JP4127120B2 - Micro gas turbine power generator and transition piece used therefor - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a gas turbine for power generation and a transition piece used therefor, and more particularly, to a small-capacity micro gas turbine power generator and a transition piece used therefor.
[0002]
[Prior art]
An example of a conventional gas turbine is described in Patent Document 1. In the gas turbine described in this pamphlet, the suction pipe of the turbine is divided into two at the maximum diameter position in the rotation axis direction. And the two scroll-shaped members formed are integrated by welding the contact part formed along the outer periphery of a division surface, and extending radially outward. Further, the integrated suction pipe is also held in a housing divided into two at the maximum diameter position in the rotation axis direction.
[Patent Document 1]
International publication WO02 / 29211 pamphlet
[0003]
[Problems to be solved by the invention]
In the above conventional gas turbine, bending flaps (folded pieces) having a Z-shaped radial cross section are provided at a plurality of locations on the inner peripheral side of the suction pipe (transition piece) divided into two, and the folded pieces are formed on the turbine nozzle side. Combine with a conical plate. Then, the flap is bent to fix the conical plate and the flap. A fluid force acts on the suction pipe of the gas turbine from the fluid flowing in the combustor, the regenerator, and the compressor. In addition, high-temperature and high-pressure combustion gas flows through the flow path formed inside the suction pipe and the turbine nozzle, while the outside of the suction pipe and the turbine nozzle has a pressure atmosphere of about atmospheric pressure. A large pressure difference occurs between the inner surface and the outer surface.
[0004]
Therefore, a great force acts during operation in the gas turbine described in this pamphlet. In particular, when the combustion temperature of the gas turbine is increased, the load on the coupling portion between the suction pipe and the turbine nozzle also increases, and it becomes difficult to ensure the strength of the coupling portion. In this case, the stress of the joint portion increases, and the life of the joint portion may decrease, or the sealing performance between the suction pipe, the inner flow path of the turbine nozzle, and the outer atmosphere may be impaired. If welding or bolt fastening used in a general structure is applied to this transition piece in order to eliminate this problem, disassembly and assembly are impaired, and it becomes difficult to realize a simple and small gas turbine.
[0005]
The present invention has been made in view of the above problems of the prior art, and an object thereof is to improve the disassembly and assembly of the micro gas turbine power generator. Another object of the present invention is to realize a micro gas turbine power generator having an inexpensive and simple configuration. Still another object of the present invention is to improve the reliability of a micro gas turbine power generator.
[0006]
[Means for Solving the Problems]
In order to achieve the above object, a feature of the present invention is that in a micro gas turbine power generator in which a rotor having a turbine impeller and a compressor impeller is connected to a generator rotor, a flow path for introducing combustion gas to the turbine impeller is formed. A transition piece, a turbine casing that forms a flow path outside the transition piece, a compressor casing that forms a flow path that guides discharge air from the compressor impeller, and a partition positioned between the turbine casing and the compressor casing And a transition piece is detachably attached to the partitioning means, and a flow path formed inside and outside the transition piece is sealed.
[0007]
In this feature, the compressor impeller is preferably a centrifugal type, and is provided with a flow sleeve that divides the turbine casing and the transition casing in a radial direction, and the flow sleeve has a flow velocity of a flow path formed outside the transition piece. It may be a thing which raises. Furthermore, it is desirable that the flow sleeve is composed of a plurality of members and can be disassembled in the axial direction.
[0008]
In the above feature, when a gourd-shaped hole is provided at a plurality of locations on the inner peripheral side of the transition piece, and the transition piece is attached to or detached from the partitioning means, the transition piece is moved from the large-diameter side of the gourd-shaped hole to the small-diameter side or its side. It is preferable to rotate in the reverse direction. Moreover, it is preferable to attach a different diameter screw to the partitioning means, and to attach this different diameter screw to the gourd type hole to prevent thermal deformation.
