JP2003120213A - Gas turbine device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine device capable of increasing the load capacity of thrust air bearings for supporting a rotary shaft. SOLUTION: This gas turbine device is provided with a gas turbine engine 1, a driven equipment having a gas turbine engine and a rotary shaft 53 for common use, and thrust air bearings 69A and 69B for supporting the rotary shaft 53 axially. The gas turbine engine 1 is provided with a compressor 4, combustor 6 and a turbine 5. The thrust air bearings 69A and 69B have a rotary disk 73, which is uniform in thickness and fixed to the rotary shaft 53, and foil elements 75 and 76, which intervene between the external peripheral section of the main face of the rotary disk 73 and a stationary section 74, which opposed to the external peripheral section. Mounting holes 82 are formed at a plurality positions separated from shaft center 1 in the rotary shaft 73, and the rotary shaft 73 is mounted on one end face of the rotary shaft 53 by mounting members 83 which are inserted into these mount ting holes 82.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine device for driving a driven machine such as a generator by a gas turbine engine, which has an improved thrust bearing.

[0002]

2. Description of the Related Art The applicant of the present invention has previously proposed, as a compact power generation gas turbine device, a heat exchanger at the rear end of a gas turbine engine equipped with a compressor, a combustor and a turbine.
We proposed a power unit in which a direct-coupled generator was connected inline at the front end (Japanese Patent Application No. 2000-3431).
No. 23). In this gas turbine device, a turbine rotor of a gas turbine engine and a compressor impeller are connected to a rotor of a generator having a magnet, and use this rotor as a common rotating shaft. The rotor has two front and rear journal air bearings. It is rotatably supported by one thrust air bearing.

The thrust air bearing is constructed by interposing a foil element between a rotary disk fixed to the front end of the rotor and a stationary portion which is arranged to face the rotary disk in the axial direction of the generator. . The rotating disk has a fitting hole at the center and a boss portion that projects in the axial direction from the main surface of the rotating disk, and after press-fitting the fitting hole into the small diameter shaft portion of the rotor front end, A rotating disk is fastened and fixed to the front end of the rotor by a nut screwed to the small diameter shaft portion.

[0004]

However, in the shape of the rotating disk of the thrust air bearing and the rotating disk mounting structure, when the rotor rotates at a high speed, the rotating disk is warped in the axial direction due to the centrifugal force generated in the rotating disk. ,
Since the flatness of the rotating disc may be distorted, high stress may be applied to the fitting hole at the center of the rotating disc, and the diameter of the fitting hole may be widened to reduce the press-fitting tightness. The capacity decreases. Further, since the rotating disk has the boss portion protruding from the main surface thereof, it is difficult to perform mirror finishing on the main surface of the rotating disk that comes into contact with the foil element, and from this point also, the load capacity of the thrust air bearing is reduced. Will be reduced.

The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a gas turbine device capable of increasing the load capacity of a thrust air bearing for supporting a rotating shaft.

[0006]

In order to achieve the above object, a gas turbine apparatus according to the present invention is a gas turbine engine equipped with a compressor, a combustor and a turbine, and has a rotating shaft shared with the gas turbine engine. A driven machine driven by a gas turbine engine, and a thrust air bearing that axially supports the rotating shaft, and the thrust air bearing includes a rotating disk having a uniform thickness fixed to the rotating shaft. A rotary element having a foil element interposed between an outer peripheral portion of a main surface of the rotating disc and a stationary portion facing the outer peripheral portion, and mounting holes are formed at a plurality of positions apart from an axis of the rotating disc, The rotating disk is attached to one end surface of the rotating shaft by an attaching member inserted through the attaching hole.

According to the above-mentioned gas turbine apparatus, since the rotating disk has a uniform thickness, that is, since it does not have the conventional boss, it is possible to eliminate the flatness deviation of the rotating disk due to the axial warpage due to the centrifugal force. Therefore, the load capacity of the thrust air bearing can be increased. In addition, since a central hole to which a large centrifugal force is applied is not required for mounting the rotating disc, high stress does not occur in the rotating disc, and thus the outer diameter of the rotating disc can be increased correspondingly. The load capacity can be increased. further,
Since the rotation disc is not attached to the end surface of the rotation shaft by press fitting, the rotation disc can be easily attached and detached. Further, since the rotating disk has a uniform thickness without a boss in the center, mirror surface finishing of the rotating disk is facilitated, and from this point as well, the load capacity of the thrust air bearing can be increased.

In a preferred embodiment of the present invention, the mounting member is a reamer bolt screwed onto the rotary shaft.

With this structure, the mounting position of the rotary disk on the rotary shaft becomes accurate, and the mounting strength can be sufficiently secured.

In a preferred embodiment of the present invention, the main surface of the rotary disk on the side in contact with one end surface of the rotary shaft,
That is, an annular groove is formed on the rear surface at a position radially outward of the rotary shaft to suppress deformation of the rotary disk due to a frictional drag force with one end surface of the rotary shaft.

