JP6547534B2 - Axial flow machine disassembly method - Google Patents

Description

  The present invention relates to an axial flow machine disassembly method.

  Axial flow machines are well known as axial flow compressors that convert kinetic energy of fluid to pressure energy, and axial flow turbines that convert kinetic energy of fluid to rotational energy that rotates a rotating shaft or a fan. The axial flow machine includes a rotating shaft having a moving blade on the outer peripheral surface, and a cylindrical casing having an inner peripheral surface having a stationary blade facing the moving blade in an axial direction surrounding the rotating shaft and extending the rotating shaft. (For example, refer to the following patent document 1).

JP, 2011-208505, A

  By the way, the conventional casing has a structure that can be divided into a plurality of cylindrical casings in the axial direction in which the rotation axis extends, and a half in the horizontal direction (radial direction) orthogonal to the axial direction in order to enable assembly and disassembly. And the structure which can be divided | segmented into the casing of a crack. In the case of an axially divided structure, the casing must be divided for each row of vanes, and in order to fasten the divided casing in the axial direction, a large number of flanges and fastening parts are required, resulting in an increase in weight. There's a problem. In addition, in the case of the structure divided in the horizontal direction, the casing is broken in half and the pressure resistance is lowered, and the casing is easily elliptically deformed, and if the clearance is not sufficiently secured, the stationary blade contacts the moving blade. There's a problem.

  Therefore, the inventor of the present application forms the stator vanes from a plurality of stator vane segments, provides an insertion / removal port capable of inserting and removing the stator vane segments on the outer peripheral surface of the casing, and guides the stator vane segments on the inner peripheral surface of the casing. The present invention has considered a structure that solves the above-mentioned problems while allowing the assembly and disassembly by providing a guide groove for holding and holding a plurality of rows of stator blades in the casing. However, when this structure is adopted, for example, in the case of periodical maintenance of an axial flow machine, the process of taking out the stationary blade from the insertion / removal opening for pulling out the rotary shaft from the casing is troublesome. There is a problem that it takes time to disassemble.

  The present invention has been made in view of the above problems, and an object thereof is to provide an axial flow machine disassembling method capable of shortening the time required for the disassembling operation.

  In order to solve the above problems, the present invention has a rotating shaft having moving blades on its outer peripheral surface, and an inner peripheral surface which surrounds the rotating shaft and which faces the moving blades in the axial direction in which the rotating shaft extends. And the casing is formed of a plurality of stator vane segments, the casing is open to the outer peripheral surface, and the stator vane segment is inserted. And a guide groove for guiding the stationary vane segment inserted through the insertion and removal opening along the inner circumferential surface, and the stationary vane segment and the stationary vane segment through the insertion and removal opening. And a hooking step engageable with the guide groove to replace the flat-plate stationary vane dummy not axially opposed to the moving blade, and after the switching step, engaging with the guide groove The stationary vane dummy and the stationary vane segment A moving step of moving along the circumferential surface and moving the next stationary vane segment to a position opposite to the insertion and removal opening is alternately repeated, and after replacing all of the stationary vane segments with the stationary vane dummy, A method is employed in which one of the rotating shaft and the casing is axially removed from the other.

  Further, in the present invention, the stator vane segment includes a shroud portion provided with a hook portion engageable with the guide groove, and a wing portion supported by the shroud portion, and the stator vane dummy is The method of having a shape corresponding to the shroud portion is adopted.

  Further, in the present invention, the stator vane dummy includes a plurality of through holes arranged at intervals in the circumferential direction along the inner circumferential surface of the casing when engaged with the guide groove, In the moving step, the method of moving the stationary blade dummy and the stationary blade segment engaged with the guide groove along the inner circumferential surface of the casing using the plurality of through holes is adopted.

  Further, in the present invention, a method is adopted in which the end face in the circumferential direction along the inner circumferential surface of the casing of the stationary blade dummy and the stationary blade segment includes a flat portion parallel to the axial direction.

  Further, in the present invention, a method is adopted in which a plurality of flat portions are provided at intervals in the axial direction.