[0009]
Another feature of the present invention that achieves the above object is to drive the compressor impeller disposed coaxially with the turbine impeller by guiding the combustion gas burned in the combustor to the turbine impeller, and to generate the compressed air generated in the combustor. In a micro gas turbine power generator that supplies power by a generator connected to a rotating shaft of a turbine impeller, a combustion gas flow path that supplies the turbine impeller is formed inside, and compressed gas is supplied to the combustor. A transition piece having a flow channel to be supplied formed outside is detachably attached to a stationary member of the micro gas turbine, and the flow channel formed inside and outside the transition piece by sealing is sealed.
[0010]
Still another feature of the present invention that achieves the above object is that a transition piece is used in a micro gas turbine power generator having a turbine, a compressor, and a combustor, and a suction port that sucks combustion gas from the combustor, and a turbine impeller. A tubular portion for supplying combustion gas to the entire circumferential direction of the turbine impeller, and a discharge port portion for introducing the combustion gas to a nozzle arranged upstream of the turbine impeller, with a plurality of intervals in the circumferential direction of the discharge port portion. In this case, a pear-shaped hole is formed.
[0011]
In this feature, the suction port may have a detachable cylindrical socket, or may be fixed to a stationary member of the gas turbine by rotating the transition piece around the rotation axis of the gas turbine rotor. .
[0012]
DETAILED DESCRIPTION OF THE INVENTION
Hereinafter, an embodiment of a micro gas turbine power generator according to the present invention and a transition piece used therefor will be described with reference to the drawings. In FIG. 8, the longitudinal cross-sectional view of the micro gas turbine power generator 11 is shown. The micro gas turbine power generator 11 includes a rotor part 41 having a compressor impeller 4 and a turbine impeller 2, a combustor part, and a generator part 43. The rotor 1 constituting the rotor portion 41 includes a rotor shaft 6 that is integrated with the turbine impeller 2 and concentric with the turbine impeller 2, and a compressor impeller 4 that is attached to the rotor shaft 6. The generator unit 43 includes a generator 7 that is assembled coaxially with the turbine impeller 2.
[0013]
A tie bolt is joined to the axial center of the turbine impeller 2. A through hole is formed at the rotation center of the compressor impeller 4, the rotor shaft 6, and the generator 7. The compressor impeller 4, the rotor shaft 6, the generator 7, and the rotor end member 8 are sequentially stacked through tie bolts through the through holes. A bolt portion 3c formed at the end opposite to the turbine impeller of the tie bolt is tightened with a nut. The turbine impeller 2 has a radial flow, and includes a blade portion 2a, a turbine end grip portion 2b, and a joint boss portion 2c.
[0014]
The turbine end grip portion 2b has a nut shape or a parallel grip portion shape. Used to fix the turbine impeller 2 when the tie bolt 3 is joined to the turbine impeller 2 by friction welding, electron beam welding or diffusion joining, and when a pretension is applied to the tie bolt 3 and the bolt portion 3c is fastened with the nut 10. . The joining boss part 2 c is provided on the back surface of the blade part 2 a of the turbine impeller 2 and is used to join the turbine impeller 2 and the tie bolt 3. A joint boss 2c is provided to separate the joint from a portion having a large change in cross-sectional area to prevent stress concentration at the joint. Since the turbine impeller 2 is exposed to high-temperature combustion gas, a nickel-base superalloy is manufactured by precision casting, forging, or machining.
[0015]
The compressor impeller 4 is centrifugal and made of titanium alloy or aluminum alloy, and is manufactured by precision casting, forging or machining. A bearing collar 5 is fitted to the rotor shaft 6. The bearing collar 5 supports a radial load and a thrust load with a lubricating fluid between a radial bearing 23a and thrust bearings 23b and 23c, which will be described later. A bearing collar 9 is fitted to the rotor end member 8, and a radial load is supported by a lubricating fluid with a radial bearing 23d described later.
[0016]
On the outer peripheral side of the turbine impeller 2, nozzles 14 are arranged at substantially equal pitches at a plurality of locations in the circumferential direction in order to blow combustion gas into the impeller 2 into the turbine. A transition piece 13 that forms a spiral flow path for supplying combustion gas to the nozzle 14 is disposed on the outer peripheral side of the nozzle 14. The nozzle 14 is fixed to the transition piece 13 with a pin. The transition piece 13 is held in a turbine outer casing 12 having turbine outer casing members 12a and 12b. The turbine outer casing 12 and the transition piece 13 are integrated by welding or integral precision casting, or manufactured as separate parts.
