JP2011506809A - Rotating machine - Google Patents

Abstract

Provided is a rotating machine capable of reducing the size of the rotating machine and improving the reliability and performance of the rotating machine. First and second casings 1 and 2 are obtained by dividing a substantially cylindrical casing 101 that surrounds the rotor shaft 4 in which the rotor blade 11 is implanted into two substantially at the center with respect to the axial direction of the rotor shaft 4. Of the first and second casings 1 and 2, respectively, having a first joining flange 1 A and a second joining flange 2 A, respectively, surrounded by the casing 101. And a third joint flange 3A that holds the vane ring 3 and is positioned at substantially the center of the axial length of the substantially cylindrical blade ring 3 that holds the stationary blade 10 and surrounds the rotor shaft 4. And assembling the first casing 1, the second casing 2 and the blade ring 3 by sandwiching the third connecting flange 3 </ b> A between the first connecting flange 1 </ b> A and the second connecting flange 2 </ b> A. It is characterized by.

Description

  The present invention relates to a rotary machine, such as a rotary machine used in a steam turbine or a gas turbine.

  Generally, a casing structure used for a steam turbine or a gas turbine is formed by dividing a casing containing a rotor shaft into two parts, an upper casing and a lower casing, and these are coupled in a horizontal plane with bolts in a horizontal plane. (For example, refer to Patent Document 1).

Alternatively, in a turbine referred to as a so-called “vase-type turbine”, the passenger compartment has an integral structure, and a rotor shaft portion is inserted from one end opening of the passenger compartment, and the end opening is the same as that of the passenger compartment. It is configured to be sealed by tightening a screw ring that engages with a screw portion provided on the inner peripheral side (see, for example, Patent Document 2).

  The above-described casing structure is intended to ensure the rigidity of the entire apparatus and prevent leakage of the working fluid with respect to the high-temperature and high-pressure working fluid.

Japanese Utility Model Publication No. 60-195908 JP 59-213907

However, in the case of the vehicle compartment structure divided into two in the horizontal plane as described above, a joining flange is provided around the entire horizontal plane of the upper and lower compartments, and this protrudes from the entire circumference of the horizontal plane of the vehicle compartment. Therefore, there is a problem that the passenger compartment itself is enlarged.
Further, when the passenger compartment is enlarged, there are problems that the mass of the entire turbine is increased, and that raw materials and manufacturing costs are increased.

  Furthermore, if the working fluid leaks from the joint surface between the upper compartment and the lower compartment, the turbine performance may be affected. However, in the case of a structure that is divided into two by the horizontal plane as described above, the joint surface is the compartment. Since the entire circumference of the horizontal plane of this is over, there is a problem that the range in which the working fluid leaks becomes wide. Further, in the case of the structure as described above, since the penetrating portion of the rotor shaft is located on the joint surface of the vehicle compartment, there is a problem that the working fluid is more likely to leak out.

  On the other hand, in the case of the vase-type casing structure, it is considered that the range in which the working fluid leaks can be reduced as compared with the case where a joining flange is provided in the entire casing. However, the structure in which the passenger compartment is sealed by the above-described screw structure can be used only for a relatively small turbine, and in a large turbine, this needs to be a flange structure. In this case, there has been a problem that the flange portion and the joining bolt protrude in the axial direction, the total length of the passenger compartment is increased, and the whole size is increased.

  For example, in the case of a turbine that uses a fluid containing a certain substance that requires attention in handling as a working fluid, it is not allowed to leak the working fluid to the atmosphere. For this reason, a pressure vessel (outer vehicle compartment) that further covers the vehicle compartment is provided, and between this pressure vessel and the vehicle compartment is filled with a clean fluid that is higher in pressure than the working fluid and is not contaminated with a certain substance. The indoor fluid is prevented from leaking outside (see FIG. 5).

  FIG. 5 shows a configuration in which the casing 101 of the turbine body described above is accommodated in the pressure vessel (outer casing) 200. The casing 101 accommodates turbine components (not shown). Further, the rotor shaft 4 passes through the vehicle interior 101 and the pressure vessel 200. Here, a space 201 between the casing 101 and the pressure vessel 200 is filled with a clean fluid that is higher in pressure than the working fluid of the turbine and is not contaminated with a certain substance, and the fluid inside the casing 101 is external. To prevent leakage. However, in the case of the above-described configuration, the increase in the size of the passenger compartment 101 is accompanied by a further increase in the size of the pressure vessel 200.