In the present invention, the stator vane segment is removed from the insertion / removal opening opened in the outer peripheral surface of the casing, and the stator vane dummy is inserted into the space from which the stator vane segment is removed. The vane dummy includes hooks engageable with guide grooves for guiding the vane segments along the inner circumferential surface of the casing, and can be replaced with the vane segments. After replacing the vane segment with a vane dummy, move the vane dummy and vane segment engaged with the guide groove along the inner circumferential surface of the casing, and move the next vane segment to a position facing the insertion and removal port And replace the next stator vane segment with a stator vane dummy. In this way, the rotary shaft can be easily pulled out of the casing by replacing all of the stator vane segments with flat vane-shaped stator dummy that does not interfere with the blades in the axial direction.
Therefore, according to the present invention, the time taken for the disassembling operation can be shortened.

BRIEF DESCRIPTION OF THE DRAWINGS It is sectional drawing which shows schematic structure of the jet engine in 1st Embodiment of this invention. It is a partial disassembled perspective view of a casing in a 1st embodiment of the present invention. It is a longitudinal cross-sectional view orthogonal to the axial direction of the casing in 1st Embodiment of this invention. It is arrow AA sectional drawing of FIG. It is BB arrow sectional drawing of FIG. It is a perspective view of a stator vane dummy in a 1st embodiment of the present invention. FIG. 7 is a cross-sectional view taken along the line CC in FIG. It is a figure for demonstrating the decomposition | disassembly procedure using the stator vane dummy in 1st Embodiment of this invention. It is a figure for demonstrating the decomposition | disassembly procedure using the stator vane dummy in 1st Embodiment of this invention. It is the schematic which shows the positional relationship of a casing and a moving blade when all the stator blade segments in 1st Embodiment of this invention are replaced with a stator blade dummy. It is a top view of a stator blade dummy and a stator blade segment in a 2nd embodiment of the present invention. It is a top view of a stator blade dummy and a stator blade segment in one modification of an embodiment of the present invention. It is the (a) top view and the (b) arrow DD sectional view of the stationary blade dummy in one modification of the embodiment of the present invention.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings. In the following description, a jet engine is illustrated as an axial flow machine of the present invention.

First Embodiment
In the following description, the left side of FIG. 1 is referred to as the upstream side, and the right side of FIG. 1 is referred to as the downstream side, with reference to the air flow direction.
As shown in FIG. 1, the jet engine 1 includes a fan cowl 2, a core cowl 3, a fan unit 4, a low pressure compressor 5, a high pressure compressor 6, a combustor 7, a high pressure turbine 8, and a low pressure turbine 9, a shaft 10 (rotation axis), a main nozzle 11 and a center vent tube 12.

  The fan cowl 2 is a substantially cylindrical member in which the upstream end and the downstream end are opened, and accommodates the fan unit 4 and the like inside. The fan cowl 2 surrounds the upstream side of the core cowl 3 disposed concentrically with the fan cowl 2 and is supported by the core cowl 3 by a support (not shown). The fan cowl 2 takes in outside air from the upstream opening and guides the taken outside air toward the core cowl 3 downstream. The core cowl 3 is a substantially cylindrical member having a diameter smaller than that of the fan cowl 2 and having an upstream end and a downstream end opened. The core cowl 3 accommodates therein a low pressure compressor 5, a high pressure compressor 6, a combustor 7, a high pressure turbine 8, a low pressure turbine 9, a shaft 10 and the like. The fan cowl 2 and the core cowl 3 are attached to the airframe of the aircraft by a pylon not shown.

  Further, a flow passage (hereinafter referred to as a core flow passage) is formed inside the core cowl 3, and a flow passage of air supplied to the combustor 7 on the upstream side of the combustor 7 and a flow passage of the combustor 7. The downstream side is a flow path of the combustion gas generated by the combustor 7. Further, the space between the fan cowl 2 and the core cowl 3 is a bypass flow path for exhausting the remaining air not taken into the core flow path out of the air taken into the fan cowl 2 to the outside .

