JP2002147250A - Gas turbine power generating apparatus with integrated rotating portion - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine power generating apparatus with integrated rotating portion, having reduced number of parts and reducing vibrations caused by improper correction of balance at a time of assembly. SOLUTION: The gas turbine engine 2 has a compressor 4, a burner 6, and a turbine 5. A turbine rotor 17 is joined on a back face of a metal impeller 11 of the compressor 4 to form the integral rotating portion 21. The gas turbine power generating apparatus 1 has the gas turbine engine 2 and the generator 3 driven by the gas turbine engine. The rotating portion 21 of the gas turbine engine 2 is fixed at an end portion of a magneto rotor 61 to which a magnet 66 of the generator 3 is attached. The magneto rotor 61 is rotatably supported by bearings 71, 72 disposed at one end portion and the other end portion of the magneto rotor, respectively.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine power generator in which a generator is directly connected to a gas turbine engine.

[0002]

2. Description of the Related Art In a conventional gas turbine power generator of this type, an impeller of a compressor and a turbine rotor are formed as an integral rotating part. However, a turbine rotor is integrated with one end of a rotating shaft integrated with the generator rotor. And the rotation shaft is fitted into a shaft hole formed in the impeller with a spline or the like, and the impeller is fastened to the turbine rotor side with a fastener such as a bolt.

[0003]

However, in such a configuration, the number of parts increases. Further, when assembling the gas turbine engine, first, a rotating part is assembled to the generator rotor, the balance is corrected, and then the rotating part is disassembled and assembled to the engine. For this reason, when the rotating part is assembled again in the engine, it deviates from the assembly position at the time of the balance correction, causing vibration.

The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a rotating part integrated gas turbine power generation apparatus which has a small number of parts, can maintain a balance corrected state, and can reduce vibration. .

[0005]

In order to achieve the above object, a gas turbine power generator according to the present invention comprises: a gas turbine engine having a compressor, a combustor and a turbine;
And a generator driven by this.
A rotating part of a gas turbine engine is fixed to one end of a generator rotor to which a magnet of the generator is attached, and the rotating part is formed by joining a turbine rotor of the turbine to a back surface of a metal impeller of the compressor. Become. Here, the term “fixed” refers to a state in which they are inseparably or separably coupled, and the term “joining” refers to a state in which they are inseparably coupled.

[0006] According to the gas turbine power generator integrated with the rotating part, the number of parts is reduced because the rotating part, which is joined to the generator rotor and includes the impeller and the turbine rotor of the compressor, is not disassembled. I do. In addition, since the rotating portion is not disassembled, the balance correction state performed before the assembly is maintained even at the time of assembling to the engine. Therefore, it is possible to prevent the balance from shifting and causing vibration.

In a preferred embodiment of the present invention, a seal member is provided between the impeller and the turbine rotor for sealing between the impeller and the turbine rotor, and the seal member comprises a plurality of radially separable divided bodies. .

With this configuration, the impeller side and the turbine rotor side of the compressor are sealed by a seal member, and the seal member is separated in a radial direction, so that the seal member can be separated from its rotating part when the engine is disassembled. Can be easily removed.

In a preferred embodiment of the present invention, the generator rotor is rotatably supported by a generator case by air bearings provided at the one end and the other end.
The air bearing at the other end of the generator rotor is preferably constituted by a radial air bearing and a thrust air bearing.

According to the gas turbine power generator, since the air bearing which is not mechanically connected to the generator rotor is used, the gas turbine generator is disassembled, and the rotating part of the gas turbine and the generator rotor are kept integral with each other. It can be withdrawn from the turbine engine side in the axial direction, which facilitates disassembly and assembly.
Further, since the rotating part of the gas turbine engine is fixed to the generator rotor supported by bearings, it is not necessary to separately support the rotating part by bearings, so that the structure is simplified and the mechanical loss is reduced. Is reduced. Further, since the other end of the generator rotor is on the opposite side to the gas turbine side, there is room in space, so that a radial air bearing and a thrust air bearing can be arranged without difficulty at this other end.

