JP2000314397A - Axial flow compressor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To suppress separation of high pressure air which flows through a diffuser, and recover a device to a further high static pressure by setting the radius of curvature in an inlet side of a passage of the diffuser smaller than that of the outlet side. SOLUTION: In a diffuser 25, a passage 26 for guiding high pressure air from a compressor turbine stage 21 to a gas turbine combustor is sectioned by a slitter 28 and is composed of a rotor side passage 26a and a casing side passage 26b. The passages 26a, 26b are formed of at least two or more radii of curvature. The relation between the radius of curvature RS1, RS2 of the inlet and outlet sides of the rotor side passage 26a is set to RS1<RS2 in the rotor side passage 26a, and the relation between the radii of curvature RS3, RS4 of the inlet and outlet sides of the casing side passage 26b is set to RS3<RS4 in the casing side passage 26b. Also when the passage 26 is not sectioned, the radius of curvature of the inlet side is set smaller than that of the outlet side.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an axial compressor, and more particularly, to an axial compressor having an improved diffuser.

[0002]

2. Description of the Related Art For example, a gas turbine plant applied for thermal power generation includes a generator 1, an air compressor 2, a gas turbine combustor 3, and a gas turbine 4, as shown in FIG. The compressed air (atmosphere) is compressed to a high pressure, and the high-pressure air is supplied to the gas turbine combustor 3 together with the fuel, where the combustion gas is generated, and the combustion gas is expanded by the gas turbine 4. The generator 1 is driven by the rotation torque generated at that time to generate electric power.

[0003] As described above, the air compressor 2 that supplies high-pressure air to the gas turbine combustor 3 has an important role in generating combustion gas that causes the gas turbine 4 to perform expansion work. There is one shown in FIG.

[0004] In the air compressor 2, a casing 8 accommodates a compressor rotor 7 in which disks 5 a, 5 b, 5 c formed in a sliced shape are layered and fixed with tie bolts 6.

[0005] The air compressor 2 includes a stationary blade 9 fixed to a casing 8 and a moving blade 1 implanted on a compressor rotor 7.
The compressor stage 11 is composed of 0 and the compressor stage 11 is formed in a so-called axial flow type in which the compressor stage 11 is arranged in a plurality of stages along the axial direction, thereby achieving a large capacity and a high pressure ratio. The air compressor 2 has a variable guide vane 12 at its inlet side to adjust the flow rate of air sucked by the variable guide vane 12 in accordance with the load, and has an outlet guide vane 13 at its outlet side. The swirling flow of air generated at the outlet guide vanes 13 is suppressed low, and the circumferential velocity component is converted into pressure.

In the axial-flow type air compressor 2 having such a configuration, the sucked air is rectified by the stationary blades 9, the rectified air is compressed by the moving blades 10, and the compressed high-pressure air is downstream. The air is supplied to the compressor stage 11 on the side to increase the air to the design pressure.

The axial-flow type air compressor 2 can have a larger capacity and a higher pressure ratio than, for example, a centrifugal type air compressor, and is therefore preferably applied to a gas turbine plant for thermal power generation. In recent years, with the development of technology, a pressure ratio exceeding 20 and a compression efficiency exceeding 90% have been realized.

[0008]

By the way, it can be said that the recent axial-flow type air compressor 2 has realized a large capacity and a high pressure ratio with the development of technology, but it has some problems. One of the points is left. One of them is how to increase the static pressure of the high-pressure air in a short axial span when introducing the high pressure air in the compressor stage 11 to the gas turbine combustor 3. You have to recover.

Generally, in the axial-flow type air compressor 2,
The compressor stage 11 sequentially performs a process of increasing the total pressure by applying rotational energy accompanying the rotation of the moving blade 10 to the sucked air and converting the increased total pressure into a static pressure by the stationary blade 9.

However, for the gas turbine combustor 3,
Of the high-pressure air supplied from the air compressor 2, what is required is a static pressure. In order to make full use of the high-pressure air supplied from the air compressor 2, it is necessary to convert the dynamic pressure to a static pressure as much as possible. There is. For this reason, in the conventional air compressor 2 shown in FIG. 13, outlet guide vanes 13, 13 are provided on the outlet side of the final compressor stage 11, and further, a double cylindrical diffuser 14 is provided on the downstream side. , Exit guide wings 13, 13
In addition, the diffuser 14 is designed to convert the dynamic pressure into a larger static pressure.

By the way, the diffuser 14 is considered to be appropriate as a cylindrical one if the spread angle θ of the expanded flow path area is set to 6 ° in consideration of prevention of fluid separation and recovery of static pressure. ing.

However, in the diffuser 14 having the dual flow path shown in FIG.
Due to structural and distance restrictions, it is difficult to secure the above θ = 6 °.