  The fan unit 4 has a plurality of fan blades 4a fixed to the shaft 10, and a fan vane 4b arranged in the bypass flow path. The fan rotor 4 a pumps air downstream as the shaft 10 rotates. Also, the fan vane 4b rectifies the air flowing through the bypass flow path. The shaft 10 is configured of a radially inner first shaft 10 a and a second shaft 10 b disposed radially outward so as to surround the first shaft 10 a. The fan bucket 4 a is fixed to the first shaft 10 a of the shaft 10.

  The low pressure compressor 5 is disposed on the upstream side of the high pressure compressor 6 and has a plurality of stator blades 5a and blades 5b alternately arranged along the flow direction of the core flow path. The stator vanes 5 a are fixed to the inner wall of the core cowl 3 and arranged in a plurality of rings around the shaft 10. The moving blades 5 b are fixed to the first shaft 10 a of the shaft 10 and are arranged in a plurality of rings around the shaft 10. The low pressure compressor 5 as described above compresses the air taken into the core flow path as the rotor blades 5b are rotationally driven by the first shaft 10a.

  The high pressure compressor 6 is disposed downstream of the low pressure compressor 5 and has substantially the same configuration as the low pressure compressor 5. That is, the high pressure compressor 6 has the stationary blades 6a and the moving blades 6b alternately arranged in a plurality along the flow direction of the core flow channel. The stationary blades 6 a are fixed to the inner wall of the core cowl 3 and are arranged in a plurality of rings around the shaft 10. The moving blades 6 b are fixed to the second shaft 10 b of the shaft 10 and arranged in a plurality of rings around the shaft 10. Such a high pressure compressor 6 further compresses the air compressed by the low pressure compressor 5 as the moving blades 6b are rotationally driven by the second shaft 10b.

  The combustor 7 is disposed downstream of the high pressure compressor 6, and burns a combustion gas by burning a mixture of compressed air fed from the high pressure compressor 6 and fuel supplied from an injector (not shown). Generate For example, in the combustor 7, the flow rate of fuel supplied from the injector is electronically controlled. As a result, the amount of generated combustion gas (that is, the thrust of the jet engine 1) is adjusted.

  The high pressure turbine 8 is disposed on the downstream side of the combustor 7, and includes a plurality of stator blades 8a and a plurality of rotor blades 8b alternately arranged along the flow direction of the core flow channel. The stator blades 8 a are fixed to the inner wall of the core cowl 3 and are arranged in a plurality of rings around the shaft 10. The moving blades 8 b are fixed to the second shaft 10 b of the shaft 10, and a plurality of the moving blades 8 b are arranged annularly around the shaft 10. Such a high pressure turbine 8 rotates the second shaft 10b by receiving the combustion gas with the moving blade 8b while rectifying the combustion gas with the stationary blade 8a.

  The low pressure turbine 9 is disposed downstream of the high pressure turbine 8 and has substantially the same configuration as the high pressure turbine 8. That is, the low pressure turbine 9 has the stationary blades 9a and the moving blades 9b alternately arranged in a plurality along the flow direction of the core flow path. The stator vanes 9 a are fixed to the inner wall of the core cowl 3 and are arranged in a plurality of rings around the shaft 10. The moving blades 9 b are fixed to the first shaft 10 a of the shaft 10 and are arranged in a plurality of rings around the shaft 10. Such a high pressure turbine 8 rotates the first shaft 10a by receiving the combustion gas with the moving blade 9b while rectifying the combustion gas with the stationary blade 9a.

  As described above, the shaft 10 is configured by the radially inner first shaft 10 a and the radially outer second shaft 10 b. The first shaft 10a has a length to reach the moving blade 9b of the low pressure turbine 9 from the moving blade 4a of the fan unit 4 and moves the moving blade 4a of the fan unit 4 and the low pressure compressor 5 closer to the upstream side. A blade 5 b is provided, and a moving blade 9 b of the low pressure turbine 9 is provided on the downstream side. The first shaft 10a has a tubular shape in which the upstream end and the downstream end are open, and the center vent tube 12 is accommodated inside. The first shaft 10a also has a narrowed portion 10a1. The narrowed portion 10a1 is a portion that reduces the inner opening area by bulging radially inward, and the tip of the center vent tube 12 is fixed. The first shaft 10 a is rotated by the moving blades 9 b of the low pressure turbine 9, and transmits the rotational power to the fan moving blades 4 a of the fan unit 4 and the moving blades 5 b of the low pressure compressor 5.