In a preferred embodiment of the present invention, the generator rotor further includes a pipe and the magnet inserted inside the pipe, and one end of the pipe includes a front end of the rotating section. The part is inserted and fixed.

With this configuration, the magnet can be protected by the pipe, and integration with the rotating part of the gas turbine engine becomes easy.

[0013]

Preferred embodiments of the present invention will be described below in detail with reference to the drawings. FIG. 1 is a longitudinal sectional view of a gas turbine power generator according to one embodiment of the present invention. The gas turbine power generator 1 includes a gas turbine engine 2 with a heat exchanger and a generator 3 driven by the gas turbine engine 2.

The gas turbine engine 2 has a centrifugal compressor 4, a turbine 5, and an annular combustor 6 located radially outward of the turbine 5. A turbine rotor 17 made of ceramic is joined to the back of the metal impeller 11 of the compressor 4. The compressor 4 compresses the air IA introduced from the intake passage 7 and supplies the compressed air A to the combustor 6 via the heat exchanger 8 connected to the exhaust gas outlet at the rear of the gas turbine engine 2. And driven by the turbine 5. The compressor 4 includes a metal impeller 11 and a shroud 12 formed at a position at the rear end of the intake housing 9 that forms the intake passage 7 so as to cover the impeller 11. A diffuser 13 for increasing the static pressure of the compressed air A is disposed radially outside the compressor 4 on the outlet side. The diffuser 13 has a large number of wings 13b on the front of an annular wall member 13a.
Is fixed.

The diffuser 13 is disposed at a position sandwiched between the rear end of the intake housing 9 and the combustor 6, and is connected to the diffuser 13 and the diffuser 13 of the combustor 6 from the rear end of the intake housing 9. A plurality of knock pins 15 and bolts 16 penetrating in the axial direction of the turbine engine 2 astride the opposing end portions, thereby forming the combustor 6.
At the same time, it is positioned at the rear end of the intake housing 9 and is detachably attached.

The turbine 5 includes a turbine rotor 17 made of ceramic and a turbine nozzle 18 which is an inlet-side member of the turbine rotor 17. The joining of the ceramic turbine rotor 17 to the back surface of the metal impeller 11 is performed, for example, as shown in FIG.
A fitting member 19 made of a metal having a coefficient of thermal expansion lower than 1 is welded to the back surface of the impeller 11 and
Is performed by shrink-fitting the front end shaft portion 20a of the turbine hub 20 of the turbine rotor 17 into the concave portion 19a. At the time of shrink fitting, it is preferable to interpose a brazing filler metal between the recess 19a and the end face and the outer peripheral face of the front end shaft portion 20a.

The impeller 11 thus joined and the turbine rotor 17 directly joined to the impeller 11 without passing through a rotating shaft.
Thus, the rotating part 21 of the gas turbine engine 2 is integrally formed. By joining the ceramic turbine rotor 17 to the back surface of the metal impeller 11 via the fitting member 19 in this manner, the difference in thermal expansion between the metal impeller 11 and the ceramic turbine rotor 17 is reduced.

The turbine nozzle 18 includes a nozzle body 1
8a, a turbine shroud 18b for covering the outer diameter side of the turbine blade 22 of the turbine rotor 17 and a mounting portion 18c extending to the outer diameter side are integrally formed of ceramic, and the mounting portion 18c is shown in FIG. It is detachably attached to the intake housing 9 by being sandwiched between the diffuser 13 fixed to the rear end of the intake housing 9 by bolts 16 and the combustor 6. A wave ring 24, which is an elastic member, is inserted between the mounting portion 18c (FIG. 2) of the turbine nozzle 18 and the front end of the combustor 6 pressed against the mounting portion 18c.