The high-pressure air that has exited the outlet guide vanes 13 has a swirling speed component, and thus flows into the diffuser 14 having a double flow path as a swirling flow. For this reason, the high-pressure air flows unevenly along the outer peripheral side of the diffuser 14, so that separation from the inner peripheral side is likely to occur, making it difficult to recover more static pressure.

As described above, in the diffuser 14 having the dual flow path shown in FIG. 13, the separation of the gas turbine combustor 3 is prevented by the addition of the swirling flow of the high-pressure air to the restriction on the arrangement of the gas turbine combustor 3 and the like.
Since the static pressure cannot be sufficiently recovered, the realization of a newly improved diffuser 14 has been desired.

The present invention has been made in view of such circumstances, and in combination with suppressing separation of high-pressure air flowing through a diffuser, a higher static pressure has been restored, and the gas turbine combustor 3 has It is an object of the present invention to provide an axial compressor capable of supplying a stable supply.

[0016]

In order to achieve the above object, an axial flow compressor according to the present invention comprises a compressor stage comprising a combination of a moving blade and a stationary blade, as described in claim 1. , While placing the compressor stages in multiple stages along the axial direction,
In the axial flow compressor provided with a diffuser with an outlet guide vane interposed downstream of the final compressor stage, the radius of curvature at the inlet side of the diffuser flow path is set to be smaller than the radius of curvature at the outlet side. It was done.

In order to achieve the above object, an axial flow compressor according to the present invention comprises a compressor stage formed by combining a moving blade and a stationary blade, wherein the compressor stage comprises an axial shaft. In an axial compressor having a plurality of stages along the direction and a diffuser provided with an outlet guide vane downstream of the final compressor stage, the flow path of the diffuser is at least one or more splitters. To form a multiple flow path, and the radius of curvature on the inlet side of the multiple flow path is set to be smaller than the radius of curvature on the outlet side.

In order to achieve the above object, the axial flow compressor according to the present invention is arranged such that at least two or more flow paths of the diffuser are provided from the inlet side to the outlet side thereof. It is formed with a radius of curvature.

In order to achieve the above object, the axial-flow compressor according to the present invention has a curvature radius of an intermediate portion in a flow path of a diffuser smaller than a curvature radius of an inlet side thereof. Are formed in the recessed region where the flow path of the intermediate portion is bulged toward the compressor rotor side.

In order to achieve the above object, an axial flow compressor according to the present invention, as described in claim 5, forms a compressor stage by combining a moving blade and a stationary blade, and forms the compressor stage with an axial shaft. In the axial flow compressor that is arranged in a plurality of stages along the direction and provided with a diffuser on the downstream side of the final compressor stage,
The channel of the diffuser is divided into at least one or more splitters to form a multiplex channel, and among the formed multiplex channels, the diameter of an inscribed circle in contact with a channel at an intermediate portion thereof is determined on the inlet side and the outlet side. It is set to be larger than the diameter of an inscribed circle that contacts each of the flow paths on the side.

In order to achieve the above object, an axial flow compressor according to the present invention, as described in claim 6, forms a compressor stage by combining a moving blade and a stationary blade, and forms the compressor stage with the shaft. In the axial flow compressor that is arranged in a plurality of stages along the direction and provided with a diffuser on the downstream side of the final compressor stage,
The flow path of the diffuser is divided into at least one or more splitters to form a multiple flow path, and the thickness of the intermediate portion of the splitter is set to be larger than the thickness of the inlet side and the outlet side.

In order to achieve the above object, an axial flow compressor according to the present invention is configured such that a compressor stage is constituted by combining a moving blade and a stationary blade, and the compressor stage is constituted by an axial shaft. In the axial flow compressor that is arranged in a plurality of stages along the direction and provided with a diffuser on the downstream side of the final compressor stage,
The diffuser flow path is divided by at least one or more splitters to form a multiple flow path, while a support plate for supporting and fixing the splitter is provided, and the support plate has an angle with respect to the axial direction. The angle is set larger on the upstream side than on the downstream side.

In order to achieve the above object, an axial flow compressor according to the present invention has a support plate for supporting and fixing the splitter provided in a flow path on the compressor rotor side. It is.

In order to achieve the above object, in the axial compressor according to the present invention, the support plate is prepared by previously dividing the support plate into two pieces. When connecting, while forming the leading edge of one piece into a streamlined sharp part, forming a notch step in the middle of the front edge, connecting the other piece through this notch step It is a thing.

In order to achieve the above object, an axial flow compressor according to the present invention comprises a compressor stage comprising a combination of a moving blade and a stationary blade, wherein the compressor stage comprises an axial shaft. In the axial flow compressor arranged in a plurality of stages along the direction, a diffuser supported and fixed by an outer wall portion and an inner wall portion is provided downstream of a final moving blade of the compressor stage.

