JP2014163263A - Gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine capable of balancing a workload taken out by a turbine with cooling of an exhaust part at a highly effective point.SOLUTION: In a gas turbine engine 1 which includes an exhaust part 20 in which an exhaust gas G exhausted from a turbine 10 circulates, the exhaust part 20 has: an exhaust air flow passage 31 in which the exhaust gas G circulates; an ejector 24 which introduces outside air A to the exhaust air flow passage 31 and in which an outflow port 24a is connected to the exhaust air flow passage 31; and an exhaust strut 23 which forms a static pressure reduction region by narrowing a flow passage area of at least one part of the exhaust air flow passage 31 and by accelerating the exhaust gas G. The outflow port 24a of the ejector 24 is provided in the static pressure reduction region.

Description

  The present invention relates to a gas turbine including an exhaust part.

  Conventionally, an aircraft gas turbine engine is known as a gas turbine (see, for example, Patent Document 1). This gas turbine engine has an exhaust inner cylinder and an exhaust outer cylinder provided outside the exhaust inner cylinder, and forms an exhaust passage between the exhaust inner cylinder and the exhaust outer cylinder. Further, the exhaust outer cylinder of the gas turbine engine has an outside air intake port, and due to the ejector effect of the exhaust gas flowing through the exhaust channel, the outside air flows into the exhaust channel via the outside air intake port, thereby By cooling the gas, the exhaust part including the exhaust inner cylinder and the exhaust outer cylinder is cooled.

JP-A-4-31636

  However, in the gas turbine engine disclosed in Patent Document 1, when a large amount of outside air is taken in to cool the exhaust gas, the pressure of the exhaust passage into which the outside air flows increases. When the pressure in the exhaust passage rises, the exhaust gas discharged from the turbine becomes difficult to flow, so that the work taken out by the turbine is reduced. On the other hand, if the amount of outside air taken in is reduced to increase the amount of work taken out by the turbine, it becomes difficult to cool the exhaust gas, so that it becomes difficult to cool the exhaust part including the exhaust inner cylinder and the exhaust outer cylinder.

  Then, this invention makes it a subject to provide the gas turbine which can perform efficiently the work amount taken out with a turbine, and cooling of an exhaust part.

  The gas turbine according to the present invention is a gas turbine including an exhaust portion through which exhaust gas discharged from the turbine flows, wherein the exhaust portion introduces outside air into the exhaust passage through which the exhaust gas flows and the exhaust passage. An ejector whose outlet is connected to the exhaust flow path, and a flow path that forms a static pressure reduction region by increasing the speed of the exhaust gas by reducing the flow area of at least a part of the exhaust flow path A throttle member, and the outlet of the ejector is provided in the static pressure reduction region.

  According to this configuration, the static pressure reduction region can be formed in the exhaust passage by the passage restricting member. Then, by providing the ejector outlet in this static pressure reduction region, a large amount of outside air can be taken in from the ejector outlet. At this time, since the outside air is taken in the static pressure reduction region, an increase in the pressure of the exhaust passage is suppressed. As a result, it is possible to increase the intake amount of the outside air while suppressing an increase in the pressure of the exhaust flow path, so that the exhaust part through which the exhaust gas flows is suitably cooled without reducing the work amount taken out by the turbine. be able to. In other words, the outlet of the ejector is provided in the static pressure drop region, and the intake air pressure is reduced to a predetermined intake amount that can cool the exhaust part, thereby reducing the pressure of the exhaust flow path in which the outside air is taken in. Can be made. As a result, the pressure of the exhaust passage can be reduced while keeping the intake amount of the outside air at a predetermined intake amount, so that the work taken out by the turbine can be improved while cooling the exhaust portion through which the exhaust gas flows. it can. From the above, the amount of work taken out by the turbine and the cooling of the exhaust part can be efficiently performed.