Due to the elongation due to the centrifugal force, a frictional force in the radial direction is generated between the rotary disc and the front end face of the rotary shaft, and the outer peripheral portion of the rotary disc is deformed so as to warp rearward. Cheap. On the other hand, in this embodiment, since the annular groove is formed on the rear surface of the rotating disk, the outer peripheral portion of the rotating disk tends to warp forward due to the centrifugal force, so the warping deformation is canceled. It
As a result, it is possible to suppress deformation of the rotating disk due to the influence of a large centrifugal force generated on the rotating disk at high speed rotation, and also in this respect, the load capacity of the thrust air bearing can be increased.

[0012]

Preferred embodiments of the present invention will be described in detail below with reference to the drawings. FIG. 1 shows a cross-sectional view of a gas turbine device which is an embodiment of the present invention. This gas turbine device includes a gas turbine engine 1 and an enclosure 2 that houses the gas turbine engine 1, a generator 3, a power converter 13, and the like.

The gas turbine engine 1 has a centrifugal compressor 4, a turbine 5, and an annular combustor 6 located radially outward of the turbine 5, as shown in a longitudinal sectional view in FIG.
And a rear heat exchanger 7 and an exhaust unit 8 (FIG. 1). The heat exchanger 7 exchanges heat between the compressed air A from the compressor 4 and the exhaust gas E from the turbine 5. A generator 3 which is a kind of driven machine driven by the gas turbine engine 1 is connected to the front surface of the compressor 4 in the front part of the gas turbine engine 1. The gas turbine engine 1 and the power generator 3 constitute a power unit 10.

In FIG. 2, a turbine rotor 22 is joined to the back surface of the impeller 21 of the compressor 4. The compressor 4 compresses the air IA taken in from the air intake 23 separated from the generator 3, and passes the compressed air A through the heat exchanger 7 connected to the exhaust gas outlet side of the rear part of the gas turbine engine 1. It is supplied to the combustor 6 and is driven by the turbine 5. This compressor 4 has an impeller 2
1 and a shroud 24 formed at a position covering the impeller 21. A diffuser 25 for increasing the static pressure of the compressed air A is arranged on the outer side in the radial direction on the outlet side of the compressor 4. The turbine 5 includes a turbine rotor 22 and a turbine nozzle 26 that is an inlet side member of the turbine rotor 22.

The combustor 6 has a fuel nozzle 28 for injecting a gas or liquid fuel F into a combustion chamber 27 in the combustor 6, and the fuel F is sent into the combustion chamber 27 through the heat exchanger 7. It is mixed with the supplied compressed air A and burned. The high-temperature and high-pressure combustion gas G is sent from the turbine nozzle 26 to the turbine 5, and the energy of the combustion gas G drives the turbine 5. The combustor 6 has an annular shape and is arranged concentrically with the rotation axis C1 of the turbine 5.

The heat exchanger 7 exchanges heat between the high temperature exhaust gas E discharged from the turbine 5 of the gas turbine engine 1 and the low temperature compressed air A discharged from the compressor 4 of the gas turbine engine 1. And a main housing 29 having a circular cross section and containing the compressor 4, the combustor 6 and the turbine 5.
A heat exchanger housing 30 is connected to a rear end portion of the heat exchanger housing 30 with a bolt B2.
A heat exchange core 30C having a circular cross section is housed. The core 30C is provided in the first passage 3 through which the compressed air A flows.
6 and a second passage 37 through which the high-temperature exhaust gas E flows, a plurality of flat heat transfer plates 38 are arranged in parallel at predetermined intervals. On the side surface of the rear portion of the core 30C,
Inflow port 39 for allowing compressed air A to flow into the first passage 36.
Is provided. Further, on the side surface of the front portion of the core 30C, an outlet 40 for the compressed air A passing through the first passage 36 is provided.
Is provided.

Between the core 30C and the heat exchanger housing 30, compressed air A is fed from the front of the core 30C to the core 30C.
An introduction path 41 is formed which is introduced into the inflow port 39 through the side of the above, that is, the outside of the side surface. A compressed air passage 42 is formed between the main housing 29 in front of the heat exchanger 7 and the annular combustor 6 to guide the compressed air A discharged from the compressor 4 to the introduction passage 41. The compressed air passage 42 is formed by a space formed between the main housing 29 and a cylindrical member 43 arranged concentrically.
The rear end of the shroud 24 that constitutes the compressor 4 is fastened and fixed to the front end of the main housing 29 by a bolt B1.

Further, on the front surface of the heat exchanger 7, on the inner peripheral side of the compressed air passage 42, the compressed air A from the outlet 40 of the heat exchanger 7 is guided to the combustor 6 of the gas turbine engine 1. A lead-out path 44 for vessels is formed. The lead-out path 44 extends forward from the front end of the cylindrical member 43 and the core 30C, and is arranged inside the cylindrical member 43.
And a trumpet-shaped member 45 arranged concentrically with each other. The front end of the trumpet-shaped member 45 extends to the rear end of the shroud 26 a of the turbine nozzle 26. The space surrounded by the trumpet-shaped member 45 forms an exhaust gas inflow passage 51 that allows the exhaust gas E that has exited the turbine 5 to flow into the second passage 37 of the core 30C. On the rear surface of the heat exchanger 7, an exhaust port 52 for discharging the exhaust gas E passing through the second passage 37 to the exhaust unit 8 is formed.

