VARIABLE INLET GUIDE VANE FOR TURBOMACHINE, TURBOMACHINE INCLUDING VARIABLE INLET GUIDE VANE AND METHOD - Patent application

Abstract

The variable inlet guide vane arrangement includes a disk-shaped member and an annular member coaxial with the disk-shaped member and forming a unit with the disk-shaped member. A set of variable inlet guide vanes are pivotally mounted between the disk-shaped member and the annular member. Each variable inlet guide vane includes a first pivot pin and a second pivot pin. The first pivot pin is pivotally supported by a first bearing housed in the disk-shaped member and the second pivot pin is pivotally supported by a second bearing housed in the annular member.

Description

[Technical field]

[0001] The present disclosure relates to the field of turbomachines, particularly, but not exclusively, to centrifugal compressors and the like. In particular, the present disclosure relates to variable inlet guide vanes for turbomachines, such as centrifugal compressors, and methods of mounting and installing variable inlet guide vanes on turbomachines. [Background technology]

[0002] A turbomachine typically includes a flow path for a fluid that includes an inlet, one or more impellers arranged to rotate within a casing, and an outlet. In a compressor, such as a centrifugal compressor, mechanical power is used to rotate the impeller and compress the fluid, while in an expander, the compressed fluid expands, rotating the impeller to generate mechanical power.

[0003] Some turbomachines, such as centrifugal compressors, include Variable Inlet Guide Vanes (IGVs) located at the inlet of the first, or most upstream, impeller. The geometry of the inlet guide vanes can be controlled and varied to maximize the efficiency of the turbomachine as the operating conditions of the turbomachine change, e.g., as the rotational speed increases or decreases relative to the design operating point.

[0004] An actuation system or systems are provided to act on each inlet guide vane simultaneously and vary the inclination of each inlet guide vane as required. The variable inlet guide vanes and associated actuation systems are complex mechanical components that must be assembled within the turbomachine casing, typically between the inlet plenum and the inlet side of the first impeller. Summary of the Invention [Problem to be solved by the invention]

[0005] It would be beneficial to simplify the variable IGV and associated actuation systems to make them easier and quicker to assemble.

[0006] According to one aspect, to overcome or mitigate the shortcomings of current art variable IGV systems, disclosed herein is a variable inlet guide vane arrangement for a turbomachine comprising in combination a disk-shaped member and an annular member coaxial with the disk-shaped member and forming a unit therewith, wherein a set of variable inlet guide vanes are pivotally mounted between the disk-shaped member and the annular member.

[0007] Each variable inlet guide vane includes a first pivot pin and a second pivot pin. Each first pivot pin is pivotally supported by a first bearing or bushing housed in the disk-shaped member, and each second pivot pin is supported by a second bearing or bushing housed in the annular member. The first and second pivot pins of each variable inlet guide vane commonly define a pivot axis that may be parallel to the axes of the disk-shaped member and the annular member.

[0008] Each variable inlet guide vane includes an aft portion integral with the pivot pin and movable about the axis of the pivot pin relative to the disk-shaped member and the annular member, and at least some of the variable inlet guide vanes include leading portions that are stationary relative to the disk-shaped member and the annular member.

[0009] The disk-like member, the annular member, and the variable inlet guide vanes disposed therebetween may be assembled as a single unit, assembly, or device and tested prior to installation in the turbomachine, which may then be installed as a subassembly in the turbomachine for simple and quick installation.

[0010] The disk-shaped member and the annular member may be fastened together by threads or other fastening or connecting members.

[0011] In embodiments disclosed herein, each variable inlet guide vane may be a so-called flap variable IGV. In such embodiments, each variable IGV may comprise a leading portion that is stationary relative to the disk-shaped member and the annular member and forms a leading edge of the inlet guide vane. Each variable IGV may further include an aft portion that forms a trailing edge of the inlet guide vane. The aft portion is integral with a first pivot pin and a second pivot pin. The aft portion of each inlet guide vane is rotatable about an axis of the first pivot pin and a second pivot pin relative to the disk-shaped member and the annular member.

[0012] According to a further aspect, disclosed herein is a turbomachine, in particular a centrifugal compressor, comprising a casing and at least one impeller rotatably supported within the casing, the turbomachine further comprising an inlet plenum and a variable IGV device, as generally described above, coaxially disposed with the impeller and positioned between the inlet plenum and the inlet of the impeller.