The combustor 6 has a fuel nozzle 32 for injecting a gas or liquid fuel F into a combustion chamber 31 in the combustor 6, and the fuel F is sent into the combustion chamber 31 via the heat exchanger 8. It mixes with the supplied compressed air A and burns. The high-temperature and high-pressure combustion gas G is sent from the turbine nozzle 18 to the turbine 5, and the energy of the combustion gas G drives the turbine 5. The combustor 6 is annular, and is arranged concentrically with the rotation axis C1 of the turbine 5. The inner end of the combustor 6 is fitted to the rear end of the turbine shroud 18b of the turbine nozzle 18 shown in FIG. 2 via an annular seal member 23, whereby the turbine shroud 18b and the combustor 6 Is sealed. The turbine shroud 18b forms a part of the wall of the combustor 6.

A seal member 33 is provided between the impeller 11 and the turbine rotor 17 to seal between the two. The seal member 33 forms a labyrinth seal with a plurality of annular projections formed on the outer periphery of the fitting member 19, and is circumferentially separated so as to be radially separable as shown in FIG. A plurality of divided bodies, for example, two divided bodies 3
3a and 33b, and their outer diameter ends 33c are fixed to the wall member 1 of the diffuser 13 by bolts 34 as shown in FIG.
By being fixedly fastened to 3a, it is indirectly detachably attached to the intake housing 9 via the diffuser 13.

The heat exchanger 8 shown in FIG. 1 exchanges heat between the high temperature exhaust gas E exiting the turbine 5 of the gas turbine engine 2 and the low temperature compressed air A exiting the compressor 4 of the gas turbine engine 2. The main housing 35, which has a circular cross section and accommodates the compressor 4, the combustor 6, and the turbine 5, is attached to the rear end of the main housing 35. In the heat exchanger 8, the front end flange 38 of the heat exchanger housing 37 is connected to the rear end flange 3 of the main housing 35.
9 is connected to the main housing 35 by being fastened with bolts and nuts (not shown). The heat exchanger housing 37 has a heat exchanger housing 37 having a circular cross section as shown in FIG. The core 36 is housed.
The heat exchange core 36 may have a rectangular cross section. Further, in this embodiment, the core 36 includes the first passage 41 through which the low-temperature compressed air A as the first fluid flows, and the second passage 41.
A plurality of flat heat transfer plates 43 that partition the second passage 42 through which the high-temperature exhaust gas E as the fluid flows, are arranged in parallel at predetermined intervals.

As shown in FIG. 5, an inflow port 44 for allowing the compressed air A to flow into the first passage 41 is provided on a rear side surface of the core 36, and a first side surface of the core 36 is provided with a first side surface. An outlet 45 for the compressed air A passing through the passage 41 is provided.

As shown in FIG. 1, between the core 36 and the heat exchanger housing 37, compressed air A passes from the front of the core 36 to the side of the core 36, that is, to the outside of the side surface. An introduction passage 46 is formed to be introduced into the inflow port 44. A compressed air passage 47 is formed between the main housing 35 in front of the heat exchanger 8 and the annular combustor 6 to guide the compressed air A exiting the compressor 4 to the introduction passage 46.
The compressed air passage 47 is formed by a space formed between the main housing 35 and a cylindrical member 48 formed concentrically with the main housing 35 inside the main housing 35. The rear end of the intake housing 9 is fastened and fixed to the front end (left end in FIG. 1) of the main housing 35 with a bolt 49. The front end of the cylindrical member 48 extends from the wall member 13a of the diffuser 13 to the outer front end of the combustor 6,
An annular seal member 50 is interposed between the front end of the cylindrical member 48 and the front end on the outer diameter side of the combustor 6 so as to be able to be pulled out in the axial direction of the gas turbine engine 2.