[0017]
A flange is formed on the rear side of the turbine outer casing 12. The flange portion and the compressor casing 17 in which the flange portion is also formed are airtightly fastened with bolts 15a and nuts 15b via a spacer 15. The spacer 15 forms a flow path to the turbine impeller 2 and the compressor impeller 3. If a labyrinth seal, a honeycomb seal or a brush seal is provided on the spacer 15 in order to prevent the working fluid from leaking from each of these flow paths, the performance of the turbine or the compressor can be improved. A pressure recovery vane may be provided at the compressed air outlet of the compressor casing 17. A turbine support 24 that supports the rotor portion 41 and fixes it to the foundation is provided at two locations on the outer peripheral side of the turbine outer casing 12.
[0018]
The generator 7 has a rotor and a stator. The rotor is a generator core 7c that is a laminated portion on the rotor shaft 6, a permanent magnet 7b disposed on the outer peripheral side of the generator core 7c, and an outer periphery of the permanent magnet 7b. , A generator rear end ring 7d and a rotor end member 8 that hold both side portions of the generator core 7c. The generator core 7c has a cylindrical shape and is made of a magnetic material.
[0019]
The permanent magnet 7b has a cylindrical shape or a divided cylindrical shape. The cover 7a prevents the permanent magnet 7a from being scattered by rotation or slipping from the generator core 7c. The cover 7a is tightly fitted to the permanent magnet 7c, and the permanent magnet 7b is pressed against the generator core 7c with a compressive stress in the radial direction. For the cover 7a, a high-strength nonmagnetic metal ring such as a nickel-base alloy or FRP is used.
[0020]
The stator of the generator 7 includes a generator coil 19a that faces the cover 7a and is spaced from the cover 7a, and a generator coil outer casing 19b that holds the generator coil 19a on the outer peripheral side of the generator coil 19a. A cylindrical generator casing positioned further on the outer peripheral side of the generator coil outer casing 19b, and a generator front casing 20 and a generator rear casing 18 that hold both front and rear sides of the generator coil outer casing 19b. is doing. A radial bearing 23d is held on the inner peripheral side of the front casing 20 of the generator. A thrust bearing 23c is held on the inner peripheral side of the rear casing 18 of the generator. As a bearing, an air bearing, a water bearing, a sliding bearing such as an oil bearing, a rolling bearing, or a magnetic bearing is used.
[0021]
A generator front end casing 21 is provided on the end side of the generator 11 further than the generator front casing 20. Further, a generator rear end casing 17b is provided on the combustor portion side of the generator rear casing 18. A radial bearing 23a and a thrust bearing 23b are held at positions corresponding to the bearing collar 5 on the inner peripheral side of the generator rear end casing 17b.
[0022]
Bolt holes 22b are formed at a plurality of circumferential positions on the outer peripheral side of the generator front end casing 21, the generator front casing 20, the generator casing 19, the generator rear casing 18, and the generator rear end casing 17b. Yes. The casings 21, 20, 19, 18, and 17b are sequentially stacked, the through bolt 22a is passed through the bolt hole 22b, and the end of the through bolt 22a is tightened with a nut 22c. Thereby, the generator unit 43 is assembled. The generator rear end casing 17b is connected to the compressor casing 17 via a strut 17a. The strut 17a is a support and clearance adjustment member between the generator rear end casing 17b and the compressor casing 17 provided at intervals in the circumferential direction.
[0023]
In the micro gas turbine power generation facility 11 configured as described above, the combustion gas flowing out from a combustor (not shown) flows in the radial direction in the flow path in the transition piece 13 as indicated by an arrow A and is rectified by the nozzle 14. . Then, it expands when passing through the turbine impeller 2. The combustion gas flowing along the turbine blade 2a flows out from the turbine impeller 2 in a substantially horizontal direction as shown by an arrow B (see FIG. 2). The combustion gas flowing out in the horizontal direction is guided to a regenerative heat exchanger (not shown). A rotor 1 having a turbine impeller 2 to which rotational power is applied by combustion gas rotates a compressor impeller 4 attached to the rotor 1 in the direction of arrow E in FIG.