[0013] According to a further aspect, disclosed herein is a method of assembling a variable inlet guide vane for a turbomachine, the method comprising: mounting a set of first bearings on the disc-like member; mounting a pair of second bearings to the annular member; and rigidly connecting the disk-shaped member and the annular member with a plurality of variable inlet guide vanes housed therebetween, each variable inlet guide vane including a first pin supported for rotation in a first bearing and a second pin supported for rotation in a second bearing, each variable inlet guide vane including an aft portion integral with the pivot pin and movable about an axis of the pivot pin relative to the disk-shaped member and the annular member, and at least some of the variable inlet guide vanes including leading portions that are stationary relative to the disk-shaped member and the annular member.

[0014] The method may further include the steps of testing the variable IGV device or subassembly thus formed, and finally installing the variable IGV device in a turbomachine. [Brief description of the drawings]

[0015] Reference will now be made briefly to the accompanying drawings, in which: [Figure 1] FIG. 1 is a partial cross-sectional view of a centrifugal compressor including a variable IGV device according to the present invention. [Figure 1A] FIG. 1A is an enlarged detail of FIG. [Diagram 2] FIG. 2 is an axonometric view of the variable IGV device from the side facing the inlet plenum. [Diagram 3] FIG. 3 is an axonometric view of the device of FIG. 2 seen from the side facing the impeller. [Figure 4] FIG. 4 is a cross-sectional view of the variable IGV device including the axis of the variable IGV device. [Diagram 5] FIG. 5 is a cross-sectional view taken along line VV of FIG. [Figure 6] FIG. 6 is a cross-sectional view taken along line VI-VI of FIG. [Figure 7] FIG. 7 is a flow chart of a method according to the present disclosure. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0016] A novel structure for a variable inlet guide vane arrangement is disclosed herein. To simplify the design, assembly, and testing of the variable IGV arrangement, the vanes are pivotally mounted between two coaxial components, thus forming a single unit or assembly including the two coaxial components and the variable inlet guide vanes disposed therebetween. The unit may further include an actuation system for controlling the angular displacement of the inlet guide vanes.

[0017] The unit including the variable inlet guide vane, the two coaxial components, and the actuation system can be assembled and tested prior to insertion into the turbomachine as a single subassembly of the turbomachine, thus making assembly, testing, and installation in the turbomachine quicker and easier.

[0018] Referring now to the drawings, Figure 1 and an enlarged view of Figure 1A show a cross-sectional view of a centrifugal compressor including variable inlet guide vanes assembled as a single unit according to the present disclosure. The compressor 1 of Figure 1 is shown as a non-limiting exemplary embodiment of a turbomachine in which the novel variable inlet guide vanes of the present disclosure can be used. Those skilled in the art of turbomachines will understand that the compressor may differ substantially from the example shown in Figure 1. Those skilled in the art of turbomachines will also understand that the inlet guide vanes disclosed herein may also be used in different types of turbomachines, such as expanders or turbines.

[0019] The compressor 1 includes a casing 3 with an inlet 5 and an outlet 7. In the exemplary embodiment of Figure 1, the casing includes a barrel 3A and a front closure 3B in a vertically split arrangement. In other embodiments, the casing can be a horizontally split casing, with the two casing sections joined along a plane parallel to the axis of rotation of the compressor.

[0020] A shaft 11 is supported for rotation about axis AA within the casing 3. One or more compressor impellers are mounted on the shaft 11 for co-rotation therewith. In other embodiments, the impellers may be configured as stacked impellers, for example with a central tie rod.

[0021] 1, the compressor 1 comprises a first upstream impeller 13 and a second downstream impeller 15. A first diaphragm 17 is disposed around the first impeller 13 and a second diaphragm 19 is disposed around the second impeller 19. The number of impellers and their arrangement are given as a non-limiting example.

[0022] The gas flow path extends from the compressor inlet 5 through the inlet plenum 21, the first impeller 13 and the second impeller 15 towards the compressor outlet 7. A variable inlet guide vane arrangement 23 is disposed between the inlet plenum 21 and the suction or inlet side 13A of the first impeller 13. Details of the arrangement 23 are disclosed below with reference to Figures 2, 3, 4, 5 and 6.

[0023] The variable inlet guide vane arrangement 23 comprises a plurality of inlet guide vanes 25 arranged circumferentially about an axis AA of the arrangement 23. When mounted on the compressor 1, the axis AA of the arrangement 23 coincides with the axis of rotation AA of the shaft 11.