As shown in FIG. 3, the generator 3 is a rotor 5 which is a rotating shaft connected to a rotating portion (the impeller 21 and the turbine rotor 22 in FIG. 2) of the gas turbine engine 1.
3 and a fixed armature (generator stator) 54 arranged around it. That is, the generator 3 shares the rotating shaft with the gas turbine engine 1. A generator case 55 arranged concentrically with the rotor 53 is a case main body 55A having a circular cross section whose front opening is covered with a front cover 55B. The fixed armature 54 is supported on the inner circumference of the case main body 55A. Has been done. The front cover 55B is a cover body 55B.
1 and the cover portion 55B2 that covers the front surface of the cover body 55B1
The cover body 55B1 is connected to the case body 55A with bolts B3. The rotor 53 is configured by inserting a magnet 57 inside a cylindrical pipe 56, and has rotating portions 21, 2 of the gas turbine engine 1 at its rear end.
2 is fixed. An annular air passage 58 for introducing cooling air is formed between the rotor 53 of the generator 3 and the fixed armature 54.

The rotor 53 thus configured has a pair of front and rear journal air bearings 59 which are axially separated from each other.
It is rotatably supported by the generator case 55 via A and 59B. The fixed armature 54 has a generator case 55.
It is composed of a ring-shaped core 60 arranged and fixed on the inner peripheral side of the case 55 concentrically with the case 55, and a coil 61 wound around a tooth portion (teeth) protruding from the core 60 to the inner diameter side. Inside the fixed armature 54, a plurality of cooling passages 66 for introducing cooling air are formed in the outer diameter side portion of the core 60 so as to penetrate back and forth along the axial direction. Generator case 55
The rear end portion, that is, the rear end portion of the case main body 55A is a rear side wall surface portion (rear wall) 67 that extends toward the inner diameter side and separates the air intake port 23 of the compressor 4 from the generator 3. The front cover 55B forming the front of the generator case 55 is also formed with a front side wall surface portion (front wall) 68 extending inward, and the pair of journal air bearings 59A are formed by the wall surface portions 67 and 68. , 59B are supported.

These journal air bearings 59A, 59
As shown in FIGS. 4 (A) and 4 (B), B has an outer ring 70, and a bump foil element 71 having a corrugated cross section in a gap between the outer ring 70 and the rotating shaft (the rotor 53 in this case). When,
A top foil element 72 made of a flat plate material is arranged, and an outer ring 70 is fixed to the inner diameter portions of the wall surface portions 67 and 68.

The front end of the rotor 53 shown in FIG. 2 is axially supported by the front cover 55B of the generator case 55 via thrust air bearings 69A and 69B. As shown in FIG. 5, each of the thrust air bearings 69A and 69B has a rotating disk 73 having a uniform thickness, that is, a locationally uniform thickness. The rotating disk 73 is opposed to the outer peripheral portion of the main surface of the rotating disk 73. The bump foil element 75 and the top foil element 76 made of a flat plate material are arranged between the stationary portion 74 and the stationary portion 74. Here, the rotating disk 73 is fixed to the front end surface of the rotor 53, which is the rotating shaft of FIG. 3, and the bump of FIG. 5 is provided between the rotating disk 73 and the inner end portion of the front side wall surface portion 68 facing the rotating disk 73. The foil element 75 and the top foil element 76 are arranged as shown in FIG.
The first thrust air bearing 69A is configured.

Further, the bump foil element 75 and the top foil element 76 shown in FIG. 5 are arranged between the rotary disk 73 and the pad disk 81 arranged on the front side of the rotary disk 73 so as to face the front surface of the rotary disk 73. The second thrust air bearing 69B of FIG. 3 is configured. In this case, the inner wall portion front end surface of the front side wall surface portion 68 becomes the stationary portion 74 of the first thrust air bearing 69A, and the pad disk 81 becomes the second portion.
It becomes the stationary portion 74 of the thrust air bearing 69B.

The rotor 5 is attached to the rotary disk 73.
3, mounting holes 82 are formed at a plurality of positions apart from the axis of the rotating disk 73, that is, the rotation axis C1 of the gas turbine engine 1, and the mounting holes 82 also function as knock pins. Reamer bolt 8 which is a member
The rotary disk 73 is attached to the front end surface of the rotor 53 by screwing 3 into a screw hole provided in the front end surface of the rotor 53. On the main surface of the rotating disk 73, which is in contact with the front end surface of the rotor 53, the rotor 5
3, the annular groove 8 that suppresses the deformation of the rotating disk 73 due to the frictional drag force with the front end surface of the rotor 53 at a position radially outward of the rotor 3.
4 are formed.

The pad disk 81 and the front side wall surface portion 68
A spacer 85 is interposed between the pad disk 8 and
The pad disk 81 is fastened and fixed to the generator case 55 by stud bolts 86 penetrating the first and spacers 85. As a result, the rotor 53, the impeller 21 (FIG. 2) connected to the rotor 53, the turbine rotor 22
A predetermined axial preload is applied to (Fig. 2). Three stud bolts 86 are provided at evenly spaced positions in the circumferential direction of the pad disk 81. The spacer 85 adjusts the distance between the front surface of the front side wall surface portion 68 and the rear surface of the pad disk 81.