  In this case, the exhaust part includes an exhaust inner cylinder member, an exhaust outer cylinder member provided on a radially outer side of the exhaust inner cylinder member, and an exhaust strut connecting the exhaust inner cylinder member and the exhaust outer cylinder member. The exhaust passage is formed between the exhaust inner cylinder member and the exhaust outer cylinder member, and the exhaust outer cylinder member is provided upstream in the flow direction of the exhaust gas. A downstream exhaust outer cylinder member and a downstream exhaust outer cylinder member provided downstream, and a downstream end of the upstream exhaust outer cylinder member and an upstream end of the downstream exhaust outer cylinder member The downstream end of the upstream exhaust outer cylinder member is partially overlapped, and is located radially inward with respect to the upstream end of the downstream exhaust outer cylinder member, and the ejector A downstream end of the exhaust outer cylinder member and an upstream end of the downstream exhaust outer cylinder member A downstream end of the upstream exhaust outer cylinder member is provided to overlap the exhaust strut in the exhaust gas flow direction, and an opening at the downstream end of the upstream exhaust outer cylinder member is Preferably, the flow path restricting member is the exhaust strut for reducing the flow area in the circumferential direction of the exhaust flow path.

  According to this configuration, the exhaust end strut that connects the exhaust inner cylinder member and the exhaust outer cylinder member by providing the downstream end of the upstream exhaust outer cylinder member overlapping the exhaust strut in the flow direction of the exhaust gas. Can be utilized as a flow path restricting member. For this reason, the exhaust passage can be narrowed in the circumferential direction with a simple configuration without any significant design change.

  In this case, it is preferable that the outlet of the ejector is provided at a position where the circumferential width of the exhaust strut is maximized.

  According to this configuration, the outlet of the ejector can be provided in a portion where the exhaust flow path is most restricted in the circumferential direction, that is, in a portion where the exhaust gas flow velocity is the fastest. For this reason, the work of the turbine and the cooling of the exhaust part can be performed more efficiently.

  In this case, the exhaust part further includes an exhaust inner cylinder member and an exhaust outer cylinder member provided on a radially outer side of the exhaust inner cylinder member, and the exhaust passage includes the exhaust inner cylinder member and the exhaust gas The exhaust outer cylinder member is formed between the upstream exhaust outer cylinder member provided on the upstream side and the downstream exhaust outer cylinder member provided on the downstream side in the exhaust gas flow direction. And the downstream end of the upstream exhaust outer cylinder member and the upstream end of the downstream exhaust outer cylinder member partially overlap, and the downstream end of the upstream exhaust outer cylinder member is It is located radially inward with respect to the upstream end of the downstream exhaust outer cylinder member, and the ejector includes a downstream end of the upstream exhaust outer cylinder member and a downstream exhaust outer cylinder member. An upstream end, and an opening at the downstream end of the upstream exhaust outer tubular member is the The flow path restricting member serves as an outlet, and the downstream end portion of the upstream exhaust outer cylinder member and the downstream side of the upstream exhaust outer cylinder member restrict the flow area in the radial direction of the exhaust flow path. It is preferable that the exhaust inner cylinder member be opposed to the end portion.

  According to this configuration, at least one of the downstream end of the upstream exhaust outer cylinder member and the exhaust inner cylinder member is narrowed so that the flow passage area becomes narrow in the radial direction of the exhaust flow passage, thereby At least one of the downstream end of the tubular member and the exhaust inner tubular member can be used as a flow path restricting member. For this reason, the exhaust passage can be narrowed in the radial direction with a simple configuration without any significant design change.

  In this case, it is preferable that the flow passage restricting member restricts the flow passage area over the entire circumference of the exhaust flow passage.

  According to this configuration, since the static pressure reduction region can be formed by reducing the flow area in the radial direction over the entire circumference of the exhaust flow path, the outside air can be sucked from the entire circumference.

  In this case, it is preferable that the flow passage restricting member restricts the flow passage area at a predetermined portion in the circumferential direction of the exhaust flow passage.

  According to this configuration, since the static pressure reduction region can be formed by narrowing the flow path area in the radial direction at a predetermined portion, outside air can be sucked from the predetermined portion. At this time, the predetermined part includes, for example, a part that does not obstruct the flow of exhaust gas, or a part that can guide the exhaust gas well.

