo
- Publication number
- CN204101109U CN204101109U CN201420591807.2U CN201420591807U CN204101109U CN 204101109 U CN204101109 U CN 204101109U CN 201420591807 U CN201420591807 U CN 201420591807U CN 204101109 U CN204101109 U CN 204101109U
- Authority
- CN
- China
- Prior art keywords
- low pressure
- kuppe
- fuselage
- pressure loss
- impeller
- 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.)
- Expired - Lifetime
Links
- 230000010354 integration Effects 0.000 title claims abstract description 16
- 210000004907 gland Anatomy 0.000 claims description 7
- 239000010687 lubricating oil Substances 0.000 claims description 4
- 239000003921 oil Substances 0.000 claims description 4
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 6
- 239000012530 fluid Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000009931 harmful effect Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
Landscapes
- Measuring Volume Flow (AREA)
Abstract
A kind of low pressure loss integration movement, comprise fuselage, the front end sleeve of described fuselage has kuppe, described kuppe is tubular structure and the inner side of described kuppe is provided with 8 flow deflectors, described flow deflector is circular array distribution centered by the center of circle of described kuppe tubular round section, is provided with low pressure chamber between described kuppe and fuselage.Its beneficial effect is: reduce flowmeter crushing; Volume is little, and integral structure is convenient to dismounting.
Description
Technical field
The utility model relates to field of flow meters, particularly a kind of turbo flow meter movement.
Background technology
Gas turbine meter is one of domestic and international most popular flow instrument, and it is the size reflecting flow by measuring the rotating speed being placed in the turbine of detected fluid.The advantages such as it is high, reproducible that gas turbine meter has measuring accuracy, and measurement range is wide.But because the structural design of movement falls behind, the optimization for table body entirety is not in place, easily causes the crushing of complete machine bigger than normal.As DN50 bore gas-turbine, generally can reach 1.5kPa at range upper limit crushing even higher, so large crushing, not only in gas transport process, adds transmission energy consumption, and produces harmful effect for distribution after table on some low pressure process flow process pipeline.
Because gas turbine meter exists mechanical movable parts, cause easy wearing and tearing, regular maintaining need be carried out to it.General gas flow turbo flow meter table body is split type package assembly, and movement all parts is separately fixed in table body, must dismantle complete machine and just can carry out maintenance, repair, and changes and need to re-start calibrating after parts and could use.Therefore bring very large difficulty to scene, complete machine dismounting must be returned, and must demarcate by complete machine, have impact on normal gage work, considerably increase the maintenance cost in later stage.
Summary of the invention
The purpose of this utility model is to solve the problem, and devises a kind of low pressure loss integration movement.Specific design scheme is:
A kind of low pressure loss integration movement, comprise fuselage, the front end sleeve of described fuselage has kuppe, described kuppe is tubular structure and the inner side of described kuppe is provided with 8 flow deflectors, described flow deflector is circular array distribution centered by the center of circle of described kuppe tubular round section, is provided with low pressure chamber between described kuppe and fuselage.
In described fuselage, impeller is installed, the rear side of described impeller is provided with impeller axle, on described impeller axle, cover has axle sleeve and described impeller axle is fixed by front bearing, rear bearing, described front bearing, rear bearing are all fixed on bearing seat, the rear and front end of described bearing seat is all provided with stationary shaft gland, and described impeller axle is run through the stationary shaft gland of front end and is connected with described impeller by set nut.
Between described fuselage and kuppe, the width of low pressure chamber is 3-5mm.
The rear side of described fuselage is provided with rear holder, and described rear holder is provided with rear seal-cover by set bolt, and be provided with magnetic patch in described rear holder and described magnetic patch and the front being positioned at described rear seal-cover, the side of described rear holder is provided with lubricating oil oil hole.
The quantity of described magnetic patch is multiple, and described multiple magnetic patch circular array distribution, and described magnetic patch is embedded on magnetic signal sender set, described edge magnetic signal sender set and described rear seal-cover are rotationally connected, and described edge magnetic signal sender set is fixedly connected with described impeller axle.
The low pressure loss integration movement obtained by technique scheme of the present utility model, its beneficial effect is:
Reduce flowmeter crushing; Volume is little, and integral structure is convenient to dismounting.