[0024]
When the compressor impeller 4 rotates, air is sucked in from the suction port of the compressor casing 17 inward in the radial direction in the direction indicated by the arrow C. Then, it is compressed by the compressor impeller 4 and flows into the scroll portion of the compressor casing 17 outward in the radial direction as indicated by an arrow D. The compressed air is preheated by a regenerative heat exchanger (not shown), and then mixed with fuel in the combustor to burn the fuel. Combustion gas generated by combustion in the combustor is supplied to the turbine impeller 2. The supplied combustion gas expands at the blade portion 2 a and rotates the turbine impeller 2. When the turbine impeller 2 rotates, the rotor of the generator 7 connected to the rotor 1 having the impeller 2 rotates in the stator to generate electric power. The alternating current induced in the generator coil 19a is converted into a direct current by a rectifier (not shown), which is also converted into an alternating current by an inverter (not shown).
[0025]
Details of the transition piece portion of the micro gas turbine power generation equipment 11 configured as described above will be described with reference to FIGS. 1 to 4. 1 and 2 are perspective views of the transition piece 13, FIG. 1 is a view as seen from the upstream side of the turbine impeller 2, and FIG. 2 is a view as seen from the downstream side of the turbine impeller 2. The transition piece 13 guides the combustion gas of the combustor to the turbine nozzle 14. The transition piece 13 includes a suction portion 13a that guides combustion gas from a cylindrically formed combustor, a tubular portion 13b that surrounds the turbine nozzle 14 to form a flow path, and a discharge port portion that guides the combustion gas to the turbine nozzle 14 It is a tubular member having 13c. A spiral chamber may be formed instead of the tubular portion 13b. The transition piece 13 is manufactured by welding or casting a sheet metal transition material manufactured by press molding or squeezing.
[0026]
A fixing flange 13d is formed in the vicinity of the discharge port portion 13c. The fixed flange 13d is provided with gourd-type (pear-shaped) holes 13e connecting two holes having different sizes of a large-diameter hole 13f and a small-diameter hole 13g at intervals in a plurality of locations in the circumferential direction. ing. The transition piece 13 is fixed by fitting the small diameter portion 30b of the screw 30 having the different diameter portion attached to the spacer 15 into the gourd-shaped hole 13e.
[0027]
This detail is shown in FIG. 3 and FIG. FIG. 3 is a longitudinal sectional view of the lower half of the rotor portion, and FIG. 4 is a view taken along the line AA. Compressor casings 17 and 17c are disposed on the back side of the compressor impeller 4, and spacers 15 are disposed adjacent to the compressor casings 17 and 17c. Holes are formed in the spacer 15 at a substantially equal pitch in the circumferential direction, and stepped screws 30 are inserted into the holes and fixed with nuts 30d. The stepped screw 30 has an end 30a opposite to the fixed end in the shape of a hexagonal bolt, and a small diameter portion 30b is formed adjacent to the hexagonal bolt-shaped portion 30a.
[0028]
When the transition piece 13 is attached to the spacer 15, the stepped screw 30 attached to the spacer 15 is first fitted into the large-diameter hole 13f of the gourd-shaped hole 13e. Then, after the axial position of the transition piece 13 is determined so that the small-diameter portion 30b of the stepped screw 30 is fitted into the small-diameter hole 13g, the direction of the transition piece is opposite to the arrow F in FIG. Rotate to As a result, the fixing flange 13 d of the transition piece 13 is sandwiched and fixed between the back surface of the hexagonal bolt-shaped portion 30 a of the stepped screw 30 and the spacer 15.