Further, on the front side of the heat exchanger 8, on the inner peripheral side of the compressed air passage 47, the compressed air A from the outlet 45 of the heat exchanger 8 is guided to the combustor 6 of the gas turbine engine 2. An outlet path 51 for the container is formed. The lead-out passage 51 is formed in a space between the cylindrical member 48 and a conical member 52 extending forward from the front end of the core 36 and disposed concentrically with the cylindrical member 48 inside the cylindrical member 48. 6 and the space between the cylindrical member 48 and the front end of the conical member 52 from the turbine shroud 18b.
(FIG. 2) is formed by the space between the substantially cylindrical exhaust diffuser 53 extending to the rear end and the combustor 6. The front end of the exhaust diffuser 53 is welded to the inside of the front end on the inner diameter side of the combustor 6. An inner space surrounded by the conical member 52 and the exhaust diffuser 53 forms an exhaust gas inflow passage 54 through which the exhaust gas E leaving the turbine 5 flows into the second passage 42 of the core 36. An exhaust port 55 for exhausting the exhaust gas E passing through the second passage 42 to the outside is formed on the rear surface of the heat exchanger 8.

The generator 3 has a generator rotor 61 connected to the rotating part 21 of the gas turbine engine 2 and a generator stator 62 disposed around the generator rotor 61. Arranged concentrically with the housing 9,
It is housed in a generator case 64 having a circular cross section supported by the intake housing 9 via struts 63. The space formed between the intake housing 9 and the generator case 64 constitutes the intake passage 7. At the front end of the intake housing 9, air I
An intake duct 85 for introducing A is connected. With such an arrangement of the generator 3, the air IA passing through the intake passage 7
The cooling of the generator 3 is performed by the above, so that a special cooling device for the generator is not required. The generator stator 62 is wound around an inner peripheral side of a generator case 64, which is disposed concentrically with the case 64 and fixed to a ring-shaped core 67, and each pole portion projecting from the core 67 to the inner diameter side. And a turned coil 68.

The generator rotor 61 is formed by press-fitting a magnet 66 inside a cylindrical pipe 65, and a rotating end 21 of the gas turbine engine 2 is provided at one end serving as a rear end.
Has been fixed. That is, inside the one end of the pipe 65 of the generator rotor 61, as shown in an enlarged view in FIG. 2, the cylindrical rotary shaft portion 14 at the front end of the impeller 11 is inserted in a press-fit state. One end surface of the pipe 65 is butted against the step portion 40 of the impeller 11, and the butted portion is welded as necessary, so that the rotating portion 21 is firmly fixed to the generator rotor 61. Thus, by inserting the front end of the rotating part 21 into one end of the pipe 65, the generator rotor 61 and the rotating part 21 can be easily integrated. Further, by inserting the magnet 66 into the pipe 65, the magnet 66 is protected. The rotation unit 21 is fixed to the generator rotor 61 by, for example, the pipe 6
Alternatively, the rotation shaft 14 of the impeller 11 of the rotation unit 21 may be screwed into the rotation unit 5.

The generator rotor 61 thus configured
Are bearings 71, 7 provided at one end and the other end shown in FIG.
1 and 72, the generator case 64, that is, the intake housing 9 rotatably supports the generator case 64. That is, one end (rear end) of the generator rotor 61 is connected to a radial bearing 71 held by a rear holding member 73 supported by a strut 83 extending from the intake housing 9 to the inner diameter side. The other end (front end) of 61 is another radial bearing 7 held by a front holding member 74 supported by struts 84 provided in the intake duct 85.
1 and a thrust bearing 72 sandwiched between fixed disks 76 via a bearing surface at the front end of the front holding member 74, and are rotatably supported by the generator case 64, respectively. Each of the bearings 71, 71, 72 is constituted by an air bearing. In this embodiment, the bearing is a self-floating type dynamic pressure air bearing. A static pressure air bearing that introduces and floats may be used.

