CN204101109U - Low pressure loss integration movement - Google Patents

Abstract

A low pressure drop integrated movement, including a fuselage, the front end of the fuselage is covered with a shroud, the shroud is a cylindrical structure and the inner side of the shroud is provided with 8 shrouds, The deflector vanes are distributed in an annular array around the center of the cylindrical circular section of the deflector, and a low-pressure chamber is provided between the deflector and the fuselage. The beneficial effect is that the pressure loss of the flow meter is reduced; the volume is small, and the integral structure is convenient for disassembly and assembly.

Description

Low pressure loss integrated movement

technical field

The utility model relates to the field of flowmeters, in particular to a turbine flowmeter movement.

Background technique

The gas turbine flowmeter is one of the most widely used flow meters at home and abroad. It reflects the flow rate by measuring the speed of the turbine placed in the measured fluid. The gas turbine flowmeter has the advantages of high measurement accuracy, good repeatability, and wide measurement range. However, due to the backward structural design of the movement, the overall optimization of the watch body is not in place, which may easily lead to a large pressure loss on the whole machine. Such as DN50 caliber gas turbine, under normal circumstances, the pressure loss at the upper limit of the range can reach 1.5kPa or even higher. Such a large pressure loss not only increases the energy consumption of the transmission during the gas transmission process, but also affects The air distribution behind the meter will have adverse effects.

Due to the mechanical movable parts of the gas turbine flowmeter, it is easy to wear and tear, so it needs to be maintained regularly. Generally, the meter body of a gas turbine flowmeter is a split assembly structure, and the various parts of the movement are fixed in the meter body separately. The whole machine must be disassembled for maintenance and repair, and after replacing parts, it needs to be re-tested before it can be used. Therefore, it brings great difficulties to the site. The whole machine must be disassembled and returned, and the whole machine must be calibrated, which affects the normal measurement work and greatly increases the maintenance cost in the later period.

Contents of the invention

The purpose of the utility model is to solve the above-mentioned problems, and to design a low pressure loss integrated movement. The specific design scheme is:

A low pressure drop integrated movement, including a fuselage, the front end of the fuselage is covered with a shroud, the shroud is a cylindrical structure and the inner side of the shroud is provided with 8 shrouds, The deflector vanes are distributed in an annular array around the center of the cylindrical circular section of the deflector, and a low-pressure chamber is provided between the deflector and the fuselage.

An impeller is installed in the fuselage, and an impeller shaft is installed on the rear side of the impeller. A shaft sleeve is sleeved on the impeller shaft and the impeller shaft is fixed by a front bearing and a rear bearing. The front bearing and the rear bearing Both are fixed on the bearing seat, and the front and rear ends of the bearing seat are equipped with fixed shaft glands, and the impeller shaft passes through the fixed shaft gland at the front end and is connected with the impeller through lock nuts.

The width of the low-pressure cavity between the fuselage and the shroud is 3-5mm.

The rear side of the fuselage is equipped with a rear fixing seat, and the rear fixing seat is equipped with a rear cover through fixing bolts, and a magnetic block is installed in the rear fixing seat, and the magnetic block is connected with the rear cover located on the rear cover. At the front, one side of the rear fixing seat is provided with a lubricating oil injection hole.

The number of the magnetic blocks is multiple, and the multiple magnetic blocks are distributed in a circular array, and the magnetic blocks are embedded on the magnetic signal sending disk, and the magnetic signal sending disk is connected to the back seal The cover is rotatably connected, and the magnetic signal sending disc is fixedly connected with the impeller shaft.

The beneficial effects of the low pressure loss integrated movement obtained through the above-mentioned technical solution of the utility model are:

Reduce the pressure loss of the flowmeter; small size, one-piece structure for easy disassembly and assembly.

