Method for starting a multi-stage axial flow compressor, air compression equipment, and gas turbine equipment

Abstract

To suppress generation of an air separation phenomenon in an activation process.SOLUTION: A method for activating a multistage axial flow compressor executes an activation initial step when a rotation speed of a rotor is lower than a first rotation speed N1 that is smaller than a rated rotation speed Nr, and an activation latter step when the rotation speed of the rotor is larger than a second rotation speed N2 that is lower than the rated rotation speed Nr and is higher than the first rotation speed N1. In the activation initial step, an angle of a first stator blade is set to a first stator blade initial angle C1x, and an angle of the second stator blade is set to a second stator blade initial angle C2x. In the activation latter step, the angle of the first stator blade is set to a first stator blade latter angle C1z, and the angle of the second stator blade is set to a second stator blade latter angle C2z. A value ΔC2 obtained by subtracting the second stator blade latter angle C2z from the second stator blade initial angle C2x is larger than a value ΔC1 obtained by subtracting the first stator blade latter angle C1z from the first stator blade initial angle C1x.SELECTED DRAWING: Figure 3

Description

[Technical Field]

[0001] The present invention relates to a start-up method for a multistage axial compressor that supplies compressed air to a combustor of a gas turbine, an air compression facility equipped with a multistage axial compressor, and a gas turbine facility. [Background technology]

[0002] An example of a compressor that supplies compressed air to a combustor of a gas turbine is a multi-stage axial compressor disclosed in the following Patent Document 1. This multi-stage axial compressor includes a rotor that rotates about an axis, a casing that covers the rotor, a plurality of stator vane rows, an inlet guide vane row, a stator vane angle changer, and a guide vane angle changer.

[0003] The rotor has a rotor shaft centered on the axis, and a plurality of moving blade rows attached to the rotor shaft. The plurality of moving blade rows are aligned in the axial direction, which is the direction in which the axis extends. The plurality of moving blade rows have a plurality of moving blades aligned in the circumferential direction about the axis. The plurality of stator blade rows are attached to a casing. Each of the plurality of stator blade rows is arranged adjacent to one of the plurality of moving blade rows on the axial downstream side. Each of the plurality of stator blade rows has a plurality of stator vanes aligned in the circumferential direction. The inlet guide vane row is arranged axially upstream of a first moving blade row, which is the axially most upstream of the plurality of moving blade rows. This inlet guide vane row has a plurality of inlet guide vanes aligned in the circumferential direction.

[0004] Here, of the multiple stator vane rows, the stator vane row located most upstream along the axis is referred to as the first stator vane row, the stator vane row arranged adjacent to the first stator vane row on the axial downstream side is referred to as the second stator vane row, and the stator vane row arranged adjacent to the second stator vane row on the axial downstream side is referred to as the third stator vane row. The stator vane angle changer includes a first stator vane angle changer that changes the angles of multiple first stator vanes constituting the first stator vane row, a second stator vane angle changer that changes the angles of multiple second stator vanes constituting the second stator vane row, and a third stator vane angle changer that changes the angles of multiple third stator vanes constituting the third stator vane row. The guide vane angle changer changes the angles of multiple inlet guide vanes.

[0005] Patent Document 1 describes that, at start-up or the like, the angles of the multiple inlet guide vanes, the angles of the multiple first stator vanes, the angles of the multiple second stator vanes, and the angles of the multiple third stator vanes are changed according to the rotation speed of the rotor. [Prior art documents] [Patent documents]

[0006] [Patent Document 1] Patent No. 5881390 Summary of the Invention [Problem to be solved by the invention]

[0007] In a multi-stage axial flow compressor, during the start-up process when the rotor rotation speed is increasing, the likelihood of air separation occurring on the blades in one of the stages increases, or this air separation may occur temporarily. When air separation occurs, the stationary vane or rotor blade where the air separation occurs vibrates, placing a large load on these blades. For this reason, it is desirable to suppress the occurrence of air separation and operate the multi-stage axial flow compressor stably, even during the start-up process when the rotor rotation speed is increasing.

[0008] Therefore, an object of the present invention is to provide a technique that can suppress the occurrence of air separation even during the start-up process and enable stable operation of a multi-stage axial flow compressor. [Means for solving the problem]

[0013] In order to achieve the above object, a start-up method for a multi-stage axial flow compressor according to another aspect of the present invention is the following start-up method for a multi-stage axial flow compressor. This multi-stage axial compressor includes a rotor that rotates about an axis, a casing that covers the outer periphery of the rotor, receives air from an upstream side that is one side in the axial direction along which the axis extends, and discharges air to a downstream side that is the other side in the axial direction, a plurality of stator vane rows attached to the casing and arranged side by side in the axial direction, and an inlet guide vane row attached to the casing and arranged upstream of the plurality of stator vane rows along the axis. Of the plurality of stator vane rows, the stator vane row located most upstream along the axis forms a first stator vane row, and the stator vane row adjacent to the first stator vane row on the downstream side along the axis forms a second stator vane row. Each of the plurality of stator vane rows has a plurality of stator vanes arranged circumferentially about the axis. The inlet guide vane row has a plurality of inlet guide vanes arranged in the circumferential direction. This multi-stage axial compressor supplies air to a combustor of a gas turbine. In this start-up method, a start-up process from when the rotor begins to rotate until the rotor reaches a rated rotational speed includes an initial start-up phase in which the rotational speed of the rotor is lower than a first rotational speed that is lower than the rated rotational speed, and a later start-up phase in which the rotational speed of the rotor is higher than a second rotational speed that is lower than the rated rotational speed and higher than the first rotational speed. In the initial start-up phase, the angles of the multiple inlet guide vanes are set to a guide vane initial angle, the angles of multiple first stator vanes that are the multiple stator vanes possessed by the first stator vane row are set to a first stator vane initial angle, and the angles of multiple second stator vanes that are the multiple stator vanes possessed by the second stator vane row are set to a second stator vane initial angle. In the later start-up phase, the angles of the multiple inlet guide vanes are set to a guide vane late angle, the angles of the multiple first stator vanes are set to a first stator vane late angle, and the angles of the multiple second stator vanes are set to a second stator vane late angle. During the start-up process, when the rotation speed of the rotor is lower than the first rotation speed, if there is a risk of air separation occurring at at least some of the second stator vanes when the angles of the plurality of inlet guide vanes are set to the guide vane initial angle, the angles of the plurality of first stator vanes are set to the first stator vane assumed initial angle, and the angles of the plurality of second stator vanes are set to the second stator vane assumed initial angle, the guide vane late angle is smaller than the guide vane initial angle, the first stator vane late angle is smaller than the first stator vane initial angle and the first stator vane assumed initial angle, the second stator vane late angle is smaller than the second stator vane initial angle and the second stator vane assumed initial angle, and the second stator vane initial angle is larger than the second stator vane assumed initial angle.

[0014] In this aspect, since the second stator vane initial angle is larger than the second stator vane assumed initial angle, air flows along the second stator vane, and the occurrence of air separation at the second stator vane can be suppressed.

[0015] Here, in the start-up method for a multi-stage axial flow compressor according to the other aspect, a difference between the second stator vane initial angle and the second stator vane assumed initial angle may be 7 to 11°.

[0016] In the start-up method for a multi-stage axial flow compressor according to any one of the above aspects, wherein the second stator vane initial angle is larger than the second stator vane assumed initial angle, the first stator vane initial angle may be smaller than the first stator vane assumed initial angle.

[0017] In this aspect, the first stator vane initial angle is smaller than the first stator vane assumed initial angle, and therefore the axial component of the directional component of the air flow upstream of the second stator vane in the axis direction becomes large, making it possible to suppress the occurrence of ring flow in the region upstream of the second stator vane row in the axis direction.

[0018] In the start-up method for a multi-stage axial flow compressor of the above aspect, the first stator vane initial angle is smaller than the first stator vane assumed initial angle, and a difference between the first stator vane initial angle and the first stator vane assumed initial angle may be 1 to 5°.

