JP2013100784A - Compressor stator and axial flow compressor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To improve assemblability of an axial flow compressor 1, by expanding a degree of freedom in assembling of the axial flow compressor 1.SOLUTION: This compressor stator 17 includes a plurality of stator segments 17S divided along the axial direction. Each stator segment 17S includes: an annular band component 19m constituting a part of an outer band 19; and stator vane components 21m formed at equal intervals in the circumferential direction on an inner peripheral surface of the band component 19m, being the same in number as stator vanes 21, and constituting a part of the stator vanes 21. Between the stator segments 17S adjacent in the axial direction, the band component 19m in the stator segment 17S on the axially front side, can be concentrically fitted to the band component 19m in the stator segment 17S on the axially rear side.

Description

  The present invention relates to a compressor stator that is a component of an axial compressor that compresses and conveys a gas such as air in the axial direction.

  The configuration of a general axial compressor used in a gas turbine or the like will be briefly described as follows.

  A general axial compressor includes a cylindrical compressor case extending in the axial direction, and a gas flow path for circulating air (an example of gas) is provided inside the compressor case. Is formed.

  In the compressor case, a plurality of stages of compressor rotors are provided along the axial direction, and each stage of the compressor rotor is rotatable around the axis of the compressor case. The compressor rotor at each stage is provided with a disk provided in the compressor case so as to be rotatable around the axis of the compressor rotor, and arranged at equal intervals in the circumferential direction on the outer periphery of the disk. And a plurality of moving blades located in the flow path.

  In the compressor case, a plurality of stages of compressor stators are provided alternately with a plurality of stages of compressor rotors along the axial direction. The compressor stator at each stage includes an annular outer band provided on the inner wall surface of the compressor case, an annular inner band disposed concentrically inside the outer band, and an inner periphery of the outer band. And a plurality of stationary blades arranged so as to be connected between the surface and the outer peripheral surface of the inner band and arranged in the circumferential direction at equal intervals and positioned in the gas flow path.

  In addition, there exist some which are shown to patent document 1-patent document 3 as a prior art relevant to this invention.

JP 2004-60544 A JP 2004-3492 A Japanese Patent Application Laid-Open No. 11-200808

  By the way, when assembling the above-mentioned general axial compressor, it is necessary to avoid mutual interference between the compressor rotor and the compressor stator, and after assembling the compressor rotor to the compressor case, The compressor stator cannot be assembled from the front side in the axial direction (upstream side in the flow direction) to the rear side in the axial direction of the compressor stator on the inner wall surface of the compressor case. Therefore, there is a problem that the degree of freedom in assembling the axial compressor becomes narrow and it is difficult to improve the assemblability of the axial compressor.

  Accordingly, an object of the present invention is to provide a compressor stator and an axial flow compressor having a novel configuration that can solve the above-described problems.

  A first feature of the present invention is a compressor stator, which is a component of an axial compressor that compresses and conveys gas in an axial direction, and is provided around an annular outer band and an inner peripheral surface of the outer band. A plurality of stator blades arranged at equal intervals in the direction, and configured by a plurality of stator segments divided along the axial direction, each stator segment constituting a part of the outer band An annular band component, and the same number of stationary blade components as the number of the stationary blades, which are formed at equal intervals in the circumferential direction on the inner circumferential surface of the band component, and constitute a part of the stationary blades. Between the stator segments adjacent in the axial direction, the band constituent member in the stator segment on the axial front side is concentrically fitted to the band constituent member in the stator segment on the axial rear side. The gist that it is ability.

  In the specification and claims of the present application, “gas” means air, nitrogen gas, hydrogen gas, and the like.

  According to the first feature, since the compressor stator is constituted by the plurality of stator segments divided along the axial direction, the width (code length) of the stationary blade constituent member is set to the width of the stationary blade. Compared to the compressor rotor, the stator segment (the outer band) is slightly rotated in the circumferential direction while moving in the axial direction while being slightly shorter in accordance with the number of divisions. Each stator blade constituent member in the stator segment can be passed between the rotor blades adjacent in the circumferential direction. Further, since the band constituent member in the stator segment on the axial front side can be fitted concentrically with the band constituent member in the stator segment on the axial rear side, the plurality of stator segments can be centered. While doing so, the compressor stator can be assembled. Thus, after the compressor rotor is assembled to the compressor case, the compressor stator is easily assembled from the axial front side to the axial rear side of the compressor stator on the inner wall surface of the compressor case. Can be attached.