Accompanying drawing explanation
Fig. 1 is the structural representation of low pressure loss described in the utility model integration movement;
Fig. 2 is that the side-looking of low pressure loss described in the utility model integration movement partly cuts open structural representation; In figure, 1, fuselage; 2, kuppe; 3, flow deflector; 4, low pressure chamber; 5, impeller; 6, impeller axle; 7, axle sleeve; 8, front bearing; 9, rear bearing; 10, bearing seat; 11, stationary shaft gland; 12, rear holder; 13, rear seal-cover; 14, magnetic patch; 15, lubricating oil oil hole; 16, magnetic signal sender set is inlayed.
Embodiment
Below in conjunction with accompanying drawing, the utility model is specifically described.
Fig. 1 is the structural representation of low pressure loss described in the utility model integration movement; Fig. 2 is that the side-looking of low pressure loss described in the utility model integration movement partly cuts open structural representation, as shown in Figure 1 and Figure 2, a kind of low pressure loss integration movement, comprise fuselage 1, the front end sleeve of described fuselage 1 has kuppe 2, described kuppe 2 is in tubular structure and the inner side of described kuppe 2 is provided with 8 flow deflectors 3, and described flow deflector 3 is circular array distribution centered by the center of circle of described kuppe 2 tubular round section, is provided with low pressure chamber 4 between described kuppe 2 and fuselage 1.
In described fuselage 1, impeller 5 is installed, the rear side of described impeller 5 is provided with impeller axle 6, on described impeller axle 6, cover has axle sleeve 7 and described impeller axle 6 is fixed by front bearing 8, rear bearing 9, described front bearing 8, rear bearing 9 are all fixed on bearing seat 10, the rear and front end of described bearing seat 10 is all provided with stationary shaft gland 11, and described impeller axle 6 is run through the stationary shaft gland 11 of front end and is connected with described impeller 5 by set nut.
Between described fuselage 1 and kuppe 2, the width of low pressure chamber 4 is 3-5mm.
The rear side of described fuselage 1 is provided with rear holder 12, described rear holder 12 is provided with rear seal-cover 13 by set bolt, be provided with magnetic patch 14 in described rear holder 12 and described magnetic patch 14 and the front being positioned at described rear seal-cover 13, the side of described rear holder 12 is provided with lubricating oil oil hole 15.
The quantity of described magnetic patch 14 is multiple, and described multiple magnetic patch 14 circular array distribution, and described magnetic patch 14 is embedded in magnetic signal sender set 16, described edge magnetic signal sender set 16 is rotationally connected with described rear seal-cover 13, and described edge magnetic signal sender set 16 is fixedly connected with described impeller axle 6.
Be fixedly connected with fuselage 1 by kuppe 2 by four gib screws, when gas is by flowmeter, first through the shaping of kuppe 2, kuppe 2 coordinates the design of 8 streamlined flow deflectors 3, carries out rectification to gas to be measured.Gas to be measured after rectification blows impeller 5, to have an appointment between kuppe 2 and impeller 5 low pressure chamber 4 of 3-5mm simultaneously, as fluid flows therethrough, the low-voltage space that described low pressure chamber 4 one-tenth one is minimum, a back suction effect is play to impeller 5 rotating mechanism, well reduces overall crushing.The impeller axle 6 that rotates through of impeller 5 drives edge magnetic signal sender set 16 together to rotate, send out some magnetic patch 14 that inquiry is inlayed periodically to rotate, by external sensor, this turn signal is changed into the electric signal that can detect, be sent to treatment circuit, the whole process that final complete signal gathers.
Technique scheme only embodies the optimal technical scheme of technical solutions of the utility model; those skilled in the art all embody principle of the present utility model to some variations that wherein some part may be made, and belong within protection domain of the present utility model.
Claims (5)
1. a low pressure loss integration movement, comprise fuselage (1), it is characterized in that, the front end sleeve of described fuselage (1) has kuppe (2), described kuppe (2) is in tubular structure and the inner side of described kuppe (2) is provided with 8 flow deflectors (3), described flow deflector (3) is circular array distribution centered by the center of circle of described kuppe (2) tubular round section, is provided with low pressure chamber (4) between described kuppe (2) and fuselage (1).