  In addition, when the inside of the turbine as described above is contaminated with a certain substance, for safety reasons, it is necessary to perform an open inspection from the installation state as it is, such as a general gas turbine or steam turbine. I can't. For this reason, it is necessary to perform open inspection by moving the turbine casing from the turbine building to a dedicated maintenance area. In such a case, the increase in the size of the passenger compartment not only ensures the rigidity of the building, but also has a problem that the capacity of the crane for lifting the passenger compartment is greatly affected.

  Furthermore, in the case of the above-described crucible-type casing structure, the blade ring portion that holds the turbine stationary blade is supported mainly on the end opening side, but in this state, the blade ring portion is cantilevered. It becomes. Especially in large turbines, the overhang of the blade ring part becomes longer with cantilever support, so that not only the core is not sufficiently held, but also the influence of the difference in axial thermal expansion between the rotating part and the stationary part becomes large. There was a problem.

  The present invention has been made to solve the above-described problem, and an object of the present invention is to provide a rotating machine capable of reducing the size of the rotating machine and improving the reliability and performance of the rotating machine. And

In order to achieve the above object, the present invention provides the following means.
According to one aspect of the turbine casing structure of the present invention, a substantially cylindrical casing that surrounds a rotor shaft in which a rotor blade is implanted is divided into two at a substantially central portion with respect to the axial direction of the rotor shaft. The first casing and the second casing, and the first casing and the second casing have openings in the first casing and the second casing, respectively. A third ring that is surrounded by the casing and that holds the stationary blade and that is positioned substantially at the center of the axial length of the substantially cylindrical blade ring that surrounds the rotor shaft and holds the blade ring. The first casing, the second casing, and the wing are sandwiched between the first and second joining flanges. It is a cabin structure that assembles the ring.

According to the above aspect, the casing is divided into two in the axial direction, for example, the casing is divided into two by the dividing plane intersecting the rotor axis, so that the casing extends in two, for example, along the rotor axis. Compared to the configuration in which the dividing surface is divided into two, the size of the passenger compartment can be reduced.
That is, when the horizontal plane is divided into two, the joint flange used for fastening the two-divided vehicle compartment projects outward from the entire circumference of the vehicle compartment. In general steam turbines and gas turbines, the cross section of the passenger compartment when divided into two in a plane perpendicular to the rotor axial direction is more horizontal than the horizontal cross section of the passenger compartment when divided into two in the horizontal plane. The cross-sectional area becomes smaller. Therefore, in the vehicle compartment (the first vehicle compartment and the second vehicle compartment) formed by being divided into two in the axial direction, the range in which the joint flange protrudes compared to the configuration in which the vehicle compartment is divided into two in the horizontal plane. Can be reduced. Thereby, size reduction of a vehicle interior can be achieved.

According to the above aspect, the first joint in the first casing in which the third joint flange extending in the direction intersecting the axial direction from the blade ring, more preferably in the substantially vertical direction, is divided into two in the axial direction. By assembling the first casing, the second casing, and the wing ring by sandwiching between the flange and the second joint flange in the second casing, the overhang of the wing ring can be reduced. it can.
In other words, by holding the blade ring with respect to the passenger compartment via the third joint flange located in the substantially central portion in the axial direction of the blade ring, for example, compared with the crucible structure described in Patent Document 2 Thus, the overhang of the blade ring can be reduced. This improves the accuracy of the blade ring core holding with respect to the rotor shaft. Further, since the blade ring is supported at the substantially central portion in the axial direction, it is possible to evenly distribute the thermal elongation in the axial direction of the blade ring.

In the above aspect, it is desirable that the connecting member disposed between the blade ring and the casing is shaped so that the inner peripheral side of the connecting member protrudes from the high pressure side to the low pressure side of the working fluid. In other words, the coupling member is disposed between the blade ring and the third joint flange, and in the working fluid flowing between the moving blade and the stationary blade toward the radially outer side centering on the rotor shaft. It is desirable that the member is a conical member that is inclined from the high pressure side to the low pressure side.
Thereby, since a connection member functions as an end plate in a pressure vessel, the strength of the connection member is improved.