FIG. 1 is a schematic configuration diagram of an exhaust portion of a gas turbine engine according to a first embodiment. FIG. 2 is a cross-sectional view taken along the line AA of FIG. FIG. 3 is a schematic configuration diagram of an exhaust portion of the gas turbine engine according to the second embodiment.

  Embodiments according to the present invention will be described below in detail with reference to the drawings. Note that the present invention is not limited to the embodiments. In addition, constituent elements in the following embodiments include those that can be easily replaced by those skilled in the art or those that are substantially the same.

  FIG. 1 is a schematic configuration diagram of an exhaust portion of a gas turbine engine according to a first embodiment. FIG. 2 is a cross-sectional view taken along line A-A ′ of FIG. 1. A gas turbine engine (gas turbine) 1 according to the first embodiment is a gas turbine engine for an aircraft. As shown in FIG. 1, the gas turbine engine 1 includes a rotor 5 serving as a rotation shaft, a turbine 10, and an exhaust unit 20. Although not shown, a compressor and a combustor are provided on the opposite side of the turbine 10 in the axial direction of the rotor 5. In the first embodiment, description will be made by applying to an aircraft gas turbine engine. However, any gas turbine having an exhaust part 20 may be used.

  The compressor sucks air from the outside, compresses the sucked air, and supplies the compressed air toward the combustor. The combustor injects fuel, mixes the injected fuel and compressed air, and burns the fuel to generate combustion gas (mainstream gas). The generated combustion gas flows into the turbine 10.

  The turbine 10 includes a plurality of stationary blades 11, a plurality of moving blades 12, and a plurality of disk plates 13. The plurality of disk plates 13 are provided according to the plurality of moving blades 12, are fixed to the rotor 5, and are connected to the moving blades 12. The plurality of stationary blades 11 and the plurality of moving blades 12 are alternately arranged.

  The gas turbine engine 1 as described above is compressed into high-temperature and high-pressure compressed air when compressed by a compressor, and combusts when a predetermined fuel is supplied to the compressed air by a combustor. . The high-temperature and high-pressure combustion gas generated by the combustor passes through the plurality of stationary blades 11 and the plurality of moving blades 12 constituting the turbine 10 to rotate the rotor 5. On the other hand, the exhaust gas G that is the combustion gas after the rotor 5 is rotationally driven is discharged from the exhaust unit 20 to the atmosphere.

  Next, the configuration around the exhaust unit 20 will be described in detail. The exhaust unit 20 includes a cylindrical exhaust inner cylinder member 21 and a cylindrical exhaust outer cylinder member 22 provided on the radially outer side of the exhaust inner cylinder member 21. The exhaust unit 20 has an exhaust strut 23 that connects the exhaust inner cylinder member 21 and the exhaust outer cylinder member 22. Between the exhaust inner cylinder member 21 and the exhaust outer cylinder member 22 is an exhaust passage 31 through which the exhaust gas G discharged from the turbine 10 flows. In addition, the exhaust unit 20 includes an ejector 24 connected to the exhaust flow path 31.

  The exhaust inner cylinder member 21 is connected to the turbine 10 at the upstream end (the left side in the drawing) in the flow direction of the exhaust gas G. The upstream end of the exhaust inner cylinder member 21 is located in a radial direction at a portion where the base end side of the moving blade 12 and the disk plate 13 are connected. The exhaust inner cylinder member 21 is formed to have a predetermined diameter from the upstream end to the downstream end.

  The exhaust outer cylinder member 22 is connected to the turbine 10 at an upstream end (left side in the drawing) in the flow direction of the exhaust gas G. The upstream end portion of the exhaust outer cylinder member 22 is located on the distal end side of the rotor blade 12 in the radial direction. The exhaust outer cylinder member 22 is formed so that the radial direction increases from the upstream end to the downstream end. The exhaust outer cylinder member 22 has an upstream side exhaust outer cylinder member 22a and a downstream side exhaust outer cylinder member 22b.