  A second feature of the present invention is an axial compressor that compresses and conveys gas in the axial direction, and has a cylindrical compressor case in which an annular gas passage for circulating gas is formed. And a compressor rotor that is provided in the compressor case, and that is rotatable about the axis of the compressor rotor, wherein the compressor rotor includes a plurality of moving blades that are located in the gas flow path and are arranged at equal intervals in the circumferential direction. And a plurality of compressor stators that are alternately provided with the compressor rotor along the axial direction in the compressor case and have the first feature.

  According to the 2nd characteristic, there exists an effect | action similar to the effect | action by a 1st characteristic.

  According to the present invention, after the compressor rotor is assembled to the compressor case, the compressor stator is moved from the axial front side to the axial rear side of the compressor stator on the inner wall surface of the compressor case. Since it can be assembled easily, the degree of freedom in assembling the axial compressor can be expanded and the assemblability of the axial compressor can be improved.

FIG. 1 is a side sectional view of an axial compressor according to a first embodiment of the present invention. FIG. 2 is a side cross-sectional view showing a main part of the axial flow compressor according to the first embodiment of the present invention. FIG. 3 is a side cross-sectional view showing another aspect of the axial flow compressor according to the first embodiment of the present invention. Fig.4 (a) is a sectional side view which shows another aspect of the axial flow compressor which concerns on 1st Embodiment of this invention, FIG.4 (b) is an expansion along the BB line in Fig.4 (a). It is sectional drawing. FIG. 5 is a schematic diagram for explaining the operation of the first embodiment of the present invention. FIG. 6 is a cross-sectional side view of an axial compressor according to the second embodiment of the present invention.

(First embodiment)
A first embodiment of the present invention will be described with reference to FIGS. In the drawings, “F” indicates the front side in the axial direction, and “R” indicates the rear side in the axial direction.

  As shown in FIG. 1, the axial flow compressor 1 according to the first embodiment of the present invention is used in, for example, a small gas turbine or the like, and compresses and conveys air (an example of gas) in the axial direction. . The axial flow compressor 1 includes a cylindrical compressor case 3 extending in the axial direction, and an annular gas passage 5 for circulating air is provided inside the compressor case 3. Is formed.

  In the compressor case 3, a plurality of stages of compressor rotors 7 are provided along the axial direction, and the compressor rotors 7 of each stage can rotate around the axis SC of the compressor case 3. The compressor rotor 7 at each stage includes a disk 9 provided in the compressor case 3 so as to be rotatable around the axis SC of the compressor rotor 7 and an outer peripheral portion of the disk 9 at equal intervals in the circumferential direction. A plurality of blades 11 (only one is shown in FIG. 1) provided side by side and positioned in the gas flow path 5 are provided. The disks 9 in the compressor rotor 7 adjacent to each other in the axial direction are coupled to each other via a Kirbic coupling 13, and the disks 9 in the plurality of compressor rotors 7 are integrated into an assembly by stacking bolts 15. Has been. The multi-stage compressor rotor 7 is integrally connected to a multi-stage turbine rotor (not shown) in a gas turbine turbine (not shown).

  In the compressor case 3, a plurality of stages of compressor stators 17 are provided alternately with the plurality of stages of compressor rotors 7 along the axial direction. And the concrete structure of the compressor stator 17 which is the principal part of 1st Embodiment of this invention is as follows.

  As shown in FIGS. 1 and 2, the compressor stator 17 includes an annular outer band 19, and the outer band 19 can be attached to the inner wall surface of the compressor case 3. In addition, a plurality (only one is shown in FIGS. 1 and 2) of stationary blades 21 are provided on the inner peripheral surface of the outer band 19 side by side at equal intervals in the circumferential direction. , Located in the gas flow path 5.