At the center of the front end of the cover 55B2 of the generator case 55, there is provided an inlet 87 for introducing the cooling air IA from the outside to the front of the generator 3. Further, in the outer diameter portion of the front side wall surface portion 68, a ventilation hole 88 for introducing the cooling air IA introduced from the introduction port 87 to the front portion of the generator 3.
Are formed along the circumferential direction. Further, a rear surface side of an inner diameter portion of the front side wall surface portion 68 is a tapered surface 68a that is narrowed backward, and is fixed from the ventilation hole 88 by a gap between the tapered surface 68a and the front end portion of the coil 61. A part of the cooling air IA introduced into the front portion of the armature 54 is used as an air passage 5 between the fixed armature 54 and the rotor 53.
8, a first supply passage 89 is formed which is inclined toward the inner diameter side toward the rear.

Further, in the inner diameter portion of the front side wall surface portion 68, a part of the cooling air IA introduced into the front portion of the fixed armature 54 from the ventilation hole 88 is connected to the front end of the front journal air bearing 59A and the first end. A plurality of second supply paths 90 are formed at equal intervals in the circumferential direction to supply to the radially inner end of the thrust air bearing 69A. Further, in the central portion of the pad disc 81, a part of the cooling air IA introduced from the inlet 87 is sandwiched between the pad disc 81 and the rotary disc 73, and a radial inner end of the second thrust air bearing 69B. Is provided with an inlet 96. Further, an outlet 97 is provided in the outer peripheral portion of the rear end of the generator case 55 to lead out the air IA after passing through the cooling passage 66 and the air passage 58 to the outside of the generator 3.

The rear end of the journal air bearing 69B supported by the inner diameter portion of the rear side wall surface portion 67 is made to communicate with the narrowed portion of the air intake 23 through which the intake air of the compressor 4 flows, and the air intake The air in the rear journal air bearing 69B is sucked toward the air intake port 23 by the ejector effect of the intake air flowing through the air conditioner 23. Further, in the rear journal air bearing 69B, as shown in FIG. 6, the rear end surface 70a of the outer ring 70 has the inner wall surface 2 of the air inlet 23.
It has a smooth shape along 3a.

The exhaust unit 8 shown in FIG. 1 has a silencer 128, which is oriented vertically and has an upper outlet port, and
Of the heat exchanger 7, the exhaust passage 130 for guiding the exhaust gas E from the exhaust port 52 to the lower part of the silencer 128, and the bypass for guiding the exhaust gas E from the exhaust port 52 to the lower part of the silencer 128 from the middle body part. And a passage 131. The exhaust passage 130 and the bypass passage 13 are provided downstream of the exhaust port 52.
A butterfly valve 132 is provided in a portion where 1 is branched, and the exhaust valve E is switched by the butterfly valve 132 to be supplied to the exhaust passage 130 and the bypass passage 131. A heat exchanger 125 of a boiler is inserted in the middle of the exhaust passage 130, and the feed water supplied from a water supplier (not shown) is heat-exchanged with the exhaust gas E by the heat exchanger 125 to generate hot water. . The heat exchanger 125 is located in the center of the gas turbine engine 1 in the left-right direction, and the silencer 128 is located on the right side (front side in FIG. 1).

Inside the enclosure 2, a partition wall 9 accommodates an air inlet 23 of the compressor 4 and a front first chamber 11 accommodating the generator 3, and at least the combustor 6, the turbine 5, and the heat exchanger 7. And a rear second chamber 12 accommodating the exhaust unit 8. As a result, the air intake 23 of the compressor 4 sucks the air in the first chamber 11 that is lower in temperature than the second chamber 12, and the efficiency and output of the gas turbine engine 11 are improved.

The first chamber 11 is provided with an upper chamber 19 accommodating the air intake port 23 of the compressor 4 and the generator 3, and is arranged below the upper chamber 19 so that air is supplied from the outside of the enclosure 2. Lower chamber 20 having air inlet 98 for introducing
And have. Between the upper chamber 19 and the lower chamber 20,
It is partitioned by the partition plate 9A and communicates with the throttle passage 99. This throttle passage 99 is the enclosure 2
Is a passage that is long in the width direction, and the passage length (vertical length) is set to be substantially equal to or longer than the wavelength of the high frequency noise (intake noise) from the gas turbine engine 1. . Thereby, the high frequency noise leaking from the upper chamber 19 to the lower chamber 20 is reduced. Upper chamber 1
The inner wall surface of 9 is covered with a sound absorbing material 91. In the upper chamber 19, devices such as a display panel, an electronic controller, a breaker, and an exciter (not shown) that generate a small amount of heat are installed.

In the lower chamber 20, the air inlet 98 is provided.
A dust filter 100 facing each other is formed to form a gas-liquid separation chamber 101 having the air inlet 98 and the dust filter 100 at both ends, and a purified air chamber 102 into which air passing through the dust filter 100 is introduced. Has been done. At the bottom of the gas-liquid separation chamber 101, a drain 92 for draining rainwater and the like accumulated on the floor is provided.

Further, in the purified air chamber 102, there is arranged a blower 103 which sucks the air in the purified air chamber 102 and supplies the cooling air to the cooling target portion including the gas turbine engine 1 and the generator 3. There is. This clean air chamber 1
The sound absorbing material 93 is also formed on the inner wall surface of the No. 02 dust filter 100.
It is covered with.