In order to achieve the above object, an axial flow compressor according to the present invention comprises a compressor stage comprising a combination of a moving blade and a stationary blade, wherein the compressor stage comprises an axial shaft. In the axial flow compressor arranged in a plurality of stages along the direction, a diffuser supported and fixed by an outer wall portion and an inner wall portion is provided downstream of the final moving blade of the compression stage, and the outer wall portion and the inner wall portion are provided. The diffuser channel supported and fixed by the above is divided into at least one or more splitters to form a multiple channel, and among the multiple channels, the guide stationary vane is provided in the channel on the outer wall side. And a support plate provided in the flow path on the inner wall side.

In order to achieve the above object, an axial compressor according to the present invention comprises a compressor stage comprising a combination of a moving blade and a stationary blade, wherein the compressor stage comprises an axial shaft. In the axial flow compressor in which a plurality of stages are arranged along the direction and a diffuser is provided downstream of the final compressor stage with an outlet guide vane interposed therebetween, the outlet guide vane is disposed between an outer wall portion and an inner wall portion. The outlet guide vanes are supported and fixed, and the outlet guide vanes are formed such that the outflow angle is discontinuous in the blade height direction.

In order to achieve the above object, an axial-flow compressor according to the present invention, as described in claim 13, forms a compressor stage by combining a moving blade and a stationary blade, and forms the compressor stage with the shaft. In the axial flow compressor in which a plurality of stages are arranged along the direction and a diffuser is provided downstream of the final compressor stage with an outlet guide vane interposed therebetween, the outlet guide vane is disposed between an outer wall portion and an inner wall portion. While supporting and fixing, the outlet guide vane is formed so that its outflow angle is discontinuous distribution toward the blade height direction, while the tip of the splitter that divides the diffuser flow path into at least one or more is provided. It is extended and fixed to the exit guide vane.

In order to achieve the above object, the axial flow compressor according to the present invention, as described in claim 14, has a shape of the outlet guide vanes in which the outflow angle has a discontinuous distribution in the blade height direction.
The outer-wall-side wing element supported and fixed by the outer wall at the center of the blade height is inclined toward the upstream side of the fluid, and the inner-wall-side wing element is supported and fixed by the inner wall to downstream of the fluid. It is inclined toward.

[0030]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of an axial compressor according to the present invention will be described below with reference to the drawings and reference numerals attached to the drawings.

FIG. 1 is a partially cutaway sectional view showing a first embodiment of an axial compressor according to the present invention.

In the axial-flow compressor according to the present embodiment, a compressor rotor 17, which is formed by laminating a disk 15 formed in a ring-shape and fixed by tie bolts 16, is housed in a casing 18, and is mounted on the compressor rotor 17. A compressor stage 21 is constituted by the rotor blades 19 provided and the stationary blades 20 fixed to the casing 18, and the compressor stages 21 are arranged in a plurality of stages along the axial direction.

In the axial compressor according to the present embodiment, the compressor rotor 17 is connected to the intermediate shaft 23 via the flange 22, while the final stage of the compressor stage 21 is supplied with the gas via the outlet guide vanes 24 via the outlet guide vanes 24. A diffuser 25 is provided for communication with a turbine combustor (not shown).

This diffuser 25 is a compressor stage 21
2 that guides high-pressure air from the gas to the gas turbine combustor
6 is provided with a rotor-side flow path 26a and a casing-side flow path 26b that are divided by a splitter 28.
26b is the center CL of the compressor rotor 17 and the intermediate shaft 23.
Is formed as an annular cylinder around the base shaft. In the rotor-side flow path 26a, support plates 27 for fixing and supporting the splitter 28 are arranged at equal pitches along the circumferential direction.

On the other hand, the stationary blade 20 in the compressor stage 21 of the last stage has an outflow angle of 30 ° to 30 ° in order to lower the circumferential speed component of the high-pressure air and convert the circumferential speed component into pressure. The angle is set to 45 °. The exit guide vane 24 also has an outflow angle of 10 for the same reason as described above.
The angle is set in the range of ° to 25 °.

On the other hand, the rotor side flow path 26 through which high-pressure air flows
a and the casing-side flow path 26b are each formed with at least two or more radii of curvature. Further, the curvature radius of the rotor-side channel 26a and _{R S1, R S2,} when the curvature radius of the casing-side passage 26b and _{R S3, R S4,} among the curvature radius _R S1 _{to R S4,} the rotor-side flow R _S1 <R _S2 is set in the path 26a, and R _S3 <R _S4 is set in the casing-side flow path. In addition, the flow path 2
Even when 6 is not divided, the radius of curvature on the entrance side is set smaller than the radius of curvature on the exit side.

The radii of curvature R _{S1 to} R _S4 can be obtained from the following equations.

The high-pressure air in the diffuser 25 flows along the flow surface as shown in FIG. Now, let s be the distance along the meridional streamline passing through the mass point P, and let n be the distance along the normal line perpendicular to it. Further, the inclination angle of the streamline is α, the radius of curvature of the streamline is R _sx , the distance from the center CL of the compressor rotor 17 and the intermediate shaft 23 to the mass point P is r, and the turning speed component acting on the mass point P is and C _theta, a meridional velocity component acting on the mass point P and C _m.

At this time, a centrifugal force component Fr and a centripetal force component Fn act on the mass point P. The centrifugal force component Fr is given by the following equation.

[0040]

## EQU1 ## Fr = C _m ² / R _sx (1) The centripetal force component Fn is given by the following equation.

[0041]

[Number 2] ^{_{Fn = C θ 2 / r ·}} cosα ...... (2) the above equation (1), (2), if equal balance condition is satisfied (1) and (2), the radius of curvature _{R sx} Can be sought. In this case, each of C _m , C _θ , r, and α is set in advance.

In the present embodiment, the diffuser 25
Of the rotor side flow path 26 by one splitter 28
a and a casing-side flow path 26b, which is a so-called double flow path, but is not limited thereto.
8 may be provided in at least two or more, and the channel 26 may be formed as a multiple channel. If the flow path 26 of the diffuser 25 is a multiple flow path, the static pressure recovery coefficient of high-pressure air can be increased by increasing the number of flow paths while maintaining the same divergence angle.

Incidentally, in order to further shorten the axial length of the diffuser 25 to shorten the overall length of the gas turbine plant, the radius of curvature R _S1 of the rotor side flow path 26a is _required.
Is preferably bulged toward the compressor rotor 17 as shown by a solid line rather than by a broken line in FIG. That is, it is preferable to form the recessed region 30 on the flow wall at the intermediate portion of the rotor-side flow path 26a.

In setting the axial length of the diffuser 25, if the inclination angle α of the streamline shown in FIG. 2 is made zero when the outflow angle of the outlet guide vane 24 is set to 25 °, the diffuser Reference numeral 25 denotes a curved surface having a radius of curvature necessary for connection to the gas turbine combustor of at least five times the radius of curvature of the portion. Excessive effort.

[0045] The present embodiment, in consideration of this point, as shown in FIG. 1, the inner diameter of the center CL of the compressor rotor 17 and the intermediate shaft 23 at the inlet side of the diffuser 25 and D _1, Assuming that the inner diameter at the intermediate portion is D ₂ and the inner diameter at the outlet side is D ₃ , each inner diameter D ₁ , D ₂ , D ₃ of the diffuser 25 is represented by D ₂ <D ₁
<Those where the recessed region 29 that satisfies the relation of D ₃ is formed in the flow wall of the intermediate portion of the rotor-side channel 26a.

Therefore, according to the present embodiment, the concave region 29 is formed in the flow wall at the intermediate portion of the rotor side flow path 26a, and the curved flow wall is formed from the concave region 29 toward the gas turbine combustor. Is formed, the axial span of the diffuser 25 can be relatively shortened, and the diffuser 25
When attaching and detaching the gas turbine to and from the gas turbine combustor, the labor of the operator can be reduced.

As described above, in the present embodiment, the flow path 26 is divided by at least one or more splitters 28 to form multiple flow paths, and the radius of curvature of the inlet side of each of the multiple flow paths formed. Is formed smaller than the radius of curvature of the outlet side, and a concave region 29 having a smaller radius of curvature toward the compressor rotor 17 is formed in the flow wall in the middle part of the flow path near the compressor rotor 17 side. Since a curved flow wall is formed from the region 29 toward the gas turbine combustor, when supplying high-pressure air from the air compressor to the gas turbine combustor,
The static pressure can be sufficiently restored, and the diffuser 25
Can be supplied stably by shortening the shaft span.

FIG. 3 is a partially cutaway sectional view showing a second embodiment of the axial compressor according to the present invention. The same parts as those of the first embodiment are denoted by the same reference numerals.

In the axial compressor according to this embodiment, the flow path 26 of the diffuser 25 is divided by the splitter 28 into the rotor side flow path 2.
6a and the casing-side flow path 26b, and the diameters of the inscribed circles A and C of the recessed region 29 formed in the intermediate portion between the divided flow paths 26a and 26b are D ₄ and D ₆ , respectively. The diameters of the inscribed circles B and D on the outlet side of 26a and 26b are D ₅ ,
When D _6, the inscribed circle A at the rotor-side channel 26a,
The diameters D ₄ and D ₅ of B are set to satisfy the relation of D ₄ > D ₅ , and the diameters D ₆ and D ₇ of the inscribed circles C and D in the casing-side flow path 26 b are set to satisfy the relation of D ₆ > D _7. It was done.

As described above, in the present embodiment, the diameter D of the inscribed circles A and C at the intermediate portions of the passages 26a and 26b of the rotor-side passage 26a and the casing-side passage 26b divided by the splitter 28. _4, the inscribed circle B of the _{D 6} its outlet side, since the larger respectively than the diameter _D 5, _{D 7} and D, it is possible to suppress separation of the high pressure air flowing each channel 26a, a 26b, diffuser Twenty-five shaft spans can be relatively short to connect to the gas turbine combustor.

FIG. 4 is a partially cutaway sectional view showing a third embodiment of the axial compressor according to the present invention. The same parts as those in the first and second embodiments are denoted by the same reference numerals.

The axial-flow compressor according to the present embodiment is configured such that after the high-pressure air jetted from the outlet guide vanes 24, the casing-side flow path 2
Speed component of the high-pressure air flowing through the rotor 6b and the rotor side flow path 2
Considering that the swirling speed component of the high-pressure air flowing through the rotor-side flow path 26a is different, for example, when the swirling speed component of the high-pressure air flowing through the rotor-side flow path 26a is large, the rotor-side flow path 26
The radius of curvature of “a” is smaller than the radius of curvature of the casing-side flow path 26b, and the swirling speed component of the high-pressure air flowing through the rotor-side flow path 26a is suppressed to suppress the separation of the high-pressure air. In this case, the splitter 28
The thicknesses T ₁ and T ₂ on the inlet side and the outlet side are reduced so that the radius of curvature 6a is smaller than the radius of curvature of the casing-side flow path 26b, and the maximum thickness T is formed at an intermediate portion. The other components are the same as in the first embodiment and the second embodiment, and a description thereof will be omitted.

As described above, in the present embodiment, the flow path is controlled by the splitter 28 that suppresses the difference in the swirling speed component based on the difference in the flow angle distribution and the flow velocity of the high-pressure air ejected from the outlet guide vane 24 in the height direction. 26 to the rotor side flow path 26
a and a casing-side flow path 26b, the thicknesses T ₁ and T ₂ of the splitter 28 into which the flow path 26 is divided on the inlet side and the outlet side are reduced, and the intermediate part is formed to have the maximum thickness T. Since the radius of curvature of the side flow path 26a is made smaller than the radius of curvature of the casing side flow path 26b, the high-pressure air can be supplied to the gas turbine combustor in a stable state without separation.

FIG. 5 is a partially cutaway longitudinal sectional view of a diffuser applied to the axial compressor according to the present invention. The same parts as those of the first embodiment are denoted by the same reference numerals.

In the diffuser 25 according to the present embodiment, a flow path 26 is formed between an outer wall section 30 surrounding the compressor rotor 17 and an inner wall section 31, and the flow path 26 is connected to the rotor side flow path 2.
6a and a casing-side flow path 26b, a splitter 28 is provided, and support plates 27 for fixing and supporting the splitter 28 are arranged at equal pitches along the inner wall 31 while the support plate 27 is arranged in the axial direction. And the angle is made larger on the upstream side than on the downstream side.

Further, the diffuser 25 according to the present embodiment.
As shown in FIGS. 6 (a) and 6 (b),
While dividing into a first piece 32 and a second piece 33, a second piece 33
Is formed in a streamlined sharp portion, a notch step 35 is provided in the front edge 34, and the first piece 3 is formed in the notch step 35.
2 is connected so as not to disturb the flow of the high-pressure air.

As described above, according to the present embodiment, the mounting angle of the support plate 27 is set to be greater than the downstream side and the mounting angle of the support plate 27 is set to be larger than the downstream side. Even when high-pressure air having a flow rate flows, the swirling speed component can be lowered to suppress the separation of the high-pressure air.

In this embodiment, the front edge 3 of the second piece 33
Since the first piece 32 divided by the cutout step 35 is connected while maintaining the shape of the streamlined sharpened portion formed in 4, the high-pressure air supplied to the diffuser 25 is not disturbed. , Can supply a stable flow.

FIG. 7 is a partially cutaway sectional view showing a fourth embodiment of the axial compressor according to the present invention. The same parts as those in the first and second embodiments are denoted by the same reference numerals.

The axial compressor according to the present embodiment has an outer wall portion 36 downstream of the rotor blades 19 in the final stage compressor stage 21.
And a diffuser 25 supported and fixed by the inner wall portion 37. The diffuser 25 includes a flow path 26
Are provided with a rotor-side flow path 26a and a casing-side flow path 26b, which are separated by a splitter 28, and are arranged at equal pitches along the circumferential direction of the inner wall portion 37 in the rotor-side flow path 26a to support and fix the splitter 28. While the support plate 27 is provided, the stationary stationary blades 38 arranged in a row in the circumferential direction of the outer wall portion 36 are provided in the casing-side flow path 26b.

As described above, in the present embodiment, the rotor side flow path 26a in which the flow path 26 of the diffuser 25 provided downstream of the rotor blade 19 in the final stage compressor stage 21 is divided by the splitter 28 and the casing side flow Road 26b,
The support plate 27 for supporting and fixing the splitter 28 is provided in the rotor-side flow path 26a, and the guide stationary blade 38 is provided in the casing-side flow path 26b, so that the high-pressure air having a relatively large swirling speed component is supplied to the diffuser 25. Even if it flows in, the static pressure can be sufficiently recovered, and high-pressure air can be supplied to the gas turbine combustor in a stable state.

FIG. 8 is a partially cutaway sectional view showing a fifth embodiment of the axial flow compressor according to the present invention. The same parts as those in the first and second embodiments are denoted by the same reference numerals.

In the axial compressor according to the present embodiment, the trailing edge 41 is improved so that the outlet guide blade 24 has an outflow angle discontinuous in the blade height direction. Specifically, the outer-wall-side wing element 39 supported and fixed by the outer wall 36 at the center of the blade height of the outlet guide wing 24 is inclined toward the upstream side of the high-pressure air AR, and Inner wall side wing element 40 supported and fixed at 37
Is inclined toward the downstream side of the high-pressure air AR.

In the axial flow compressor according to this embodiment, the flow path 26 of the diffuser 25 provided on the downstream side of the outlet guide vane 24 is divided into a rotor side flow path 26a and a casing side flow path 26b by a splitter 28. Further, a support plate 27 that supports and fixes the splitter 28 along the flow of the high-pressure air AR is provided in the rotor-side flow path 26a.

Generally, in the diffuser 25 in which the flow path 26 is divided into a plurality of sections, the radial inflow angle of the high-pressure air AR flowing into the rotor-side flow path 26a and the casing-side flow path 26
It is preferable that the high-pressure air AR flowing into b has a different inflow angle from the radial direction. That is, as shown in FIG. 9, when the radial inflow angle is set to a negative angle in the rotor-side flow path 26a and is set to a positive angle in the casing-side flow path 26b, the high-pressure air AR
Flow along each of the flow paths 26a and 26b to reduce the separation.

In the present embodiment, in consideration of such a point, the flow path 26 of the diffuser 25 is divided into a rotor side flow path 26 and a casing side flow path 26b by a splitter 28, and the upstream side of the diffuser 25 The outer-wall-side wing element 39 is inclined toward the upstream side of the high-pressure air AR with respect to the trailing edge 41 of the outlet-guide wing 24 at the center of the blade height. Since the element 40 is inclined toward the downstream side of the high-pressure air AR, the element 40 can be supplied to the gas turbine combustor in a stable state in which separation of the high-pressure air AR is suppressed.

FIG. 10 shows a sixth embodiment of the axial compressor according to the present invention.
It is a partially cutaway sectional view showing an embodiment. The same parts as those in the first and second embodiments are denoted by the same reference numerals.

In the axial compressor according to this embodiment, similarly to the fifth embodiment, the inflow angle of the high-pressure air AR flowing into the rotor-side flow path 26a is made negative, and the high-pressure air flowing into the casing-side flow path 26b. The inflow angle of the AR is made positive, and the turning angle of the high-pressure air AR is cut by the outlet guide vanes 24.

That is, similarly to the fifth embodiment, the axial flow compressor according to the present embodiment has the trailing edge 41 of the outlet guide vane 24.
Of these, the outer-wall-side wing element 39 supported and fixed by the outer wall 36 is inclined toward the upstream side of the high-pressure air AR at the center of the blade height, and the inner-wall-side wing supported and fixed by the inner wall 37. The element 40 is inclined toward the downstream side of the high-pressure air AR, so that the outflow angle of the outlet guide vane 24 is discontinuous in the blade height direction.

In the axial compressor according to the present embodiment, the flow path 26 of the diffuser 25 provided downstream of the outlet guide vanes 24 is divided into a rotor side flow path 26a and a casing side flow path 26b by a splitter 28. In addition, a support plate 27 for supporting and fixing the splitter 28 along the flow of the high-pressure air AR is provided in the rotor-side flow path 26a, and a tip end portion 28a of the splitter 28 is extended and fixed to the outlet guide vane 24. .

In general, in the diffuser 25 in which the flow path 26 is divided into a plurality of sections, as shown in FIG. 11, the radial inflow angle of the high-pressure air AR flowing into the rotor-side flow path 26a,
The high-pressure air AR flowing into the casing-side flow path 26b has a different radial inflow angle from the high-pressure air AR.
It is said that if the turning angle of the flow path is cut by the splitter 28, the separation of each of the flow paths 26a and 26b can be reduced.

In the present embodiment, in consideration of such a point, the outer wall side wing element 39 of the trailing edge 41 of the outlet guide blade 24 is positioned upstream of the high-pressure air AR at the center of the blade height. And the inner wall side wing element 40 is inclined toward the downstream side of the high-pressure air AR, and the tip end 28a of the splitter 28 is extended and fixed to the outlet guide wing 24 to reduce the turning angle of the high-pressure air AR. Since the cutting is performed, the high-pressure air AR flowing in each of the flow paths 26a and 26b can be supplied to the gas turbine combustor in a stable state in which separation of the high-pressure air AR is reduced.

[0073]

As described above, in the axial compressor according to the present invention, the diffuser flow path is divided into at least one splitter by a plurality of splitters to form a multi-flow path, and a concave portion is formed at an intermediate portion of the multi-flow path. Since the region is provided and connected to the gas turbine combustor through a curved flow wall from the concave region, the axial span of the diffuser can be relatively shortened, which is coupled with the separation of high-pressure air. Thus, the static pressure can be sufficiently recovered.

[Brief description of the drawings]

FIG. 1 is a partially cutaway sectional view showing a first embodiment of an axial compressor according to the present invention.

FIG. 2 is a schematic diagram showing a vector of a force acting on a mass passing through a streamline.

FIG. 3 is a partially cutaway sectional view showing a second embodiment of the axial flow compressor according to the present invention.

FIG. 4 is a partially cutaway sectional view showing a third embodiment of the axial flow compressor according to the present invention.

FIG. 5 is a partially cutaway sectional view of a diffuser applied to the axial compressor according to the present invention.

FIG. 6 shows a support plate supporting the splitter shown in FIG.
FIG. 3A is a diagram viewed from the direction of the arrow, where FIG. 3A shows a state where the support plate is divided, and FIG. 3B shows a state where the divided support plates are connected to each other.

FIG. 7 is a partially cutaway sectional view showing a fourth embodiment of the axial compressor according to the present invention.

FIG. 8 is a partially cutaway sectional view showing a fifth embodiment of the axial flow compressor according to the present invention.

FIG. 9 is an inflow angle distribution diagram showing an inflow angle of high-pressure air flowing into the diffuser shown in FIG. 8;

FIG. 10 is a partially cutaway sectional view showing a sixth embodiment of the axial compressor according to the present invention.

11 is an inflow angle distribution diagram showing the inflow angle of high-pressure air flowing into the diffuser shown in FIG.

FIG. 12 is a schematic system diagram showing a gas turbine plant applied to conventional thermal power generation.

FIG. 13 is a partially cutaway longitudinal sectional view showing a conventional axial compressor.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Generator 2 Air compressor 3 Gas turbine combustor 4 Gas turbine 5a, 5b, 5c Disk 6 Tie bolt 7 Compressor rotor 8 Casing 9 Stator vane 10 Rotating blade 11 Compressor paragraph 12 Variable guide vane 13 Exit guide vane 14 Diffuser 15 Disk 16 Tie bolt 17 Compressor rotor 18 Casing 19 Rotor blade 20 Stator blade 21 Compressor paragraph 22 Flange 23 Intermediate shaft 24 Outlet guide blade 25 Diffuser 26 Flow path 26a Rotor flow path 26b Casing flow path 27 Support plate 28 Splitter 28a Tip Part 29 Depressed part area part 30 Outer wall part 31 Inner wall part 32 First piece 33 Second piece 34 Front edge 345 Notch step 36 Outer wall part 37 Inner wall part 38 Guide stationary blade 39 Outer wall side wing element 40 Inner wall side wing element 41 Trailing edge

Claims (14)

[Claims] A compressor stage is constructed by combining a moving blade and a stationary blade, and the compressor stages are arranged in a plurality of stages along the axial direction, and an outlet guide blade is provided downstream of the final compressor stage. An axial compressor having an interposed diffuser, wherein a radius of curvature at an inlet side of a flow path of the diffuser is set smaller than a radius of curvature at an outlet side of the diffuser. 2. A compressor stage is constructed by combining a moving blade and a stationary blade, and the compressor stages are arranged in a plurality of stages along the axial direction, and an outlet guide blade is provided downstream of the final compressor stage. In the axial compressor provided with a diffuser interposed, the flow path of the diffuser is divided into at least one or more splitters to form a multiple flow path, the radius of curvature on the inlet side of the multiple flow path, its outlet An axial flow compressor characterized in that the radius of curvature is set smaller than the radius of curvature of the side. 3. The axial flow compressor according to claim 1, wherein a flow path of the diffuser is formed with at least two or more radii of curvature from an inlet side to an outlet side thereof. 4. A radius of curvature of an intermediate portion in a flow path of the diffuser is made smaller than a radius of curvature on an inlet side of the diffuser, and the flow path of the intermediate portion is formed in a recessed region which bulges toward a compressor rotor side. 3. The method according to claim 1, wherein
An axial compressor as described. 5. A compressor stage is constructed by combining a moving blade and a stationary blade, and the compressor stages are arranged in a plurality of stages along the axial direction, and a diffuser is provided downstream of the final compressor stage. In the axial flow compressor, the diffuser channel is divided into at least one or more splitters to form a multiplex channel, and a diameter of an inscribed circle in contact with a channel at an intermediate portion of the multiplex channel formed. Wherein the diameter is set larger than the diameter of an inscribed circle that contacts the respective flow paths on the inlet side and the outlet side. 6. A compressor stage is configured by combining a moving blade and a stationary blade, and the compressor stages are arranged in a plurality of stages along the axial direction, and a diffuser is provided downstream of the final compressor stage. In the axial compressor, the diffuser flow path is divided into at least one or more splitters to form a multiple flow path, and the thickness of the intermediate portion of the splitter is set to be thicker than the thickness of the inlet side and the outlet side. An axial compressor characterized by: 7. A compressor stage is constructed by combining a moving blade and a stationary blade, and the compressor stages are arranged in a plurality of stages along the axial direction, and a diffuser is provided downstream of the final compressor stage. In the axial-flow compressor, the diffuser flow path is divided into at least one or more splitters to form a multiplex flow path, while a support plate for supporting and fixing the splitter is provided, and the support plate is disposed in the axial direction. An axial compressor characterized in that it has an angle and the angle is set larger on the upstream side than on the downstream side. 8. A support plate for supporting and fixing the splitter,
The axial flow compressor according to claim 7, wherein the axial flow compressor is provided in a flow path on a compressor rotor side. 9. A method in which the support plate is divided into two pieces in advance, and when the two pieces are connected to each other, the front edge of one of the pieces is formed into a streamlined sharpened portion. The axial flow compressor according to claim 7, wherein a notch step is formed in the middle of the leading edge, and the other piece is connected through the notch step. 10. An axial flow compressor in which a compressor stage is constructed by combining a moving blade and a stationary blade, and the compressor stage is arranged in a plurality of stages along the axial direction, wherein a final moving blade of the compressor stage is provided. An axial compressor comprising a diffuser supported and fixed by an outer wall portion and an inner wall portion on a downstream side of the compressor. 11. An axial flow compressor in which a moving blade and a stationary blade are combined to form a compressor stage, and the compressor stages are arranged in a plurality of stages along the axial direction. A diffuser supported and fixed by the outer wall and the inner wall is provided on the downstream side, and the flow path of the diffuser supported and fixed by the outer wall and the inner wall is divided and multiplexed by at least one or more splitters. An axial flow compressor formed in a flow path, wherein a guide stationary blade is provided in a flow path on an outer wall side of a multiplex flow path, and a support plate is provided in a flow path on an inner wall side. 12. A compressor stage is constructed by combining a moving blade and a stationary blade, and the compressor stages are arranged in a plurality of stages along the axial direction, and an outlet guide blade is provided downstream of the final compressor stage. In an axial flow compressor provided with an interposed diffuser, the outlet guide vanes are supported and fixed by the outer wall and the inner wall, and the outlet guide vanes have an outflow angle discontinuous distribution in the blade height direction. An axial flow compressor characterized by being formed so that 13. A compressor stage is constructed by combining a moving blade and a stationary blade, and the compressor stages are arranged in a plurality of stages along the axial direction. An outlet guide blade is provided downstream of the final compressor stage. In an axial flow compressor provided with an interposed diffuser, the outlet guide vanes are supported and fixed by the outer wall and the inner wall, and the outlet guide vanes have an outflow angle discontinuous distribution in the blade height direction. An axial flow compressor characterized in that a front end of a splitter that divides the flow path of the diffuser into at least one or more is extended and fixed to the outlet guide vane. 14. An outer-wall-side wing element in which the shape of an outlet guide vane in which the outflow angle has a discontinuous distribution in the wing height direction is supported and fixed by the outer wall at the center of the wing height, and the outer guide wing element is provided with a fluid. 14. The axial flow compressor according to claim 12, wherein the wing element is inclined toward the upstream side, and is supported and fixed by the inner wall, and the wing element on the inner wall side is inclined toward the downstream side of the fluid.