  The compressor stator 17 includes a plurality of stator segments 17S divided along the axial direction. Each stator segment 17S includes an annular band constituting member 19m that constitutes a part of the outer band 19, and a static vane that constitutes a part of the stationary blade 21 is formed on the inner peripheral surface of the band constituting member 19m. The same number of stationary blade constituent members 21m as the number of blades 21 are formed at equal intervals in the circumferential direction.

  Between the stator segments 17S adjacent in the axial direction, the band constituent member 19m in the stator segment 17S on the front side in the axial direction can be fitted concentrically from the inner side in the radial direction to the band constituent member 19m in the stator segment 17S on the rear side in the axial direction. It has become. As shown in FIG. 3, the band constituent member 19m in the axially front stator segment 17S can be fitted concentrically from the radially outer side to the band constituent member 19m in the axially rear stator segment 17S. It doesn't matter.

  As shown in FIG. 2, the band constituting member 19 m in the stator segment 17 </ b> S located on the most axial rear side (most downstream in the flow direction) can be attached to the inner wall surface of the compressor case 3 via the attachment bolts 23. ing. Similarly, the band constituting member 19m in the stator segment 17S located on the most axial front side (most upstream in the flow direction) can be attached to the inner wall surface of the compressor case 3 via the attachment bolt 25.

  Normally, the stator blade constituent members 21m in the stator segments 17S adjacent in the axial direction are in contact with each other, but as shown in FIG. 4A, the stator blade constituent members 21m in the stator segments 17S adjacent in the axial direction are between. Alternatively, the gap 27 may be formed.

  As shown in FIGS. 1 and 2, an annular spacer 29 is disposed on the front side of each stator segment 17 </ b> S, and each spacer 29 is attached to the inner wall surface of the compressor case 3 via attachment bolts 31. It is possible.

  Then, the effect | action and effect of 1st Embodiment of this invention are demonstrated.

(i) Action concerning assembly of compressor stator 17 Since the compressor stator 17 is constituted by a plurality of stator segments 17S divided along the axial direction, the width (code length) of the stationary blade component 21m is divided. By shortening the stator segment 17S (outer band 19) slightly in the circumferential direction and moving it in the axial direction relative to the compressor rotor 7, as shown in FIG. Each stator blade constituent member 21m in the stator segment 17S can be passed between the rotor blades 11 adjacent in the circumferential direction. Further, since the band constituting member 19m in the axially front stator segment 17S can be fitted concentrically with the band constituting member 19m in the axially rear stator segment 17S, the plurality of stator segments 17S can be centered. The compressor stator 17 can be assembled while doing so. Thereby, after assembling a plurality of stages of compressor rotors 7 in an assembly form with respect to the compressor case 3, the compressor stator 17 is attached to the appropriate compressor stator 17 on the inner wall surface of the compressor case 3 from the front side in the axial direction. It can be easily assembled on the rear side in the axial direction.

(ii) Operation related to the operation of the axial compressor 1 The turbine (not shown) of the gas turbine is driven by the expansion of the combustion gas from the combustor (not shown) of the gas turbine, and the compressor rotor 7 of a plurality of stages is connected to the turbine in the turbine. It is rotated integrally with a multi-stage turbine rotor (not shown). Thereby, the multistage compressor rotor 7 and the multistage compressor stator 17 can cooperate with each other, and the air taken into the gas flow path 5 can be compressed in the axial direction and conveyed.

  Here, when the gap 27 is formed between the stator blade constituent members 21m in the stator segments 17S adjacent in the axial direction, the operation of the axial compressor 1 is performed as shown in FIG. In the inside, a leakage flow is generated from the pressure surface (pressure surface) Sp of the stationary blade 21 to the suction surface Sn via the gap 27, and separation of the boundary layer on the suction surface Sn side of the stationary blade 21 can be suppressed.

(iii) Effects of the First Embodiment Therefore, according to the first embodiment of the present invention, the compressor stator 17 is pivoted after the assembly-type multi-stage compressor rotor is assembled to the compressor case 3. Since it can be easily assembled to the axially rear side of the appropriate compressor stator 17 on the inner wall surface of the compressor case 3 from the front side in the direction, the degree of freedom in assembling the axial flow compressor 1 is expanded, and the axial flow compressor is expanded. Assembling property of 1 can be improved.