  The upstream side exhaust outer cylinder member 22a is provided on the downstream side of the turbine 10, and is provided on the upstream side of the downstream side exhaust outer cylinder member 22b. The upstream exhaust outer cylinder member 22a has a downstream end diameter smaller than the upstream end diameter of the downstream exhaust outer cylinder member 22b, and the downstream exhaust outer cylinder member 22b. It is arranged inside. In other words, the downstream exhaust outer cylinder member 22b has an upstream end diameter larger than the downstream end diameter of the upstream exhaust outer cylinder member 22a. It arrange | positions on the outer side of the outer cylinder member 22a.

  The upstream exhaust outer cylinder member 22a and the downstream exhaust outer cylinder member 22b partially overlap in the radial direction. Specifically, the downstream end 22a1 of the upstream exhaust outer cylinder member 22a and the upstream end 22b1 of the downstream exhaust outer cylinder member 22b overlap in the radial direction, and the structure of the double pipe It has become. As will be described later, the downstream end 22a1 of the upstream exhaust outer cylinder member 22a and the upstream end 22b1 of the downstream exhaust outer cylinder member 22b constitute a part of the ejector 24.

  The exhaust struts 23 are members that connect the exhaust inner cylinder member 21 and the downstream exhaust outer cylinder member 22b, and a plurality of exhaust struts 23 are provided in the circumferential direction at predetermined intervals. As shown in FIG. 2, each exhaust strut 23 has a blade shape in a cross section cut by a plane orthogonal to the radial direction, and guides the exhaust gas G from the upstream side to the downstream side. The exhaust strut 23 has a maximum width L that maximizes the length (width) in the circumferential direction between the upstream end and the central portion in the axial direction.

  The ejector 24 takes outside air A into the exhaust passage 31 due to the ejector effect caused by the flow of the exhaust gas G in the exhaust passage 31. As described above, the ejector 24 includes the downstream end 22a1 of the upstream exhaust outer cylinder member 22a and the upstream end 22b1 of the downstream exhaust outer cylinder member 22b. In the ejector 24, an opening at the upstream end of the downstream side exhaust outer cylinder member 22b is an inflow port 24b for the outside air A, and is formed in the circumferential direction. The ejector 24 has an opening at the downstream end of the upstream side exhaust outer cylinder member 22a serving as an outlet 24a for the outside air A, and is formed in the circumferential direction. Although not shown in the drawing, an annular slit plate in which a plurality of slits are formed in the circumferential direction at a predetermined interval may be disposed at the inlet 24b of the ejector 24.

  In the ejector 24, the downstream end 22 a 1 of the upstream exhaust outer cylinder member 22 a is provided so as to overlap the exhaust strut 23 in the flow direction of the exhaust gas G. Specifically, the downstream end of the upstream side exhaust outer cylinder member 22a is located in the region of the maximum width L of the exhaust strut 23 in the flow direction of the exhaust gas G. At this time, the downstream side end 22a1 of the upstream side exhaust outer cylindrical member 22a is formed by cutting out a portion overlapping with the exhaust strut 23 so as to have a shape complementary to the wing shape of the exhaust strut 23. For this reason, the outlet 24a of the ejector 24 is formed at a position where the exhaust passage 31 is most restricted in the circumferential direction. Therefore, the exhaust strut 23 functions as a flow passage restricting member that restricts the flow passage area of the exhaust flow passage 31 in the circumferential direction.

  Next, the intake of outside air A by the ejector 24 will be described. The exhaust gas G discharged from the turbine 10 circulates in the exhaust passage 31 between the exhaust inner cylinder member 21 and the upstream side exhaust outer cylinder member 22a. The exhaust gas G flowing through the exhaust passage 31 flows into the exhaust strut 23. Here, since the exhaust flow path 31 is provided with the exhaust strut 23, the flow area of the exhaust flow path 31 in the circumferential direction is reduced. When the flow passage area of the exhaust flow passage 31 is reduced by the exhaust strut 23, the flow rate of the exhaust gas G passing through the exhaust strut 23 becomes faster than the flow velocity before flowing into the exhaust strut 23. In particular, the flow velocity of the exhaust gas G becomes the fastest at the portion of the exhaust strut 23 having the maximum width L where the flow passage area of the exhaust flow passage 31 is most restricted in the circumferential direction. For this reason, when the axial direction of the exhaust strut 23 is set to the front-rear direction, the side surface of the exhaust strut 23 and the periphery of the side surface have a static pressure reduction region E lower than the static pressure on the upstream side and downstream side of the exhaust strut 23 Is formed.