The second chamber 12 is provided with equipment having a large amount of heat generation such as a power converter 13 for frequency-converting the output of the generator 3, a battery 104, a fuel compressor and the like. The power converter 13 has an AC / AC converter for converting high-frequency power (the same frequency as the engine speed) output from the generator 3 into commercial low-frequency power.
The battery 104 is used for starting the power unit 10, for power failure countermeasures, for starter power supply during islanding, for rapid charging due to sudden increase in electric load during sudden braking, and the like.

The enclosure 2 includes a main body 105,
The main body 105 has a front cover 106 provided on a drawer base 107 that is housed so as to be drawn forward (to the left in FIG. 1). The partition wall 9 is provided on the front cover 106, and the partition wall 9 and the front cover 106 form the first chamber 11
Are formed. On the rear floor side in the enclosure body 105, a battery chamber 11 accommodating the battery 104 is provided.
1 is provided separately from the other part in the second chamber 12.

The drawer base 107 is a caster 112 provided at the rear end of the drawer base 107, and the rear end of the drawer base 107 is the enclosure body 105.
Is supported on the guide rail 113 on the floor surface of the enclosure, and the front end of the drawer base 107 is supported by the casters 114 provided on the front surface of the floor of the enclosure body 105, which allows the drawer base 107 to move back and forth. It is said that. The power unit 10 is supported on the drawer base 107 via an installation frame 115, and the power converter 13 and the fuel compressor 109 are directly supported on the drawer base 107.

On the front surface of the installation frame 115, the blower 103 for supplying cooling air to a plurality of cooling target parts including the power unit 10 is attached. That is, the blower 103 is arranged in the lower chamber 20 in the first chamber 11, which is the front part in the enclosure 2. An air reservoir 116 is attached to the lower surface of the installation frame 115 to introduce cooling air from the blower 103 and branch the cooling air into a plurality of objects to be cooled. That is, the air reservoir 116 is in communication with the power converter 13, the battery chamber 111, the inlet 87 of the generator 3, and the servomotor of the fuel compressor 109. Cooling air is the air reservoir 1
16 enters the inside of the power converter 13 through the inlet opening 13a of the power converter 13, and the air after cooling the inside is the outlet openings 13b, 13 at the upper and rear parts of the power converter 13.
It is discharged from c to the second chamber 12 and used for ventilation of the second chamber 12.

The air reservoir 116 and the battery chamber 111 are made to communicate with each other by a flexible hose 117 wound in a spiral shape so that the flexible hose 1 can follow the drawer of the drawer base 107. Has been done. An exhaust port 118 with a louver is provided on the back wall of the enclosure body 105 that also serves as one surface of the battery chamber 111, and the ventilation air introduced from the air reservoir 116 to the battery chamber 111 via the flexible hose 117 is provided. The exhaust port 118
Is discharged from the aircraft.

The flexible hose 1 passing between the air reservoir 116 and the inlet 87 of the generator 3 passes through the throttle passage 99.
Connected by 19. A secondary filter 120 is inserted in the middle of the flexible hose 119. The secondary filter 120 has a function of removing magnetic powder so that the magnetic material does not enter the generator 3. Air reservoir 116
The servo motor of the fuel compressor 109 is also cooled by the air from, and the cooled air is used for ventilation of the second chamber 12.

Further, the outlet port 97 of the generator 3 housed in the upper chamber 19 of the first chamber 11 and the pipe 119 provided in the partition wall 9 for communicating the second chamber 12 and the upper chamber 19 are allowed. The flexible hose 127 communicates with each other, whereby the air IA exiting the outlet 97 of the generator 3 is supplied to the second chamber 12 for ventilation.

The drawer base 107 is the enclosure body 10.
In the state of being housed in the exhaust unit 5, the upper end which is the outlet of the silencer 128 in the exhaust unit 8 is inserted into the exhaust tube 129 provided on the ceiling wall of the enclosure body 105. The exhaust pipe 129 is detachably attached to the ceiling wall of the enclosure body 105 with bolts. When the drawer base 107 is pulled out from the enclosure body 105, the bolts of the exhaust pipe 129 are removed to remove the exhaust pipe 129. The exhaust pipe 129 can be disengaged from the silencer 128 by pulling it upward from the ceiling wall of the enclosure body 105.

Next, the intake / exhaust path in the gas turbine device will be described. In FIG. 1, the lower chamber 20 of the first chamber 11 that is the space at the front of the enclosure 2
The outside air from the air introduction port 98 of the first, the gas-liquid separation chamber 1
No. 01 is introduced into the purified air chamber 102 through the dust filter 100. Rainwater or the like collected on the floor of the gas-liquid separation chamber 101 is discharged outside the machine by the drain 92. Part of the air that has been purified by passing through the dust filter 100 is sucked by the blower 103 of the purified air chamber 102, and is sent to the air reservoir 116 below the drawer table 107.
Further, a part of the air introduced into the purified air chamber 102 is introduced into the upper chamber 19 through the throttle passage 99. Upper chamber 19
The air introduced into the compressor 4 is introduced as intake air IA from the air intake 23 of the compressor 4 and used in the gas turbine engine 1.