  Further, when the gap 27 is formed between the stator blade constituent members 21m in the stator segment 17S adjacent in the axial direction, the separation of the boundary layer on the negative pressure surface Sn side of the stator blade 21 can be suppressed. Therefore, energy loss (pressure loss) in the compressor stator 17 can be reduced, and the compressor efficiency of the axial flow compressor 1 can be improved.

(Second Embodiment)
A second embodiment of the present invention will be described with reference to FIG. In the drawings, “F” indicates the front side in the axial direction, and “R” indicates the rear side in the axial direction.

  As shown in FIG. 6, the axial compressor 33 according to the second embodiment of the present invention is used in, for example, a small gas turbine or the like, and compresses and conveys air (an example of gas) in the axial direction. Thus, the first embodiment of the present invention has the same configuration as the axial flow compressor 1. Hereinafter, only parts of the configuration of the axial flow compressor 33 that are different from the configuration of the axial flow compressor 1 will be briefly described. In addition, about the component corresponding to the component in the axial flow compressor 1 among the some components in the axial flow compressor 33, the same number is attached | subjected in drawing.

  A cylindrical drum 35 is disposed in the compressor case 3, and the drum 35 can rotate around the axis SC of the compressor case 3. A plurality of stages of compressor rotors 37 are provided along the axial direction on the outer periphery of the drum 35, and each stage of the compressor rotor 37 is connected to the drum 35 around the axis SC of the compressor case 3. It can rotate integrally. Further, the compressor rotor 37 of each stage includes a plurality of moving blades 39 that are provided on the outer peripheral portion of the drum 35 side by side in the circumferential direction and are positioned in the gas flow path 5. The multi-stage compressor rotor 37 is integrally connected to a multi-stage turbine rotor (not shown) in a gas turbine turbine (not shown) via a drum 35.

  And also in 2nd Embodiment of this invention, there exists an effect | action and effect similar to the effect | action and effect of 1st Embodiment of this invention.

  In addition, this invention is not restricted to description of the above-mentioned embodiment, It can implement in a various aspect by making an appropriate change. Further, the scope of rights encompassed by the present invention is not limited to these embodiments.

DESCRIPTION OF SYMBOLS 1 Axial flow compressor 3 Compressor case 5 Gas flow path 7 Compressor rotor 9 Disk 11 Moving blade 13 Carbic coupling 15 Stacking bolt 17 Compressor stator 17S Stator segment 19 Outer band 19m Band component 21 Stator blade 21m Stator blade Component 23 Mounting bolt 25 Mounting bolt 27 Clearance 33 Axial compressor 35 Drum 37 Compressor rotor 39 Rotor blade

Claims (4)

A compressor stator that is a component of an axial compressor that compresses and conveys gas in the axial direction,
An annular outer band, and a plurality of stationary blades provided at equal intervals in the circumferential direction on the inner peripheral surface of the outer band,
Consists of a plurality of stator segments divided along the axial direction,
Each stator segment
An annular band constituting member constituting a part of the outer band;
It is formed on the inner peripheral surface of the band component member at equal intervals in the circumferential direction, and includes the same number of stator blade component members as the number of stator blades constituting a part of the stator blades,
Between the stator segments adjacent in the axial direction, the band constituent member in the stator segment on the front side in the axial direction can be fitted concentrically with the band constituent member in the stator segment on the rear side in the axial direction. Compressor stator characterized.   The said band structural member in the said stator segment located in the axial direction rearmost side can be attached to the compressor case which is another component of the said axial flow compressor. Compressor stator.   The compressor stator according to claim 1, wherein a gap is formed between the stationary blade constituent members in the stator segments adjacent in the axial direction. An axial compressor that compresses and transports gas in the axial direction,
A cylindrical compressor case in which an annular gas passage for allowing gas to flow inside is formed;
A compressor rotor provided in the compressor case, provided with a plurality of moving blades positioned in the gas flow path and arranged at equal intervals in the circumferential direction, and rotatable around the axis of the compressor case;
A plurality of compressor stators, which are alternately provided with the compressor rotor along the axial direction in the compressor case, and have the configuration according to any one of claims 1 to 3. An axial flow compressor characterized by comprising:

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