  And since the outflow port 24a of the ejector 24 is located in the site | part of the maximum width L of the exhaust strut 23, it will be located in the static pressure fall area | region E. FIG. For this reason, since the ejector 24 can take in the outside air A by the ejector effect in the region where the static pressure is low, more outside air is provided compared to the case where the outlet 24 a is provided on the upstream side of the exhaust strut 23. A can be captured. The outside air A taken into the exhaust passage 31 via the ejector 24 is sent to the downstream side while being mixed with the exhaust gas G flowing through the exhaust passage 31, thereby cooling the exhaust gas G.

  As described above, according to the configuration of the first embodiment, the static pressure reduction region E can be formed in the exhaust passage 31 by the exhaust strut 23. Then, by providing the outlet 24 a of the ejector 24 in the static pressure reduction region E, a large amount of outside air A can be taken from the outlet 24 a of the ejector 24. At this time, since the outside air A is taken in the static pressure lowering region E, an increase in the pressure of the exhaust passage 31 is suppressed. Thereby, since the intake amount of the outside air A can be increased while suppressing an increase in the pressure of the exhaust passage 31, the exhaust portion 20 through which the exhaust gas G flows without reducing the work amount taken out by the turbine 10. Can be suitably cooled. In other words, the outlet 24a of the ejector 24 is provided in the static pressure reduction region E, and the intake amount of the outside air A is suppressed to a predetermined intake amount that can cool the exhaust portion 20 so that the outside air A is taken in. The pressure (static pressure) in the path 31 can be reduced. As a result, the pressure of the exhaust passage 31 can be reduced while the intake amount of the outside air A is set to a predetermined intake amount, so that the work amount taken out by the turbine 10 while cooling the exhaust portion 20 through which the exhaust gas G flows is cooled. Can be improved. From the above, the work taken out by the turbine 10 and the cooling of the exhaust part 20 can be efficiently performed.

  Further, according to the configuration of the first embodiment, the downstream end portion 22a1 of the upstream side exhaust outer cylinder member 22a is provided to overlap the exhaust strut 23 in the flow direction of the exhaust gas G, so that the exhaust strut 23 can be It can be used as a road throttle member. For this reason, the exhaust passage 31 can be narrowed in the circumferential direction with a simple configuration without any significant design change.

  Further, according to the configuration of the first embodiment, since the outlet 24a of the ejector 24 can be provided at a position where the exhaust strut 23 has the maximum width L, the exhaust passage 31 is narrowed down most in the circumferential direction. That is, the outlet 24a of the ejector 24 can be provided at a portion where the flow velocity of the exhaust gas G is the fastest. For this reason, the work taken out by the turbine 10 and the cooling of the exhaust part 20 can be performed more efficiently.

  In the first embodiment, the downstream end of the upstream side exhaust outer cylinder member 22a is positioned at a portion having the maximum width L of the exhaust strut 23 in the flow direction of the exhaust gas G, whereby the outlet 24a of the ejector 24 is The exhaust strut 23 is formed at a position where the maximum width L is reached. However, the downstream end of the upstream exhaust outer cylinder member 22 a may be at any position as long as it overlaps the exhaust strut 23.

  Moreover, in Example 1, although the exhaust strut 23 was functioned as a flow-path throttle member, it is not limited to this structure. That is, another member different from the exhaust strut 23 may be provided in the exhaust passage 31 as long as it is a member (for example, a manhole) that narrows the flow passage area of the exhaust passage 31 in the circumferential direction.

  Next, a gas turbine engine 50 according to the second embodiment will be described with reference to FIG. FIG. 3 is a schematic configuration diagram of an exhaust portion of the gas turbine engine according to the second embodiment. In the second embodiment, only parts different from the first embodiment will be described in order to avoid the description overlapping with the first embodiment. In the first embodiment, the exhaust strut 23 functions as a flow path restricting member. However, in the second embodiment, the upstream exhaust outer cylinder member 22a functions as a flow path restricting member. Hereinafter, the exhaust part 20 of the gas turbine engine 50 according to the second embodiment will be described.