  The second shaft 10b has a length from the moving blade 6b of the high pressure compressor 6 to the moving blade 8b of the high pressure turbine 8, and the moving blade 6b of the high pressure compressor 6 is provided on the upstream side The moving blades 8 b of the high pressure turbine 8 are provided on the The second shaft 10b has a tubular shape surrounding the first shaft 10a from the outer side in the radial direction, and is provided concentrically with the first shaft 10a. The second shaft 10 b is rotated by the moving blade 8 b of the high pressure turbine 8, and transmits the rotational power to the moving blade 6 b of the high pressure compressor 6.

  The main nozzle 11 is an opening provided on the further downstream side of the low pressure turbine 9 and provided on the most downstream side of the jet engine 1. The main nozzle 11 injects the combustion gas that has passed through the low pressure turbine 9 toward the rear of the jet engine 1. A thrust is obtained by the reaction when the combustion gas is injected from the main nozzle 11.

  The center vent tube 12 is a straight pipe whose upstream end and downstream end are open, and is inserted into the inside of the first shaft 10a. The center vent tube 12 is fixed at its tip end by the narrow portion 10a1 of the first shaft 10a, and rotates with the rotation of the first shaft 10a. Such a center vent tube 12 exhausts the lubricating oil used in a bearing or the like (not shown) from the oil reservoir to the main nozzle 11 side with air.

  In the jet engine 1 having such a configuration, a portion of the air taken in by the rotational drive of the fan blades 4a of the fan unit 4 is two-stage compressed by the low pressure compressor 5 and the high pressure compressor 6, thereby generating Combustion of the compressed air and the fuel in the combustor 7 produces a combustion gas. By passing the combustion gas through the high pressure turbine 8 and the low pressure turbine 9, the shaft 10 is rotationally driven, and further, by being injected rearward from the main nozzle 11, a propulsive force is obtained. Further, the center vent tube 12 exhausts the air containing the lubricating oil to the main nozzle 11 side.

  The casing 20 shown in FIG. 2 forms, for example, an inner peripheral wall portion on the upstream side of the core cowl 3 shown in FIG. The casing 20 is formed in a tubular shape, and has on the inner circumferential surface 20a a stator vane 5a opposed in the axial direction to which the moving blade 5b provided on the outer circumferential surface of the shaft 10 extends.

  The casing 20 has an inner circumferential surface 20a and an outer circumferential surface 20b, and both sides in the axial direction are open. On at least one side opening in the axial direction of the casing 20, a flange portion 21 for axially connecting with another casing (not shown) via a bolt is provided. The inner circumferential surface 20a of the casing 20 is provided with at least one row of vanes 5a (shown in simplified form in FIG. 2). In the case where the stator blades 5a are provided in the casing 20 in a plurality of rows, the stator blades 5a are arranged at intervals in the axial direction.

  The vane 5 a is formed of a plurality of vane segments 30. The vane segment 30 includes a wing portion 31, a first shroud portion 32 (shroud portion), and a second shroud portion 33. A plurality of wing portions 31 are arranged between the first shroud portion 32 and the second shroud portion 33. The plurality of wing portions 31 are integrally fixed to the first shroud portion 32 and the second shroud portion 33. The first shroud portion 32 includes a hook portion 34 engageable with the guide groove 27 as shown in FIG. As shown in FIG. 2, the first shroud portion 31 is disposed radially outward, and the second shroud portion 33 is disposed radially inward.

  As shown in FIG. 2, the casing 20 is provided with an insertion / removal opening 22 which is open to the outer peripheral surface 20 b and into which the stator vane segment 30 can be inserted and removed. The insertion and removal opening 22 is formed slightly larger than the outer shape of the first shroud portion 32 of the vane segment 30 viewed from the radial outer side. The vane segments 30 are insertable into and removable from the casing 20 one by one through the insertion and removal opening 22. The pressure resistance of the casing 20 can be prevented from being lowered by setting the size of the insertion and removal opening 22 to a minimum size that allows one vane segment 30 to pass through.