The air sent to the air reservoir 116 is further supplied to the cooling target portion including the gas turbine engine 1. That is, a part of the air in the air reservoir 116 passes through the flexible hose 119 and the secondary filter 120, and then the generator 3
Is supplied to the introduction port 87, and the generator 3 is cooled thereby. The air used for air cooling and discharged from the outlet 97 of the generator 3 is further supplied to the second chamber 12 for ventilation via the flexible hose 127. The other part of the air in the air reservoir 116 is supplied to the power converter 13, the servomotor of the fuel compressor 109, and the battery chamber 111 as described above. The air after cooling the power converter 13 and the servomotor is discharged to the second chamber 12 and used for ventilation of the second chamber 12, and the air after ventilating the battery chamber 111 is the rear surface of the enclosure body 105. The air is exhausted from the exhaust port 118 on the wall.

The exhaust gas E of the gas turbine engine 1 is used for heat exchange with the compressed air A (FIG. 2) from the compressor 4 in the heat exchanger 7, and then discharged to the exhaust unit 8. When the heat exchanger 125 of the boiler incorporated in the exhaust unit 8 is used, the butterfly valve 132 is set to the upward switching position shown by the broken line that opens the exhaust passage 130, and the exhaust gas E that has passed through the heat exchanger 125 is exhausted. It is supplied to the lower side of the silencer 128 on the right side (front side of FIG. 1) through the passage 130, and the exhaust pipe 129 is supplied from the upper end of the silencer 128.
Is discharged to the outside of the aircraft. At this time, in the boiler heat exchanger 125 in the middle of the exhaust passage 130, heat exchange is performed between the exhaust gas E and the feed water, and hot water is taken out from the boiler heat exchanger 125. When the boiler heat exchanger 125 is not used, the butterfly valve 132 is set to the downward switching position shown by the chain double-dashed line that opens the bypass passage 131,
The exhaust gas E that has exited the heat exchanger 7 has an upper bypass passage 131.
Through the outer passage of the double pipe in the silencer 128,
It is supplied from here to the lower side of the silencer 128, is silenced through the inner passage of the double pipe in the silencer 128, and is then discharged from the upper end of the silencer 128 through the exhaust pipe 129 to the outside of the machine.

In the generator 3, a part of the cooling air CA introduced from the blower 103 through the flexible hose 119 to the inlet 87 at the center of the front end of the generator case 55 (FIG. 2) is shown in FIG.
It is introduced to the front part inside the generator 3 through the ventilation hole 88 of the front side wall surface part 68 shown in FIG. A part of the cooling air CA introduced into the front portion of the generator 3 through the ventilation holes 88 is part of the fixed armature 5.
4 is introduced into the cooling passage 66 in the No. 4, thereby cooling the fixed armature 54. The other part of the cooling air CA introduced to the front part of the generator 3 is supplied to the first side between the inner tapered surface 68 a of the front side wall surface part 68 and the front end part of the coil 61. It is introduced into the air passage 58 between the rotor 53 and the fixed armature 54 via the passage 89. As a result, the pipe 56 and the magnet 57 of the rotor 53 are cooled.

Further, another part of the cooling air CA introduced into the front portion of the generator 3 passes through the second supply passage 90 formed in the inner diameter portion of the front side wall surface portion 68, and the front journal air bearing. 59A front end and first thrust air bearing 69A
Introduced to the inner diameter end of the front journal air bearing 59A
It passes through the inside toward the rear and also passes through the inside of the first thrust air bearing 69A toward the outside diameter side. This allows
The bearing functions of the front journal air bearing 59A and the first thrust air bearing 69A are maintained and cooled. The air that has passed through the front journal air bearing 59A is introduced into the air passage 58 and used for cooling the rotor 53, and prevents the temperature of the magnet in the rotor 53 from rising and deteriorating the characteristics of the magnet. The cooling air CA that has cooled the first thrust air bearing 59A is again introduced into the front portion inside the generator 3 through the ventilation holes 88 in the front side wall surface portion 68.

Further, another part of the cooling air CA introduced into the inlet 87 at the center of the front end of the generator case 55 passes through the inlet 96 at the center of the pad disk 81 and the inner diameter of the second thrust air bearing 69B. It is introduced at the end and passes through the thrust air bearing 69B toward the outer diameter side. This allows the second
The bearing function of the thrust air bearing 69B is maintained and cooled. The air that has cooled the second thrust air bearing 69B is also introduced into the front portion inside the generator 3 through the ventilation holes 88 in the front side wall surface portion 68.

A part of the cooling air CA passing through the air passage 58 between the rotor 53 and the fixed armature 54 is, together with the cooling air CA passing through the cooling passage 66 of the fixed armature 54, the rear end of the generator 3. From the outlet port 97 in the outer peripheral portion, the electric power is drawn out obliquely to the outside in the radial direction of the generator 3. The derived cooling air CA is supplied to the second chamber 12 at the rear of the enclosure 2 for ventilation via the flexible hose 127 of FIG. 1 connected to the outlet 97.

Another part of the cooling air CA passing through the air passage 58 between the rotor 53 and the fixed armature 54 in FIG.
It is introduced at the front end of the rear journal air bearing 59B and passes rearward in the journal air bearing 59B.
As a result, the bearing function of the rear journal air bearing 59B is maintained and cooled. During operation of the gas turbine engine 1, the air passing through the inside of the journal air bearing 59B is sucked toward the air intake port 23 side by the ejector effect of the intake air IA introduced into the air intake port 23 of the compressor 4. The amount of air passing through the journal air bearing 59B is increased, and the cooling effect of the journal air bearing 59B is improved.