[0019] In the start-up method for a multi-stage axial flow compressor according to any one of the above aspects, a value obtained by subtracting the guide vane late angle from the guide vane initial angle may be greater than a value obtained by subtracting the first stator vane late angle from the first stator vane initial angle.

[0020] In the start-up method for a multi-stage axial flow compressor according to any one of the above aspects, in the initial start-up step, angles of the plurality of inlet guide vanes may be maintained at the initial guide vane angle, angles of the plurality of first stator vanes may be maintained at the initial first stator vane angle, and angles of the plurality of second stator vanes may be maintained at the initial second stator vane angle, throughout an initial rotation speed range in which the rotation speed of the rotor is lower than the first rotation speed.

[0021] In the start-up method for a multi-stage axial flow compressor according to any one of the above aspects, in the late start-up step, angles of the plurality of inlet guide vanes may be maintained at the guide vane late angle, angles of the plurality of first stator vanes may be maintained at the first stator vane late angle, and angles of the plurality of second stator vanes may be maintained at the second stator vane late angle, throughout an entire late rotation speed range in which the rotation speed of the rotor is greater than the second rotation speed and equal to or less than the rated rotation speed.

[0022] In any of the above-described aspects of the start-up method for a multi-stage axial flow compressor, a start-up intermediate step may be executed during the start-up process when the rotational speed of the rotor is equal to or greater than the first rotational speed and equal to or less than the second rotational speed. In this case, in the start-up intermediate step, when the rotational speed of the rotor is the first rotational speed, the angles of the multiple inlet guide vanes are set to the guide vane initial angle, and when the rotational speed of the rotor becomes greater than the first rotational speed, the angles of the multiple inlet guide vanes are gradually reduced as the rotational speed of the rotor increases, and when the rotational speed of the rotor is at the second rotational speed, the angles of the multiple inlet guide vanes are set to the guide vane late angle. When the rotational speed of the rotor is at the first rotational speed, the angles of the multiple first stator vanes are set to the first stator vane initial angle, and when the rotational speed of the rotor is greater than the first rotational speed, the angles of the multiple first stator vanes are gradually reduced as the rotational speed of the rotor increases, and when the rotational speed of the rotor is at the second rotational speed, the angles of the multiple first stator vanes are set to the first stator vane late angle. When the rotation speed of the rotor is the first rotation speed, the angles of the plurality of second stator vanes are set to the second stator vane initial angle, and when the rotation speed of the rotor becomes greater than the first rotation speed, the angles of the plurality of second stator vanes are gradually reduced as the rotation speed of the rotor increases, until when the rotation speed of the rotor becomes the second rotation speed, the angles of the plurality of second stator vanes are set to the second stator vane late angle.

[0023] In the start-up method for a multi-stage axial flow compressor according to any of the above aspects, a plurality of stator vanes constituting each of the stator vane rows downstream of the second stator vane row along the axis may be fixed vanes. In either case, the angles of the plurality of stator vanes constituting each of the stator vane rows downstream of the second stator vane row along the axis are not changed.

[0024] In order to achieve the above object, an air compression facility according to one aspect of the invention includes a multistage axial compressor that supplies compressed air to a combustor of a gas turbine, and a control device that controls the multistage axial compressor. the multi-stage axial flow compressor includes: a rotor that rotates about an axis; a casing that covers an outer circumferential side of the rotor, into which air flows in from an upstream side that is one side in the axial direction along which the axis extends, and through which air is discharged to a downstream side that is the other side in the axial direction; a plurality of stator vane rows that are attached to the casing and arranged side by side in the axial direction; an inlet guide vane row that is attached to the casing and arranged upstream of the plurality of stator vane rows in the axial direction; a first stator vane angle changer that changes angles of a plurality of first stator vanes that constitute a first stator vane row that is located most upstream along the axis among the plurality of stator vane rows; a second stator vane angle changer that changes angles of a plurality of second stator vanes that constitute a second stator vane row that is adjacent to the first stator vane row on the downstream side along the axis among the plurality of stator vane rows; a guide vane angle changer that changes angles of a plurality of inlet guide vanes that constitute the inlet guide vane row; and a revolution speed meter that detects the rotation speed of the rotor. When the tachometer detects a rotation speed lower than a first rotation speed that is lower than the rated rotation speed during a startup process from when the rotor starts to rotate until the rotor reaches a rated rotation speed, the control device instructs the guide vane angle changer to set the angles of the plurality of inlet guide vanes to a guide vane initial angle, instructs the first stator vane angle changer to set the angles of the plurality of first stator vanes to a first stator vane initial angle, and instructs the second stator vane angle changer to set the angles of the plurality of second stator vanes to a second stator vane initial angle. When the rotation speed meter detects a rotation speed that is higher than a second rotation speed that is lower than the rated rotation speed and higher than the first rotation speed, during the start-up process, the guide vane angle changer is instructed to set the angles of the plurality of inlet guide vanes to a guide vane late angle, the first stator vane angle changer is instructed to set the angles of the plurality of first stator vanes to a first stator vane late angle, and the second stator vane angle changer is instructed to set the angles of the plurality of second stator vanes to a second stator vane late angle. During the start-up process, when the rotation speed of the rotor is lower than the first rotation speed, if the angles of the plurality of inlet guide vanes are set to the guide vane initial angle, the angles of the plurality of first stator vanes are set to the first stator vane assumed initial angle, and the angles of the plurality of second stator vanes are set to the second stator vane assumed initial angle, there is a risk that air separation will occur in at least a part of the plurality of second stator vanes, The guide vane late angle is smaller than the guide vane initial angle, and the first stator vane late angle is smaller than the first stator vane initial angle. and the first stator vane assumed initial angle and the second stator vane late angle is smaller than the second stator vane initial angle and the second stator vane assumed initial angle Smaller, The second stator vane initial angle is larger than the second stator vane assumed initial angle.

[0025] In the air compression facility of the above aspect, the first stator vane initial angle may be an angle that is smaller than the guide vane initial angle by 14 to 18° in terms of angle difference.

[0026] In order to achieve the above object, a gas turbine facility according to one aspect of the invention comprises: The air compression facility includes any one of the above aspects, the combustor that burns fuel in the compressed air from the multi-stage axial compressor to generate combustion gas, and a turbine that is driven by the combustion gas. [Effects of the Invention]

[0027] According to one aspect of the present invention, the occurrence of air separation phenomenon can be suppressed, and a multi-stage axial flow compressor can be stably operated. [Brief explanation of the drawings]

[0028] [Figure 1] 1 is a schematic diagram of a gas turbine in a first embodiment according to the present invention. FIG. [Figure 2] 1 is a cross-sectional view of a main portion of a multi-stage axial flow compressor according to a first embodiment of the present invention. FIG. [Figure 3] FIG. 3 is an explanatory diagram of a map showing the relationship between the rotation speed of the rotor and the angle of the variable vane in the first embodiment according to the present invention. [Figure 4] FIG. 4 is an explanatory diagram showing the state of air flow around the second stator vane during an assumed operating mode. [Figure 5] FIG. 4 is an explanatory diagram showing the state of airflow around the second stator vane during an actual operation mode in the first embodiment according to the present invention. [Figure 6] FIG. 10 is an explanatory diagram of a map showing the relationship between the rotation speed of the rotor and the angle of the variable vane in the second embodiment according to the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0029] Hereinafter, various embodiments of a gas turbine facility according to the present invention will be described in detail with reference to the drawings.

[0030] "First embodiment" A first embodiment of a gas turbine facility according to the present invention will be described with reference to FIGS.

[0031] 1, the gas turbine facility of this embodiment includes a gas turbine 10 and a control device 90 that controls the gas turbine 10. The gas turbine 10 includes a multi-stage axial compressor 40 (hereinafter simply referred to as the compressor 40) that compresses air A, a combustor 20 that burns fuel F in the compressed air, which is the air A compressed by the compressor 40, to generate combustion gas G, and a turbine 30 that is driven by the combustion gas G.