  According to the above aspect, by forming the vehicle compartment in two in the axial direction, compared with the configuration in which the horizontal plane is divided into two, leakage of the working fluid to the outside of the vehicle compartment, Inflow of fluid is reduced. That is, since there is no joint surface of the flange in the through-hole portion of the rotor shaft, leakage of the working fluid to the outside of the vehicle interior, inflow of other fluid into the vehicle interior, and the like are reduced.

  In the above aspect, an outer peripheral surface of the third joint flange sandwiched between the first and second joint flanges of the first and second casings divided into two in the axial direction is the first and second joints. It can also be set as the structure enclosed between the flanges. In other words, the first joining flange and the second joining flange are joined directly on the radially outer side centering on the rotor shaft, and joined with the third joining flange sandwiched therebetween on the radially inner side. It can also be configured.

  As a result, the flange joint surface on the outer peripheral surface in the passenger compartment becomes one place, and the range of the joint surface can be reduced, so that leakage of working fluid to the outside of the passenger compartment and inflow of other fluid into the passenger compartment is further reduced. .

  In the above aspect, a pressure vessel that houses the vehicle compartment is provided outside the vehicle compartment, and flows between the moving blade and the stationary blade in a space between the vehicle compartment and the pressure vessel. It is desirable to fill a higher pressure fluid than the working fluid.

  According to the above aspect, by filling the space between the vehicle compartment and the pressure vessel with a fluid having a pressure higher than that of the working fluid, the working fluid is prevented from flowing out into the space described above. The outflow of the working fluid to the is prevented.

According to the rotating machine of the present invention, the casing is divided into two in the axial direction, so that the casing and the pressure vessel (external casing) surrounding the casing can be reduced in size, and the outside of the casing can be reduced. Leakage of the working fluid into the vehicle, inflow of other fluid into the vehicle compartment, and the like are reduced, and the reliability and performance of the rotating machine are improved.
Furthermore, the accuracy of the blade ring core holding with respect to the rotor shaft is improved, and the reliability of the rotating machine can be improved.

It is a mimetic diagram explaining the whole gas turbine composition concerning the 1st example of the present invention. FIG. 2A is a schematic plan view of a configuration in which the passenger compartment structure is divided into two in the axial direction. FIG. 2B is a schematic axial side view of a configuration in which the passenger compartment structure is divided into two in the axial direction. FIG. 3A is a schematic plan view of a configuration in which the passenger compartment structure is divided into two horizontally. FIG. 3B is a schematic axial side view of a configuration in which the vehicle interior structure is divided into two horizontally. It is a schematic diagram explaining the whole structure of the gas turbine which concerns on the 2nd Example of this invention. It is a schematic diagram explaining the structure by which a gas turbine casing is accommodated in a pressure vessel.

[First Embodiment]
A casing structure of a gas turbine according to an embodiment of the present invention and a gas turbine including the same will be described with reference to FIGS. 1 to 5.

FIG. 1 is a schematic diagram for explaining the overall configuration of a gas turbine according to a first embodiment of the present invention.
As shown in FIG. 1, the gas turbine (rotary machine) 100 includes a casing 101 that forms the outer shape of the gas turbine 100, a blade ring 3 that holds the turbine stationary blade 10 on the inner peripheral side, and a turbine blade. The rotor shaft 4 in which the turbine 11 is implanted, the inlet scroll portion 5 that supplies the working fluid to the first stage of the turbine stationary blade 10, and the working fluid discharged from the final stage of the turbine section rotor blade 11 flows in. An exhaust scroll unit 6 is provided.

  In the gas turbine 100, the working fluid is accelerated by the turbine stationary blade 10 and sprayed to the turbine rotor blade 11, thereby converting the thermal energy of the working fluid into mechanical rotational energy, rotating the rotor shaft 4, and generating power. It is something to take out. The turbine stationary blade 10 and the turbine rotor blade 11 are generally provided in a plurality of stages.

  As shown in FIG. 1, the casing 101 constitutes the outer shape of the gas turbine 100, and the blade ring 3, the rotor shaft 4, the inlet scroll portion 5, the exhaust scroll portion 6, and the like are accommodated therein. It is. The vehicle interior 101 is divided into two substantially at the center in the direction of the rotor shaft 4, and is defined as a high pressure side vehicle interior 1 (first vehicle interior) and a low pressure side vehicle interior 2 (second vehicle interior). .