Further, in this gas turbine apparatus, even when the gas turn-bin engine 1 of FIG. 2 is stopped, the cooling air CA is supplied from the blower 103 (FIG. 1) to cool the generator 3 as described above. Is done. In particular,
Since the magnet 57 of the rotor 53 can be cooled by the cooling air CA, it is possible to prevent the temperature of the magnet 57 of the rotor 53 from rising due to heat conduction from the gas turbine engine 1, and the generator can be used as a motor as in the conventional case. It is not necessary to idle the gas turbine engine, and the power consumption of the motor can be saved.

Further, since the cooling passage 66 for introducing the cooling air CA is formed inside the fixed armature 54 of the generator 3, the cooling air CA flowing through the cooling passage 66 cools the fixed armature 54. You can also do it.

Since the generator 3 is connected in front of the compressor 4 of the gas turbine engine 1, the front side of the generator 3 is
Since it is farther from the gas turbine engine 1 than the rear side, the temperature is lower than that of the rear side. However, since the inlet 87 for introducing the cooling air CA is provided in the front portion of the generator 3, the cooling air CA is provided. Flows from the low temperature front side of the generator 3 to the high temperature rear side, thereby improving the cooling efficiency.

Further, the blower 103 shown in FIG. 1 is arranged below the gas turbine engine 1, and since the blower 103 and the generator 3 are connected by the flexible hose 119 through which the cooling air CA passes, the blower 103 is It is difficult to receive the heat of the gas turbine engine 1, and it is possible to avoid the functional deterioration of the blower 103 and the temperature increase of the cooling air CA from the blower 103 due to the heat.

Further, a lead-out port 97 for leading the cooling air CA, which has passed through the air passage 58 and the cooling passage 66, to the outside of the generator 3 is provided on the outer peripheral portion of the generator 3 shown in FIG. Therefore, the air used for cooling is smoothly discharged to the outside of the generator 3, and the cooling effect of the generator 3 is improved.

In this gas turbine device, the rotor 53 of the generator 3 is rotatably supported by a pair of front and rear journal air bearings 59A and 59B which are axially separated from each other, and the rear journal air closer to the compressor 4 is supported. The rear end of the bearing 59B communicates with the air intake port 23 through which the intake air IA of the compressor 4 flows, and the intake air IA of the compressor 4 moves the air in the rear journal air bearing 59B toward the air intake port 23 side. Sucked. Therefore, the flow rate of the cooling air CA flowing in the rear journal air bearing 59B can be sufficiently secured by the ejector effect by the intake air IA of the compressor 4, and the rear side that is easily affected by the heat conduction from the gas turbine engine 1 The journal air bearing 59B can be cooled sufficiently. As a result, when selecting the material of the bump foil element 71 and the top foil element 72 of the journal air bearing 59B, ordinary heat resistant steel such as SUS304 can be used, and the transfer surface side of the top foil element 72, that is, high wear resistance. Since a Teflon (registered trademark) -based baked coating film can be applied to the low-friction material coating to be applied to the portion where is required, cost reduction can be achieved while maintaining high wear resistance.

Further, the rear journal air bearing 59 shown in FIG.
Since the rear end surface 70a of the outer ring 70 of B has a shape along the inner wall surface 23a of the air intake 23 of the compressor 3, the air flow near the rear end surface 70a in the intake passage 23 is not disturbed. Air intake 2 as a result of less smoothness
Rear journal air bearing 59B by intake air IA of 3
The ejector efficiency in which the air inside is sucked toward the air intake port 23 can be improved.

Further, a part of the cooling air CA introduced from the outside to the inside of the generator 3 is supplied to the air passage 58 formed between the rotor 53 and the fixed armature 54 of the generator 3 in FIG. Since the first supply passage 89 is provided, it overcomes the ventilation resistance in the air passage 58 caused by the entrainment of the air layer of the air passage 58 due to the rotation of the rotor 53,
A sufficient flow rate of the cooling air CA can be supplied to the air passage 58, and the cooling efficiency of the rotor 53 can be increased accordingly.

Further, at the front end of the front journal air bearing 59A and the radially inner end of the first thrust air bearing 69A,
Since the second supply path 90 for supplying a part of the cooling air CA introduced from the outside to the inside of the generator 3 is provided,
Sufficient cooling air CA can be supplied also to the front journal air bearing 59A and the first thrust air bearing 69A, and the cooling efficiency of these air bearings 59A and 69A can be improved.

As for the thrust bearing, the thrust air bearings 69A and 69B for supporting the rotor 53 in the axial direction use a rotating disk 73 of a uniform thickness fixed to the rotor 53 and project from the rotating disk 73. Since there is no boss, there is no axial warpage due to centrifugal force. Moreover,
Mounting holes 82 are formed at a plurality of positions apart from the axis of the rotary disk 73, and the rotary disk 73 is mounted on the front end surface of the rotor 53 by mounting members (reamer bolts) 83 inserted through these mounting holes 82. . As a result, the flatness of the rotary disk 73 can be eliminated, and the load capacity of the thrust air bearings 69A and 69B can be increased.