[0032] The combustor 20 has a combustion liner (or transition piece) 22 in which fuel is burned, and a burner 21 that injects fuel F and compressed air into the combustion liner 22. A fuel line 25 through which the fuel F flows is connected to the combustor 20. A fuel control valve 26 that adjusts the flow rate of the fuel F flowing through the fuel line 25 is provided in the fuel line 25.

[0033] The turbine 30 has a turbine rotor 31 that rotates about an axis Ar, a turbine casing 35 that covers the turbine rotor 31, and a plurality of stator blade rows 37. Hereinafter, the direction in which the axis Ar extends will be referred to as the axial direction Da, one side of this axial direction Da will be referred to as the axial upstream side Dau, and the other side of this axial direction Da will be referred to as the axial downstream side Dad. The circumferential direction relative to the axis Ar will simply be referred to as the circumferential direction Dc. Furthermore, the direction perpendicular to the axis Ar will be referred to as the radial direction Dr, the side of this radial direction Dr that is closer to the axis Ar will be referred to as the radially inner side Dri, and the side of this radial direction Dr opposite the radially inner side Dri will be referred to as the radially outer side Dro.

[0034] The turbine rotor 31 has a rotor shaft 32 extending in an axial direction Da centered on the axis Ar, and a plurality of rotor blade rows 33 attached to the rotor shaft 32. The plurality of rotor blade rows 33 are aligned in the axial direction Da. Each of the plurality of rotor blade rows 33 has a plurality of rotor blades aligned in the circumferential direction Dc. The plurality of stator blade rows 37 are fixed to the turbine casing 35. Each of the plurality of stator blade rows 37 has a plurality of stator blades aligned in the circumferential direction Dc. Each of the plurality of stator blade rows 37 is arranged adjacent to one of the plurality of rotor blade rows 33 on the axial upstream side Dau.

[0035] The multi-stage axial flow compressor 40 is disposed on the axial upstream side Dau of the turbine 30. As shown in Fig. 1 and Fig. 2 , the multi-stage axial flow compressor 40 includes a compressor rotor 41 that rotates about an axis Ar, a compressor casing 45 that covers the compressor rotor 41, a plurality of stator vane rows 50, an inlet guide vane row 52, ​​a stator vane angle changer 55, and a guide vane angle changer 56.

[0036] The compressor rotor 41 has a rotor shaft 42 extending in the axial direction Da centered on the axis Ar, and a plurality of rotor blade rows 43 attached to the rotor shaft 42. The rotor blade rows 43 are aligned in the axial direction Da. Each of the rotor blade rows 43 has a plurality of rotor blades 44 aligned in the circumferential direction Dc. Here, of the rotor blade rows 43, the rotor blade row 43 located most upstream on the axial direction Dau is referred to as the first rotor blade row 43a, the rotor blade row 43 located adjacent to the axial downstream side Dad of the first rotor blade row 43a is referred to as the second rotor blade row 43b, and the rotor blade row 43 located adjacent to the axial downstream side Dad of the second rotor blade row 43b is referred to as the third rotor blade row 43c. The inlet guide vane row 52 is positioned axially upstream Dau of the first rotor blade row 43a. The inlet guide vane row 52 has a plurality of inlet guide vanes 53 aligned in the circumferential direction Dc.

[0037] The compressor casing 45 has an outer casing 48o, an inner casing 48i, and a plurality of struts 49. The inner casing 48i is cylindrical and centered on the axis Ar, and covers a portion of the rotor shaft 42 on the axially upstream side Dau of the inlet guide vane row 52. The outer casing 48o is cylindrical and centered on the axis Ar, and is spaced radially outward Dro from the inner casing 48i and the rotor shaft 42, covering the outer circumferential side of the inner casing 48i and the outer circumferential side of the rotor shaft 42. The plurality of struts 49 are aligned in the circumferential direction Dc between the inner casing 48i and the outer casing 48o. The plurality of struts 49 connect the inner casing 48i and the outer casing 48o. The compressor casing 45 has an open end on the axially upstream side Dau. This opening forms the suction port 46i. The edge of the axial upstream side Dau of the inner casing 48i forms the edge of the radially inner side Dri of the suction port 46i. In addition, the edge of the axial upstream side Dau of the outer casing 48o forms the edge of the radially outer side Dro of the suction port 46i. The end of the axial downstream side Dad of the compressor casing 45 is also open. This opening forms the discharge port 46o. An air compression flow path 47, through which air flowing in from the suction port 46i flows, is formed between the inner circumferential surface of the outer casing 48o and the outer circumferential surface of the inner casing 48i and the outer circumferential surface of the rotor shaft 42.

[0038] The multiple stator vane rows 50 are arranged in the air compression flow path 47 and attached to the compressor casing 45. Each of the multiple stator vane rows 50 has multiple stator vanes 51 arranged in the circumferential direction Dc. The multiple stator vane rows 50 are arranged in the axial direction Da. Here, of the multiple stator vane rows 50, the stator vane row 50 located most upstream along the axial direction Dau is referred to as the first stator vane row 50a, the stator vane row 50 arranged adjacent to the first stator vane row 50a on the axial downstream side Dad is referred to as the second stator vane row 50b, and the stator vane row 50 arranged adjacent to the second stator vane row 50b on the axial downstream side Dad is referred to as the third stator vane row 50c. Furthermore, the multiple stator vanes 51 constituting the first stator vane row 50a are referred to as the first stator vanes 51a, the multiple stator vanes 51 constituting the second stator vane row 50b are referred to as the second stator vanes 51b, and the multiple stator vanes 51 constituting the third stator vane row 50c are referred to as the third stator vanes 51c.

[0039] Each of the multiple stator vane rows 50 is arranged adjacent to the axial downstream side Dad of any one of the multiple rotor blade rows 43. Specifically, the first stator vane row 50a is arranged adjacent to the axial downstream side Dad of the first rotor blade row 43a, the second stator vane row 50b is arranged adjacent to the axial downstream side Dad of the second rotor blade row 43b, and the third stator vane row 50c is arranged adjacent to the axial downstream side Dad of the third rotor blade row 43c.

[0040] The stator vane angle changer 55 includes a first stator vane angle changer 55a that changes the angles of the multiple first stator vanes 51a, a second stator vane angle changer 55b that changes the angles of the multiple second stator vanes 51b, and a third stator vane angle changer 55c that changes the angles of the multiple third stator vanes 51c. Therefore, the multiple first stator vanes 51a, the multiple second stator vanes 51b, and the multiple third stator vanes 51c are all variable stator vanes. The guide vane angle changer 56 changes the angles of the multiple inlet guide vanes 53. Note that hereinafter, the first stator vane 51a, the second stator vane 51b, the third stator vane 51c, and the inlet guide vane 53 may be simply referred to as variable vanes.

[0041] As shown in FIG. 2, each of the blade angle changers 55, 56 includes a blade shaft 57 extending from the radially outer end Dro of the variable blade toward the radially outer side Dro, and a rotation mechanism 58 that rotates the blade shaft 57 around the central axis Av of the blade shaft 57. The blade shaft 57 is provided on all variable blades that make up the variable blade row. The rotation mechanism 58 rotates the blade shafts 57 of all variable blades that make up the variable blade row at the same rotation angle. When the rotation angle of the variable blades changes, the flow passage area between two variable blades adjacent in the circumferential direction Dc among the multiple variable blades that make up the variable blade row changes. An angle command indicating the angle of the variable blade is sent from the control device 90 to the blade angle changers 55, 56. Upon receiving this angle command, the blade angle changers 55, 56 drive the angles of all variable blades that make up the variable blade row to the angle indicated by the angle command. Here, the angle of the variable blade is the angle of rotation around the blade axis 57 from the reference position, and the angle is expressed as smaller as the variable blade is opened. As explained above, the "blade angle" in the specification and claims is an angle expressed as smaller as the blade is opened.