  As shown in FIG. 3, in the exhaust portion 20, the upstream side exhaust outer cylindrical member 22 a has a shape such that the downstream side end portion 22 a 1 narrows the flow passage area of the exhaust passage 31 in the radial direction. Specifically, the downstream end 22 a 1 of the upstream exhaust outer cylinder member 22 a is curved toward the exhaust inner cylinder member 21. That is, the downstream end 22a1 of the upstream exhaust outer cylinder member 22a has a short radial distance between the downstream end 22a1 of the upstream exhaust outer cylinder member 22a and the exhaust inner cylinder member 21 on the upstream side. To be curved. Further, the downstream end 22a1 of the upstream exhaust outer cylinder member 22a has a radial distance between the downstream end 22a1 of the upstream exhaust outer cylinder member 22a and the exhaust inner cylinder member 21 on the downstream side. It is slightly longer than the upstream side so as to extend in the flow direction of the gas G. That is, the downstream end 22a1 has a portion between which the distance in the radial direction from the exhaust inner cylinder member 21 is shortened between the upstream side and the downstream side. Therefore, the downstream end 22a1 of the upstream exhaust outer cylinder member 22a functions as a flow passage restricting member that restricts the flow passage area of the exhaust flow passage 31 in the circumferential direction.

  Here, the downstream end 22 a 1 of the upstream exhaust outer cylinder member 22 a may have a reduced flow area over the entire circumference of the exhaust flow path 31. Further, the downstream end 22 a 1 of the upstream exhaust outer cylinder member 22 a may have a reduced flow area at a predetermined site (local site) in the circumferential direction of the exhaust flow channel 31.

  As described above, according to the configuration of the second embodiment, the downstream end 22a1 of the upstream exhaust outer cylinder member 22a is narrowed so that the flow passage area becomes narrower in the radial direction of the exhaust flow passage 31. The downstream end 22a1 of the side exhaust outer cylinder member 22a can be used as a flow path restricting member. For this reason, the exhaust passage 31 can be narrowed in the radial direction with a simple configuration without any significant design change.

  Further, according to the configuration of the second embodiment, when the flow passage area is reduced over the entire circumference of the exhaust flow passage 31 by the downstream end 22a1 of the upstream exhaust outer cylinder member 22a, Since the static pressure reduction region E can be formed over the entire circumference, a large amount of outside air A can be taken from the entire circumference.

  Further, according to the configuration of the second embodiment, the flow path area is reduced at a predetermined site (local site) in the circumferential direction of the exhaust flow channel 31 by the downstream end 22a1 of the upstream exhaust outer cylinder member 22a. In this case, since the static pressure reduction region E can be formed at a predetermined part of the exhaust passage 31, a large amount of outside air A can be taken from the predetermined part. At this time, as the predetermined part, there is a part that does not obstruct the flow of the exhaust gas G or a part that can guide the exhaust gas G satisfactorily. Specifically, in consideration of the positions of the plurality of exhaust struts 23 provided in the circumferential direction, for example, at a part located between the exhaust struts 23 when viewed from the flow direction or a part overlapping the exhaust struts 23 The flow passage area of the exhaust flow passage 31 may be reduced.

  In the second embodiment, the downstream end 22a1 of the upstream exhaust outer cylinder member 22a is narrowed so that the flow passage area becomes narrower in the radial direction of the exhaust flow passage 31, but the present invention is not limited to this configuration. For example, the exhaust inner cylinder member 21 may be restricted so that the flow passage area becomes narrower in the radial direction of the exhaust flow passage 31 without restricting the downstream end 22a1 of the upstream exhaust outer tubular member 22a. Further, both the downstream end 22 a 1 of the upstream exhaust outer cylinder member 22 a and the exhaust inner cylinder member 21 may be narrowed so that the flow passage area becomes narrow in the radial direction of the exhaust flow passage 31. That is, any configuration may be used as long as the static pressure reduction region E can be formed in the exhaust flow path 31 by narrowing the flow path area in the radial direction of the exhaust flow path 31.