The passenger compartments 1 and 2 are substantially cylindrical members whose one end is closed, in other words, a bottomed cylindrical member, that is, a so-called bowl-shaped member. The vehicle compartments 1 and 2 have flanges 1A and 2A, respectively, on the outer periphery of the opening end. The casings 1 and 2 are configured to be fastened with the opening ends facing each other and sandwiching a flange 3A of a blade ring 3 described later between the flange 1A and the flange 2A.
A through hole 7 through which the rotor shaft 4 is inserted is provided at the closed ends of the casings 1 and 2, and an opening 8 through which a pipe through which a working fluid flows in or out is inserted in the cylindrical surfaces of the casings 1 and 2. Is provided.

As shown in FIG. 1, the blade ring 3 surrounds the rotor shaft 4 together with the casings 1 and 2, constitutes the gas turbine 100, and supports the turbine stationary blade 10.
The blade ring 3 includes a substantially cylindrical member extending in the axial direction centered on the rotation axis L, a flange 3A disposed on the outermost periphery, and a substantially conical surface that holds the substantially cylindrical blade ring member by the flange 3A. The connecting member 3B is a member, and the flange 3A is disposed between the flanges 1A and 2A. A turbine stationary blade 10 is held on the inner peripheral side of the blade ring 3. The flange 3 </ b> A is substantially at the center position in the axial length of the blade ring 3.

  As shown in FIG. 1, the rotor shaft 4 is rotationally driven around the rotation axis L by spraying the working fluid accelerated by the turbine stationary blade 10 onto the turbine blade 11. It is. In general, the turbine stationary blades 10 and the turbine rotor blades 11 are alternately provided in a plurality of stages, and these configurations can use known configurations and are not particularly limited.

  As shown in FIG. 1, the inlet scroll unit 5 and the exhaust scroll unit 6 pass the working fluid therein, and supply the working fluid to the first stage of the turbine stationary blade 10, respectively. The working fluid discharged from the final stage flows in.

Next, the operation of the gas turbine 100 having the above configuration will be described.
As shown in FIG. 1, the working fluid heated to a high temperature in the high temperature gas furnace flows into the inlet scroll portion 5 of the gas turbine 100. The working fluid that has flowed into the inlet scroll portion 5 flows into the annular flow path 31 and flows into the cylindrical flow path 32 at a substantially uniform flow rate in the circumferential direction. The working fluid that has flowed into the cylindrical flow path 32 is guided toward the first stage of the turbine vane 10.

  As shown in FIG. 1, the turbine rotor blade 11 is rotationally driven by the flowing working fluid, and the rotational driving force extracted by the rotor blade 11 is transmitted to the rotary shaft 4. The working fluid in which the rotational driving force is extracted by the turbine blades 11 and the temperature is lowered is discharged from the final stage of the turbine blades 11.

  The working fluid discharged from the final stage of the turbine rotor blade 11 flows into the cylindrical flow path 32 of the exhaust scroll portion 6 and flows toward the annular flow path 31 as shown in FIG. The working fluid that has flowed into the annular flow path 31 is discharged from the exhaust scroll portion 6, that is, the gas turbine 100, and is again guided to the high temperature gas furnace through each device.

  According to said structure, compared with the structure which divided the horizontal surface into 2 parts by forming the compartment 101 in the axial direction, the size of the said compartment 101 can be achieved. That is, the flanges 1A and 1B used to fasten the two compartments 1 and 2 protrude outward from the entire circumference of the compartment 101, but the cross section of the cross section perpendicular to the axial direction is larger than the horizontal cross section. Due to the small size, in the vehicle compartment formed in the axial direction divided into two parts, the protruding range of the flange can be made small compared to the structure in which the horizontal plane is divided into two parts.

This is schematically shown using FIGS. 2A, 2B, 3A and 3B.
2A and 2B show a casing structure of a gas turbine having an axially divided configuration, and are a plan view and a side view as seen from the axial direction, respectively. The hatched portions 1 </ b> A and 1 </ b> B are connecting flanges provided in the vehicle compartment 1 and the vehicle compartment 2 that are divided into two in the axial direction, and project from the vehicle compartment 1 and the vehicle compartment 2. Further, the length of the entire passenger compartment 101 is L1, and the diameter of the passenger compartment 101 is D1. In a general gas turbine, L1 is larger than D1. Here, when a cylindrical pressure vessel is provided outside the vehicle compartment 1 and the vehicle compartment 2, the external shape of the pressure vessel is as indicated by a two-dot chain line 200, the length is L2, and the diameter is D2.