[0042] As shown in FIG. 1 , the compressor rotor 41 and the turbine rotor 31 are located on the same axis Ar and are connected to each other to form a gas turbine rotor 11. For example, a rotor of a generator GEN is connected to this gas turbine rotor 11. A tachometer 15 that detects the rotation speed of the gas turbine rotor 11 or the rotor of the generator GEN is provided on the gas turbine rotor 11 or the rotor of the generator GEN. An intermediate casing 13 is connected to the end of the axial downstream side Dad of the compressor casing 45. A turbine casing 35 is connected to the end of the axial downstream side Dad of the intermediate casing 13. The compressor casing 45, the intermediate casing 13, and the turbine casing 35 are connected to each other to form a gas turbine casing 12. The combustor 20 described above is provided in the intermediate casing 13. The intermediate casing 13 connects the compressor casing 45 and the turbine casing 35 and also serves to guide compressed air flowing out of the compressor 40 into the combustor 20.

[0043] The control device 90 has a reception unit 91 that receives data, signals, and the like from outside, a fuel control unit 92, and an intake control unit 93. The reception unit 91 receives a required output PWd for the gas turbine 10 and signals from various sensors including the tachometer 15. The fuel control unit 92 determines a fuel flow rate according to the required output PWd, etc., and sends a valve angle according to this fuel flow rate to the fuel control valve 26. The intake control unit 93 determines the angles of the multiple inlet guide vanes 53, the angle of the multiple first stator vanes 51a, the angle of the multiple second stator vanes 51b, and the angle of the multiple third stator vanes 51c according to the required output PWd and the rotation speed detected by the tachometer 15. Then, the intake control unit 93 sends the angles of the multiple inlet guide vanes 53 to the guide vane angle changer 56, sends the angles of the multiple first stator vanes 51a to the first stator vane angle changer 55a, sends the angles of the multiple second stator vanes 51b to the second stator vane angle changer 55b, and sends the angles of the multiple third stator vanes 51c to the third stator vane angle changer 55c.

[0044] As described above, the control device 90 controls the angles of the multiple inlet guide vanes 53, the angles of the multiple first stator vanes 51a, the angles of the multiple second stator vanes 51b, and the angles of the multiple third stator vanes 51c. Therefore, the control device 90 also functions as a control device for the multi-stage axial compressor 40. The air compression equipment of this embodiment includes the multi-stage axial compressor 40 and the control device 90.

[0045] During the startup process from when the compressor rotor 41 starts to rotate until the compressor rotor 41 reaches the rated rotation speed Nr, the intake control unit 93 determines the angles of the multiple inlet guide vanes 53, the angles of the multiple first stator vanes 51a, the angles of the multiple second stator vanes 51b, and the angles of the multiple third stator vanes 51c in accordance with the rotation speed of the compressor rotor 41. The intake control unit 93 stores a map that shows the relationship between the angles of the multiple inlet guide vanes 53, the angles of the multiple first stator vanes 51a, the angles of the multiple second stator vanes 51b, and the angles of the multiple third stator vanes 51c and the rotation speed of the compressor rotor 41. Using this map, during the startup process from when the compressor rotor 41 starts to rotate until the compressor rotor 41 reaches the rated rotation speed Nr, the intake control unit 93 determines the angles of the multiple inlet guide vanes 53, the angles of the multiple first stator vanes 51a, the angles of the multiple second stator vanes 51b, and the angles of the multiple third stator vanes 51c in accordance with the rotation speed of the compressor rotor 41.

[0046] The map stored in the intake control unit 93 will be described with reference to Fig. 3. In the map shown in Fig. 3, the horizontal axis represents the rotation speed of the compressor rotor 41, in other words, the rotation speed detected by the rotation speed meter 15, and the vertical axis represents the angle of the variable vanes.

[0047] The angle of the variable vanes varies between an initial rotation speed range, an intermediate rotation speed range, and a later rotation speed range. The initial rotation speed range is a range in which the rotation speed of the compressor rotor 41 is equal to or greater than 0 and less than a first rotation speed N1 which is smaller than the rated rotation speed Nr. The intermediate rotation speed range is a range in which the rotation speed of the compressor rotor 41 is equal to or greater than the first rotation speed N1 and is equal to or less than a second rotation speed N2 which is larger than the first rotation speed N1 and smaller than the rated rotation speed Nr, and is equal to or greater than the first rotation speed N1. The later rotation speed range is a range in which the rotation speed of the compressor rotor 41 is larger than the second rotation speed N2 and is equal to or less than the rated rotation speed Nr.

[0048] The rated rotation speed Nr is, for example, 3600 rpm. The second rotation speed N2 is a rotation speed that is about 80 to 85° of the rated rotation speed Nr, for example, 3000 rpm. The first rotation speed N1 is a rotation speed that is about 65 to 75° of the rated rotation speed Nr, for example, 2500 rpm.

[0049] The angle of the inlet guide vane 53 is the guide vane initial angle IGVx throughout the entire initial rotation speed range, the guide vane mid-stage angle IGVy throughout the intermediate rotation speed range, and the guide vane late stage angle IGVz throughout the entire late rotation speed range. The guide vane late stage angle IGVz is an angle smaller than the guide vane initial angle IGVx by about 15 to 20° in terms of angle difference ΔIGV, for example, an angle smaller by 18° in terms of angle difference ΔIGV. The guide vane mid-stage angle IGVy gradually decreases as the rotation speed of the compressor rotor 41 increases. When the rotation speed of the compressor rotor 41 is the first rotation speed N1, the guide vane mid-stage angle IGVy is the guide vane initial angle IGVx. When the rotation speed of the compressor rotor 41 is the second rotation speed N2, the guide vane mid-stage angle IGVy is the guide vane late stage angle IGVz.

[0050] The angle of the first stator vane 51a is a first stator vane initial angle C1x throughout the initial rotation speed range, a first stator vane mid-phase angle C1y throughout the mid-phase rotation speed range, and a first stator vane late phase angle C1z throughout the late rotation speed range. The first stator vane late phase angle C1z is an angle smaller than the first stator vane initial angle C1x in terms of angle difference ΔC1 of about 12 to 16°, for example, an angle smaller by 14°. The first stator vane late phase angle C1z is an angle smaller than the guide vane late phase angle IGVz in terms of angle difference of about 7 to 11°, for example, an angle smaller by 9°. The first stator vane initial angle C1x is an angle smaller than the guide vane initial angle IGVx in terms of angle difference of about 11 to 15°, for example, an angle smaller by 13°. The first stator vane mid-phase angle C1y gradually decreases as the rotation speed of the compressor rotor 41 increases. The first stator vane mid-phase angle C1y is the first stator vane initial angle C1x when the rotation speed of the compressor rotor 41 is the first rotation speed N1. Also, the first stator vane mid-phase angle C1y is the first stator vane late angle C1z when the rotation speed of the compressor rotor 41 is the second rotation speed N2.

[0051] The angle of the second stator vane 51b is the second stator vane initial angle C2x throughout the initial rotation speed range, the second stator vane mid-phase angle C2y throughout the mid-phase rotation speed range, and the second stator vane late phase angle C2z throughout the late rotation speed range. The second stator vane late phase angle C2z is an angle smaller than the second stator vane initial angle C2x by about 15 to 19°, for example, an angle smaller by 17°. The second stator vane late phase angle C2z is an angle smaller than the guide vane late phase angle IGVz by about 14 to 18°, for example, an angle smaller by 16°. The second stator vane initial angle C2x is an angle smaller than the guide vane initial angle IGVx by about 10 to 14°, for example, an angle smaller by 12°. The second stator vane mid-phase angle C2y gradually decreases as the rotation speed of the compressor rotor 41 increases. When the rotation speed of the compressor rotor 41 is the first rotation speed N1, the second stator vane mid-phase angle C2y is the second stator vane initial angle C2x. When the rotation speed of the compressor rotor 41 is the second rotation speed N2, the second stator vane mid-phase angle C2y is the second stator vane late angle C2z.

[0052] Furthermore, the value ΔC2 (15 to 19°, for example, 17°) obtained by subtracting the second stator vane late angle C2z from the second stator vane initial angle C2x is greater than the value ΔC1 (12 to 16°, for example, 14°) obtained by subtracting the first stator vane late angle C1z from the first stator vane initial angle C1x. In other words, the magnitude relationship between ΔC1 and ΔC2 is ΔC1<ΔC2. Therefore, in the mid-rotation speed range, the angular displacement ΔC2 of the second stator vane 51b is greater than the angular displacement ΔC1 of the first stator vane 51a.