[0029]
That is, the transition piece 13 is fixed with the hexagonal bolt-shaped portion 30a of the stepped screw 30 and the spacer 15 via the fixing flange 13d in the axial direction of the rotor 1. The surface direction perpendicular to the rotation axis of the rotor 1 is fixed to the spacer 15 by the small diameter portion 30b of the stepped screw 30 via the fixing flange 13d. In this embodiment, the stepped screw 30 is formed of a hexagonal bolt, so that the stepped screw can be easily replaced.
[0030]
When removing the transition piece 13 from the spacer 15, the above-described method is performed in reverse. That is, the transition piece 13 is rotated in the direction of the arrow F. The hexagonal bolt-shaped portion 30a of the stepped bolt 30 is positioned on the large-diameter hole 13f side of the gourd-shaped hole 13e provided in the fixing flange 13d, and then the transition piece 13 is moved to the front side in FIG. Thereby, the transition piece 13 is removed from the spacer 15. During operation, it is necessary to fix the transition piece 13 in the direction of arrow F. For fixing the transition piece 13, the weight of the transition piece 13, the frictional force of the contact portion between the fixing flange 14 and the stepped bolt 30, and the transition piece The force or frictional force from the combustor when the combustor is inserted into the 13 suction ports 13a is used.
[0031]
In the above embodiment, when fixing the transition piece 13 to the spacer 15, the stepped bolt 30 is put into the gourd-shaped hole 13e, and then the transition piece is rotated by a slight angle in the circumferential direction. It is also possible to provide a fitting part that fits when both of the spacers 15 are relatively displaced in the circumferential direction, and rotate and fix the fitting part. Examples of such a fitting part include a fitting part composed of a male member and a female member, a fitting part composed of a convex member and a concave member, a member like a clip, a hook-shaped member, and a screw.
[0032]
A flow path for supplying combustion gas to the turbine impeller 2 is formed inside the transition piece 13, and a flow path for compressed air supplied to the combustor is formed outside the transition piece 13. In order to completely separate these two flow paths, the inner peripheral side of the transition piece 13 is sealed. This is shown in FIG. FIG. 5 is a partial perspective view of the rotor portion from the turbine impeller 2 to the transition piece 3.
[0033]
The discharge port 13c portion of the transition piece 13 has a rear discharge flange 13k located on the boss portion 2c side of the turbine impeller 2 and a front discharge flange 13j located on the opposite boss portion side. The front discharge flange 13j and the rear discharge flange 13k form an annular space. The front discharge flange 13j and the rear discharge flange 13k are welded to the 13 tubular portions 13b of the transition piece forming a flow path surrounding the turbine nozzle 14.
[0034]
Further, the front discharge flange 13j and the rear discharge flange 13k are finished with high planar accuracy by machining. When the transition piece 13 is rotated in the direction opposite to the arrow F and fixed to the spacer 15, the front flange 14 a of the nozzle 14 is connected to the front discharge flange 13 j of the transition piece 13, and the nozzle 14 is connected to the rear discharge flange 13 k of the transition piece 13. The rear flange 14b is brought into contact. Alternatively, the flanges 13j, 14a, 13k, and 14b are attached with a narrow gap. Thereby, the flow path formed inside and outside the transition piece 13 and the turbine nozzle 14 can be sealed. In order to improve the sealing performance, metal gaskets or asbestos seals are provided on the front discharge flange 13j, the rear discharge flange 13k, and the front flange 14a and the rear flange 14b of the nozzle 14 facing each other.
[0035]
In the above embodiment, the cooling holes 13h and 13i are formed in the front discharge flange 13j and the rear discharge flange 13k of the transition piece 13 to prevent the discharge flanges 13j and 13k from being overheated. And the heat conduction amount between the discharge flanges 13j and 13k and the flange 14 is reduced, and the temperature rise of the flange 14 is prevented. Furthermore, since the thermal deformation of the discharge flanges 13j and 13k is prevented, the sealing performance between the flow paths formed inside and outside the transition piece 13 is improved.