As shown in an enlarged view in FIG. 4, a tip member 78 having a male screw 77 projecting forward is press-fitted to the other end of the pipe 65 of the generator rotor 61. Have been welded. A rotating disk 75 for generating dynamic pressure is fitted to the front and rear surfaces of the male screw portion 77, and is fastened and fixed to the distal end member 78 by a nut 79 screwed to the male screw portion 77. The proximal end of the male screw portion 77 is a tapered portion, and the rotary disk 75 can be mounted on the distal end member 78 so as to be concentric with the generator rotor 61 by the guide of the tapered portion.

A fixed disk 76 is disposed on the front side of the rotating disk 75, and a collar 80 is interposed between the fixed disk 76 and the front holding member 74. Penetrating bolt 81
As a result, the fixed disk 76 is fastened and fixed to the front holding member 74. Due to the interposition of the collar 80, the distance between the bearing surface at the front end of the front holding member 74 and the fixed disk 76 is kept constant, whereby the rotating disk 75 is set rotatable between the two 74, 76, Thrust bearing 7
2 are formed.

As described above, since both ends of the generator rotor 61 are rotatably supported in the generator case 64 by the radial bearing 71 and the thrust bearing 72, the generator rotor 61 can be smoothly rotated. Can be.

The rotating module 82 having the rotating part 21 of the gas turbine engine 2 fixed to one end of the generator rotor 61 shown in FIG. 1 rotates the rotating disk 75 when the intake housing 9 is removed from the main housing 35. Can be removed from the intake housing 9 rearward in the axial direction.

In the above configuration, heat exchange is performed between the compressed air A exiting the compressor 4 of the gas turbine engine 2 and the exhaust gas E exiting the turbine 5 by the heat exchanger 8 of FIG. Compressed air A is supplied to the gas turbine engine 2
, The heat efficiency of the gas turbine engine 2 is improved. The generator 3 is driven by the turbine 5 of the gas turbine engine 2.

In particular, in the gas turbine engine 2, since the ceramic rotor 17 of the turbine 5 is joined to the back of the metal impeller 11 of the compressor 4 to form an integral rotating part 21, the number of parts is reduced. . Also, the rotating unit 2
1 is not disassembled, and once the balance of the rotating part 21 is corrected, the balance corrected state is maintained even after the rotating module 82 including the rotating part 21 is assembled to the engine. To avoid causing vibration.

A gas turbine engine 2 is attached to one end of a generator rotor 61 to which a magnet 66 of the generator 3 is attached.
Is fixed, and the generator rotor 61 is rotatably supported by the generator case 64 by bearings 71 and 72 provided at one end and the other end thereof.
Need not be separately supported by bearings, and the structure is simplified. Moreover, since the bearings 71 and 72 are air bearings and are not mechanically connected to the generator rotor 61, when the gas turbine power generator 1 is disassembled, if the rotating disk 75 is removed, the rotating part 21 of the gas turbine engine 2 and the power generator 21 generate power. With the machine rotor 61 and the integral rotary module 82, the gas turbine engine 2 can be pulled out from the gas turbine engine 2 side (rear side) in the axial direction, which facilitates disassembly and assembly.

The removal of the rotating module 82 can be performed by the procedure shown in FIGS. That is, as shown in FIG. 6, first, the fuel nozzle 32 is connected to the main housing 3.
After being removed from the housing 5, the intake housing 9 is released from the main housing 35 by removing the fastening of the intake housing 9 to the main housing 35 by the bolt 49. By this removal, on the intake housing 9 side,
The combustor 6, the rotary module 82, and the generator stator 62 remain attached, and the heat exchanger 8 remains on the main housing 35 side.

Next, as shown in FIG.
The combustor 6 is removed from the intake housing 9 by loosening the bolt 16 of the combustor 6 to release the fastening of the combustor 6 and pulling the combustor 6 rearward in the axial direction. As a result, the turbine nozzle 18 previously sandwiched between the diffuser 13 and the combustor 6 can also be removed rearward.