  On the other hand, FIGS. 3A and 3B show a casing structure of a gas turbine having a structure in which a horizontal plane is divided into two, and are a plan view and a side view as seen from the axial direction, respectively. The hatched portions 111A and 111B are connecting flanges provided in the upper compartment 111 (upper compartment) and the lower compartment 112 (lower compartment) of the compartment divided in two on a horizontal plane. The vehicle body 111 and the vehicle compartment 112 have a shape projecting radially outward and axially outward with the rotation axis L as the center. Further, the length of the entire passenger compartment 101 is L1, and the diameter of the passenger compartment 101 is D1. If the shape of the gas turbine itself is the same in the case of the axially divided configuration (configuration of the present embodiment) and the configuration in which the casing is divided into two on the horizontal plane, L1 and D1 have the same dimensions. Here, when a cylindrical pressure vessel is provided outside the vehicle compartment 111 and the vehicle compartment 112, the outer shape of the pressure vessel is as indicated by a two-dot chain line 210, the length thereof is L3, and the diameter is D3. To do.

Here, as is apparent from the figure, the axially divided configuration shown in FIGS. 2A and 2B (configuration of the present embodiment) is more than the horizontal split configuration shown in FIGS. 3A and 3B (conventional configuration). The shaded area is also small. That is, it can be seen that the protruding range of the flange is small.
Also, when the pressure vessel is provided outside the passenger compartment 101, the diameter D2 of the axially divided configuration is equal to the diameter D3 of the horizontally divided configuration, but the length L2 of the axially divided configuration is equal to the length of the flange. It can be seen that the length can be shortened by a length corresponding to the protruding width than the length L3 of the horizontal two-part configuration.

  As a result, it is possible to reduce the size of the passenger compartment 101, not only reduce the material and manufacturing costs, but also reduce the mass of the entire gas turbine 100, which makes it easy to move the gas turbine 100 by inspection or the like. , Improving maintainability. Further, when the pressure vessel 200 is provided outside the gas turbine 100, the size can be reduced, so that not only the material and the manufacturing cost can be reduced, but also the building of the gas turbine can be reduced. Note that, as described above, in a general gas turbine, the length L1 is larger than the diameter D1, and therefore, the casing 101 can be reduced in size by adopting a two-axis configuration.

  According to the above configuration, the blade ring 3 is overhanged by assembling the casings 1 and 2 and the blade ring 3 by sandwiching the flange 3A of the blade ring between the joint flanges 1A and 2A of the casings 1 and 2. Can be reduced. That is, by holding the substantially central portion of the blade ring 3 in the axial direction with respect to the passenger compartment, the overhang of the blade ring 3 can be reduced as compared with the crucible structure. Thereby, the precision of the core holding | maintenance of the blade ring 3 with respect to the rotor shaft 4 is improved. Further, since the blade ring 3 is supported at substantially the center in the axial direction, the axial thermal expansion of the blade ring 3 can be evenly distributed, and the reliability of the gas turbine 100 is improved.

According to said structure, the connection member 3B of the blade ring 3 plays the role of the end plate in a pressure vessel. A region 12 surrounded by the casing 1 and the blade ring 3 is the inlet side of the working fluid, and a region 13 surrounded by the casing 2 and the blade ring 3 is the outlet side of the working fluid. The pressure in the region 12 is higher. Therefore, as shown in FIG. 1, the pressure resistance of the connecting member 3 </ b> B is improved by projecting the radially inner peripheral side of the connecting member 3 from the high pressure side region 12 toward the low pressure side region 13.
In this embodiment, the connecting member 3B has a substantially conical surface shape, but may have a curved surface shape as long as it plays a role as an end plate. Moreover, if the intensity | strength requested | required of the connection member 3B by the pressure difference of the area | region 12 and the area | region 13 is relatively small, the connection member 3B may be flat form, and is not specifically limited.