[0036]
FIG. 6 shows a modification of the above embodiment. This modification is different from the above-described embodiment in that the suction portion 13a of the transition piece 13 is composed of a plurality of members. A cylindrical socket 13m is detachably disposed on the end side of the suction portion 13a which is a connection portion to the combustor. If this cylindrical socket 13m is removed, the length of the transition piece 13 can be shortened. When the suction portion 13a is shortened, the mounting rotation angle G (see FIG. 4) of the transition piece 13 can be increased, and the transition piece 13 can be more firmly fixed to the spacer 15.
[0037]
Another embodiment of the present invention is shown in FIG. This embodiment is different from the above embodiment in that a flow sleeve 31 is provided between the transition piece 13 and the turbine outer casing 12. The turbine outer casing 12 has a left casing 12a and a right casing 12b in which flange portions are formed, and is configured by connecting the flange portions. The flow sleeve 31 includes a left flow three portion 31 a extending from the compressor impeller 4 side and a right flow sleeve 31 b extending to the discharge side of the turbine impeller 2.
[0038]
In the present embodiment, the air guided from the regenerative heat exchanger or the air discharged from the compressor impeller 4 flows through the flow path sandwiched between the transition piece 13 and the flow sleeve 31. The combustion gas generated by introducing the compressed air to the combustor is guided to a flow path formed inside the transition piece 13 and supplied from the turbine nozzle 14 to the turbine impeller 4.
[0039]
Since the flow sleeve 31 is provided outside the transition piece 13, the flow velocity of the air flowing outside the transition piece 13 can be increased, and the cooling performance of the transition piece 13 can be improved. Therefore, the transition piece 13 can be prevented from being overheated, and the reliability of the transition piece 13 is increased and the life is extended.
[0040]
In this embodiment, the flow sleeve 31 is divided in the axial direction. Thereby, the assembly property of the transition piece 13 improves. Since the casing 12 is also divided in the axial direction, the assembly of the flow sleeve 31 and the transition piece 13 is further improved.
[0041]
According to each of the above embodiments, the transition piece 13 can be firmly held by the spacer 15 during operation of the micro gas turbine power generator, and can be easily disassembled during assembly inspection. Moreover, the sealing performance between the flow paths formed inside and outside the transition piece can be improved.
[0042]
【The invention's effect】
According to the present invention, since the transition piece can be easily attached to and detached from the stationary portion, the disassembly and assembly of the micro gas turbine power generator can be improved. In addition, the micro gas turbine power generator can be configured in a small and simple manner. Furthermore, since the sealing performance has been improved, the reliability of the micro gas turbine power generator can be improved.
[Brief description of the drawings]
FIG. 1 is a perspective view of an embodiment of a transition piece of a gas turbine according to the present invention.
2 is another perspective view of the transition piece shown in FIG. 1. FIG.
3 is a partial longitudinal sectional view of the transition piece shown in FIG. 1. FIG.
4 is a cross-sectional view taken along line AA of the transition piece shown in FIG. 3. FIG.
FIG. 5 is a partial perspective sectional view of the transition piece shown in FIG. 1;
6 is a cross-sectional view of the transition piece shown in FIG.
7 is a partial perspective sectional view of the transition piece shown in FIG. 1. FIG.
FIG. 8 is a longitudinal sectional view (upper half) and a front view (lower half) of an embodiment of a micro gas turbine according to the present invention.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 ... Rotor, 2 ... Turbine impeller, 3 ... Tie bolt, 4 ... Compressor impeller, 5 ... Bearing collar, 6 ... Rotor shaft, 7 ... Generator, 7a ... Cover, 7b ... Permanent magnet, 7c ... Generator core, 7d ... Generator rear end ring, 8 ... Rotor end, 9 ... Bearing collar, 10 ... Nut, 11 ... Micro gas turbine power generator, 12 ... Turbine outer case, 12a ... Turbine outer casing member, 12b ... Turbine outer casing member, DESCRIPTION OF SYMBOLS 13 ... Transition piece, 13a ... Suction part, 13b ... Tubular part, 13c ... Discharge port part, 13d ... Fixed flange, 13e ... Gourd-shaped hole, 13f ... Large diameter hole, 13g ... Small diameter hole, 13h, 13j ... Cooling hole, 13j ... front discharge flange, 13k ... rear discharge flange, 13m ... cylindrical socket, 14 ... nozzle, 14a ... front nozzle of nozzle Lung, 14b ... rear flange of nozzle, 15 ... spacer (partitioning means), 16 ... bolt and nut, 17 ... compressor casing, 17a ... strut, 17b ... generator rear end casing, 18 ... compressor rear end casing, 19 ... Generator casing, 19a ... Generator coil, 19b ... Generator coil outer casing, 20 ... Generator front casing, 21 ... Generator front end casing, 22a ... Through bolt, 22b ... Bolt hole, 22c ... Nut, 23a ... Radial Bearing, 23b ... Thrust bearing, 23c ... Thrust bearing, 23d ... Radial bearing, 24 ... Turbine support, 30 ... Stepped screw, 30a ... Large diameter part, 30b ... Small diameter part, 31, 31a, 31b ... Flow sleeve.