[0024] In the illustrated embodiment, each variable inlet guide vane 25 includes a leading portion 27 and an aft portion 29, as best shown in Figure 5. The leading portion 27 defines a leading edge 25L of the respective variable inlet guide vane 25, and the aft portion 29 defines a trailing edge 25T of the variable inlet guide vane 25. As best shown in Figure 5, the shape of the inlet guide vanes 25 may vary from one vane to the other about the axis AA. In some embodiments, one or several additional variable inlet guide vanes 25X that include an aft portion 29X but no leading portion may be added to the set of variable inlet guide vanes 25.

[0025] As best shown in Figures 4 and 6, each aft portion 29 of the variable inlet guide vanes 25 includes a first pin 31 and a second pin 33 adapted to pivotally support a respective variable inlet guide vane, and more specifically, the aft portion 29 of the variable inlet guide vane.

[0026] The variable IGV device 23 includes a disk-shaped member 35 and an annular member 37 connected to each other with the inlet guide vanes 25 disposed therebetween. The annular member 37 and the disk-shaped member 35 are rigidly connected to each other by a connecting member 39. In some embodiments, the connecting member 39 may be or include a thread. The connecting member 39 preferably extends through leading portions 27 of at least some of the variable inlet guide vanes, as best shown in Figures 1A, 2 and 5, to prevent them from interfering with the gas path extending through the variable IGV device 23.

[0027] The disk-shaped member 35 has an axial opening 41 and the annular member 37 has an axial opening 43. The two axial openings 41, 43 are coaxial, allowing the compressor shaft to extend therethrough. Furthermore, the axial opening 41 and the flow passage between the variable inlet guide vanes 25 characterize the gas flow path towards the impeller inlet 13A when the device 23 is installed in the compressor 1 (see Figures 1 and 1A).

[0028] The disk-shaped member 35 includes a plurality of first bearings or bushings 45. Each first bearing or bushing 45 receives a respective first pin 31. The annular member 37 includes a plurality of second bearings or bushings 47. Each second bearing or bushing 47 receives a respective second pin 33. Thus, each aft portion 29 of the variable inlet guide vane 25 is supported between the disk-shaped member 35 and the annular member 37 and can rotate about the axis of each coaxial first pin 31 and 33.

[0029] The angular displacement of each rear portion 39 may be controlled by an actuation system 51 (see FIG. 3 ). The actuation system 51 may be housed in a seat 52 formed in the side of the disc-shaped member 35 facing opposite the annular member 37.

[0030] In some embodiments, as best shown in Figure 3, the actuation system 51 includes a connector 53 for connection to a servo actuator or the like (not shown). The connector 53 is hinged to a ring 55 coaxial with the disk-shaped member 35 and the annular member 37. The ring 55 is capable of angular displacement about the axis AA of the device 23. The ring 55 is drivably coupled to the first pin 31 of each aft portion of the variable inlet guide vanes 25 by connecting levers 57, 59. The actuation system 51 is thus adapted to control the simultaneous rotation of each aft portion 29 of the variable inlet guide vanes 25.

[0031] Thus, the bearings or bushings 45, 47, disc-shaped member 35, annular member 37 and actuation system 51 are combined into a single unit or subassembly that can be assembled separately from the compressor 1. Once assembled, the apparatus 23 can be tested and finally installed in the compressor 1.

[0032] The variable IGV device 23 is accommodated within the compressor 1 in a position such that the inlet guide vanes 25 are located within an annular opening fluidly connecting the inlet plenum 21 to the suction side 13A of the first impeller 13. In the embodiment of FIG. 1, the disk-shaped member 35 is accommodated in a seat formed in the fixed diaphragm 17, more specifically in an annular seat 18 provided on the surface of the diaphragm 17 facing the inlet plenum 21. Once mounted, the annular member 37 of the variable IGV device 23 can be at least partially accommodated within a seat 20 formed in a forward portion of the casing 3, which in the embodiment shown in the drawings is characterized by a forward closure 3B.

[0033] FIG. 7 shows a flow chart summarizing a method for assembling and installing the inlet guide vanes in a compressor.