  According to the above configuration, the casing 101 is divided into two parts in the axial direction, so that compared with the configuration in which the horizontal plane is divided into two parts, leakage of the working fluid to the outside, Inflow due to the entrainment of the fluid can be reduced. That is, since there is no flange joint surface in the through-hole portion of the rotor shaft, the leakage of the working fluid to the outside of the passenger compartment and the inflow of other fluids into the passenger compartment are further reduced.

According to the above configuration, by forming the casing 101 in two in the axial direction, the internal pressure load acting on the joint flange of the split surface by the pressure of the working fluid is compared with the configuration in which the horizontal plane is divided into two. It can be made uniform and reduced.
When the horizontal plane is divided into two parts, the high pressure part and the low pressure part exist in the vehicle interior as described above, and therefore the internal pressure load acting on the joint flange part is not constant depending on the position. For this reason, it is necessary to consider this in the strength design of the bolt for fastening the flange and the flange itself. On the other hand, since the casing 101 is divided into two parts in the axial direction, the loads acting on the flanges 1A and 2A are uniform in the circumferential direction, so that the strength design of the flanges and fastening bolts is facilitated. Further, as schematically shown below using FIGS. 2A, 2B, 3A, and 3B, the internal pressure load acting on the flange can be reduced.

In the case of the axially divided configuration, the pressure receiving area A1 of the flange joint portion is roughly calculated by the following equation (1).
A1 = π × D1 ÷ 4. . . (1)
Here, π is the circumference ratio.

On the other hand, in the case of the horizontal two-part configuration, the pressure receiving area A2 of the flange joint is roughly calculated by the following equation (2).
A2 = L1 × D1. . . (2)

Here, since π≈3.14 and L1> D1, it can be seen that A1 <A2 from the following equation (3).
A1 = π × D1 ² ÷ 4 <D1 ² <L1 × D1 = A2. . . (3)
Assuming that the pressure acting on the split surface is approximately the average pressure of the high-pressure part and the low-pressure part, and the internal pressure load acting on the flange is determined by the aforementioned pressure-receiving area in both the axially divided structure and the horizontally divided structure. Therefore, it can be seen that the internal pressure load is reduced in the axially divided configuration.

[Second Embodiment]
FIG. 4 is a schematic diagram illustrating the overall configuration of the gas turbine according to the second embodiment of the present invention. The basic configuration of the gas turbine of this embodiment is the same as that of the first embodiment, but the third joining flange holding structure is different from that of the first embodiment. Therefore, in the present embodiment, only the holding structure of the third joint flange will be described with reference to FIG. 4, and description of other components will be omitted. The same components as those in the first embodiment are designated by the same reference numerals and the description thereof is omitted.

  In the second embodiment, as shown in FIG. 4, the outer peripheral surface of the flange 3A sandwiched between the casing 1 of the gas turbine 300 divided into two in the axial direction and the flanges 1A and 1B of the casing 2 is flanged. It is the structure enclosed between 1A and 1B.

  Here, in the first embodiment, the flange 3A is sandwiched between the flange 1A and the flange 2A of the passenger compartment 1 and the passenger compartment 2. For this reason, there are two flange joint surfaces on the outer peripheral side of the passenger compartment 101. On the other hand, according to the configuration of the second embodiment, the outer peripheral portion 3C of the flange 3A is enclosed between the flange 1A and the flange 2A, so that the flange 1A and the flange 2A are directly joined on the outer peripheral side of the vehicle interior 101. Is done. As a result, the number of joints is one, and the peripheral length of the joint surface can be substantially halved. As a result, leakage of the working fluid to the outside of the passenger compartment, inflow of other fluids into the passenger compartment, and the like are reduced.

  According to said structure, compared with the horizontal two division structure, the axial direction two division structure has the circumference length of the cross section of a flange junction part shorter, and forms the said vehicle interior 101 into two axial directions division | segmentation. Thus, the range of the joint surface can be reduced as compared with the configuration divided into two. As a result, leakage of the working fluid to the outside of the passenger compartment, inflow of other fluid into the outer casing, and the like are reduced.

This is schematically shown using FIGS. 2A, 2B, 3A and 3B.
As described in the first embodiment, FIG. 2A and FIG. 2B show a casing structure of a gas turbine having an axially divided configuration, and are a plan view and a side view as seen from the axial direction, respectively. Here, hatched portions 1A and 1B are connecting flanges provided in the vehicle compartment 1 and the vehicle compartment 2 that are divided into two in the axial direction. In a general gas turbine, the length L1 is larger than the diameter D1 of the passenger compartment 101. Here, the peripheral length L10 of the cross section of the flange joint is roughly calculated by the following equation (4).
L10 = π × D1. . . (4)
Here, π is the circumference ratio.

