Patent Grant
10280938
This application claims priority to French application Ser. No. FR 1061391, filed Dec. 31, 2010, the entire disclosure of which is incorporated herein by this reference.
The invention relates to centrifugal motorcompressor units and, more particularly, to centrifugal compressor units of the integrated type in which the compressor and a motor means of driving the compressor are mounted in a common casing that is sealed against the gas handled by the compressor.
A conventional integrated compressor unit comprises a motor means, generally consisting of an electric drive motor, and a centrifugal compressor comprising one or more compression stages depending on the application.
Each compression stage comprises a bladed impeller mounted on a driven shaft driven by a rotor which is itself driven by the motor.
In certain applications, and in particular for low-pressure applications, it has been proposed for use to be made of blades with variable pitch vanes so as to modify the work developed by the compression stage to suit the gas flow rate.
In order to modify the orientation of the vanes, use is made of mechanical devices, for example by fitting the vanes with crown gears driven by worm-type devices.
A motor external to the casing is then used to operate the mechanical device that controls the orientation of the vanes. Such an arrangement entails making holes in the body of the rotary machine and the consequential use of sealing devices. Now, providing holes in the casing of a compressor considerably limits the range in which the compressor can be used, which range remains dedicated to low, or sometimes medium, pressures, which means to say pressures of below around 20 bar.
It is an object of the invention therefore to alleviate this disadvantage and to propose an integrated motorcompressor unit with variable aerodynamic profile, which means to say one capable of modifying the flow of gas within the compression stages, and of doing so over a broader range of pressures.
The invention therefore proposes a compressor unit comprising at least one motor driving the rotation of a rotor and at least one compression stage comprising a set of bladed impellers mounted on a driven shaft the rotation of which is driven by the rotor, the ensemble comprising the motor and the or each compressor being mounted in a common casing that is gastight with respect to the gas handled by the compressor unit.
According to one general feature of this compressor unit, at least one of the compression stages comprises at least one aerodynamic member for regulating the angle of incidence of the flow of gas through the said stage and a motor for controlling the said regulating member mounted in the common casing. For preference, the regulating member is able to vary the flow angle of gas arriving at a bladed impeller, or leaving a bladed impeller. According to one first embodiment alternative, the member is capable of varying the angle of incidence of the flow of gas arriving at at least one bladed impeller. According to another embodiment variant, the member is capable of varying the flow angle of gas leaving a bladed impeller, for example progressing towards a diffuser.
Because the motor that controls the aerodynamic member is incorporated into the casing, the holes in the casing through which the mechanical regulating member passes can be dispensed with, so that the casing therefore remains sealed allowing the motorcompressor unit to operate at higher pressures.
It has been found in particular that, thanks to such an arrangement, the operating range of the motorcompressor unit could be extended out to values of the order of 60 to 80 bar.
According to another feature, the regulating member comprises a vane arranged across a diameter of a gas passage in the compression stage. The regulating member may for example comprise a number of radial vanes, each of a length shorter than or equal to half the diameter of the gas passage. The vanes can thus be actuated simultaneously for example by mechanical devices such as one or more crown gears driven by devices of the worm type. For preference, the regulating member is configured so that it is possible to obtain at least three different angles of incidence or of departure of gaseous flow towards a bladed impeller or from a bladed impeller.
According to yet another feature, the motorcompressor unit comprises between one and three compression stages, preferably one compression stage, at least one of the said stages being provided with the regulating member.
When the compressor unit comprises several compression stages, provision may be made for the flow to be modified by means of an aerodynamic member provided at each stage.
Each regulating stage comprises, in succession, in the direction in which the handled gas flows, a gas supply zone, a bladed compression impeller and a diffuser. The regulating member may then be positioned upstream of the bladed impeller.
As an alternative, it may be arranged in the diffuser.
Another variant involves simultaneously installing a regulating member upstream of the compression stage and a regulating member in the diffuser.
According to yet another feature, the motorcompressor unit further comprises an electronic control unit external to the casing and connected to the control motor by supply and control cables that pass through the casing at fluidtight lead-throughs.
Other objects, features and advantages of the invention will become apparent from reading the following description, given solely by way of nonlimiting example, and made with reference to the attached drawings, in which:
The motorcompressor unit illustrated in
As can be seen, the motorcompressor unit thus comprises a single compression stage consisting of the centrifugal bladed impeller 4 which draws in a gas which is delivered from a supply pipe 5 in order to increase its pressure and deliver it at outlet 5′.
In the embodiment depicted, the rotor 2 is supported by two end bearings 6 and 7. Such is also the case of the driven shaft 3 which is likewise supported by two end bearings 8 and 9. Thus, with this arrangement, the rotor 2 and the driven shaft 3 are connected by a flexible coupling 10.
However, it would not constitute a departure from the scope of the invention if the rotor and the driven shaft were to be connected by a fixed coupling. In such a case, one of the bearings such as 7 and 8 could be omitted.
However, the arrangement depicted is advantageous because it considerably simplifies the assembly of the compressor unit by, in particular, eliminating the problems of aligning the rotor with the driven shaft.