[0053] The angle of the third stator vane 51c is a third stator vane initial angle C3x throughout the entire initial rotation speed range, a third stator vane mid-stage angle C3y in the mid-stage rotation speed range, and a third stator vane late stage angle C3z throughout the entire late rotation speed range. The third stator vane late stage angle C3z is an angle smaller than the third stator vane initial angle C3x by about 5 to 9 degrees, for example, an angle smaller by 7 degrees. The third stator vane late stage angle C3z is an angle smaller than the guide vane late stage angle IGVz by about 14 to 18 degrees, for example, an angle smaller by 16 degrees. The third stator vane initial angle C3x is an angle smaller than the guide vane initial angle IGVx by about 20 to 24 degrees, for example, an angle smaller by 22 degrees. The third stator vane mid-phase angle C3y is the third stator vane initial angle C3x when the rotation speed of the compressor rotor 41 is the first rotation speed N1, and is an angle that gradually decreases as the rotation speed of the compressor rotor 41 increases when the rotation speed of the compressor rotor 41 becomes greater than the first rotation speed N1, and is the third stator vane late angle C3z when the rotation speed of the compressor rotor 41 is the second rotation speed N2. The third stator vane mid-phase angle C3y gradually decreases as the rotation speed of the compressor rotor 41 increases. When the rotation speed of the compressor rotor 41 is the first rotation speed N1, the third stator vane mid-phase angle C3y is the third stator vane initial angle C3x. When the rotation speed of the compressor rotor 41 is the second rotation speed N2, the third stator vane mid-phase angle C3y is the third stator vane late angle C3z.

[0054] Here, the angles of the variable vanes in assumed operating conditions where there is a risk of air separation occurring at the stator vanes will also be described.

[0055] The angle of the inlet guide vane 53 in the assumed operating mode is the same as the angle of the inlet guide vane 53 in the actual operating mode described above, across the entire rotational speed range of the startup process. The angle of the first stator vane 51a in the assumed operating mode is the same as the angle of the first stator vane 51a in the actual operating mode described above, across the entire rotational speed range of the startup process. The angle of the third stator vane 51c in the assumed operating mode is the same as the angle of the third stator vane 51c in the actual operating mode described above, across the entire rotational speed range of the startup process. On the other hand, the angle of the second stator vane 51b in the assumed operating mode is different from the angle of the second stator vane 51b in the actual operating mode described above.

[0056] The angle of the second stator vane 51b in the assumed operating mode is the second stator vane assumed initial angle C2ax throughout the entire initial rotation speed range, the second stator vane assumed mid-phase angle C2ay in the mid-phase rotation speed range, and the second stator vane assumed late phase angle C2az throughout the entire late rotation speed range. This second stator vane assumed late phase angle C2az is the same as the second stator vane assumed late phase angle C2z in the actual operating mode described above. The second stator vane assumed initial angle C2ax is an angle that is approximately 6 to 10° larger in angle difference than the second stator vane assumed late phase angle C2az (= second stator vane late phase angle C2z), for example, an angle that is 8° larger in angle difference. This second stator vane assumed initial angle C2ax is an angle that is approximately 24 to 28° smaller in angle difference than the guide vane initial angle IGVx, for example, an angle that is 26° smaller in angle difference. Furthermore, the second stator vane assumed initial angle C2ax is an angle smaller than the second stator vane initial angle C2x by about 7 to 11°, for example, an angle smaller by 9°. In other words, the second stator vane initial angle C2x is an angle larger than the second stator vane assumed initial angle C2ax by about 7 to 11°, for example, an angle larger by 9°. The second stator vane assumed mid-phase angle C2ay gradually decreases as the rotation speed of the compressor rotor 41 increases. When the rotation speed of the compressor rotor 41 is the first rotation speed N1, the second stator vane assumed mid-phase angle C2ay is the second stator vane assumed initial angle C2ax. When the rotation speed of the compressor rotor 41 is the second rotation speed N2, the second stator vane assumed mid-phase angle C2ay is the second stator vane late phase angle C2z.

[0057] Furthermore, the value ΔC2a (6 to 10°, for example, 8°) obtained by subtracting the second stator vane assumed late angle C2az (= second stator vane late angle C2z) from the second stator vane assumed initial angle C2ax is smaller than the value ΔC1 (12 to 16°, for example, 14°) obtained by subtracting the first stator vane late angle C1z from the first stator vane initial angle C1x. In other words, the magnitude relationship between ΔC2a and ΔC1 is ΔC2a<ΔC1. Therefore, unlike the actual operating mode, in the mid-phase rotation speed range, the angular displacement ΔC2a of the second stator vane 51b is smaller than the angular displacement ΔC1 of the first stator vane 51a.

[0058] In this embodiment, an initial startup step, an intermediate startup step, and a later startup step are executed during the startup process of the compressor 40. The initial startup step is executed when the rotation speed of the compressor rotor 41 during the startup process is lower than the first rotation speed N1, i.e., in the initial rotation speed range. The intermediate startup step is executed when the rotation speed of the compressor rotor 41 during the startup process is equal to or higher than the first rotation speed N1 and equal to or lower than the second rotation speed N2, i.e., in the intermediate rotation speed range. The later startup step is executed when the rotation speed of the compressor rotor 41 during the startup process is higher than the second rotation speed N2, i.e., in the final rotation speed range.

[0059] In each of the initial startup phase, the middle startup phase, and the final startup phase, the intake control unit 93 uses the maps described above to determine the angle of the inlet guide vane 53, the angle of the first stator vane 51a, the angle of the second stator vane 51b, and the angle of the third stator vane 51c according to the rotation speed of the compressor rotor 41. Then, the intake control unit 93 sends the determined angle of the inlet guide vane 53 to the guide vane angle changer 56, the determined angle of the first stator vane 51a to the first stator vane angle changer 55a, the determined angle of the second stator vane 51b to the second stator vane angle changer 55b, and the determined angle of the third stator vane 51c to the third stator vane angle changer 55c. As a result, the angles of the variable vanes become the angles determined by the intake control unit 93.

[0060] In the initial startup phase, as described above, the angle of the inlet guide vane 53 becomes the guide vane initial angle IGVx, the angle of the first stator vane 51a becomes the first stator vane initial angle C1x, the angle of the second stator vane 51b becomes the second stator vane initial angle C2x, and the angle of the third stator vane 51c becomes the first stator vane initial angle C1x.

[0061] As described above, in the intermediate startup phase, the angle of the inlet guide vane 53, the angle of the first stator vane 51a, the angle of the second stator vane 51b, and the angle of the third stator vane 51c each gradually decreases as the rotation speed of the compressor rotor 41 increases.

[0062] In the late startup phase, as described above, the angle of the inlet guide vane 53 becomes the late guide vane angle IGVz, the angle of the first stator vane 51a becomes the late first stator vane angle C1z, the angle of the second stator vane 51b becomes the late second stator vane angle C2z, and the angle of the third stator vane 51c becomes the late first stator vane angle C1z.

[0063] In the assumed operating mode described above, as shown in FIGS. 2 and 4 , during the initial startup process, there is a risk of air separation regions (raps) occurring along at least some of the second stator vanes 51b of the second stator vane row 50b. In these air separation regions (raps), air separates from the blade surfaces of the second stator vanes 51b. When air separation occurs, the stator vane or rotor blade where the air separation occurs vibrates, placing a heavy load on the blade and potentially damaging it. Furthermore, when air separation occurs, the flow rate of air passing between two adjacent blades in the circumferential direction Dc is significantly reduced. Therefore, it is desirable to suppress the occurrence of air separation. The phrase "there is a risk of air separation regions (raps) occurring" refers to cases where air separation regions (raps) are expected to occur in an actual compressor based on factors such as air flow rate and pressure fluctuations, or cases where air separation regions (raps) occur as a result of simulations.