Claims (9)

In a micro gas turbine power generator in which a rotor having a turbine impeller and a compressor impeller is connected to a generator rotor,
A transition piece that forms a flow path for guiding combustion gas to the turbine impeller;
A turbine casing forming a flow path outside the transition piece;
A compressor casing forming a flow path for guiding discharge air from the compressor impeller;
Partition means located between the turbine casing and the compressor casing; and
The transition piece is detachably attached to the partitioning means, and the flow path formed inside and outside the transition piece is sealed,
When a plurality of holes having different sizes of a large-diameter hole and a small-diameter hole are provided at a plurality of locations on the inner peripheral side of the transition piece, and the transition piece is attached to and detached from the partition means, the transition piece A micro gas turbine power generator, wherein a piece is rotated from the large diameter portion side to the small diameter portion side of the hole connecting the two holes or in the opposite direction.   The micro gas turbine power generator according to claim 1, wherein the compressor impeller is a centrifugal type. The micro sleeve according to claim 1, wherein a flow sleeve that divides the turbine casing and the transition piece in a radial direction is provided, and the flow sleeve increases a flow velocity of a flow path formed outside the transition piece. Gas turbine power generator.   The micro gas turbine power generator according to claim 3, wherein the flow sleeve includes a plurality of members and can be disassembled in an axial direction.   2. The micro gas turbine power generator according to claim 1, wherein a different diameter screw is attached to the partitioning means, and the different diameter screw is attached to a hole connecting the two holes to prevent thermal deformation. The combustion gas burned in the combustor is guided to the turbine impeller to drive the compressor impeller disposed coaxially with the turbine impeller, and the generated compressed air is supplied to the combustor and connected to the rotating shaft of the turbine impeller In the micro gas turbine power generator that generates power with the generated generator,
A transition piece, in which a combustion gas passage for supplying to the turbine impeller is formed inside and a passage for supplying compressed gas to the combustor is formed outside, is detachably attached to a stationary member of the micro gas turbine. , Seal the flow path formed inside and outside the transition piece by mounting,
When a plurality of holes having different sizes of a large-diameter hole and a small-diameter hole are provided at a plurality of locations on the inner peripheral side of the transition piece, and the transition piece is attached to and detached from the partition means, the transition piece A micro gas turbine power generator, wherein a piece is rotated from the large diameter portion side to the small diameter portion side of the hole connecting the two holes or in the opposite direction. Used in a micro gas turbine power generator having a turbine, a compressor, and a combustor, a suction port for sucking combustion gas from the combustor, a tubular portion for supplying combustion gas to the entire circumferential direction of the turbine impeller, and A discharge port portion for introducing combustion gas to a nozzle disposed upstream of the turbine impeller,
A transition piece in which two holes having different sizes of a large-diameter hole and a small-diameter hole are formed at intervals in a plurality of locations in the circumferential direction of the discharge port portion.   The transition piece according to claim 7, wherein the suction port includes a detachable cylindrical socket.   The transition piece according to claim 8, wherein the transition piece is rotated around a rotation axis of a gas turbine rotor and can be fixed to a stationary member of the gas turbine.

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