It may also be seen that the motorcompressor unit is also provided with a thrust bearing 11 that limits the axial movement of the driven shaft 3 under the action of the rotation of the impeller 4.
Finally, the assembly, which means to say the motor 1 and the compression stage, is arranged in a common casing 12 which is sealed against the gas handled by the compressor. In other words, the motor 1 here is at the intake pressure of the motorcompressor unit.
This figure shows the gas intake orifice 5 via which the gas to be compressed is drawn in in the direction of the arrow F, and the impeller 4 which actually compresses the gas in order to deliver it, downstream, to a diffuser D in which the gas is slowed down in order to increase its pressure before it is delivered at outlet.
Upstream of the impeller 4, the compressor is provided with a regulating member, referenced 13, produced in the form of a vane mounted across a diameter of a gas passage 14 running between the intake orifice 5 and the impeller 4. This vane constitutes an aerodynamic element which makes it possible to control the angle of the flow and keep it optimum over a wide range of flow rates. As will be seen, this vane 13 is mounted on a control rod 15 which is turned by a control motor 16, for example a stepping motor incorporated into the motorcompressor, which means to say arranged inside the common casing 12. The motor 16 is electrically powered from outside the motorcompressor and is operated by a central control unit (not depicted) which causes the motor to turn and accordingly orients the vane 13 in the passage 14 in such a way as to shift the operating curve of the motorcompressor.
Of course, the supply and control cables that connect the control motor and the central control unit pass through the casing 12 at lead-throughs (not depicted) that are sealed against the gas handled by the motorcompressor in such a way as to maintain a level of sealing that is far superior to the seals required at the penetrations for the mechanical devices according to the state of the art, when the motor is located outside the casing.
It will be noted that the compression stage comprises, in succession, between the inlet 5 and the outlet 5′, a supply zone A, the centrifugal impeller 4 and the diffuser D. It will be noted that the aerodynamic member 13 here is positioned upstream of the impeller 4. It would also be possible, according to the variant illustrated in
With reference to
In particular, in terms of the developed work, starting out from an original position (curve a) in which the vane 13 extends across the overall axis of the flow passage of gas through the compressor, it is possible, by varying the angular position of the vane, to modify the angle of the gaseous flow and thereby modify the flow rate for the same pressure value.
In other words, it is found that modifying the angle of incidence of the gaseous flow allows the operating curve of the compressor to be shifted translationally, thereby adapting its operating range.
Moreover, the motor 1 and the compression stage 3 are arranged in one and the same casing 12 that is sealed against the gas being handled, which means that the inside of the motorcompressor unit, particularly the motor 1 and at least the compression stage 3, are immersed in the gas that is being handled, at the pressure of the gas entering via the supply pipe 5. The inside of the motorcompressor has no shaft output sealing packing because the shafts bearing the motor 1 and bearing the bladed impeller 4, and the bearings that support them, are fully contained within the casing. The motorcompressor unit has only rotary seals subjected to small pressure differences, for example seals of the labyrinth seal type. No leak of process gas to the atmosphere can therefore occur, because the openings in the casing are confined to the gas supply pipe 5, the gas outlet pipe 5′, the lead-throughs for the cables that control and power the motors 1 and 16, and the periphery of a cover (not depicted) that allows the various components to be inserted into the casing. Further, in order to limit ventilation losses, the motor 1 is subject to the intake pressure set up at the supply pipe 5. A circulation of gas can moreover be set up in order to cool it.
One particularly advantageous application of the invention is in gas transfer stations in which the pressure ratios that have to be developed between the intake and delivery sides are relatively small, notably below 2, and for which the motorcompressor units are preferably single-stage units or, in general, comprise fewer than three stages. Specifically, for this type of application, it is often desirable to have a relatively wide range of flow rates so that small or large flow rates can be offered.
However, of course, any other application in which it is desirable to have a relatively wide range of flow rates may also be envisaged.
It will moreover be noted that the use of an aerodynamic member for controlling the angle of incidence of the gas flow is advantageous for motorcompressor units comprising from 1 to 3 compression stages. However, such a member may advantageously be installed in single-stage motorcompressor units. However, when using a multi-stage compressor, the aerodynamic member can be mounted either on the first compression stage or on all the stages.
As indicated earlier, the aerodynamic member can be mounted either at the inlet to the compression bladed impeller, so as to modify the angle of incidence of the gas flow handled by the bladed impeller, or at the diffuser so as to modify the deceleration of the gas and thereby modify the operating range. It is also possible, according to another embodiment, to provide one aerodynamic regulating member upstream or at the inlet of the bladed impeller or, in other words, upstream of the compression stage, and one regulating member in the diffuser.
| Number | Date | Country | Kind |
|---|---|---|---|
| 10 61391 | Dec 2010 | FR | national |
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| Entry |
|---|
| EPO Form 1503, FR dated Aug. 10, 2011, French Search Report for FR1061391. |
| Number | Date | Country | |
|---|---|---|---|
| 20120171056 A1 | Jul 2012 | US |