  A frame 23 is provided around the insertion and removal opening 22. The frame portion 23 stands in the radial direction with respect to the outer peripheral surface 20 b of the casing 20. A plurality of screw holes are formed on the upper surface of the frame portion 23. The lid 25 is fixed to the frame 23 via the bolt 24. The lid 25 is formed in a plate shape that covers the insertion and removal opening 22. An insertion port 25 a through which the bolt 24 is inserted is formed at the edge of the lid 25. As shown in FIG. 4, the lid 25 engages with the inner wall of the frame 23 and contacts the first shroud 32 of the vane segment 30 from the outside in the radial direction. A gasket (not shown) may be provided between the lid 25 and the frame 23. In addition, the lid 25 may be fixed to the casing 20 by another method other than the bolt 24.

  In addition, as shown in FIGS. 4 and 5, the casing 20 is provided with a guide groove 27 for guiding the vane segment 30 inserted through the insertion and removal opening 22 along the inner circumferential surface 20 a. The guide groove 27 has a dovetailed cross section as shown in FIG. The guide groove 27 has a pair of guide portions 27a in which the tip end portions projecting in the axial direction are opposed with a gap. The pair of guide portions 27 a is annularly provided circumferentially along the inner circumferential surface 20 a of the casing 20 from the position where the insertion and removal opening 22 is provided.

  An opening 27b is formed between the pair of guides 27a. The width of the opening 27 b in the axial direction is smaller than the maximum width of the first shroud 32 of the vane segment 30 and larger than the maximum widths of the wing 31 of the vane segment 30 and the second shroud 33. For this reason, the first shroud portion 32 of the vane segment 30 engages with the pair of guide portions 27a, and the wing portion 31 and the second shroud portion 33 of the vane segment 30 move to the inside of the casing 20 from the opening 27b. Stand out. Thus, the vane segment 30 engages with the guide groove 27 in a state in which the falling of the casing 20 inward is restricted.

  On the other hand, the size in the radial direction of the space 28 (the space from the upper surface of the pair of guides 27 a to the bottom of the guide groove 27) of the guide groove 27 accommodating the hook portion 34 of the first shroud portion 32 is The thickness is equal to or slightly larger than the thickness of the hook portion 34 of the shroud portion 32. Therefore, the stator vane segment 30 is configured to be movable in the circumferential direction of the casing 20 in a state where the first shroud portion 32 is slidably held by the guide groove 27.

  According to the casing 20 of the above configuration, as shown in FIG. 2, the stator vane segment 30 is inserted and inserted from the insertion opening 22 which opens in the outer peripheral surface 20 b of the casing 20 in a state where the shaft 10 is inserted. The stator vane segment 30 is moved circumferentially along the inner circumferential surface 20a by the guide groove 27, and the insertion and movement of the stator vane segment 30 are repeated, thereby arranging the stator vanes 5a annularly along the inner circumferential surface 20a. It becomes possible. According to this configuration, the casing 20 is light in weight and high in strength, and the efficiency of the jet engine 1 can be improved.

By the way, the jet engine 1 needs to pull out the shaft 10 from the casing 20 assembled as described above and disassemble it in order to perform regular maintenance.
Next, the stator vane dummy 40 used to pull out the shaft 10 from the casing 20 configured as described above will be described with reference to FIGS. 6 and 7.

  As shown in FIG. 6, the vane dummy 40 has a shape obtained by removing the wing portion 31 and the second shroud portion 33 from the vane segment 30, that is, a shape corresponding to the first shroud portion 32. Specifically, the stationary blade dummy 40 is formed in a flat plate shape, and includes a hook portion 41 engageable with the guide groove 27.