Description of drawings

Fig. 1 is a schematic structural view of the low pressure loss integrated movement described in the utility model;

Fig. 2 is a side view semi-sectional structural schematic diagram of the low pressure loss integrated movement described in the utility model; in the figure, 1, the fuselage; 2, the guide cover; 3, the guide vane; 4, the low pressure chamber; 5, the impeller ; 6, impeller shaft; 7, shaft sleeve; 8, front bearing; 9, rear bearing; 10, bearing seat; 11, fixed shaft gland; 12, rear fixed seat; 13, rear cover; 14, magnetic block; 15. Lubricating oil injection hole; 16. Inlaid magnetic signal sending plate.

Detailed ways

Below in conjunction with accompanying drawing, the utility model is described in detail.

Fig. 1 is a structural schematic diagram of the low-pressure loss integrated movement described in the utility model; Fig. 2 is a side view half-section structural diagram of the low-pressure loss integrated movement described in the utility model, as shown in Fig. 1 and Fig. 2 , a A low pressure loss integrated movement, comprising a fuselage 1, the front end of the fuselage 1 is covered with a shroud 2, the shroud 2 is a cylindrical structure and the inner side of the shroud 2 is provided with 8 The deflectors 3 are distributed in an annular array around the center of the cylindrical circular section of the deflector 2 , and a low-pressure chamber 4 is provided between the deflector 2 and the fuselage 1 .

An impeller 5 is installed in the fuselage 1, and an impeller shaft 6 is installed on the rear side of the impeller 5. A shaft sleeve 7 is sleeved on the impeller shaft 6, and the impeller shaft 6 is carried by a front bearing 8 and a rear bearing 9. fixed, the front bearing 8 and the rear bearing 9 are fixed on the bearing housing 10, the front and rear ends of the bearing housing 10 are equipped with fixed shaft glands 11, and the impeller shaft 6 runs through the fixed shaft gland 11 at the front end And it is connected with the impeller 5 through a lock nut.

The width of the low-pressure chamber 4 between the fuselage 1 and the shroud 2 is 3-5mm.

The rear side of the fuselage 1 is equipped with a rear fixed seat 12, and the rear fixed seat 12 is equipped with a rear cover 13 by a fixing bolt, and a magnetic block 14 is installed in the described rear fixed seat 12, and the magnetic block 14 is connected with the Located in front of the rear cover 13 , one side of the rear fixing base 12 is provided with a lubricating oil injection hole 15 .

The number of the magnetic blocks 14 is multiple, and the plurality of magnetic blocks 14 are distributed in a circular array, and the magnetic blocks 14 are embedded in the magnetic signal sending disk 16, and the magnetic signal sending disk 16 and the magnetic signal sending disk 16 are embedded The rear cover 13 is rotatably connected, and the magnetic signal sending disk 16 is fixedly connected to the impeller shaft 6 .

The air deflector 2 is fixedly connected with the body 1 by four fixing screws. When the gas passes through the flowmeter, it is firstly shaped by the air deflector 2. The air deflector 2 cooperates with the design of 8 streamlined deflectors 3, and the measured gas Perform rectification. The rectified gas to be measured blows the impeller 5, and there is a low-pressure chamber 4 of about 3-5 mm between the shroud 2 and the impeller 5. When the fluid flows through, the low-pressure chamber 4 forms a very small low-pressure space , It plays a back-suction effect on the rotating mechanism of the impeller 5, which reduces the overall pressure loss very well. The rotation of the impeller 5 drives the inlaid magnetic signal sending disc 16 to rotate together through the impeller shaft 6, and several magnetic blocks 14 inlaid on the sending disc rotate periodically, and the rotation signal is converted into a detectable electrical signal through an external sensor , sent to the processing circuit, and finally complete the whole process of signal acquisition.

The above-mentioned technical solutions only embody the preferred technical solutions of the technical solutions of the present utility model, and some changes that may be made by those skilled in the art to some parts thereof reflect the principles of the present utility model and belong to the protection scope of the present utility model within.

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).