DESCRIPTION OF SYMBOLS 1 Gas turbine engine 5 Rotor 10 Turbine 11 Stator blade 12 Moving blade 13 Disc plate 20 Exhaust part 21 Exhaust inner cylinder member 22 Exhaust outer cylinder member 22a Upstream exhaust outer cylinder member 22b Downstream exhaust outer cylinder member 23 Exhaust strut 24 Ejector 24a Outlet 24b Inlet 31 Exhaust flow path 50 Gas turbine engine G Exhaust gas A Outside air L Maximum width E Static pressure drop region

Claims (6)

In a gas turbine including an exhaust part through which exhaust gas discharged from a turbine flows,
The exhaust part is
An exhaust passage through which the exhaust gas flows;
An ejector for introducing outside air into the exhaust flow path, and an outlet connected to the exhaust flow path;
A flow passage restricting member that forms a static pressure lowering region by squeezing at least a part of the flow passage area of the exhaust flow passage to increase the exhaust gas speed,
The gas turbine according to claim 1, wherein the outlet of the ejector is provided in the static pressure reduction region. The exhaust part is
An exhaust inner cylinder member;
An exhaust outer cylinder member provided on a radially outer side of the exhaust inner cylinder member;
An exhaust strut connecting the exhaust inner cylinder member and the exhaust outer cylinder member, and
The exhaust passage is formed between the exhaust inner cylinder member and the exhaust outer cylinder member,
The exhaust outer cylinder member has an upstream exhaust outer cylinder member provided on the upstream side in the flow direction of the exhaust gas, and a downstream exhaust outer cylinder member provided on the downstream side, and the upstream exhaust outer cylinder The downstream end of the member and the upstream end of the downstream exhaust outer cylinder member partially overlap, and the downstream end of the upstream exhaust outer cylinder member is upstream of the downstream exhaust outer cylinder member Located radially inward of the end,
The ejector includes a downstream end of the upstream exhaust outer cylinder member and an upstream end of the downstream exhaust outer cylinder member, and the downstream end of the upstream exhaust outer cylinder member is The exhaust gas strut is provided so as to overlap with the exhaust strut in the flow direction of the exhaust gas, and an opening at the downstream end of the upstream exhaust outer cylinder member serves as the outlet.
2. The gas turbine according to claim 1, wherein the flow passage restricting member is the exhaust strut that restricts a flow passage area in a circumferential direction of the exhaust flow passage.   The gas turbine according to claim 2, wherein the outlet of the ejector is provided at a position where a width in the circumferential direction of the exhaust strut is maximized. The exhaust part is
An exhaust inner cylinder member;
An exhaust outer cylinder member provided on a radially outer side of the exhaust inner cylinder member, and
The exhaust passage is formed between the exhaust inner cylinder member and the exhaust outer cylinder member,
The exhaust outer cylinder member has an upstream exhaust outer cylinder member provided on the upstream side in the flow direction of the exhaust gas, and a downstream exhaust outer cylinder member provided on the downstream side, and the upstream exhaust outer cylinder The downstream end of the member and the upstream end of the downstream exhaust outer cylinder member partially overlap, and the downstream end of the upstream exhaust outer cylinder member is upstream of the downstream exhaust outer cylinder member Located radially inward of the end,
The ejector includes a downstream end of the upstream exhaust outer cylinder member and an upstream end of the downstream exhaust outer cylinder member, and an opening at the downstream end of the upstream exhaust outer cylinder member is formed. The outlet,
The flow passage restricting member restricts the flow passage area in the radial direction of the exhaust flow passage and faces the downstream end of the upstream exhaust outer tubular member and the downstream end of the upstream exhaust outer tubular member. The gas turbine according to claim 1, wherein the gas turbine is at least one of an exhaust inner cylinder member.   The gas turbine according to claim 4, wherein the flow passage restricting member restricts a flow passage area over the entire circumference of the exhaust flow passage.   The gas turbine according to claim 4, wherein the flow passage restricting member restricts a flow passage area at a predetermined portion in a circumferential direction of the exhaust flow passage.

Images