[0064] 5, increasing the angle of the blade where air separation occurs, that is, closing the blade, causes the air to flow along the blade surface, thereby eliminating the air separation phenomenon. Therefore, in this embodiment, the air separation phenomenon is suppressed by increasing the angle of the second stator vane 51b, where air separation occurs in the assumed operating mode. In other words, in this embodiment, the value ΔC2 obtained by subtracting the second stator vane late angle C2z from the second stator vane initial angle C2x is set to be greater than the value ΔC1 obtained by subtracting the first stator vane late angle C1z from the first stator vane initial angle C1x. As a result, the angle of the second stator vane 51b during the initial startup phase is increased, thereby suppressing the air separation phenomenon.

[0065] As described above, in this embodiment, the value ΔC2 obtained by subtracting the second stator vane initial angle C2x from the second stator vane late angle C2z is approximately 12 to 16° larger than the value ΔC1 obtained by subtracting the first stator vane initial angle C1x from the first stator vane late angle C1z. A difference of 12° is the minimum value that suppresses the occurrence of air separation. On the other hand, a difference of 16° is the maximum value that suppresses air separation while keeping the air flow rate within the allowable flow rate. For this reason, it is most preferable that this difference be approximately 14°, which is an intermediate value between 12 and 16°.

[0066] As described above, in this embodiment, the second stator vane initial angle C2x is an angle that is approximately 7 to 11 degrees larger in angle difference than the second stator vane assumed initial angle C2ax. An angle difference of 7 degrees is the minimum value that suppresses the occurrence of air separation. On the other hand, an angle difference of 11 degrees is the maximum value that can suppress the air separation phenomenon while keeping the air flow rate within the allowable flow rate. For this reason, it is most preferable that this angle difference be approximately 9 degrees, which is an intermediate value between 7 and 11 degrees.

[0067] As described above, in this embodiment, the separation phenomenon can be suppressed during the startup process of the compressor 40, and the compressor 40 can be operated stably.

[0068] Second Embodiment A second embodiment of the gas turbine facility according to the present invention will be described with reference to FIG.

[0069] The configuration of the gas turbine facility of this embodiment is the same as the configuration of the gas turbine facility of the first embodiment. Therefore, like the gas turbine facility of the first embodiment, the gas turbine facility of this embodiment also includes a gas turbine 10 and a control device 90. However, in this embodiment, the map stored in the intake control unit 93 of the control device 90 is different from the map in the first embodiment. Therefore, the following mainly describes the map stored in the intake control unit 93 of this embodiment.

[0070] 6, the angle of the inlet guide vane (IGV) 53 in the starting process of this embodiment is the same as the angle of the inlet guide vane (IGV) 53 in the starting process of the first embodiment over the entire rotation speed range of the starting process. Therefore, in this embodiment, the angle of the inlet guide vane (IGV) 53 in the initial rotation speed range is the guide vane initial angle IGVx, the angle of the inlet guide vane (IGV) 53 in the middle rotation speed range is the guide vane middle angle IGVy, and the angle of the inlet guide vane (IGV) 53 in the late rotation speed range is the guide vane late angle IGVz.

[0071] The angle of the second stator vane (C2) 51b in the start-up process of this embodiment is the same as the angle of the second stator vane (C2) 51b in the start-up process of the first embodiment across the entire rotation speed range of the start-up process. Therefore, in this embodiment, the angle of the second stator vane (C2) 51b in the initial rotation speed range is the second stator vane initial angle C2x, the angle of the second stator vane (C2) 51b in the middle rotation speed range is the second stator vane middle angle C2y, and the angle of the second stator vane (C2) 51b in the late rotation speed range is the second stator vane late angle C2z.

[0072] The angle of the third stator vane (C3) 51c in the start-up process of this embodiment is the same as the angle of the third stator vane (C3) 51c in the start-up process of Embodiment 1 across the entire rotation speed range of the start-up process. Thus, in this embodiment, the angle of the third stator vane (C3) 51c in the initial rotation speed range is a third stator vane initial angle C3x, the angle of the third stator vane (C3) 51c in the middle rotation speed range is a third stator vane middle angle C3y, and the angle of the third stator vane (C3) 51c in the late rotation speed range is a third stator vane late angle C3z.

[0073] On the other hand, the angle of the first stator vane (C1) 51a in the start-up process of this embodiment is different from the angle of the first stator vane (C1) 51a in the start-up process of the first embodiment. In this embodiment, the angle of the first stator vane (C1) 51a in the initial rotation speed range is a first stator vane initial angle C1xs that is different from the first stator vane initial angle C1x of the first embodiment. The angle of the first stator vane (C1) 51a in the middle rotation speed range is a first stator vane middle angle C1ys that is different from the first stator vane middle angle C1y of the first embodiment. The angle of the first stator vane (C1) 51a in the late rotation speed range is a first stator vane late angle C1z that is the same as the first stator vane late angle C1z of the first embodiment.

[0074] The first stator vane late angle C1z in this embodiment is an angle smaller than the first stator vane initial angle C1xs by about 9 to 13°, for example, an angle smaller by 11°. In other words, the first stator vane initial angle C1xs is an angle larger than the first stator vane late angle C1z by about 9 to 13°, for example, an angle larger by 11°. This first stator vane initial angle C1xs is an angle smaller than the guide vane initial angle IGVx by about 14 to 18°, for example, an angle smaller by 16° (=45-29). The first stator vane mid-phase angle C1ys gradually decreases as the rotation speed of the compressor rotor 41 increases. When the rotation speed of the compressor rotor 41 is the first rotation speed N1, the first stator vane mid-phase angle C1ys is the first stator vane initial angle C1xs. When the rotation speed of the compressor rotor 41 is the second rotation speed N2, the first stator vane mid-stage angle C1ys is the first stator vane late-stage angle C1z.

[0075] Furthermore, in this embodiment, as in the first embodiment, the value ΔC2 (15 to 19°, for example, 17°) obtained by subtracting the second stator vane late angle C2z from the second stator vane initial angle C2x is greater than the value ΔC1s (9 to 13°, for example, 11°) obtained by subtracting the first stator vane late angle C1z from the first stator vane initial angle C1xs.

[0076] Here, the angles of the variable vanes in the assumed operating mode will also be described.

[0077] The angle of the inlet guide vane (IGV) 53 in the assumed operating mode in this embodiment is the same as the angle of the inlet guide vane 53 in the assumed operating mode in the first embodiment, over the entire rotation speed range of the startup process. Therefore, in this embodiment as well, the angle of the inlet guide vane 53 in the assumed operating mode is the same as the angle of the inlet guide vane 53 in the actual operating mode over the entire rotation speed range of the startup process.

[0078] The angle of the third stator vane (C3) 51c in the assumed operating mode in this embodiment is the same as the angle of the third stator vane 51c in the assumed operating mode in the first embodiment, over the entire rotation speed range of the startup process. Therefore, in this embodiment as well, the angle of the third stator vane 51c in the assumed operating mode is the same as the angle of the third stator vane 51c in the actual operating mode over the entire rotation speed range of the startup process.

[0079] The angle of the first stator vane (C1) 51a in the assumed operating mode in this embodiment is the same as the angle of the first stator vane 51a in the assumed operating mode in the first embodiment across the entire rotation speed range of the startup process. Therefore, in this embodiment, unlike the first embodiment, the angle of the first stator vane 51a in the assumed operating mode is different from the angle of the first stator vane 51a in the actual operating mode. In this embodiment, the assumed first stator vane initial angle C1ax is an angle that is larger than the first stator vane initial angle C1xs by about 1 to 5 degrees, for example, an angle that is larger by 3 degrees. In other words, the first stator vane initial angle C1xs is an angle that is smaller than the assumed first stator vane initial angle C1ax by about 1 to 5 degrees, for example, an angle that is smaller by 3 degrees. Note that the assumed first stator vane initial angle C1ax in this embodiment is the same as the first stator vane initial angle C1x in the first embodiment. In this embodiment, the assumed first stator vane late angle C1az is the same as the first stator vane late angle C1z. Therefore, in this embodiment, the first stator vane assumed mid-term angle C1ay is the same angle as the first stator vane mid-term angle C1y in the first embodiment.