  The outer shape of the stationary blade dummy 40 viewed from the outer side in the radial direction is equal to the outer shape of the first shroud portion 32 viewed from the outer side in the radial direction. For this reason, the stator vane dummy 40 is insertable into and removable from the casing 20 one by one via the insertion and removal opening 22. The shape of the hook portion 41 of the stator vane dummy 40 shown in FIG. 7 is the same as the shape of the hook portion 34 of the first shroud portion 32 shown in FIGS. 4 and 5. As described above, the thickness of the hook portion 41 of the stationary blade dummy 40 may be smaller than the thickness of the hook portion 34 of the first shroud portion 32 because it is not necessary to fix the casing 20 without rattling.

In addition, the stator vane dummy 40 includes a plurality of through holes 42 arranged at intervals in the circumferential direction along the inner circumferential surface 20a of the casing 20 when engaged with the guide groove 27 (see FIG. 6). The through hole 42 is formed in a circular shape when viewed from the outer side in the radial direction.
The vane dummy 40 having the above configuration has a shape corresponding to the first shroud portion 32. The first shroud portion 32 does not face the bucket 5b in the axial direction, and the vane dummy 40 is also shown in FIG. As described above, when the guide groove 27 is engaged, the moving blade 5b is not opposed in the axial direction. The stationary blade dummy 40 can be formed of a material cheaper than the stationary blade segment 30 (for example, an inexpensive metal such as an iron material, a resin material having good slidability such as polytetrafluoroethylene, or the like).

  Subsequently, the present method (a method of disassembling an axial flow machine) for drawing out the shaft 10 from the casing 20 using the stationary blade dummy 40 having the above-described configuration will be described with reference to FIGS.

In the present method, as shown in FIGS. 8A and 8B, the vane segment 30 and the vane dummy 40 are interchanged via the insertion and removal opening 22 of the casing 20 (replacement step).
Specifically, in the replacement step, first, the bolt 24 is removed and the lid 25 is opened to expose the insertion and removal opening 22 of the casing 20. Next, as shown in FIG. 8 (a), the vane segment 30 located at a position facing the insertion and removal opening 22 is removed. And as shown in FIG.8 (b), the stator blade dummy 40 is inserted in the space which removed the stator blade segment 30. As shown in FIG. The vane dummy 40 includes hooks 41 (see FIG. 7) engageable with the guide grooves 27 for guiding the vane segments 30 along the inner circumferential surface 20 a of the casing 20, and replaces the vane segments 30. be able to.

After the replacement step, in the present method, as shown in FIG. 9A, the vane dummy 40 and the vane segment 30 engaged with the guide groove 27 are moved along the inner circumferential surface 20 a of the casing 20 , Move the next stator vane segment 30 to a position facing the insertion and removal opening 22 (moving step).
Specifically, in the moving step, the stator vane dummy 40 and the stator vane segment 30 engaged with the guide groove 27 using the plurality of through holes 42 (see FIG. 6) provided in the stator vane dummy 40 are casing 20 And move along the inner circumferential surface 20a of the That is, the plurality of through holes 42 are arranged at intervals in the circumferential direction along the inner circumferential surface 20 a of the casing 20, and hold the stationary vane dummy 40 through the through holes 42 or a jig at the through holes 42. The stator vane dummy 40 can be easily pushed in the circumferential direction by inserting an insert or the like.

  When the stator vane dummy 40 is pushed in the circumferential direction, as shown in FIG. 9A, the next stator vane segment 30 is pushed out from the opposite side to a position facing the insertion and removal opening 22. As a result, as shown in FIG. 9 (b), it is possible to remove the next vane segment 30 located opposite to the insertion and removal opening 22. Thereafter, as in FIG. 8 (b), the stator vane dummy 40 is inserted into the space from which the next stator vane segment 30 is removed, and, similarly to FIG. 9 (a), the stator vane dummy 40 and the stator vane segment 30. Are moved along the inner circumferential surface 20 a of the casing 20. As described above, in the present method, all of the vane segments 30 are replaced with the vane dummy 40 by alternately repeating the above-described replacement step and the moving step.

  As shown in FIG. 10, when all of the stator vane segments 30 are replaced with the stator vane dummy 40, the stator vane dummy 40 has a shape corresponding to the first shroud portion 32 and does not axially oppose the rotor blade 5b. Because of the flat shape, the casing 20 does not axially interfere with the moving blade 5b. In this manner, the shaft 10 can be easily pulled out of the casing 20 by replacing all of the vane segments 30 with the flat plate-like vane dummy 40 which does not interfere with the moving blade 5 b in the axial direction.