Further, since the central hole to which a large centrifugal force is applied is not required for mounting the rotary disc 73, high stress is not generated in the rotary disc 73, and the outer diameter of the rotary disc 73 can be increased accordingly. Also, the load capacity of the thrust air bearings 69A and 69B can be increased. Further, since the rotating disk 73 is not attached to the end surface of the rotor 53 by press fitting, the rotating disk 73 can be easily attached and detached, and the rotating disk 73 has a uniform thickness without a boss in its center. The mirror finish of the rotary disk 73 is facilitated, and from this point as well, the load capacity of the thrust air bearings 69A, 69B can be increased. Moreover,
Since the reamer bolt 83 is used as a mounting member for mounting the rotating disk 73 on the front end surface of the rotor 53,
Sufficient mounting strength of the rotary disk 73 to the rotor 53 can be secured.

A radial frictional force is generated between the rotating disk 73 and the front end of the rotor 53 due to the elongation due to the centrifugal force, and the outer peripheral portion of the rotating disk 73 is indicated by a chain double-dashed line D in FIG. As shown by, it is easy to deform so as to warp backward. On the other hand, the rotor 53 of the rotating disk 73
Since the annular groove 84 is formed on the main surface on the side contacting the front end surface of the rotor 53 at the position radially outward of the rotor 53, the annular groove 8
Since the portion of the outer periphery of 4 tends to be warped forward, the warping deformation is canceled. as a result,
The load capacity of the thrust air bearings 69A and 69B can be increased.

In addition to the generator 3, the present invention can be applied to a gas turbine device that drives other driven machines such as a pump and a blower.

[0063]

As described above, according to the gas turbine apparatus of the present invention, the gas turbine engine, the driven machine that shares a rotary shaft with the gas turbine engine, and the thrust that axially supports the rotary shaft. An air bearing is provided, and the thrust air bearing is interposed between a rotating disc having a uniform thickness fixed to the rotating shaft, an outer peripheral portion of a main surface of the rotating disc, and a stationary portion facing the outer peripheral portion. A foil element, mounting holes are formed at a plurality of positions apart from the shaft center of the rotating disc, and the rotating disc is attached to one end surface of the rotating shaft by a mounting member inserted into the mounting hole. Therefore, the flatness of the rotating disk can be eliminated, and the load capacity of the thrust air bearing can be increased. In addition, since the central hole to which a large centrifugal force is applied is not required for mounting the rotating disc, high stress does not occur in the rotating disc, and the outer diameter of the rotating disc can be increased accordingly. The load capacity can be increased. Further, since the rotation disc is not attached to the end face of the rotation shaft by press fitting, the rotation disc can be easily attached and detached, and the rotation disc has a uniform thickness without a boss in its center. The mirror surface finish of is easy, and from this point also the load capacity of the thrust air bearing can be increased.

[Brief description of drawings]

FIG. 1 is a right side sectional view of a gas turbine device according to an embodiment of the present invention.

FIG. 2 is a vertical cross-sectional view of a power unit in the gas turbine device.

FIG. 3 is an enlarged vertical sectional view of a generator in the power unit.

FIG. 4A is a transverse cross-sectional view of a journal air bearing used in the generator, and FIG. 4B is an expanded view showing a part of the journal air bearing.

FIG. 5 is an enlarged cross-sectional view along a concentric circle showing a main part of a thrust air bearing used in the generator.

FIG. 6 is an enlarged vertical sectional view showing a rear journal air bearing in the generator.

[Explanation of symbols]

1 ... Gas turbine engine, 3 ... Generator (driven machine),
4 ... Compressor, 5 ... Turbine, 6 ... Combustor, 53 ... Rotor (rotating shaft), 69A, 69B ... Thrust air bearing, 73
... rotating disk, 75 ... bump foil element, 76 ... top foil element, 82 ... mounting hole, 83 ... reamer bolt (mounting member), 84 ... annular groove, C1 ... axial center.

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[Procedure amendment]

[Submission date] November 8, 2001 (2001.11.
8)

[Procedure Amendment 1]

[Document name to be corrected] Drawing

[Name of item to be corrected] Figure 1

[Correction method] Change

[Correction content]

[Figure 1]

─────────────────────────────────────────────────── ─── Continuation of front page (51) Int.Cl. ⁷ Identification code FI theme code (reference) F16C 32/06 F16C 32/06 Z

Claims (3)

[Claims] 1. A gas turbine engine including a compressor, a combustor, and a turbine, a driven machine that shares a rotating shaft with the gas turbine engine and is driven by the gas turbine engine, and the rotating shaft is axially supported. And a thrust air bearing, wherein the thrust air bearing comprises a disc having a uniform thickness fixed to the rotating shaft, and a disc between a peripheral portion of a main surface of the disc and a stationary portion facing the disc. And an intervening foil element, mounting holes are formed at a plurality of positions apart from the axis of the disc, and the disc is attached to one end face of the rotary shaft by a mounting member inserted into the mounting hole. Gas turbine equipment. 2. The gas turbine device according to claim 1, wherein the mounting member is a reamer bolt that is screwed onto the rotary shaft. 3. The frictional force with the one end surface of the rotary shaft at a position radially outward of the rotary shaft on the main surface of the disc that is in contact with the one end surface of the rotary shaft. A gas turbine device in which an annular groove is formed to suppress the deformation of the disk due to.