[0080] The angle of the second stator vane (C2) 51b in the assumed operating mode in this embodiment is the same as the angle of the second stator vane 51b in the assumed operating mode in the first embodiment across the entire rotation speed range of the startup process. Therefore, in this embodiment, as in the first embodiment, the angle of the second stator vane 51b in the assumed operating mode is different from the angle of the second stator vane 51b in the actual operating mode. Therefore, in this embodiment, as in the first embodiment, the assumed second stator vane initial angle C2ax is an angle larger than the assumed second stator vane late angle C2az (= second stator vane late angle C2z) by about 6 to 10 degrees, for example, an angle larger by 8 degrees. This assumed second stator vane initial angle C2ax is an angle smaller than the initial guide vane angle IGVx by about 24 to 28 degrees, for example, an angle smaller by 26 degrees. Furthermore, the assumed second stator vane initial angle C2ax is an angle smaller than the initial second stator vane angle C2x by about 7 to 11 degrees, for example, an angle smaller by 9 degrees. In other words, the second stator blade initial angle C2x is an angle that is larger than the second stator blade assumed initial angle C2ax by about 7 to 11° in angle difference, for example, an angle that is larger by 9°.

[0081] Furthermore, the value ΔC2a (6 to 10°, for example, 8°) obtained by subtracting the second stator vane assumed late angle C2az (= second stator vane late angle C2z) from the second stator vane assumed initial angle C2ax is smaller than the value ΔC1s (9 to 13°, for example, 11°) obtained by subtracting the first stator vane late angle C1z from the first stator vane initial angle C1xs. In other words, the magnitude relationship between ΔC2a and ΔC1s is ΔC2a<ΔC1s. Therefore, in the mid-rotation speed range, the angular displacement ΔC2a of the second stator vane 51b is smaller than the angular displacement ΔC1s of the first stator vane 51a.

[0082] Furthermore, the value ΔC2 (15 to 19°, for example, 17°) obtained by subtracting the second stator vane late angle C2z from the second stator vane initial angle C2x is greater than the value ΔC1s (9 to 13°, for example, 11°) obtained by subtracting the first stator vane late angle C1z from the first stator vane initial angle C1xs. In other words, the magnitude relationship between ΔC1s and ΔC2 is ΔC1s<ΔC2. Therefore, unlike the assumed operating mode, in the mid-rotation speed range, the angular displacement ΔC2a of the second stator vane 51b is greater than the angular displacement ΔC1s of the first stator vane 51a.

[0083] As described above, the angle of each variable vane in the assumed operating mode in this embodiment is the same as the angle of each vane in the assumed operating angle in the first embodiment.

[0084] During the startup process, when the angles of each variable vane are set to the angle in the assumed operating mode in this embodiment, that is, the angle of each variable vane is set to the angle in the assumed operating angle in the first embodiment, as described in the first embodiment, air separation occurs in at least some of the second stator vanes 51b that make up the second stator vane row 50b.

[0085] In the first embodiment, the occurrence of air separation is suppressed by increasing the angle of the second stator vane 51b, at which air separation occurs in the assumed operating mode. Increasing the angle of the second stator vane 51b, at which air separation occurs in the assumed operating mode, increases the likelihood that the region where the first rotor blade row 43a and the first stator vane row 50a are located, which is an area on the axially upstream side Dau of the second stator vane row 50b, will become a ring flow region Rrf, as shown in FIG. 2 . In this ring flow region Rrf, the circumferential component Dc of the air flow components is much larger than the axial component, i.e., a ring flow occurs in which the air swirls around the axis Ar. When this ring flow occurs, the intake air flow rate of the compressor 40 decreases significantly.

[0086] Therefore, in this embodiment, as in the first embodiment, the angle of the second stator vane 51b, at which the air separation phenomenon occurs in the assumed operating mode, is increased to suppress the occurrence of this air separation phenomenon, while the first stator vane initial angle C1xs is made smaller than the first stator vane assumed initial angle C1ax (=first stator vane initial angle C1x in the first embodiment) to suppress the occurrence of ring flow.

[0087] In the above embodiment, the third stator vane 51c is a variable stator vane, but it may be a fixed stator vane fixed to the compressor casing 45. In this case, the angle of the third stator vane 51c is not controlled. Therefore, in this case, the third stator vane 51c and all of the stator vanes Dad downstream of the third stator vane 51c along the axis are fixed stator vanes. [Explanation of symbols]

[0088] 10: Gas turbine 11: Gas turbine rotor 12: Gas turbine casing 13: Intermediate casing 15::Tachometer 20: Combustor 21: Burner 22: Combustion tube (tail tube) 25: Fuel line 26: Fuel control valve 30: Turbine 31: Turbine rotor 32: Rotor shaft 33: Moving blade row 35: Turbine casing 37: Stator blade row 40: Multistage axial flow compressor (compressor) 41: Compressor rotor 42: Rotor shaft 43: Moving blade row 43a: First rotor blade row 43b: Second rotor blade row 43c: Third rotor blade row 44: Moving blade 45: Compressor casing 46i: Intake port 46o:Discharge port 47: Air compression channel 48o: Outer casing 48i: Inner casing 49: Strut 50: Stator blade row 50a: First stator blade row 50b: Second stator blade row 50c: Third stator blade row 51: Static wing 51a: First stationary wing 51b:Second stator blade 51c: Third stationary wing 52: Inlet guide vane row 53: Entrance guide wing 55: Variable stator blade angle aircraft 55a: First stator blade angle changer 55b: Second stator blade angle changer 55c: Third stator blade angle change aircraft 56: Guide wing angle changer 57: Wing axis 58: Rotation mechanism 90: Control device 91: Reception 92: Fuel control unit 93: Intake control unit A: Air F:Fuel G: Combustion gas Rap: Air separation region Rrf: Ring flow region PWd: Request output N1: First rotation speed N2: Second rotation speed Nr: Rated rotation speed IGVx: Initial guide vane angle IGVy: Guide wing mid-range angle IGVz: Late guide vane angle C1x, C1xs: Initial angle of first stationary blade C1y, C1ys: First stationary blade intermediate angle C1z: First stationary blade late angle C1ax: First stator vane assumed initial angle C1ay: First stator vane assumed mid-term angle C1az: First stator vane assumed late angle C2x: Second stationary blade initial angle C2y: Second stationary blade mid-term angle C2z: Second stationary blade late angle C2ax: Assumed initial angle of the second stationary blade C2ay: Second stator vane assumed mid-term angle C2az: Second stator vane assumed late angle C3x: Initial angle of third stationary blade C3y: Third stationary blade mid-term angle C3z: Third stationary blade late angle Ar: Axis line Da: Axial direction Dau: Axis upstream side Dad: Downstream of the axis Dc: Circumferential direction Dr: Radial direction Dri: Radial inner direction Dro: Radial outer side