  As described above, according to the present embodiment described above, the shaft 10 having the moving blade 5 b on the outer peripheral surface and the stationary blade 5 a facing the moving blade 5 b in the axial direction surrounding the shaft 10 and extending the shaft 10 20. A method of disassembling an axial flow machine comprising: a cylindrical casing 20 having a cylindrical shape 20a, wherein the stationary blade 5a is formed of a plurality of stationary blade segments 30, the casing 20 is opened to the outer peripheral surface 20b, An insertion slot 22 through which the segment 30 can be inserted and removed, and a guide groove 27 for guiding the stator vane segment 30 inserted through the insertion slot 22 along the inner circumferential surface 20 a, through the insertion slot 22 Replacement step of replacing the stationary vane segment 30 and the flat-plate-like stationary vane dummy 40 having the hook portion 41 engageable with the guide groove 27 and not axially facing the rotor blade 5b; Engage with the guide groove 27 A moving process of moving the stationary vane dummy 40 and the stationary vane segment 30 along the inner circumferential surface 20a of the casing 20 and moving the next stationary vane segment 30 to a position facing the insertion / removal opening 22 is alternately repeated. The shaft 10 can be easily pulled out of the casing 20 by adopting a method of axially removing one of the shaft 10 and the casing 20 after replacing all of the wing segments 30 with the vane dummy 40. The time required for disassembly can be shortened.

Second Embodiment
Next, a second embodiment of the present invention will be described. In the following description, the same or equivalent components as or to those of the embodiment described above are designated by the same reference numerals, any explanation of which will be simplified or omitted.

  As shown in FIG. 11, in the second embodiment, the above-described embodiment is that the end surface 40 a in the circumferential direction along the inner peripheral surface 20 a of the casing 20 of the stator vane dummy 40 A includes a flat portion 40 a 1 parallel to the axial direction. It is different from Further, the second embodiment differs from the above embodiment in that the end face 30a in the circumferential direction along the inner circumferential surface 20a of the casing 20 of the stator blade segment 30A includes a flat portion 30a1 parallel to the axial direction.

  Since the stator vane segment 30A has the wing portion 31 inclined with respect to the axial direction, it is preferable that the end face 30a (division surface) be obliquely aligned with the axial direction, but if the end face 30a is oblique, the stator vane When the dummy 40A is pushed in the circumferential direction, the force pushing the stationary vane segment 30A in the circumferential direction is decomposed (reduced) by the inclination, so an extra force is required. Therefore, in the second embodiment, while the end face 40a of the stator vane dummy 40A is inclined as a whole, the flat portion 40a1 is included, and the end face 30a of the stator vane segment 30A is also inclined as a whole. I have included it.

Specifically, the end face 40a of the stationary vane dummy 40A is formed such that a first inclined portion 40a2, a flat portion 40a1, and a second inclined portion 40a3 are axially connected. Further, an end face 30a of the stator vane segment 30A is formed such that a first inclined portion 30a2, a flat portion 30a1, and a second inclined portion 30a3 are connected in the axial direction.
According to the second embodiment of the above configuration, when the stator vane dummy 40 is pushed in the circumferential direction, the force for pushing the stator vane segment 30A in the circumferential direction is directly transmitted from the flat portion 40a1 to the flat portion 30a1. It is possible to push the stator vane segment 30A in the circumferential direction without applying any force.

  As mentioned above, although the suitable embodiment of the present invention was described referring to drawings, the present invention is not limited to the above-mentioned embodiment. The shapes, combinations, and the like of the constituent members shown in the above-described embodiment are merely examples, and various changes can be made based on design requirements and the like without departing from the spirit of the present invention.

  For example, the present invention can adopt a method as shown in FIG. 12 and FIG. 13 as a modification.