On the other hand, FIG. 3A and FIG. 3B show the casing structure of the gas turbine of the horizontal plane divided structure, and are a plan view and a side view as seen from the axial direction, respectively. Here, hatched portions 111A and 111B are connecting flanges provided in the vehicle interior 111 and the vehicle interior 112 that are divided into two on a horizontal plane. Similarly, if the length of the entire casing 101 is L1 and the diameter of the casing is D1, the peripheral length L11 of the cross section of the flange joint is roughly calculated by the following equation (5).
L11 = 2 × (L1 + D1). . . (5)

Here, since π≈3.14 and L1> D1, it can be seen that L10 <L11 by the following equation (6).
L10 = π × D1 <2 × (D1 + D1) <2 × (L1 + D1) = L11. . . (6)
As a result, the axial two-part configuration is shorter than the horizontal two-part configuration, and the circumferential length of the cross section of the flange joint is shorter. Compared to the configuration, the range of the joint surface can be reduced. As a result, the leakage of the working fluid to the outside of the passenger compartment, the inflow of other fluids into the passenger compartment, and the like can be further reduced, so that the reliability of the gas turbine 300 can be improved.

The technical scope of the present invention is not limited to the above embodiment, and various modifications can be made without departing from the spirit of the present invention.
For example, in the above embodiment, the present invention is applied to an axial flow turbine, but the present invention is not limited to an axial flow turbine, and a centrifugal or mixed flow turbine, It can be applied to other various turbines.

  The present invention can be applied to other types of gas turbines such as gas turbines using air as a working fluid and combustion energy such as fossil fuel as a heat source, or rotating machines such as steam turbines and compressors in particular. It is not limited.

1 compartment (first compartment)
2 compartment (second compartment)
1A, 2A, 3A, 111A, 112A Flange 3 Blade ring 3B Connecting member 3C Flange outer peripheral surface 4 Rotor shaft 5 Inlet scroll portion 6 Exhaust scroll portion 7 Shaft through portion 10 Turbine stationary blade 11 Turbine blade 12 High pressure side (high pressure portion)
13 Low pressure side (low pressure part)
31 annular flow channel 32 cylindrical flow channel 100,300 gas turbine (rotary machine)
101 Cabin (entire cabin)
111 compartment (upper compartment)
112 Car compartment (lower car compartment)
200,210 Pressure vessel (external compartment)
201 Space L Rotation axis L1 Length of vehicle compartment L2 Length of pressure vessel (in the case of a two-part configuration in the axial direction)
L3 Pressure vessel length (in the case of horizontal two-part configuration)
D1 Cabin diameter D2 Pressure vessel diameter (in the case of an axially divided configuration)
D3 Pressure vessel diameter (in the case of horizontal two-part configuration)

Claims (4)

A first casing and a second casing, which are divided into two substantially in the center with respect to the axial direction of the rotor shaft, are substantially cylindrical casings surrounding the rotor shaft in which the rotor blades are implanted. Have
In the opening in the first casing and the second casing, respectively, a first joining flange and a second joining flange are provided,
A third ring that is surrounded by the casing and that holds the stationary blade and that is positioned substantially at the center of the axial length of the substantially cylindrical blade ring that surrounds the rotor shaft and holds the blade ring. With a joining flange of
The first casing, the second casing, and the blade ring are assembled by sandwiching the third joining flange between the first joining flange and the second joining flange. Rotating machine. The blade ring is held by a substantially conical connecting member with respect to the third joint flange,
2. The rotation according to claim 1, wherein the blade ring side inner peripheral surface of the coupling member protrudes from a high pressure side to a low pressure side in a working fluid flowing between the moving blade and the stationary blade. machine.   The rotating machine according to claim 1 or 2, wherein an outer peripheral portion of the third joint flange is enclosed between the first joint flange and the second joint flange. A pressure vessel is provided outside the passenger compartment to house the passenger compartment,
The space between the casing and the pressure vessel is filled with a fluid having a pressure higher than that of the working fluid flowing between the moving blade and the stationary blade. Rotating machine.

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