Claims

1. a rotor that rotates around an axis; a casing that covers an outer circumferential side of the rotor, into which air flows from an upstream side that is one side in the axial direction in which the axis extends, and into which air is discharged to a downstream side that is the other side in the axial direction; a plurality of stator blade rows attached to the casing and arranged side by side in the axial direction; an inlet guide vane row attached to the casing and arranged upstream of the plurality of stator vane rows in the axial direction; Equipped with Among the plurality of stator vane rows, the stator vane row located most upstream on the axis line forms a first stator vane row, and the stator vane row adjacent to the first stator vane row on the downstream side of the axis line forms a second stator vane row, Each of the plurality of stator blade rows has a plurality of stator blades arranged in a circumferential direction with respect to the axis, the inlet guide vane row has a plurality of inlet guide vanes aligned in the circumferential direction, 1. A method for starting a multi-stage axial compressor that supplies air to a combustor of a gas turbine, comprising: The start-up process from when the rotor starts to rotate until the rotor reaches the rated rotation speed is as follows: an initial startup process in which the rotation speed of the rotor is lower than a first rotation speed that is lower than the rated rotation speed; a later start-up phase in which the rotational speed of the rotor is greater than a second rotational speed that is smaller than the rated rotational speed and greater than the first rotational speed; Including, in the initial startup step, angles of the plurality of inlet guide vanes are set to a guide vane initial angle, angles of a plurality of first stator vanes that are the plurality of stator vanes possessed by the first stator vane row are set to a first stator vane initial angle, and angles of a plurality of second stator vanes that are the plurality of stator vanes possessed by the second stator vane row are set to a second stator vane initial angle, In the late startup step, the angles of the plurality of inlet guide vanes are set to a guide vane late angle, the angles of the plurality of first stator vanes are set to a first stator vane late angle, and the angles of the plurality of second stator vanes are set to a second stator vane late angle, if, during the start-up process, when the rotation speed of the rotor is lower than the first rotation speed, if the angles of the plurality of inlet guide vanes are set to the guide vane initial angle, the angles of the plurality of first stator vanes are set to the first stator vane assumed initial angle, and the angles of the plurality of second stator vanes are set to the second stator vane assumed initial angle, there is a risk that an air separation phenomenon will occur in at least a part of the plurality of second stator vanes, the guide vane late angle is smaller than the guide vane initial angle, the first stator vane late angle is smaller than the first stator vane initial angle and the first stator vane assumed initial angle, the second stator vane late angle is smaller than the second stator vane initial angle and the second stator vane assumed initial angle, the second stator vane initial angle is greater than the second stator vane assumed initial angle, How to start a multistage axial compressor.

2. In the method for starting the multi-stage axial compressor according to claim 1, a difference between the second stator vane initial angle and the second stator vane assumed initial angle is 7 to 11 degrees; How to start a multistage axial compressor.

3. A method for starting a multi-stage axial compressor according to claim 1 or 2, the first stator vane initial angle is smaller than the first stator vane assumed initial angle; How to start a multistage axial compressor.

4. In the method for starting the multi-stage axial compressor according to claim 3, a difference between the first stator vane initial angle and the first stator vane assumed initial angle is 1 to 5 degrees; How to start a multistage axial compressor.

5. 5. The method for starting a multi-stage axial flow compressor according to claim 1, a value obtained by subtracting the guide vane late angle from the guide vane initial angle is greater than a value obtained by subtracting the first stator vane late angle from the first stator vane initial angle; How to start a multistage axial compressor.

6. 6. The method for starting a multi-stage axial flow compressor according to claim 1, in the initial startup step, throughout an initial rotation speed range in which the rotation speed of the rotor is lower than the first rotation speed, angles of the plurality of inlet guide vanes are maintained at the guide vane initial angle, angles of the plurality of first stator vanes are maintained at the first stator vane initial angle, and angles of the plurality of second stator vanes are maintained at the second stator vane initial angle. How to start a multistage axial compressor.

7. 7. The method for starting a multi-stage axial flow compressor according to claim 1, in the late startup step, throughout a late rotation speed range in which the rotation speed of the rotor is greater than the second rotation speed and equal to or less than the rated rotation speed, angles of the plurality of inlet guide vanes are maintained at the guide vane late angle, angles of the plurality of first stator vanes are maintained at the first stator vane late angle, and angles of the plurality of second stator vanes are maintained at the second stator vane late angle. How to start a multistage axial compressor.

8. The method for starting a multi-stage axial flow compressor according to any one of claims 1 to 7, the startup process includes a startup middle stage in which the rotational speed of the rotor is equal to or higher than the first rotational speed and equal to or lower than the second rotational speed, In the startup intermediate stage step, when the rotation speed of the rotor is the first rotation speed, the angles of the plurality of inlet guide vanes are set to the guide vane initial angle, and when the rotation speed of the rotor becomes greater than the first rotation speed, the angles of the plurality of inlet guide vanes are gradually reduced as the rotation speed of the rotor increases, and when the rotation speed of the rotor becomes the second rotation speed, the angles of the plurality of inlet guide vanes are set to the guide vane final angle; when the rotation speed of the rotor is the first rotation speed, the angles of the plurality of first stator vanes are set to the first stator vane initial angle, and when the rotation speed of the rotor becomes higher than the first rotation speed, the angles of the plurality of first stator vanes are gradually reduced as the rotation speed of the rotor increases, and when the rotation speed of the rotor becomes the second rotation speed, the angles of the plurality of first stator vanes are set to the first stator vane late angle; when the rotation speed of the rotor is the first rotation speed, the angles of the plurality of second stator vanes are set to the second stator vane initial angle, and when the rotation speed of the rotor becomes higher than the first rotation speed, the angles of the plurality of second stator vanes are gradually reduced as the rotation speed of the rotor increases, and when the rotation speed of the rotor becomes the second rotation speed, the angles of the plurality of second stator vanes are set to the second stator vane late angle. How to start a multistage axial compressor.

9. 9. The method for starting a multi-stage axial flow compressor according to claim 1, Among the plurality of stator vane rows, a plurality of stator vanes constituting each of the stator vane rows downstream of the second stator vane row in the axis direction are fixed vanes, In either case, the angles of the plurality of stator vanes constituting each of the stator vane rows downstream of the second stator vane row in the axis direction are not changed. How to start a multistage axial compressor.

10. a multi-stage axial flow compressor for supplying compressed air to a combustor of the gas turbine; a control device for controlling the multistage axial flow compressor; Equipped with The multi-stage axial flow compressor comprises: a rotor that rotates around an axis; a casing that covers an outer circumferential side of the rotor, into which air flows from an upstream side that is one side in the axial direction in which the axis extends, and into which air is discharged to a downstream side that is the other side in the axial direction; a plurality of stator blade rows attached to the casing and arranged side by side in the axial direction; an inlet guide vane row attached to the casing and arranged upstream of the plurality of stator vane rows in the axial direction; a first stator vane angle changer that changes angles of a plurality of first stator vanes constituting a first stator vane row located furthest upstream on the axis line among the plurality of stator vane rows; a second stator vane angle changer that changes angles of a plurality of second stator vanes constituting a second stator vane row adjacent to the first stator vane row on the downstream side of the axis, among the plurality of stator vane rows; a guide vane angle changer that changes the angles of the plurality of inlet guide vanes that make up the inlet guide vane row; a tachometer for detecting the rotation speed of the rotor; and The control device during a start-up process from when the rotor starts to rotate until the rotor reaches a rated rotation speed, when the tachometer detects a rotation speed smaller than a first rotation speed that is smaller than the rated rotation speed, instruct the guide vane angle changer to set angles of the plurality of inlet guide vanes to a guide vane initial angle, instruct the first stator vane angle changer to set angles of the plurality of first stator vanes to a first stator vane initial angle, and instruct the second stator vane angle changer to set angles of the plurality of second stator vanes to a second stator vane initial angle, During the start-up process, when the tachometer detects a rotation speed higher than a second rotation speed that is lower than the rated rotation speed and higher than the first rotation speed, instruct the guide vane angle changer to set angles of the plurality of inlet guide vanes to a guide vane late angle, instruct the first stator vane angle changer to set angles of the plurality of first stator vanes to a first stator vane late angle, and instruct the second stator vane angle changer to set angles of the plurality of second stator vanes to a second stator vane late angle, if, during the start-up process, when the rotation speed of the rotor is lower than the first rotation speed, if the angles of the plurality of inlet guide vanes are set to the guide vane initial angle, the angles of the plurality of first stator vanes are set to the first stator vane assumed initial angle, and the angles of the plurality of second stator vanes are set to the second stator vane assumed initial angle, there is a risk that an air separation phenomenon will occur in at least a part of the plurality of second stator vanes, the guide vane late angle is smaller than the guide vane initial angle, the first stator vane late angle is smaller than the first stator vane initial angle and the first stator vane assumed initial angle, the second stator vane late angle is smaller than the second stator vane initial angle and the second stator vane assumed initial angle, the second stator vane initial angle is greater than the second stator vane assumed initial angle, Air compression equipment.

11. An air compression facility according to claim 10; the combustor combusting fuel in compressed air from the multi-stage axial compressor to generate combustion gas; a turbine driven by the combustion gas; A gas turbine facility comprising:

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