  A stationary vane dummy 40B illustrated in FIG. 12 includes a plurality of flat portions 40b1 parallel to the axial direction at intervals in the axial direction. Two flat portions 40b1 are provided on the end face 40b on the side where the stationary vane segment 30B is pushed out. According to this configuration, since the stator vane segment 30B can be pushed out with a plurality of contact points, for example, the stator vane segment 30B can be more stably pushed in the circumferential direction than pushing the stator vane segment 30B at one central point. It becomes possible. The gap between the two flat portions 40b1 is preferably made as small as possible, as shown in FIG. 12, in order to minimize the leakage of compressed air.

  The vane dummy 40 </ b> C shown in FIG. 13 has a lubricant guiding groove 43 extending in the circumferential direction in the hook portion 41. The lubricant guide groove 43 is formed in a straight line on the top surface of the hook portion 41. According to this configuration, the lubricant can be easily supplied to the guide groove 27 of the casing 20 through the lubricant guide groove 43 of the vane dummy 40C. This makes it possible to improve the slip between the stator vane segment 30C and the guide groove 27 and to push the stator vane segment 30C in the circumferential direction without applying an extra force.

  Also, for example, in the present method, when extruding the stator vane segment in the circumferential direction, the casing is heated and thermally expanded in advance to form a gap between the stator vane segment and the guide groove, which facilitates the stator vane segment A method of pushing in the circumferential direction may be adopted.

  Also, for example, the present method is applied to axial flow machines such as axial flow compressors and axial flow turbines. Further, axial flow machines are applied to gas turbine engines such as turbofan engines, turbojet engines, turboprop engines, turboshaft engines, and turbo ramjet engines. Also, the application of gas turbine engines is not limited to aircraft. For example, it can be applied to gas turbine engines for ships and for power generation.

1 jet engine (axial flow machine)
5a stator vane 5b rotor blade 10 shaft (rotation axis)
Reference Signs List 20 casing 20a inner circumferential surface 20b outer circumferential surface 22 insertion / removal opening 27 guide groove 30 stator vane segment 31 wing portion 32 first shroud portion (shroud portion)
34 hook portion 40 stationary blade dummy 41 hook portion 42 through hole

Claims (5)

An axial flow machine comprising: a rotating shaft having a moving blade on an outer peripheral surface; and a cylindrical casing having an inner peripheral surface having a stationary blade opposed to the moving blade in an axial direction surrounding the rotating shaft and extending the rotating shaft. Method of decomposition of
The vanes are formed from a plurality of vane segments.
The casing is open at an outer peripheral surface, and an insertion opening through which the stator vane segment can be inserted and removed, and a guide groove for guiding the stator vane segment inserted through the insertion opening along the inner peripheral surface Have
A replacing step of replacing the stationary vane segment and the flat plate dummy having a hook portion engageable with the guide groove via the insertion and removal opening and not axially facing the moving vane;
After the replacement step, the stator vane dummy and the stator vane segment engaged with the guide groove are moved along the inner peripheral surface of the casing, and the next stator vane segment is opposed to the insertion and removal port. Moving process to move to
The method for disassembling an axial flow machine, comprising alternately repeating all of the stator blade segments with the stator blade dummy, and then axially removing one of the rotating shaft and the casing from the other. The vane segment includes a shroud portion provided with a hook portion engageable with the guide groove, and a wing portion supported by the shroud portion.
The method of disassembling an axial flow machine according to claim 1, wherein the stator vane dummy has a shape corresponding to the shroud portion. The stator vane dummy includes a plurality of through holes arranged at intervals in the circumferential direction along the inner circumferential surface of the casing when engaged with the guide groove,
In the moving step, the vane dummy and the vane segment engaged with the guide groove are moved along the inner circumferential surface of the casing by using the plurality of through holes. The method of disassembling an axial flow machine according to 1 or 2.   The end face in the circumferential direction in alignment with the inner skin of the casing of the above-mentioned stator blade dummy and the above-mentioned stator blade segment includes a flat part parallel to the above-mentioned axial direction. The method of disassembling an axial flow machine according to claim 1.   The method for disassembling an axial flow machine according to claim 4, wherein the flat portion is provided in a plurality at intervals in the axial direction.

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