2. according to the low pressure loss integration movement described in claim 1, it is characterized in that, impeller (5) is installed in described fuselage (1), the rear side of described impeller (5) is provided with impeller axle (6), the upper cover of described impeller axle (6) have axle sleeve (7) and described impeller axle (6) by front bearing (8), rear bearing (9) is fixed, described front bearing (8), rear bearing (9) is all fixed on bearing seat (10), the rear and front end of described bearing seat (10) is all provided with stationary shaft gland (11), described impeller axle (6) is run through the stationary shaft gland (11) of front end and is connected with described impeller (5) by set nut.
3., according to the low pressure loss integration movement described in claim 1, it is characterized in that, between described fuselage (1) and kuppe (2), the width of low pressure chamber (4) is 3-5mm.
4. according to the low pressure loss integration movement described in claim 2, it is characterized in that, the rear side of described fuselage (1) is provided with rear holder (12), described rear holder (12) is provided with rear seal-cover (13) by set bolt, be provided with magnetic patch (14) in described rear holder (12) and described magnetic patch (14) and the front being positioned at described rear seal-cover (13), the side of described rear holder (12) is provided with lubricating oil oil hole (15).
5. according to the low pressure loss integration movement described in claim 4, it is characterized in that, the quantity of described magnetic patch (14) is multiple, and described multiple magnetic patch (14) circular array distribution, and described magnetic patch (14) is embedded on magnetic signal sender set (16), described edge magnetic signal sender set (16) and described rear seal-cover (13) are rotationally connected, and described edge magnetic signal sender set (16) is fixedly connected with described impeller axle (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420591807.2U CN204101109U (en) | 2014-10-14 | 2014-10-14 | Low pressure loss integration movement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420591807.2U CN204101109U (en) | 2014-10-14 | 2014-10-14 | Low pressure loss integration movement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204101109U true CN204101109U (en) | 2015-01-14 |
Family
ID=52269528
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420591807.2U Expired - Lifetime CN204101109U (en) | 2014-10-14 | 2014-10-14 | Low pressure loss integration movement |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204101109U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105156898A (en) * | 2015-07-09 | 2015-12-16 | 罗美特（上海）自动化仪表股份有限公司 | Intelligent flow measurement centralized control device |
-
2014
- 2014-10-14 CN CN201420591807.2U patent/CN204101109U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105156898A (en) * | 2015-07-09 | 2015-12-16 | 罗美特（上海）自动化仪表股份有限公司 | Intelligent flow measurement centralized control device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103884504A (en) | Axial force bearing test structure of elastic foil dynamic pressure gas thrust bearings | |
| CN204101109U (en) | Low pressure loss integration movement | |
| WO2013004951A3 (en) | Device and method for measuring blade tip passage times in a turbomachine | |
| CN202928632U (en) | V-shaped inner cone flowmeter | |
| CN204476567U (en) | It is a kind of that for monitoring, engine interior is total, the bleed mechanism of static pressure pressure ratio signal | |
| CN202350755U (en) | Detection device for detecting valve seat sealing surface and valve guide pipe of engine | |
| CN102322901A (en) | Vertical Woltmann water meter | |
| CN202101701U (en) | Vertical helix type water meter | |
| CN101545818B (en) | Turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure | |
| CN201908767U (en) | Buffer-type water turbine runner | |
| CN201926603U (en) | Cavitation test device for testing material properties | |
| CN203685670U (en) | Combined structure of turbine blade and pump blade | |
| CN203534640U (en) | Internal fluid drive device of helical vane type small-diameter water meter | |
| CN103776496A (en) | Turbofan flow sensor | |
| Schubert et al. | Source mechanisms of acoustic emissions as an indicator of injury during a full scale fatigue test of a wind turbine rotor blade | |
| CN202255470U (en) | Wireless digital monitoring flowmeter | |
| CN102384770A (en) | Flow sensor for water source well | |
| CN201016756Y (en) | Gas turbine flow-meter | |
| CN105784430A (en) | Novel vacuum sampling pump | |
| CN201772955U (en) | Streamline ultrasonic wave heat quantity meter flow channel | |
| CN204101096U (en) | Compact high-precision gas turbo flow meter | |
| CN105444820A (en) | V-cone flowmeter | |
| CN204388925U (en) | Flow-guiding structure before a kind of gas meter | |
| CN202793221U (en) | Instrument is beaten in adjustment of equipment shaft coupling | |
| CN202756272U (en) | Slurry pump |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |