Axial flow rotary machine

文档序号：1602505 发布日期：2020-01-07 浏览：32次中文

阅读说明：本技术 轴流旋转机械 (Axial flow rotary machine ) 是由门间和弘妹尾茂树于 2018-06-06 设计创作，主要内容包括：轴流旋转机械具备转子(20)、多个静叶(42)、介质流变更构件(60)。静叶(42)具有内侧护罩(44)、一个以上的密封翅片(49)。在转子轴(21)形成有朝向径向内侧(Dri)凹陷且供内侧护罩(44)及密封翅片(49)非接触地进入的环状槽(22)。从内侧护罩(44)中的最靠轴线下游侧(Dad)的端(58)至下游侧槽侧面(25)为止的距离为距离(L)。从最下游密封翅片(49d)至介质流变更面(61)为止的距离(Lf)在轴线下游侧(Dad)为距离(L)以下。(The axial flow rotary machine is provided with a rotor (20), a plurality of vanes (42), and a medium flow changing member (60). The vane (42) has an inner shroud (44) and one or more sealing fins (49). An annular groove (22) that is recessed toward the radially inner side (Dri) and into which the inner shroud (44) and the seal fin (49) enter in a non-contact manner is formed in the rotor shaft (21). The distance from the end (58) of the inner shroud (44) closest to the axis downstream side (Dad) to the downstream side groove side surface (25) is a distance (L). The distance (Lf) from the most downstream sealing fin (49d) to the medium flow changing surface (61) is equal to or less than the distance (L) on the downstream side (Dad) of the axis.)

1. An axial-flow rotating machine, comprising:

a rotor that rotates about an axis;

a housing covering an outer peripheral side of the rotor;

a plurality of stationary blades provided inside the casing and arranged in a circumferential direction with respect to the axis; and

a medium flow alteration member having a medium flow alteration surface extending in a radial direction with respect to the axis,

the housing has: a medium inlet for guiding the working medium to the inside; a medium outlet located on a downstream side of the axis in an axial direction extending from the medium inlet toward the axis,

the rotor has: a rotor shaft that is long in an axial direction extending about the axis; a plurality of blades arranged in the circumferential direction and fixed to the rotor shaft,

the plurality of stationary blades and the plurality of movable blades are arranged between the medium inlet and the medium outlet in the axial direction, the plurality of movable blades are arranged on a downstream side of the axial direction with respect to the plurality of stationary blades,

the plurality of vanes each have: an airfoil body extending in the radial direction to form an airfoil shape; an inboard shroud disposed radially inboard of the airfoil body relative to the axis; one or more sealing fins disposed radially inward of the inner shroud,

an annular groove is formed in the rotor shaft, the annular groove being recessed inward in the radial direction, and being formed in an annular shape with the axis as a center, the inner shroud and the one or more sealing fins entering the annular groove in a non-contact manner,

the annular groove has: a groove bottom surface facing radially outward with respect to the axis; a downstream side groove flank that expands from an end on the axis downstream side of the groove bottom toward the radially outer side,

the medium flow changing surface is directed toward an axis upstream side opposite to the axis downstream side in the axis direction and expands from the groove bottom surface toward the radially outer side,

a distance in the axial direction from an end of the inner shroud located most downstream of the axial line to the downstream-side groove side surface is a distance L,

the medium flow changing surface is disposed on the axial upstream side of the downstream groove side surface,

a distance Lf in the axial direction from a most downstream sealing fin located on the most downstream side of the axial line among the one or more sealing fins to the medium flow changing surface is equal to or less than the distance L on the axial line downstream side.

2. The axial flow rotary machine according to claim 1,

the inner shroud has a downstream end surface facing the downstream side of the axis and facing the downstream side groove side surface,

the downstream-side end surface includes an inclined surface gradually toward the axis downstream side as it goes toward the radially outer side.

3. The axial flow rotary machine according to claim 2,

the inclined surface is present in a direction of 170 ° with respect to the medium flow changing surface from the end on the radially outer side of the medium flow changing surface.

4. An axial flow rotating machine is provided with:

a rotor that rotates about an axis;

a housing covering an outer peripheral side of the rotor;

a plurality of stationary blades provided inside the casing and arranged in a circumferential direction with respect to the axis; and

a medium flow alteration member having a medium flow alteration surface extending in a radial direction with respect to the axis,

the rotor has: a rotor shaft that is long in an axial direction extending about the axis; a plurality of blades arranged in the circumferential direction and fixed to the rotor shaft,

the inner shroud has a downstream end surface facing the downstream side of the axis and facing the downstream side groove side surface,

the downstream-side end surface includes an inclined surface gradually toward the axis downstream side as it goes toward the radially outer side,

the medium flow changing surface is located on the axis upstream side of the downstream groove side surface and on the axis downstream side of a most downstream sealing fin located on the axis downstream side of the most downstream sealing fin among the one or more sealing fins,

the inclined surface is present in a direction of 170 ° with respect to the medium flow changing surface from the end on the radially outer side of the medium flow changing surface.

5. The axial flow rotary machine according to any one of claims 2 to 4,

the inside shield has: a shroud body having the airfoil body disposed radially outwardly thereof; a seal ring fixed to the radially inner side of the shield main body and provided with one or more seal fins on the radially inner side,

the seal ring has the inclined surface.

6. The axial flow rotary machine according to any one of claims 2 to 4,

the inner shroud has a gas passage surface facing the radially outer side and formed with the wing body,

the inclined surface is present at least in a range from the gas passage surface of the inner shroud to a position that is located radially inward by a distance that is half the radial thickness of the inner shroud.

7. The axial flow rotary machine according to claim 6,

the radially inner end of the inclined surface is located within a range from the gas passage surface of the inner shroud toward the radially inner side to a position that is a distance of half the radial thickness of the inner shroud.

8. The axial flow rotary machine according to any one of claims 2 to 7,

the medium flow changing surface is located in a region where the inclined surface exists in the axial direction.

9. The axial flow rotary machine according to any one of claims 2 to 8,

a change bottom height that is the radial distance from the groove bottom surface to the radially outer end of the medium flow change bottom surface is lower than an inclined surface height that is the radial distance from the groove bottom surface to the radially inner end of the inclined surface.

10. The axial flow rotary machine according to any one of claims 2 to 9,

an imaginary extension line from the inclined surface toward the radially outer side and toward the axis line downstream side does not intersect with the downstream side groove side surface.

11. The axial flow rotary machine according to any one of claims 1 to 10,

the shortest distance from the radially outer end of the medium flow change surface to the inner shroud is equal to or less than the distance L.

12. The axial flow rotary machine according to any one of claims 1 to 11,

the distance Lf is a distance 0.5 times or more the distance L.

13. The axial flow rotary machine according to any one of claims 1 to 12,

a change surface height that is the radial distance from the groove bottom surface to the radially outer end of the medium flow change surface is equal to or less than a seal surface height that is the radial distance from the groove bottom surface to the radially inner end of the inner shroud.

14. The axial flow rotary machine according to any one of claims 1 to 12,

a change surface height, which is a distance in the radial direction from the groove bottom surface to the end on the radially outer side of the medium flow change surface, is equal to or less than a fin height, which is a length in the radial direction of the one or more seal fins.

15. The axial flow rotary machine according to any one of claims 1 to 14,

the casing is a casing of a steam turbine,

the steam turbine casing has: a steam inlet as the medium inlet that guides the steam as the working medium to the inside; a steam outlet as the medium outlet.

16. The axial flow rotary machine according to any one of claims 1 to 14,

the shell is a gas turbine shell, and the gas turbine shell is a gas turbine shell,

the gas turbine casing has: a combustion gas inlet as the medium inlet for introducing combustion gas as the working medium to the inside; a combustion gas outlet as the medium outlet.

Technical Field

The present invention relates to an axial flow rotary machine including a rotor that rotates via a working medium and a casing that covers an outer peripheral side of the rotor.

The present application claims priority based on application No. 2017-115364 filed on the sun at 12.6.2017, the contents of which are incorporated herein by reference.

Background

A steam turbine, which is one type of axial-flow rotary machine, includes a rotor that rotates about an axis, a casing that covers an outer circumferential side of the rotor, and a plurality of stationary blades provided inside the casing. The rotor includes a rotor shaft that is long in an axial direction extending around an axis, and a plurality of blades fixed to the rotor shaft. The movable vane is provided with a wing body in a wing shape and a platform. The platform is fixed to the rotor shaft. The stator vane includes an airfoil-shaped blade body and an inner shroud. The rotor shaft is recessed radially inward with respect to the axis and has an annular groove formed around the axis. The inner shroud of the vane enters the annular groove in a non-contact manner. In the casing, a space in which each of the plurality of blades and each of the plurality of vanes are present is an annular space centered on the axis. The annular space forms a main steam flow path through which steam flows.

In the steam turbine having the above-described configuration, a part of the steam flowing into the casing flows into the annular groove from the chamber inlet as leakage steam while passing through the main steam flow path. The leakage steam returns from the chamber outlet to the main steam flow path through a space between the inner shroud and the groove bottom surface of the annular groove. The chamber inlet is a portion of the opening of the annular groove on the axial upstream side of the inner shroud. The chamber outlet is a portion of the opening of the annular groove on the axial downstream side of the inner shroud. The leakage steam passing between the inner shroud and the groove bottom of the annular groove and towards the chamber outlet contains a radial flow velocity component. The flow of the leakage steam along the downstream groove side surface of the annular groove among the leakage steam has a larger radial flow velocity component than the flow of the leakage steam separated from the downstream groove side surface toward the axial upstream side. The main steam in the main steam flow path is directed toward the axis downstream side. The leakage steam from the radially inner side to the radially outer side flows into the main steam flow flowing to the radially downstream side in the main steam flow path. As a result, a secondary flow having a complicated flow is generated on the downstream side of the mixing portion of the main steam and the leak steam.

When the secondary flow is generated in the main steam flow path, the efficiency of the steam turbine is reduced. Therefore, in the following patent document 1, in order to suppress the secondary flow loss, a fin extending radially outward from the groove bottom surface of the annular groove is provided. The fins are disposed at positions between the inner shroud and the downstream side surface of the annular groove in the axial direction. In the technique described in patent document 1, the presence of the fins suppresses a radial flow velocity component in the flow of the leakage steam along the downstream side surface of the annular groove, thereby suppressing the secondary flow loss.

Prior art documents

Patent document

Patent document 1: european patent application publication No. 2292897

Disclosure of Invention

Drawings

Fig. 1 is an overall cross-sectional view of an axial flow rotary machine according to a first embodiment of the present invention.

Fig. 2 is a main part sectional view of an axial flow rotary machine according to a first embodiment of the present invention.

Fig. 3 is a sectional view of the inner annular groove and the periphery of the inner shroud of the axial flow rotary machine according to the first embodiment of the present invention.

Fig. 4 is a cross-sectional view of the inner annular groove and the periphery of the inner shroud of the axial flow rotary machine according to the comparative example.

Fig. 5 is a sectional view of the inner annular groove and the periphery of the inner shroud of the axial flow rotary machine according to the second embodiment of the present invention.

Fig. 6 is a sectional view of the inner annular groove and the periphery of the inner shroud of the axial flow rotary machine according to the third embodiment of the present invention.

Fig. 7 is a sectional view of the inner annular groove and the periphery of the inner shroud of the axial flow rotary machine according to the fourth embodiment of the present invention.

Fig. 8 is a sectional view of the inner annular groove and the periphery of the inner shroud of the axial flow rotary machine according to the fifth embodiment of the present invention.

Fig. 9 is a cross-sectional view of the periphery of the inner shroud and the inner annular groove of the axial flow rotary machine including the medium flow changing member according to the modification of the present invention.

Fig. 10 is a cross-sectional view of the inner annular groove and the periphery of the inner shroud of the axial flow rotary machine including the inclined surface according to the first modification of the present invention.

Fig. 11 is a cross-sectional view of the inner annular groove and the periphery of the inner shroud of an axial flow rotary machine including an inclined surface according to a second modification of the present invention.

Fig. 12 is a whole cross-sectional view of an axial flow rotary machine according to a modification of the present invention.

Fig. 13 is a main part sectional view of an axial flow rotary machine according to a modification of the present invention.

Fig. 14 is a sectional view of the annular groove and the periphery of the inner shroud of the axial flow rotary machine according to the modification of the present invention.

Detailed Description

Hereinafter, various embodiments and various modifications of the axial flow rotary machine according to the present invention will be described in detail with reference to the drawings.

"first embodiment"

A first embodiment of an axial flow rotary machine according to the present invention will be described with reference to fig. 1 to 4.

The axial flow rotary machine of the first embodiment is a steam turbine. As shown in fig. 1, the steam turbine includes a rotor 20 that rotates about an axis Ar, a steam turbine casing 10 that covers an outer peripheral side of the rotor 20, and a plurality of vane rows 41 that are fixed to the steam turbine casing 10. Hereinafter, the direction in which the axis Ar extends is referred to as an axis direction Da, the circumferential direction around the axis Ar is simply referred to as a circumferential direction Dc, and the direction perpendicular to the axis Ar is referred to as a radial direction Dr. In the radial direction Dr, a side close to the axis Ar is referred to as a radial inner side Dri, and an opposite side is referred to as a radial outer side Dro.

The steam turbine casing 10 includes an inflow portion 11 into which steam flows from the outside, a trunk portion 12, and an exhaust portion 15 which exhausts the steam to the outside. Hereinafter, the steam turbine casing is simply referred to as a casing. The inflow portion 11 is formed with a steam inlet (medium inlet) 11i for introducing steam as a working medium into the inside. The trunk portion 12 is substantially cylindrical about the axis Ar. The exhaust portion 15 is formed with a steam outlet (medium outlet) 15o for exhausting steam to the outside. The inflow portion 11, the trunk portion 12, and the exhaust portion 15 are arranged in this order along the axial direction Da. In the axial direction Da, the side of the exhaust portion 15 where the inflow portion 11 is present is referred to as an axial upstream side Dau, and the opposite side is referred to as an axial downstream side Dad.

The rotor 20 has: a rotor shaft 21 extending in the axial direction Da about the axis Ar; and a plurality of rotor blade rows 31 attached to the rotor shaft 21. The plurality of rotor blade rows 31 are arranged in the axial direction Da and are disposed radially inward Dri of the tubular main portion 12. Each of the rotor blade rows 31 is formed of a plurality of rotor blades 32 arranged in the circumferential direction Dc.

The plurality of vane rows 41 are arranged in the axial direction Da. Each of the vane rows 41 is disposed on the axially upstream side Dau of any one of the plurality of blade rows 31. Each of the vane rows 41 is formed of a plurality of vanes 42 arranged in the circumferential direction Dc. Each of the vanes 42 is disposed radially inward Dri of the cylindrical main portion 12 and fixed to the main portion 12.

The end of the rotor shaft 21 on the axial upstream side Dau protrudes from inside the housing 10 to the axial upstream side Dau. Further, an end of the rotor shaft 21 on the axis downstream side Dad protrudes from inside the housing 10 toward the axis downstream side Dad. An upstream shaft seal 16u is provided in a portion of the inflow portion 11 of the housing 10, which penetrates the rotor shaft 21 to the outside. Further, a downstream shaft seal 16d is provided in the exhaust portion 15 of the housing 10 at a portion where the rotor shaft 21 penetrates to the outside. In the rotor shaft 21, a portion on the axial upstream side Dau of the upstream shaft seal 16u is supported by the upstream bearing 17 u. Further, in the rotor shaft 21, a portion on the axis line downstream side Dad of the downstream shaft seal 16d is supported by the downstream bearing 17 d. The rotor 20 is supported by the upstream bearing 17u and the downstream bearing so as to be rotatable about the axis Ar.

As shown in fig. 2, the bucket 32 has an airfoil-shaped blade body 33 extending in the radial direction Dr and an outer shroud 34 provided radially outward Dro of the blade body 33. The wing body 33 is fixed to the rotor shaft 21. The radially inner Dri surface of the outer shroud 34 forms a gas passage surface 35. The rotor blade 32 illustrated here has the outer shroud 34, but the outer shroud 34 may be omitted.

In the trunk portion 12 of the casing 10, an outer annular groove 13 is formed in a portion facing the outer shroud 34 of the rotor blade 32 in the radial direction Dr. The outer annular groove 13 is recessed radially outward Dro and is annular about the axis Ar. The outer shroud 34 of the rotor blade 32 is disposed in the outer annular groove 13. A plurality of seal fins 14 extending from the groove bottom surface to the radially inner side Dri are provided on the groove bottom surface of the outer annular groove 13. The outer shroud 34 of the rotor blade 32 is disposed in the outer annular groove 13 in a state of not contacting the outer annular groove 13 and the plurality of seal fins 14.

The vane 42 includes: an airfoil body 43 having an airfoil shape and extending in a radial direction Dr; an inner shroud 44 provided radially inward Dri of the airfoil body 43; a plurality of sealing fins 49 provided radially inward Dri of the inner shroud 44. The inner shroud 44 includes a shroud main body 45 and a seal ring 46 fixed to a radially inner side Dri of the shroud main body 45. As described above, the vane 42 is disposed on the radial direction inner side Dri of the cylindrical trunk portion 12 and fixed to the trunk portion 12. A plurality of seal fins 49 extending from the seal ring 46 to the radially inner side Dri are provided on the radially inner side Dri of the seal ring 46. The plurality of seal fins 49 are arranged in the axial direction Da.

In the rotor shaft 21, an inner annular groove 22 is formed in a portion facing the inner shroud 44 of the stator vane 42 in the radial direction Dr. The inner annular groove (hereinafter, simply referred to as an annular groove) 22 is recessed radially inward Dri and is annular about the axis Ar. The inner shroud 44 and the plurality of sealing fins 49 are disposed in the annular groove 22 so as not to contact the annular groove 22. The portion of the opening of the annular groove 22 on the axial upstream side Dau of the inner shroud 44 serves as the chamber inlet 26. Further, a portion of the opening of the annular groove 22 on the axial downstream side Dad of the inner shroud 44 serves as a chamber outlet 27.

The annular groove 22 has: a groove bottom surface 23 facing the radially outer side Dro; an upstream groove side surface 24 extending from an end of the axial upstream side Dau of the groove bottom surface 23 toward the radially outer side Dro; and a downstream groove side surface 25 extending from an end of the axial downstream side Dad of the groove bottom surface 23 toward the radially outer side Dro. The upstream side groove side surface 24 and the downstream side groove side surface 25 face each other in the axial direction Da.

The steam turbine of the present embodiment further includes a medium flow changing member 60. The medium flow changing member 60 has a plate shape, a part of which is embedded in the rotor shaft 21, and the remaining part of which protrudes radially outward Dro from the rotor shaft 21. The medium flow changing member 60 has a medium flow changing surface 61. The medium flow change surface 61 is directed toward the axis upstream side Dau and expands from the groove bottom surface 23 toward the radially outer side Dro. The medium flow changing surface 61 is located on the axial upstream side Dau with respect to the downstream groove side surface 25 of the annular groove 22 and on the axial downstream side Dad with respect to the most downstream sealing fin 49d located on the axial downstream side Dad among the plurality of sealing fins 49.

The inner shroud 44 has: an upstream end surface 51 facing the upstream groove side surface 24 toward the axial upstream Dau; a downstream end surface 52 facing the downstream groove side surface 25 toward the axis downstream side Dad; a gas passage surface 56 facing the radially outer side Dro; towards the radially inner side Dri. The upstream end surface 51 and the downstream end surface 52 are in a back-to-back relationship in the axial direction Da. The vane body 43 is formed on the gas passage surface 56. The gas passage surface 56 and the seal surface 57 are in a back-to-back relationship in the radial direction Dr. The downstream-side end surface 52 includes: a parallel surface 53 substantially parallel to the downstream-side groove side surface 25; and an inclined surface 54 inclined with respect to the downstream groove side surface 25. The parallel surface 53 forms a radially outer Dro surface of the downstream end surface 52. The inclined surface 54 is a surface gradually facing the axis line downstream side Dad as facing the radial direction outer side Dro. The inclined surface 54 forms a radially inner Dri surface of the downstream end surface 52. The inclined surface 54 is formed over the shield main body 45 of the inner shield 44 and the seal ring 46 of the inner shield 44.

The space in which each blade 33 of the plurality of blades 32 and each blade 43 of the plurality of vanes 42 are present is a space annular around the axis Ar. The annular space forms a medium main flow path 18 through which steam as a working medium flows. The medium main flow path 18 is defined by the gas passage surface 56 of the inner shroud 44 of the stationary blade 42, a portion of the inner circumferential surface of the casing 10 facing the inner shroud 44 in the radial direction Dr, a portion of the outer circumferential surface of the rotor shaft 21 to which the rotor blade 32 is fixed, and the gas passage surface 35 of the outer shroud 34 of the rotor blade 32.

Next, the position of the medium flow changing surface 61 in the axial direction Da and the height in the radial direction Dr will be described with reference to fig. 3.

Here, the distance in the axial direction Da from the end 58 of the inner shroud 44 closest to the axial downstream side Dad to the downstream side groove side surface 25 is referred to as a distance L. In this case, the distance Lf in the axial direction Da from the most downstream seal fin 49d to the medium flow changing surface 61 is equal to or less than the distance L and equal to or more than the distance (0.5 × L). That is, the relationship between the distance L and the distance Lf is as follows.

0.5×L≤Lf≤L

In the present embodiment, the medium flow changing surface 61 is located on the axis downstream side Dad from the end 58 of the inner shroud 44 located on the axis downstream side Dad.

The relationship between the change surface height Hc, which is the distance in the radial direction Dr from the groove bottom surface 23 to the end 62 on the radial outer side Dro of the medium flow change surface 61, and other heights, etc., is as follows.

Hg<(Hg+Hh)＝Hp<Hc

Hg: a seal clearance, which is a distance in the radial direction Dr from the groove bottom surface 23 to an end of the radially inner side Dri of the seal fin 49

Hf: the length of the radial Dr of the sealing fin 49, i.e. the fin height

Hp: the radial Dr distance from the pocket bottom surface 23 to the sealing surface 57 of the inner shroud 44, i.e., the sealing surface height

Next, before explaining the effects of the steam turbine of the present embodiment, a steam turbine of a comparative example will be explained with reference to fig. 4.

The steam turbine of the comparative example also includes the rotor 20 and the plurality of vanes 42x, as in the steam turbine of the present embodiment. The rotor 20 is identical to the rotor 20 of the present embodiment. The vane 42x also includes a blade 43, an inner shroud 44x, and a plurality of seal fins 49, as in the vane 42 of the present embodiment. The inner shroud 44x has an upstream end surface 51, a downstream end surface 52x, a gas passage surface 56, and a seal surface 57, as in the inner shroud 44 of the present embodiment. However, the downstream end surface 52x does not include the inclined surface 54 of the present embodiment. That is, the downstream end surface 52x is a parallel surface whose entire surface is substantially parallel to the downstream groove side surface 25. The steam turbine of the comparative example does not include the medium flow changing member 60 of the steam turbine of the present embodiment.

In the steam turbine of the comparative example, a part of the main steam Sm flowing through the medium main passage 18 flows into the annular groove 22 from the chamber inlet 26 as the leak steam Sl. The leakage steam Sl flows toward the axis line downstream side Dad between the seal surface 57 of the inner shroud 44x and the groove bottom surface 23 of the annular groove 22. However, since the plurality of seal fins 49 are present between the seal surface 57 of the inner shroud 44x and the groove bottom surface 23 of the annular groove 22, the flow rate of the leak steam Sl passing between the seal surface 57 of the inner shroud 44x and the groove bottom surface 23 of the annular groove 22 can be suppressed. The leakage steam Sl having passed through the plurality of sealing fins 49 flows mainly radially outward Dro between the downstream end surface 52x of the inner shroud 44x and the downstream groove side surface 25 of the annular groove 22. The leak steam Sl returns from the chamber outlet 27 to the medium main passage 18.

The leak steam Sl is mixed with the flow of the main steam Sm flowing to the axis line downstream side Dad in the medium main passage 18. As a result, a complicated flowing secondary flow Ss is generated on the downstream side of the mixed portion of the main steam Sm and the leak steam Sl. If the secondary flow Ss is generated in the medium main flow path 18, the efficiency of the steam turbine decreases.

The leak steam Sl that has passed between the end of the radially inner side Dri of the most downstream seal fin 49d of the plurality of seal fins 49 and the groove bottom surface 23 of the annular groove 22 mainly flows along the groove bottom surface 23 toward the axial downstream side Dad. When the leakage steam Sl contacts the downstream-side groove side surface 25, the leakage steam Sl mainly flows substantially radially outward Dro along the downstream-side groove side surface 25. Therefore, of the leakage steam Sl flowing between the downstream side end surface 52x of the inner shroud 44x and the downstream side groove side surface 25 of the annular groove 22, the flow velocity component in the radial direction Dr is increased in the leakage steam Sl flowing radially outward Dro along the downstream side groove side surface 25 as compared with the leakage steam Sl flowing radially outward Dro at a position separated from the downstream side groove side surface 25 toward the axial upstream side Dau. That is, the flow velocity distribution of the leak steam Sl at the chamber outlet 27 in relation to the flow in the radial direction Dr is shown by the two-dot chain line in fig. 4. As shown in this flow velocity distribution, the flow velocity in the radial direction Dr is extremely large at a position close to the downstream groove side surface 25 in the axial direction Da. In the comparative example, the flow velocity in the radial direction Dr sharply decreases as the flow velocity deviates from the position where the flow velocity value is maximum toward the position on the axis upstream side Dau.

Next, the effects of the steam turbine according to the present embodiment will be described with reference to fig. 3.

In the steam turbine of the present embodiment, as in the steam turbine of the comparative example, a part of the main steam Sm flowing through the medium main channel 18 flows into the annular groove 22 from the chamber inlet 26 as the leak steam Sl. The leakage steam Sl flows toward the axis downstream side Dad between the seal surface 57 of the inner shroud 44 and the groove bottom surface 23 of the annular groove 22. In the present embodiment, since the plurality of seal fins 49 are also present between the seal surface 57 of the inner shroud 44 and the groove bottom surface 23 of the annular groove 22, the flow rate of the leak steam Sl passing between the seal surface 57 of the inner shroud 44 and the groove bottom surface 23 of the annular groove 22 can be suppressed.

The leakage steam Sl flowing along the groove bottom surface 23 to the axial downstream side Dad between the end of the radially inner side Dri of the most downstream seal fin 49d and the groove bottom surface 23 of the annular groove 22 contacts the medium flow changing surface 61 present on the axial upstream side Dau with respect to the downstream side groove side surface 25. When contacting the medium flow changing surface 61, the leakage steam Sl mainly flows substantially radially outward Dro along the medium flow changing surface 61.

The leak steam Sl then flows mainly radially outward Dro between the downstream end surface 52 of the inner shroud 44 and the downstream groove side surface 25 of the annular groove 22. The leak steam Sl returns to the medium main passage 18 through the chamber outlet 27.

In the present embodiment, since the plurality of seal fins 49 are provided on the inner shroud 44, the flow of the leak steam Sl passing through the end of the radially inner side Dri of the most downstream seal fin 49d and the groove bottom surface 23 of the annular groove 22 is mainly the flow along the groove bottom surface 23 as described above. Therefore, most of the leaked steam Sl passing between the seal surface 57 of the inner shroud 44 and the groove bottom surface 23 of the annular groove 22 can be brought into contact with the medium flow changing surface 61. Thus, in the present embodiment, the flow rate of the leak steam Sl flowing substantially radially outward Dro along the medium flow changing surface 61 can be increased.

In the present embodiment, as described above, the distance Lf in the axial direction Da from the most downstream seal fin 49d to the medium flow changing surface 61 is equal to or less than the distance L in the axial direction Da from the end 58 of the inner shroud 44 on the most axial downstream side Dad to the downstream side groove side surface 25, and therefore the flow of the main leakage steam Sl can be changed to the flow on the radially outer side Dro at the position on the axial upstream side Dau of the downstream side groove side surface 25.

Thus, in the present embodiment, the flow rate of the leak steam Sl flowing radially outward Dro along the downstream groove side surface 25 is reduced and the flow velocity in the radial direction Dr of the leak steam Sl is also reduced as compared with the comparative example. On the other hand, in the present embodiment, the flow rate of the leak steam Sl flowing radially outward Dro at the position separated from the downstream groove side surface 25 toward the axial upstream side Dau is increased as compared with the comparative example, and the flow velocity in the radial direction Dr of the leak steam Sl is also increased. That is, in the present embodiment, the flow velocity distribution of the leak steam Sl at the chamber outlet 27 with respect to the flow in the radial direction Dr is made uniform as compared with the comparative example, and the maximum flow velocity in the radial direction Dr is also reduced.

In the present embodiment, the inner shroud 44 is formed with the inclined surface 54 which is not formed in the comparative example. Therefore, at least a part of the leak steam Sl flowing substantially radially outward of the medium flow changing surface 61 contacts the inclined surface 54 and flows along the inclined surface 54. As described above, the inclined surface 54 is a surface gradually facing the axis line downstream side Dad as facing the radial direction outer side Dro. Thus, the leakage steam Sl flowing along the inclined surface 54 gradually goes toward the axis line downstream side Dad as going toward the radial outside Dro. Therefore, the flow velocity component of the radial direction Dr in the flow velocity component of the leak steam Sl is reduced as compared with the comparative example. That is, in the present embodiment, the flow velocity component in the radial direction Dr of the leak steam Sl at the chamber outlet 27 can be reduced by the inclined surface 54 as compared with the comparative example.

As described above, in the present embodiment, the flow velocity distribution of the leak steam Sl in the radial direction Dr at the chamber outlet 27 is made uniform as compared with the comparative example as shown by the two-dot chain line in fig. 3 due to the presence of the medium flow changing surface 61 and the inclined surface 54, and the maximum flow velocity in the radial direction Dr is also reduced.

The movement amount is proportional to the square of the velocity, so the flow velocity distribution at the chamber outlet 27 is made uniform, and the smaller the maximum flow velocity in the radial direction Dr is, the more the growth of the secondary flow Ss formed on the axis line downstream side Dad of the mixing position of the main steam Sm and the leak steam Sl can be suppressed. Therefore, in the present embodiment, the growth of the secondary flow Ss can be suppressed compared to the comparative example, and the secondary flow loss can be suppressed.

In the present embodiment, as described above, the secondary flow loss can be suppressed, and therefore, the efficiency of the steam turbine can be improved. In addition, in the present embodiment, since the plurality of seal fins 49 are provided on the inner shroud 44, the flow rate of the leak steam Sl can be suppressed, and from this viewpoint, the efficiency of the steam turbine can be improved.

However, the flow velocity distribution of the leakage steam Sl in the radial direction Dr at the chamber outlet 27 can be made more uniform as the change surface height Hc is higher and the medium flow change surface 61 is closer to the downstream end surface 52 of the inner shroud 44. On the other hand, even if the vane 42 fixed to the casing 10 moves relative to the rotor 20 due to the difference in thermal expansion between the casing 10 and the rotor 20, it is necessary to avoid contact between the downstream end surface 52 of the inner shroud 44 and the medium flow changing member 60.

Here, the distance L in the axial direction Da from the end 58 of the inner shroud 44 closest to the axial downstream side Dad to the downstream side groove side surface 25 is set to a dimension such that the inner shroud 44 of the vane 42 does not contact the downstream side groove side surface 25 of the rotor 20 even if the vane 42 fixed to the casing 10 moves to the axial downstream side Dad relative to the rotor 20 to the maximum extent due to the difference in thermal expansion between the casing 10 and the rotor 20.

In the present embodiment, the distance Lf in the axial direction Da from the most downstream seal fin 49d to the medium flow changing surface 61 is shorter than the distance L, but the inclined surface 54 is formed in the portion on the radially inner side Dri of the downstream end surface 52 of the inner shroud 44, and therefore the portion on the radially inner side Dri of the downstream end surface 52 of the inner shroud 44 escapes to the axially upstream side Dau from the end 58 on the most axial downstream side Dad of the inner shroud 44. In the present embodiment, the distance Lf in the axial direction Da from the most downstream seal fin 49d to the medium flow changing surface 61 is equal to or greater than the distance (0.5 × L). Therefore, in the present embodiment, even if the vane 42 moves relative to the rotor 20 due to the difference in thermal expansion between the casing 10 and the rotor 20, the contact between the downstream end surface 52 of the inner shroud 44 and the medium flow changing member 60 can be avoided.

In the present embodiment, the downstream end surface 52 of the inner shroud 44 includes the inclined surface 54, but the inclined surface 54 may not be included. In this case, the manufacturing cost of the inner shroud 44 can be suppressed, and the effect of the inclined surface 54 cannot be obtained. Thus, in the case where the downstream end surface 52 of the inner shroud 44 does not include the inclined surface 54, the flow velocity distribution of the leak steam Sl in the radial direction Dr at the chamber outlet 27 can be made uniform by the plurality of seal fins 49 and the medium flow changing member 60 provided in the inner shroud 44, but the effect of making the flow velocity distribution uniform is small as compared with the present embodiment.

"second embodiment"

A second embodiment of the axial flow rotary machine according to the present invention will be described with reference to fig. 5.

The axial flow rotary machine according to the present embodiment is also a steam turbine as in the first embodiment. The steam turbine of the present embodiment changes the angle of the inclined surface 54 of the steam turbine of the first embodiment, and the other configurations are basically the same as those of the steam turbine of the first embodiment.

The downstream-side end surface 52a of the inner shroud 44a of the present embodiment also includes a parallel surface 53a substantially parallel to the downstream-side groove side surface 25 and an inclined surface 54a inclined with respect to the downstream-side groove side surface 25, as in the downstream-side end surface 52 of the first embodiment. The parallel surface 53a forms a surface of the radial outer side Dro in the downstream end surface 52 a. The inclined surface 54a is a surface gradually facing the axis line downstream side Dad as facing the radial direction outer side Dro. The inclined surface 54a forms a radially inner Dri surface of the downstream end surface 52 a. The inclined surface 54a is formed over the shield main body 45a of the inner shield 44a and the seal ring 46a of the inner shield 44 a.

A virtual extension line regarding the inclined surface 54a of the present embodiment, i.e., a virtual extension line lv from the inclined surface 54a toward the radial outer side Dro and toward the axis line downstream side Dad does not intersect with the downstream groove side surface 25. In other words, the virtual extension line lv intersects with a virtual extension line extending from the downstream side groove side surface 25 to the radially outer side Dro.

In the present embodiment, the shortest distance Ls from the end 62 on the radial outer side Dro of the medium flow changing surface 61 to the inner shroud 44a is equal to or less than the distance L in the axial direction Da from the end 58 on the most axial downstream side Dad of the inner shroud 44a to the downstream groove side surface 25. That is, the relationship between the distance L and the distance Ls is as follows.

Ls≤L

The distance L, the distance Lf, the changed surface height Hc, the seal gap Hg, the fin height Hf, and the seal surface height Hp in the present embodiment are the same as the corresponding dimensions in the first embodiment.

In the present embodiment, as described above, at least a part of the leak steam Sl flowing along the medium flow changing surface 61 substantially radially outward Dro contacts the sloped surface 54a and flows along the sloped surface 54 a. The leakage steam Sl flowing along the inclined surface 54a gradually moves toward the axis line downstream side Dad as it moves toward the radially outer side Dro.

It is assumed that an imaginary extension line lv associated with the inclined surface intersects the downstream side groove side surface 25. In this case, a part of the leak steam Sl flowing along the inclined surface contacts the downstream-side groove side surface 25. When a part of the leak steam Sl contacts the downstream side groove surface 25, the leak steam Sl flows radially outward Dro along the downstream side groove surface 25. Therefore, in this case, the flow speed of the leak steam Sl flowing in the radial direction Dr at the position of the chamber outlet 27 in the radial direction Dr and at the position close to the downstream side groove side surface 25 in the axial direction Da increases, and the flow amount of the leak steam Sl increases. In this case, the effect of the inclined surface is thereby reduced. Therefore, as in the present embodiment, it is preferable that the imaginary extension line lv of the inclined surface 54a does not intersect with the downstream groove side surface 25, thereby increasing the effect of the inclined surface 54 a.

Here, a space between the end 62 of the medium flow changing surface 61 on the radially outer side Dro and the portion 59 of the inner shroud 44a located at the shortest distance Ls from the end 62 is set as an inlet of the downstream side flow passage in the chamber. The outlet of the flow path on the downstream side of the chamber is referred to as a chamber outlet 27. In the present embodiment, as described above, the shortest distance Ls from the end 62 of the medium flow changing surface 61 on the radially outer side Dro to the inner shroud 44a is equal to or less than the distance L. Thus, the downstream side flow path in the chamber of the present embodiment is an expanded flow path in which the opening area of the outlet is larger than the opening area of the inlet. In the present embodiment, the outlet of the downstream flow passage in the chamber is located on the axis line downstream side Dad of the inlet of the downstream flow passage in the chamber. Therefore, in the present embodiment, the axial direction Da component of the velocity component of the leak steam Sl flowing out from the chamber outlet 27, which is the outlet of the chamber downstream side flow path, can be increased, and the radial direction Dr component can be reduced. Thus, in the present embodiment, the secondary flow Ss formed on the axis line downstream side Dad of the mixing position of the main steam Sm and the leak steam Sl can be suppressed from growing.

"third embodiment"

A third embodiment of the axial flow rotary machine according to the present invention will be described with reference to fig. 6.

The axial flow rotary machine according to the present embodiment is a steam turbine as in the above embodiments. The steam turbine of the present embodiment has the position of the inclined surface 54 of the steam turbine of the first embodiment changed, and the other configurations are basically the same as those of the steam turbine of the first embodiment.

The downstream-side end surface 52b of the inner shroud 44b of the present embodiment also includes a parallel surface 53b substantially parallel to the downstream-side groove side surface 25 and an inclined surface 54b inclined with respect to the downstream-side groove side surface 25, as in the downstream-side end surface 52 of the first embodiment. Unlike the above embodiments, the parallel surface 53b of the present embodiment forms the radially inner Dri surface of the downstream end surface 52 b. The inclined surface 54b is a surface gradually facing the axis line downstream side Dad as facing the radial direction outer side Dro. The inclined surface 54b of the present embodiment forms the radially outer side Dro of the downstream end surface 52. Accordingly, the inclined surface 54b is present in a range from the gas passage surface 56 to a position half the distance between the gas passage surface 56 and the seal surface 57, in other words, a position Ph half the thickness of the inner shroud 44. Further, as described above, since the inclined surface 54b of the present embodiment forms the surface of the radial outer side Dro of the downstream end surface 52b, a virtual extended line extending from the inclined surface 54b does not intersect with the downstream groove side surface 25, as in the second embodiment. The inclined surface 54b of the present embodiment is located at 170 ° relative to the medium flow changing surface 61 from the end 62 on the radially outer side Dro of the medium flow changing surface 61.

In the present embodiment, as in the above embodiments, the relationship between the distance L in the axial direction Da from the end 58 of the inner shroud 44 closest to the axial downstream side Dad to the downstream side groove side surface 25 and the distance Lf in the axial direction Da from the downstream most seal fin 49d to the medium flow changing surface 61 is as follows.

0.5×L≤Lf≤L

In the present embodiment, as in the second embodiment, the relationship between the shortest distance Ls from the end 62 of the medium flow changing surface 61 on the radial outer side Dro to the inner shroud 44b and the distance L is as follows.

Ls≤L

The modified surface height Hc, the seal gap Hg, the fin height Hf, and the seal surface height Hp in the present embodiment are the same as the corresponding dimensions in the first embodiment. In the present embodiment, the inclined surface height Hs, which is the distance in the radial direction Dr from the groove bottom surface 23 to the end of the inclined surface 54 on the inner side Dri in the radial direction, is higher than the modified surface height Hc.

In the present embodiment, in the annular groove 22, a part of the leak steam Sl flowing radially outward between the inner shroud 44b and the downstream groove side surface 25 can be made to follow the inclined surface 54b at a position close to the chamber outlet 27 in the radial direction Dr. Thus, in the present embodiment, the flow velocity component in the radial direction Dr among the flow velocity components of the leak steam Sl at the chamber outlet 27 can be reduced. Thus, in the present embodiment, the flow velocity distribution of the leak steam Sl at the chamber outlet 27 with respect to the flow in the radial direction Dr can be made uniform as compared with the first and second embodiments.

The flow direction of the leaked steam Sl at the position of the end 62 on the radially outer side Dro of the medium flow changing surface 61 is a direction at an angle α of substantially 170 ° with respect to the medium flow changing surface 61. That is, when the leak steam Sl contacts the medium flow changing surface 61, it flows to the radially outer side Dro and slightly flows to the axially upstream side Dau. Note that 170 ° is an angle obtained as a result of flow analysis by a computer. In the present embodiment, as described above, the inclined surface 54b is present in the direction of 170 ° from the end 62 of the radial outer side Dro of the medium flow changing surface 61 with respect to the medium flow changing surface 61. Therefore, in the present embodiment, most of the leak steam Sl flowing substantially radially outward Dro along the medium flow changing surface 61 can be directed toward the inclined surface 54 b. Thus, the end 62 of the inclined surface 54b located radially outward Dro from the medium flow changing surface 61 is oriented at 170 ° to the medium flow changing surface 61, and the effect of the inclined surface 54b can be enhanced.

In the present embodiment, although the distance Lf in the axial direction Da from the most downstream seal fin 49d to the medium flow change surface 61 is shorter than the distance L, the height Hc of the medium flow change surface 61 is lower than the inclined surface height Hs, and the parallel surface 53b present on the radially inner side Dri than the inclined surface 54b escapes to the axially upstream side Dau than the end 58 on the most axial downstream side Dad of the inner shroud 44 b. Therefore, in the present embodiment, even if the vane 42 moves relative to the rotor 20 due to the difference in thermal expansion between the casing 10 and the rotor 20, the contact between the downstream end surface 52b of the inner shroud 44 and the medium flow changing member 60 can be avoided.

"fourth embodiment"

A fourth embodiment of the axial flow rotary machine according to the present invention will be described with reference to fig. 7.

The axial flow rotary machine according to the present embodiment is also a steam turbine as in the above embodiments. The steam turbine of the present embodiment has the position of the medium flow changing surface 61 of the steam turbine of the third embodiment changed, and the other configurations are basically the same as those of the steam turbine of the third embodiment.

In the present embodiment, the distance Lf in the axial direction Da from the most downstream seal fin 49d to the medium flow changing surface 61a of the medium flow changing member 60a is made shorter than that in the third embodiment, and the medium flow changing surface 61a is positioned in the region where the inclined surface 54b exists in the axial direction Da. In the present embodiment, the distance Lf in the axial direction Da from the most downstream seal fin 49d to the medium flow changing surface 61a is shorter than the distance L in the axial direction Da from the end 58 of the most axially downstream side Dad of the inner shroud 44 to the downstream groove side surface 25.

By shortening the distance Lf in the axial direction Da from the most downstream seal fin 49d to the medium flow changing surface 61a in this way, the position in the axial direction Da of the leak steam Sl flowing radially outward to the medium flow changing surface 61a can be positioned on the axial upstream side Dau than in the above embodiments. In the present embodiment, most of the leaking steam Sl flowing radially outward Dro along the medium flow changing surface 61a can be guided to the inclined surface 54 b. Therefore, in the present embodiment, the flow velocity distribution of the leak steam Sl at the chamber outlet 27 with respect to the flow in the radial direction Dr is made uniform as compared with the above embodiments, and the maximum flow velocity in the radial direction Dr is also reduced.

However, if the distance Lf in the axial direction Da from the most downstream seal fin 49d to the medium flow changing surface 61a is shortened, the possibility of contact between the downstream end surface 52 of the inner shroud 44 and the medium flow changing member 60a is increased when the vane 42 moves relative to the rotor 20 due to the difference in thermal expansion between the casing and the rotor 20. Therefore, the modified surface height Hc is equal to or less than the sealing surface height Hp, and preferably equal to or less than the fin height Hf.

Although this embodiment is a modification of the third embodiment, the medium flow changing surface 61 may be located in a region where the inclined surface exists in the axial direction Da in the first and second embodiments as well.

The modified surface height Hc in the above embodiments and the fifth embodiment described below may be equal to or less than the sealing surface height Hp or equal to or less than the fin height Hf.

"fifth embodiment"

A fifth embodiment of an axial flow rotary machine according to the present invention will be described with reference to fig. 8.

The axial flow rotary machine according to the present embodiment is also a steam turbine as in the above embodiments. The steam turbine of the present embodiment also changes the position of the medium flow changing surface 61 of the steam turbine of the third embodiment, and the other configurations are basically the same as those of the steam turbine of the third embodiment.

In each of the above embodiments, the distance Lf in the axial direction Da from the most downstream seal fin 49d to the medium flow changing surface 61 is equal to or less than the distance L in the axial direction Da from the end 58 of the inner shroud 44 on the most axial downstream side Dad to the downstream groove side surface 25. On the other hand, in the present embodiment, the distance Lf in the axial direction Da from the most downstream sealing fin 49d to the medium flow changing surface 61b of the medium flow changing member 60b is greater than the distance L in the axial direction Da from the end 58 of the most axially downstream side Dad of the inner shroud 44 to the downstream groove side surface 25.

However, in the present embodiment, as in the third embodiment, the inclined surface 54b is present at the end 62b radially outside Dro of the medium flow changing surface 61b in the direction of 170 ° with respect to the medium flow changing surface 61 b. Therefore, in the present embodiment, at least a part of the leak steam Sl flowing substantially radially outward Dro along the medium flow changing surface 61b is in contact with the inclined surface 54, and the leak steam Sl can be caused to flow along the inclined surface 54.

Thus, in the present embodiment, the effect of the inclined surface 54 can be obtained as in the third embodiment.

"modification of medium flow changing member"

The medium flow changing member of each of the above embodiments is a plate-shaped member, and a part of the plate-shaped member is embedded in the rotor shaft 21. That is, the medium flow changing member of each of the above embodiments is a member independent from the rotor shaft 21.

However, in the process of machining the rotor shaft 21 from the rotor shaft material, the rotor shaft 21 and the medium flow changing member may be machined together from the rotor shaft material. That is, as shown in fig. 9, the medium flow changing member 60c may be integrated with the rotor shaft 21 without a joint portion with the rotor shaft 21. The medium flow changing member 60c of the present modification has a block-like cross section, and the surface 63 of the radially inner side Dri thereof is directly connected to the downstream groove side surface 25. However, the medium flow changing member 60c integral with the rotor shaft 21 does not have to have a block-shaped cross section, nor does it have to have its radially inner Dri surface connected to the downstream groove side surface 25. Therefore, the medium flow changing member 60c integrated with the rotor shaft 21 may be plate-shaped as in the medium flow changing members 60, 60a, and 60b of the above embodiments.

As described above, the height of the medium flow changing surface of the medium flow changing member and the position in the axial direction Da are important, and the connection relationship with the rotor shaft 21, the thickness of the medium flow changing member in the axial direction Da, and the like can be appropriately changed.

Modification of inclined surface "

The inclined surface in each of the above embodiments is present only in a part of the downstream end surface of the inner shroud.

However, as shown in fig. 10, the downstream end surface 52c of the inner shroud 44c may be entirely inclined.

As shown in fig. 11, the end 55 of the inclined surface 54d of the inner shroud 44d on the radially outer side Dro may not be directly connected to the end 58 of the inner shroud 44d on the axially downstream side Dad of the gas passage surface 56.

The position of the end of the radially inner side Dri of the inclined surface may be limited in the axial direction Da depending on the positional relationship with the most downstream seal fin 49 d. In this case, as can be seen from a comparison between fig. 10 and 11, when the end is positioned radially outward Dro, the inclination direction of the inclined surface approaches the direction of the axis line direction Da. When the inclined surface 54 is inclined in a direction close to the axial direction Da, the flow velocity component in the radial direction Dr of the flow velocity components of the leak steam Sl flowing along the inclined surface decreases. Thus, the flow velocity component in the radial direction Dr of the leak steam Sl at the chamber outlet 27 can be reduced as compared with the case where the position of the end is located on the radially outer side Dro, and the growth of the secondary flow Ss can be suppressed. In this case, the position of the end of the radially inner portion Dri of the inclined surface is preferably within the range from the gas passage surface 56 of the inner shroud to the position Ph of the distance of half the thickness of the radially inner portion Dri of the inner shroud.

The inclined surface may be a curved surface instead of a flat surface. In this case, the inclined surface is preferably a curved surface that gradually displaces toward the axis line downstream side Dad by an amount that increases as it goes toward the radial outside Dro.

Modification of axial-flow rotary machine "

The above embodiments and the above modifications are each exemplified by a steam turbine which is a kind of an axial flow rotary machine. However, the axial flow rotary machine is not limited to the steam turbine. For example, the axial flow rotary machine may be a gas turbine. Therefore, the following description will be given, as a modification of the axial flow rotary machine, with reference to fig. 12 to 14, with respect to a case where the axial flow rotary machine is a gas turbine.

As shown in fig. 12, a gas turbine 100 of the present modification includes a compressor 170 that compresses air a, a combustor 180 that burns fuel F in the air compressed by the compressor 170 to generate combustion gas, a turbine 101 driven by the combustion gas, and an intermediate casing 105.

The compressor 170 includes: a compressor rotor 171 that rotates about an axis Ar; a compressor housing 178 covering the compressor rotor 171; a plurality of vane rows 174. In the present modification, the direction in which the axis Ar extends is referred to as the axial direction Da, the circumferential direction around the axis Ar is simply referred to as the circumferential direction Dc, and the direction perpendicular to the axis Ar is referred to as the radial direction Dr. In the radial direction Dr, a side close to the axis Ar is referred to as a radial inner side Dri, and an opposite side thereof is referred to as a radial outer side Dro. One side in the axial direction Da is referred to as an axial upstream side Dau, and the other side is referred to as an axial downstream side Dad.

The compressor rotor 171 includes: a rotor shaft 172 extending in the axial direction Da about the axis Ar thereof; and a plurality of rotor blade rows 173 attached to the rotor shaft 172. The plurality of rotor blade rows 173 are aligned in the axial direction Da. Each of the rotor blade rows 173 is formed of a plurality of rotor blades arranged in the circumferential direction Dc. Any one of the plurality of stator blade rows 174 is disposed on the downstream side Dad of each axis of the plurality of rotor blade rows 173. Each row 174 of vanes is disposed inboard of a compressor casing 178. Each of the vane rows 174 is formed of a plurality of vanes arranged in the circumferential direction Dc. An annular space between the radially outer peripheral side Dro of the rotor shaft 172 and the radially inner peripheral side Dri of the compressor housing 178 and in a region where the stationary blade row 174 and the movable blade row 173 are arranged in the axial direction Da serves as an air compression flow passage 179 through which air flows and is compressed.

As shown in fig. 13, the burner 180 includes: a combustion liner (or transition piece) 181 that transfers the high-temperature and high-pressure combustion gas G into the turbine 101; and a fuel injector 182 for injecting fuel F into the combustion cylinder 181 together with air compressed by the compressor 170. A fuel line 185 through which the fuel F flows is connected to the fuel injector 182. A fuel control valve 186 is provided in the fuel line 185.

As shown in fig. 12 and 13, the turbine 101 is disposed on the axial downstream side Dad of the compressor 170. The turbine 101 includes: a turbine rotor 120 that rotates about an axis Ar; a turbine housing 110 covering the turbine rotor 120; a plurality of vane rows 141.

As shown in fig. 12, the compressor rotor 171 and the turbine rotor 120 are positioned on the same axis Ar and are coupled to each other to constitute the gas turbine rotor 102. The gas turbine rotor 102 is connected to, for example, a rotor of a generator 189. The intermediate casing 105 is disposed between the compressor casing 178 and the turbine casing 110. The compressor casing 178, the intermediate casing 105, and the turbine casing 110 are connected to each other to form the gas turbine casing 103. The burner 180 is mounted to the intermediate housing 105.

As shown in fig. 12 and 13, the turbine casing 110 includes: a combustion gas inlet (medium inlet) 111 for introducing combustion gas G as a working medium into the interior; and a combustion gas outlet (medium outlet) 115 for discharging the combustion gas G to the outside. The combustion cylinder 181 of the burner 180 is connected to the combustion gas inlet 111. The combustion gas outlet 115 is located on the axis line downstream side Dad with respect to the combustion gas inlet 111.

The turbine rotor 120 includes: a rotor shaft 121 extending in the axial direction Da about the axis Ar; and a plurality of blade rows 131 attached to the rotor shaft 121. The plurality of rotor blade rows 131 are arranged in the axial direction Da and are disposed radially inward Dri of the turbine casing 110. Each of the rotor blade rows 131 is formed of a plurality of rotor blades 132 arranged in the circumferential direction Dc.

The plurality of vane rows 141 are arranged in the axial direction Da. Each of the vane rows 141 is disposed on the axially upstream side Dau of any one of the plurality of blade rows 31. Each of the vane rows 141 is formed of a plurality of vanes 142 arranged in the circumferential direction Dc. Each of the vanes 142 is disposed on the radially inner side Dri of the turbine casing 110 and fixed to the turbine casing 110.

The bucket 132 has an airfoil 133 that is airfoil shaped and extends in a radial direction Dr. The wing 133 is fixed to the rotor shaft 121.

As shown in fig. 13 and 14, the vane 142 includes: an airfoil 143 having an airfoil shape and extending in a radial direction Dr; an inboard shroud 144 provided radially inward Dri of the airfoil 143; a plurality of sealing fins 149 are provided radially inward Dri of the inner shroud 144. The inner shroud 144 has: a shield body 145; and a seal ring 146 fixed to the radially inner side Dri of the shroud body 145. As described above, the vane 142 is disposed on the radially inner side Dri of the turbine casing 110 and fixed to the turbine casing 110. A plurality of seal fins 149 extending from the seal ring 146 to the radially inner side Dri are provided on the radially inner side Dri of the seal ring 146. The plurality of sealing fins 149 are arranged along the axial direction Da.

In the rotor shaft 121, an annular groove 122 is formed in a portion facing the inner shroud 144 of the vane 142 in the radial direction Dr. The annular groove 122 is recessed radially inward Dri and is annular about the axis Ar. The inner shroud 144 and the plurality of sealing fins 149 are disposed in the annular groove 122 in a state of not contacting the annular groove 122. A portion of the opening of the annular groove 122 on the axial upstream side Dau of the inner shroud 144 serves as a chamber inlet 126. Further, of the openings of the annular groove 122, a portion on the axial downstream side Dad of the inner shroud 144 serves as a chamber outlet 127.

The annular groove 122 has: a groove bottom surface 123 facing the radially outer side Dro; an upstream groove side surface 124 extending from an end of the axially upstream side Dau of the groove bottom surface 123 toward the radially outer side Dro; and a downstream groove side surface 125 extending from an end of the axial downstream side Dad of the groove bottom surface 123 toward the radially outer side Dro. The upstream side groove side surface 124 and the downstream side groove side surface 125 face each other in the axial direction Da.

The gas turbine of the present modification further includes a medium flow changing member 160. The medium flow changing member 160 has a plate shape, a part of which is embedded in the rotor shaft 121, and the remaining part of which protrudes radially outward Dro from the rotor shaft 121. The medium flow changing member 160 has a medium flow changing surface 161. The medium flow changing surface 161 is directed toward the axially upstream side Dau and extends from the groove bottom surface 123 toward the radially outer side Dro. The medium flow changing surface 161 is located on the axial upstream side Dau with respect to the downstream groove side surface 125 of the annular groove 122 and on the axial downstream side Dad with respect to the most downstream sealing fin 149d located on the axial downstream side Dad among the plurality of sealing fins 149.

The inner shroud 144 has: an upstream-side end surface 151 facing the upstream-side groove side surface 124 toward the axial upstream side Dau; a downstream end surface 152 facing the downstream groove side surface 125 toward the axis downstream side Dad; a gas passage surface 156 facing the radially outer side Dro; toward the radially inner side Dri. The upstream end surface 151 and the downstream end surface 152 are in a back-to-back relationship in the axial direction Da. The vane body 143 is formed on the gas passage surface 156. The gas passage surface 156 is in back-to-back relationship with the sealing surface 157 in the radial direction Dr. The downstream-side end surface 152 includes an inclined surface 154 inclined with respect to the downstream-side groove side surface 25. The inclined surface 154 is a surface gradually facing the axis line downstream side Dad as it goes to the radial outside Dro. The inclined surface 154 forms a radially inner Dri surface of the downstream end surface 152. The inclined surface 154 is formed over the shield main body 145 of the inner shield 144 and the seal ring 146 of the inner shield 144.

The space in which each blade 133 of the plurality of blades 132 and each blade 143 of the plurality of vanes 142 are present is a space annular around the axis Ar. The annular space forms a medium main flow path 118 through which the combustion gas G as the working medium flows. The medium main flow path 118 is defined by the gas passage surface 156 of the inner shroud 144 of the stationary blade 142, a portion of the inner circumferential surface of the turbine casing 110 that faces the inner shroud 144 in the radial direction Dr, a portion of the outer circumferential surface of the rotor shaft 121 to which the rotor blade 132 is fixed, and a portion of the inner circumferential surface of the turbine casing 110 that faces the rotor blade 132 in the radial direction Dr.

The arrangement of the medium flow changing member 160, the various dimensions of the medium flow changing member 160, the angle and the position of the inclined surface 154 of the inner shroud 144, and the like of the gas turbine 100 according to the present modification described above are the same as those of the first to fifth embodiments and the modifications described above.

As described above, if the configurations of the embodiments and the modifications described above are applied to the gas turbine 100, the flow rate of the leaking combustion gas Gl flowing radially outward Dro along the downstream groove side surface 125 in the annular groove 122 is reduced, and the flow velocity in the radial direction Dr of the leaking combustion gas Gl is also reduced, as in the case of the steam turbine described above. Thus, in the present modification as well, similarly to the steam turbine example described above, it is possible to suppress the growth of the secondary flow formed on the axis line downstream side Dad from the mixing position of the main combustion gas Gm flowing toward the axis line downstream side Dad in the medium main passage 118 and the leaked combustion gas Gl flowing into the medium main passage 118 from the annular groove 122, and to suppress the secondary flow loss.

Thus, in the present modification as well, as described above, the secondary flow loss can be suppressed, and therefore, the efficiency of the gas turbine can be improved.

Industrial applicability

In the axial flow rotary machine according to an aspect of the present invention, the efficiency of the axial flow rotary machine can be improved by suppressing the secondary flow loss.

Description of the symbols

10: steam turbine outer casing (or outer casing)

11: inflow part

11 i: steam inlet (Medium inlet)

12: trunk part

13: outer annular groove

14: sealing fin

15: exhaust part

15 o: steam outlet (Medium outlet)

16 u: upstream side shaft seal

16 d: downstream side shaft seal

17 u: upstream side bearing

17 d: downstream side bearing

18: medium main channel

20: rotor

21: rotor shaft

22: inner annular groove (or simply annular groove)

23: bottom surface of groove

24: upstream side groove side surface

25: downstream side groove flank

26: chamber inlet

27: chamber outlet

31: rotor blade row

32: moving vane

33: wing body

34: outer shield

35: gas passage surface

41: stationary blade row

42: stationary blade

43: wing body

44. 44a, 44b, 44c, 44 d: inner side shield

45. 45 b: shield main body

46. 46 a: sealing ring

49: sealing fin

49 d: downstream-most sealing fin

51: upstream side end face

52. 52a, 52b, 52c, 52 d: downstream side end face

53. 53a, 53 b: parallel surface

54. 54a, 54b, 54 d: inclined plane

55: (radially outer of inclined plane) end

56: gas passage surface

57: sealing surface

58: (most downstream of the axis in the inner shroud) end

60. 60a, 60b, 60 c: medium flow changing member

61. 61a, 61 b: medium flow changing surface

62. 62 b: (radially outer of the medium flow-changing surface) end

100: gas turbine

101: turbine wheel

102: gas turbine rotor

103: gas turbine casing

105: middle outer casing

110: turbine housing

111: combustion gas inlet (media inlet)

114: sealing fin

115: combustion gas outlet (medium outlet)

118: medium main channel

120: turbine rotor

121: rotor shaft

122: annular groove

123: bottom surface of groove

124: upstream side groove side surface

125: downstream side groove flank

126: chamber inlet

127: chamber outlet

131: rotor blade row

132: moving vane

133: wing body

141: stationary blade row

142: stationary blade

143: wing body

144: inner side shield

145: shield main body

146: sealing ring

149: sealing fin

149 d: downstream-most sealing fin

151: upstream side end face

152: downstream side end face

154: inclined plane

156: gas passage surface

157: sealing surface

160: medium flow changing member

161: medium flow changing surface

189: generator

170: compressor with a compressor housing having a plurality of compressor blades

171: compressor rotor

172: rotor shaft

173: rotor blade row

174: stationary blade row

178: compressor shell

179: air compression flow path

180: burner with a burner head

181: combustion barrel (or tail barrel)

182: fuel injector

185: fuel line

186: fuel regulating valve

A: air (a)

F: fuel

G: combustion gas

Gl: leaking combustion gas

Gm: main combustion gas

Sm: main steam

Sl: leaking steam

And Ss: secondary flow

Da: axial direction

And 2, Dau: axial upstream side

And Dad: downstream side of axis

Dc: circumferential direction

Dr: radial direction

Dri: radially inner side

Dro: radially outside

39页详细技术资料下载

上一篇：一种医用注射器针头装配设备

下一篇：通过比色法进行外壳的非破坏性测试的方法

Axial flow rotary machine

相关技术

网友询问留言