Next, the nut 79 is unfastened from the external thread 77 at the other end of the generator rotor 61 shown in FIG.
5 and the turbine nozzle 18 as shown in FIG.
After removing the diffuser 13 with the bolt 34
The seal member 33 is released from being tightened. Seal member 33 located between impeller 11 and turbine rotor 17
Is composed of a plurality of divided bodies 33a and 33b that can be separated in the radial direction, and is separated from the rotary module 82 by pulling out each of the divided bodies 33a and 33b in the radial direction. In this state, the rotating module is pulled out rearward in the axial direction.

In the present invention, the turbine rotor 17
Is not limited to ceramic, but may be metal. In the case of metal, the metal turbine rotor 17 is directly joined to the metal impeller 11.

[0039]

As described above, according to the gas turbine power generator of the present invention, since the ceramic rotor of the turbine is joined to the back of the metal impeller of the compressor to form an integral rotating part, The number of parts decreases. In addition, since the rotating portion is not disassembled, the balance correction state performed before the assembly is maintained even at the time of assembling to the engine. Therefore, it is possible to prevent the balance from shifting and causing vibration.

[Brief description of the drawings]

FIG. 1 is a longitudinal sectional view of a gas turbine power generator according to an embodiment of the present invention.

FIG. 2 is an enlarged vertical sectional view showing a turbine portion of the gas turbine power generator.

FIG. 3 is an exploded rear view showing a seal member of the gas turbine power generator.

FIG. 4 is an enlarged vertical sectional view showing a front portion of a generator of the gas turbine power generation device.

FIG. 5 is a perspective view showing a core of a heat exchanger in the gas turbine power generator.

FIG. 6 is an exploded vertical sectional view showing removal of an intake housing from a main housing in the gas turbine power generator.

FIG. 7 is an exploded longitudinal sectional view showing removal of a combustor from an intake housing in the gas turbine power generator.

FIG. 8 is an exploded vertical sectional view showing extraction of a rotary module in the gas turbine power generator.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Gas turbine generator, 2 ... Gas turbine engine, 3 ... Generator, 4 ... Compressor, 5 ... Turbine, 6 ... Combustor, 8 ... Heat exchanger, 9 ... Intake housing, 11 ... Impeller, 17 ... Turbine Rotor, 21 rotating part, 33 seal member, 35 main housing, 37 heat exchanger housing, 61 generator rotor, 64 generator case, 6
5 ... pipe, 66 ... magnet, 71 ... radial bearing (air bearing), 72 ... thrust bearing (air bearing), 82 ... rotating module

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁷ Identification symbol FI Theme coat ゛ (Reference) F02C 7/28 F02C 7/28 D H02K 7/08 H02K 7/08 A 7/18 7/18 Z F term (Reference) 5H607 AA04 AA12 AA14 BB02 BB14 CC01 CC05 DD16 DD19 FF30 GG01 GG02 GG09 GG14

Claims (5)

[Claims] 1. A gas turbine power generator comprising a gas turbine engine having a compressor, a combustor, and a turbine, and a generator driven by the gas turbine engine, wherein a generator rotor to which a magnet of the generator is attached A rotating portion of a gas turbine engine is fixed to one end of the gas turbine engine, and the rotating portion is configured by joining a turbine rotor of the turbine to a back surface of a metal impeller of the compressor. 2. The device according to claim 1, further comprising: a seal member provided between the impeller and the turbine rotor for sealing between the impeller and the turbine rotor. A gas turbine power generator with a body shape. 3. The gas turbine power generator according to claim 1, wherein the generator rotor is rotatably supported by a generator case by air bearings provided at the one end and the other end. 4. The gas turbine power generator according to claim 3, wherein a radial air bearing and a thrust air bearing are provided at the other end of the generator rotor. 5. The generator rotor according to claim 1, wherein the generator rotor has a pipe and the magnet inserted inside the pipe, and one end of the pipe has a front end of the rotating part. A gas turbine power generator in which a part is inserted and fixed.