[0034] The method includes the steps of mounting a first bearing 45 on the disk-shaped member 35 (step 101) and mounting a second bearing 47 on the annular member 37 (step 102). Steps 101 and 102 can be performed in any order or simultaneously. The method further includes the step of rigidly connecting the disk-shaped member 35 and the annular member 37 to each other (step 103) with the variable inlet guide vanes 25 housed therebetween. Each variable inlet guide vane 25 has a first pin 31 housed for rotation in the respective first bearing 45 and a second pin 33 housed for rotation in the respective second bearing 47. Thus, the disk-shaped member 35, the annular member 37 and the variable inlet guide vanes 25 form a unit or subassembly. An actuation system 51 can be mounted on the back of the disk-shaped member 35 (step 104). The subassembly or unit thus assembled can be tested (step 105) and then introduced and installed in the compressor 1 (step 106).

[0035] The order of operations described above may be modified such that some of the steps are performed in reverse order. For example, the actuation system 51 may be installed with the inlet guide vanes 25 attached to the disk-shaped member 35, followed by the first pin 31 installed in the first bushing or bearing 45, and then the annular member 37 may be installed on the disk-shaped member 35 with the second pin 33 installed in the second bearing or bushing 47.

[0036] Exemplary embodiments are disclosed above and illustrated in the accompanying drawings. It will be understood by those skilled in the art that various modifications, omissions, and additions may be made to what is specifically disclosed herein without departing from the scope of the invention as defined in the following claims.

Claims

1. 1. A variable inlet guide vane apparatus for a turbomachine, comprising: A disk-shaped member; an annular member coaxial with the disk-shaped member and forming a unit with the disk-shaped member; a set of variable inlet guide vanes pivotally mounted between said disk-shaped member and said annular member; Equipped with Each variable inlet guide vane includes a first pivot pin and a second pivot pin, each first pivot pin pivotally supported by a first bearing housed in the disk-like member and each second pivot pin pivotally supported by a second bearing housed in the annular member; each variable inlet guide vane includes an aft portion integral with the pivot pin and movable about the axis of the pivot pin relative to the disk-shaped member and the annular member, and at least some of the variable inlet guide vanes include leading portions that are stationary relative to the disk-shaped member and the annular member.

2. The apparatus of claim 1 , further comprising a plurality of connecting members rigidly connecting said disk-shaped member and said annular member to one another to form said unit.

3. The apparatus of claim 2 , wherein each connecting member extends through a respective leading portion of one of the variable inlet guide vanes.

4. 4. The apparatus of claim 1, wherein the disk-shaped member has a first side facing the annular member and a second side facing an opposite side of the annular member, and an actuation system for controlling the angular displacement of the variable inlet guide vanes is disposed on a seat on the second side of the disk-shaped member.

5. 1. A turbomachine, comprising: A casing; at least one impeller rotatably supported within the housing; The entrance plenum, A variable inlet guide vane device according to any one of claims 1 to 4, arranged coaxially with the impeller between the inlet plenum and the inlet of the impeller; The turbomachine comprising:

6. The turbomachine of claim 5 , wherein the turbomachine is a centrifugal compressor.

7. 7. A turbomachine according to claim 5 or 6, further comprising a diaphragm stationarily disposed within the casing and coaxial with the impeller, the disk-shaped member being housed within the diaphragm.

8. The turbomachine of claim 7 , wherein the annular member is received in a seat coaxial with the impeller and disposed at a front portion of the casing.

9. 1. A method of assembling a variable inlet guide vane for a turbomachine, comprising the steps of: mounting a first set of bearings on a disk-like member; mounting a pair of second bearings to the annular member; rigidly connecting the disk-shaped member and the annular member together with a plurality of variable inlet guide vanes housed therebetween; each variable inlet guide vane comprises a first pin supported for rotation in the first bearing and a second pin supported for rotation in the second bearing, the disk-shaped member, the annular member and the variable inlet guide vane disposed therebetween form a unit, each variable inlet guide vane comprises an aft portion integral with the pivot pin and movable about an axis of the pivot pin relative to the disk-shaped member and the annular member, and at least some of the variable inlet guide vanes include leading portions that are stationary relative to the disk-shaped member and the annular member.

10. 10. The method of claim 9, further comprising mounting an actuation system to a seat on the second side of the disk-shaped member for controlling angular displacement of the variable inlet guide vanes, and connecting each variable inlet guide vane to the actuation system.

11. The method of claim 9 or 10, further comprising mounting the unit on a turbomachine.

12. The method of claim 11 , wherein the turbomachine is a centrifugal compressor.

13. 13. The method according to claim 11 or 12, wherein the unit is disposed between a stationary diaphragm of the turbomachine and a forward casing portion of the turbomachine.

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